Fuel steam alcohol of hydrogen peroxide. Conversations about rocket engines. Blow from depth

Summary. As the size of the satellites developed is reduced, it becomes more difficult to pick up for them motor installations (Du), providing the necessary parameters of controllability and maneuverability. Compressed gas is traditionally used on the smallest satellites. To increase efficiency, and at the same time reducing the cost compared with hydrazine removal, hydrogen peroxide is proposed. Minimum toxicity and small required installation dimensions allow multiple tests in convenient laboratory conditions. Achievements are described in the direction of creating low-cost engines and fuel tanks with self-ad.

Introduction

IN last years Investigation of concentrated hydrogen peroxide was revived as rocket fuel for engines of various scales. The peroxide is most attractive when used in new developments, where previous technologies cannot compete directly. Such developments are the satellites weighing 5-50 kg. As one-component fuel, the peroxide has a high density (\u003e 1300 kg / cubic meters) and a specific impulse (UI) in a vacuum of about 150 ° C [approximately 1500 m / s]. Although it is significantly less than the hydrazine Ui, approximately 230 s [about 2300 m / s], alcohol or hydrocarbon in combination with peroxide are capable of lifting UI to the range of 250-300 s [from about 2500 to 3000 m / s].

The price is an important factor here, since it only makes sense to use peroxide if it is cheaper than to build reduced variants of classical DU technologies. Sharpness is very likely to consider that work with poisonous components increases the development, checking and launch of the system. For example, for testing rocket engines On poisonous components there are only a few stands, and their number gradually decreases. In contrast, microsatellite developers can themselves develop their own peroxidant technology. The fuel safety argument is especially important when working with little accelerated systems. It is much easier to make such systems if you can carry out frequent inexpensive tests. In this case, the accidents and spills of the components of rocket fuel should be considered as proper, just as, for example, an emergency to stop a computer program when debugging it. Therefore, when working with poisonous fuels, the standard are working methods that prefer evolutionary, gradual changes. It is possible that the use of less toxic fuels in microsteps will benefit from serious changes in the design.

The work described below is part of a greater research program aimed at studying new space technologies for small applications. Tests are completed by the completed prototypes of microsatellites (1). Similar topics, which are of interest, include small fills with a pumping supply of fuel for flights to Mars, Moon and back with small financial costs. Such possibilities can be very useful for sending small research apparatus to deductible trajectories. The purpose of this article is to create a Du technology that uses hydrogen peroxide and does not require expensive materials or development methods. Efficiency criterion in this case is a significant superiority over the possibilities provided by the remote control on the compressed nitrogen. A neat analysis of microsatellite needs helps to avoid unnecessary system requirements that increase its price.

Requirements for motor technology

If for electronic systems Typically, the characteristics are considered specified, then for Du it is not at all. This concerns the possibility of storing in orbit, sharp inclusions and shutdowns, the ability to withstand arbitrarily long periods of inaction. From the point of view of the engine engineer, the definition of the task includes a schedule showing when and how long each engine should work. This information may be minimal, but in any case it lowers engineering difficulties and cost. For example, the AU can be tested using relatively inexpensive equipment if it does not matter to observe the time of operation of the Du with an accuracy of milliseconds.

Other conditions, usually reducing the system, may be, for example, the need for accurate prediction of thrust and specific impulse. Traditionally, such information made it possible to apply precisely calculated speed correction with a predetermined time of operation of the Du. Given the modern level of sensors and computational capabilities available on board the satellite, it makes sense to integrate acceleration until a specified change in speed is reached. Simplified requirements allow you to reduce individual developments. It is possible to avoid accurate fitting pressure and streams, as well as expensive tests in a vacuum chamber. The thermal conditions of the vacuum, however, still have to take into account.

The easiest Motor Maswer - turn on the engine only once, at an early stage of the satellite. In this case, the initial conditions and time of heating Du affect the least. Fuel leakage deaches before and after the maneuver will not affect the result. Such a simple scenario may be difficult for another reason, for example, due to the large speed gain. If the required acceleration is high, then the size of the engine and its mass become even more important.

The most complex tasks of the work of Du are tens of thousands or more short pulses separated by clock or minutes of inaction over the years. Transition processes at the beginning and end of the pulse, thermal losses in the device, fuel leakage - all this should be minimized or eliminated. This type of thrust is typical for the task of 3-axis stabilization.

The problem of intermediate complexity can be considered periodic inclusions of the Du. Examples are changes orbit, atmospheric loss compensation, or periodic changes in the orientation of the satellite stabilized by rotation. Such a mode of operation is also found in satellites that have inertial flywheels or which are stabilized by the gravitational field. Such flights usually include brief periods of high-activity Du. This is important because the hot components of fuel will lose less energy during such periods of activity. You can use more simple devicesThan for long-term maintenance of orientation, so such flights are good candidates for the use of inexpensive liquid doors.

Requirements for the developed engine

Requirements for the service life also limit the allowable mass and size of the motor installation. For example, in the case of one-component fuel, the addition of the catalyst can increase the service life. The orientation system engine can operate in the amount of several hours during the time of service. However, the satellite tanks can be empty in minutes if there is a sufficiently large change of orbit. To prevent leaks and ensure the tight closing of the valve, even after many starts in the lines, several valves put in a row. Additional valves may be unjustified for small satellites.

Fig. 1 shows that liquid engines It is not always possible to reduce proportionally, for use for small thrust systems. Large engines Usually raise 10 - 30 times more than their weight, and this number increases to 100 for rocket carrier engines with pumping fuel. However, the smallest liquid engines cannot even raise their weight.

Engines for satellites is difficult to make small.

Even if a small existing engine is slightly easy to serve as the main engine maneuvering engine, select a set of 6-12 liquid engines for a 10-kilogram device is almost impossible. Therefore, microsavers are used for the orientation of compressed gas. As shown in Fig. 1, there are gas engines with a traction ratio to mass the same as large rocket engines. Gas engines It is simply a solenoid valve with a nozzle.

In addition to solving the problem of the mass of the propulsion, the system on compressed gas allows you to obtain shorter pulses than liquid motors. This property is important for continuous maintaining orientation for long flights, as shown in the application. As the sizes of spacecraft decrease, increasingly short pulses can be quite sufficient to maintain orientation with a given accuracy for this service life.

Although the systems on compressed gas look as a whole well for use on small spacecraft, gas storage containers occupy quite large volume and weigh quite a lot. Modern composite tanks for storing nitrogen, designed for small satellites, weigh as much as nitrogen itself prisonered in them. For comparison, tanks for liquid fuels in space ships can store fuel weighing up to 30 masses of tanks. Given the weight of both the tanks and engines, it would be very useful to store fuel in liquid form, and convert it to the gas for the distribution between different orientation system engines. Such systems were designed to use hydrazine in short subborital experimental flights.

Hydrogen peroxide as rocket fuel

Concentration and cleaning

For use in this project, 35% peroxide is bought in polyethylene containers with a volume of 1 gallon. First, it concentrates to 85%, then cleaned on the installation shown in Fig. 2. This variant of the previously used method simplifies the installation scheme and reduces the need to clean the glass parts. The process is automated, so that for obtaining 2 liters of peroxide per week requires only daily filling and emptying of vessels. Of course, the price per liter is high, but the full amount is still justified for small projects.

First, in two liter glasses on electric shields in the exhaust cabinet evaporated most Water for a period controlled period at 18 o'clock. The volume of fluid in each glass decreases four-solid, to 250 ml, or about 30% of the initial mass. When evaporation, a quarter of the initial peroxide molecules is lost. The loss rate is growing with a concentration, so that for this method, the practical concentration limit is 85%.

Installation on the left is a commercially available rotary vacuum evaporator. 85% solution having about 80 ppm extraneous impurities is heated by the amounts of 750 ml on a water bath at 50c. Installation is supported by a vacuum not higher than 10 mm Hg. Art. that ensures fast distillation for 3-4 hours. Condensate flows into the container on the left below with losses less than 5%.

The bath with a water jet pump is visible behind the evaporator. It has two electric pumps, one of which supplies water to the water jet pump, and the second circulates the water through the freezer, the water refrigerator of the rotary evaporator and the bath itself, maintaining the water temperature just above the zero, which improves both the condensation of the vapor in the refrigerator and the vacuum in System. Packey pairs that did not condensed on the refrigerator fall into the bath and bred to a safe concentration.

Pure hydrogen peroxide (100%) is significantly densely water (1.45 times at 20c), so that the floating glass range (in the range of 1.2-1.4) usually determines the concentration with an accuracy of up to 1%. As purchased initially, the peroxide and the distilled solution were analyzed to the content of impurities, as shown in Table. 1. The analysis included plasma-emission spectroscopy, ion chromatography and the measurement of the complete content of organic carbon (TOTAL ORGANIC CARBON - TOC). Note that phosphate and tin are stabilizers, they are added in the form of potassium and sodium salts.

Table 1. Analysis of hydrogen peroxide solution

Safety measures when handling hydrogen peroxide

Action on the eyes and lungs are more dangerous. Fortunately, the pressure of the peroxide vapor is quite low (2 mm Hg. Art. At 20c). Exhaust ventilation easily supports the concentration below the respiratory limit in 1 ppm installed by OSHA. The peroxide can be overflowing between open containers over the folds in case of spill. For comparison, N2O4 and N2H4 should be constantly in sealed vessels, a special breathing apparatus is often used when working with them. This is due to their significantly higher pressure of vapors and limiting concentration in air at 0.1 ppm for N2H4.

Washing spilled peroxide water makes it not hazardous. As for protective clothing requirements, uncomfortable suits can increase the probability of the strait. When working with small quantities, it is possible that it is more important to follow the issues of convenience. For example, work with wet hands is a reasonable alternative to work in gloves that can even skip splashes if they proceed.

Although the liquid peroxide does not decompose in the mass under the action of the source of fire, the pair of concentrated peroxide can be detected with insignificant effects. This potential danger puts the limit of the production volume of the installation described above. Calculations and measurements show a very high degree of security for these small production volumes. In fig. 2 The air is drawn into horizontal ventilation gaps located behind the device, at 100 CFM (cubic feet per minute, about 0.3 cubic meters per minute) along 6 feet (180 cm) of the laboratory table. The concentration of vapors below 10 ppm was measured directly over concentrating glasses.

