Liquid power system for assisting in adjusting pitch attitude of aircraft

Abstract

The invention provides a liquid power system for assisting in adjusting the pitch attitude of an aircraft, a gas cylinder is connected to an electric explosion valve through a gas pipeline, the other end of the electric explosion valve is connected with a pressure reduction module, the gas pipeline behind the pressure reduction module is divided into three branches which are connected in parallel, and one branch is divided into multiple branches which are connected to electromagnetic valves of engines; the other two branches are respectively connected with a storage tank, a liquid propellant is filled in the storage tank, an outlet of the storage tank is divided into a plurality of branches after being connected with a rupture diaphragm through a liquid pipeline, each branch is respectively and correspondingly connected with an engine, and the whole system is an integrated modular structure and is manufactured into an installation module unit in a liquid propellant pre-packaging mode. The device is compact in structure, small in size, free of high-pressure gas and propellant filling work on site, safe, reliable and capable of being repeatedly used for multiple times of aircraft precise attitude auxiliary adjustment. And the device is high in applicability and is used for aircraft products with different requirements and different models.

Description

Technical Field

[0001] The invention belongs to the technical field of aerospace vehicles, and in particular relates to a liquid power system for assisting in adjusting the pitch attitude of an aircraft. Background Art

[0002] At present, the pitch attitude adjustment of aerospace vehicles during flight mainly depends on the adjustment of the wing rudders of the aircraft. As the professional capabilities of current aviation aircraft are continuously improved, the maneuverability of aircraft is getting stronger and stronger, resulting in the attitude adjustment capability of the wing rudders alone being unable to meet the needs of the aircraft during flight.

[0003] In the prior art, the pitch attitude of aircraft is mostly assisted by solid gunpowder. The force generated depends on the amount of gunpowder used. The force provided when the aircraft adjusts its attitude is relatively fixed, which cannot satisfy the requirement of making multiple and precise attitude adjustments of the aircraft. Therefore, a reusable device for assisting in precise attitude control of the aircraft is needed. Summary of the invention

[0004] The technical problem solved by the present invention is to provide a liquid power system for assisting in adjusting the pitch attitude of an aircraft, which is used for adjusting the pitch angle of the aircraft head during takeoff and landing, thereby solving the problem that the aircraft attitude adjustment is not accurate enough and cannot be repeatedly adjusted during flight.

[0005] The technical solution adopted by the present invention is: a liquid power system for assisting in adjusting the pitch attitude of an aircraft, comprising a gas cylinder, a tank, an inflation valve, an electric explosion valve, a decompression module, a discharge valve, a rupture diaphragm, and an engine group, wherein the engine group comprises a plurality of engines with different thrusts, the tank and the gas cylinder are fixedly mounted on the system module through a mounting plate, the gas cylinder is connected to the electric explosion valve through a gas pipeline, the other end of the electric explosion valve is connected to the decompression module, the gas pipeline after the decompression module is divided into three parallel branches, one branch is divided into multiple branches connected to the solenoid valves of each engine to provide the solenoid valves with opening driving gas, and the other two branches are respectively connected to tanks, and the tanks are filled with liquid The propellant tank outlet is connected to the ruptured diaphragm through a liquid pipeline and is divided into multiple branches. Each branch is connected to an engine respectively. The engine includes a solenoid valve and a thrust chamber. The opening and closing of the engine are controlled by the solenoid valve. The liquid propellant reacts in the thrust chamber to generate high-temperature and high-pressure combustion gas, thereby generating thrust. The gas pipeline and the liquid pipeline are integrated with the supporting structure of the system and fixed on the mounting plate. The overall system is an integrated modular structure made into an installation module unit by pre-packaging the liquid propellant. The installation module unit is provided with a mounting hole for connecting with the aircraft.

[0006] Preferably, a charging valve is connected to the gas pipeline between the gas cylinder and the electric explosion valve.

