CN117963182A - Lunar leap verification aircraft propulsion system - Google Patents

Abstract

The invention provides a lunar leap verification aircraft propulsion system, which comprises: the device comprises a gas cylinder, a high-pressure sensor, an inflation valve, a gas circuit high-pressure self-locking valve, a pressure reducing valve, a one-way valve, a gas circuit isolation self-locking valve, a gas circuit adding and discharging valve, a storage tank, a liquid circuit adding and discharging valve, a liquid circuit isolation self-locking valve, a pipeline adding and discharging valve, a rail control engine, a gesture control engine, a chamber pressure sensor and a low-pressure sensor. The invention solves the problems of oblique take-off, repeated propellant filling, propellant shaking, reliable propellant isolation and the like, and can be used for ground validators with lunar leaps.

Description

Lunar leap verification aircraft propulsion system

Technical Field

The invention relates to the technical field of aerospace propulsion systems, in particular to a lunar leap verification aircraft propulsion system.

Background

The lunar leap detector can leap and land on the lunar surface for many times, expands the moving range of the detector, and has great practical application and scientific research value. The lunar leap verifier mainly aims to test and verify an on-orbit control strategy and a working mode of a leap detector in a ground environment.

However, the existing propulsion system has the problems of oblique take-off, multiple propellant filling, propellant shaking, incapability of realizing reliable propellant isolation and the like;

In addition, during take-off, the posture of the detector changes severely, and if the propellant in the storage tank shakes, disturbance moment is brought to the detector.

Patent document CN115743621a discloses a propellant replenishing system for a multi-aircraft, which comprises a propellant replenishing system, a first propellant replenishing system and a second propellant replenishing system, wherein the propellant replenishing system comprises a first gas cylinder, a first high-pressure self-locking valve, a first pressure reducing valve, a first storage tank air cavity, a first storage tank liquid cavity, a first liquid path replenishing valve and a first liquid path quick-break valve driving end. However, the present patent cannot completely solve the existing technical problems, and cannot meet the needs of the present invention.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide a lunar leap verification aircraft propulsion system.

The lunar leap verification aircraft propulsion system provided by the invention comprises: the device comprises a gas cylinder, a high-pressure sensor, an inflation valve, a gas circuit high-pressure self-locking valve, a pressure reducing valve, a one-way valve, a gas circuit isolation self-locking valve, a gas circuit adding and discharging valve, a storage tank, a liquid circuit adding and discharging valve, a liquid circuit isolation self-locking valve, a pipeline adding and discharging valve, a rail control engine, a gesture control engine, a chamber pressure sensor and a low-pressure sensor;

The gas cylinder, the high-pressure sensor, the inflation valve and the gas path high-pressure self-locking valve are in star connection;

one end of the pressure reducing valve is connected with the other end of the gas path high-pressure self-locking valve, and the other end of the pressure reducing valve is sequentially connected with the one-way valve and the gas path isolation self-locking valve;

the gas circuit adding and discharging valve, the storage tank and the gas circuit isolation self-locking valve are connected in a triangular mode;

the storage tank, the liquid path adding and discharging valve and the liquid path isolation self-locking valve are connected in a triangular mode;

The liquid path isolation self-locking valve, the pipeline adding and discharging valve and the low pressure sensor are connected in a triangular mode;

The rail control engine is connected with the low pressure sensor;

The room pressure sensor is connected with the rail control engine;

The attitude control engine is connected with the two low pressure sensors in parallel, and the rail control engine is positioned between the two low pressure sensors.

Preferably, the storage tank adopts a rubber diaphragm as a propellant management device, the propellant discharge is realized through orderly overturning of the rubber diaphragm, and the propellant without air inclusion is provided for a downstream rail-controlled engine.

Preferably, the reservoir is a nonmetallic bladder reservoir.

Preferably, setting a redundant backup measure includes:

the oxidant and the gas circuit of the fuel storage tank are isolated through the serial arrangement of 2 groups of one-way valves and gas circuit isolation self-locking valves; connecting a liquid path isolation self-locking valve with an engine electromagnetic valve to manage liquid propellant;

Before the first ignition test, vacuumizing a liquid path through a pipeline adding and discharging valve; and after ignition is finished, closing the gas path isolation self-locking valve and the liquid path isolation self-locking valve.

