Interstage separation reverse thrust power device

Abstract

The utility model provides an interstage separation reverse thrust power device. The interstage separation reverse thrust power device comprises an electric explosion valve, a check valve, a heating chamber, an electromagnetic valve, a spray pipe, a cold guide pipe and a hot guide pipe. The heating chamber is communicated with the liquid oxygen storage tank through a cold conduit; the electric explosion valve and the check valve are arranged in a pipeline of the cold guide pipe; pressurized gas is stored in the liquid oxygen storage tank, the pressurized gas in the liquid oxygen storage tank enters the heating chamber through the cold guide pipe, and the temperature of the pressurized gas is increased by the heating chamber; the heating chamber is connected with the spray pipe through the heat pipe; and the electromagnetic valve is arranged in a pipeline of the heat pipe. The dead weight of the rocket is reduced, the influence of stage separation on the upper stage attitude is weakened, and the ablation problem faced by the upper stage is weakened.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of rocket interstage separation, in particular to an interstage separation anti-thrust power device. BACKGROUND

[0002] At present, solid rocket engines are used as anti-thrust engines for multi-stage rockets to increase the speed difference and displacement difference between the lower stage and the upper stage, and non-electric transmission explosion is used to start multiple anti-thrust engines to slow down the lower stage.

[0003] For rockets, in addition to the fuel filled inside, the shell, initiator and support of the anti-thrust engine are all waste weight. In addition, the synchronization of the ignition of multiple anti-thrust rockets has a great influence on the separation attitude, and the upper stage also faces the ablation problem of the exhaust plume of the anti-thrust rocket. When the anti-thrust rocket is working, the temperature of the exhaust plume is usually extremely high, up to several thousand degrees Celsius. When the exhaust plume directly impacts the surface of the upper stage, the huge heat will cause the surface temperature of the material to rise sharply, causing the material properties to decrease and even melt and evaporate, thereby causing ablation. The exhaust plume contains high-speed flowing gas and particles, which have a strong scouring and eroding effect on the surface of the upper stage. Long-term scouring by the exhaust plume will gradually wear and peel off the surface material, accelerating the ablation process.

[0004] The existing patent with publication number CN113405410B discloses an interstage separation device suitable for rocket cold separation, which comprises a separation side thrust device and a gas generator, both of which are installed on the rocket substage. The separation side thrust device comprises an axial impulse generating mechanism and a lateral impulse generating mechanism, and the gas generator and the lateral impulse generating mechanism are connected with the axial impulse generating mechanism. The axial impulse generating mechanism converts the internal energy of high-pressure gas into mechanical energy to separate the rocket parent stage from the rocket substage. It solves the technical problem of reducing the structural efficiency and reliability of the interstage separation system caused by separately setting the separation energy and the substage deviation energy. However, it does not solve the problems of dead weight, the influence of interstage separation on the attitude of the upper stage, and the ablation problem faced by the upper stage.

[0005] Therefore, the technical problem to be solved at present is how to provide an interstage separation anti-thrust power device to reduce the dead weight of the rocket, weaken the influence of interstage separation on the attitude of the upper stage, and weaken the ablation problem faced by the upper stage. CONTENT OF THE INVENTION

[0006] The purpose of the present application is to provide an interstage separation anti-thrust power device to reduce the dead weight of the rocket, weaken the influence of interstage separation on the attitude of the upper stage, and weaken the ablation problem faced by the upper stage.

[0007] To achieve the above object, the application provides an inter-stage separation reverse thrust power device, which comprises an electric explosion valve, a check valve, a heating chamber, a solenoid valve, a nozzle, a cold conduit and a hot conduit; the heating chamber is connected with a liquid oxygen storage tank through the cold conduit; the electric explosion valve and the check valve are arranged in the pipeline of the cold conduit; the liquid oxygen storage tank stores pressurized gas, the pressurized gas in the liquid oxygen storage tank enters the heating chamber through the cold conduit, and the heating chamber increases the temperature of the pressurized gas; the heating chamber is connected with the nozzle through the hot conduit; the solenoid valve is arranged in the pipeline of the hot conduit.