The utilization of small amounts of peroxide after breeding them does not lead to environmental consequences, although it contradicts the most strict interpretation of the rules for the disposal of hazardous waste. Peroxide - oxidizing agent, and, therefore, potentially flammable. At the same time, however, it is necessary for the presence of combustible materials, and anxiety is not justified when working with small amounts of materials due to heat dissipation. For example, wet spots on tissues or loose paper will stop the ugly flame, since the peroxide has a high specific heat capacity. Containers for storing peroxide should have ventilating holes or safety valves, since the gradual decomposition of the peroxide per oxygen and water increases pressure.

Compatibility of materials and self-discharge when stored

Historical works include experiments on compatibility with samples of materials conducted in glass vessels with concentrated peroxide. In maintaining tradition, small sealing vessels were made of samples for testing. Observations for changing pressure and vessels show the rate of decomposition and peroxide leakage. In addition to this, the possible increase in volume or weakening of the material becomes noticeable, since the vessel walls are exposed to pressure.

Fluoropolymers, such as polytetrafluoroethylene (POLYTETRAFLUROTHYLENE), POLYCHLOCHLOROTRIFLUROTHYLENE) and Polyvinylidene fluoride (PLDF - Polyvinylidene Fluoride) are not decomposed under the action of peroxide. They also lead to a slowdown in the peroxide decomposition, so that these materials can be used to cover the tanks, or intermediate containers if they need to store fuel for several months or years. Similarly, the compactors from the fluorooelastomer (from the standard "Witon") and fluorine-containing lubricants are quite suitable for long-term contact with peroxide. Polycarbonate plastic is surprisingly not affected by concentrated peroxide. This material that does not form fragments is used wherever transparency is necessary. These cases include the creation of prototypes with a complex internal structure and tanks in which it is necessary to see the fluid level (see Fig. 4).

Decomposition When contacting the material AL-6061-T6 is only several times faster than with the most compatible aluminum alloys. This alloy is durable and easily accessible, while the most compatible alloys have insufficient strength. Open purely aluminum surfaces (i.e. al-6061-t6) are saved for many months upon contact with peroxide. This is despite the fact that water, for example, oxidizes aluminum.

Contrary to historically established recommendations, complex cleaning operations that use harmful to health cleaners are not necessary for most applications. Most parts of the devices used in this work with concentrated peroxide were simply washed off with water with washing powder at 110f. Preliminary results show that such an approach is almost the same nice resultsas recommended cleaning procedures. In particular, the washing of the vessel from PVDF during the day with 35% nitric acid reduces the decomposition rate of only 20% for a 6-month period.

It is easy to calculate that the decomposition of one percent of the peroxide contained in the closed vessel with 10% free volume, raises the pressure to almost 600psi (pounds per square inch, i.e. approximately 40 atmospheres). This number shows that reducing the efficiency of peroxide with a decrease in its concentration is significantly less important than security considerations during storage.

Planning space flights using concentrated peroxide requires a comprehensive consideration of the possible need to reset the pressure by ventilation of the tanks. If the operation of the motor system begins for days or weeks from the start of the start, the empty volume of the tanks can immediately grow several times. For such satellites, it makes sense to make all-metal tanks. Storage period, of course, includes the time assigned to the assuction.

Unfortunately, formal rules for working with fuel, which were developed taking into account the use of highly toxic components, usually prohibit automatic ventilation systems on the Flight Equipment. Usually used expensive pressure tracking systems. The idea of \u200b\u200bimproving safety by the prohibition of ventilation valves contradicts the normal "earthly" practice when working with liquid pressure systems. This question may have to have to revise depending on which the carrier rocket is used when starting.

If necessary, the decomposition of peroxide can be maintained at 1% per year or lower. In addition to compatibility with tank materials, the decomposition coefficient is highly dependent on temperature. It may be possible to store peroxide indefinitely in space flights if it is possible to freeze. The peroxide is not expanding during freezing and does not create threats for valves and pipes, as it happens with water.

Since the peroxide decomposes on the surfaces, an increase in the volume ratio to the surface can increase the shelf life. Comparative analysis With samples of 5 cubic meters. See and 300 cubic meters. cm confirm this conclusion. One experiment with 85% peroxide in 300 cu containers. See, made from PVDF, showed the decomposition coefficient at 70f (21c) 0.05% per week, or 2.5% per year. Extrapolation up to 10 liter tanks gives the result of about 1% per year at 20c.

In other comparative experiments using PVDF or PVDF coating on aluminum, peroxide, having 80 PPM stabilizing additives, decomposed only 30% slower than purified peroxide. This is actually good that stabilizers do not greatly increase the shelf life of peroxide in tanks with long flights. As shown in the next section, these additives are strongly interfere with the use of peroxide in engines.

Engine development

Silver-based catalyst

The composition of the surface and the mechanism of the catalyst operation is completely unclear, as follows from a variety of inexplicable and contradictory statements in the literature. The catalytic activity of the surface of pure silver can be enhanced by the application of samarium nitrate with subsequent calcination. This substance decomposes on samarium oxide, but can also oxidize silver. Other sources in addition to this refer to the treatment of pure silver nitric acid, which dissolves silver, but also is an oxidizing agent. An even easiest way is based on the fact that a purely silver catalyst can increase its activity when used. This observation was checked and confirmed, which led to the use of a catalyst without a nitrate of Samaria.

Silver oxide (AG2O) has a brownish-black color, and silver peroxide (AG2O2) has a gray-black color. These colors appeared one after another, showing that silver gradually oxidized more and more. The youngest color corresponded to the best action of the catalyst. In addition, the surface was increasingly uneven compared to the "fresh" silver when analyzing under a microscope.

A simple method for checking the activity of the catalyst was found. Separate mugs of the silver mesh (diameter 9/16 inch [approximately 14 mm] were superimposed on drops of peroxide on the steel surface. Only purchased silver grid caused a slow "hiss". The most active catalyst is repeatedly (10 times) caused a steam stream for 1 second.

This study does not prove that oxidized silver is a catalyst, or that the observed darkening is mainly due to oxidation. The mention is also worth mentioning that both silver oxide are known to decompose with relatively low temperatures. Excess oxygen during engine operation, however, can shift the reaction equilibrium. Attempts to experimentally find out the importance of oxidation and irregularities of the surface of the unequivocal result did not give. Attempts included an analysis of the surface using an X-ray photoelectron spectroscopy (X-Ray PhotooElectron Spectroscopy, XPS), also known as an electronic spectroscopic chemical analyzer (Electron Spectroscopy Chemical Analysis, ESCA). Attempts were also made to eliminate the likelihood of surface pollution in freshly pulled silver grids, which worsened catalytic activity.

Independent checks have shown that neither the Nitrate of Samaria nor its solid decomposition product (which is probably oxide) does not catalyze the decomposition of peroxide. It may mean that samarium nitrate treatment can work by oxidation of silver. However, there is also a version (without a scientific justification) that the treatment of samarium nitrate prevents the adhesion of bubbles of gaseous decomposition products to the surface of the catalyst. In the present work, ultimately, the development of light engines was considered more important than the solution of the Catalysis puzzles.

Engine scheme

Instead, in this paper, quite good results were obtained using the engine cameras made from bronze (Copper alloy C36000) on the lathe. Bronze is easily processed, and in addition, its thermal expansion coefficient is close to the silver coefficient. At the decomposition temperature of 85% peroxide, about 1200F [approximately 650c], the bronze has excellent strength. This relatively low temperature also allows you to use an aluminum injector.

Such a choice of easily processed materials and peroxide concentrations, easily achievable in laboratory conditions, is a rather successful combination for experiments. Note that the use of 100% peroxide would lead to the melting of both the catalyst and the walls of the chamber. The resulting choice is a compromise between price and efficiency. It is worth noting that the bronze chambers are used on the RD-107 and RD-108 engines applied on such a successful carrier as an alliance.

In fig. 3 is shown easy option The engine that screws itself directly to the base of the liquid valve of a small maneuvering machine. Left - 4 gram aluminum injector with fluoroalastomer seal. The 25-gram silver catalyst is divided to be able to show it from different sides. Right - 2-gram plate supporting the catalyst grid. Full mass Parts shown in the figure - approximately 80 grams. One of these engines was used for terrestrial controls of the 25-kilogram research apparatus. The system worked in accordance with the design, including the use of 3.5 kilograms of peroxide without the visible loss of quality.

150-gram commercially available solenoid valve of direct action, having a 1.2 mm hole and a 25-ohm coil controlled by a 12 volt source showed satisfactory results. The surface of the valve coming into contact with the liquid consists of stainless steel, aluminum and witon. The full mass is favorably different from mass over 600 grams for a 3-pound [approximately 13n] engine used to maintain the orientation of the Centaurian stage until 1984.

Engine testing

Fig. 4 shows the installation ready for the experiment. Direct experiments in laboratory conditions are possible due to the use of sufficiently harmless fuel, low rod values, operation under normal indoor conditions and atmospheric pressure, and applying simple devices. The protective walls of the installation are made of polycarbonate sheets of thicknesses in half: approximately 12 mm], which are installed on the aluminum frame, in good ventilation. The panels were tested for a flushing force in 365.000 N * C / m ^ 2. For example, a fragment of 100 grams, moving with a supersonic speed of 365 m / s, stop if the stroke of 1 kV. cm.

In the photo, the engine camera is oriented vertically, just below the exhaust pipe. Pressure sensors at the inlet in the injector and pressure inside the chamber are located on the platform of the scales that measure the craving. Digital performance and temperature indicators are outside the installation walls. The opening of the main valve includes a small array of indicators. Data recording is carried out by installing all indicators in the visibility field of the camcorder. The final measurements were carried out using a heat-sensitive chalk, which conducted a line along the length of the Catalysis chamber. Color change corresponded to temperatures above 800 F [approximately 430c].

The capacitance with concentrated peroxide is located on the left of the scales on a separate support, so that the change in the mass of the fuel does not affect the measurement of the thrust. With the help of reference weights, it was checked that the tubes, bringing peroxide to the chamber, are quite flexible to achieve measurement accuracy within 0.01 pounds [approximately 0.04n]. The peroxide capacitance was made of a large polycarbonate pipe and is calibrated so that the change in the level of the fluid can be used to calculate the UI.