Preferably, a pressure reducing valve is arranged between the gas path high-pressure self-locking valve and the one-way valve.

Preferably, the number of the storage tanks is 4, wherein 2 are filled with oxidant and 2 are filled with fuel, and the propellant is dinitrogen tetroxide or methyl hydrazine; the number of the gas cylinders is 1, and pressurized helium is filled.

Preferably, before working, the detector is powered on, and the liquid path isolation self-locking valve is opened to fill the engine pipeline with propellant; the high-pressure self-locking valve of the gas circuit is opened, the gas circuit isolation self-locking valve of the oxygen circuit and the fuel circuit is opened to pressurize the storage tank, the rail-controlled engine and the attitude-controlled engine are ignited according to the control time sequence, the system works in a constant-pressure mode, and 4 propellant storage tanks are synchronously output.

Preferably, after each working condition is finished, the gas path high-pressure self-locking valve, the one-way valve, the gas path isolation self-locking valve and the liquid path isolation self-locking valve are arranged to be closed, the ignition work of the engine is controlled for 5s, the ignition is carried out for 1-2 times, and the pressure of the engine pipeline is relieved to be within a preset safety range through the engine work.

Preferably, before the propellant is replenished, a gas circuit charging and discharging valve of the storage tank is opened, the storage tank is depressurized to normal pressure, the storage tank is connected with a filling device through a liquid circuit charging and discharging valve, and filling is carried out after a filling pipeline is vacuumized, and then filling is carried out.

Compared with the prior art, the invention has the following beneficial effects:

(1) The propulsion system overcomes the problems of oblique take-off, repeated propellant filling, propellant shaking, reliable propellant isolation and the like, and is used for a ground validator for lunar leaping;

(2) The rubber diaphragm storage box used in the invention has the advantages that the diaphragm can be tightly attached to the liquid level of the propellant, so that the propellant is prevented from shaking, and the interference moment is reduced;

(3) The storage tank adopts a nonmetallic bag type storage tank, so that the safety of repeated filling is ensured, and the requirements of repeated work and repeated filling in the ground test process are met; the method can correct the weight deviation caused by unbalanced consumption of the storage tank and deviation of mixing ratio of the engine by filling back the discharge mode, ensures accurate propellant quantity in the storage tank, is beneficial to stable mass center of the detector and is convenient for balancing;

(4) The attitude control engine adopts a pressure relief strategy, so that the condition of overpressure of a pipeline after the temperature of the propellant is increased during the product parking period is avoided;

(5) The propulsion system adopts thermal protection, so that adverse effects caused by plume and high temperature generated by ignition of the engine are reduced;

(6) The reliable isolation of the oxidant and the gas circuit of the fuel storage tank is ensured through the serial arrangement of the 2 groups of one-way valves and the gas circuit isolation self-locking valves; the outlet of the storage tank adopts a liquid path isolation self-locking valve scheme, which is used for ensuring the safety isolation between the storage tank and the downstream after filling and during the ground storage period until before ignition; the design of the gesture control engine branch adopts the redundant backup of the isolation self-locking valve, and the track control function and the gesture adjustment function borne by the gesture control engine realize the backup; the management of the liquid propellant adopts two-stage safety management of a liquid path isolation self-locking valve and an engine electromagnetic valve, so that the reliable and safe use of the propellant is ensured; before the first ignition test, the liquid path is vacuumized through the pipeline adding and discharging valve, so that the engine is prevented from working with air; after ignition is finished, the gas path self-locking valve and the liquid path self-locking valve are closed, so that the gas path and the liquid path of the storage tank are reliably isolated.

Drawings

Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:

FIG. 1 is a schematic diagram of a lunar leap verification aircraft propulsion system;

FIG. 2 is a schematic diagram of a typical nonmetallic semi-membrane tank.

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.