[0008] The inter-stage separation reverse thrust power device as described above, wherein the nozzle comprises a plurality of nozzles, and the input ends of the plurality of nozzles are connected with the output end of the heating chamber through the hot conduit and the solenoid valve.

[0009] The inter-stage separation reverse thrust power device as described above, wherein the solenoid valve comprises one solenoid valve, the input end of the solenoid valve is connected with the output end of the heating chamber, and the output end of the solenoid valve is connected with the input end of the nozzle.

[0010] The inter-stage separation reverse thrust power device as described above, wherein the output end of the solenoid valve comprises a plurality of ports, and each port is connected with one nozzle through the hot conduit.

[0011] The inter-stage separation reverse thrust power device as described above, wherein the solenoid valve comprises a plurality of solenoid valves, the input ends of the plurality of solenoid valves are connected with the output end of the heating chamber through the hot conduit, the output end of each solenoid valve is connected with at least one nozzle through the hot conduit, the high-temperature and high-pressure gas in the heating chamber is branched to the plurality of solenoid valves through the hot conduit, the high-temperature and high-pressure gas passing through the solenoid valve is input to the nozzle, and the high-temperature and high-pressure gas is sprayed from the nozzle to provide reverse thrust for the lower stage.

[0012] The inter-stage separation reverse thrust power device as described above, wherein the inter-stage separation reverse thrust power device uses the pressurized gas in the liquid oxygen storage tank as a medium.

[0013] The inter-stage separation reverse thrust power device as described above, wherein one end of the electric explosion valve is connected with the liquid oxygen storage tank through the cold conduit, and the other end of the electric explosion valve is connected with the check valve through the cold conduit.

[0014] The inter-stage separation reverse thrust power device as described above, wherein one end of the check valve is connected with the electric explosion valve through the cold conduit, and the other end of the check valve is connected with the heating chamber through the cold conduit.

[0015] The interstage separation anti-thrust power device as described above, wherein the heating chamber, the electromagnetic valve and the electric explosion valve are one, and the nozzle comprises a plurality; the plurality of nozzles share one heating chamber, one electromagnetic valve and one electric explosion valve, and the plurality of nozzles synchronously generate anti-thrust force for the lower stage.

[0016] The interstage separation anti-thrust power device as described above, wherein the gas ejection port of the nozzle is opened towards the upper stage, and the nozzle provides anti-thrust force for the lower stage after ejecting gas.

[0017] The application achieves the following beneficial effects:

[0018] (1) The application uses the tank pressurized gas as medium, and provides anti-thrust force for the lower stage by increasing the temperature and pressure of the tank pressurized gas and ejecting the tank pressurized gas through the nozzle, without other waste weight except necessary components.

[0019] (2) The plurality of nozzles of the application share the same heating chamber and electromagnetic valve and electric explosion valve, and there is no problem of asynchronous thrust.

[0020] (3) The gas ejection port of the nozzle of the application is opened towards the upper stage, the temperature of the gas ejected by the nozzle is low, and does not cause ablation to the upper stage; the generation and cancellation of the thrust of the nozzle are controllable. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description are only some embodiments described in the present application, and other drawings can also be obtained by those skilled in the art based on these drawings.

[0022] Figure 1 The structure of an interstage separation anti-thrust power device according to an embodiment of the present application.

[0023] The drawings are as follows: 1-liquid oxygen tank; 2-electric explosion valve; 3-check valve; 4-heating chamber; 5-electromagnetic valve; 6-nozzle; 7-cold conduit; 8-hot conduit. DETAILED DESCRIPTION

[0024] The technical solutions in the embodiments of the present application will be described clearly and completely below in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are only some embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0025] As Figure 1As shown in the figure, the application provides an inter-stage separation reverse thrust device, which comprises an electric explosion valve 2, a check valve 3, a heating chamber 4, a solenoid valve 5, a nozzle 6, a cold conduit 7 and a hot conduit 8; the heating chamber 4 is communicated with a liquid oxygen tank 1 through the cold conduit 7; the electric explosion valve 2 and the check valve 3 are arranged in the pipeline of the cold conduit 7; the liquid oxygen tank 1 stores pressurized gas; the pressurized gas in the liquid oxygen tank 1 enters the heating chamber 4 through the cold conduit 7, and the heating chamber 4 increases the temperature of the pressurized gas; the heating chamber 4 is connected with the nozzle 6 through the hot conduit 8; and the solenoid valve 5 is arranged in the pipeline of the hot conduit 8. The application uses the pressurized gas in the tank as a medium, increases the temperature and pressure of the medium by heating, and sprays the medium through the nozzle 6 to provide reverse thrust for the lower stage, and no other waste weight is needed except for necessary components, so that the dead weight of the rocket is reduced.