Engine parameters

The initial short-term launch was carried out to avoid a "wet" start at which a visible exhaust appeared. Typically, the initial start was carried out within 5 s at consumption<50%, но вполне хватало бы и 2 с. Затем шёл основной прогон в течение 5-10 с, достаточных для полного прогрева двигателя. Результаты показывали температуру газа в 1150F , что находится в пределах 50F от теоретического значения. 10-секундные прогоны при постоянных условиях использовались для вычисления УИ. Удельный импульс оказывался равным 100 с , что, вероятно, может быть улучшено при использовании более оптимальной формы сопла, и, особенно, при работе в вакууме.

The length of the silver catalyst was successfully reduced from a conservative 2.5 inches [approximately 64 mm to 1.7 inches [approximately 43 mm]. The final engine scheme had 9 holes with a diameter of 1/64 inches [approximately 0.4 mm] in a flat surface of the injector. The critical section of the size of 1/8 inches made it possible to obtain a 3.3 pound of force of force at a pressure in the PSIG chamber 220 and the pressure difference 255 PSIG between the valve and the critical section.

Distilled fuel (Table 1) gave stable results and stable pressure measurements. After a run of 3 kg of fuel and 10 starts, a point with a temperature of 800F was on the chamber at a distance of 1/4 inches from the surface of the injector. At the same time, for comparison, the engine performance time at 80 ppm impurities was unacceptable. Pressure fluctuations in the chamber at a frequency of 2 Hz reached a value of 10% after spending only 0.5 kg of fuel. The temperature point is 800F departed over 1 inches from the injector.

A few minutes in 10% nitric acid restored a catalyst to a good condition. Despite the fact that, together with pollution, a certain amount of silver was dissolved, the catalyst activity was better than after the nitric acid treatment of a new, not used catalyst.

It should be noted that, although the engine warming time is calculated by seconds, significantly shorter emissions are possible if the engine is already heated. The dynamic response of the liquid subsystem of traction weighing 5 kg on the linear portion showed the pulse time in short, than in 100 ms, with a transmitted pulse about 1 H * p. In particular, the offset was approximately +/- 6 mm at a frequency of 3 Hz, with a limitation set by the system speed system.

Options for building Du

Traditional schemes

Embodiment B is the simplest liquid scheme, and was repeatedly tested in flights with hydrazine as fuel. Gas supporting pressure in the tank usually takes a quarter of a tank during start. Gas gradually expands during the flight, so they say that the pressure "blows out". However, the pressure drop reduces both cravings and ui. The maximum fluid pressure in the tank takes place during the launch, which increases the mass of the tanks for security reasons. A recent example is the device of Lunar Prospector, which had about 130 kg of hydrazine and 25 kg of weight of the Du.

The variant C is widely used with traditional poisonous single-component and two-component fuels. For the smallest satellites, it is necessary to add Du on compressed gas to maintain the orientation, as described above. For example, the addition of Du on a compressed gas to the variant C leads to option D. Motor systems of this type, working on nitrogen and concentrated peroxide, were built in the Laurenov Laboratory (LLNL) so that you can safely experience the orientation systems of microsteps prototypes operating on non-fuels .

Maintaining orientation with hot gases

To further reduce the mass of the equipment and simplify the storage system, it is desirable to generally avoid gas storage capacities. Option F is potentially interesting for miniature systems on peroxide. If prior to the start of work, a long-term storage of fuel in orbit is required, the system can start without initial pressure. Depending on the free space in the tanks, the size of the tanks and their material, the system can be calculated for pumping pressure at a predetermined moment in flight.

In version D, there are two independent fuel sources, to maneuvering and maintaining the orientation, which makes it separately to take into account the flow rate for each of these functions. E and F systems that produce hot gas to maintain fuel orientation used for maneuvering have greater flexibility. For example, unused when maneuvering fuel can be used to extend the life of the satellite, which needs to maintain its orientation.

Ideas Samonaduva

Variants G and H can be called liquid systems of "hot gas under pressure", or "blow-up", as well as "gas from liquid" or "self-trunk". For controlled supervision of the tank, the spent fuel is required to increase the pressure.

Embodiment G uses a tank with a membrane deflected by pressure, so first the fluid pressure above the gas pressure. This can be achieved using a differential valve or an elastic diaphragm that shares gas and liquid. Acceleration can also be used, i.e. Gravity in ground applications or centrifugal force in a rotating spacecraft. Option H is working with any tank. A special pump for maintaining pressure provides circulation through a gas generator and back to a free volume in the tank.

In both cases, the liquid controller prevents the appearance of feedback and the occurrence of arbitrarily greater pressures. For normal operation of the system, an additional valve is included in sequentially with the regulator. In the future, it can be used to control the pressure in the system within the pressure of the regulator being installed. For example, maneuvers on the change of orbit will be made under full pressure. The reduced pressure will allow to achieve a more accurate maintenance of orientation of 3 axes, while maintaining fuel to extend the service life of the device (see Appendix).

Over the years, experiments with pumps of difference area were carried out both in pumps and in tanks, and there are many documents describing such structures. In 1932, Robert H. Goddard and others built a pump driven by a machine to control liquid and gaseous nitrogen. Several attempts were made between 1950 and 1970, in which the options G and H were considered for atmospheric flights. These attempts to reduce volume were carried out in order to reduce windshield resistance. These works were subsequently discontinued with the widespread development of solid fuel missiles. Working on self-adequate systems and differential valves were performed relatively recently, with some innovations for specific applications.

Liquid fuel storage systems with self-ads were not considered seriously for long-term flights. There are several technical reasons why in order to develop a successful system, it is necessary to ensure well predictable properties of thrust during the entire service life of the Du. For example, a catalyst suspended in a gas supply gas can decompose fuel inside the tank. It will require the separation of tanks, as in the version G, to achieve performance in flights that require a long period of rest after the initial maneuvering.

The working cycle of thrust is also important from thermal considerations. In fig. 5G and 5H The heat released during the reaction in the gas generator is lost in the surrounding parts in the process of long flight with rare inclusions of the Du. This corresponds to the use of soft seals for hot gas systems. High-temperature metal seals have a greater leakage, but they will only be needed if the working cycle is intense. Questions about the thickness of thermal insulation and heat capacity of the components should be considered, well representing the intended nature of the work of the Du during the flight.

Pumping engines

Although fig. 5J is somewhat simplified, it is included here in order to show that this is a completely different option than H. In the latter case, the pump is used as an auxiliary mechanism, and the pump requirements differ from the engine pump.

Work continues, including testing rocket engines operating at concentrated peroxide and using pumping units. It is possible that easily repeated inexpensive tests of engines using non-toxic fuel will allow achieving even simpler and reliable schemes than previously achieved when using pumping hydrazine developments.

Prototype self-adhesive system tank

Fig. 6 depicts inexpensive test equipment that uses a differential valve pump made from a segment of an aluminum pipe with a diameter of 3 inches [approximately 75 mm with a wall thickness of 0.065 inches [approximately 1.7 mm], squeezed at the ends between sealing rings. Welding here is missing, which simplifies the system check after testing, changing the system configuration, and also reduces the cost.

This system with self-adequate concentrated peroxide was tested using solenoid valves available on sale, and inexpensive tools, as in engine development. An exemplary system diagram is shown in Fig. 7. In addition to the thermocouple immersed in gas, the temperature also measured on the tank and the gas generator.

The tank is designed so that the pressure of the liquid in it is a little higher than the pressure of the gas (???). Numerous starts were carried out using the initial air pressure of 30 psig [approximately 200 kPa]. When the control valve opens, the flow through the gas generator supplies steam and oxygen into the pressure maintenance channel in the tank. The first order of positive feedback of the system leads to exponential pressure growth until the liquid controller is closed when 300 psi is reached [Approximately 2 MPa].

Input sensitivity is invalid for gas pressure regulators, which are currently used on satellites (Fig. 5a and C). In the fluid system with self-admiration, the regulator's input pressure remains in the narrow range. Thus, it is possible to avoid many difficulties inherent in conventional regulators schemes used in the aerospace industry. A regulator weighing 60 grams has only 4 moving parts, not counting springs, seals and screws. The regulator has a flexible seal for closing when the pressure is exceeded. This simple axisymmetric diagram is sufficient due to the fact that it is not necessary to maintain the pressure at certain limits at the entrance to the regulator.

The gas generator is also simplified thanks to the low requirements for the system as a whole. When the pressure difference in 10 PSI, the fuel flow is sufficiently small, which allows the use of the simplest injectors schemes. In addition, the absence of a safety valve at the inlet in the gas generator leads only to small vibrations of about 1 Hz in the decomposition reaction. Accordingly, a relatively small reverse flow during the start of the system starts the regulator not higher than 100F.

Initial tests did not use the regulator; In this case, it was shown that the pressure in the system can be maintained by any in the limits of the compactor allowed by friction to the safe pressure limiter in the system. Such flexibility of the system can be used to reduce the required orientation system for most of the satellite service life, for the reasons specified above.

One of the observations that seem to be apparent later was that the tank is heated stronger if low-frequency pressure fluctuations occur in the system during control without using the regulator. Safety valve at the entrance to the tank, where compressed gas is supplied, could eliminate the additional heat flow occurring due to pressure fluctuations. This valve would also not give Baku to accumulate pressure, but it is not necessarily important.

Although the aluminum parts are melted at a decomposition temperature of 85% peroxide, the temperature is somewhat slightly due to the loss of heat and the intermittent gas flow. The tank shown in the photo had a temperature noticeably below 200f during testing with pressure maintenance. At the same time, the gas temperature at the outlet exceeded 400F during a rather energetic switching of a warm gas valve.

The gas temperature at the output is important because it shows that water remains in a state of superheated steam inside the system. The range from 400F to 600F looks perfect, as this is cold enough for cheap light equipment (aluminum and soft seals), and heat enough to obtain a significant part of the fuel energy used to support the orientation of the apparatus using gas jets. During periods of work under reduced pressure, an additional advantage is that the minimum temperature. Required to avoid moisture condensation, also decreases.

To work as long as possible in the permissible temperature limits, such parameters such as the thickness of the thermal insulation and the overall heat capacity of the design must be customized for a specific traction profile. As expected, after testing in the tank, the condensed water was discovered, but this unused mass is a small part of the total fuel mass. Even if all the water from the gas flow used for the orientation of the apparatus is condensed, any equal to 40% of the mass of the fuel will be gaseous (for 85% peroxide). Even this option is better than using compressed nitrogen, as water is easier than the dear modern nitrogen tank.

