A coaxial multi-component mixed working fluid space combined propulsion system

Abstract

The present invention discloses a coaxial multi-component mixed working fluid space combined propulsion system, including a working fluid supply system and a coaxial chemical-electric hybrid thruster; the working fluid supply system includes a high-pressure gas cylinder, an oxidant supply system, a fuel supply system and an electric propulsion mixed working fluid supply pipeline; the coaxial chemical-electric hybrid thruster includes a chemical thrust unit and an electric thrust unit coaxial from inside to outside; the electric thrust unit includes a metal shell, a gas distribution ring and an anode base; a mixed working fluid gas collecting cavity is arranged in the metal shell; the gas distribution ring is evenly distributed with n distribution holes along the circumference; the anode base is provided with a secondary mixing cavity and n spray holes arranged alternately with the distribution holes. On the basis of not affecting the basic structure of the chemical propulsion system and the electric propulsion system, the present invention aims to minimize the configuration changes of the core device thrusters in the two types of original space propulsion systems, fully utilizes the characteristics of the chemical propulsion system and the electric propulsion system, and at the same time meets the requirements of large thrust and high specific impulse required for space propulsion.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft space propulsion technology, in particular to a coaxial multi-component mixed working fluid space combined propulsion system. Background Art

[0002] As human beings continue to explore space, diversified space missions have put forward higher and more complex requirements for propulsion systems. Electric propulsion technology has a high specific impulse and has significant advantages in service life and precise thrust control, but it is limited by its small thrust. It is currently mainly used in spacecraft orbit, attitude maintenance and deep space exploration tasks, and cannot meet the requirements of rapid maneuvering of spacecraft. In comparison, the outstanding features of chemical propulsion technology are simple structure, high thrust-to-weight ratio and low cost. For spacecraft with large mass and rapid maneuvering, chemical thrusters are an ideal choice, but due to the limitations of propellant chemical energy and wall temperature, chemical thrusters have a low specific impulse and cannot achieve the requirements of continuously variable thrust. Therefore, the above two propulsion technologies cannot simultaneously meet the requirements of large thrust and high specific impulse required for space propulsion when used alone.

[0003] The chemical propulsion system and electric propulsion system equipped in the current spacecraft propulsion system are two independent systems, using their own tanks and corresponding supporting pipelines, which increases the transportation cost. Chemical propulsion technology relies on the high-temperature combustion gas generated by the combustion of fuel and oxidant to form thrust, while electric propulsion technology can ionize almost all working fluids. The sharing of working fluids for chemical propulsion and electric propulsion helps reduce the size and weight of spacecraft and improve the payload capacity. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a coaxial multi-component mixed working fluid space combined propulsion system in view of the deficiencies of the above-mentioned prior art. The coaxial multi-component mixed working fluid space combined propulsion system, without affecting the basic structure of the chemical propulsion system and the electric propulsion system, aims to minimize the change in the thruster configuration of the core device in the two types of original space propulsion systems, fully utilizes the characteristics of the chemical propulsion system and the electric propulsion system, and at the same time meets the requirements of large thrust and high specific impulse required for space propulsion.

[0005] In order to solve the above technical problems, the technical solution adopted by the present invention is:

[0006] A coaxial multi-component hybrid working fluid space combined propulsion system comprises a working fluid supply system and a coaxial chemical-electric hybrid thruster.

[0007] The working fluid supply system includes a high-pressure gas cylinder, an oxidant supply system, a fuel supply system and an electric propulsion mixed working fluid supply pipeline.

[0008] The high-pressure gas cylinder is used to provide high-pressure extruded gas to the oxidizer supply system and the fuel supply system.

[0009] The electric propulsion mixed working fluid supply pipeline includes an oxygen supply branch and a fuel supply branch.

[0010] The oxidant supply system is used to provide oxidant to the chemical thrust unit and the oxygen supply branch.

[0011] The fuel supply system is used to provide fuel to the chemical thrust unit and the fuel supply branch.