[0026] It can be understood that the reverse thrust device is composed of the electric explosion valve 2, the check valve 3, the cold conduit 7, the heating chamber 4, the hot conduit 8, the solenoid valve 5 and the nozzle 6. The reverse thrust device uses the pressurized gas in the liquid oxygen tank 1 as a medium, heats the gas by the heating chamber 4, increases the temperature and pressure of the gas, then divides the gas to each solenoid valve 5 through the hot conduit 8, and finally sprays the gas from the nozzle 6 to slow down the lower stage. The heating chamber 4 can use electric heating or oxygen self-generating pressurized gas heating. The heating chamber 4 uses a heater to increase the temperature and pressure of the medium.

[0027] It should be explained that the cold conduit 7 is mainly used for transmitting the pressurized gas in the liquid oxygen tank 1 to the heating chamber 4, and the hot conduit 8 is mainly used for conveying the pressurized gas heated by the heating chamber 7 to the nozzle 6.

[0028] As shown in the figure, Figure 1 The nozzle 6 comprises a plurality of nozzles 6, and the input ends of the plurality of nozzles 6 are communicated with the output end of the heating chamber 4 through the hot conduit 8 and the solenoid valve 5.

[0029] As shown in the figure, Figure 1 The solenoid valve 5 comprises one solenoid valve 5, the input end of the solenoid valve 5 is communicated with the output end of the heating chamber 4, and the output end of the solenoid valve 5 is communicated with the input end of the nozzle 6. The solenoid valve 5 is used for controlling the connection or disconnection of the heating chamber 4 to the nozzle 6 for conveying the gas.

[0030] As a specific embodiment of the application, the output end of the solenoid valve 5 comprises a plurality of ports, and each port is communicated with one nozzle 6 through the hot conduit 8. The plurality of output ends of one solenoid valve 5 are communicated with the plurality of nozzles 6, so that the high-temperature and high-pressure gas input to the plurality of nozzles 6 is controlled by one solenoid valve 5 at the same time, the plurality of nozzles 6 realize synchronous action, and synchronous reverse thrust is provided for the lower stage.

[0031] As other embodiments of the utility model, electromagnetic valve 5 includes a plurality, a plurality of electromagnetic valve 5 input end all through heat pipe 8 with heating chamber 4 output end communication, the output of each electromagnetic valve 5 through heat pipe 8 and at least one nozzle 6 communication, heating chamber 4 inside high temperature and high pressure gas is shunted to a plurality of electromagnetic valve 5 through heat pipe 8, after the high temperature and high pressure gas of electromagnetic valve 5 is input to nozzle 6, from nozzle 6, provide the counterthrust of the following stage.

[0032] As specific embodiments of the utility model, stage separation counterthrust device uses the pressurized gas in liquid oxygen tank 1 as medium.

[0033] As shown in Figure 1 , one end of electric explosion valve 2 is connected with liquid oxygen tank 1 through cold conduit 7, and the other end is connected with check valve 3 through cold conduit 7. Electric explosion valve 2 is a kind of valve that realizes rapid opening or closing by electric explosion driving device. Electric explosion valve 2 is used to accurately control the supply of pressurized gas in heating chamber 4, and adjust the supply flow of pressurized gas in heating chamber 4. Electric explosion valve 2 uses existing electric explosion valve, which can realize accurate control of the supply of pressurized gas in heating chamber 4.