Test equipment shown in Fig. 6, obviously, far from being called a complete traction system. Liquid motors of an approximately the same type as described in this article may, for example, are connected to the output tank connector, as shown in Fig. 5G.

Plans for Supervising the Pump

It is planned to use a pair of pumping chambers that work alternately, instead of the minimum necessary single camera. This will ensure the permanent job of the orientation subsystem on warm gas at constant pressure. The task is to pick up the tank to reduce the mass of the system. The pump will work on the gas parts of the gas generator.

Discussion

This article addressed the possibility of using hydrogen peroxide using low-cost materials and techniques applicable in small scales. The results obtained can also be applied to the Du on a single-component hydrazine, as well as in cases where the peroxide can serve as an oxidizing agent in unseated two-component combinations. The latter option includes self-flameless alcohol fuels, described in (6), as well as liquid and solid hydrocarbons, which are flammable when contact with hot oxygen, resulting in decomposition of concentrated peroxide.

Relatively simple technology with peroxide, described in this article, can be directly used in experimental spacecraft and other small satellites. Just one generation back low near-earth orbits and even deep space were studied using actually new and experimental technologies. For example, the Lunar Sirewiper planting system included numerous soft seals, which can be considered unacceptable today, but were quite adequate to the tasks. Currently, many scientific tools and electronics are highly miniaturized, but the technology of the Du does not meet the requests of small satellites or small lunar landing probes.

The idea is that custom equipment can be designed for specific applications. This, of course, contradicts the idea of \u200b\u200b"inheritance" technologies, which usually prevails when selecting satellite subsystems. The base for this opinion is the assumption that the details of the processes are not well studied well to develop and launch completely new systems. This article was caused by the opinion that the possibility of frequent inexpensive experiments will allow to give the necessary knowledge to the designers of small satellites. Together with the understanding of both the needs of satellites and the capabilities of the technole, the potential reduction of unnecessary requirements for the system comes.

Thanks

The study was part of the Clementine-2 program and microsatellite technologies in Laureren's laboratory, with the support of the US Air Force Research Laboratory. This work used the US government funds and was held at the Louuren's National Laboratory in Livermore, the University of California as part of the W-7405-ENG-48 contract with the US Department of Energy.

Hydrogen peroxide H 2 O 2 - transparent colorless liquid, noticeably more viscous than water, with characteristic, albeit weak odor. Anhydrous hydrogen peroxide is difficult to get and stored, and it is too expensive for use as rocket fuel. In general, high cost is one of the main drawbacks of hydrogen peroxide. But, compared to other oxidizing agents, it is more convenient and less dangerous in circulation.
The proposal of peroxide to spontaneous decomposition is traditionally exaggerated. Although we observed a decrease in concentration from 90% to 65% in two years of storage in liter polyethylene bottles at room temperature, but in large volumes and in a more suitable container (for example, in a 200-liter barrel of sufficiently pure aluminum) decomposition rate of 90% Packsi would be less than 0.1% per year.
The density of anhydrous hydrogen peroxide exceeds 1450 kg / m 3, which is significantly larger than in liquid oxygen, and a little less than that of nitric acid oxidants. Unfortunately, water impurities quickly reduce it, so that 90% solution has a density of 1380 kg / m 3 at room temperature, but it is still a very good indicator.
The peroxide in the EDD can also be used as unitary fuel, and as an oxidizing agent - for example, in a pair with kerosene or alcohol. Neither kerosene nor alcohol is self-proposal with peroxide, and to ensure ignition in fuel, it is necessary to add a catalyst for the decomposition of peroxide - then the released heat is sufficient for ignition. For alcohol, a suitable catalyst is acetate manganese (II). For kerosene, also there are appropriate additives, but their composition is kept secret.
The use of peroxide as unitary fuel is limited to its relatively low energy characteristics. Thus, the achieved specific impulse in vacuo for 85% peroxide is only about 1300 ... 1500 m / s (for different degrees of expansion), and for 98% - approximately 1600 ... 1800 m / s. However, the peroxide was applied first by the Americans for the orientation of the descent apparatus of the Mercury spacecraft, then, with the same purpose, the Soviet designers on the Savior Soyk QC. In addition, hydrogen peroxide is used as an auxiliary fuel for the TNA drive - for the first time on the V-2 rocket, and then on its "descendants", up to P-7. All modifications "Sexok", including the most modern, still use peroxide to drive TNA.
As an oxidizer, hydrogen peroxide is effective with various combustible. Although it gives a smaller specific impulse, rather than liquid oxygen, but when using a high concentration peroxide, the values \u200b\u200bof the UI exceed that for nitric acid oxidants with the same flammable. Of all space-carrier missiles, only one used peroxide (paired with kerosene) - English "Black Arrow". The parameters of its engines were modest - Ui of engine I steps, a little exceeded 2200 m / s at the Earth and 2500 m / s in vacuo, "since only 85% concentration was used in this rocket. This was done due to the fact that to ensure self-ignition peroxide decomposed on a silver catalyst. More concentrated peroxide would melt silver.
Despite the fact that interest in the peroxide from time to time is activated, the prospects remain foggy. So, although the Soviet EDRD of the RD-502 (fuel pair - peroxide plus pentabran) and demonstrated the specific impulse of 3680 m / s, it remained experimental.
In our projects, we focus on the peroxide also because the engines on it turn out to be more "cold" than similar engines with the same UI, but on other fuels. For example, the combustion products of "caramel" fuels have almost 800 ° with a larger temperature with the same UI. This is due to a large amount of water in peroxide reaction products and, as a result, with a low average molecular weight of the reaction products.

Usage: in internal combustion engines, in particular in the method of ensuring improved combustion of fuels with the participation of hydrocarbon compounds. SUMMARY OF THE INVENTION: The method provides for the introduction to the composition of 10-80 vol. % peroxide or pecox connections. The composition is introduced separately from the fuel. 1 Z.P. F-lies, 2 tab.

