Maintenance-free dual-mode attitude control power system

Abstract

The invention provides a maintenance-free dual-mode attitude control power system which is used for being installed on an aerospace vehicle and comprises a positive feedback circulation system, a thruster set, a fuel gas generator, a fuel storage box and an oxidizing agent storage box. The positive feedback circulation system is used for self-pressurization of the attitude control power system; the positive feedback circulation system comprises a gunpowder starter, a differential storage tank, a liquid path pressure stabilizing valve, a fuel gas generator and a pressurizing one-way valve; the thruster group comprises a gas thruster, a single-component thruster and a double-component thruster; an inlet of the fuel gas generator is communicated with the positive feedback circulation system; the outlet is communicated with the gas thruster, the fuel storage tank and the oxidant storage tank; the fuel tank and the oxidant tank are in communication with the thruster set. The advantages of a single-component engine and a double-component engine are organically combined, the overall performance of the power system is improved, the use and maintenance requirements of the attitude control power system before rocket launching are lowered, and the launching preparation time is shortened.

Description

Technical Field

[0001] The present application relates to the technical field of attitude control power systems, and in particular to a maintenance-free dual-mode attitude control power system. Background Art

[0002] Attitude control power systems are widely used in space vehicles such as launch vehicles, upper stages, satellites, and spacecraft to achieve functions such as attitude control, terminal velocity correction, and position keeping. According to the type and quantity of propellants, attitude control power systems are usually divided into monopropellant systems and bipropellant systems. Monopropellant systems have the advantages of simplicity, reliability, low thrust, and good pulse performance, but have disadvantages such as low specific impulse; bipropellant systems have the advantages of high thrust and high specific impulse, but have disadvantages such as complex systems. Dual-mode attitude control power systems can organically combine the advantages of high reliability, low thrust, and good pulse performance of monopropellants with the advantages of high specific impulse of bipropellants, so that the system has higher overall performance. However, the currently used dual-mode attitude control power systems require complex use and maintenance work such as adding propellants and filling high-pressure gas before launch, and the launch preparation time is long.

[0003] Therefore, the current attitude control power system has the following defects:

[0004] (1) For complex application scenarios of attitude control power systems, single-component and dual-component systems cannot fully exert their respective advantages, affecting the overall performance of the power system.

[0005] (2) Before launching, a space launch vehicle needs to be filled with propellant and high-pressure gas, which makes its use and maintenance more complicated and increases the launch preparation time, which is not conducive to rapid launch.

[0006] Therefore, the technical problem that urgently needs to be solved is: how to provide a maintenance-free dual-mode attitude control power system that organically combines the advantages of single- and dual-component engines, improves the overall performance of the power system, reduces the demand for use and maintenance of the attitude control power system before rocket launch, and shortens launch preparation time. Summary of the invention

[0007] The purpose of this application is to provide a maintenance-free dual-mode attitude control power system, which organically combines the advantages of single- and dual-component engines, improves the overall performance of the power system, reduces the maintenance requirements of the attitude control power system before rocket launch, and shortens the launch preparation time.

[0008] To achieve the above-mentioned purpose, the present application provides a maintenance-free dual-mode attitude control power system for installation in a space vehicle, the maintenance-free dual-mode attitude control power system comprising: a positive feedback circulation system, a thruster group, a gas generator, a fuel tank and an oxidant tank; the positive feedback circulation system is used for self-pressurization of the attitude control power system; the positive feedback circulation system comprises: a gunpowder starter, a differential tank, a liquid circuit pressure regulating valve, a gas generator and a pressurization check valve; the thruster group comprises: a gas thruster, a monopropellant thruster and a bipropellant thruster; the inlet of the gas generator is connected to the positive feedback circulation system; the outlet is connected to the gas thruster, the fuel tank and the oxidant tank; the fuel tank and the oxidant tank are connected to the thruster group.

[0009] In the maintenance-free dual-mode attitude control power system as described above, a safety valve and a combined check valve are provided on the pipelines connecting the gas generator with the fuel tank and the oxidant tank.