[0007] Preferably, a filling and discharging valve is connected to the liquid pipeline between the tank and the rupture membrane for filling and discharging the propellant in the tank.

[0008] Preferably, the decompression module adopts a module structure that integrates decompression function and safety pressure relief function.

[0009] Preferably, the tank adopts a metal diaphragm structure, and the metal diaphragm divides the tank into an air cavity and a liquid cavity, thereby realizing physical isolation of the pressurized gas and the propellant. After the high-pressure gas source is injected into the air cavity of the tank, the diaphragm is overturned and deformed toward the liquid cavity by the action of the high-pressure gas, thereby squeezing out the propellant stored in the liquid cavity of the tank. The two tanks on the two branches are respectively filled with propellant A and propellant B, which are spontaneously ignited after being mixed.

[0010] Preferably, the engine group includes a low-thrust engine, a medium-thrust engine and a high-thrust engine, and the solenoid valve of each engine receives an electrical signal to perform switch control of the corresponding engine, and the control response time is in the order of milliseconds.

[0011] Preferably, the gas cylinder adopts an aluminum alloy inner liner fully wound composite material structure, which is filled with nitrogen or helium.

[0012] Preferably, the electric explosion valve adopts a cutter-type structure, on which a dull igniter is installed.

[0013] The beneficial effects of the present invention are as follows: the present invention has a compact structure, a small volume, a modular pre-packaging design, is easy to transport, does not require high-pressure gas and propellant filling on site, is safe and reliable, is easy to install and disassemble, has a small size envelope, and can be reused for multiple precise attitude auxiliary adjustments of aircraft. It has strong applicability and can be used for aircraft products of different needs and models by using engines with different thrusts. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 The schematic diagram of the structure of a liquid power system for assisting in adjusting the pitch attitude of an aircraft.

[0015] Figure numerals: 1-gas cylinder, 2-charging valve, 3-electric explosion valve, 4-pressure relief module, 5-tank, 6-filling and discharging valve, 7-rupture diaphragm, 8-engine unit, 9-solenoid valve, 10-thrust chamber. DETAILED DESCRIPTION

[0016] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0017] The liquid power system adopts a constant pressure extrusion bipropellant propulsion system, and selects MON-3 / MMH as the propellant. The constant pressure extrusion system has the advantages of high stability and stable thrust, which can ensure the stable and reliable thrust output of the system throughout the working process. As a bipropellant, MON-3 / MMH can self-ignite, with a simple structure and fast response speed. By controlling the start-up time of each engine, one or more engines can also be controlled to start working at the same time, so that the thrust changes, thereby adjusting the flight pitch angle of the aircraft. The pitch angle to be adjusted can be judged according to the real-time (instantaneous) pitch angle of the aircraft, so as to start different thrust engines at relative times, so that the aircraft can reach the desired pitch attitude at this stage.

[0018] This system can use 1, 2, 3 or more engines, and use engines with different thrusts according to needs, so that different thrust working conditions can be combined. If the aircraft needs a large-angle pitch adjustment, a large-thrust engine or multiple engines will be started for a longer time for adjustment. If a small angle is required, the small-thrust engine will be turned on for a short time.

