RU2425244C2 - Golodyaev launching booster for rockets - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: launching booster for rocket includes engine housing, nozzle with a cap, transportation and startup conveyor at the bottom of which there located is engine housing and combustion chamber in which thermoemitting element, ignition device and working medium is located. Working medium represents liquid material forming superheated steam during combustion of thermoemitting element. Thermoemitting element is made from thermit mixture in the form of hollow tube with walls of cyclically variable thickness and covered on all sides with thin-wall metal with high heat conductivity. Inside combustion chamber coaxially to thermoemitting element there located is heat resistant tube having the length equal to the length of thermoemitting element. Pump with drive for supply of working medium to lower part of combustion chamber to thermoemitting element is located immediately above engine housing; at that, smaller part of working medium returns from pump to hollow cavities of tanks for their wetting.

EFFECT: higher reliability of launching booster.

1 dwg

Description

The invention relates to aviation and astronautics, in particular to jet engines capable of operating both in the atmosphere and in space, namely, rocket technology, launch accelerators for aircraft, launch accelerators for long-range anti-aircraft missiles as a short-pulse launch accelerator of high power, or third stage rockets.

The aim of the invention is the creation of a launch accelerator for missiles with actively reactive (mortar) launch, providing:

- environmental cleanliness,

- with the possibility of long-term storage,

- capable of helping the missile to overcome the missile defense system in the active part of the flight due to the absence of a light pulse at launch to a height of 10-25 km, i.e. above the cloudy layer of the atmosphere, which greatly gives off the luminosity of ordinary rocket launches, and due to the location of the water tanks outside the transport and launch container,

- cheap

- fireproof and explosion proof from an external heat source.

Known:

1. - The name "REACTIVE ENGINE", publication number No. 2313683. Application # 2006123116/06, C1. Publication date 2007.12.27, RU, 2006.06.30, 2007.12.27 IPC index F02K 7/00 (2006.01).

A jet engine comprises a hollow body with a diffuser at one end thereof and an output nozzle at the other, as well as a device for igniting the fuel mixture installed in the body. The engine is equipped with a fuel chamber mounted in the housing in such a way that the inner surface of the housing and the outer surface of the fuel chamber form a diffusion gap, with a fairing installed at the end of the fuel chamber facing the diffuser and an outlet nozzle at its other end in the cavity of the fuel chamber having the ability to connect to the fuel tank, a heater is placed, and a fuel valve is located at its outlet, while the device for igniting the fuel mixture is located behind the outlet nozzle of the fuel chamber. The fuel chamber or fairing can be mounted axially displaceable in the housing, and nozzles can be installed on the housing for supplying the fuel mixture component to the diffusion gap. A jet engine may contain several housings fastened in a block, with a fuel chamber in each of them. The invention provides a simplification of design and cost reduction (analogue).

The disadvantage of this design is the design complexity, the presence of separate fuel chambers and a combustion chamber, a combustible working fluid is used - a fuel mixture, the high cost of components and fuel mixture, a high degree of fire hazard in running order, because most flammable liquids ignite at temperatures below 500 degrees Celsius, and with a certain oxidizer-fuel ratio, an engine explosion is possible. Organic chemistry products used as fuels are mostly toxic to humans. Bright radiation in the optical range at the time of launch and flight in a dense atmosphere (through the clouds), which makes it easy to fix the launch of the rocket in the optical range.

2. - The name "REACTIVE ENGINE OF SOLID FUEL", publication number No. 2141571, C1, Date of publication. 1999.11.20, RU. Application No. 97109228/06. Application submission date 1997.05.30. Published 1999.11.20, IPC6, F02K 9/00.

A jet engine of solid fuel, to increase the efficiency of the design of the combustion chamber, streamlining the process of gas outflow, increase traction, improve the reliability and safety of the design of the rocket engine, is achieved in a jet engine of solid fuel containing a housing, a cylindrical fuel charge with a combustion chamber made in it, according to the invention the combustion chamber has the shape of a cone of non-combustible material with holes for the passage of gases, facing its apex in the direction of travel, and inside oplivnogo charge has metal strips on which the electric current is supplied to create an electric arc (prototype).

The disadvantage of this design is the presence of easily combustible solid fuel, its explosiveness, the possibility in different temperature conditions of the environment to non-linear combustion of the fuel and to its explosion. Bright radiation in the optical range at the time of launch and flight in a dense atmosphere (through the clouds), which makes it easy to fix the launch of the rocket in the optical range.

