Liquid oxygen methane auxiliary power system

Abstract

The utility model relates to a liquid oxygen methane auxiliary power system which comprises an oxygen storage box, a methane storage box and a thrust chamber, an oxygen communicating piece is arranged between the oxygen storage box and the thrust chamber, and the oxygen storage box and the thrust chamber are communicated with a combustion chamber of the thrust chamber through the oxygen communicating piece. A methane communicating piece is arranged between the methane storage box and the thrust chamber, and the methane storage box is communicated with the combustion chamber of the thrust chamber through the methane communicating piece; an oxygen return pipeline is arranged on the oxygen communicating piece, one end of the oxygen return pipeline is communicated with one end, close to the oxygen storage box, of the oxygen communicating piece, and the other end of the oxygen return pipeline is communicated with one end, close to the thrust chamber, of the oxygen communicating piece; a methane return pipeline is arranged on the methane communicating piece, one end of the methane return pipeline is communicated with one end, close to the methane storage tank, of the methane communicating piece, and the other end of the methane return pipeline is communicated with one end, close to the thrust chamber, of the methane communicating piece. The working stability and reliability of the auxiliary power system can be improved, waste of low-temperature propellants can be reduced, and the carrying capacity of the rocket can be improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to spaceflight engine technical field especially relates to a liquid oxygen methane auxiliary power system. BACKGROUND

[0002] The auxiliary power system of the domestic active carrier rocket usually adopts the technical scheme of single group element catalytic decomposition engine or four nitrogen dioxide / hydrazine double group element self-ignition engine, and the specific impulse performance of the scheme is low, the propellant contains toxic, the operation and maintenance cost are very expensive, and the scheme cannot be reused.

[0003] Therefore, using liquid oxygen methane as the propellant of the auxiliary power system of the carrier rocket gradually becomes the first choice in the future. The liquid oxygen methane belongs to low-temperature propellant, and the liquid oxygen methane has the advantages of less carbon deposition, long-term storage, low cost, no pollution and good repeatability. Therefore, the auxiliary power system of the carrier rocket using liquid oxygen methane helps to realize the unity and non-toxicity of the whole rocket propellant, and helps the rocket to be efficient and completely reusable. The liquid oxygen methane engine is used as the power system of the carrier rocket by SpaceX, blue source and several commercial rocket companies in China, and the technology of the liquid oxygen methane space propulsion system is gradually developed and matured.

[0004] Usually, the main power system of the carrier rocket continuously generates jet to drive the rocket to fly when working, and the working mode is fixed. Compared with the main power system of the carrier rocket, the auxiliary power system of the carrier rocket has various working modes, and the working condition is not fixed. In addition, the auxiliary power system of the carrier rocket has the problems of small second flow, random interval time and random pulse number. Therefore, the low-temperature propellant in the auxiliary power system of the carrier rocket is more likely to have temperature rise and low-temperature propellant gasification.

[0005] The gasified low-temperature propellant not only causes the flow, mixing ratio and density of the low-temperature propellant in the pipeline of the auxiliary power system to change sharply, thereby causing the instability of the whole system, but also is easy to cause the "gas jam" in the pipeline, thereby causing the pipeline of the auxiliary power system to be blocked.

[0006] When the gasified low-temperature propellant enters the thrust chamber for combustion, the reaction is more violent and unstable compared with the liquid low-temperature propellant entering the thrust chamber for combustion, and even directly causes the damage of the thrust chamber, which seriously affects the stability and reliability of the auxiliary power system when working.

[0007] Therefore, in the auxiliary power system, it is necessary to ensure the continuous flow of the cryogenic propellant in the liquid state into the thrust chamber, and also prevent the cryogenic propellant from being gasified in the process. At present, in order to ensure the continuous flow of the cryogenic propellant in the liquid state in the pipeline, the usual way is to open a discharge port in the pipeline of the auxiliary power system; when the auxiliary power system works, the discharge port will discharge a part of the cryogenic propellant in the pipeline of the auxiliary power system to the outside, so as to ensure the continuous flow of the cryogenic propellant in the pipeline and prevent it from being gasified. However, this way will cause serious waste of the cryogenic propellant.

[0008] At the same time, in order to ensure the continuous flow of the cryogenic propellant in the liquid state by discharging the cryogenic propellant, additional cryogenic propellant needs to be added in the carrier rocket, which increases the load of the rocket in flight and reduces the effective carrying capacity of the rocket.

[0009] Therefore, there is an urgent need for an auxiliary power system which can prevent the cryogenic propellant from being gasified, ensure the stability and reliability of the auxiliary power system, and also reduce the waste of the cryogenic propellant and improve the effective carrying capacity of the rocket. Content of the utility model

[0010] The utility model aims at providing a liquid oxygen and methane auxiliary power system to solve the problems in the prior art.

