阅读说明：本技术 实现氧化亚氮自增压稳定供应的再生热补偿系统及方法 (Regeneration heat compensation system and method for realizing self-pressurization stable supply of nitrous oxide ) 是由 方杰 李开阳 孙冰 蔡国飙 于 2020-08-17 设计创作，主要内容包括：本申请涉及航天器推进技术领域,尤其涉及一种实现氧化亚氮自增压稳定供应的再生热补偿系统及方法。实现氧化亚氮自增压稳定供应的再生热补偿系统包括贮箱、推力室组件、喷管热端换热组件、贮箱冷端换热组件及管路冷端换热组件；贮箱通过输出管路和推进剂供应管路组件与推力室组件连通,喷管热端换热组件套设在推力室组件上,贮箱冷端换热组件设置在贮箱的热补偿端口；管路冷端换热组件套设在第二热补偿供应管路和推进剂供应管路组件上。贮箱内的部分氧化亚氮气体经喷管热端换热组件、管路冷端换热组件及贮箱冷端换热组件实现推进剂供应管路与贮箱的热补偿,节省航天器上的能源,实现气相氧化亚氮推进剂的稳定供应,保证航天器推进系统稳定运行。(The application relates to the technical field of spacecraft propulsion, in particular to a regenerative thermal compensation system and method for realizing self-pressurization and stable supply of nitrous oxide. The regenerative thermal compensation system for realizing the self-pressurization stable supply of the nitrous oxide comprises a storage tank, a thrust chamber assembly, a spray pipe hot end heat exchange assembly, a storage tank cold end heat exchange assembly and a pipeline cold end heat exchange assembly; the storage tank is communicated with the thrust chamber assembly through an output pipeline and a propellant supply pipeline assembly, the spray pipe hot end heat exchange assembly is sleeved on the thrust chamber assembly, and the storage tank cold end heat exchange assembly is arranged at a thermal compensation port of the storage tank; the pipeline cold end heat exchange assembly is sleeved on the second thermal compensation supply pipeline and the propellant supply pipeline assembly. Partial nitrous oxide gas in the storage tank passes through the spray pipe hot end heat exchange assembly, the pipeline cold end heat exchange assembly and the storage tank cold end heat exchange assembly to realize thermal compensation of a propellant supply pipeline and the storage tank, so that energy on the spacecraft is saved, stable supply of gaseous nitrous oxide propellant is realized, and stable operation of a spacecraft propulsion system is ensured.)

1. A regenerative thermal compensation system for achieving a self-pressurized stable supply of nitrous oxide comprising: the device comprises a storage tank, a thrust chamber assembly, a spray pipe hot end heat exchange assembly, a storage tank cold end heat exchange assembly and a pipeline cold end heat exchange assembly;

the output port of the storage tank is communicated with the thrust chamber assembly sequentially through an output pipeline and a propellant supply pipeline assembly;

the hot end heat exchange assembly of the spray pipe is sleeved on the thrust chamber assembly, and the cold end heat exchange assembly of the storage tank is arranged at a thermal compensation port of the storage tank;

the output port of the storage tank is communicated with the input end of the spray pipe hot end heat exchange assembly through the output pipeline and the first heat compensation supply pipeline in sequence; the output end of the spray pipe hot end heat exchange assembly is communicated with the propellant supply pipeline assembly sequentially through a second thermal compensation supply pipeline, the storage tank cold end heat exchange assembly and a third thermal compensation supply pipeline;

the pipeline cold end heat exchange assembly is sleeved on the outer sides of the second thermal compensation supply pipeline and the propellant supply pipeline assembly.

2. The regenerative thermal compensation system for realizing self-pressurization stable supply of nitrous oxide according to claim 1, wherein the lance hot end heat exchange assembly comprises a bracket and a first heat conduction pipe wound on the bracket;

the bracket is sleeved on the thrust chamber component;

the input end of the first heat conduction pipe is communicated with the first thermal compensation supply pipeline; the output end of the first heat conduction pipe is communicated with the second heat compensation supply pipeline.