3. - The name "Golodyaev's Jet Engine" MPK6 F02K 7/00, MPK6 F02K 9/00, application for invention No. 200911699. Positive decision 11.01.2010. The author and applicant A. Golodyaev Correspondence address: 394088, Voronezh, ul. gene. Lizyukova 99-47.

A jet engine comprising a housing, a nozzle with a plug, a combustion chamber in which a thermally emitting element from a thermite mixture and an ignition device are located, and the working fluid turns into superheated steam when the thermally emitting element is burned, characterized in that the heat emitting element is made in the form of a cylindrical hollow tube with walls of cyclically variable thickness, the surface of the heat-generating element located from the nozzle to the rear wall of the engine is covered on all sides with a thin-walled metal with high heat conductivity, the working fluid is located in the cavities of the combustion chamber and is a liquid or solid material, the combustion chamber is divided by thin-walled sealing bulkheads across the heat-generating element into one or more compartments, a heat-resistant tube having a length equal to the length of the heat-generating element is located inside the combustion chamber coaxially with the heat-generating element ( analogue).

The disadvantage is that the volume of the working fluid is equal to the volume of the working chamber, and this does not allow the rocket body to be protected by the working fluid when starting from the thermal effect of an optical quantum generator (laser) of the ABM system.

4. - A technical solution is known to US 3082666 A, IPC P41P 3/00, 1963, Fig.2, 8, in the dock 17 l.

A rocket launch accelerator comprising an engine casing, a nozzle with a plug, a combustion chamber in which a heat-generating element is located, an ignition device and a working fluid, which is a liquid material and forms superheated steam when burning a heat-generating element (prototype).

The disadvantage is the lack of protection of the missile body from damage by its energy pulse from high-power quantum generators of the missile defense system.

Technical result: the solution is a rocket launch accelerator containing an engine casing, a nozzle with a plug, a combustion chamber in which there is a heat-generating element, an ignition device and a working fluid, which is a liquid material and generates superheated steam when the heat-generating element is burning, characterized in that it contains transport and launch container, at the bottom of which the engine housing is located, while the working fluid is additionally located in tanks outside the transport and launch container, term the ejection element is made of a thermite mixture in the form of a hollow tube with walls of cyclically variable thickness and is coated on all sides with a thin-walled metal with high heat conductivity, a heat-resistant tube is located inside the combustion chamber, coaxial to the heat-emitting element, having a length equal to the length of the heat-emitting element, while directly above the body the engine is a pump with a drive for supplying a working fluid to the lower part of the combustion chamber to the heat-generating element, and a small part of the working fluid returns about t of pump into empty tank cavities to wet them

Thus, the rocket, together with its transport and launch container, launches and takes off from the ground. After the working fluid is developed at a height of 10-25 km from the earth, a mortar launch of the rocket takes place. The transport and launch container falls to the ground by parachute, and the rocket continues to fly toward the target, already having a high initial speed (the speed of the transport and launch container at the time of separation). To protect against a laser pulse, the empty internal cavities of the tanks are wetted with a working fluid.

Preferably termites are used as the heat release element. In the 60s of the last century, the outstanding Russian scientist N.N. Beketov carried out the reaction of interaction between barium oxide and aluminum and this, as well as his further research on the production of alkali metals and the action of metallic aluminum on their compounds, laid the foundation for a new branch of metallurgy - aluminothermy. The reactions proceeding according to the scheme MO + M1 = M1O + M + Q kcal, where MO is the metal oxide and M1 is the metal used for reduction (aluminum), were called aluminothermic reactions, and the reactive mixtures of metal oxides with another metal were called termites . As an example, we can cite the well-known combustion reaction of iron-aluminum termite: Fe ₂ O ₃ + 2Al = 2Fe + Al ₂ O ₃ +198 kcal.

Aluminothermic reactions have found great application in the civilian industry to produce a large number of pure carbon-free metals: chromium, manganese, etc. Iron-aluminum termite is widely used for welding ferrous metals (aluminothermic welding of rails). The characteristic features that distinguish the process of burning termites from the burning of other pyrotechnic compositions are:

1) the absence of gaseous reaction products during combustion, which determines the flamelessness of combustion;

2) high temperature of the combustion reaction; for most termites used, it is in the range of 2000-2800 ° C;

3) the formation during combustion of molten fire-liquid slag.

Among other qualities, it is necessary to indicate the difficulty of igniting termites (the self-ignition temperature of all aluminum termites is higher than 800 ° С, the self-ignition temperature of iron-aluminum termite is 1300 ° С) and the high density due to the use of oxides having a large specific gravity (for example, Fe ₂ O ₃ - specific weight 5.1).