[0011] To achieve the above-mentioned purpose, the utility model provides the following scheme:

[0012] The utility model provides a liquid oxygen and methane auxiliary power system, which comprises an oxygen storage tank, a methane storage tank and a thrust chamber.

[0013] The oxygen storage tank and the thrust chamber are connected through an oxygen communication member, and the methane storage tank and the thrust chamber are connected through a methane communication member.

[0014] The oxygen communication member is provided with an oxygen backflow pipeline, one end of the oxygen backflow pipeline is communicated with one end of the oxygen communication member close to the oxygen storage tank, and the other end of the oxygen backflow pipeline is communicated with one end of the oxygen communication member close to the thrust chamber.

[0015] The methane communication member is provided with a methane backflow pipeline, one end of the methane backflow pipeline is communicated with one end of the methane communication member close to the methane storage tank, and the other end of the methane backflow pipeline is communicated with one end of the methane communication member close to the thrust chamber.

[0016] According to one embodiment of the utility model, the oxygen communication piece is oxygen branch pipeline, both ends of oxygen branch pipeline are communicated with oxygen storage tank, combustion chamber of the thrust chamber respectively, the methane communication piece is methane branch pipeline, both ends of methane branch pipeline are communicated with methane storage tank, combustion chamber of the thrust chamber respectively, oxygen backflow pipeline is communicated on oxygen branch pipeline, methane backflow pipeline is communicated on methane branch pipeline.

[0017] According to one embodiment of the utility model, the number of thrust chamber is several, oxygen branch pipeline is extended and communicated with combustion chamber of several thrust chamber in turn, methane branch pipeline is extended and communicated with combustion chamber of several thrust chamber in turn, the oxygen branch pipeline of extension setting and the methane branch pipeline of extension setting are independently arranged.

[0018] According to one embodiment of the utility model, oxygen branch pipeline is provided with oxygen power mechanism, oxygen power mechanism is located between the communication of oxygen storage tank and oxygen backflow pipeline, the communication between oxygen backflow pipeline and oxygen branch pipeline, oxygen power mechanism is used for pressurizing oxygen in oxygen branch pipeline,

[0019] Methane branch pipeline is provided with methane power mechanism, methane power mechanism is located between the communication of methane storage tank and methane backflow pipeline, the communication between methane backflow pipeline and methane branch pipeline, methane power mechanism is used for pressurizing methane in methane branch pipeline.

[0020] According to one embodiment of the utility model, oxygen power mechanism includes the oxygen pump of setting on oxygen branch pipeline, oxygen pump is located between the communication of oxygen storage tank and oxygen backflow pipeline, the communication between oxygen backflow pipeline and oxygen branch pipeline, oxygen pump motor is installed on oxygen pump, oxygen pump motor is used for providing power for oxygen pump, oxygen pump is used for pressurizing oxygen in oxygen branch pipeline,

[0021] Methane power mechanism includes the methane pump of setting on methane branch pipeline, methane pump is located between the communication of methane storage tank and methane backflow pipeline, the communication between methane backflow pipeline and methane branch pipeline, methane pump motor is installed on methane pump, methane pump motor is used for providing power for methane pump, methane pump is used for pressurizing methane in methane branch pipeline.

[0022] According to one embodiment of the utility model, oxygen branch pipeline, oxygen backflow pipeline, methane branch pipeline and methane backflow pipeline are all vacuum tubes.

[0023] According to one embodiment of the utility model, the outer wall of oxygen branch pipeline, oxygen return pipeline, methane branch pipeline and methane return pipeline is coated with a thermal insulation layer.

[0024] According to one embodiment of the utility model, the oxygen return pipeline and the methane return pipeline are provided with a cavitation tube and a return valve.

[0025] According to one embodiment of the utility model, the oxygen branch pipeline is provided with an oxygen electromagnetic valve, and the oxygen electromagnetic valve is located at the inlet of the thrust chamber combustion chamber; the methane branch pipeline is provided with a methane electromagnetic valve, and the methane electromagnetic valve is located at the inlet of the thrust chamber combustion chamber.

[0026] According to one embodiment of the utility model, the outlet of the oxygen electromagnetic valve and the methane electromagnetic valve is integrally arranged at the inlet of the thrust chamber combustion chamber, and the outlet of the oxygen electromagnetic valve and the methane electromagnetic valve is located on the same plane as the inlet of the thrust chamber combustion chamber.

[0027] The utility model has at least the following technical effects:

[0028] Firstly, the utility model sets the oxygen return pipeline and the methane return pipeline, which can make liquid oxygen and methane (i.e. low-temperature propellant) return in the oxygen return pipeline and the methane return pipeline respectively when the auxiliary power system works, effectively avoiding the occurrence of "air plug" condition, ensuring the continuous flow of liquid oxygen and methane in the auxiliary power system pipeline, avoiding the blockage of the pipeline, and ensuring the stability and reliability of the auxiliary power system.