3. The regenerative thermal compensation system for achieving self-pressurized stable supply of nitrous oxide of claim 1, wherein said tank cold end heat exchange assembly comprises a first water storage tank, a heat exchange column, a fourth heat pipe, and a heat pipe;

the first water storage tank is used for storing hot water;

one end of the first water storage tank is communicated with the heat exchange column, the heat exchange column is connected to the first water storage tank, the heat pipe is arranged in the heat exchange column, and one end of the heat pipe extends into the first water storage tank;

the main body of the fourth heat transfer pipe is disposed in the first water storage tank; the input end of the fourth heat conduction pipe extends out of the first water storage tank and is communicated with the second heat compensation supply pipeline; the output end of the fourth heat conduction pipe extends out of the first water storage tank and is communicated with the third heat compensation supply pipeline.

4. A regenerative thermal compensation system for achieving self-pressurized regulated supply of nitrous oxide as claimed in claim 1, wherein said propellant supply line assembly includes a first propellant supply line and a second propellant supply line;

one end of the output pipeline is communicated with the input end of the first propellant supply pipeline; an output end of the first propellant supply line communicates with an input end of the second propellant supply line, an output end of the second propellant supply line communicates with the thrust chamber assembly;

a first pressure reducer and a second pressure sensor are sequentially arranged on the first propellant supply pipeline; and the second propellant supply pipeline is sequentially provided with a flowmeter, an impulse control valve, a third pressure sensor and a sonic nozzle.

5. The regenerative thermal compensation system for enabling self-pressurized stable supply of nitrous oxide as claimed in claim 4 wherein said line cold end heat exchange assembly comprises: a second water storage tank, a second heat transfer pipe, and a third heat transfer pipe;

the second water storage tank is used for storing hot water; the main body of the second heat conduction pipe is arranged in the second water storage tank, the input end of the second heat conduction pipe extends out of the second water storage tank and is communicated with the output end of the first propellant supply pipeline, and the output end of the second heat conduction pipe extends out of the second water storage tank and is communicated with the input end of the second propellant supply pipeline;

the main body of the third heat conduction pipe is arranged in the second water storage tank, and the input end of the third heat conduction pipe extends out of the second water storage tank and is communicated with the first communication part of the second heat compensation supply pipeline;

the output end of the third heat conduction pipe extends out of the second water storage tank and is communicated with a second communication part of the second heat compensation supply pipeline.

6. The regenerative thermal compensation system for enabling self-pressurized stable supply of nitrous oxide of claim 2, wherein said thrust chamber assembly comprises a catalytic decomposition chamber and a nozzle in communication with said catalytic decomposition chamber;

the catalytic decomposition chamber is used for decomposing the nitrous oxide propellant; the bracket is sleeved on the spray pipe.

7. The regenerative thermal compensation system for realizing self-pressurization stable supply of nitrous oxide according to claim 1, wherein a temperature sensor and a first pressure sensor are arranged on the output pipeline;

the temperature sensor is proximate to the output port of the tank.

8. The regenerative thermal compensation system for realizing self-pressurization stable supply of nitrous oxide according to claim 1, wherein a thermal compensation control valve is arranged on the first thermal compensation supply pipeline; a second pressure reducer, a fourth pressure sensor and a one-way valve are sequentially arranged on the third thermal compensation supply pipeline;

the one-way valve is arranged close to the propellant supply pipeline assembly, and the second pressure reducer is arranged close to the cold end heat exchange assembly of the storage tank.

9. The regenerative thermal compensation system for achieving self-pressurized stable supply of nitrous oxide as claimed in claim 3, wherein said heat exchange column is threadably connected to said tank; and a heat insulation plate is arranged on the end surface of the heat exchange column, which is in contact with the storage box.

