RU2846645C2 - Space bomber interceptor - Google Patents

Abstract

FIELD: aviation; astronautics.

SUBSTANCE: invention relates to aircraft and aerospace engineering, namely to hypersonic interceptors. Space bomber interceptor comprises first and second combat stages. First stage is made in the form of three cylindrical solid-propellant tanks with rocket engines in the lower part, equipped with wings and vertical stabilizers located perpendicular to the attachment plane. Second stage is equipped with laser weapons and four liquid-propellant rocket engines running on liquid hydrogen and oxygen with central body arranged there between. Oxygen feed pipeline runs inside hydrogen tank while both fuel components are fed via interconnected pipelines to all engines.

EFFECT: higher speed of interceptor.

7 cl, 12 dwg

Description

The invention relates to aerospace technology, and specifically to interceptors of space bombers, and can be used and applied for intercepting and destroying various satellite systems and various spacecraft.

A supersonic aircraft is known under Russian Federation Patent for Invention No. 2 010744, IPC B83C 39/10, Published April 15, 1996. The supersonic aircraft's fuselage is designed in any longitudinal section along a cubic parabola with a blunt aft section and a sweep angle along the leading edge of at least 60°. The aircraft's elevator is designed as a hinged front section of the fuselage.

The disadvantage is the relatively low flight speed of this supersonic aircraft, Mach 3...5. This aircraft cannot reach hypersonic speeds.

A supersonic aircraft is known under Russian Federation patent for invention No. 2130407, IPC B64C 39/02, Published March 10, 1999. This supersonic aircraft contains a fuselage, wings, launch and cruise propulsion systems.

The starting propulsion systems of this supersonic aircraft are made in the form of gas turbine engines (GTE), and the cruise engines are in the form of ramjet engines; specifically, in the patented development, it is proposed to also use pulse detonation air-breathing engines.

The disadvantages of this aircraft are its relatively low flight speed, but also the long time it takes to accelerate to hypersonic speeds due to the low thrust of the gas turbine engine.

A hypersonic aircraft is known according to the Russian Federation patent for invention No. 2305056, IPC B64D 37/06, Published on August 27, 2007, prototype.

The hypersonic aircraft comprises a fuselage, wings, fuel tanks, ramjet engines, and booster rocket motors. The booster rocket motors are powered by liquid propellant components. The fuselage of this hypersonic aircraft contains oxidizer and fuel tanks.

Disadvantages of the prototype:

- the relatively low flight speed of a hypersonic aircraft and the long time it takes to accelerate to hypersonic speeds due to the low thrust of the launch rocket engines and low efficiency due to the consumption of oxidizer from its own reserves.

- the impossibility of using ramjet engines, for example, on the PKB (space bomber interceptor) and on other spacecraft.

The objectives of the invention are to ensure greater and increased flight speed of the aircraft and improve its efficiency.

The technical result achieved: an increase in the hypersonic flight speed of the PKB, and a sharp improvement in its efficiency.

The solution of the already mentioned problems is achieved due to the fact that the Space Bomber Interceptor, containing a fuselage and wings, fuel tanks, liquid rocket engines and pipelines for supplying fuel components to them, is distinguished by the fact that it is made two-stage and contains in the second combat stage four liquid rocket engines operating on liquid hydrogen and liquid oxygen, but with a central body between them, the pipeline for supplying oxygen passes inside the hydrogen tank, and the hydrogen and oxygen tanks are connected by pipelines for supplying hydrogen and oxygen to all LRE (Liquid Rocket Engine), and the first launch stage is made in the form of three cylindrical containers installed in one plane, but with solid fuel and three SRM (Solid Fuel Rocket Engine) at the lower end, the wings are also installed in this plane, and the vertical stabilizers are located perpendicular to this plane on the middle cylindrical container with solid fuel on both sides.

The central body is made in the form of a cone with a rounding in the area of the nozzle outlet section.

R=(0.51-0.52) Dc,

where R is the radius of curvature in the area of the exhaust section of the nozzle,

Dc is the diameter of the exhaust section of the nozzle.

The Space Bomber Interceptor may contain solid propellant rocket motor (SPRM) roll nozzle assemblies on the first launch stage and liquid propellant rocket motor (LPRE) roll nozzle assemblies on the second combat stage.

The wings and vertical stabilizers on the first launch stage of the interceptor may be designed to rotate on the first launch stage of the interceptor.