[0010] The maintenance-free dual-mode attitude control power system as described above, wherein the differential tank comprises: a differential tank liquid chamber housing, a differential tank air chamber housing, a vent nozzle, a differential piston, a filling and discharge valve and a differential tank outlet liquid circuit diaphragm valve; the differential piston is arranged in the differential tank liquid chamber housing and the differential tank air chamber housing, and the differential piston divides the differential tank liquid chamber housing and the differential tank air chamber housing into a differential tank liquid chamber and a differential tank air chamber; the vent nozzle is arranged on the differential tank air chamber housing and is communicated with the differential tank air chamber; the filling and discharge valve is arranged on the differential tank liquid chamber housing and is communicated with the differential tank liquid chamber; the differential tank outlet liquid circuit diaphragm valve is arranged on the differential tank liquid chamber housing.

[0011] The maintenance-free dual-mode attitude control power system as described above, wherein the fuel tank comprises a fuel tank air cavity shell, a fuel tank liquid cavity shell, a fuel tank diaphragm, a fuel tank air path diaphragm valve, a fuel tank vent nozzle, a fuel tank filling and discharge valve, and a fuel tank liquid path diaphragm valve. The fuel tank diaphragm divides the internal space of the fuel tank air cavity shell and the fuel tank liquid cavity shell into a fuel tank air cavity and a fuel tank liquid cavity respectively; the fuel tank air path diaphragm valve and the fuel tank vent nozzle are arranged at the inlet of the fuel tank; the fuel tank filling and discharge valve and the fuel tank liquid path diaphragm valve are arranged at the outlet of the fuel tank.

[0012] The maintenance-free dual-mode attitude control power system as described above, wherein the oxidizer tank comprises an oxidizer tank air cavity shell, an oxidizer tank liquid cavity shell, an oxidizer tank diaphragm, an oxidizer tank air circuit diaphragm valve, an oxidizer tank vent nozzle, an oxidizer tank filling and discharge valve and an oxidizer tank liquid circuit diaphragm valve; the oxidizer tank diaphragm divides the internal space of the oxidizer tank air cavity shell and the oxidizer tank liquid cavity shell into an oxidizer tank air cavity and an oxidizer tank liquid cavity respectively; the oxidizer tank air circuit diaphragm valve and the oxidizer tank vent nozzle are arranged at the inlet of the oxidizer tank; the oxidizer tank filling and discharge valve and the oxidizer tank liquid circuit diaphragm valve are arranged at the outlet of the oxidizer tank.

[0013] The maintenance-free dual-mode attitude control power system as described above, wherein the monopropellant thruster includes a monopropellant solenoid valve and a monopropellant thrust chamber; and the bipropellant thruster includes a fuel solenoid valve, an oxidizer solenoid valve and a bipropellant thrust chamber.

[0014] The maintenance-free dual-mode attitude control power system as described above, wherein the gas generator inlet and outlet are respectively equipped with a gas generator inlet diaphragm valve and a gas generator outlet diaphragm valve.

[0015] The maintenance-free dual-mode attitude control power system as described above, wherein, after the space vehicle is launched, when the attitude control power system receives a start command, the system enters a start filling state; the gunpowder starter explodes to generate high-temperature and high-pressure combustion gas, the hot combustion gas breaks through the diaphragm valve at the outlet of the gunpowder starter, fills into the air cavity of the differential tank, and squeezes the fuel in the differential tank through the differential piston, and when the fuel reaches a certain pressure, it breaks through the diaphragm valve of the liquid circuit at the outlet of the differential tank, and flows through the liquid circuit pressure-stabilizing valve into the gas generator.

[0016] As described above, the maintenance-free dual-mode attitude control power system, wherein the gas path generated by the gas generator is divided into three paths, the first path flows into the differential tank air cavity through the differential tank boost check valve, the second path is filled in front of the gas thruster, and the third path passes through the combined check valve and respectively breaks through the fuel tank gas path diaphragm valve and the oxidizer tank gas path diaphragm valve to enter the fuel tank and the oxidizer tank.