[0034] As shown in Figure 1 , one end of check valve 3 is connected with electric explosion valve 2 through cold conduit 7, and the other end is connected with heating chamber 4 through cold conduit 7. Check valve 3, also known as check valve or non-return valve, is an automatic valve, which functions to prevent backflow of medium. In the pipeline system, check valve 3 can ensure that the medium flows in the specified direction only, preventing it from flowing in the opposite direction, to ensure the safe operation of the system. Check valve 3 can avoid flow fluctuation and pressure fluctuation caused by backflow of medium, making the system run more stably and reliably.

[0035] As shown in Figure 1 , heating chamber 4, electromagnetic valve 5 and electric explosion valve 2 are one, and nozzle 6 includes a plurality; a plurality of nozzles 6 share one heating chamber 4, one electromagnetic valve 5 and one electric explosion valve 2, and a plurality of nozzles 6 generate counterthrust to the lower stage synchronously.

[0036] It needs to be explained that the plurality of nozzles 6 synchronously generate counterthrust to the lower stage, which has the advantages of improving thrust uniformity and stability. The synchronous operation of a plurality of nozzles 6 can distribute the total thrust more evenly on the surface of the lower stage, avoid stress concentration caused by excessive local thrust, make the lower stage bear force more evenly, and reduce the risk of structural deformation and damage. The cooperative action of a plurality of nozzles 6 can effectively reduce the influence of single nozzle 6 working state fluctuation on the overall thrust, make the thrust output more stable, and help to improve the control accuracy of flight attitude and flight stability.

[0037] In addition, the plurality of nozzles 6 provide thrust with multi-directional control capability: by adjusting the thrust size and direction of different nozzles 6, multi-directional control of the lower stage can be achieved, such as attitude adjustment in pitch, yaw and roll during rocket launch, which can more flexibly cope with various flight requirements and improve the control accuracy of the flight trajectory. When the plurality of nozzles 6 work synchronously, the thrust of a single or multiple nozzles 6 can be fine-tuned to quickly correct small deviations of the lower stage and timely correct small changes in the flight attitude, ensuring the smooth progress of the flight mission. When part of the nozzles 6 fail, the normally working nozzles 6 can still provide sufficient thrust to maintain the control and propulsion of the lower stage, reduce the risk of the entire mission failing due to the failure of a single nozzle 6, and improve the reliability and success rate of the system. The plurality of nozzles 6 jointly bear the thermal load and mechanical wear caused by the thrust, and compared with a single large nozzle, the working conditions of each nozzle 6 are relatively more relaxed, which can reduce the thermal stress and wear degree of a single nozzle 6, prolong the service life of the nozzle 6, and thus improve the reliability and maintainability of the entire propulsion system.

[0038] It should be explained that the plurality of nozzles 6 in the present application work synchronously to more evenly disperse the total thrust, make the exhaust plume more evenly diffuse, and reduce the concentrated impact of the exhaust plume on the specific parts of the upper stage. At the same time, the combustion process of the retro-rocket is optimized, and compared with the higher exhaust plume temperature (thousands of degrees Celsius) of the existing nozzle, the exhaust plume temperature of the nozzle 6 of the present application is lower than the temperature (thousands of degrees Celsius) of the existing nozzle, thereby weakening the ablation problem of the nozzle 6 gas to the upper stage.

[0039] As a specific embodiment of the present application, the gas outlet of the nozzle 6 faces the upper stage, but the temperature of the gas sprayed out is relatively low, which can weaken the ablation problem of the upper stage. After the gas is sprayed out of the nozzle 6, the retro-thrust is provided for the lower stage.

[0040] As a specific embodiment of the present application, the inner diameters of the cold pipe 7 and the hot pipe 8 can be selected according to actual conditions, the power and volume of the heating chamber 4 can be selected according to actual conditions, and the number and direction of the nozzles 6 can be selected according to actual conditions. The inner diameters of the cold pipe 7 and the hot pipe 8, the power and volume of the heating chamber 4, and the number and direction of the nozzles 6 are not limited herein. The beneficial effects achieved by the present application are as follows:

[0041] (1) The present application uses the pressurized gas in the tank as a medium, which provides retro-thrust for the lower stage by increasing the temperature and pressure and spraying out through the nozzle, and has no other waste weight except necessary components.