The Space Bomber Interceptor contains and has at the first launch stage three solid propellant rocket nozzle assemblies, each with two oppositely mounted solid propellant rocket bank nozzles, a solid propellant rocket bank switch and a solid propellant rocket bank drive.

The interceptor of space bombers may contain and have on the second combat stage four nozzle blocks of the liquid-propellant rocket engine, each with two oppositely mounted nozzles of the liquid-propellant rocket engine, a switch of the liquid-propellant rocket engine roll and a drive of the liquid-propellant rocket engine roll.

The space bomber interceptor can also be equipped with a second-stage weapon - a laser weapon.

The proposed technical solutions for the already presented design bureau are novel, involve an inventive step and have industrial applicability.

The novelty is confirmed by the patent research conducted, and the inventive level is confirmed by the fact that the new set of essential features made it possible to obtain new technical effects, namely a sharp reduction in the acceleration time of the spacecraft to hypersonic speeds.

Industrial applicability is determined by the fact that the implementation of the invention does not require the creation of new and unknown from the state of the art units, parts, components, and new technologies.

The essence of the invention is explained in Fig. 1...12, where:

Fig. 1 shows a diagram of a space bomber interceptor,

Fig. 2 - diagram of the second combat stage,

Fig. 3 - diagram of the first launch stage,

Fig. 4 - diagram of a rocket engine, view A,

Fig. 5 - view of the lower end and the central body of the second combat stage, section B - B,

Fig. 6 - diagram of the installation of a liquid rocket engine - LRE,

Fig. 7 shows a diagram of the installation of a liquid propellant rocket engine on a frame and its swing,

Fig. 8 shows view C of the end of the first launch stage,

Fig. 9 shows a diagram of the roll blocks of the first launch stage,

Fig. 10 shows a D-view of the second combat stage with the piping around the solid propellant rocket engine's roll nozzles,

Fig. 11 shows a view of the solid propellant rocket engine roll nozzle block,

Fig. 12 shows the electrical control circuit of the first stage.

Essential features used in the description:

fuselage 1,

stabilizer 2,

wing 3,

vertical stabilizer 4,

weapon 5,

weapon bracket 6,

hydrogen tank 7,

hydrogen pipeline 8,

oxygen tank 9,

oxygen pipeline 10,

thermal insulation 11,

LRE 12,

central body 13.

connector 14,

solid fuel tanks 15,

Solid propellant rocket motor 16,

cable channel 17,

block of roll nozzles of liquid propellant rocket engine 18,

second stage control unit 19,

connections 20.

combustion chamber 21,

turbopump unit 22,

TNA shaft 23,

oxidizer pump impeller 24,

fuel pump impeller 25,

starting turbine 26,

additional fuel pump 27,

shaft of additional fuel pump 28,

cartoonist 29,

building 30,

main turbine 31,

gas generator 32,

nozzle 33,

gap 34,

combustion chamber head 35,

outer plate 36,

inner plate 37,

cavity between slabs 38,

oxygen injectors 39,

hydrogen injectors 40,

blowdown pipeline 41,

chamber cavity 42,

oxygen fuel line 43,

oxygen valve 44,

main hydrogen collector 45,

high pressure fuel line 46,

flow regulator 47,

flow regulator drive 48,

high pressure valve 49,

intermediate cavity 50,

hydrogen supply pipeline 51,

hydrogen valve 52,

gas generator cavity 53,

ignition device of chamber 54,

generator igniters 55,

high pressure pipeline 56,

starting valve 57,

blowdown pipeline 58,

purge valve 59,

hollow ball joint 60.

gas extraction pipeline 61,

bellows 62,

hinge 63,

hydraulic cylinder 64,

rod 65,

hydroelectric power station 66,

oil pipeline 67,

additional hinges 68,

additional rods 69,

frame 70,

support corners 71,

roll nozzles of the liquid propellant rocket engine 72,

roll switch of the LRE 73,

roll drive of the liquid propellant rocket engine 74,

block of solid propellant rocket motor roll nozzles 75,

combustion product selection pipeline 76,

nozzle block of solid propellant rocket motor 77,

Roll nozzles of solid propellant rocket motor 78.

roll switch of solid propellant rocket motor 79,

roll drive of solid propellant rocket motor 80,

first stage control unit 81,

first stage energy source 82,

wing drive 83,

vertical stabilizer drive 84,

wires 85,

shaft 86.

The main and fundamental feature of the proposed Space Bomber Interceptor (Fig. 1) is its ability to take off quickly and almost vertically.