[0029] Secondly, the utility model sets the oxygen return pipeline and the methane return pipeline, which can ensure that liquid oxygen and methane enter the thrust chamber in a liquid state for combustion, thereby ensuring the stability of the combustion of liquid oxygen and methane in the combustion chamber, and avoiding the damage of the thrust chamber due to violent reaction, further ensuring the stability and reliability of the auxiliary power system.

[0030] Finally, the utility model sets the oxygen return pipeline and the methane return pipeline, which do not need to discharge liquid oxygen and methane to ensure the flow of liquid oxygen and methane. Liquid oxygen and methane return in the oxygen return pipeline and the methane return pipeline respectively to ensure their flow, thus reducing the waste of liquid oxygen and methane and improving the effective carrying capacity of the rocket. BRIEF DESCRIPTION OF DRAWINGS

[0031] In order to more clearly illustrate the technical solutions of the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings without creative labor.

[0032] Figure 1 The present application is an exemplary overall structure schematic diagram.

[0033] Figure 2 The present application is a structure schematic diagram of the heat preservation layer.

[0034] 1, oxygen storage tank; 2, methane storage tank; 3, oxygen main pipeline; 4, methane main pipeline; 5, oxygen branch pipeline; 6, oxygen return pipeline; 7, methane branch pipeline; 8, methane return pipeline; 9, oxygen electromagnetic valve; 10, methane electromagnetic valve; 11, thrust chamber; 12, oxygen pump; 13, oxygen pump motor; 14, methane pump; 15, methane pump motor; 16, cavitation tube; 17, return valve; 18, polyethylene foam; 19, ultralow temperature glue. DETAILED DESCRIPTION

[0035] The features and exemplary embodiments of each aspect of the present application will be described in detail below. In order to make the purpose, technical solutions and advantages of the present application more clear and apparent, the present application will be further described in detail below with reference to the drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present application and to illustrate the principles of the present application, and are not configured to limit the present application. In addition, the components in the drawings are not necessarily drawn to scale. For example, the size of some components in the drawings can be enlarged for other components or regions to help understand the embodiments of the present application.

[0036] The orientation words appearing in the following description are the directions shown in the drawings, and are not limited to the specific structure of the embodiments of the present application. In the description of the present application, it should be noted that, unless otherwise specified, the terms "mounting", "connecting", "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be directly connected, or indirectly connected through an intermediate medium. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0037] Moreover, the terms "including", "comprising", "having" and the like are used synonymously to denote open ended inclusion, and do not exclude additional, unrecited elements or method steps. In the absence of further limitation, the term "including", "comprising", "having" and the like should be understood as meaning that the recited steps or components can be present, but not necessarily, and that additional steps or components can also be present.

[0038] Spatially relative terms such as "beneath", "below", "lower", "under", "above", "upper", "over", "on", and "side", are used to facilitate the description of the embodiments, and are not intended to constrict the scope of the application to the positions described. Such relative terms do not require a particular orientation of the device or material or method in use or end use, and the terms so used are intended to encompass different orientations of the device or material or method in use or end use. For example, "above" can encompass both orientations of the device or material or method in use or end use. The terms "first", "second", and the like, do not imply any particular order, but are used to name various elements. Similar terms are used to describe similar elements.

[0039] In the following description of the present application, the term "rocket", "launch vehicle", "spacecraft", "space launch vehicle", or "missile" can be used in some context only for the convenience of description, and the connotation is not limited to the specific word used. Generally, the launch vehicle of the present application includes space launch vehicles, rockets, missiles, and other weapons for carrying military payloads, as well as similar products capable of delivering payloads into the air. Those skilled in the art should not limit the launch vehicle to only one of the space launch vehicle, rocket, or missile based on the specific word used in the description context, thereby narrowing the scope of protection of the present application.

[0040] For those skilled in the art, the present application can be implemented without some of these specific details. The following description of the embodiments is only to provide a better understanding of the present application by showing examples of the present application.

[0041] The thrust chamber of the rocket (i.e. the thrust chamber 11 in the present application) can be roughly divided into a combustion chamber and a nozzle from top to bottom. The combustion chamber can burn propellants, and the nozzle can eject the gas generated by the combustion of the propellants, thereby propelling the rocket to launch and fly. The above are all prior art known to those skilled in the art, and will not be described in detail here.

[0042] The liquid oxygen and methane auxiliary power system can be applied to the first stage, the second stage or the upper stage of a carrier rocket.

[0043] The utility model provides a kind of liquid oxygen methane auxiliary power system, refer to Figure 1 Including oxygen storage tank 1, methane storage tank 2 and thrust chamber 11, wherein:

[0044] Oxygen storage tank 1 is communicated with oxygen main pipeline 3, methane storage tank 2 is communicated with methane main pipeline 4, the other end of oxygen main pipeline 3 and methane main pipeline 4 is communicated with the main engine of rocket, so as to realize the effect of sharing tank with the main engine of rocket, simplify the structure of rocket overall power system, improve the carrying efficiency of rocket;Wherein, the main engine of rocket is the prior art known in the art, not more described here.