[0012] The coaxial chemical-electric hybrid thruster includes a chemical thrust unit and an electric thrust unit coaxially arranged on the periphery of the chemical thrust unit.

[0013] The electric thrust unit includes a metal shell, a gas distribution ring and an anode base.

[0014] The metal shell comprises a large cylindrical section and a small cylindrical section which are coaxially sleeved on the outer circumference of the chemical thruster in sequence from front to back; wherein the outer diameter of the large cylindrical section is greater than the outer diameter of the small cylindrical section.

[0015] An annular discharge cavity is formed between the inner wall surface of the small cylindrical section and the outer wall surface of the chemical thruster; wherein the outer wall surface of the chemical thruster is made of insulating material.

[0016] A mixed working fluid gas collecting chamber is arranged at the inner end of the large cylindrical section located at the outer periphery of the chemical thruster; the mixed working fluid gas collecting chamber is connected to the oxygen supply branch through the oxygen flow channel built into the large cylindrical section; the mixed working fluid gas collecting chamber is also connected to the fuel supply branch through the fuel flow channel built into the large cylindrical section; the side of the mixed working fluid gas collecting chamber facing the electric thrust chamber is open.

[0017] The gas distribution ring sealing cover is arranged on the open surface of the mixed working medium gas collecting cavity; the gas distribution ring is evenly provided with n distribution holes along the circumferential direction.

[0018] The anode base is arranged in the discharge chamber at the top of the gas distribution ring, and a secondary mixing chamber connected with n distribution holes is arranged on the side of the anode base facing the gas distribution ring; the anode base is evenly distributed with n spray holes along the circumference; the n spray holes and the n distribution holes are staggered along the circumference, and each spray hole is connected with the secondary mixing chamber and the discharge chamber.

[0019] The staggered angle between the n spray holes and the n distribution holes is 180° / n.

[0020] The diameter of the spray hole is smaller than the diameter of the dispensing hole.

[0021] The oxidant is oxygen or nitrous oxide; the fuel is kerosene, methane or ethylene.

[0022] The metal shell is made of titanium alloy, and the outer wall of the chemical thruster is made of silicon-based ceramics or carbon-carbon composite materials.

[0023] The chemical thrust units include pulse detonation thrusters, monopropellant chemical thrusters and bipropellant chemical thrusters; the electric thrust units include Hall electric thrusters, toroidal ion thrusters, microwave electric thrusters or helical wave electric thrusters.

[0024] The oxidant supply system comprises an oxidant storage tank and an oxidant delivery pipeline; an oxidant isolation valve and an oxidant high-flow control valve are arranged in sequence on the oxidant delivery pipeline along the gas flow direction.

[0025] The fuel supply system includes a fuel tank and a fuel delivery pipeline; a fuel isolation valve and a fuel high flow control valve are arranged in sequence on the fuel delivery pipeline along the fuel flow direction.

[0026] The inlet end of the oxygen supply branch is connected to the oxidant delivery pipeline between the oxidant isolation valve and the oxidant large flow control valve, and the oxidant small flow control valve is arranged on the oxygen supply branch.

[0027] The inlet end of the fuel supply branch is connected to the fuel delivery pipeline between the fuel isolation valve and the fuel large flow control valve, and a fuel small flow control valve is arranged on the fuel supply branch.

[0028] Through the coordinated cooperation of the oxidizer isolation valve, the oxidizer large flow control valve, the fuel isolation valve, the fuel large flow control valve, the oxidizer small flow control valve and the fuel small flow control valve, the switching between the separate independent working mode and the coordinated working mode of the chemical thruster and the electric thruster can be achieved.

