Non-toxic reusable attitude and orbit control power system

Abstract

The invention provides a non-toxic reusable attitude and orbit control power system. The non-toxic reusable attitude and orbit control power system comprises a gas cylinder (1), a high-pressure self-locking valve (2), a pressure reducing valve (3), a storage tank (4), a low-pressure self-locking valve (5), a gas-driven turbine pump (6), a gas generator (10), a gas valve (12), an ignition charge bag (13), an injector (14) and an oxygen-enriched solid rocket engine (15). A novel structure principle form is provided by combining the extrusion type principle and the pumping pressure type principle of the liquid rocket engine and the characteristics of the liquid rocket engine and the solid rocket engine, and the provided power can be used as anti-missile and precise impact missile orbit control and attitude control force.

Description

Technical Field

[0001] The present invention belongs to the technical field of aerospace vehicle and weapon missile power systems, and in particular relates to a non-toxic and reusable attitude and orbit control power system. Background Art

[0002] The power system is a core component of weapons and equipment. The working medium of traditional attitude and orbit control power systems uses toxic and self-igniting propellants, which are costly and difficult to maintain. Leakage poses the risk of explosion and is not conducive to long-term storage.

[0003] There is an urgent need for a green and safe working medium that can achieve multiple functions through novel structural principles, simplify product types and quantities, solve the shortcomings of the current power systems in the field of weapons and missiles, and achieve green, non-toxic, easy maintenance and low cost.

[0004] Patent document CN111946490A discloses a gas-boosted attitude and orbit control propulsion system based on an electric pump. Its core boosting method relies on the gas generated by the autolysis of monopropellants. However, these autopropellants are highly toxic and chemically reactive. A leak of these propellants could result in poisoning, fire, or explosion. The present invention, however, uses non-toxic kerosene to generate gas through an electric ignition process, which in turn drives a turbopump for boosting pressure. This boosting method offers the advantages of being non-toxic and reusable. Summary of the Invention

[0005] In view of the defects in the prior art, the purpose of the present invention is to provide a non-toxic and reusable attitude and orbit control power system.

[0006] According to the present invention, a non-toxic and reusable attitude and orbit control power system is provided, comprising: a gas cylinder 1, a high-pressure self-locking valve 2, a pressure reducing valve 3, a storage tank 4, a low-pressure self-locking valve 5, a gas-driven turbopump 6, a gas generator 10, a gas valve 12, an ignition charge 13, an injector 14, and an oxygen-enriched solid rocket engine 15;

[0007] The outlet of the gas cylinder 1 storing air is connected to the inlet of the high-pressure self-locking valve 2, the outlet of the high-pressure self-locking valve 2 is connected to the inlet of the pressure reducing valve 3, and the outlet of the pressure reducing valve 3 is connected to the inlet of the air cavity of the storage tank 4 and the air path inlet of the gas generator 10;

[0008] One outlet of the liquid chamber of the kerosene storage tank 4 is connected to the liquid inlet of the gas generator 10, and the other outlet is connected to the inlet of the low-pressure latching valve 5. The outlet of the low-pressure latching valve 5 is connected to the liquid inlet of the gas turbine pump 6. One outlet of the gas generator 10 is connected to the inlet of the gas valve 12, and the other outlet is connected to the hot gas drive line of the gas turbine pump 6.

[0009] The gas generator 10 generates gas and generates attitude control thrust by controlling the energization of the gas valve 12;

[0010] The ignition charge 13 ignites the oxygen-enriched solid propellant to start working. The low-pressure self-locking valve 5 is opened and the gas drives the turbo pump 6 to further increase the pressure of the kerosene and change the supply flow rate. The solid oxygen-enriched propellant of the oxygen-enriched solid rocket motor 15 is mixed and burned by the injector 14 to generate orbit control thrust.

[0011] The speed of the gas turbine pump 6 is controlled by the gas generator 10 to adjust the orbit control thrust.

[0012] Preferably, when the high-pressure self-locking valve 2 is in the open state, the high-pressure air in the air cylinder 1 is reduced in pressure and stabilized by the pressure reducing valve 3 and output to the storage tank 4 and the air inlet of the solenoid valve of the gas generator 10 to achieve system pressure building.