[0045] Oxygen storage tank 1 and thrust chamber 11 are provided with oxygen communication piece and are communicated with the combustion chamber of thrust chamber 11 by oxygen communication piece.

[0046] In the embodiment, refer to Figure 1 One end of oxygen communication piece is communicated with oxygen main pipeline 3, and then communicated with oxygen storage tank 1;The other end of oxygen communication piece is communicated with the combustion chamber of thrust chamber 11.

[0047] Methane storage tank 2 and thrust chamber 11 are provided with methane communication piece and are communicated with the combustion chamber of thrust chamber 11 by methane communication piece.

[0048] In the embodiment, refer to Figure 1 One end of methane communication piece is communicated with methane main pipeline 4, and then communicated with methane storage tank 2;The other end of methane communication piece is communicated with the combustion chamber of thrust chamber 11.

[0049] Oxygen return pipeline 6 is arranged on oxygen communication piece, one end of oxygen return pipeline 6 is communicated with the end of oxygen communication piece close to oxygen storage tank 1 through oxygen main pipeline 3, the other end of oxygen return pipeline 6 is communicated with the end of oxygen communication piece close to thrust chamber 11.

[0050] In the embodiment, refer to Figure 1 One end of oxygen return pipeline 6 is communicated with oxygen main pipeline 3, and the connection can be located between the connection of oxygen communication piece and oxygen main pipeline 3 and the outlet of oxygen storage tank 1;The other end of oxygen return pipeline 6 is communicated with the end of oxygen communication piece close to thrust chamber 11.

[0051] Methane return pipeline 8 is arranged on methane communication piece, one end of methane return pipeline 8 is communicated with the end of methane communication piece close to methane storage tank 2 through methane main pipeline 4, the other end of methane return pipeline 8 is communicated with the end of methane communication piece close to thrust chamber 11.

[0052] In the embodiment, referring to Figure 1 , one end of the methane return pipeline 8 is communicated with the methane main pipeline 4, and the connection position can be located between the connection position of the methane communication member and the methane main pipeline 4 and the outlet position of the methane storage tank 2; the other end of the methane return pipeline 8 is communicated with one end of the methane communication member close to the thrust chamber 11.

[0053] According to one embodiment of the utility model, the oxygen communication member can be an oxygen branch pipeline 5, and the methane communication member can be a methane branch pipeline 7.

[0054] In the embodiment, referring to Figure 1 , two ends of the oxygen branch pipeline 5 are communicated with the oxygen storage tank 1 and the combustion chamber of the thrust chamber 11 respectively, wherein one end of the oxygen branch pipeline 5 is communicated with the oxygen main pipeline 3, thereby being communicated with the oxygen storage tank 1. Two ends of the methane branch pipeline 7 are communicated with the methane storage tank 2 and the combustion chamber of the thrust chamber 11 respectively, wherein one end of the methane branch pipeline 7 is communicated with the methane main pipeline 4, thereby being communicated with the methane storage tank 2.

[0055] In the embodiment, referring to Figure 1 , one end of the oxygen return pipeline 6 is arranged on the oxygen branch pipeline 5, and the other end of the oxygen return pipeline 6 is communicated with the oxygen branch pipeline 5 through the oxygen main pipeline 3. That is, the other end of the oxygen return pipeline 6 is communicated with the oxygen main pipeline 3, and the connection position is located on the oxygen main pipeline 3 between the outlet position of the oxygen storage tank 1 and the oxygen branch pipeline 5.

[0056] In the embodiment, referring to Figure 1 , one end of the methane return pipeline 8 is arranged on the methane branch pipeline 7, and the other end of the methane return pipeline 8 is communicated with the methane branch pipeline 7 through the methane main pipeline 4. That is, the other end of the methane return pipeline 8 is communicated with the methane main pipeline 4, and the connection position is located on the methane main pipeline 4 between the outlet position of the methane storage tank 2 and the methane branch pipeline 7.

[0057] The liquid oxygen in the oxygen storage tank 1 will flow into the oxygen main pipeline 3 when the liquid oxygen methane auxiliary power system works, the liquid oxygen flowing into the oxygen main pipeline 3 will flow into the oxygen branch pipeline 5, and then flow into the combustion chamber of the thrust chamber 11. The methane in the methane storage tank 2 will flow into the methane main pipeline 4, the methane flowing into the methane main pipeline 4 will flow into the methane branch pipeline 7, and then flow into the combustion chamber of the thrust chamber 11. The liquid oxygen and the methane flowing into the combustion chamber of the thrust chamber 11 will simultaneously form the propellant of the rocket, and after the oxidation-reduction reaction (i.e. combustion) in the combustion chamber of the thrust chamber 11, the gas formed will be sprayed from the nozzle of the thrust chamber 11, thereby providing the rocket with reverse auxiliary power by using Newton's third law (i.e. action and reaction).