[0017] The maintenance-free dual-mode attitude control power system as described above, wherein, after the gas generator receives a work instruction, the gas pipeline pressure decreases due to the discharge of gas; after the single-propellant thruster and the bipropellant thruster receive a work instruction, the fuel tank and the oxidizer tank have their air cavity volumes increased and their pressures decreased due to the outflow of propellant; the reduction in air cavity pressure of the fuel tank and the oxidizer tank is transmitted to the outlet cavity of the upstream liquid circuit pressure regulating valve, the liquid circuit pressure regulating valve opens, and the fuel flows from the differential tank through the liquid circuit pressure regulating valve into the gas generator, generating gas to supplement the downstream pressure, and the differential tank has its air cavity volume increased and its pressure decreased due to the outflow of fuel, and when the gas cavity pressure is less than the gas pipeline pressure upstream of the boost check valve, the boost check valve opens, and the system enters a positive feedback working state.

[0018] The beneficial effects achieved by this application are as follows:

[0019] (1) This application adopts a single-propellant and dual-propellant dual-mode attitude control power system, which combines the advantages of small thrust and good pulse performance of a single-propellant system and high specific impulse of a dual-propellant system.

[0020] (2) The present application realizes the fuel pressurization function through the area difference between the differential piston air chamber and the differential piston liquid chamber; realizes the self-pressurization function of the attitude control power system through the positive feedback circulation system composed of a gunpowder starter, a differential tank, a liquid circuit pressure-stabilizing valve, a gas generator and a pressurization check valve, eliminates the high-pressure gas cylinder and the charging link, and improves the usability and maintainability.

[0021] (3) The differential tank, fuel tank and oxidizer tank of the present application all adopt an integrated design, which enables early filling of propellant, simplifies launch preparation work, and shortens launch preparation time.

[0022] (4) The present application utilizes two components, fuel and oxidizer, and achieves optimal performance of the attitude control power system under different thrusts and different working modes through the combined use of gas thrusters, single-component thrusters and dual-component thrusters.

[0023] (5) The differential tank of the present application adopts an integrated design. The air chamber integrates the gunpowder starter, the boost check valve and the vent nozzle, and the liquid chamber integrates the filling and discharge valve and the differential tank outlet liquid circuit diaphragm valve, thereby realizing the propellant pre-packaging function in the differential tank.

[0024] (6) The fuel tank and oxidizer tank of the present application adopt an integrated design. The fuel tank air cavity and the oxidizer tank air cavity are integrated with a vent nozzle and an air circuit diaphragm valve, and the fuel tank liquid cavity and the oxidizer tank liquid cavity are integrated with a filling and discharge valve and a liquid circuit diaphragm valve, thereby realizing the pre-packaging function of the fuel tank and the oxidizer tank.

[0025] (7) The attitude control power system of the present application can be adapted to various application scenarios of aerospace vehicles such as launch vehicles, upper stages, satellites, and spacecraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present application. For those skilled in the art, other drawings can also be obtained based on these drawings.

[0027] Figure 1 This is a schematic structural diagram of a maintenance-free dual-mode attitude control power system according to an embodiment of the present application.

[0028] Figure numerals: 1-differential tank; 2-liquid circuit pressure stabilizing valve; 3-boosting non-return valve; 4-gas generator; 5-safety valve; 6-combined non-return valve; 7-monopropellant thruster; 8-bipropellant thruster; 9-fuel tank; 10-oxidizer tank; 11-differential tank liquid chamber shell; 12-differential tank gas chamber shell; 13-vent nozzle; 14-differential piston; 15-filling discharge valve; 16-propellant starter; 17-differential tank outlet liquid circuit diaphragm valve; 18-propellant starter outlet diaphragm valve; 20-gas thruster; 41-gas generator inlet diaphragm valve; 42-gas generator outlet diaphragm valve; 71-monopropellant thrust chamber; 72 -single component solenoid valve; 81-two component thrust chamber; 82-oxidizer solenoid valve; 83-fuel solenoid valve; 91-fuel tank air cavity shell; 92-fuel tank liquid cavity shell; 93-fuel tank diaphragm; 94-fuel tank air circuit diaphragm valve; 95-fuel tank vent nozzle; 96-fuel tank filling and discharge valve; 97-fuel tank liquid circuit diaphragm valve; 101-oxidizer tank air cavity shell; 102-oxidizer tank liquid cavity shell; 103-oxidizer tank diaphragm; 104-oxidizer tank air circuit diaphragm valve; 105-oxidizer tank vent nozzle; 106-oxidizer tank filling and discharge valve; 107-oxidizer tank liquid circuit diaphragm valve. DETAILED DESCRIPTION