[0013] Preferably, the gas turbine pump 6 increases the pressure of the upstream kerosene and supplies it to the downstream at a variable flow rate.

[0014] Preferably, it further comprises: a filling port;

[0015] The filling port is between the outlet of the gas cylinder 1 and the inlet of the high-pressure self-locking valve 2, and between the outlet of the liquid cavity of the storage tank 4 and the inlet of the low-pressure self-locking valve 5.

[0016] Preferably, it further comprises: a pressure sensor 7;

[0017] The pressure sensor 7 monitors the working pressure of the storage tank 4. When the pressure exceeds the limit, the gas circuit solenoid valve and the gas valve 12 of the gas generator 10 are triggered to open according to the working pressure, and the high-pressure self-locking valve 2 is closed.

[0018] Preferably, it further comprises: a temperature sensor 11;

[0019] The temperature sensor 11 monitors the gas temperature at the outlet of the gas generator 10. When the temperature is higher than a threshold value, all downstream gas valves 12 are triggered to open according to the gas temperature.

[0020] Preferably, kerosene is squeezed to the gas generator inlet and the turbine pump inlet through air, and the combustion of air and kerosene produces high-pressure gas to drive the turbine to do work, driving the centrifugal pump to further increase the kerosene pressure and supply it to the oxygen-enriched solid engine fuel inlet.

[0021] Preferably, air participates in the combustion as the extrusion gas and oxidant, and a part of the combustion gas is used as hot gas to perform work on the gas-driven turbine pump 6, and the kerosene pressure is increased to a specified adjustable pressure through the gas-driven turbine pump 6, and then variable thrust is provided by combustion of the oxygen-enriched solid engine.

[0022] According to the present invention, a spacecraft is provided, comprising the non-toxic and reusable attitude and orbit control power system.

[0023] A weapon missile provided by the present invention includes the non-toxic and reusable attitude and orbit control power system.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] 1. The present invention combines the extrusion and pump-pressure principles of liquid rocket engines, and the characteristics of liquid rocket engines and solid rocket engines to propose a novel structural principle form. The power provided can be used as the trajectory control and attitude control force for anti-missile and precision strike missiles.

[0026] 2. The power system of the present invention utilizes inexpensive propellants consisting of air, kerosene, and oxygen-enriched solid gunpowder. This makes the power system non-toxic, easy to maintain, cost-effective, convenient to transport, and safe to store. The working medium is safe and non-toxic, the system is easy to maintain, and the system can be easily recovered and reused.

[0027] 3. The present invention's combination of extrusion and pump-type operating principles, along with the gas valve and solid-liquid hybrid engine operating modes, improves system efficiency and simplifies system complexity, eliminating some liquid attitude control engines and other components, reducing system weight and product variety. It is particularly suitable for use in missiles, providing attitude and trajectory control power for all phases of a mission.

[0028] 4. The present invention provides two-way self-locking valves for managing the long-term storage and working supply of gas and liquid. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0030] Figure 1 It is a structural schematic diagram of the present invention.

[0031] The figure shows:

[0032] DETAILED DESCRIPTION

[0033] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0034] The present invention relates to a non-toxic and reusable attitude and orbit control power system, in particular to a power system in the field of weapons and missiles. The first characteristic is that the fuel used in the system is green, non-toxic, easy to maintain, low-cost and reusable; the second characteristic is that the system has a novel structure, the orbit control can achieve adjustable thrust through a solid-liquid hybrid engine, and the attitude control can achieve repeatedly controllable thrust through a gas valve. In the solid-liquid hybrid attitude and orbit control power system provided by the present invention, the orbit control power adopts the principle of a pump-type liquid rocket, using the combustion of a solid-liquid hybrid engine to provide the main thrust; the attitude power adopts the principle of an extrusion liquid rocket engine, providing auxiliary attitude control thrust by controlling the high-temperature gas generated by a gas generator. The present invention solves the problems of the existing liquid attitude and orbit power systems of spacecraft or weapons and missiles, such as the difficulty in storing toxic propellants and the inconvenience in maintenance and use. In addition, the power raw materials used in the present invention are low-cost and the system is highly economical; the fuel is non-toxic and has a simple structure and can be reused after treatment; the system principle is novel and efficient, reducing the weight and volume of the system structure.