[0058] Firstly, in the process that the auxiliary power system provided by the utility model works, the liquid oxygen in the oxygen branch pipeline 5 can flow back through the oxygen backflow pipeline 6, and the methane in the methane branch pipeline 7 can flow back through the methane backflow pipeline 8, thereby the continuous flow of the liquid oxygen and the methane in the auxiliary power system pipeline can be ensured, the pipeline blockage can be avoided, the liquid oxygen and the methane can be normally supplied into the thrust chamber 11, and the stability and reliability of the auxiliary power system can be ensured.

[0059] Secondly, the liquid oxygen and the methane can flow back in the oxygen branch pipeline 5 and the methane backflow pipeline 8 respectively, the gasification of the liquid oxygen and the methane in the pipeline due to the temperature rise caused by the blockage can be avoided, thereby the "gas jam" situation can be avoided, the pipeline blockage can be further avoided, the flow of the pipeline can be ensured, and the stability and reliability of the auxiliary power system can be further ensured.

[0060] Thirdly, the liquid oxygen and the methane flowing back will not enter the combustion chamber of the thrust chamber 11 in the gaseous form to burn, thereby the stability of the liquid oxygen and the methane burning in the thrust chamber 11 can be ensured, the thrust chamber 11 will not be damaged due to the violent reaction, and the stability and reliability of the auxiliary power system can be further ensured.

[0061] Finally, the liquid oxygen and the methane in the auxiliary power system of the utility model are ensured to flow by flowing back in the oxygen backflow pipeline 6 and the methane backflow pipeline 8 respectively, that is, the liquid oxygen and the methane do not need to be discharged by the outside, thereby the waste of the liquid oxygen and the methane is reduced, and the effective carrying capacity of the rocket is improved.

[0062] According to an embodiment of the utility model, the number of the thrust chambers 11 is several, the oxygen branch pipeline 5 is extended and sequentially communicated with the combustion chambers of the several thrust chambers 11, and the methane branch pipeline 7 is extended and sequentially communicated with the combustion chambers of the several thrust chambers 11. The extended oxygen branch pipeline 5 and the extended methane branch pipeline 7 are independently arranged, that is, the extended oxygen branch pipeline 5 and the extended methane branch pipeline 7 are not communicated.

[0063] In the embodiment, referring to Figure 1 , the number of the thrust chambers 11 can be three, and the number of the thrust chambers 11 can be adjusted by the person skilled in the art according to the actual situation, and the extended oxygen branch pipeline 5 and the extended methane branch pipeline 7 are respectively communicated with the combustion chambers of each thrust chamber 11, thereby the liquid oxygen and the methane are introduced into the combustion chambers of each thrust chamber 11. Compared with arranging one thrust chamber 11, the arrangement of the several thrust chambers 11 can increase the auxiliary power of the rocket (that is, the thrust of the rocket).

[0064] According to one embodiment of the present application, the oxygen branch pipeline 5 is provided with an oxygen power mechanism, the oxygen power mechanism is located on the oxygen branch pipeline 5, and is specifically arranged between the communication position of the oxygen branch pipeline 5 and the oxygen main pipeline 3 and the communication position of the oxygen branch pipeline 5 and the oxygen return pipeline 6.

[0065] Further, in the present embodiment, referring to Figure 1 , the oxygen power mechanism is located between the communication position of the oxygen branch pipeline 5 and the oxygen main pipeline 3 and the communication position of the oxygen branch pipeline 5 and the oxygen return pipeline 6.

[0066] Preferably, the oxygen power mechanism can be an oxygen pump 12, the oxygen pump 12 is located on the oxygen return pipeline 6, and is specifically located between the communication position of the oxygen main pipeline 3 and the oxygen branch pipeline 5 and the communication position of the oxygen branch pipeline 5 and the oxygen main pipeline 3. An oxygen pump motor 13 is installed on the oxygen pump 12, the oxygen pump motor 13 is used to provide power for the oxygen pump 12, and the oxygen pump 12 is used to pressurize oxygen in the oxygen branch pipeline 5.

[0067] According to one embodiment of the present application, the methane branch pipeline 7 is provided with a methane power mechanism, the methane power mechanism is located on the methane main pipeline 4, and is specifically located between the communication position of the methane main pipeline and the methane return pipeline 8 and the communication position of the methane return pipeline 8 and the methane branch pipeline 7.

[0068] Further, in the present embodiment, referring to Figure 1 , the methane power mechanism is located between the communication position of the methane branch pipeline 7 and the methane main pipeline 4 and the communication position of the methane branch pipeline 7 and the methane return pipeline 8.

