Space propulsion system device based on automatic separation of modules and design method of space propulsion system device

Abstract

The invention provides a space propulsion system device based on automatic module separation and a design method thereof. The space propulsion system device is characterized in that one end of a propellant storage and supply module is connected with an orbit control engine module through a first separation interface, and the other end of the propellant storage and supply module is connected with an attitude control engine module through a second separation interface; the storage and supply module is used for providing propellants for the orbit control engine module and the attitude control engine module, the orbit control engine module is used for providing thrust torque required by orbit transfer, and the attitude control engine module is used for providing thrust torque required by attitude control; the first separation interface and the second separation interface provide a module separation function for the storage and supply module, the orbit control engine module and the attitude control engine module. Separation of the propulsion system can be achieved, part of the propulsion system is removed, the total size and mass of extraterrestrial landing aircrafts such as lunar surfaces and Mars are reduced, the operation efficiency of the propulsion system can be improved, and energy consumption can be reduced.

Description

Technical Field

[0001] The present invention relates to the field of space propulsion technology, and in particular to a module-based automatically separable space propulsion system device and a design method thereof. Background Art

[0002] As the lunar exploration program is further developed, the establishment of a lunar scientific research base has become the goal of lunar exploration projects in various countries. The establishment of a lunar scientific research base requires a large number of facilities and equipment to be transported from the earth to the moon, and assembled and built on the lunar surface. Extraterrestrial landing vehicles that can efficiently carry, achieve rapid movement on the lunar surface, and complete a variety of lunar surface experimental tasks will become one of the research focuses of China's future lunar exploration projects.

[0003] For extraterrestrial landing vehicles, propellants are consumables and are in high demand. The propulsion system also often occupies a considerable portion of the load and volume. At the same time, due to the use of toxic propellants and high-pressure gases, it is dangerous. At the same time, extraterrestrial landing vehicles will remain active on the lunar surface for a long time after landing, and there is no need to frequently travel between the lunar surface and the near-lunar orbit, and there is no need to use the propulsion system function.

[0004] Designing the propulsion system to be detachable can not only greatly reduce the mass of the extraterrestrial landing vehicle, improve its performance and reduce energy consumption, but also avoid the harm of toxic propellants and high-pressure gases to the spacecraft and astronauts. The current space system separation scheme is mostly for the separation of the propulsion system as a whole.

[0005] Patent document CN112298617B discloses a main structure of an on-orbit detachable satellite propulsion service module, including: a central bearing cylinder, an oxygen tank, two fuel tanks, two horizontal brackets, four side plates, an upper inner support plate, a lower inner support plate, a bearing cylinder adapter frame and more than two connecting components; the lower end of the bearing cylinder adapter frame is detachably connected to the bearing cylinder upper frame of the central bearing cylinder; the standard strapping interface at the upper end of the bearing cylinder adapter frame is detachably connected to the external payload cabin through the strapping; the oxygen tank, the upper inner support plate and the lower inner support plate are all coaxially installed inside the central bearing cylinder; the two horizontal brackets are respectively fixed on the outer circumferential surface of the central bearing cylinder; the two fuel tanks are respectively coaxially fixed in the circular rings of the corresponding horizontal brackets; the two sides of the horizontal bracket are integrally connected to the side wall of the central bearing cylinder and the upper inner support plate and the lower inner support plate through side plates and connecting components.

[0006] However, patent document CN112298617B requires the addition of independent compartments or additional modules, which places high demands on the spacecraft configuration; at the same time, there is no method and device for designing separable propulsion system modules suitable for extraterrestrial landing vehicles. Summary of the invention

[0007] In view of the defects in the prior art, the object of the present invention is to provide a module-based automatically separable space propulsion system device and a design method thereof.

[0008] According to the present invention, a module-separable space propulsion system device includes: a storage and supply module, a track control engine module, an attitude control engine module, a first separation interface and a second separation interface;

[0009] One end of the propellant storage and supply module is connected to the orbit control engine module through a first separation interface, and the other end is connected to the attitude control engine module through a second separation interface; the storage and supply module provides propellant to the orbit control engine module and the attitude control engine module, the orbit control engine module provides the thrust torque required for orbit change, and the attitude control engine module provides the thrust torque required for attitude control; the first separation interface and the second separation interface provide the storage and supply module, the orbit control engine module, and the attitude control engine module with the function of separation between modules.

[0010] Preferably, the downstream of the storage and supply module is connected to the first separation interface and the second separation interface through a pipeline;

[0011] The upstream of the rail control engine module is connected to the first separation interface through a pipeline;

[0012] The upstream of the attitude control engine module is connected to the second separation interface through a pipeline.

[0013] Preferably, the first separation interface and the second separation interface include a standardized gas-liquid pipeline connection and separation device, an electrical connection and separation device, a mechanical structure connection and unlocking device and a mechanical structure separation device.

[0014] Preferably, the gas-liquid pipeline connection and separation device is arranged at the pipeline connection position;

[0015] The mechanical structure connection unlocking device is a pneumatic unlocking device, and the mechanical structure separation device is a pneumatic separation device, which can be driven by the gas in the upstream gas circuit to achieve the connection unlocking and separation functions of the mechanical structure.