The invention relates to a method and liquid composition for initiating and optimizing the combustion of hydrocarbon compounds and reducing the concentration of harmful compounds in exhaust gases and emissions, where a liquid composition containing peroxide or peroxo-compound is fed into the combustion air or into the fuel and air mixture. Prerequisites for the creation of the invention. In recent years, increasing attention is paid to environmental pollution and high energy waste, especially due to the dramatic death of forests. However, the exhaust gases have always been the problem of populated centers. Despite the continuous improvement of motors and heating equipment with lower emissions or exhaust gases, the increasing number of cars and incineration plants led to a total increase in the number of exhaust gases. The primary cause of contamination of exhaust gases and a large consumption of energy is incomplete combustion. The scheme of the combustion process, the efficiency of the ignition system, the quality of fuel and the fuel mixture determines the combustion efficiency and the content of unburned and dangerous compounds in the gases. To reduce the concentration of these compounds, various methods are used, such as recycling and well-known catalysts, leading to the afterburning of exhaust gases outside the basic burning zone. Burning is the reaction of compound with oxygen (O 2) under the action of heat. Such compounds like carbon (C), hydrogen (H 2), hydrocarbons and sulfur (S) generate enough heat to maintain their combustion, and for example nitrogen (N 2) requires heat supply for oxidation. At high temperature, 1200-2500 o with and sufficient oxygen, complete combustion is achieved, where each compound binds the maximum amount of oxygen. The final products are CO 2 (carbon dioxide), H 2 O (water), SO 2 and SO 3 (sulfur oxides) and sometimes NO and NO 2 (nitrogen oxides, NO x). Sulfur and nitrogen oxides are responsible for the acidification of the environment, it is dangerous to inhale and especially the last (NO x) absorb the combustion energy. It can also be obtained by cold flames, such as the blue flame candle flame, where the temperature is only about 400 o C. Oxidation here is not complete and ended products can be H 2 O 2 (hydrogen peroxide), CO (carbon monoxide) and possibly with (soot) . The two last indicated compounds, like NO, are harmful and can give energy with full combustion. Gasoline is a mixture of hydrocarbons of crude oil with boiling temperatures in the range of 40-200 o C. It contains about 2,000 different hydrocarbons with 4-9 carbon atoms. The detailed process of burning is very complicated for simple compounds. Fuel molecules decompose into smaller fragments, most of which are so-called free radicals, i.e. Unstable molecules that quickly react, for example, with oxygen. The most important radicals are atomic oxygen o, atomic hydrogen H and hydroxyl radical. The latter is especially important for decomposition and oxidation of fuel both at the expense of direct addition and the cleavage of hydrogen, as a result of which water is formed. At the beginning of the initiation of burning, the water enters into the reaction H 2 O + M ___ H + CH + M where M is another molecule, for example nitrogen, or the wall or surface of the spark electrode, which faces the water molecule. Since water is a very stable molecule, it requires a very high temperature for its decomposition. The best alternative is the addition of hydrogen peroxide, which is decomposed similarly H 2 O 2 + M ___ 2OH + M. This reaction proceeds much easier and at a lower temperature, especially on the surface where the ignition of the fuel and air mixture flows easier and more controlled manner. The additional positive effect of the surface reaction is that hydrogen peroxide is easily reacting with soak and resin on the walls and the ignition candle with the formation of carbon dioxide (CO 2), which leads to the cleaning of the electrode surface and the better ignition. Water and hydrogen peroxide strongly reduce the content of CO in the exhaust gases of the following scheme 1) CO + O 2 ___ CO 2 + O: initiation 2) O: + H 2 O ___ 2OH branching 3) OH + CO ___ CO 2 + H Height 4) H + O 2 ___ OH + O; Branching from the reaction 2) shows that the water plays the role of the catalyst and then formed again. Since hydrogen peroxide leads to many thousands of times a higher content of on-radicals than water, then Stage 3) is significantly accelerated, leading to the removal of most of the generated CO. As a result, additional energy is exempt, helping to maintain burning. NO and NO 2 are highly toxic compounds and is approximately 4 times more toxic than CO. In acute poisoning, pulmonary fabric is damaged. NO is an undesirable combustion product. In the presence of water, NO is oxidized to NNO 3 and in this form causes approximately half of the acidification, and the other half is due to H 2 SO 4. In addition, NO can decompose ozone in the upper layers of the atmosphere. Most of the NO is formed as a result of the oxygen reaction with air nitrogen at high temperatures and, therefore, does not depend on the composition of the fuel. The amount of X X depends on the duration of maintaining the combustion conditions. If the decrease in temperature is carried out very slowly, this leads to equilibrium at moderately high temperatures and to a relatively low concentration of NO. The following methods can be used to achieve low NO content. 1. Double-step combustion of the mixture enriched with fuel. 2. Low incineration temperature due to: a) greater excess air,
b) severe cooling
c) recycling gas burning. As often is observed in a chemical analysis of the flame, the concentration of NO in the flame is higher than after it. This is the process of decomposition of O. Possible reaction:
SH 3 + NO ___ ... H + H 2 O
Thus, the formation of N 2 is maintained by conditions that give a high concentration of CH 3 in hot fuel enriched flames. As practice shows, fuels containing nitrogen, for example, in the form of heterocyclic compounds such as pyridine, give a greater number of NO. CONTENT N in various fuels (approximate),%: Crying oil 0.65 asphalt 2.30 Heavy gasoline 1.40 Light gasoline 0.07 Coal 1-2
In SE-B-429.201, a liquid composition containing 1-10% by volume of hydrogen peroxide is described, and the rest is water, aliphatic alcohol, lubricating oil and is possible inhibitor of corrosion, where the specified liquid composition is fed into the air of burning or in the fuel and air mixture. With such a low content of hydrogen peroxide, the resulting amount of α-radicals is not enough for a reaction with fuel and with CO. With the exception of the compositions leading to the self-burning of fuel, the positive effect achieved here is small compared to the addition of one water. B DE-A-2.362.082 describes the addition of an oxidizing agent, for example, hydrogen peroxide, during combustion, however, hydrogen peroxide is decomposed on water and oxygen with a catalyst before it is inserted into the combustion air. The goal and the most important features of the present invention. The purpose of this invention is to improve the combustion and reducing the emission of harmful exhaust gases in the processes of combustion involving hydrocarbon compounds, due to improved initiation of combustion and maintain optimal and complete combustion in such good conditions that the content of harmful exhaust gases is much reduced. This is achieved by the fact that a liquid composition containing peroxide or people-compound and water is supplied to the air of burning or in the air-fuel mixture, where the liquid composition contains 10-80% by weight peroxide or pecoxide compound. At alkaline conditions, hydrogen peroxide is decomposed on hydroxyl radicals and peroxide ions according to the following scheme:
H 2 O 2 + HO 2 ___ HO + O 2 + H 2 O
The resulting hydroxyl radicals can react with each other, with peroxide ions or with hydrogen peroxide. As a result of these reactions presented below, hydrogen peroxide, gas oxygen and hydroperical radicals are formed:
HO + HO ___ H 2 O 2
HO + O ___ 3 O 2 + OH -
HO + H 2 O 2 ___ HO 2 + H 2 O It is known that the PCA peroxide radicals is 4.88 0.10 and this means that all hydroperoxyradicals are dissociated to peroxide ions. Peroxide ions can also react with hydrogen peroxide, with each other or capture the forming singlet oxygen. O + H 2 O 2 ___ O 2 + HO + OH -
O + O 2 + H 2 O ___ I O 2 + HO - 2 + OH -
O + I O 2 ___ 3 O 2 + O + 22 kcal. Thus, gas-made oxygen, hydroxyl radicals, singlet oxygen, hydrogen peroxide and triplet oxygen with a 22 kcal energy is formed. It is also confirmed that the ions of heavy metals present during the catalytic decomposition of hydrogen peroxide, give hydroxyl radicals and peroxide ions. There is information about speed constants, for example, the following data for typical oil alkanes. Denate constants of the interaction of N-octane with H, O and it. K \u003d A EXP / E / RT Reaction A / cm 3 / Mol: C / E / KJ / Mol / N-s 8 H 18 + H 7.1: 10 14 35.3
+ O 1.8: 10 14 19.0
+ It is 2.0: 10 13 3.9
From this example, we see that the attack by the radicals proceeds faster and at a lower temperature than H and O. The CO + + + H _ CO 2 rate constant has an unusual temperature dependence due to the negative activation and high temperature coefficient. It can be written as follows: 4.4 x 10 6 x t 1.5 EXP / 3.1 / RT. The reaction rate will be almost constant and equal to about 10 11 cm 3 / mol s at temperatures below 1000 o to, i.e. Up to room temperature. Above 1000 o to the reaction rate increases several times. By virtue of this, the reaction completely dominates in converting CO in CO 2 when burning hydrocarbons. Because of this, early and complete combustion of CO improves thermal efficiency. An example illustrating the antagonism between O 2 and it is the NH 3 -H 2 O 2 -NO reaction, where the addition of H 2 O 2 leads to a 90% reduction in NO x in an oxygen-free medium. If 2 is present, even with only 2% by x, the decline is greatly reduced. In accordance with this invention, H 2 O 2 is used to generate, dissociating approximately 500 o S. Their lifetime is equal to a maximum of 20 ms. With normal incineration of ethanol, 70% of the fuel is consumed on the reaction with it radicals and 30% with n-atoms. In this invention, it is already at the stage of combustion initiation, it is formed by radicals, incineration due to the immediate fuel attack. When the liquid composition with a high hydrogen peroxide content is added (above 10%), it has sufficiently on-radicals for the immediate oxidation of the generated CO. With lower contents of hydrogen peroxide, it is not enough for interaction with both fuel and CO. The liquid composition is supplied in such a way that there is no chemical reaction in the gap between the container with the liquid and the combustion chamber, i.e. The decomposition of hydrogen peroxide on water and gaseous oxygen does not proceed, and the liquid unchanged reaches the combustion zone or pre-target, where the mixture of fluid and fuel is ignited outside the main combustion chamber. With a sufficiently high concentration of hydrogen peroxide (about 35%), self-burning fuel and maintenance of combustion can occur. The ignition of the mixture of the liquid with fuel can flow by self-burning or contact with a catalytic surface at which it does not need something like that. The ignition can be carried out through thermal energy, for example, fused the accumulating heat, open flame, etc. Aliphatic alcohol mixing with hydrogen peroxide may initiate self-burning. This is especially useful in the system with a preliminary chamber, where you can prevent mixing of hydrogen peroxide with alcohol until the pre-camera is reached. If you provide each cylinder injector valve for a liquid composition, then a liquid dosing is very accurate and adapted for all service conditions. Using a controlled device that regulates injector valves, and various sensors connected to a motor feeding to a controlled engine of the motor shaft position, motor velocity and load and, possibly, the temperature of the ignition can be achieved by serial injection and synchronization of opening and closing injector valves and dispensing liquid not only depending on the load and the desired power, as well as with the speed of the motor and the temperature of the injected air, which leads to good movement in all conditions. The liquid mixture replaces the air supply to some extent. A large number of tests were conducted to identify differences in the effect between water mixtures and hydrogen peroxide (23 and 35%, respectively). Loads that are selected correspond to the movement along the high-speed track and in the cities. The engine was tested in a water brake. Motor warmed up before the test. With high-speed load on the motor, the release of NO X, CO and NS increases when the hydrogen peroxide is replaced by water. The content of NOs decreases with increasing the number of hydrogen peroxide. Water also reduces the content of NOs, however, with this load, it takes 4 times more water than 23% of hydrogen peroxide for the same reduction in the content of NO. With the load of movement in the city, 35% of hydrogen peroxide is first supplied, while the speed and moment of the motor increases somewhat (20-30 revs per min / 0.5-1 nm). When moving at 23%, hydrogen peroxide and the motor speed are reduced while simultaneously increasing the content of NO. When filing clean water, it is difficult to maintain the rotation of the motor. The NA content increases sharply. Thus, hydrogen peroxide improves combustion, while at the same time reducing the content of NO. Tests carried out in the Swedish inspection of motors and transport on SAAB 900i and Voivo 760 models with mixing and without mixing to fuel 35% hydrogen peroxide gave the following results on the allocation of CO, NA, NO and CO 2. The results are presented in% of the values \u200b\u200bobtained using hydrogen peroxide relative to the results without the use of the mixture (Table 1). When testing on the Volvo 245 G14FK / 84, at idling, the content of CO was 4% and the content of NA 65 ppm without air pulsation (exhaust purification). When mixed with a 35% hydrogen peroxide solution, the content of the CO decreased to 0.05%, and the NA content - up to 10 ppm. The ignition time was equal to 10 o and hoisters at idle were equal to 950 rpm in both cases. In the trials carried out in the Norwegian Marine Technological Research Institute of A / S in Treddheim, the discharge of the National Assembly of the National Assembly of the National Assembly of the National Assembly of the National Assembly of the National Assembly of National Assembly (table 2). The above is the use of only hydrogen peroxide. A similar effect can also be achieved with other peroxides and pecox connections, both inorganic and organic. A liquid composition, in addition to the peroxide and water, can also contain up to 70% aliphatic alcohol with 1-8 carbon atoms and up to 5% oil containing corrosion inhibitor. The amount of liquid composition mixed in fuel can vary from several tenths percentage of liquid composition from the amount of fuel to several hundred%. Large quantities are used, for example, for so-flamded fuels. The liquid composition can be used in internal combustion engines in other incineration processes with the participation of hydrocarbons such as oil, coal, biomass, etc., in burning furnaces for more complete combustion and reduce the content of harmful compounds in emissions.

Claim

1. A method of providing improved combustion with the participation of hydrocarbon compounds, in which a liquid composition containing peroxide or peroxo compounds and water, characterized in that, in order to reduce the content of harmful compounds in exhaust emission gases to reduce the content of harmful compounds, liquid The composition contains 10 - 60 vol. % peroxide or peroxotion and it is administered directly and separately from fuel into the combustion chamber without prior decomposition of peroxide or peroxo compound or it is injected into the pre-chamber, where the mixture of fuel and liquid composition flames out of the main combustion chamber. 2. The method according to claim 1, characterized in that aliphatic alcohol is administered, containing 1 to 8 carbon atoms, in the preliminary chamber separately.

The first sample of our liquid rocket engine (EDRD) operating on kerosene and highly concentrated hydrogen peroxide is assembled and ready for tests on the stand in MAI.