10. A regenerative thermal compensation method for achieving a self-pressurized stable supply of nitrous oxide, comprising the steps of:

closing the thermal compensation control valve, opening the impulse control valve, and adjusting the front pressure of the sonic nozzle through the first pressure reducer;

keeping the impulse control valve open, opening the thermal compensation control valve, and adjusting the pressure value at the outlet of a second pressure reducer in the third thermal compensation supply pipeline;

closing the thermal compensation control valve, and preheating the catalytic chamber by using a preheating power supply;

after the nitrous oxide gas is continuously decomposed in the catalytic chamber, the preheating power supply is closed;

and opening the thermal compensation control valve again, taking nitrous oxide as a coolant to absorb the heat of the outer wall of the spray pipe at the spray pipe heat exchanger assembly, transmitting part of the heat to the propellant supply pipeline assembly in the pipeline cold end heat exchange assembly, transmitting part of the heat to the water in the first water storage tank at the storage tank cold end heat exchange assembly, and transmitting the heat to the storage tank through the heat pipe to complete the thermal compensation of the storage tank.

Technical Field

The application relates to the technical field of spacecraft micro-propulsion, in particular to a regenerative thermal compensation system and method for realizing self-pressurization and stable supply of nitrous oxide.

Background

Nitrous oxide is widely known as a green propellant in spacecraft propulsion systems, and has a high saturated vapor pressure on the one hand and can realize self-pressurization supply of the propellant on the other hand.

In the process of self-pressurization supply of the nitrous oxide propellant, on one hand, the pressure in the storage tank is gradually reduced along with the continuous consumption of the nitrous oxide propellant, and when the pressure of the air pillow part of the storage tank is lower than the saturated vapor pressure, the nitrous oxide liquid is vaporized to maintain the pressure in the storage tank in a state of the saturated vapor pressure. However, as a large amount of heat is consumed in the process of vaporizing the nitrous oxide liquid, the temperature in the storage tank can be gradually reduced without external temperature compensation, the saturated vapor pressure of the nitrous oxide is closely related to the temperature, and the saturated vapor pressure of the nitrous oxide is reduced when the temperature is reduced, which is not beneficial to the stable supply of the propellant; on the other hand, in the process that nitrous oxide in the storage tank provides gas-phase propellant for the thruster in a self-pressurization mode, when incoming flow gas contains a small amount of nitrous oxide liquid drops, the control precision of the flow rate of the propellant is reduced, the stable supply of the propellant is not facilitated, and the thrust stability of the propulsion system is poor in the two aspects.

Disclosure of Invention

The application aims to provide a regeneration heat compensation system and method for realizing self-pressurization stable supply of nitrous oxide, and solves the technical problem that in the prior art, nitrous oxide propellant is unstable in supply, so that the thrust stability of a propulsion system is poor.

The application provides a realize regeneration thermal compensation system of stable supply of nitrous oxide self-pressurization, includes: the device comprises a storage tank, a thrust chamber assembly, a spray pipe hot end heat exchange assembly, a storage tank cold end heat exchange assembly and a pipeline cold end heat exchange assembly;

the storage tank is used for storing nitrous oxide propellant; the hot end heat exchange assembly of the spray pipe is sleeved on the thrust chamber assembly, and the cold end heat exchange assembly of the storage tank is arranged at a thermal compensation port of the storage tank;

the output port of the storage tank is communicated with the thrust chamber assembly sequentially through an output pipeline and a propellant supply pipeline assembly;

the output port of the storage tank is communicated with the input end of the spray pipe hot end heat exchange assembly through the output pipeline and the first heat compensation supply pipeline in sequence; the output end of the spray pipe hot end heat exchange assembly is communicated with the propellant supply pipeline assembly sequentially through a second thermal compensation supply pipeline, the storage tank cold end heat exchange assembly and a third thermal compensation supply pipeline;

the storage tank cold end heat exchange assembly is arranged at a heat compensation port of the storage tank;

the pipeline cold end heat exchange assembly is sleeved on the outer sides of the second thermal compensation supply pipeline and the propellant supply pipeline assembly.