[0035] like Figure 1 As shown, the present invention provides a non-toxic and reusable attitude and orbit control power system, including a gas cylinder 1, a high-pressure self-locking valve 2, a pressure reducing valve 3, a storage tank 4, a low-pressure self-locking valve 5, a gas turbine pump 6, a pressure sensor 7, an igniter 8, an electric nozzle 9, a gas generator 10, a temperature sensor 11, a gas valve 12, an ignition charge 13, an injector 14, an oxygen-enriched solid rocket engine 15, and a filling port 16.

[0036] The functions of each stand-alone machine are as follows:

[0037] Gas cylinder 1 stores high-pressure air for extrusion and working medium;

[0038] The high-pressure self-locking valve 2 is used to control the circulation of high-pressure air;

[0039] The pressure reducing valve 3 is used to throttle and reduce the pressure of high-pressure air and stabilize the pressure to the low-pressure air specified downstream;

[0040] Storage tank 4 is used to store kerosene;

[0041] The low-pressure self-locking valve 5 is used to control the flow of kerosene;

[0042] The gas turbine pump 6 is used to increase the pressure of the upstream kerosene and supply it to the downstream at a variable flow rate;

[0043] The pressure sensor 7 is used to detect the outlet air of the pressure reducing valve 3 or the working pressure of the storage tank 4;

[0044] The igniter 8 and the electric nozzle 9 are used to ignite the air and kerosene;

[0045] The gas generator 10 is used to burn air and kerosene and provide gas output to the downstream for work;

[0046] The temperature sensor 11 is used to monitor the gas temperature;

[0047] The gas valve 12 is used to control the gas output to provide attitude control power;

[0048] The ignition charge 13 is used to ignite the solid motor powder;

[0049] The injector 14 is used to atomize the kerosene and fully mix it with the solid oxygen-enriched solid gunpowder;

[0050] The oxygen-rich solid rocket motor 15 is used to burn and generate variable orbit control thrust;

[0051] The filling port is used to add air and kerosene.

[0052] The present invention will be described in more detail below.

[0053] The outlet of gas cylinder 1 communicates with the inlet of high-pressure latching valve 2, which in turn communicates with the inlet of pressure-reducing valve 3, which in turn communicates with the gas chamber inlet of tank 4 and the gas inlet of gas generator 10. A pressure sensor 7 is installed at the outlet of pressure-reducing valve 3. One channel of the liquid chamber outlet of tank 4 communicates with the liquid inlet of gas generator 10 and another channel connects to the inlet of low-pressure latching valve 5. The outlet of low-pressure latching valve 5 connects to the liquid inlet of gas turbine pump 6. One channel of the gas generator 10 outlet connects to the inlet of gas valve 12 and another channel connects to the hot gas drive line of gas turbine pump 6. A temperature sensor 11 is installed at the outlet of gas generator 10. The liquid supply outlet of gas turbine pump 6 is connected to an injector 14 integrated into an oxygen-enriched solid rocket engine 15. An ignition charge 13 is installed within the oxygen-enriched solid rocket engine 15. Filling ports are installed between the outlet of gas cylinder 1 and the inlet of high-pressure latching valve 2, and between the outlet of the liquid chamber of tank 4 and the inlet of low-pressure latching valve 5.

[0054] The pressure sensor 7 monitors the working pressure of the storage tank 4. When overpressure occurs, the gas generator 10 gas circuit solenoid valve and gas valve 12 are opened in time, and the high-pressure self-locking valve 2 is closed, which plays a role in system pressure safety protection monitoring.

[0055] The temperature sensor 11 monitors the outlet gas temperature of the gas generator 10. When the temperature is higher than the threshold value, all downstream gas valves 12 are opened to play the role of temperature safety protection monitoring and troubleshooting.

[0056] The excitation end of the igniter 8 is connected to the electric nozzle of the gas generator 10, and the air and kerosene are ignited by electric sparks to generate high-temperature and high-pressure hot gas for power generation.