[0019] like Figure 1 As shown, the system mainly comprises a gas cylinder 1, a storage tank 5, a charging valve 2, an electric explosion valve 3, a pressure reducing module 4, a charging and discharging valve 6, a rupture diaphragm 7, an engine unit 8, and system-related parts. The storage tank 5 and the gas cylinder 1 are fixedly installed on the system module through the mounting plate. The gas cylinder 1 is connected to the electric explosion valve through a gas pipeline. The gas pipeline between the gas cylinder 1 and the electric explosion valve 3 is connected with an inflation valve 2. The other end of the electric explosion valve 3 is connected to the pressure reducing module 4. The gas pipeline after the pressure reducing module 4 is divided into three parallel branches. One branch is divided into multiple branches connected to the solenoid valve 9 of each engine to provide the solenoid valve 9 with opening driving gas. The other two branches are respectively connected with the storage tank 5. After the outlet of the storage tank 5 is connected to the rupture diaphragm 7 through the liquid pipeline, it is divided into multiple branches, and each branch is respectively connected to an engine. The engine includes a solenoid valve 9 and a thrust chamber 10. The opening and closing of the engine are controlled by the solenoid valve 9. The liquid propellant reacts in the thrust chamber 10 to generate high-temperature combustion gas, thereby generating thrust. The rupture diaphragm 7 is a metal disc with a cutting edge, which is opened once and is opened by the pressurized liquid in the system directly acting on the cutting edge to impact and open. A filling and discharging valve 6 is connected to the liquid pipeline between the tank 5 and the ruptured membrane 7 for filling and discharging the propellant in the tank 5. The gas pipeline and the liquid pipeline are integrated with the supporting structure of the system and fixed on the mounting plate. The overall system is an integrated modular structure made into an installation module unit by pre-packaging the liquid propellant. The installation module unit is provided with a mounting hole for connection with the aircraft.

[0020] The gas cylinder 1 in the system adopts an aluminum alloy liner fully wrapped composite material structure, which is used to store high-pressure gas medium, and the gas can be nitrogen or helium; the charging valve 2 is used to inflate the high-pressure gas cylinder, so that the gas cylinder 1 has the function of repeated filling and deflation; the electric explosion valve 3 adopts a cutter-type structure, on which a dull igniter is installed. When the electric explosion valve 3 is not working, the high-pressure gas can be reliably stored in the gas cylinder 1. When the electric explosion valve 3 is working, the igniter receives an electrical signal to detonate and generate high-pressure gas to act on the cutter, pushing the cutter to move and cut off the nozzle, thereby realizing the system gas The circuit is opened to release the high-pressure gas in the gas cylinder 1 to the downstream; the decompression module 4 adopts a module structure that combines decompression function and safety pressure relief function. When the high-pressure gas passes through the decompression module 4, the output is a stable working pressure through the internal action. Under the condition that the pressure in the system is abnormally high, the safety valve in the decompression module 4 opens to release the pressure and release the gas, thereby ensuring the safety of the system; the storage tank 5 is used to store the propellant required for the system operation. The storage tank 5 adopts a metal diaphragm structure. The metal diaphragm divides the storage tank into an air cavity and a liquid cavity. The pressurized gas is physically isolated from the propellant. After the high-pressure gas source is injected into the gas cavity of the tank, the diaphragm is overturned and deformed toward the liquid cavity by the high-pressure gas, squeezing out the propellant stored in the liquid cavity of the tank 5; the filling and discharging valve 6 is used for filling and discharging the propellant in the tank; the rupture diaphragm 7 is used to isolate the propellant in the tank 5 from the downstream pipeline before working, so that the propellant is stably stored in the tank 5. When the system starts working, it ruptures and opens under the pressure in the system, so that the propellant A and the propellant B fill the downstream liquid pipeline to the front of the engine group 8; the engine group 8 is composed of a plurality of engines with different thrusts, and the engine is composed of a solenoid valve 9 and a thrust chamber 10. The solenoid valve 9 receives an electrical signal to control the switch of the engine. The control response time is in the order of milliseconds, and the response speed is fast. When the system is working, the solenoid valve 9 is opened, and the liquid propellant enters the thrust chamber 10, completing the atomization, mixing and combustion process, and generating high-temperature and high-pressure combustion gas. The combustion gas is discharged from the outlet of the nozzle at a very high speed, and the heat energy is converted into kinetic energy in the nozzle to generate the thrust required by the system.

[0021] The storage tank 5 and the gas cylinder 1 in the system are fixedly installed through the mounting plate, and the liquid pipelines are integrated with the supporting structure to reduce the system pipeline branches, integrate the individual machines into the system, reduce the system envelope size, and make it modular. The position of the system mounting holes can be adjusted according to the aircraft structure requirements, and it can be used for aircraft products with different requirements and models.