[0029] The following is a clear and complete description of the technical solutions in the embodiments of the present application in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0030] like Figure 1As shown, the present application provides a maintenance-free dual-mode attitude control power system for installation in a space vehicle, the maintenance-free dual-mode attitude control power system comprising: a positive feedback circulation system, a thruster group, a gas generator 4, a fuel tank 9 and an oxidant tank 10; the positive feedback circulation system is used for self-pressurization of the attitude control power system; the positive feedback circulation system comprises: a gunpowder starter 16, a differential tank 1, a liquid circuit pressure regulating valve 2, a gas generator 4 and a pressurization check valve 3; the thruster group comprises: a gas thruster 20, a monopropellant thruster 7 and a bipropellant thruster 8; the inlet of the gas generator 4 is connected to the positive feedback circulation system; the outlet is connected to the gas thruster 20, the fuel tank 9 and the oxidant tank 10; the fuel tank 9 and the oxidant tank 10 are connected to the thruster group.

[0031] Specifically, Figure 1 As shown, a maintenance-free dual-mode attitude control power system includes a differential tank 1, a hydraulic pressure regulating valve 2, a boost check valve 3, a gas generator 4, a safety valve 5, a combined check valve 6, a monopropellant thruster 7, a bipropellant thruster 8, a fuel tank 9, an oxidizer tank 10 and a gas thruster 20.

[0032] As a preferred embodiment of the present invention, the thrust of the gas thruster 20 is not greater than 20N, the thrust of the monopropellant thruster 7 is not greater than 300N, and the thrust of the bipropellant thruster 8 is not greater than 2000N.

[0033] like Figure 1 As shown, a safety valve 5 and a combination check valve 6 are arranged on the pipeline connecting the gas generator 4 with the fuel tank 9 and the oxidant tank 10. The safety valve 5 is used to prevent the system from overpressure, and the combination check valve 6 is used to prevent the gas in the fuel tank 9 and the oxidant tank 10 from returning to the upstream gas path.

[0034] like Figure 1 As shown, the differential tank 1 includes: a differential tank liquid chamber housing 11, a differential tank air chamber housing 12, a vent nozzle 13, a differential piston 14, a filling and discharge valve 15 and a differential tank outlet liquid circuit diaphragm valve 17; a differential piston 14 is arranged in the differential tank liquid chamber housing 11 and the differential tank air chamber housing 12, and the differential piston 14 divides the differential tank liquid chamber housing 11 and the differential tank air chamber housing 12 into a differential tank liquid chamber and a differential tank air chamber; the vent nozzle 13 is arranged on the differential tank air chamber housing 12 and is connected to the differential tank air chamber; the filling and discharge valve 15 is arranged on the differential tank liquid chamber housing 11 and is connected to the differential tank liquid chamber; the differential tank outlet liquid circuit diaphragm valve 17 is arranged on the differential tank liquid chamber housing 11.

[0035] like Figure 1 As shown, the powder starter 16 and the powder starter outlet diaphragm valve 18 are mounted on the differential tank air chamber housing 12.

[0036] like Figure 1As shown, the fuel tank 9 comprises a fuel tank air cavity shell 91, a fuel tank liquid cavity shell 92, a fuel tank diaphragm 93, a fuel tank air path diaphragm valve 94, a fuel tank vent nozzle 95, a fuel tank filling and discharge valve 96 and a fuel tank liquid path diaphragm valve 97. The fuel tank diaphragm 93 divides the internal space of the fuel tank air cavity shell 91 and the fuel tank liquid cavity shell 92 into a fuel tank air cavity and a fuel tank liquid cavity respectively; the fuel tank air path diaphragm valve 94 and the fuel tank vent nozzle 95 are arranged at the inlet of the fuel tank; the fuel tank filling and discharge valve 96 and the fuel tank liquid path diaphragm valve 97 are arranged at the outlet of the fuel tank 9.