It all started about a year ago from the creation of 3D models and the release of design documentation.

We sent ready-made drawings to several contractors, including our main partner for metalworking "artmehu". All the work on the chamber was duplicated, and the manufacture of nozzles was generally obtained by several suppliers. Unfortunately, here we faced with all the complexity of the manufacture would seem like simple metal products.

Especially a lot of effort had to spend on centrifugal nozzles for spraying fuel in the chamber. On the 3D model in the context, they are visible as cylinders with blue nuts on the end. And so they look in the metal (one of the injectors is shown with a rejected nut, the pencil is given for scale).

We already wrote about the injectors' tests. As a result, many dozens of nozzles were selected seven. Through them, Kerosene will come to the chamber. The kerosene nozzles themselves are built into the upper part of the chamber, which is an oxidizer gasifier - an area where hydrogen peroxide will pass through a solid catalyst and decomposed on water vapor and oxygen. Then the resulting gas mixture will also go to the EDD chamber.

To understand why the manufacture of nozzles caused such difficulties, it is necessary to look inside - inside the nozzle channel there is a screw jigger. That is, the kerosene entering the nozzle is not just exactly flowing down, but twisted. The screw jigger has a lot of small parts, and on how accurately it is possible to withstand their size, the width of the gaps, through which the kerosene will flow and spray in the chamber. The range of possible outcomes - from "through the nozzle, the liquid does not flow at all" to "spraying evenly in all sides." The perfect outcome - kerosene is sprayed with a thin cone down. Approximately the same as in the photo below.

Therefore, obtaining an ideal nozzle depends not only on the skill and conscientiousness of the manufacturer, but also from the equipment used and, finally, the shallow motility of the specialist. Several series of tests of ready-made nozzles under different pressure allowed us to choose those whose cone is close to perfect. In the photo - a swirl that has not passed the selection.

Let's see how our engine looks in the metal. Here is the LDD cover with highways for the receipt of peroxide and kerosene.

If you raise the lid, then you can see that peroxide pumps through the long tube, and through short - kerosene. Moreover, kerosene is distributed over seven holes.

A gasifier is connected to the lid. Let's look at it from the camera.

The fact that we from this point seems to be the bottom of the details, in fact it is its upper part and will be attached to the LDD cover. Of the seven holes, kerosene in nozzles is poured into the chamber, and from the eighth (on the left, the only asymmetrically located peroxide) on the catalyst rushes. More precisely, it rushes not directly, but through a special plate with microcers, evenly distributing the flow.

In the next photo, this plate and nozzles for kerosene are already inserted into the gasifier.

Almost all free gasifier will be engaged in a solid catalyst through which hydrogen peroxide flows. Kerosene will go on nozzles without mixing with peroxide.

In the following photo, we see that the gasifier has already been closed with a cover from the combustion chamber.

Through seven holes ending with special nuts, Kerosene flows, and a hot steamer will go through the minor holes, i.e. Already decomposed on oxygen and water vapor peroxide.

Now let's deal with where they will drown. And they flow into the combustion chamber, which is a hollow cylinder, where kerosene flammives in oxygen, heated in the catalyst, and continues to burn.

Preheated gases will go to a nozzle, in which they accelerate to high speeds. Here is nozzle from different angles. A large (narrowing) part of the nozzle is called pretreatic, then a critical section is going on, and then the expanding part is the cortex.

As a result, the assembled engine looks like this.

Handsome, however?

We will produce at least one instance of stainless steel platforms, and then proceed to the manufacture of EDRs from Inkonel.

The attentive reader will ask, and for which fittings are needed on the sides of the engine? Our relocation has a curtain - the liquid is injected along the walls of the chamber so that it does not overheat. In flight the curtain will flow the peroxide or kerosene (clarify the test results) from the rocket tanks. During fire tests on the bench in a curtain, both kerosene and peroxide, as well as water or nothing to be served (for short tests). It is for the curtain and these fittings are made. Moreover, the curtains are two: one for cooling the chamber, the other - the pre-critical part of the nozzle and critical section.

If you are an engineer or just want to learn more of the characteristics and the EDD device, then an engineering note is presented in detail for you.

EDD-100S.

The engine is designed for the standsight of the main constructive and technological solutions. Engine tests are scheduled for 2016.

The engine works on stable high-boiling fuel components. The calculated thrust at sea level is 100 kgf, in vacuo - 120 kgf, the estimated specific impulse of the thrust at sea level - 1840 m / s, in vacuo - 2200 m / s, the estimated share is 0.040 kg / kgf. The actual characteristics of the engine will be refined during the test.

The engine is single-chamber, consists of a chamber, a set of automatic system units, nodes and parts of the general assembly.

The engine is fastened directly to the bearing stands through the flange at the top of the chamber.

The main parameters of the chamber
fuel:
- Oxidizer - PV-85
- Fuel - TS-1
traction, kgf:
- at sea level - 100.0
- in emptiness - 120.0
Specific pulse traction, m / s:
- at sea level - 1840
- in emptiness - 2200
Second consumption, kg / s:
- Oxidizer - 0,476
- Fuel - 0.057
Weight ratio of fuel components (O: D) - 8,43: 1
Oxidizer excess coefficient - 1.00
Gas pressure, bar:
- in the combustion chamber - 16
- in the weekend of the nozzle - 0.7
Mass of the chamber, kg - 4.0
Inner engine diameter, mm:
- cylindrical part - 80.0
- in the area of \u200b\u200bthe cutting nozzle - 44.3

The chamber is a precast design and consists of a nozzle head with an oxidizer gasifier integrated into it, a cylindrical combustion chamber and a profiled nozzle. The elements of the chamber have flanges and are connected by bolts.

On the head 88 single-component jet oxidizer nozzles and 7 single-component centrifugal fuel injectors are placed on the head. Nozzles are located on concentric circles. Each combustion nozzle is surrounded by ten oxidizer nozzles, the remaining oxidizer nozzles are located on the free space of the head.

Cooling the camera internal, two-stage, is carried out by liquid (combustible or oxidizing agent, the choice will be made according to the results of bench tests) entering the chamber cavity through two veins of the veil - the upper and lower. The top belt curtain is made at the beginning of the cylindrical part of the chamber and provides cooling of the cylindrical part of the chamber, the lower - is made at the beginning of the subcritical part of the nozzle and provides cooling of the subcritical part of the nozzle and the critical section.

The engine uses self-ignition of fuel components. In the process of starting the engine, an oxidizing agent is improved in the combustion chamber. With the decomposition of the oxidant in the gasifier, its temperature rises to 900 K, which is significantly higher than the temperature of the self-ignition of fuel TC-1 in the air atmosphere (500 K). The fuel supplied to the chamber into the atmosphere of the hot oxidant is self-propagated, in the future the combustion process goes into self-sustaining.

Oxidizer gasifier works on the principle of catalytic decomposition of highly concentrated hydrogen peroxide in the presence of a solid catalyst. Frameing hydrogen peroxide formed by the decomposition of hydrogen (a mixture of water vapor and gaseous oxygen) is an oxidizing agent and enters the combustion chamber.

The main parameters of the gas generator
Components:
- stabilized hydrogen peroxide (weight concentration),% - 85 ± 0.5
hydrogen peroxide consumption, kg / s - 0,476
Specific load, (kg / s hydrogen peroxide) / (kg of catalyst) - 3.0
continuous work time, not less, C - 150
Parameters of the vapor of the output from the gasifier:
- Pressure, bar - 16
- Temperature, k - 900

The gasifier is integrated into the design of the nozzle head. Her glass, inner and middle bottom form the gasifier cavity. The bottoms are connected between fuel nozzles. The distance between the bottom is regulated by the height of the glass. The volume between fuel nozzles is filled with a solid catalyst.

Reactive "Comet" of the Third Reich

However, Crigismarine was not the only organization that appealing to the turbine Helmut Walter. She intently became interested in the department of German Gering. As in any other, and this has been its beginning. And it is connected with the name of the employee of the Messerschmitt officer Alexander Lippisch, an ardent supporter of the unusual designs of aircraft. Not inclined to take generally accepted decisions and opinions on faith, he began to create a fundamentally new aircraft in which he saw everything in a new way. According to his concept, the aircraft must be easy, possess as little as possible mechanisms and auxiliary units, to have a rational in the point of view of creating a lifting force form and the most powerful engine.

The traditional piston engine Lippisch was not satisfied, and he turned his eyes to reactive, more precisely - to rocket. But all those known by the time the system of support with their cumbersome and heavy pumps, tanks, hilt and adjustment systems also did not suit it. So gradually crystallized the idea of \u200b\u200busing self-ignorant fuel. Then on board you can only place fuel and oxidizing agent, create the most simple two-component pump and combustion chamber with a reactive nozzle.

In this matter, Lippishu was lucky. And lucky twice. First, such an engine already existed - the same Valter turbine. Secondly, the first flight with this engine was already made in the summer of 1939 by the non-176 plane. Despite the fact that the results obtained, to put it mildly, did not impressive - the maximum speed that this aircraft reached the engine after 50 seconds was only 345 km / h, the Luftwaffe management counted this direction is quite promising. The reason for low speed they saw in the traditional layout of the aircraft and decided to test their assumptions on the "Neuthest" Lippisch. So the Messerschmittovsky Novator received at his disposal a glider DFS-40 and the RI-203 engine.

To power the engine was used (all very secret!) Two-component fuel consisting of T-STOFF and C-STOFF. Overland ciphers were hidden than the same hydrogen peroxide and fuel - a mixture of 30% hydrazine, 57% methanol and 13% water. The solution of the catalyst was named Z-STOFF. Despite the presence of three solutions, the fuel was considered two-component: a catalyst solution for some reason was not considered a component.

Soon the fairy tale affects, but no sooner is done. This Russian saying is how it is impossible to better describe the history of the creation of a missile fighter-interceptor. Layout, development of new engines, jetty, training of pilots - All this has delayed the process of creating a full-fledged machine until 1943. As a result, the combat version of the aircraft - M-163B - was a completely independent machine inherited from the predecessors only the base layout. The small size of the glider did not leave the space designers not to retractable chassis, none of the spacious cabin.