[0057] The gas valve 12 completes gas control through valve switching. The gas valve outlet is equipped with an expansion nozzle, which serves as a system attitude control engine and can control the thrust of the entire device attitude adjustment, auxiliary trimming, etc.

[0058] The oxygen-rich solid rocket motor 15 is a track control engine that can provide variable thrust for controlling orbit adjustment and large-scale ballistic shaping.

[0059] The working principle of the present invention is as follows:

[0060] This invention utilizes a combined pumping and extrusion principle. Air acts as the extrusion gas and oxidant in combustion. A portion of the resulting combustion gas serves as hot fuel gas to drive the turbine, generating work for the turbopump. The pump rapidly increases the kerosene pressure to a specified, adjustable pressure, which is then burned by the oxygen-enriched solid motor to provide variable thrust. Specifically, the kerosene is squeezed by air to the gas generator inlet and the turbopump inlet. The combustion of air and kerosene generates high-pressure fuel gas that propels the turbine, generating work. This fuel gas drives a centrifugal pump to further increase the kerosene pressure and supplies it to the fuel inlet of the oxygen-enriched solid motor. The remaining portion of the fuel gas is controlled by the on / off switching of a high-temperature gas valve to achieve attitude control.

[0061] More specifically, if Figure 1 As shown, when not working, the system is in a de-energized state, the valve is in a closed state, and high-pressure air and kerosene are stored in the gas cylinder 1 and the storage tank 4 respectively; when working, the system solenoid valve, igniter 8 and ignition charge 13 are opened or closed according to the control command. The specific work is system pressure building, attitude engine operation and orbit control engine operation. When the high-pressure self-locking valve 2 is in the open state, the high-pressure air in the air cylinder 1 is reduced in pressure and output to the storage tank 4 and the air path inlet of the solenoid valve of the gas generator 10 through the pressure reducing valve for stabilization. The system completes pressure building and adopts the rocket engine extrusion working principle; when the attitude control engine is working, the gas and liquid path solenoid valves and igniter of the gas generator 10 are controlled to be energized to generate gas, and the attitude control thrust is generated by controlling the energization of the gas valve 12. When the system temperature is too high, the four directions are opened at the same time to ensure system safety. The orbit control engine variable thrust start-up starts by igniting the oxygen-enriched solid propellant through the ignition charge 13, and further increases the pressure of kerosene and changes the supply flow rate by opening the low-pressure self-locking valve 5 and driving the gas-powered turbine pump. The solid oxygen-enriched propellant mixed with the oxygen-enriched solid rocket engine 15 is burned by the injector 14 to generate orbit control thrust. The speed of the gas turbine pump 6 is controlled by the gas generator 10, thereby realizing orbit control thrust adjustment.

[0062] The system is equipped with pressure sensors to monitor pressure entering the gas generator and gas turbine pump, and temperature sensors to measure the gas generator output temperature and monitor the operating environment of the gas valve and gas turbine. When pressure exceeds a safety threshold, the high-pressure latching valve closes to isolate the system. When temperature exceeds a safety threshold, all gas valves are opened to reduce the temperature.

[0063] More specifically, the orbital control thrust is generated by the combustion of a solid-liquid hybrid engine. The attitude control thrust is generated by the high-temperature gas generated by air and kerosene. The gas valve operates on the principle of a high-temperature solenoid valve, effectively controlling the high-temperature and high-pressure gas output by the gas generator. The flight attitude is controlled by opening and closing the gas valve, providing attitude control torque. The oxygen-enriched solid rocket engine can self-sustain combustion, achieving the optimal mixture ratio combustion output through the supplied kerosene, and the thrust can be adjusted according to the changes in the kerosene supply flow rate to control the flight trajectory.