[0069] Preferably, the methane power mechanism can be a methane pump 14, the methane pump 14 is located between the communication position of the methane branch pipeline 7 and the methane main pipeline 4 and the communication position of the methane branch pipeline 7 and the methane return pipeline 8. A methane pump motor 15 is installed on the methane pump 14, the methane pump motor 15 is used to provide power for the methane pump 14, and the methane pump 14 is used to pressurize methane in the methane branch pipeline 7.

[0070] The oxygen pump 12 and the methane pump 14 are all prior art known to those skilled in the art, for example, a centrifugal pump or a gear pump known in the art is used; the oxygen pump motor 13 and the methane pump motor 15 are also all prior art known to those skilled in the art, for example, a motor that provides power for a centrifugal pump or a gear pump, which is not particularly limited here.

[0071] In the present embodiment, through the arrangement of the oxygen pump 12 and the methane pump 14, pump power can be provided for liquid oxygen and methane flowing into the oxygen branch pipeline 5 and the methane branch pipeline 7 from the oxygen storage tank 1 and the methane storage tank 2 respectively, and then the liquid oxygen and the methane can flow into the combustion chamber of the thrust chamber 11 better, and the normal operation of the auxiliary power system is further ensured.

[0072] According to an embodiment of the present application, the oxygen main pipeline 3, the methane main pipeline 4, the oxygen branch pipeline 5, the oxygen return pipeline 6, the methane branch pipeline 7 and the methane return pipeline 8 can all be vacuum tubes. Referring to Figure 2 , the periphery of the vacuum tube is a vacuum interlayer. The vacuum interlayer can almost eliminate heat conduction and air convection, thereby significantly improving the heat preservation performance of the vacuum tube, effectively preventing the outside environment from affecting the temperature of the oxygen and methane in the vacuum tube, and thereby effectively avoiding the situation of temperature rise of the oxygen and methane in the vacuum tube and gasification of the propellant in the pipeline. The auxiliary power system of the embodiment of the present application further reduces the probability of "air blockage" by setting the vacuum tube and the interlayer outside the vacuum tube, better prevents blockage in the pipeline, ensures the stability of the auxiliary power system, and further improves the working reliability of the auxiliary power system. The vacuum tube and the vacuum interlayer are all prior art known to those skilled in the art, and will not be described in detail here.

[0073] According to an embodiment of the present application, the outer wall of the oxygen main pipeline 3, the methane main pipeline 4, the oxygen branch pipeline 5, the oxygen return pipeline 6, the methane branch pipeline 7 and the methane return pipeline 8 is all coated with a heat preservation layer.

[0074] In the present embodiment, referring to Figure 2 , Figure 2 is a schematic view of the heat preservation layer coated on the outer wall of the vacuum tube; wherein the heat preservation layer is preferably polyethylene foam 18 and ultra-low temperature glue 19 known to those skilled in the art, and the polyethylene foam 18 is located between the outer wall of the vacuum tube and the ultra-low temperature glue 19. The polyethylene foam 18 and the ultra-low temperature glue 19 have good heat preservation performance, can bring good heat preservation effect to the vacuum tube, improve the heat preservation of the vacuum tube, reduce the influence of the outside environment on the temperature of the liquid oxygen and methane in the vacuum tube, and thereby effectively avoid the situation of temperature rise of the oxygen and methane in the vacuum tube and gasification of the propellant in the pipeline, reduce the probability of "air blockage", further ensure the stability of the auxiliary power system, and improve the working reliability of the auxiliary power system.

[0075] In addition, the heat preservation layer can also be any heat preservation material suitable for the pipeline of the auxiliary power system known to those skilled in the art, such as glass fiber or aerogel known in the art, etc., which is not particularly limited here.

[0076] According to an embodiment of the present application, the oxygen return pipeline 6 and the methane return pipeline 8 are both provided with a cavitation tube 16 and a return valve 17.

[0077] In the present embodiment, referring to Figure 1The reflux valve 17 installed on the oxygen reflux pipeline 6 is located between the connection of the oxygen reflux pipeline 6 and the oxygen main pipeline 3 and the cavitation pipeline 16 installed on the oxygen reflux pipeline 6; the reflux valve 17 installed on the methane reflux pipeline 8 is located between the connection of the methane reflux pipeline 8 and the methane main pipeline 4 and the cavitation pipeline 16 installed on the methane reflux pipeline 8.

[0078] The reflux valve 17 is a prior art known in the art, which can prevent reverse flow. When the liquid oxygen and the methane reflux in the oxygen reflux pipeline 6 and the methane reflux pipeline 8 respectively, the reflux valve 17 can effectively avoid the reverse flow of the liquid oxygen and the methane in the oxygen reflux pipeline 6 and the methane reflux pipeline 8 respectively, that is, the liquid oxygen can only reflux from the oxygen branch pipeline 5 into the oxygen reflux pipeline 6 under the action of the reflux valve 17, and the methane can only reflux from the methane branch pipeline 7 into the methane reflux pipeline 8 under the action of the reflux valve 17, thereby ensuring the normal operation of the reflux work.