[0029] The valve openings of the oxidizer small flow control valve and the fuel small flow control valve can be freely adjusted according to the remaining amount of oxidizer in the oxidizer tank and the remaining amount of fuel in the fuel tank; when the fuel is in excess, the valve opening of the fuel small flow control valve is increased so that the ratio of fuel to oxidizer in the electric propulsion mixture is greater than 1; when the oxidizer is in excess, the valve opening of the oxidizer small flow control valve is increased so that the ratio of fuel to oxidizer in the electric propulsion mixture is less than 1.

[0030] The squeezed gas stored in the high-pressure gas cylinder is nitrogen or helium.

[0031] The present invention has the following beneficial effects:

[0032] 1. The chemical thrust unit and the electric thrust unit in the present invention can work independently without affecting each other. When the spacecraft needs to complete a rapid maneuvering mission, the chemical thrust unit works alone to provide a large thrust for the spacecraft; when the spacecraft needs to maintain its orbit and attitude or complete a deep space exploration mission, the electric thrust unit works independently to provide a high specific impulse for the spacecraft.

[0033] 2. For the designed coaxial multi-component mixed working fluid space combined propulsion system, considering factors such as thruster type, mission type, reliability and cost, the propellant working fluid adopts extrusion supply. The high-pressure gas cylinder is filled with inert gas such as nitrogen or helium, and enters the oxidizer tank and fuel tank respectively through the filling and discharge valve and the control valve. The extrusion supply method has a simple structure and can largely ensure the reliability of the entire system in multiple startups in a short period of time.

[0034] 3. The flow rates of the working fluids required by the chemical thrust unit and the electric thrust unit are usually not at the same order of magnitude. Therefore, large flow control valves are used in the oxidizer supply pipeline and the fuel supply pipeline, and small flow control valves are used in the electric propulsion mixed working fluid supply pipeline.

[0035] 4. The mixed working fluid gas collecting chamber, n distribution holes, secondary mixing chamber and n nozzle holes together form an electric propulsion working fluid mixing component. The angle between the n distribution holes and the n nozzle holes is 180° / n. After the mixed working fluid enters the secondary mixing chamber, the residence time is prolonged due to the resistance. After being evenly mixed again, it enters the discharge channel. In theory, the effect of complete mixing can be achieved.

[0036] 5. The oxidants that can be used for chemical thrusters include but are not limited to oxygen, nitrous oxide, etc., and the fuels include but are not limited to kerosene, methane, ethylene, etc. These oxidants and fuels can be used as mixed working fluids for electric thrusters. Large molecular fuels such as kerosene are not easy to ionize. After adding gases with lower ionization energy such as oxygen and nitrous oxide and fully mixing them with them, efficient utilization of propellant working fluids can be achieved. Oxidants usually have strong oxidizing properties after ionization alone. The performance and life of some components of the electric propulsion unit will be greatly reduced after being oxidized. After the fuels such as methane and ethylene are fully mixed with oxidants, the service life of the propulsion system can be maximized and the mission cost can be reduced.

[0037] 6. Compared with electric thrust units, chemical thrust units consume many orders of magnitude more fuel and oxidizer, and chemical thrust units have stricter requirements on the ratio of fuel and oxidizer when working, which can easily cause partial excess and inexhaustible fuel and oxidizer, resulting in waste of propellant resources. Electric thrust units have very flexible requirements for the ratio of mixed working fluids. When the fuel is in excess, the fuel / oxidizer in the mixed working fluid is greater than 1; when the oxidizer is in excess, the fuel / oxidizer in the mixed working fluid is less than 1. The coaxial combination of chemical thrust units and electric thrust units can effectively avoid the waste of propellant resources.

[0038] 7. The chemical thrust unit is located at the center of the coaxial multi-component mixed working fluid space combined thruster, and its outer wall also serves as the inner wall of the electric thrust unit. When the chemical thrust unit is working, the temperature of the nozzle wall will rise sharply, so it is necessary to optimize the wall material. The outer shell of the chemical thrust unit is made of insulating materials with good high temperature resistance, such as silicon-based ceramics and carbon-carbon composite materials. It is suitable for the extreme environment brought by chemical combustion, and can also serve as the inner wall of the external electric thrust unit to maintain the generation of plasma in the discharge channel. The outer shell of the electric thrust unit is made of materials with good high temperature resistance, such as titanium alloy, to reduce its influence by the high temperature combustion gas of the chemical thrust unit.