Examples

Referring to fig. 1, the present invention provides a lunar leap verification aircraft propulsion system comprising:

1. propulsion system assembly

The propulsion system comprises: the gas cylinder 1, the high pressure sensor 2, the inflation valve 3, the gas circuit high pressure self-locking valve 4, the pressure reducing valve 5, the one-way valve 6, the gas circuit isolation self-locking valve 7, the gas circuit adding and discharging valve 8, the storage tank 9, the liquid circuit adding and discharging valve 10, the liquid circuit isolation self-locking valve 11, the pipeline adding and discharging valve 12, the rail control engine 13, the attitude control engine 14, the room pressure sensor 15 and the low pressure sensor 16;

The gas cylinder 1, the high-pressure sensor 2, the inflation valve 3 and the gas path high-pressure self-locking valve 4 are in star connection;

one end of the pressure reducing valve 5 is connected with the other end of the air path high-pressure self-locking valve 4, and the other end of the pressure reducing valve 5 is sequentially connected with the one-way valve 6 and the air path isolation self-locking valve 7;

the gas circuit adding and discharging valve 8, the storage tank 9 and the gas circuit isolation self-locking valve 7 are connected in a triangular mode;

the storage tank 9, the liquid path adding and discharging valve 10 and the liquid path isolation self-locking valve 11 are connected in a triangular mode;

the liquid path isolation self-locking valve 11, the pipeline adding and discharging valve 12 and the low pressure sensor 16 are connected in a triangular mode;

the rail control engine 13 is connected with a low pressure sensor 16;

the chamber pressure sensor 15 is connected with the rail control engine 13;

the attitude control engine 14 is connected with two low pressure sensors 16 in parallel, and the attitude control engine 13 is positioned between the two low pressure sensors 16.

The propulsion system is a constant pressure extrusion type dual-component unified system, the pressurized gas is helium, and the propellant is dinitrogen tetroxide and methyl hydrazine.

The pressurized gas is stored in the gas cylinder 1. The gas path high-pressure self-locking valve 4 realizes reliable isolation of the high-pressure gas cylinder from a downstream low-pressure storage tank and the like before the system works. The gas path high-pressure self-locking valve 4 is arranged at the upstream of the pressure reducing valve 5 and is used for realizing the management of high-pressure gas. The pressure reducing valve 5 is a key component of the propulsion system, and functions to reduce the high-pressure gas throttle to the working pressure used by the tank through the pressure reducing valve and to keep the output pressure stable.

The one-way valve 6 is arranged on the pressurizing pipeline of the storage tank for the oxidant and the fuel respectively at the downstream of the pressure reducing valve, and can ensure the one-way flow of the pressurizing gas and prevent downstream gas and liquid from entering the upstream of the one-way valve. Each one-way valve is connected with a gas path isolation self-locking valve 7 in series, and the gas path isolation self-locking valve can be closed, so that the reliability of gas path isolation of the oxygen storage tank is further enhanced.

The storage tank 9 adopts a rubber diaphragm storage tank, the rubber diaphragm inside the storage tank realizes reliable physical isolation of pressurized gas and propellant, and the air passage inlet of the storage tank is directly connected with the outlet of the air passage isolation self-locking valve. In order to meet the requirement of mass center balance of the verifier, 4 storage tanks are arranged in total.

The propulsion system is provided with a track control engine 13 and a gesture control engine 14. The upstream oxygen path and the fuel path of the track control engine and the attitude control engine module are respectively provided with a liquid path isolation self-locking valve 11 for propellant management; when the system is not in operation or the downstream leakage is found, the liquid path isolation self-locking valve can be closed to cut off the supply of the propellant.

Each of the track control engine and the attitude control engine is provided with a chamber pressure sensor 15 for judging the working state of the engine and analyzing the performance thereof.

The charging valve 3 is used for charging the gas cylinder in the system. The high pressure sensor 2 is used to monitor cylinder pressure. The gas circuit adding and discharging valve 8 is used for discharging gas from the storage tank. The liquid line fill valve 10 is used to fill the tank with propellant. The line charge valve 12 is used to evacuate the inlet line prior to first ignition. Each low pressure sensor 16 is used to monitor the propellant supply line pressure.

2. Mode of operation

1) The propulsion system is filled and inflated for the first time;

The first filling adopts a scheme of vacuumizing and filling. The self-locking valves 7 and 11 are set to be in a closed state, the storage tank 9 is vacuumized through the storage tank gas channel charging and discharging valve 8 and the liquid channel charging and discharging valve 10, and the ground filling equipment extrudes the propellant into the liquid cavity of the storage tank. The storage tank rubber diaphragm can isolate the air cavity and the liquid cavity of the storage tank. After filling, the gas cylinder is inflated to a specified pressure. The pipeline of the engine is vacuumized through the pipeline adding and discharging valve 12, so that the risk of air clamping operation of the engine is reduced.