All space occupied fuel tanks and a rocket engine itself. And with him, too, everything was "not than glory to God." HA "Helmut Walter Veerke" calculated that the RII-211 RII-211 missile engine will have a thrust of 1,700 kg, and the fuel consumption of the total rush will be somewhere 3 kg per second. By the time of these calculations, the engine RII-211 existed only in the form of a layout. Three consecutive runs on Earth were unsuccessful. The engine is more or less managed to bring to the flight state only in the summer of 1943, but even then he was still considered experimental. And experiments again showed that the theory and practice often diverge with each other: fuel consumption was significantly higher than the calculated - 5 kg / s per maximum thrust. So Me-163V had a fuel reserve only six minutes of the flight on the full rift of the engine. At the same time, its resource was 2 hours of operation, which was on average about 20 - 30 departures. The incredible voyage of the turbine completely changed the tactics of the use of these fighters: take off, a set of height, entering the target, one attack, exit from the attack, return home (often, in a glider mode, as the fuel is no longer left). It was simply not necessary to talk about air battles, the entire calculation was on rapidness and superiority at speed. Confidence in the success of the attack was added and solid weapons "Comet": two 30 mm guns, plus the armored cabin of the pilot.

About problems that accompanied the creation of an aviation version of the engine Walter can say at least these two dates: the first flight of the experimental sample took place in 1941; The me-163 was adopted in 1944. Distance, as said one unsolving Griboedovsky character, a huge scale. And this is despite the fact that designers and developers did not spit into the ceiling.

At the end of 1944, the Germans made an attempt to improve the aircraft. To increase the duration of the flight, the engine was equipped with an auxiliary combustion chamber for flight on cruising mode with a reduced burden, increased fuel reserve, instead of a separate trolley installed a conventional wheel chassis. Until the end of the war, it was possible to build and test only one sample, which received the designation of Me-263.

Toothless "violet"

The impotence of the "Milestone Reich" before attacks from the air forced to look for any, sometimes the most incredible ways to counter carpet bombing of the allies. The task of the author does not include the analysis of all the wickers, with the help of which Hitler hoped to make a miracle and save if neither Germany, then himself from an imminent death. I will dwell on the same "invention" - the vertically-taking interceptor of the VA-349 "NATTER" ("Gadyuk"). This miracle of hostile technique was created as a cheap alternative to M-163 "Comet" with a focus on the mass production and the casting of materials. Its production provided for the use of the most affordable varieties of wood and metal.

In this brainchild, Erich Bachema, everything was known and everything was unusual. The takeoff was planned to exercise vertically as a rocket, with four powder accelerators installed on the sides of the rear of the fuselage. At an altitude of 150 m, the spent rockets were dropped and the flight continued at the expense of the main engine - the LDD Walter 109-509a is a certain prototype of two-stage missiles (or rockets with solid fuel accelerators). Guidance on the target was carried out first by automatically on the radio, and by the pilot by the pilot. No less unusual was the armament: approaching the goal, the pilot gave a volley from twenty-four,73-mm reactive shells installed under the fairing of the aircraft's nose. Then he had to separate the front of the fuselage and descend with parachute to the ground. The engine was also to be reset with parachute so that it could be reused. If desired, this can be seen in this and the "Shuttle" type is a modular aircraft with an independent return home.

Usually in this place they say that this project was ahead of the technical capabilities of the German industry, which explains the catastrophe of the first instance. But, in spite of such an in the literal sense of a word, the construction of another 36 "Hatters" was completed, of which 25 were tested, and only 7 in the piloted flight. In April 10 "Hatters" of the A-series (and who only counted on the next?) Were taken from Kiromem under Stildgart, to reflect the raids of American bomber. But the bashhema batch did not give the allies tanks, which they waited before bombers. "Hatter" and their launchers were destroyed by their own calculations. So argue after that, with the opinion that the best air defense is our tanks on their airfields.

Still, the attraction of the EDD was huge. So huge that Japan bought a license to produce a rocket fighter. Her problems with US aircraft were akin to German, because it is not surprising that they turned to the allies. Two submarines with technical documentation and equipment samples were sent to the shores of the Empire, but one of them was sweeping during the transition. The Japanese on their own restored the missing information and Mitsubishi built an experimental sample J8M1. In the first flight, on July 7, 1945, he crashed due to the refusal of the engine at a height set, after which the topic was safely and quietly died.

In order to reader, the reader did not have the opinion that instead of the inspired fruits, the distance of hydrogen brought its apologists only disappointment, I will bring an example, obviously, the only case when it was a sense. And it was received precisely when the designer did not try to squeeze the last drops of possibilities from it. We are talking about a modest, but necessary detail: a turbochargeable unit for feeding the fuel components in the Rocket A-4 (Fow-2). Serve the fuel (liquid oxygen and alcohol) by creating an overpressure in the tanks for the rocket of this class was impossible, but a small and light gas turbine at hydrogen peroxide and permanganate created a sufficient number of parogas to rotate the centrifugal pump.

Turbosas aggregate, steam-poase generator for a turbine and two small tanks for hydrogen peroxide and potassium permanganate were placed in one compartment with a propulsion unit. The spent parogase, passing through the turbine, still remained hot and could make additional work. Therefore, he was directed to the heat exchanger, where he heated a certain amount of liquid oxygen. By turning back to the tank, this oxygen created there a small prediment, that somewhat facilitated the operation of the turbosate unit and at the same time warned flattening the walls of the tank when it became empty.

The use of hydrogen peroxide was not the only possible solution: it was possible to use the main components, feeding them into the gas generator in the ratio, far from optimal, and thereby ensuring a decrease in the temperature of combustion products. But in this case it would be necessary to solve a number of complex problems associated with ensuring reliable ignition and maintain stable burning of these components. The use of hydrogen peroxide in the middle concentration (here the exhaust capacity was for nothing) allowed to solve the problem simply and quickly. So a compact and uniform mechanism forced to fight the deadly heart of a rocket stuffed with a ton explosive.

Blow from depth

The name of the book of Z. Pearl, as it is thought to be the author, as it is impossible to suit the name and this chapter. Without seeking a claim for the truth in the last instance, I still allow myself to say that there is nothing terrible than the sudden and practically inevitable blow to the board of two or three centners of TNT, from which the bulkheads are bursting, the steel is burned and flourished with multi-torque mechanisms. The roar and whistle of the burning couple becomes a requiem ship, which in cramps and convulsions goes under the water, having taken with me to the kingdom of Neptune of those unfortunate who did not have time to jump into the water and saved away from the sinking vessel. And a quiet and imperceptible, similar to the insulatory shark, the submarine slowly dissolved in the sea depth, carried in its steel womb of a dozen of the same deadly hotels.

The idea of \u200b\u200ba self-applied miner, capable of combining the speed of the ship and the gigantic explosive force of the Anchor "Flyer", appeared quite a long time. But in the metal, it was realized only when there were enough compact and powerful engines that have reported to it a great speed. Torpeda is not a submarine, but also its engine is also needed fuel and oxidizer ...

Torped-killer ...

It is so called the legendary 65-76 "KIT" after the tragic events of August 2000. The official version states that the spontaneous explosion of "Tolstoy Torpeda" caused the death of a submarine K-141 Kursk. At first glance, the version, at a minimum, deserves attention: Torpeda 65-76 - not at all children's rattle. This is dangerous, the appeal to which requires special skills.

One of the "weaknesses" torpedoes was called its propulsion - the impressive shooting range was achieved using the propulsion at the hydrogen peroxide. And this means the presence of an entirely familiar bouquet of charms: giant pressure, rapidly reacting components and the potential opportunity to start an involuntary explosive response. As an argument, supporters of the explosion version of the "Tolstoy Torpeda" leads such a fact that all "civilized" countries of the world refused from the torpedo at hydrogen peroxide.

Traditionally, the oxidizer reserve for the torpedo engine was a balloon with air, the amount of which was determined by the power of the unit and the distance of the stroke. The disadvantage is obvious: the ballast weight of a thick-walled cylinder, which could be reversed for anything more useful. To store air pressure up to 200 kgf / cm² (196 GPa), thick-walled steel tanks are required, the mass of which exceeds the mass of all energy components by 2.5 - 3 times. The latter accounts for only about 12 - 15% of the total mass. For the operation of the ESU, a large amount of fresh water is necessary (22-6% of the mass of energy components), which limits the reserves of fuel and oxidizing agent. In addition, compressed air (21% oxygen) is not the most efficient oxidizing agent. The nitrogen present in the air is also not just ballast: it is very poorly soluble in water and therefore it creates a well-noticeable bubble mark 1 - 2 m wide for a torpedo. However, such torpedo had no less obvious advantages that were a continuation of the shortcomings, most importantly of which are high security. Torpedes operating on pure oxygen (liquid or gaseous) were more effective. They significantly reduced the tracks, increased the efficiency of the oxidant, but did not solve the problems with the milking (the balloon and cryogenic equipment still constituted a significant part of the weight of the torpedo).

Hydrogen peroxide in this case was a kind of antipode: with significantly higher energy characteristics, it was the source of increased danger. When replaced in the air thermal torpedo of compressed air to an equivalent amount of hydrogen peroxide, its range has managed to increase 3 times. The table below shows the efficiency of using various types of applied and promising energy carriers in Esu Torpeda:

In Esu Torpeda, everything occurs in the traditional way: the peroxide is decomposed on water and oxygen, oxygen oxidizes fuel (kerosene), the received steamer rotates the turbine shaft - and here the deadly cargo rushes towards the ship.

Torpeda 65-76 "KIT" is the last Soviet development of this type, the beginning of which put in 1947 the study of the German torpedoes not brought to the "to mind" in the Lomonosov branch of the NII-400 (later "Mortheterery") under the leadership of the chief designer D.A . Cochenakov.

The works ended with the creation of a prototype, which was tested in Feodosia in 1954-55. During this time, the Soviet designers and Materialists had to develop the mechanisms unknown to them until the mechanisms, to understand the principles and thermodynamics of their work, to adapt them for compact use in the body of the Torpeda (one of the designer somehow said that the complexity of torpedoes and cosmic missiles are approaching the clock ). As an engine, a high-speed turbine of an open type of own development was used. This unit spoke a lot of blood to its creators: problems with the sorceration of the combustion chamber, searching for the storage capacity of peroxide, the development of the fuel component regulator (kerosene, low-water hydrogen peroxide (concentration 85%), sea water) - All this has been tested and tested to the torpedoes before 1957 This year, the fleet received the first torpedo at hydrogen peroxide 53-57 (According to some data, it had the name "Alligator", but perhaps it was the name of the project).