According to experiments, the amount of heat released during the burning of termites should be at least 0.55 kcal per 1 g of composition; otherwise, the combustion reaction proceeds with difficulty and does not reach the end. Based on this situation and taking into account the large amount of heat that should be spent on the decomposition of metal oxide, it becomes obvious that only high-calorie combustibles can be used in termites. The properties of some simple substances characterizing the possibility of their use in termites are shown in Table 1. The most suitable fuel for termites, both in calorific value and significant specific gravity, and in the relatively low melting temperature (2050 ° С) of the oxide, is aluminum. The use of magnesium, in addition to economic considerations and low specific gravity, is hindered by the still high melting point of its oxide (2800 ° С).

Fuel for termites

Table 1

Fuel Specific gravity of fuel Oxide Formula Heat of formation of oxide, counting per 1 g-atom of oxygen Termite Recipe Thermal effect of combustion of 1 g of termite, kcal % Fe ₂ O ₃ % fuel Al 2.7 Al ₂ O ₃ 131 75 25 0.93 Mg 1.7 MgO 146 69 31 1.05 Sa 1,5 Cao 152 57 43 0.93 Ti 4,5 TiO ₂ 109 69 31 0.57 Si 2,3 SiO ₂ 104 79 21 0.58 B 2,3 B ₂ O ₃ 101 88 12 0.59

It was established by experience that iron-magnesium termite does not produce liquid spreading toxins at all. The use in termites of Ca, Ti, Si, and B as individual fuels does not seem appropriate, but their alloys may be of some interest in this regard. The termite, in which the CaSi alloy was taken as fuel (in a weight ratio of 2: 1), produced very low-melting slags. The CaSi alloy is quite corrosion resistant in air, and the thermal effect of a termite made with its participation is 0.7 kcal / g; the presence of silicon in the termite slows down the combustion process. Lowering the solidification temperature of slag occurs due to the formation of calcium silicate CaSiO ₃ having a melting point of 1512 ° C. The special fusibility of the slag resulting from the combustion of a mixture of two termites - iron-aluminum and iron-calcium, taken in a weight ratio of 60:40. The thermal effect of such a mixture is 0.9 kcal / g. The compound 5CaO · 3Al ₂ O ₃ melts at a temperature of about 1400 ° C. Aluminosilicates formed during the combustion of iron-aluminum termite containing silicon have a higher melting point. So, sillimanite Al ₂ O ₃ · SiO ₂ melts three 1816 ° C. The oxide used to make termites must satisfy the following requirements:

1) have a minimum heat of formation;

2) contain a sufficient amount of oxygen (not less than 25-30%);

3) have the largest possible specific gravity;

4) to be reduced to a metal having a low melting point and a high boiling point.

The properties of some oxides are shown in table 2.

table 2

Oxide Heat of formation of oxide, counting per 1 g-atom of oxygen The oxygen content in the oxide,% Specific gravity of oxide Termite Recipe Thermal effect of combustion of 1 g of termite, kcal % oxide % aluminum B ₂ O ₃ 101 69 1.8 56 44 0.73 SiO ₂ 104 53 2.2 63 37 0.56 Cr ₂ O ₃ 90 32 5.2 74 26 0.60 MnO ₂ 62 37 5,0 71 29th 1.12 Fe ₂ O ₃ 66 thirty 5.1 75 25 0.93

CuO 38 twenty 6.41 81 29th 0.94 Pb ₃ O ₄ 43 9 9.1 90 10 0.47

Chromium melts at 1800 ° C, boils at 2300 ° C. Copper melts at 1083 ° C, boils at 2360 ° C. Oxides of elements with low atomic weight are unsuitable for use in termites due to the fact that they have significant heat of formation and low specific gravity. The use of metal oxides with a large atomic weight (for example, Pb ₃ O ₄ ) is impeded by the low oxygen content in them; termites made with their participation contain little fuel and produce insufficient heat during combustion. The most appropriate should be considered the use in termites of metal oxides having an average atomic weight [about 40 to 80 (see table)]. Copper oxide in the presence of appropriate reducing agents very easily gives off its oxygen; The burning of copper-aluminum termite proceeds at high speeds and resembles an explosion. The manganese metal released during combustion of manganese-aluminum termite has a lower boiling point (2000 ° С) compared with iron; during combustion, its rapid evaporation occurs:

3MnO ₂ + 4Al-3Mn + 2Al ₂ O ₃ +411 kcal.