2) Filling a pipeline and pressurizing a storage tank;

before working, the detector is powered up. The engine pipeline is filled with propellant by opening the liquid path isolation self-locking valve 11. And opening the high-pressure self-locking valve 4, and opening the oxygen path and the fuel path isolating self-locking valve to pressurize the storage tank.

3) The engine works;

And according to the control time sequence, the track control engine and the gesture control engine are ignited. The system works in a constant pressure mode, and 4 propellant storage tanks are synchronously output so as to ensure constant thrust of the attitude control and rail control engine and balanced consumption of the storage tanks.

4) Decompression of the pipeline;

After each working condition is finished, a high-pressure self-locking valve, a gas path isolation self-locking valve and a liquid path isolation self-locking valve are arranged to be closed. The attitude control engine is ignited for 5s and is ignited for 1-2 times, and the engine pipeline is decompressed to a safe range through the engine operation.

5) Propellant replenishing and gas cylinder replenishing;

According to the test requirement, the system works for a plurality of times, and propellant supplement is needed. Before supplementing, the gas circuit of the storage tank is opened to add a discharge valve, and the storage tank is depressurized to normal pressure. The liquid line filling and discharging valve of the storage tank is connected with filling equipment, and the filling pipeline is filled after vacuuming and then filling. According to the test requirement, the gas cylinder is supplemented with gas through the charging valve.

3. Rubber diaphragm as propellant management device to reduce adverse effects of lunar surface inclination and detector shake

The propulsion system adopts a rubber diaphragm storage tank as a propellant management device, and the structure of the propulsion system is shown in figure 2. The working principle is that the propelling discharge is realized through orderly overturning of the rubber diaphragm, and the propellant without air inclusion is provided for the downstream engine. In addition, during take-off, the detector pose changes dramatically. If the propellant in the tank is sloshing, disturbing moments are given to the detector. The rubber diaphragm storage box used in the invention can tightly adhere to the liquid level of the propellant, so that the propellant is prevented from shaking, and the interference moment is reduced.

4. Engine performance assessment

During the test, a single engine contained steady state and multiple pulsed modes of operation. Since a plurality of engines are combined differently, the working states of the engines are complex, and the evaluation of the engine performance under each state is an important purpose of the test. A chamber pressure sensor 15 is installed in each engine to measure the combustion chamber pressure during operation, and the engine thrust can be obtained through the relationship between the chamber pressure and the thrust, thereby evaluating the engine performance.

5. Pressure relief of engine to avoid overpressure of pipeline

After the engine is ignited, its temperature increases, and the heat in turn causes the temperature of the propellant in the engine's circuit to rise. The temperature rise causes the density of the propellant to be reduced and the volume to be increased, and as the closed pipeline is formed between the liquid path isolation self-locking valve and each engine valve, the pressure of the liquid path isolation self-locking valve can be rapidly increased and exceeds the rated use pressure of the valve and the pipeline, thereby bringing potential safety hazard to products.

The propulsion subsystem adopts the pressure relief of the engine to avoid the overpressure of the pipeline. The specific strategy is that the liquid path isolation self-locking valve is closed, the downward attitude control engine is adopted to work for 5 seconds, the propellant in the pipeline is combusted and discharged a little, a certain cavity exists in the pipeline, and after the temperature of the propellant is increased, the volume increment is smaller than the cavity volume, so that the overpressure of the pipeline can not occur.

6. Accurate filling again

Before refilling, the gas channel adding and discharging valve of the storage tank is opened, and the storage tank is depressurized to normal pressure. The liquid line filling and discharging valve of the storage tank is connected with filling equipment, and the filling pipeline is filled after vacuumizing, so that propellant is ensured not to be clamped, and then filling is carried out. The filling pressure is larger than the saturated vapor pressure of the propellant, the flow resistance of the pipeline and the pressure difference of the parking height, the filling valve is opened to fill the storage tank, and when the electronic scale is unchanged, the storage tank is considered to be filled. The gas circuit charging and discharging valve at the upstream of the storage tank is connected with a pressurizing pipeline, pressurizes and discharges propellant back into the storage tank until the required value is filled, and closes the charging and discharging valve. And then removing the filling pipeline, deflating the gas circuit filling and discharging valve to zero gauge pressure, and closing the gas circuit filling and discharging valve. The storage tank is filled and then discharged, so that unbalanced consumption of the storage tank and weight deviation caused by mixing ratio deviation of the engine can be corrected, accurate propellant quantity in the storage tank is ensured, stable mass center of the detector is facilitated, and balancing is facilitated.