[0079] The cavitation pipeline 16 is a prior art known in the art, which can fix the flow of the fluid flowing through. When the liquid oxygen and the methane pass through the cavitation pipeline 16 in the oxygen reflux pipeline 6 and the methane reflux pipeline 8 respectively, the liquid oxygen and the methane will first pass through the contraction section of the cavitation pipeline 16, so that the flow rate is increased and the static pressure is reduced. Then the liquid oxygen and the methane will pass through the rear part of the cavitation pipeline 16, at this time, the flow rate reaches the maximum value, and the flow rate is reduced to the minimum value. Finally, with the increase of the pressure difference between the inlet and the outlet of the cavitation pipeline 16, the flow rate is gradually increased, and the throat static pressure is continuously reduced, until the throat static pressure of the cavitation pipeline 16 is reduced to the saturated vapor pressure of the liquid oxygen and the methane, the liquid oxygen and the methane are sharply vaporized, and the cavitation phenomenon occurs in the throat. At this time, if the inlet pressure of the cavitation pipeline 16 remains unchanged, even if the outlet pressure of the cavitation pipeline 16 is continuously reduced, the flow rate through the cavitation pipeline 16 can remain unchanged, thereby playing a fixed reflux role.

[0080] In addition, the direction of the thrust chamber 11 installed on the rocket body is not particularly limited, and the person skilled in the art can install the thrust chamber 11 on the rocket body at different positions and different angles according to the actual situation, so as to realize the functions of the rocket pitch, yaw, roll and sinking by combination.

[0081] According to one embodiment of the present application, with reference to Figure 1The oxygen electromagnetic valve 9 is arranged on the oxygen branch pipeline 5 and is located at the inlet of the combustion chamber of the thrust chamber 11, i.e. between the communication between the oxygen return pipeline 6 and the oxygen branch pipeline 5 and the thrust chamber 11; the methane electromagnetic valve 10 is arranged on the methane branch pipeline 7 and is located at the inlet of the combustion chamber of the thrust chamber 11, i.e. between the communication between the methane return pipeline 8 and the methane branch pipeline 7 and the thrust chamber 11.

[0082] The oxygen electromagnetic valve 9 can be opened and closed to control the flow of liquid oxygen to the thrust chamber 11, and the methane electromagnetic valve 10 can be opened and closed to control the flow of methane to the thrust chamber 11, thereby controlling the combustion ratio of liquid oxygen and methane in the combustion chamber of the thrust chamber 11, and further ensuring the smooth operation of the liquid oxygen and methane supplied to the thrust chamber 11.

[0083] The oxygen electromagnetic valve 9 and the methane electromagnetic valve 10 are both prior art known to those skilled in the art, and will not be described in detail here.

[0084] According to an embodiment of the present application, with reference to Figure 1 The outlet of the oxygen electromagnetic valve 9 and the outlet of the methane electromagnetic valve 10 are both integrally arranged with the inlet of the combustion chamber of the thrust chamber 11, and the outlet of the oxygen electromagnetic valve 9 and the outlet of the methane electromagnetic valve 10 are both located on the same plane as the inlet of the combustion chamber of the thrust chamber 11. The connection between the outlet of the oxygen electromagnetic valve 9, the outlet of the methane electromagnetic valve 10 and the inlet of the combustion chamber of the thrust chamber 11 can be welding known to those skilled in the art.

[0085] The auxiliary power system of the present embodiment can reduce the cavity volume between the oxygen electromagnetic valve 9, the methane electromagnetic valve 10 and the thrust chamber 11 through the above-mentioned integrated arrangement, thereby reducing the influence of the external environment on the pulse operation of the auxiliary power system, improving the response under pulse operation, and further ensuring the normal operation of the auxiliary power system.

[0086] The auxiliary power system of the present embodiment can avoid the case where there is still a pipeline between the oxygen electromagnetic valve 9 and the thrust chamber 11 and between the methane electromagnetic valve 10 and the thrust chamber 11; liquid oxygen and methane are in a liquid state before flowing through the oxygen electromagnetic valve 9 and the methane electromagnetic valve 10, and after passing through the oxygen electromagnetic valve 9 and the methane electromagnetic valve 10, the liquid oxygen and methane can directly enter the combustion chamber of the thrust chamber 11 in a liquid state and react rapidly, without gasification in the subsequent pipeline, improving the working stability of the thrust chamber 11 and the pulse response rate of the thrust chamber 11, and further ensuring the stability and reliability of the operation of the auxiliary power system. The above-mentioned embodiments of the present application can be combined with each other and have corresponding technical effects.