[0039] 8. The coaxial structure design makes the space combined thruster compact and light in weight. This design can optimize the space layout, reduce the system complexity, and is conducive to the lightweight design of the spacecraft propulsion system. At the same time, this structure also helps to improve the reliability and durability of the thruster and reduce the failure rate.

[0040] 9. The chemical thrust unit and the electric thrust unit are closely connected, and the residual heat of the chemical thrust unit after operation is beneficial to the vaporization and ionization of the electric propulsion mixed working fluid. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 The schematic diagram shows the principle of a coaxial multi-component mixed working fluid space combined propulsion system of the present invention.

[0042] Figure 2 A schematic diagram showing the principle of a coaxial electric hybrid thruster in the present invention is shown.

[0043] Figure 3 A three-dimensional cross-sectional structure diagram of the electric thrust unit of the present invention is shown.

[0044] Among them are:

[0045] 10. High-pressure gas cylinder; 11. Extruded gas filling and exhaust valve; 12. Extruded gas control valve;

[0046] 20. Oxidant supply system; 21. Oxidant storage tank; 22. Oxidant isolation valve; 23. Oxidant high flow control valve;

[0047] 30. Fuel supply system; 31. Fuel tank; 32. Fuel isolation valve; 33. Fuel high flow control valve;

[0048] 40. Electric propulsion mixed working fluid supply pipeline;

[0049] 41. Oxygen supply branch; 42. Oxidant small flow control valve; 43. Fuel supply branch; 44. Fuel small flow control valve;

[0050] 50. Coaxial chemical-electric hybrid thruster;

[0051] 60. Electric thrust unit;

[0052] 61. Metal shell; 611. Insulation pad;

[0053] 62. Large cylindrical section; 621. Central through hole; 622. Mixed working medium collecting cavity; 623. Oxygen flow channel; 624. Fuel flow channel;

[0054] 63. Small cylindrical section; 631. Discharge chamber;

[0055] 64. Gas distribution ring; 641. Distribution hole;

[0056] 65. Anode base; 651. Secondary mixing chamber; 652. Convex ring; 653. Spray hole;

[0057] 66. Electric propulsion working fluid mixing components;

[0058] 70. Chemical thrust unit. DETAILED DESCRIPTION

[0059] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific preferred embodiments.

[0060] In the description of the present invention, it should be understood that the terms "left side", "right side", "upper part", "lower part" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. "First", "second" and the like do not indicate the importance of the components, and therefore cannot be understood as limiting the present invention. The specific dimensions used in this embodiment are only for illustrating the technical solution, and do not limit the scope of protection of the present invention.

[0061] like Figure 1 As shown, a coaxial multi-component hybrid working fluid space combined propulsion system includes a working fluid supply system and a coaxial chemical-electric hybrid thruster 50.

[0062] The working medium supply system includes a high-pressure gas cylinder 10 , an oxidant supply system 20 , a fuel supply system 30 and an electric propulsion mixed working medium supply pipeline 40 .

[0063] The high-pressure gas cylinder provides high-pressure extruded gas to the oxidant supply system and the fuel supply system through the extruded gas delivery pipeline. The extruded gas stored in the high-pressure gas cylinder is preferably an inert gas such as nitrogen or helium.

[0064] The extruded gas delivery pipeline is preferably provided with an extruded gas adding and discharging valve 11 and an extruded gas control valve 12 in sequence along the extruded gas flow direction. The extruded gas adding and discharging valve 11 is used for pressure relief control of the extruded gas to avoid pressure overload. The extruded gas control valve 12 is used for controlling the on-off and flow control of the extruded gas.