In any of the above technical solutions, further, the nozzle hot end heat exchange assembly includes a bracket and a first heat pipe wound around the bracket;

the bracket is sleeved on the thrust chamber component;

the input end of the first heat conduction pipe is communicated with the first thermal compensation supply pipeline; the output end of the first heat conduction pipe is communicated with the second heat compensation supply pipeline.

In any of the above technical solutions, further, the storage tank cold end heat exchange assembly includes a first storage tank, a heat exchange column, a fourth heat pipe, and a heat pipe;

the first water storage tank is used for storing hot water;

one end of the first water storage tank is communicated with the heat exchange column, the heat exchange column is connected to the storage tank, the heat pipe is arranged in the heat exchange column, and one end of the heat pipe extends into the storage tank;

the main body of the fourth heat transfer pipe is disposed in the first water storage tank; the input end of the fourth heat conduction pipe extends out of the first water storage tank and is communicated with the second heat compensation supply pipeline; the output end of the fourth heat conduction pipe extends out of the first water storage tank and is communicated with the third heat compensation supply pipeline.

In any of the above solutions, further, the propellant supply line assembly includes a first propellant supply line and a second propellant supply line;

one end of the output pipeline is communicated with the input end of the first propellant supply pipeline; an output end of the first propellant supply line communicates with an input end of the second propellant supply line, an output end of the second propellant supply line communicates with the thrust chamber assembly;

a first pressure reducer and a second pressure sensor are sequentially arranged on the first propellant supply pipeline; and the second propellant supply pipeline is sequentially provided with a flowmeter, an impulse control valve, a third pressure sensor and a sonic nozzle.

In any one of the above technical solutions, further, the pipeline cold end heat exchange assembly includes: a second water storage tank, a second heat transfer pipe, and a third heat transfer pipe;

the second water storage tank is used for storing hot water; the main body of the second heat conduction pipe is arranged in the second water storage tank, the input end of the second heat conduction pipe extends out of the second water storage tank and is communicated with the output end of the first propellant supply pipeline, and the output end of the second heat conduction pipe extends out of the second water storage tank and is communicated with the input end of the second propellant supply pipeline;

the main body of the third heat conduction pipe is arranged in the second water storage tank, and the input end of the third heat conduction pipe extends out of the second water storage tank and is communicated with the first communication part of the second heat compensation supply pipeline;

the output end of the third heat conduction pipe extends out of the second water storage tank and is communicated with a second communication part of the second heat compensation supply pipeline.

In any of the above technical solutions, further, the thrust chamber assembly includes a catalytic decomposition chamber and a nozzle tube communicating with the catalytic decomposition chamber;

the catalytic decomposition chamber is used for decomposing the nitrous oxide propellant; the bracket is sleeved on the spray pipe.

In any of the above technical solutions, further, a temperature sensor and a first pressure sensor are disposed on the output pipeline;

the temperature sensor is proximate to the output port of the tank.

In any of the above technical solutions, further, a thermal compensation control valve is disposed on the first thermal compensation supply pipeline; the third thermal compensation supply pipeline is sequentially provided with a one-way valve, a fourth pressure sensor and a second pressure reducer;

the one-way valve is close to the second pressure sensor, and the second pressure reducer is close to the cold end heat exchange assembly of the storage tank.

In any of the above technical solutions, further, the heat exchange column is connected with the storage tank by a screw thread; and a heat insulation plate is arranged on the end surface of the heat exchange column, which is in contact with the storage box.