The Space Bomber Interceptor (Fig. 1) comprises a fuselage 1, stabilizers 2 on the second stage, wings 3, and vertical stabilizers 4 on the first stage. Furthermore, the second stage houses a weapon 5 with a weapon bracket 6. Laser weapons are preferred and are most effective in space.

The second combat stage contains a hydrogen tank 7, a hydrogen pipeline 8, an oxygen tank 9, and an oxygen pipeline 10.

Thermal insulation was applied to all 11 tanks and pipelines.

The second combat stage of the design bureau contains four liquid-propellant rocket engines 12, and there is also a special central body 13 between them.

The central body 13 is made in the form of a cone with a rounding in the area of the outlet section of the nozzle 33.

R=(0.51-0.52) Dc,

where R is the radius of curvature in the area of the exhaust section of the nozzle,

D _c - diameter of the exhaust section of the nozzle.

The use of the central body 13 will increase the expansion ratio of the nozzles 33 of the liquid propellant rocket engine 12 and thereby significantly improve their efficiency by 8 - 10%.

The internal surfaces of the central body 13 for the design bureau have been designed and will be further created and manufactured similar to the characteristics of the Laval nozzle of the liquid propellant rocket engine.

The connection of the first and second stages of the PCB is made by connector 14, which can be very easily destroyed by pyrobolts (pyrobolts are not shown in Figs. 1-12).

The first stage contains three cylindrical solid propellant tanks (15), mounted parallel and coplanar. Solid propellant rocket motors (16) are mounted on the lower ends of the solid propellant tanks (15). Cable channels (17) run along the surface of the first stage.

The second combat stage of the PKB is equipped with four blocks of the liquid propellant rocket engine (LPRE) roll nozzles 18. The second stage of the PKB is also equipped with a second stage instrument compartment, in which the second stage control unit 19 is installed, which is connected by electrical connections 20 to all the units of the LRE 12 necessary for operation.

The LRE roll nozzle blocks 18 are each equipped with two oppositely mounted LRE roll nozzles 72 and a LRE roll switch 73 with a LRE roll drive 74. The roll switch 73 turns on the required LRE roll nozzle 72, which is needed to control the roll.

LIQUID ROCKET ENGINE SCHEME

Liquid rocket engines ZhRD 12 (Fig. 6) are designed to accelerate the spacecraft in space to hypersonic speeds of M=15-20. They operate on fuel components: liquid hydrogen and oxygen. The LRE 12 (Fig. 6 and 7) contains a combustion chamber 21 and a turbopump unit 22. The turbopump unit 22, in turn, contains an impeller of an oxidizer pump 24, an impeller of a fuel pump 25, a starting turbine 26, an additional fuel pump 27, mounted on the shaft of the TPA 23, with a shaft of an additional fuel pump 28 connected by a multiplier 29 placed in a housing 30 with the shaft of the TPA 23, a main turbine 31 made in the upper part of the turbopump unit 22. The gas generator 32 is installed above the main turbine 31 coaxially with the turbopump unit 22. The combustion chamber 21 contains a nozzle 33 made of two shells and a gap 34 between them, and a combustion chamber head 35, inside which an outer plate 36 and an inner plate 37 are made with a cavity between the plates 38 between them. Inside the head of the combustion chamber 35, oxygen injectors 39 and hydrogen injectors 40 are installed. Oxygen injectors 39 communicate with the cavity of the chamber 42, and hydrogen injectors 40 communicate the cavity between the plates 38 with the cavity of the chamber 42. On the outer surface of the combustion chamber 21, the main fuel manifold 45 is installed, from which hydrogen fuel lines extend to the lower part of the nozzle 33. The outlet from the hydrogen valve 52 is connected to the main hydrogen manifold 45, the inlet of which is connected by a hydrogen line 51 to the outlet from the impeller of the fuel pump 25. The outlet from the additional fuel pump 27 is connected by a high-pressure fuel line 46 through a flow regulator 47, which has a regulator drive 48 and a high-pressure valve 49 with the gas generator 32, specifically with the cavity of the gas generator 53. The outlet from the impeller of the oxidizer pump 24 is also connected by an oxygen line 43 through an oxygen valve 44. with gas generator 32, specifically with the cavity of gas generator 53. On the head of combustion chamber 35, ignition devices of chamber 54 are installed, and on gas generator 32, ignition devices of gas generator 55 are installed.