[0022] During the flight of the aircraft, when the pitch attitude needs to be assisted, the liquid power system starts to work, the electric explosion valve 3 receives the opening electric signal command, the electric explosion valve 3 opens, the high-pressure gas in the gas cylinder 1 is reduced to the working pressure by the decompression module 4, and the tank 5 is pressurized. The rupture diaphragm 7 downstream of the tank 5 opens under the pressure, and the propellant in the tank 5 is transported to the front of the engine solenoid valve 9. The engine solenoid valve 9 receives the control system command to open, and the propellant enters the thrust chamber 10 to burn and produce high-temperature and high-pressure combustion gas, which is ejected from the nozzle to generate thrust. The aircraft achieves pitch attitude adjustment under the thrust of the liquid power system. The solenoid valve 9 in the liquid power system can control the working sequence of the engine group 8 in the system as required according to the electric signal command, so that the aircraft can make multiple and accurate attitude adjustments.

[0023] Before the system is not working, the whole system realizes effective isolation of high-pressure gas and propellant through the electric explosion valve 3 and the tank diaphragm, and seals the propellant in the tank 5 by rupturing the diaphragm 7 to realize pre-packaging, which can realize rapid on-site assembly before the aircraft takes off.

[0024] The following is an exemplary description of the method of use and specific implementation steps of the present invention: This time, the pitch attitude of a certain aircraft was assisted in adjustment. Since the aircraft was flying at a high speed, during its landing process, the liquid power system was required to apply an upward force of 7000N for 800ms to the aircraft at a specified time point, and then apply a force of 10000N for 1500ms after an interval of 500ms, and then apply an upward force of 500N for 500ms after an interval of 800ms, so that the aircraft could land smoothly.

[0025] According to the requirements of a certain aircraft, the engine group 8 in the liquid power system adopts three engines, including a large thrust engine, a medium thrust engine and a small thrust engine, the gas cylinder 1 adopts a high-pressure composite material metal liner gas cylinder, and the tank 5 adopts two tank diaphragm tanks; Before the product is delivered for use, high-pressure nitrogen is charged into the gas cylinder 1 through the charging valve 2 of the liquid power system, and propellant A and propellant B are charged into the storage tank 5 through the charging and discharging valve 6. After the charging is completed, the charging valve 2 and the charging and discharging valve 6 are closed and the plug is installed. At this time, the high-pressure nitrogen is safely sealed in the gas cylinder 1 by the electric explosion valve 3, and the propellant is safely sealed in the storage tank 5 by the rupture diaphragm 7. After the work is completed, it is tested with professional instruments to ensure that there is no leakage of the medium in the system, and then it is packed in a special packaging box, thereby completing the pre-packaging of the liquid power system and can be transported.

[0026] Before the aircraft takes off, the liquid power system can be directly installed at the designated position of the aircraft. There is no need to fill high-pressure gas and propellant on site. It is safe and reliable, and the installation and operation are easy. The aircraft and the liquid power system can be installed and fixed with only 4 bolts.

[0027] During the landing process of the aircraft, the liquid power system starts working at a specified time point, the electric explosion valve 3 receives the opening electric signal instruction, the electric explosion valve 3 opens, the high-pressure gas in the gas cylinder 1 is reduced to the working pressure by the decompression module 4, and the tank 5 is pressurized. The rupture diaphragm 7 downstream of the tank 5 opens under the pressure, and the propellant in the tank 5 is transported to the front of the engine solenoid valve 9. The solenoid valve 9 of the high-thrust engine in the engine group 8 receives the control system instruction to open, so that the high-thrust engine produces a continuous 800ms, applying 7000N upward thrust to the aircraft, and then the engine group 8 stops working for 500ms under the electric signal instruction; a new electric signal instruction is sent, and the high-thrust engine and the medium-thrust engine in the engine group 8 work simultaneously for 1500ms, applying 10000N force to the aircraft, and the engine group 8 stops working again for 800ms; then according to the electric signal instruction, the low-thrust engine in the engine group 8 works for the last 500ms, applying 500N upward force to the aircraft, and then the system stops working. During the landing process, the liquid power system assists in adjusting the pitch attitude of the aircraft, allowing the aircraft to land smoothly. After the aircraft lands, the liquid power system can be directly disassembled in modular form, which is convenient and quick.