[0065] The oxidant supply system is used to provide oxidant to the chemical thrust unit and oxygen supply branch described below. The oxidant is preferably, but not limited to, oxygen or nitrous oxide.

[0066] The oxidant supply system preferably includes an oxidant tank 21 and an oxidant delivery pipeline; an oxidant isolation valve 22 and an oxidant high flow control valve 23 are arranged in sequence on the oxidant delivery pipeline along the gas flow direction. The oxidant isolation valve 22 is used for on-off and size control of the total oxidant supply flow. The oxidant high flow control valve 23 is used to control the on-off and size control of the oxidant delivery to the chemical thrust unit.

[0067] The fuel supply system is used to provide fuel to the chemical thrust unit and the fuel supply branch. The fuel is preferably, but not limited to, kerosene, methane or ethylene.

[0068] The fuel supply system includes a fuel tank 31 and a fuel delivery pipeline; a fuel isolation valve 32 and a fuel high flow control valve 33 are arranged in sequence on the fuel delivery pipeline along the fuel flow direction. The fuel isolation valve 32 is used to control the on-off and size of the total fuel supply flow. The fuel high flow control valve 33 is used to control the on-off and size of the fuel delivered to the chemical thrust unit.

[0069] The electric propulsion mixed working medium supply pipeline includes an oxygen supply branch 41 and a fuel supply branch 43 .

[0070] The inlet end of the oxygen supply branch is connected to the oxidant delivery pipeline between the oxidant isolation valve and the oxidant large flow control valve, and an oxidant small flow control valve 42 is provided on the oxygen supply branch, which is used to control the on-off and flow control of the oxidant delivery to the electric thrust unit.

[0071] The inlet end of the fuel supply branch is connected to the fuel delivery pipeline between the fuel isolation valve and the fuel large flow control valve, and a fuel small flow control valve 44 is provided on the fuel supply branch, which is used to control the on-off and flow control of fuel delivery to the electric thrust unit.

[0072] like Figure 2 As shown, the coaxial chemical-electric hybrid thruster includes a chemical thrust unit 70 and an electric thrust unit 60 coaxially arranged on the periphery of the chemical thrust unit.

[0073] The chemical thrust unit is preferably a pulse detonation thruster, a monopropellant chemical thruster, a bipropellant chemical thruster, etc.; the electric thrust unit is preferably a Hall electric thruster, a toroidal ion thruster, a microwave electric thruster, or a helical wave electric thruster, etc.

[0074] like Figure 3 As shown, the electric thrust unit includes a metal shell 61 , a gas distribution ring 64 and an anode base 65 .

[0075] The metal shell is preferably made of a high-temperature resistant metal material such as a titanium alloy material, and the bottom or periphery of the metal shell is preferably wrapped with an insulating pad 611 .

[0076] The metal shell includes a large cylindrical section 62 and a small cylindrical section 63 which are coaxially sleeved on the outer circumference of the chemical thrust unit from front to back; wherein the outer diameter of the large cylindrical section is greater than the outer diameter of the small cylindrical section.

[0077] An annular discharge chamber 631 is formed between the inner wall of the small cylindrical section and the outer wall of the chemical thrust unit; wherein the outer wall of the chemical thrust unit is made of high temperature resistant insulating materials such as silicon-based ceramics or carbon-carbon composite materials.

[0078] A central through hole 621 is provided at the center of the large cylindrical section for installing a chemical thrust unit.

[0079] A mixed working fluid collecting chamber 622 is provided at the inner end of the large cylindrical section located at the periphery of the chemical thrust unit; the mixed working fluid collecting chamber is connected to the oxygen supply branch through an oxygen flow channel 623 built into the large cylindrical section; the mixed working fluid collecting chamber is also connected to the fuel supply branch through a fuel flow channel 624 built into the large cylindrical section; the side of the mixed working fluid collecting chamber facing the electric thrust chamber is open.