Chrome-aluminum termite burns relatively slowly, but emits significantly less heat when burning than other termites:

Cr ₂ O ₃ + 2Al = 2Cr + Al ₂ O ₃ +123 kcal.

The most acceptable from all points of view should be considered the use of iron-aluminum termite as an incendiary composition. For the manufacture of iron-aluminum termite, iron oxide (Fe ₂ O ₃ ) and iron oxide Fe ₃ O ₄ (ferrous oxide) are more often used. The equation for the termite combustion reaction in this case is as follows:

3Fe ₃ O ₄ + 8Al = 4A1 ₂ O ₃ + 9Fe + 774 kcal, where:

W (Fe ₃ O ₄ ) = 76%

W (Al) = 24%

W (Al ₂ O ₃ ) = 45%

W (Fe) = 55%

One of the positive factors of iron-aluminum termite should be considered low fluidity and rapid solidification of the slags formed during its combustion. Powdered iron-aluminum termite has a gravimetric density of 1.8-2.0, compressed (with the addition of several percent cement) - 3-3.4. On presses of high power, allowing for pressures of the order of 3000-6000 kg / cm ² , the termite is well pressed and without the addition of a cementer; compressed termite has great mechanical strength. For the manufacture of termite take iron oxide and aluminum powder coarsely ground (sieve No. 8-10); the presence of dust is not allowed, since its presence greatly accelerates the termite combustion process. Termite samples of conventional grinding without pressing in weighing 1 kg burn for 15-20 seconds; the same samples, but pressed under a pressure of 200 kg / cm ² , burn for 35-50 seconds. A termite briquette weighing 1 kg, having the shape of a cylinder with a height of 15.5 cm and a diameter of 5.5 cm, burns out in 40 seconds. 50 g of termite melt a sheet of iron 2 mm thick for several seconds. Pure iron-aluminum termite, which does not contain additives, is non-explosive, insensitive to lumbago bullet and very little sensitive to both mechanical and thermal influences. Ignition of iron-aluminum termite can not be carried out either with the help of matches, or from stopin, or from conventional igniter compositions. To ignite the powdered termite, several different mixtures are proposed. All of them contain magnesium fuel or finely ground aluminum powder as fuel.

Ignition mixtures:

SiO ₂ - 55%

Magnesium - 45%

MnO ₂ - 68%

Aluminum powder - 7.5%

Aluminum powder - 7.5%

Magnesium powder - 17%

BaO ₂ - 88%

Magnesium - 12%

A.A.Shidlovsky. Fundamentals of pyrotechnics. Moscow.

As the working fluid, it is preferable to use water H ₂ O. The weight of 1 mole of water is 18 grams. In the vapor state, in the form of gas under normal conditions, has a volume of 22.4 liters. 1800 grams of water is 100 moles or 2240 liters of saturated water vapor. If this steam is heated to a temperature of 100 ° C, then taking into account the coefficient of volumetric expansion of gases (Gay-Lusaka) equal to 0.00366 per 1 degree, the volume of steam will be 3060 liters, and when heated to 1500 ° C, the volume in 14537 liters. 1 gram of rocket fuel based on ammonium nitrate with hexogen and aluminum powder emits about 2 liters of gas, and 1800 grams produce about 3600 liters of gas, which is about 30 percent relative to superheated steam. Given the weight of the termite, the excess of the vapor volume over the volume of powder gases is approximately 1.5 times at a steam temperature of 700 ° C, and 2 times at a steam temperature of 1500 ° C.

The best performance in iron-aluminum termite

3Fe ₃ O ₄ + 8Al = 4Al ₂ O ₃ + 9Fe + 774 kcal.

If in a closed volume equal to the volume of water heat water to 400 ° C, then the water will be in the form of steam at any pressure. Those. 774 kcal of heat from 3 moles of iron oxide and 8 moles of aluminum can heat up to 774 ° C 1000 grams of water, or about 450 grams of water to a temperature of approximately 1500 ° C. This creates a simultaneous pressure in the initial fluid volume of 1.8 liters per 8000 kg per square centimeter. The calculated cross section of the engine nozzle allows you to keep the pressure within 100-400 kg per square centimeter, which means that if there is a large excess of the working fluid inside the combustion chamber, it will be ejected through the nozzle with a steam outlet speed, which will increase engine thrust. For normal engine operation, it is enough to create a volume of steam that constantly maintains pressure within the strength of the engine body, and the remaining volume can be occupied by water with a low temperature. This effect is provided by the properties of molten metal: create a layer of superheated gas around the metal. And the magnitude of this gas depends on the burning area of the termite. The area is provided by the wavy surface of the termite (cyclic variable thickness). T.O. the volume of water can many times exceed the volume and mass of termite.