[0028] The above are specific embodiments of the present invention and the technical principles used. Any modifications and equivalent changes based on the technical solution of the present invention should be included in the protection scope of the present invention.

Claims

1. A liquid power system for assisting in adjusting the pitch attitude of an aircraft, characterized in that: The utility model comprises a gas cylinder, a tank, an inflation valve, an electric explosion valve, a decompression module, a discharge valve, a rupture diaphragm and an engine group, wherein the engine group comprises a plurality of engines with different thrusts, the tank and the gas cylinder are fixedly mounted on the system template through a mounting plate, the gas cylinder is connected to the electric explosion valve through a gas pipeline, the other end of the electric explosion valve is connected to the decompression module, the gas pipeline after the decompression module is divided into three parallel branches, one branch is divided into multiple branches connected to the solenoid valves of each engine, and the solenoid valves are provided with opening driving gas, the other two branches are respectively connected with tanks, the tanks are filled with liquid propellant, the tank outlet is connected to the rupture diaphragm through a liquid pipeline, and then is divided into a plurality of branches, each branch is respectively connected to an engine, the engine comprises a solenoid valve and a thrust chamber, the opening and closing of the engine are controlled by the solenoid valve, the gas pipeline and the liquid pipeline are integrated with the supporting structure of the system and fixed on the mounting plate, the overall system is an integrated modular structure, which is made into an installation module unit by pre-packaging of liquid propellant, and the installation module unit is provided with an installation hole for connecting with the aircraft.

2. A liquid power system for assisting in adjusting the pitch attitude of an aircraft according to claim 1, characterized in that: A charging valve is connected to the gas pipeline between the gas cylinder and the electric explosion valve.

3. A liquid power system for assisting in adjusting the pitch attitude of an aircraft according to claim 1, characterized in that: A filling and discharging valve is connected to the liquid pipeline between the storage tank and the ruptured membrane for filling and discharging the propellant in the storage tank.

4. A liquid power system for assisting in adjusting the pitch attitude of an aircraft according to claim 1, characterized in that: The decompression module adopts a module structure that integrates decompression function and safety pressure relief function.

5. The liquid power system for assisting in adjusting the pitch attitude of an aircraft according to claim 3, characterized in that: The tank adopts a metal diaphragm structure, and the metal diaphragm divides the tank into an air cavity and a liquid cavity, thereby realizing physical isolation of the pressurized gas and the propellant. After the high-pressure gas source is injected into the air cavity of the tank, the diaphragm is overturned and deformed toward the liquid cavity by the action of the high-pressure gas, thereby squeezing out the propellant stored in the liquid cavity of the tank. The two tanks on the two branches are respectively filled with propellant A and propellant B, which are spontaneously ignited after being mixed.

6. The liquid power system for assisting in adjusting the pitch attitude of an aircraft according to claim 1, characterized in that: The engine group includes a low-thrust engine, a medium-thrust engine and a high-thrust engine. The solenoid valves of the respective engines receive electrical signals to perform switch control of the corresponding engines, and the control response time is in the order of milliseconds.

7. The liquid power system for assisting in adjusting the pitch attitude of an aircraft according to claim 1, characterized in that: The gas cylinder adopts an aluminum alloy inner liner fully wound composite material structure and is filled with nitrogen or helium.

8. The liquid power system for assisting in adjusting the pitch attitude of an aircraft according to claim 1, characterized in that: The electric explosion valve adopts a cutter-type structure, on which a dull igniter is installed.

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