[0037] like Figure 1 As shown, the oxidant tank 10 includes an oxidant tank air cavity shell 101, an oxidant tank liquid cavity shell 102, an oxidant tank diaphragm 103, an oxidant tank gas path diaphragm valve 104, an oxidant tank vent nozzle 105, an oxidant tank filling and discharge valve 106 and an oxidant tank liquid path diaphragm valve 107; the oxidant tank diaphragm 103 separates the internal space of the oxidant tank air cavity shell 101 and the oxidant tank liquid cavity shell 102 into an oxidant tank air cavity and an oxidant tank liquid cavity respectively; the oxidant tank air path diaphragm valve 104 and the oxidant tank vent nozzle 105 are arranged at the inlet of the oxidant tank 10; the oxidant tank filling and discharge valve 106 and the oxidant tank liquid path diaphragm valve 107 are arranged at the outlet of the oxidant tank 10.

[0038] like Figure 1 As shown, the monopropellant thruster 7 includes a monopropellant solenoid valve 72 and a monopropellant thrust chamber 71 ; the bipropellant thruster 8 includes a fuel solenoid valve 83 , an oxidant solenoid valve 82 and a bipropellant thrust chamber 81 .

[0039] like Figure 1 As shown, the inlet and outlet of the gas generator 4 are respectively provided with a gas generator inlet diaphragm valve 41 and a gas generator outlet diaphragm valve 42. The outlet of the propellant starter 16 is provided with a gas generator outlet diaphragm valve 42 to prevent the propellant starter 16 from being damp.

[0040] As a specific embodiment of the present invention, after the space vehicle is launched, when the attitude control power system receives a start command, the system enters a start filling state; the gunpowder starter 16 explodes to generate high-temperature and high-pressure combustion gas, and the hot combustion gas breaks through the gunpowder starter outlet diaphragm valve 18, fills into the differential tank air cavity, and squeezes the fuel in the differential tank 1 through the differential piston 14. When the fuel reaches a certain pressure, it breaks through the differential tank outlet liquid circuit diaphragm valve 17, and flows through the liquid circuit pressure regulating valve 2 into the gas generator 4.

[0041] As a specific embodiment of the present invention, the gas path generated by the gas generator 4 is divided into three paths. The first path flows into the differential tank air cavity through the differential tank boost check valve 3, the second path is filled in front of the gas thruster 20, and the third path passes through the combined check valve 6 and respectively squeezes the fuel tank gas path diaphragm valve 94 and the oxidant tank gas path diaphragm valve 104 to enter the fuel tank 9 and the oxidant tank 10.

[0042] As a specific embodiment of the present invention, before the attitude control power system is installed on the space vehicle, fuel is added to the differential tank 1 through the differential tank filling and relief valve 15, and the fuel is hydrazine, anhydrous hydrazine, single thrust-3, etc.; fuel is added to the fuel tank 9 through the fuel tank filling and relief valve 96, and the fuel is the same as the fuel in the differential tank 1; oxidant is added to the oxidant tank 10 through the oxidant tank filling and relief valve 106, and the oxidant is nitrogen tetroxide.

[0043] As a specific embodiment of the present invention, after the attitude control power system is installed on the space vehicle, the differential tank outlet liquid circuit diaphragm valve 17 seals the fuel in the differential tank liquid chamber. In order to prevent the gunpowder starter 16 from getting wet, a gas generator outlet diaphragm valve 42 is provided at the outlet of the gunpowder starter 16. The fuel tank liquid circuit diaphragm valve 97 seals the fuel between the fuel tank liquid chamber shell 92 and the fuel tank diaphragm 93. The fuel tank diaphragm 93 is usually made of aluminum or titanium alloy. The oxidizer tank liquid circuit diaphragm valve 107 seals the oxidizer between the oxidizer tank liquid chamber shell 102 and the oxidizer tank diaphragm 103. The oxidizer tank diaphragm 103 is usually made of aluminum or titanium alloy.