The drawing shows "Golodyaev's launch accelerator for missiles."

Statics

The launch accelerator for a rocket (see drawing) consists of an engine casing (1), a nozzle (2) with a plug (3), a combustion chamber (4), in which there is a heat-generating element (5), an ignition device (6) and a working fluid (7), which is a liquid material (8) and which forms superheated steam (9) when the heat-generating element (5) is burning, differs in that it contains a transport-launch container (10), at the bottom (11) of which is the engine body (1) ), while the working fluid (7) is additionally located in the tanks (12) outside the transport and launch container (10), the heat-generating element (5) is made of a thermite mixture in the form of a hollow tube (13) with walls (14) of cyclically variable thickness and coated on all sides with a thin-walled metal (15) with high thermal conductivity, inside the combustion chamber (4), coaxial to the heat-generating element (5), a heat-resistant tube (16) is located, having a length equal to the length of the heat-generating element (5), while a pump (17) with a drive (18) for supplying the working fluid (7) is located directly above the motor housing (1) ) to the lower part (19) of the combustion chamber (4) to the heat-generating element y (5), and a small portion of the working body (7) is returned from the pump (17) in the empty cavities (20), tanks (12) for their wetting

Work

During the combustion of the heat-generating element (5), the working fluid is transformed into superheated steam. From the lower part (19) of the combustion chamber (4), steam (9) passes around a heat-generating element (5) along its walls (14) with a cyclically variable thickness, which provide a large area of contact between the steam (9) and the working fluid (7) with the heat-generating element (5). Next, steam (9) enters the heat-resistant tube (16) and goes through it to the nozzle (2). A small part of the working fluid (7) goes back to the tanks (12) located around the launch container (10), and wets the outer walls (22) of the tanks (12). This eliminates the overheating of the walls of the launch container (10) from the energy of the quantum generator of the ABM system. The launch accelerator works without emitting a powerful light pulse, which means that the rocket launch does not illuminate the launch site and the surrounding clouds, and it cannot be fixed with optical instruments from reconnaissance satellites. Thermal radiation (infrared) will be detected by reconnaissance satellite devices only at the starting point of a small area (soil heating point) and an inversion trace comparable to that of a heavy aircraft. The launch of the rocket (21) from the transport and launch container (10) occurs at a height significantly higher than the cloud layer (in the stratosphere). The rocket (21) already has a significant speed, the flash and the light from burning the fuel of the engine is already less noticeable, while the rocket can fly a much greater distance to the target, or take more weapons with it. Due to the high flight speed, it will be very difficult to get into the body of a flying rocket (21) and keep the momentum of a quantum generator in one place for warming up before the destruction of the rocket.

Technical and economic indicators relative to the prototype are much higher, because allow you to save a larger number of missiles from the missile defense system.

The list of positions:

1 - engine housing

2 - nozzle

3 - stub

4 - combustion chamber

5 - thermal element

6 - ignition device

7 - working fluid

8 - liquid material

9 - superheated steam

10 - transport and launch container

11 - bottom of the container (10)

12 - tank

13 - thermite hollow tube mixture

14 - wall cyclically variable thickness

15 - thin-walled metal

16 - heat-resistant tube

17 - pump

18 - drive

19 - lower part of the combustion chamber

20 - tank cavity

21 - rocket

22 - the outer wall of the tank

Claims (1)

A launch booster for a rocket comprising an engine casing, a nozzle with a plug, a combustion chamber in which there is a heat-generating element, an ignition device and a working fluid, which is a liquid material and generates superheated steam when the heat-generating element is burned, characterized in that it contains a transport-launch container , at the bottom of which the engine housing is located, while the working fluid is additionally located in the tanks outside the transport and launch container, the heat-generating element is made of ter of a hollow tube in the form of a hollow tube with walls of cyclically variable thickness and coated on all sides with a thin-walled metal with high thermal conductivity, a heat-resistant tube having a length equal to the length of the heat-generating element is located inside the combustion chamber coaxially with the heat-generating element, and a pump with a drive is located directly above the engine case for supplying the working fluid to the lower part of the combustion chamber to the heat-generating element, and a small part of the working fluid is returned from the pump to the empty cavity of the tanks for and x wetting.

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