In 1962, the anti-religious self-equipped torpedo was adopted 53-61 created on the basis of 53-57 and 53-61m with an improved homing system.

Torped developers paid attention not only to their electronic stuffing, but did not forget about her heart. And it was, as we remember, quite capricious. To increase the stability of work while increasing the capacity, a new turbine was developed with two combustion chambers. Together with the new filling of the homing, she received an index 53-65. Another engine modernization with an increase in its reliability gave a ticket to the life of modification 53-65m.

The beginning of the 70s was marked by the development of compact nuclear ammunition, which could be installed in the BC torpedo. For such a torpedo, the symbiosis of powerful explosives and a high-speed turbine was quite obvious and in 1973 unmanaged peroxidant torpedo was adopted 65-73 With a nuclear warhead, designed to destroy large surface ships, its groupings and coastal objects. However, the sailors were not only interested in such purposes (and most likely - not at all) and after three years she received an acoustic guidance system for a brilvater trail, an electromagnetic fuse and an index 65-76. The BC also became more universal: it could be both nuclear and carry 500 kg of ordinary trout.

And now the author would like to pay a few words to the thesis about the "bearing" of countries having torpedoes on hydrogen peroxide. First, in addition to the USSR / Russia, they are in service with some other countries, for example, a Swedish heavy torpedo TR613, which has developed in 1984, operating on a mixture of hydrogen peroxide and ethanol, is still in service with Navy of Sweden and Norway. The head in the FFV TP61 series, Torpeda TP61 was commissioned in 1967 as a heavy controlled torpedo for use by surface ships, submarines and coastal batteries. The main energy installation uses hydrogen peroxide with ethanol, resulting in an action of a 12-cylinder steam machine, providing a torpedo to almost complete failure. Compared to modern electric torpedoes, at a similar speed, the running distance is 3 - 5 times more. In 1984, a longer-range TP613 was admitted, replacing TP61.

But the scandinavians were not alone on this field. Prospects for the use of hydrogen peroxide in military affair were taken into account by the US Navy before 1933, and before the US joining the Warrior on the sea torpedo station in Newport, there were strictly classified work on torpedo, in which hydrogen peroxide was supplied as an oxidizing agent. In the engine, a 50% solution of hydrogen peroxide decomposes under pressure with an aqueous solution of permanganate or other oxidizing agent, and decomposition products are used to maintain the burning of alcohol - as we can see the scheme after the story. The engine was significantly improved during the war, but torpedoes leading to movement with hydrogen peroxide, until the end of hostilities did not find combat use in the US Flot.

So not only "poor countries" considered peroxide as an oxidizing agent for torpedo. Even quite respectable United States gave tribute to such a rather attractive substance. The reason for refusing to use these Esu, as it seems to the author, it was not in the cost of the development of ESU on oxygen (in the USSR, such torpedoes were also successfully applied and successfully used, which perfectly showed themselves in various conditions), and in all the same aggressiveness, danger and disrupor Hydrogen peroxide: No stabilizers guarantee a 100% guarantee of lack of decomposition processes. What it can end, tell, I think, do not ...

... and torpedo for suicides

I think that such a name for the sad and widely known controlled torpedo "Kaiten" is more than justified. Despite the fact that the leadership of the Imperial Fleet required the introduction of a evacuation hatch into the structure of "man-torpedoes", the pilots did not use them. It was not only in the samurai spirit, but also an understanding of a simple fact: to survive when an explosion in the water of a semi-trifle wip, being at a distance of 40-50 meters, it is impossible.

The first model "Kaitena" "Type-1" was created on the basis of 610 mm oxygen torpedo "Type 93" and was essentially its enlarged and habitable version, occupying a niche between the torpedo and mini-submarine. The maximum range of speed at a speed of 30 nodes was about 23 km (at the rate of 36 knots under favorable conditions, it could pass to 40 km). Created at the end of 1942, it was then not adopted on the weapon of the fleet of the rising sun.

But by the beginning of 1944, the situation has changed significantly and the project of weapons that can realize the principle "Each Torpeda - to the goal" was removed from the shelf, Gleie he dust almost a year and a half. What made the admirals change their attitude, to say it's difficult: if the letter of designers of Lieutenant Nisima Sakio and senior lieutenant of Hiroshi Cuppet, written in its own blood (Code of honor required to immediately read such a letter and providing an argued response), then a catastrophic position on the sea TVD. After small modifications "Kaiten Type 1" in March 1944 went to the series.

But in April 1944, work began on its improvement. Moreover, it was not about the modification of the existing development, but on the creation of a completely new development from scratch. It was also a tactical and technical task issued by the fleet to the new "Kaiten Type 2", included the maximum speed of at least 50 nodes, the distance of -50km, the depth of dive -270 m. Work on the design of this "man-torpedo" was charged by Nagasaki-Heiki K.K., which is part of Mitsubishi's concern.

The choice was non-random: as mentioned above, it was this firm who actively led the work on various rocket systems based on hydrogen peroxide on the basis of information received from German colleagues. The result of their work was "Engine No. 6", operating on a mixture of hydrogen peroxide and hydrazine with a capacity of 1500 hp.

By December 1944, two prototypes of the new "man-torpedo" were ready for testing. The tests were carried out on the ground stand, but the demonstrated characteristics of neither the developer nor the customer were satisfied. The customer has decided not to even start marine tests. As a result, the second "Kaiten" remained in the number of two pieces. Further modifications were developed under the oxygen engine - the military understood that even such a number of hydrogen peroxide their industry is not released.

On the effectiveness of this weapon, it is difficult to judge: the Japanese propaganda of the time of war almost every occasion of the use of "Kaitenov" attributed the death of a large American ship (after the war, conversations on this topic for obvious reasons were subsided). The Americans, on the contrary, are ready to swear on anything that their losses were meager. Will not be surprised if after a dozen years they will generally be denied those in principle.

Star hour

The works of German designers in the field of turbochargeable aggregate design for the FAu-2 missile did not remain unnoticed. All German developing armaments that have come to us have been thoroughly investigated and tested for use in domestic structures. As a result of these works, turbocharging units operating on the same principle as the German prototype appeared. American rackets naturally also applied this decision.

The British, practically lost during the Second World War all their empire, tried to cling to the remnants of the former greatness, using a full coil using a trophy heritage. Without practically no workflow in the field of rocket technology, they focused on what they had. As a result, they were almost impossible: the Black Arrow rocket, which used a pair of kerosene - hydrogen peroxide and porous silver as a catalyst provided the UK place among cosmic powers. Alas, a further continuation of the Space Program for the rapidly drastic British Empire turned out to be an extremely costly occupation.

Compact and pretty powerful peroxidant turbines were used not only for fuel supply in combustion chambers. It was applied by Americans for the orientation of the descent apparatus of the Mercury spacecraft, then with the same purpose, the Soviet constructors on the CA KK "Union".

In its energy characteristics, the peroxide as an oxidizer is inferior to liquid oxygen, but superior to nitric acid oxidizers. In recent years, interest has been reborn in the use of concentrated hydrogen peroxide as rocket fuel for engines of various scales. According to experts, the peroxide is most attractive when used in new developments, where previous technologies cannot compete directly. Such developments are the satellites weighing 5-50 kg. True, skeptics still believe that its prospects are still foggy. So, although the Soviet EDRD of the RD-502 (fuel pair - peroxide plus pentabran) and demonstrated the specific impulse of 3680 m / s, it remained experimental.

"My name is Bond. James Bond"

I think, hardly there are people who did not hear this phrase. Some fewer fans of "spy passions" will be able to call without a trip of all performers of the role of Supergent Intelligence Service in chronological order. And absolutely fans will remember this not quite ordinary gadget. At the same time, and in this area did not cost without an interesting coincidence that our world is so rich. Wendell Moore, Engineer of Bell Aerosystem and Single-Feathers of one of the most famous performers, became an inventor and one of the exotic means of movement of this eternal character - flying (or rather jumping).

Structurally, this device is as simple as fantastic. The foundation was three cylinders: one with a compressed to 40 atm. Nitrogen (shown in yellow) and two with hydrogen peroxide (blue color). The pilot turns the control knob and the valve controller (3) opens. Compressed nitrogen (1) displaces the liquid peroxide of hydrogen (2), which enters the tubes in the gas generator (4). There it comes into contact with the catalyst (thin silver plates covered with a layer of samarium nitrate) and decompose. The resulting steaway mixture of high pressure and temperature enters two pipes, emerging from the gas generator (pipes are covered with a layer of heat insulator to reduce heat loss). Then the hot gases are entered into the rotary jet nozzles (nozzle of the footer), where they first accelerate, and then expand, purchasing supersonic speed and creating a reactive traction.

Pold control and wheelchair knobs are mounted in a box that is reinforced on the pilot breast and are connected to the aggregates through cables. If you needed to turn to the side, the pilot rotated one of the handicrafts, rejecting one nozzle. In order to fly forward or backward, the pilot rotated both handwheel at the same time.

So it looked in theory. But in practice, as it often happened in the biography of hydrogen peroxide, everything turned out not quite so. Or rather, it is not like this: the wrath was not able to make a normal independent flight. The maximum duration of the rocket waller flight was 21 seconds, a range of 120 meters. At the same time, the satisfied was accompanied by a whole team of service personnel. For one twenty-second flight, up to 20 liters of hydrogen peroxide were consumed. According to the military, Bell Rocket Belt was rather a spectacular toy than an effective vehicle. The expenses of the army under the contract with Bell Aerosystem amounted to $ 150,000, another 50,000 dollars spent Bell herself. From further financing the program, the military refused, the contract was completed.

And yet it was still possible to fight with the "enemies of freedom and democracy", but only not in the hands of the Sons of Uncle Sam, but behind the shoulders of the film-super-super-survey. But what will be his further fate, the author will not make assumptions: ungrateful this thing is the future to predict ...

Perhaps, in this place, the story of the military quarry of this conventional and unusual substance can be put in the point. She was like in a fairy tale: and not long, and not short; and successful and failure; and promising, and unpromising. He was referred to him a great future, they tried to use in many energy-generating installations, disappointed and returned again. In general, everything is like in life ...

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