[0042] (2) The plurality of nozzles in the present application share the same heating chamber and electromagnetic valve and electric explosion valve, and there is no problem of asynchronous thrust.

[0043] (3) The gas temperature of the nozzle is low, and the upper stage is not ablated; the generation and cancellation of the nozzle thrust are controllable.

[0044] In the description of the present application, the terms "first", "second" are only used for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined with "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "a plurality of" is two or more, unless otherwise specifically limited.

[0045] In the description of the present application, the word "for example" is used to mean "serving as an example, instance, or illustration". Any embodiment described as "for example" in this application is not necessarily to be construed as preferred or advantageous over other embodiments. The following description is presented to enable any person skilled in the art to make and use the present application. In the following description, details are set forth for the purpose of explanation. It will be appreciated that one of ordinary skill in the art can realize and implement the present application without using these specific details. In other instances, well-known structures and processes are not described in detail in order to avoid obscuring the description of the present application. Therefore, the present application is not intended to be limited to the embodiments shown, but is to be consistent with the most broad scope consistent with the principles and features presented herein.

[0046] The above only describes the embodiments of the present application and is not intended to limit the present application. For those skilled in the art, the present application can have various changes and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the scope of the claims of the present application.

Claims

1. An interstage separation reverse push power device characterized by, The device comprises an electric explosion valve, a check valve, a heating chamber, a solenoid valve, a nozzle, a cold conduit and a hot conduit; The heating chamber is connected with the liquid oxygen storage tank through the cold conduit; The electric explosion valve and the check valve are arranged in the pipeline of the cold conduit; The liquid oxygen storage tank stores pressurized gas, the pressurized gas in the liquid oxygen storage tank enters the heating chamber through the cold conduit, and the heating chamber increases the temperature of the pressurized gas; The heating chamber is connected with the nozzle through the hot conduit; The solenoid valve is arranged in the pipeline of the hot conduit.

2. The interstage separation counter-propulsion device of claim 1, wherein, The nozzle comprises a plurality of nozzles, and the input ends of the plurality of nozzles are connected with the output end of the heating chamber through the hot conduit and the solenoid valve.

3. The interstage separation counter-propulsion device of claim 2, wherein, The solenoid valve comprises one, The input end of the solenoid valve is connected with the output end of the heating chamber; The output end of the solenoid valve is connected with the input end of the nozzle.

4. The interstage separation counter-propulsion device of claim 2, wherein, The output end of the solenoid valve comprises a plurality of ports, Each port is connected with one nozzle through the hot conduit.

5. The interstage separation counter-propulsion device of claim 2, wherein, The solenoid valve comprises a plurality of solenoid valves, The input ends of the plurality of solenoid valves are connected with the output end of the heating chamber through the hot conduit, and the output end of each solenoid valve is connected with at least one nozzle through the hot conduit; The heating chamber divides the high-temperature and high-pressure gas in the heating chamber into a plurality of solenoid valves through the hot conduit, the high-temperature and high-pressure gas passing through the solenoid valve is input into the nozzle, and then is sprayed from the nozzle to provide the reverse thrust for the lower stage.

6. The interstage separation counter-propulsion device of claim 1, wherein, The stage separation reverse thrust device uses the pressurized gas in the liquid oxygen storage tank as a medium.

7. The interstage separation counter-propulsion device of claim 1, wherein, One end of the electric explosion valve is connected with the liquid oxygen storage tank through the cold conduit, and the other end is connected with the check valve through the cold conduit.

8. The interstage separation counter-propulsion device of claim 7, wherein, One end of the check valve is connected with the electric explosion valve through the cold conduit, and the other end is connected with the heating chamber through the cold conduit.

9. The interstage separation counter-propulsion device of claim 1, wherein, The heating chamber, the solenoid valve and the electric explosion valve are one, and the nozzle comprises a plurality of nozzles; The plurality of nozzles share one heating chamber, one solenoid valve and one electric explosion valve, and the plurality of nozzles synchronously generate the reverse thrust for the lower stage.

10. The interstage separation counter-propulsion device of claim 1, wherein, The gas spray outlet of the nozzle is opened towards the upper stage, and the nozzle sprays the gas to provide the reverse thrust for the lower stage.

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