[0044] As a specific embodiment of the present invention, after the launch of the space vehicle, when the attitude control power system receives the start command, the system enters the start filling state. The gunpowder starter 16 is detonated to generate high-temperature and high-pressure combustion gas, and the hot combustion gas breaks through the gunpowder starter outlet diaphragm valve 18, fills into the differential tank air cavity, and squeezes the fuel in the differential tank 1 through the differential piston 14. When the fuel reaches a certain pressure, it squeezes the differential tank outlet liquid circuit diaphragm valve 17, and flows through the liquid circuit pressure regulating valve 2 into the gas generator 4. The fuel is catalytically decomposed by the catalyst bed in the gas generator 4 to generate high-temperature and high-pressure combustion gas. When the combustion gas reaches a certain pressure, it breaks through the gas generator outlet diaphragm valve 42 to fill the downstream pipeline. The fuel gas path is divided into three paths. The first path flows into the differential tank gas cavity through the differential tank boost check valve 3, the second path is filled in front of the gas thruster 20, and the third path passes through the combined check valve 6 and respectively squeezes the fuel tank gas path diaphragm valve 94 and the oxidant tank gas path diaphragm valve 104 to enter the fuel tank 9 and the oxidant tank 10. Specifically, after the fuel pressure increases, the fuel tank liquid path diaphragm valve 97 is squeezed and flows out of the fuel tank 9. After the oxidant pressure increases, the oxidant tank liquid path diaphragm valve 107 is squeezed and flows out of the oxidant tank 10. The fuel is filled in front of the solenoid valve of the monopropellant thruster 7 and in front of the fuel solenoid valve 83 of the bipropellant thruster 8, and the oxidant is filled in front of the oxidant solenoid valve 82 of the bipropellant thruster 8.

[0045] As a specific embodiment of the present invention, during the filling process, the pressures in the gas pipeline and the propellant tank gradually increase. When the gas pipeline pressure is greater than the differential tank air cavity pressure, the boost check valve 3 opens, and the gas in the pipeline flows into the differential tank air cavity for pressurization. The differential tank liquid cavity pressure increases synchronously under the amplification effect of the differential piston 14. The fuel in the differential tank liquid cavity is continuously supplied to the gas generator 4 downstream, resulting in a further increase in the downstream gas pipeline pressure. The gas in the gas pipeline continues to flow into the differential tank air cavity to pressurize it, thereby increasing the differential tank liquid cavity pressure and the gas pipeline pressure again. That is, under the action of this positive feedback mechanism, the system pressure rises rapidly until the outlet pressure of the liquid circuit pressure-stabilizing valve 2 reaches its set closing pressure. The liquid circuit pressure-stabilizing valve 2 is closed, and the gas generator 4 stops working, the startup filling process is completed, and the system enters a working standby state.

[0046] As a specific embodiment of the present invention, after the gas generator 4 receives the working instruction, the gas pipeline pressure decreases due to the discharge of gas; after the monopropellant thruster 7 and the bipropellant thruster 8 receive the working instruction, the fuel tank 9 and the oxidizer tank 10 have their air cavity volumes increased and their pressures decreased due to the outflow of propellant; the reduction in air cavity pressure of the fuel tank 9 and the oxidizer tank 10 is transmitted to the outlet cavity of the upstream liquid circuit pressure regulating valve 2, the liquid circuit pressure regulating valve opens, and the fuel flows from the differential tank 1 through the liquid circuit pressure regulating valve 2 into the gas generator 4 to generate gas, the generated gas supplements the downstream pressure, and the differential tank 1 has its air cavity volume increased and its pressure decreased due to the outflow of fuel, when the gas cavity pressure is less than the gas pipeline pressure upstream of the boost check valve 3, the boost check valve 3 opens, and the system enters a positive feedback working state.

[0047] The beneficial effects achieved by this application are as follows:

[0048] (1) This application adopts a single-propellant and dual-propellant dual-mode attitude control power system, which combines the advantages of small thrust and good pulse performance of a single-propellant system and high specific impulse of a dual-propellant system.

[0049] (2) The present application realizes the fuel pressurization function through the area difference between the differential piston air chamber and the differential piston liquid chamber; realizes the self-pressurization function of the attitude control power system through the positive feedback circulation system composed of a gunpowder starter, a differential tank, a liquid circuit pressure-stabilizing valve, a gas generator and a pressurization check valve, eliminates the high-pressure gas cylinder and the charging link, and improves the usability and maintainability.