[0064] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0065] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A non-toxic and reusable attitude and orbit control power system, characterized in that: include: Gas cylinder (1), high-pressure self-locking valve (2), pressure reducing valve (3), storage tank (4), low-pressure self-locking valve (5), gas-driven turbo pump (6), gas generator (10), gas valve (12), ignition charge (13), injector (14), oxygen-enriched solid rocket motor (15); The outlet of the gas cylinder (1) storing air is communicated with the inlet of the high-pressure self-locking valve (2), the outlet of the high-pressure self-locking valve (2) is communicated with the inlet of the pressure reducing valve (3), and the outlet of the pressure reducing valve (3) is communicated with the inlet of the gas cavity of the storage tank (4) and the gas path inlet of the gas generator (10); One outlet of the liquid chamber of the kerosene storage tank (4) is connected to the liquid inlet of the gas generator (10), and the other outlet is connected to the inlet of the low-pressure self-locking valve (5). The outlet of the low-pressure self-locking valve (5) is connected to the liquid inlet of the gas turbine pump (6). One outlet of the gas generator (10) is connected to the inlet of the gas valve (12), and the other outlet is connected to the hot gas drive path of the gas turbine pump (6). The gas generator (10) generates gas and generates attitude control thrust by controlling the energization of the gas valve (12); The ignition charge (13) ignites the oxygen-enriched solid propellant to start working, and the low-pressure self-locking valve (5) is opened and the gas drives the turbo pump (6) to achieve further pressure increase and supply flow change of the kerosene, and the solid oxygen-enriched propellant of the oxygen-enriched solid rocket engine (15) is mixed and burned through the injector (14) to generate orbit control thrust; The speed of the gas turbine pump (6) is controlled by the gas generator (10) to adjust the orbit control thrust.

2. The non-toxic and reusable attitude and orbit control power system according to claim 1 is characterized in that: When the high-pressure self-locking valve (2) is in the open state, the high-pressure air in the air cylinder (1) is reduced in pressure and output to the storage tank (4) and the air path inlet of the solenoid valve of the gas generator (10) through the pressure reducing valve (3) to achieve system pressure building.

3. The non-toxic and reusable attitude and orbit control power system according to claim 1 is characterized in that: The gas turbine pump (6) increases the pressure of the upstream kerosene and supplies it to the downstream at a variable flow rate.

4. The non-toxic and reusable attitude and orbit control power system according to claim 1 is characterized in that: Also includes: Filling port; The filling port is between the outlet of the gas cylinder (1) and the inlet of the high-pressure self-locking valve (2), and between the outlet of the liquid cavity of the storage tank (4) and the inlet of the low-pressure self-locking valve (5).

5. The non-toxic and reusable attitude and orbit control power system according to claim 1 is characterized in that: Also includes: Pressure sensor 7; The pressure sensor 7 monitors the working pressure of the storage tank (4). When the pressure exceeds the limit, the gas generator (10) gas circuit solenoid valve and the gas valve (12) are triggered to open according to the working pressure, and the high-pressure self-locking valve (2) is closed.

6. The non-toxic and reusable attitude and orbit control power system according to claim 1 is characterized in that: Also includes: Temperature sensor 11; The temperature sensor 11 monitors the gas temperature at the outlet of the gas generator (10). When the temperature is higher than a threshold value, all downstream gas valves (12) are triggered to open according to the gas temperature.

7. The non-toxic and reusable attitude and orbit control power system according to claim 1 is characterized in that: Kerosene is squeezed to the gas generator inlet and the turbine pump inlet through air. The combustion of air and kerosene produces high-pressure gas to drive the turbine to work, driving the centrifugal pump to further increase the kerosene pressure and supply it to the oxygen-enriched solid engine fuel inlet.

8. The non-toxic and reusable attitude and orbit control power system according to claim 1 is characterized in that: Air participates in the combustion as a compression gas and an oxidant, and a portion of the combustion gas acts as hot gas to perform work on the gas-driven turbine pump (6), thereby increasing the kerosene pressure to a specified adjustable pressure through the gas-driven turbine pump (6), and then providing variable thrust through combustion of the oxygen-enriched solid engine.

9. An aerospace vehicle, characterized in that: A non-toxic, reusable attitude and orbit control power system comprising any one of claims 1 to 8.

10. A weapon missile, characterized in that: A non-toxic, reusable attitude and orbit control power system comprising any one of claims 1 to 8.

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