[0080] The gas distribution ring sealing cover is arranged on the open surface of the mixed working medium gas collecting cavity; the gas distribution ring is preferably a circular copper sheet, and n distribution holes 641 are evenly distributed along the circumference.

[0081] The anode base is arranged in the discharge chamber at the top of the gas distribution ring, and a secondary mixing chamber 651 connected with n distribution holes is arranged on the side of the anode base facing the gas distribution ring; n spray holes 653 are evenly distributed along the circumference of the anode base; the n spray holes and the n distribution holes are staggered along the circumference, and each spray hole is connected with the secondary mixing chamber and the discharge chamber.

[0082] Furthermore, the staggered angle between the n spray holes and the n distribution holes is preferably 180° / n.

[0083] Further, the diameter of the spray hole is smaller than the diameter of the dispensing hole.

[0084] Furthermore, the upper surfaces of the n nozzle holes are convex upward to form a convex ring 652, so that the height of the nozzle holes is increased to further evenly mix.

[0085] The mixed working medium gas collecting chamber 622 , the n distribution holes, the secondary mixing chamber and the n spray holes together form an electric propulsion working medium mixing assembly 66 .

[0086] The present invention can realize the switching between the separate independent working mode and the cooperative working mode of the chemical thruster and the electric thruster through the coordinated cooperation of the oxidant isolation valve, the oxidant large flow control valve, the fuel isolation valve, the fuel large flow control valve, the oxidant small flow control valve and the fuel small flow control valve. Both can work independently without affecting each other. When the spacecraft needs to complete a rapid maneuvering mission, the chemical thrust unit works alone to provide a large thrust for the spacecraft; when the spacecraft needs to maintain its orbit and attitude or complete a deep space exploration mission, the electric thrust unit works independently to provide the spacecraft with a high specific impulse.

[0087] The valve openings of the oxidizer small flow control valve and the fuel small flow control valve can be freely adjusted according to the remaining amount of oxidizer in the oxidizer tank and the remaining amount of fuel in the fuel tank; when the fuel is in excess, the valve opening of the fuel small flow control valve is increased so that the ratio of fuel to oxidizer in the electric propulsion mixture is greater than 1; when the oxidizer is in excess, the valve opening of the oxidizer small flow control valve is increased so that the ratio of fuel to oxidizer in the electric propulsion mixture is less than 1.

[0088] When the spacecraft needs to complete a rapid maneuvering mission, the chemical thrust unit works independently. The oxidizer and fuel are supplied by the oxidizer input pipeline and the fuel input pipeline connected to the chemical thrust unit respectively. When the mixed oxidizer and fuel reach the appropriate conditions, the ignition system is activated to generate sparks or high temperatures, thereby initiating the combustion of the mixture. The high-temperature and high-pressure gas generated by the combustion is ejected at high speed through the thruster nozzle to generate thrust.

[0089] When the spacecraft needs to maintain its orbit and attitude or complete a deep space exploration mission, the electric thrust unit works independently. The mixed working fluid is introduced into the mixed working fluid gas collecting chamber by the electric propulsion mixed working fluid supply pipeline, and is evenly mixed in the secondary mixing chamber between the gas distribution ring and the anode base before being introduced into the discharge chamber. Neutral atoms undergo a series of electron collision reactions with drifting electrons to form ions, which are accelerated by the electromagnetic field and ejected from the discharge chamber to generate thrust.

[0090] Different types of electric thrusters have some differences in structure, mainly in the generation and acceleration mechanisms of plasma. Corresponding components can be added on the basis of the present invention.

[0091] Taking the generation and acceleration of plasma in Hall electric thruster as an example, it is necessary to Figure 3A hollow cathode and a magnetic pole are added to the structure shown in the figure. The hollow cathode emits electrons into the discharge channel, and the magnetic pole forms a radial magnetic field in the annular cavity. Under the radial magnetic field, the discharge plasma generates a self-consistent axial electric field in the annular cavity. After the electrons emitted by the hollow cathode enter the discharge cavity, they form a circumferential drift under the action of the orthogonal electromagnetic field, also known as Hall drift. The ions are accelerated under the action of the electromagnetic field and generate thrust after being ejected from the discharge cavity.