[0050] (3) The differential tank, fuel tank and oxidizer tank of the present application all adopt an integrated design, which enables early filling of propellant, simplifies launch preparation work, and shortens launch preparation time.

[0051] (4) The present application utilizes two components, fuel and oxidizer, and achieves optimal performance of the attitude control power system under different thrusts and different working modes through the combined use of gas thrusters, single-component thrusters and dual-component thrusters.

[0052] (5) The differential tank of the present application adopts an integrated design. The air chamber integrates the gunpowder starter, the boost check valve and the vent nozzle, and the liquid chamber integrates the filling and discharge valve and the differential tank outlet liquid circuit diaphragm valve, thereby realizing the propellant pre-packaging function in the differential tank.

[0053] (6) The fuel tank and oxidizer tank of the present application adopt an integrated design. The fuel tank air cavity and the oxidizer tank air cavity are integrated with a vent nozzle and an air circuit diaphragm valve, and the fuel tank liquid cavity and the oxidizer tank liquid cavity are integrated with a filling and discharge valve and a liquid circuit diaphragm valve, thereby realizing the pre-packaging function of the fuel tank and the oxidizer tank.

[0054] (7) The attitude control power system of the present application can be adapted to various application scenarios of aerospace vehicles such as launch vehicles, upper stages, satellites, and spacecraft.

[0055] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, "plurality" means two or more, unless otherwise clearly and specifically defined.

[0056] In the description of the present application, the word "for example" is used to mean "used as an example, illustration or explanation". Any embodiment described as "for example" in the present application is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is given to enable any technician in the field to implement and use the present invention. In the following description, details are listed for the purpose of explanation. It should be understood that a person of ordinary skill in the art can recognize that the present invention can be implemented without using these specific details. In other examples, well-known structures and processes will not be elaborated in detail to avoid obscuring the description of the present invention with unnecessary details. Therefore, the present invention is not intended to be limited to the embodiments shown, but is consistent with the widest scope consistent with the principles and features disclosed in the present application.

[0057] The above description is only an embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent substitution, improvement, etc. made within the spirit and principle of the present invention should be included in the scope of the claims of the present invention.

Claims

1. A maintenance-free dual-mode attitude control power system for installation on a space vehicle, characterized in that: The maintenance-free dual-mode attitude control power system includes: a positive feedback loop system, a thruster group, a gas generator, a fuel tank and an oxidizer tank; The positive feedback loop system is used for self-pressurization of the attitude control power system; the positive feedback loop system includes: a propellant starter, a differential tank, a hydraulic pressure regulating valve, a gas generator and a pressurization check valve; The thruster group includes: gas thruster, monopropellant thruster and bipropellant thruster; The inlet of the gas generator is in communication with the positive feedback loop system; the outlet is in communication with the gas thruster, the fuel tank and the oxidant tank; The fuel tank and the oxidizer tank are in communication with the thruster group.

2. The maintenance-free dual-mode attitude control power system according to claim 1, characterized in that: A safety valve and a combined check valve are provided on the pipelines connecting the gas generator with the fuel tank and the oxidant tank.

3. The maintenance-free dual-mode attitude control power system according to claim 1, characterized in that: The differential tank comprises: a differential tank liquid chamber housing, a differential tank air chamber housing, a vent nozzle, a differential piston, a filling and discharge valve and a differential tank outlet liquid circuit diaphragm valve; The differential tank liquid chamber housing and the differential tank air chamber housing are provided with the differential piston, and the differential piston divides the differential tank liquid chamber housing and the differential tank air chamber housing into a differential tank liquid chamber and a differential tank air chamber; The vent nozzle is arranged on the differential tank air cavity housing and is communicated with the differential tank air cavity; The filling and discharge valve is arranged on the differential tank liquid cavity housing and is in communication with the differential tank liquid cavity; The differential tank outlet liquid circuit diaphragm valve is arranged on the differential tank liquid chamber housing.