7. Test heat protection

In the test process, plume and high temperature are generated during the ignition operation of the engine, and adverse effects are generated on equipment on the device, so that the propulsion product is required to be subjected to heat-proof coating. The method mainly comprises the following steps:

Gas cylinder: the gas cylinder is integrally coated with a single-sided aluminized polyimide film with the thickness of 18-25 mu m, and the aluminum surface faces outwards; and the GB/T16400-2003 aluminum silicate fiber felt with the thickness of 5mm is coated at the position of the engine nozzle accessory, and the outermost layer is coated with flame-proof fine plain cloth and fixed by stainless steel wires.

A storage tank: the lower surface of the storage tank is coated with GB/T16400-2003 aluminum silicate fiber felt with the thickness of 5mm, the outer layer is coated with flame-retardant fine flat cloth, the aluminum silicate fiber felt is fixed by stainless steel wires, and an aluminum plating film is adhered to the outer side of the aluminum silicate fiber felt.

Cabin gap: and filling with a GB/T16400-2003 aluminum silicate fiber felt with the thickness of 5mm, and fixing with a glued aluminized film and a stainless steel wire.

And (3) a pipeline: wrapped with asbestos tape and secured with stainless steel wire.

8. High safety propulsion system

The propulsion system not only meets the use function of the system, but also performs necessary redundancy backup, and has the characteristics of high reliability:

1) In order to safely and reliably physically isolate oxygen from propellant vapor, 1 gas path isolating self-locking valve is arranged at the downstream of the oxygen and fuel one-way valve respectively, and the isolating self-locking valve is closed during the non-working period of the system;

2) The downstream of the storage tank is provided with a liquid path self-locking valve which is used for ensuring the safety isolation between the storage tank and the downstream after filling and before ignition during the ground storage period;

3) The filling valve and the charging valve are provided with more than two sealing measures;

4) The nonmetallic bag type storage tank is adopted, so that the safety of multiple filling is ensured, and the phenomenon of gas clamping output can not occur under various working conditions in the test process;

5) Vacuumizing the liquid path before the first ignition test to avoid the air clamping operation of the engine;

6) Before pressurizing, the system seals the liquid paths of the oxygen and fuel storage tanks through two measures of a liquid path self-locking valve and an engine electromagnetic valve; after the system is pressurized, two measures of a liquid path self-locking valve and an electromagnetic valve are still provided between the liquid paths of the oxygen and fuel storage tank to seal, so that the leakage of the propellant can be effectively prevented;

7) After ignition is finished, the gas path self-locking valve and the liquid path self-locking valve are closed, so that the gas path and the liquid path of the storage tank are reliably isolated.

In the description of the present application, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application.

Those skilled in the art will appreciate that the systems, apparatus, and their respective modules provided herein may be implemented entirely by logic programming of method steps such that the systems, apparatus, and their respective modules are implemented as logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers, etc., in addition to the systems, apparatus, and their respective modules being implemented as pure computer readable program code. Therefore, the system, the apparatus, and the respective modules thereof provided by the present invention may be regarded as one hardware component, and the modules included therein for implementing various programs may also be regarded as structures within the hardware component; modules for implementing various functions may also be regarded as being either software programs for implementing the methods or structures within hardware components.

The foregoing describes specific embodiments of the present application. It is to be understood that the application is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the application. The embodiments of the application and the features of the embodiments may be combined with each other arbitrarily without conflict.