[0092] Taking microwave electric thruster as an example, Figure 3 A microwave connector, an antenna and a magnetic pole are added to the structure shown, and the input microwave energy is transmitted to the discharge channel. When the cyclotron frequency of the Larmor motion of the free electrons in the discharge channel is equal to the microwave frequency, the microwave energy is absorbed by the electrons to form high-energy electrons. The electrons that gain energy continuously collide with the mixed working fluid to generate a discharge plasma. The ions are accelerated under the action of the electromagnetic field and are ejected from the annular cavity to generate thrust.

[0093] The device of the present invention can work in two modes, chemical propulsion and electric propulsion, respectively, and combines the advantages of large thrust and high specific impulse of the two modes, so it is suitable for various space missions; the device of the present invention is easy to process, and the chemical thrusters and electric thrusters used have simple structures and mature processing technologies; the electric thrust unit of the present invention adopts a multi-component mixed working fluid, which can more effectively utilize limited propellant resources, and at the same time can provide a more flexible working fluid combination scheme according to mission requirements, and at the same time, the electric thruster mixed working fluid input pipeline is designed in a targeted manner, which is conducive to achieving a better mixing effect, thereby realizing efficient ionization; the device of the present invention adopts a modular design to facilitate the replacement of other types of thrust units for different scenarios in the future and recombination.

[0094] The technical effect is to combine the chemical thrusters and electric thrusters coaxially without affecting their structures, with the goal of minimizing the changes to the original space thruster configuration, to achieve the sharing of propellants, and to propose a specific implementation method for the separate operation of the chemical thrust unit and the electric thrust unit in a coaxial multi-mixed working fluid space combination thruster.

[0095] The preferred embodiments of the present invention are described in detail above; however, the present invention is not limited to the specific details in the above embodiments. Within the technical concept of the present invention, various equivalent transformations can be made to the technical solutions of the present invention, and these equivalent transformations all belong to the protection scope of the present invention.

Claims

1. A coaxial multi-component mixed working fluid space combined propulsion system, characterized in that: It includes a working fluid supply system and a coaxial chemical-electric hybrid thruster; The working fluid supply system includes a high-pressure gas cylinder, an oxidant supply system, a fuel supply system and an electric propulsion mixed working fluid supply pipeline; The high-pressure gas cylinder is used to provide high-pressure extruded gas to the oxidant supply system and the fuel supply system; The electric propulsion mixed working medium supply pipeline includes an oxygen supply branch and a fuel supply branch; The oxidant supply system is used to supply oxidant to the chemical thrust unit and the oxygen supply branch; The fuel supply system is used to supply fuel to the chemical thrust unit and the fuel supply branch; The coaxial chemical-electric hybrid thruster comprises a chemical thrust unit and an electric thrust unit coaxially arranged on the periphery of the chemical thrust unit; The electric thrust unit includes a metal shell, a gas distribution ring and an anode base; The metal shell includes a large cylindrical section and a small cylindrical section which are coaxially sleeved on the outer circumference of the chemical thrust unit in sequence from front to back; wherein the outer diameter of the large cylindrical section is greater than the outer diameter of the small cylindrical section; An annular discharge cavity is formed between the inner wall of the small cylindrical section and the outer wall of the chemical thrust unit; wherein the outer wall of the chemical thrust unit is made of insulating material; A mixed medium gas collecting chamber is provided at the inner end of the large cylindrical section located at the outer periphery of the chemical thrust unit; the mixed medium gas collecting chamber is connected to the oxygen supply branch through the oxygen flow channel built in the large cylindrical section; the mixed medium gas collecting chamber is also connected to the fuel supply branch through the fuel flow channel built in the large cylindrical section; the mixed medium gas collecting chamber is open on one side facing the electric thrust chamber; The gas distribution ring sealing cover is arranged on the open surface of the mixed working medium gas collecting chamber; the gas distribution ring is evenly provided with n distribution holes along the circumferential direction; the anode base is arranged in the discharge chamber at the top of the gas distribution ring, and a secondary mixing chamber connected to the n distribution holes is arranged on the side of the anode base facing the gas distribution ring; the anode base is evenly provided with n spray holes along the circumferential direction; the n spray holes and the n distribution holes are staggered along the circumferential direction, and each spray hole is connected to the secondary mixing chamber and the discharge chamber.