4. The maintenance-free dual-mode attitude control power system according to claim 1, characterized in that: The fuel tank comprises a fuel tank air cavity shell, a fuel tank liquid cavity shell, a fuel tank diaphragm, a fuel tank air path diaphragm valve, a fuel tank vent nozzle, a fuel tank filling and discharge valve and a fuel tank liquid path diaphragm valve. The fuel tank diaphragm separates the internal space of the fuel tank air cavity shell and the fuel tank liquid cavity shell into a fuel tank air cavity and a fuel tank liquid cavity respectively; The fuel tank gas path diaphragm valve and the fuel tank vent nozzle are arranged at the inlet of the fuel tank; The fuel tank filling and discharge valve and the fuel tank liquid path diaphragm valve are arranged at the outlet of the fuel tank.

5. The maintenance-free dual-mode attitude control power system according to claim 1, characterized in that: The oxidant tank comprises an oxidant tank air cavity shell, an oxidant tank liquid cavity shell, an oxidant tank diaphragm, an oxidant tank air path diaphragm valve, an oxidant tank vent nozzle, an oxidant tank filling and discharge valve, and an oxidant tank liquid path diaphragm valve; The oxidant tank diaphragm divides the inner spaces of the oxidant tank air cavity shell and the oxidant tank liquid cavity shell into an oxidant tank air cavity and an oxidant tank liquid cavity, respectively; The oxidant tank gas path diaphragm valve and the oxidant tank vent nozzle are arranged at the inlet of the oxidant tank; The oxidant tank filling and discharge valve and the oxidant tank liquid path diaphragm valve are arranged at the outlet of the oxidant tank.

6. The maintenance-free dual-mode attitude control power system according to claim 1, characterized in that: The monopropellant thruster includes a monopropellant electromagnetic valve and a monopropellant thrust chamber; the bipropellant thruster includes a fuel electromagnetic valve, an oxidizer electromagnetic valve and a bipropellant thrust chamber.

7. The maintenance-free dual-mode attitude control power system according to claim 1, characterized in that: The gas generator inlet and outlet are respectively equipped with a gas generator inlet diaphragm valve and a gas generator outlet diaphragm valve.

8. The maintenance-free dual-mode attitude control power system according to claim 3, characterized in that: After the space vehicle is launched, when the attitude control power system receives the start command, the system enters the start-up filling state; The pyrotechnic starter explodes to generate high-temperature and high-pressure gas. The hot gas breaks through the diaphragm valve at the outlet of the pyrotechnic starter and fills into the air cavity of the differential tank. The fuel in the differential tank is squeezed through the differential piston. When the fuel reaches a certain pressure, it breaks through the diaphragm valve at the outlet of the differential tank and flows through the liquid pressure-stabilizing valve into the gas generator.

9. The maintenance-free dual-mode attitude control power system according to claim 8, characterized in that: The gas generated by the gas generator is divided into three paths. The first path flows into the differential tank air cavity through the differential tank boost one-way valve, the second path is filled in front of the gas thruster, and the third path passes through the combined check valve and squeezes through the fuel tank gas path diaphragm valve and the oxidizer tank gas path diaphragm valve to enter the fuel tank and oxidizer tank respectively.

10. The maintenance-free dual-mode attitude control power system according to claim 1, characterized in that: After the gas generator receives the working instruction, the gas pipeline pressure decreases due to the discharge of gas; after the monopropellant thruster and the bipropellant thruster receive the working instruction, the fuel tank and the oxidizer tank have their air cavity volumes increased and their pressures decreased due to the outflow of propellant; the reduction in air cavity pressure of the fuel tank and the oxidizer tank is transmitted to the outlet cavity of the upstream liquid circuit pressure-stabilizing valve, the liquid circuit pressure-stabilizing valve opens, and the fuel flows from the differential tank through the liquid circuit pressure-stabilizing valve into the gas generator, generating gas to supplement the downstream pressure, and the differential tank has its air cavity volume increased and its pressure decreased due to the outflow of fuel. When the gas cavity pressure is less than the pressure of the gas pipeline upstream of the boost check valve, the boost check valve opens, and the system enters a positive feedback working state.

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