[0087] The above merely describes the preferred embodiments of the present application, and is not intended to limit the present application, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A liquid oxygen-methane assisted power system, characterized by, The oxygen tank (1), the methane tank (2) and the thrust chamber (11) are provided with oxygen communication members and communicate with the combustion chamber of the thrust chamber (11) through the oxygen communication members; the methane tank (2) and the thrust chamber (11) are provided with methane communication members and communicate with the combustion chamber of the thrust chamber (11) through the methane communication members. The oxygen communication member is provided with an oxygen backflow pipeline (6), one end of the oxygen backflow pipeline (6) communicates with one end of the oxygen communication member close to the oxygen tank (1), and the other end of the oxygen backflow pipeline (6) communicates with one end of the oxygen communication member close to the thrust chamber (11). The methane communication member is provided with a methane backflow pipeline (8), one end of the methane backflow pipeline (8) communicates with one end of the methane communication member close to the methane tank (2), and the other end of the methane backflow pipeline (8) communicates with one end of the methane communication member close to the thrust chamber (11). The oxygen communication member includes an oxygen branch pipeline (5), and the two ends of the oxygen branch pipeline (5) respectively communicate with the oxygen tank (1) and the combustion chamber of the thrust chamber (11); the methane communication member includes a methane branch pipeline (7), and the two ends of the methane branch pipeline (7) respectively communicate with the methane tank (2) and the combustion chamber of the thrust chamber (11); the oxygen backflow pipeline (6) is connected to the oxygen branch pipeline (5), and the methane backflow pipeline (8) is connected to the methane branch pipeline (7).

2. The liquid oxygen-methane assisted power system of claim 1, wherein, The number of the thrust chambers (11) is several, the oxygen branch pipeline (5) is extended and sequentially communicates with the combustion chambers of the several thrust chambers (11), and the methane branch pipeline (7) is extended and sequentially communicates with the combustion chambers of the several thrust chambers (11); the extended oxygen branch pipeline (5) and the extended methane branch pipeline (7) are independently arranged.

3. The liquid oxygen-methane assisted power system of claim 2, wherein, The oxygen branch pipeline (5) is provided with an oxygen power mechanism, which is located between the communication position of the oxygen tank (1) and the oxygen backflow pipeline (6) and the communication position of the oxygen backflow pipeline (6) and the oxygen branch pipeline (5), and is used for pressurizing the oxygen in the oxygen branch pipeline (5); 4. The liquid oxygen-methane assisted power system of claim 2, wherein, The methane branch pipeline (7) is provided with a methane power mechanism, which is located between the communication position of the methane tank (2) and the methane backflow pipeline (8) and the communication position of the methane backflow pipeline (8) and the methane branch pipeline (7), and is used for pressurizing the methane in the methane branch pipeline (7). ​ 5. The liquid oxygen-methane assisted power system of claim 4, wherein, The oxygen power mechanism comprises an oxygen pump (12) arranged on the oxygen branch pipeline (5), which is located between the communication between the oxygen storage tank (1) and the oxygen return pipeline (6) and the communication between the oxygen return pipeline (6) and the oxygen branch pipeline (5); an oxygen pump motor (13) is installed on the oxygen pump (12), which is used to provide power for the oxygen pump (12), and the oxygen pump (12) is used to pressurize the oxygen in the oxygen branch pipeline (5); The methane power mechanism comprises a methane pump (14) arranged on the methane branch pipeline (7), which is located between the communication between the methane storage tank (2) and the methane return pipeline (8) and the communication between the methane return pipeline (8) and the methane branch pipeline (7); a methane pump motor (15) is installed on the methane pump (14), which is used to provide power for the methane pump (14), and the methane pump (14) is used to pressurize the methane in the methane branch pipeline (7).

6. The liquid oxygen-methane assisted power system of claim 3, wherein, The oxygen branch pipeline (5), the oxygen return pipeline (6), the methane branch pipeline (7) and the methane return pipeline (8) are all vacuum pipes.

7. The liquid oxygen-methane assisted power system of claim 3, wherein, The outer walls of the oxygen branch pipeline (5), the oxygen return pipeline (6), the methane branch pipeline (7) and the methane return pipeline (8) are all coated with a heat preservation layer.

8. The liquid oxygen-methane assisted power system of claim 1, wherein, The oxygen return pipeline (6) and the methane return pipeline (8) are both provided with a cavitation tube (16) and a return valve (17).

9. The liquid oxygen-methane assisted power system of claim 3, wherein, The oxygen branch pipeline (5) is provided with an oxygen electromagnetic valve (9) located at the inlet of the combustion chamber of the thrust chamber (11); the methane branch pipeline (7) is provided with a methane electromagnetic valve (10) located at the inlet of the combustion chamber of the thrust chamber (11).

10. The liquid oxygen-methane assisted power system of claim 9, wherein, The outlets of the oxygen electromagnetic valve (9) and the methane electromagnetic valve (10) are integrally arranged with the inlet of the combustion chamber of the thrust chamber (11), and the outlets of the oxygen electromagnetic valve (9) and the methane electromagnetic valve (10) are located on the same plane as the inlet of the combustion chamber of the thrust chamber (11).

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