2. The coaxial multi-component mixed working fluid space combined propulsion system according to claim 1 is characterized in that: The staggered angle between the n spray holes and the n distribution holes is 180° / n.

3. The coaxial multi-component mixed working fluid space combined propulsion system according to claim 1 is characterized in that: The diameter of the spray hole is smaller than the diameter of the dispensing hole.

4. The coaxial multi-component mixed working fluid space combined propulsion system according to claim 1 is characterized in that: The oxidant is oxygen or nitrous oxide; the fuel is kerosene, methane or ethylene.

5. The coaxial multi-component mixed working fluid space combined propulsion system according to claim 1 is characterized in that: The metal shell is made of titanium alloy, and the outer wall of the chemical thrust unit is made of silicon-based ceramics or carbon-carbon composite materials.

6. The coaxial multi-component mixed working fluid space combined propulsion system according to claim 1 is characterized in that: The chemical thrust units include pulse detonation thrusters, monopropellant chemical thrusters and bipropellant chemical thrusters; the electric thrust units include Hall electric thrusters, toroidal ion thrusters, microwave electric thrusters or helical wave electric thrusters.

7. The coaxial multi-component mixed working fluid space combined propulsion system according to claim 1 is characterized in that: The oxidant supply system includes an oxidant storage tank and an oxidant delivery pipeline; an oxidant isolation valve and an oxidant high flow control valve are arranged in sequence on the oxidant delivery pipeline along the gas flow direction; The fuel supply system includes a fuel tank and a fuel delivery pipeline; a fuel isolation valve and a fuel high flow control valve are arranged in sequence on the fuel delivery pipeline along the fuel flow direction; The inlet end of the oxygen supply branch is connected to the oxidant delivery pipeline between the oxidant isolation valve and the oxidant large flow control valve, and the oxidant small flow control valve is arranged on the oxygen supply branch; The inlet end of the fuel supply branch is connected to the fuel delivery pipeline between the fuel isolation valve and the fuel large flow control valve, and a fuel small flow control valve is arranged on the fuel supply branch.

8. The coaxial multi-component mixed working fluid space combined propulsion system according to claim 7 is characterized in that: Through the coordinated cooperation of the oxidizer isolation valve, the oxidizer large flow control valve, the fuel isolation valve, the fuel large flow control valve, the oxidizer small flow control valve and the fuel small flow control valve, the switching between the separate independent working mode and the coordinated working mode of the chemical thruster and the electric thruster can be achieved.

9. The coaxial multi-component mixed working fluid space combined propulsion system according to claim 8 is characterized in that: The valve openings of the oxidizer small flow control valve and the fuel small flow control valve can be freely adjusted according to the remaining amount of oxidizer in the oxidizer tank and the remaining amount of fuel in the fuel tank; when the fuel is in excess, the valve opening of the fuel small flow control valve is increased so that the ratio of fuel to oxidizer in the electric propulsion mixture is greater than 1; when the oxidizer is in excess, the valve opening of the oxidizer small flow control valve is increased so that the ratio of fuel to oxidizer in the electric propulsion mixture is less than 1.

10. The coaxial multi-component mixed working fluid space combined propulsion system according to claim 1 is characterized in that: The squeezed gas stored in the high-pressure gas cylinder is nitrogen or helium.

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