To ensure multiple activation and deactivation of the liquid propellant rocket engine 12, ignition devices 54 and 55 are used, which can be made of laser.

A high-pressure pipeline 56 with a starting valve 57, intended for starting the starting turbine 26, is connected to the starting turbine 26.

Igniters 54 and 55 (can be laser-based), hydrogen valve 45, oxygen valve 44, flow regulator drive 48, and starting valve 57 are connected to the second stage control unit 19 via electrical connections 20.

A purge line 58 with a purge valve 59 is connected to the fuel manifold 43. A hollow ball joint 60 is provided on the combustion chamber 21 for its oscillation in one plane. The drive is provided by a hydraulic cylinder 64, connected to the second-stage control unit 19 via electrical connections 20.

Fig. 1 shows the hydrogen tank 7 (liquid hydrogen is used as fuel in the second combat stage for the liquid propellant rocket engine of the specified design bureau).

SPACE BOMBER INTERCEPTOR OPERATION

During launch, three solid-propellant rocket motors 16 are fired simultaneously. They create thrust that allows the space bomber interceptor to take off almost vertically.

Estimated characteristics of the space bomber interceptor:

Flight speed M=15-20 Starting weight, t 100 Thrust of liquid rocket engines, T 4×150 Time to reach speed M=12-15, s 80 Rocket fuel components for liquid propellant rocket engines Oxidant oxygen Fuel hydrogen Thrust of solid propellant engines, T 3×100

When the interceptor is launched, the first stage is launched by command from the first stage control unit 81, which is located in the instrument compartment of the middle solid fuel tank 15 in the instrument compartment of the first stage.

All three solid propellant rocket motors 16 are launched simultaneously and operate until the fuel burns out completely, allowing the PKB to take off almost vertically to its designated targets.

They accelerate the Interceptor within the atmosphere and to supersonic speeds.

The flight control of the first stage and the assembly with the second stage of the PCB in pitch, yaw and roll angles (Fig. 12) is performed by the first stage control unit 81.

Used to operate drives and other first stage energy sources 82

A similar energy source is installed on the second combat stage for the PKB, but the energy source for the second stage is not shown.

From the first stage control unit 81, signals are sent to the wing drives 83, the vertical stabilizer drives 84 and the solid propellant rocket motor roll drives 80.

The signals are transmitted via wires 85. Wires 85 have a fireproof sheath and are additionally thermally insulated from the powerful heat flows emitted by the solid propellant rocket motors 16.

The rotation of the wings 3 and vertical stabilizers 4 is carried out by shafts 86 located inside them (Fig. 12).

For roll control, (4) blocks of solid propellant rocket motor roll nozzles 75 are used. The blocks of solid propellant rocket motor roll nozzles 75 are equipped (Fig. 12) with combustion product extraction pipelines 76 from the solid propellant rocket motor 16. They contain a solid propellant rocket motor nozzle block 77 with two oppositely mounted solid propellant rocket motor roll nozzles 78, which have a solid propellant rocket motor roll switch 79 and a solid propellant rocket motor roll drive 80.

When the solid propellant rocket motor 16 is completely switched off, the connector 14 (Fig. 1) is destroyed by a command from the control unit of the second combat stage 19 by detonating the explosive bolts (the explosive bolts are not shown in Figs. 1-12), and then all four liquid propellant rocket motors 12 of the second stage are switched on.

For this purpose, hydrogen from the hydrogen tank 7 is fed through the hydrogen pipeline 8 by the fuel pump (not shown in Fig. 1-12) into four liquid propellant rocket engines 12.

At the same time, oxygen from the oxygen tank 9 is also supplied through the oxygen pipelines 10 and also to the liquid propellant rocket engine 12.

When accelerating the Space Bomber Interceptor, the flight angles are controlled by misaligning the thrust of the liquid propellant rocket engine 12 and swinging it on the hollow ball joint 60 using hydraulic cylinders 64 by supplying oil to them from the hydraulic station 66 through the oil pipeline 67.

During vertical launch and takeoff, and then acceleration of the interceptor, the interceptor is controlled by the second stage control unit 19 via communication channels 20 and wires 85. The energy source of the second combat stage is (Fig. 1-12) at the interceptor (not shown).

In hypersonic flight modes, the control of the PKB is performed by the first stage control unit 81, via electrical communication 20 and via wires 85 (Figs. 1 and 12).

Wires 85 must be made with insulation from fire-resistant material and additionally thermally insulated from the powerful heat flow during operation of the solid propellant rocket motor 16.