The application also provides a regenerative thermal compensation method for realizing self-pressurization stable supply of nitrous oxide, which comprises the following steps of:

closing the thermal compensation control valve, opening the impulse control valve, and adjusting the front pressure of the sonic nozzle through the first pressure reducer;

keeping the impulse control valve open, opening the thermal compensation control valve, and adjusting the pressure value at the outlet of a second pressure reducer in the third thermal compensation supply pipeline;

closing the thermal compensation control valve, and preheating the catalytic chamber by using a preheating power supply;

after the nitrous oxide gas is continuously decomposed in the catalytic chamber, the preheating power supply is closed;

and opening the thermal compensation control valve again, taking nitrous oxide as a coolant to absorb the heat of the outer wall of the spray pipe at the spray pipe heat exchanger assembly, transmitting part of the heat to the propellant supply pipeline assembly in the pipeline cold end heat exchange assembly, transmitting part of the heat to the water in the first water storage tank at the storage tank cold end heat exchange assembly, and transmitting the heat to the storage tank through the heat pipe to complete the thermal compensation of the storage tank.

Compared with the prior art, the beneficial effect of this application is:

the application provides a realize regeneration thermal compensation system of stable supply of nitrous oxide self-pressurization, includes: the device comprises a storage tank, a thrust chamber assembly, a spray pipe hot end heat exchange assembly, a storage tank cold end heat exchange assembly and a pipeline cold end heat exchange assembly;

the output port of the storage tank is communicated with the thrust chamber assembly sequentially through an output pipeline and a propellant supply pipeline assembly.

This application is provided with storage tank cold junction heat exchange assemblies at the thermal compensation port that states the storage tank, storage tank cold junction heat exchange assemblies be used for to the storage tank heat supply is used for realizing right the thermal compensation of storage tank, promptly when the liquid vaporization of nitrous oxide in the storage tank is in order to maintain the state that the pressure of storage tank inside is in saturated vapor pressure, to the storage tank provides the required heat of nitrous oxide liquid vaporization, guarantees that saturated vapor pressure is invariable with this to realize the continuous stable supply to the nitrous oxide propellant, guarantee propulsion system's thrust stability.

Specifically, a spray pipe hot end heat exchange assembly is arranged on the outer side of the thrust chamber assembly, another part of nitrous oxide gas in the storage tank is used as a coolant and sequentially flows into the spray pipe hot end heat exchange assembly through the output pipeline and the first thermal compensation supply pipeline, the nitrous oxide coolant of the part completes heat exchange in the spray pipe hot end heat exchange assembly, specifically, the nitrous oxide propellant heats the nitrous oxide coolant in a heat conduction manner at the thrust chamber assembly, so that the nitrous oxide coolant of the part has a certain temperature, the nitrous oxide coolant with the certain temperature after passing through the spray pipe hot end heat exchange assembly flows into the storage tank cold end heat exchange assembly through the second thermal compensation supply pipeline, and the nitrous oxide coolant with the certain temperature can transfer the heat to the storage tank cold end heat exchange assembly in the storage tank cold end heat exchange assembly again in a heat conduction manner, the self temperature of the cold end heat exchange assembly of the storage tank is improved, and the cold end heat exchange assembly of the storage tank is further ensured to realize stable heat compensation for the storage tank.

More specifically, the pipeline cold end heat exchange assembly is sleeved on the second thermal compensation supply pipeline and the outer side of the propellant supply pipeline assembly, and the pipeline cold end heat exchange assembly can realize the gasification of a small amount of nitrous oxide droplets contained in incoming flow gas, so that the small amount of nitrous oxide droplets are gasified into a small amount of nitrous oxide gas.

In summary, the regenerative thermal compensation system for self-pressurization and stable supply of nitrous oxide provided by the application realizes heating of the storage tank by using part of nitrous oxide gas in the storage tank through the spray pipe hot end heat exchange assembly and the storage tank cold end heat exchange assembly, realizes thermal compensation of the storage tank, not only saves limited energy on a spacecraft, but also ensures stable supply of gaseous phase nitrous oxide propellant, provides stable nitrous oxide propellant for a propulsion system of the spacecraft, and further ensures stability of the propulsion system.