Claims (10)

1. A lunar leap verification aircraft propulsion system comprising: the device comprises a gas cylinder (1), a high-pressure sensor (2), an inflation valve (3), a gas circuit high-pressure self-locking valve (4), a pressure reducing valve (5), a one-way valve (6), a gas circuit isolation self-locking valve (7), a gas circuit adding and discharging valve (8), a storage tank (9), a liquid circuit adding and discharging valve (10), a liquid circuit isolation self-locking valve (11), a pipeline adding and discharging valve (12), a rail control engine (13), a gesture control engine (14), a chamber pressure sensor (15) and a low-pressure sensor (16);

The gas cylinder (1), the high-pressure sensor (2), the inflation valve (3) and the gas path high-pressure self-locking valve (4) are in star connection;

one end of the pressure reducing valve (5) is connected with the air path high-pressure self-locking valve (4), and the other end of the pressure reducing valve (5) is sequentially connected with the one-way valve (6) and the air path isolation self-locking valve (7);

the gas path adding and discharging valve (8), the storage tank (9) and the gas path isolation self-locking valve (7) are connected in a triangular mode;

The storage tank (9), the liquid path adding and discharging valve (10) and the liquid path isolation self-locking valve (11) are connected in a triangular mode;

the liquid path isolation self-locking valve (11), the pipeline adding and discharging valve (12) and the low pressure sensor (16) are connected in a triangular mode;

The rail control engine (13) is connected with a low pressure sensor (16);

The room pressure sensor (15) is connected with the rail control engine (13);

the attitude control engine (14) is connected with the two low pressure sensors (16) in parallel, and the rail control engine (13) is positioned between the two low pressure sensors (16).

2. Lunar leap verification aircraft propulsion system according to claim 1, characterized in that the tank (9) adopts a rubber membrane as a propellant management means, the propulsive discharge is achieved by orderly turning of the rubber membrane, and a propellant without air entrapment is provided to the downstream rail-controlled engine (13).

3. Lunar leap verification aircraft propulsion system according to claim 1, characterized in that the tank (9) is a nonmetallic bladder tank.

4. The lunar leay verifying aircraft propulsion system of claim 1, wherein providing redundant backup measures comprises:

the oxidant and the gas circuit of the fuel storage tank are isolated through the serial arrangement of 2 groups of one-way valves (6) and gas circuit isolation self-locking valves (7); connecting a liquid path isolation self-locking valve (11) with an engine electromagnetic valve to manage liquid propellant;

before the first ignition test, vacuumizing the liquid path through a pipeline adding and discharging valve (12); after ignition is finished, the gas path isolation self-locking valve (7) and the liquid path isolation self-locking valve (11) are closed.

5. Lunar leap verification aircraft propulsion system according to claim 1, characterized in that the pressure reducing valve (5) reduces the high pressure gas throttle to the working pressure used by the tank and keeps its output pressure stable.

6. The lunar leay verifying aircraft propulsion system according to claim 1, characterized in that the number of tanks (9) is 4, 2 of which are filled with oxidizing agent, 2 of which are filled with fuel, the propellants being dinitrogen tetroxide, methyl hydrazine; the number of the gas cylinders (1) is 1, and the gas cylinders are filled with pressurized helium.

7. The lunar leay verification aircraft propulsion system according to claim 1, characterized in that before operation, the detector is powered up, and the liquid path isolation self-locking valve (11) is opened to charge the engine pipeline with propellant; opening the gas path high-pressure self-locking valve (4), and opening the gas path isolation self-locking valve (7) of the oxygen path and the fuel path to pressurize the storage tank (9).

8. The lunar leay verification aircraft propulsion system according to claim 1, wherein the system operates in a constant pressure mode with the ignition of the track engine (13) and the attitude engine (14) according to the control timing, and the 4 propellant tanks are synchronously output.

9. The lunar leay verification aircraft propulsion system according to claim 1 is characterized in that after each working condition is finished, an air passage high-pressure self-locking valve (4), a pressure reducing valve (5), an air passage isolation self-locking valve (7) and a liquid passage isolation self-locking valve (11) are arranged to be closed, an attitude control engine (14) is ignited for 5s, the ignition is performed for 1-2 times, and an engine pipeline is decompressed to a preset safety range through the engine operation.

10. The lunar surface leay verification aircraft propulsion system according to claim 1 is characterized in that before propellant is replenished, a gas circuit charging and discharging valve (8) of a storage tank (9) is opened, the storage tank (9) is depressurized to normal pressure, the storage tank (9) is connected with a filling device through a liquid circuit charging and discharging valve (10), and filling is carried out after a filling pipeline is vacuumized, and then filling is carried out; the storage tank adopts a mode of filling and then discharging back to correct unbalanced consumption of the storage tank and weight deviation caused by mixing ratio deviation of the engine, so that the accurate propellant quantity in the storage tank is ensured.