OPERATION OF LIQUID ROCKET ENGINES

When the liquid propellant rocket engine 12 (Fig. 4) is started, signals are sent from the second stage control unit 19 via electrical communication 20 to the starting valve 57. High-pressure air is supplied via high-pressure pipeline 56 to the starting turbine 26 and rotates the shaft of the turbopump 23. The pressure of oxygen and hydrogen at the outlet of the impellers of the oxidizer pump 24 and fuel pump 25 increases.

A signal is sent to open valves 44, 49, and 52. Oxidizer and fuel (in the form of components: oxygen and hydrogen) enter combustion chamber 21 and gas generator 32. A signal is sent to igniters 54 and 55, then the fuel mixture in combustion chamber 21 and gas generator 32 ignites. LRE 12 has started.

The flow regulator 47 is used with the help of the flow regulator drive 48 to regulate its operating mode.

When the liquid propellant rocket engine 12 is turned off, a signal is sent from the control unit of the second combat stage 19 via electrical communication 20 to valves 44, 49 and 52, which close.

Then a signal is sent to open the purge valve 59 and the inert gas (Nitrogen) enters the main hydrogen manifold 45 through the purge pipeline 58 and then into the gap 34 for purging and removing residual hydrogen.

The use of the invention made it possible to:

1. Increase the Interceptor's flight speed to M=15-20 by using solid propellant rocket engines and liquid rocket engines running on hydrogen and oxygen.

2. Accelerate the ascent process and reduce the time it takes to accelerate the spacecraft to maximum hypersonic speeds by using two different types and kinds of engines operating in different conditions: at launch in the atmosphere, but also higher in space.

3. Simplify the fuel supply schemes for starting and cruise engines.

4. Significantly increase the reliability of the given Interceptor.

5. Increase the power and specific characteristics of the PCB.

6. Ensure reliable control of the interceptor in all modes of its operation.

7. Ensure multiple switching on and off of the liquid propellant rocket engine.

8. Improve the start-up and shutdown of liquid rocket engines (LPRE) and ensure reliable and efficient operation in a vacuum and their cleaning from residual hydrogen after shutdown.

Claims (10)

1. An interceptor of space bombers, comprising a fuselage, wings, fuel tanks, liquid rocket engines and pipelines for supplying liquid components: fuel and oxidizer to them, characterized in that the said interceptor is made two-stage and contains a first and second combat stage, where its second combat stage contains a laser weapon, four liquid rocket engines operating on liquid hydrogen and liquid oxygen, with a central body installed between them, the oxygen supply pipeline passes inside the hydrogen tank, and the hydrogen and oxygen tanks are connected by hydrogen and oxygen supply pipelines with all liquid rocket engines, and its first launch stage is made in the form of three cylindrical containers installed directly in one plane, but with a different type and appearance - solid fuel, and solid fuel rocket engines at the lower end, the wings are also installed in this plane, and the vertical stabilizers are located perpendicular to this plane on the middle cylindrical container with solid fuel, on both sides. 2. An interceptor for space bombers according to paragraph 1, characterized in that the central body is made in the form of a tetrahedral cone with a rounding in the area of the nozzle outlet section: R = (0.51-0.52) Dc, where R is the radius of rounding in the area of the exhaust section of the nozzle; Dc is the diameter of the exhaust section of the nozzle. 3. A space bomber interceptor according to claim 1, characterized in that it contains blocks of solid propellant rocket engine roll nozzles at its first stage and blocks of liquid propellant rocket engine roll nozzles at its second combat stage. 4. An interceptor of space bombers according to paragraph 1, characterized in that its wings and vertical stabilizers on its first stage are designed with the possibility of their rotation on the first stage of the interceptor. 5. An interceptor for space bombers according to claim 1, characterized in that it contains, at the first launch stage, three solid propellant rocket motor nozzle blocks, each with two oppositely mounted solid propellant rocket motor roll nozzles, a solid propellant rocket motor roll switch, and a solid propellant rocket motor roll drive. 6. An interceptor of space bombers according to paragraph 1, characterized in that it contains, at its second combat stage, four nozzle blocks of a liquid-propellant rocket engine, each with two oppositely mounted liquid-propellant rocket engine roll nozzles, a liquid-propellant rocket engine roll switch, and a liquid-propellant rocket engine roll drive. 7. An interceptor of space bombers according to paragraph 1, characterized in that it is equipped with weapons and has a combat laser at the second combat stage.