The application also provides a regeneration thermal compensation method for realizing self-pressurization stable supply of nitrous oxide, which comprises the following steps:

closing the thermal compensation control valve, opening the impulse control valve, and adjusting the front pressure of the sonic nozzle through the first pressure reducer;

keeping the impulse control valve open, opening the thermal compensation control valve, and adjusting the pressure value at the outlet of a second pressure reducer in the third thermal compensation supply pipeline;

closing the thermal compensation control valve, and preheating the catalytic chamber by using a preheating power supply;

after the nitrous oxide gas is continuously decomposed in the catalytic chamber, the preheating power supply is closed;

and opening the thermal compensation control valve again, taking nitrous oxide as a coolant to absorb the heat of the outer wall of the spray pipe at the spray pipe heat exchanger assembly, transmitting part of the heat to the propellant supply pipeline assembly in the pipeline cold end heat exchange assembly, transmitting part of the heat to the water in the first water storage tank at the storage tank cold end heat exchange assembly, and transmitting the heat to the storage tank through the heat pipe to complete the thermal compensation of the storage tank.

In conclusion, the propellant supply pipeline assembly and the storage tank are heated by utilizing part of nitrous oxide gas in the storage tank through the spray pipe hot end heat exchange assembly, the pipeline cold end heat exchange assembly and the storage tank cold end heat exchange assembly, so that limited energy on the spacecraft is saved, stable supply of gaseous phase nitrous oxide propellant can be realized, and stable work of a spacecraft propulsion system is further ensured.

Drawings

In order to more clearly illustrate the detailed description of the present application or the technical solutions in the prior art, the drawings needed to be used in the detailed description of the present application or the prior art description will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative efforts.

FIG. 1 is a schematic structural diagram of a regenerative thermal compensation system for realizing self-pressurization stable supply of nitrous oxide according to an embodiment of the present disclosure;

fig. 2 is a schematic structural diagram of a hot-end heat exchange assembly of a nozzle according to an embodiment of the present disclosure;

FIG. 3 is a schematic structural diagram of a cold-end heat exchange assembly of a storage tank according to an embodiment of the present application;

fig. 4 is a schematic structural diagram of a cold-end heat exchange assembly of a pipeline according to an embodiment of the present application;

fig. 5 is a flowchart of a regenerative thermal compensation method for realizing self-pressurization stable supply of nitrous oxide according to the second embodiment of the present application.

Reference numerals:

100-a storage tank; 101-a thrust chamber assembly; 102-a nozzle hot end heat exchange assembly; 103-a storage tank cold end heat exchange assembly; 104-output line; 106-a first thermally compensated supply line; 107-second thermally compensated supply line; 108-a third thermally compensated supply line; 110-a thermal compensation port; 111-a scaffold; 112-a first heat pipe; 113-a first water storage tank; 114-a heat exchange column; 115-a heat pipe; 116-a first propellant supply line; 117-second propellant supply line; 118-a first pressure reducer; 119-a second pressure sensor; 120-a flow meter; 121-impulse control valve; 122-a third pressure sensor; 123-sonic nozzle; 124-a second water storage tank; 125-a second heat pipe; 126-a third heat conducting pipe; 127-a catalytic decomposition chamber; 128-a nozzle; 129-temperature sensor; 130-a first pressure sensor; 131-a thermally compensated control valve; 132-a one-way valve; 133-a fourth pressure sensor; 134-a second pressure reducer; 135-heat insulation plate; 136-an input end of a second heat pipe; 137-the output end of the second heat conduction pipe; 138-an input end of a third heat pipe; 139 — output end of third heat conducting pipe; 140-line cold end heat exchange assembly.

Detailed Description

The technical solutions of the present application will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are only some embodiments of the present application, but not all embodiments.

The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present application, presented in the accompanying drawings, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application.

All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.