[0016] The electrical connection and separation device, the mechanical structure connection and unlocking device and the mechanical structure separation device are arranged between the storage and supply module, the orbit control engine module, the attitude control engine module and the outer side of the spacecraft cabin.

[0017] Preferably, the storage and supply module, the track control engine module and the attitude control engine module are all connected to the gas-liquid pipeline connection and separation device through pipelines; the circuits are all connected to the electrical connection and separation device; and the mechanical structures are all fixed to the mechanical structure connection unlocking device.

[0018] Preferably, each device of the gas-liquid pipeline of the separation interface can realize the automatic unlocking or separation function controlled by the system without the assistance of external devices;

[0019] Any one or more of the storage and supply module, the track control engine module, and the attitude control engine module can be separated and sealed from the pipelines of other modules through the gas-liquid pipeline connection separation device of the separation interface;

[0020] Any one or more of the storage and supply module, the track control engine module, and the attitude control engine module can realize unmanned automatic electrical separation of the module itself through the electrical connection separation device of the separation interface;

[0021] Any one or more of the storage and supply module, orbit control engine module, and attitude control engine module can connect the unlocking device and the mechanical structure separation device through the gas-driven mechanical structure of the separation interface, so as to realize the ejection and separation of the module's own structure from the surface of the spacecraft cabin.

[0022] A design method for a module-separable space propulsion system device according to the present invention comprises the following steps:

[0023] Step S1: Determine the propulsion system composition and modularize it, dividing the propulsion system components into the storage and supply module, the orbit control engine module, and the attitude control engine module;

[0024] Step S2: According to the modular design results, analyze and determine the connection pipelines between modules, the circuit connection between the modules and the spacecraft, and the mechanical structure connection, determine the possible separation nodes, and obtain the corresponding separation plan according to the separation nodes;

[0025] Step S3: Design and add a separation interface for each solution and determine the automatic separation process.

[0026] Preferably, the storage and supply module provides propellant for the downstream engine of the propulsion system, including a gas cylinder, a tank and a pressure relief valve;

[0027] The orbit control engine module provides the thrust torque required for orbit change, including the orbit control engine;

[0028] The attitude control engine module provides the thrust torque required for attitude control, including attitude control engines;

[0029] The remaining components are distributed in the storage and supply module, the track control engine module, and the attitude control engine module, and the modules are connected by as few pipes as possible.

[0030] Preferably, step S2 includes determining the separation points of the pipelines between the modules according to the pipeline connections between the propulsion system modules, the orbit control engine module is connected to the storage and supply module through a liquid circuit; the attitude control engine module is connected to the storage and supply module through a liquid circuit, each module is arranged on the surface of the spacecraft, the components in the module are fixed to the same separation surface, the connection fixed points of each separation surface and the circuit interface are designed, and the gas drive pipeline required for separation is additionally provided.

[0031] Preferably, the separation interface in step S3 includes a gas-liquid pipeline connection separation part, an electrical connection separation part, a mechanical structure connection unlocking part and a mechanical structure separation part;

[0032] The automatic separation process is determined, including the separation order of each module and the separation order of the separation interface, with priority given to the separation of the gas-liquid pipeline connection separation part, followed by the unlocking of the mechanical structure connection unlocking part, and finally the separation of the electrical connection separation part and the separation of the mechanical structure separation part.

[0033] Compared with the prior art, the present invention has the following beneficial effects:

[0034] 1. The present invention can separate the propulsion system and discard part of the propulsion system, thereby reducing the total volume and mass of the landing vehicle on the moon, Mars and other extraterrestrials, and can improve the operating efficiency of the propulsion system and reduce energy consumption.

[0035] 2. The present invention removes redundant structures such as gas cylinders, tanks, and engines, reduces the potential risks of high-pressure gases and toxic propellants to spacecraft and astronauts, and is more conducive to improving the safety and reliability of the spacecraft during operation.

[0036] 3. The separation interface and separation procedure proposed in the present invention can realize the separation of propulsion system modules under remote control without the assistance of external personnel or robotic arms, which greatly expands the scope of application.

[0037] 4. The gas-driven mechanical structure used in the present invention connects the unlocking device and the mechanical structure separation device, and uses the gas source of the upstream gas path of the propulsion system to reduce energy consumption and increase separation reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0039] Figure 1 A schematic diagram of the module-separable space propulsion system configuration and method provided by the present invention;

[0040] Figure 2 A schematic diagram of a module-separable space propulsion system device provided by the present invention;

[0041] Figure 3 A schematic diagram of the structure of the separation interface gas-liquid pipeline separation and connection device provided by the present invention;

[0042] Figure 4 A schematic diagram of the installation positions of the separation interface electrical separation device, the mechanical structure connection unlocking device and the mechanical structure separation device provided by the present invention;

[0043] Figure 5 This is a general schematic diagram of the modular system and separation surface provided by the present invention. DETAILED DESCRIPTION

[0044] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0045] In recent years, with the further development of the lunar exploration program, my country has proposed the concept of a manned lunar laboratory with a landing function. The propulsion system is the key to the landing function, but it is no longer used after landing. The propulsion system not only occupies a considerable part of the load and volume of the lunar surface facilities, but also has certain dangers due to the use of toxic propellants and high-pressure gases. If the propulsion system is separated after the lunar surface facility lands, it can not only greatly reduce the mass of the lunar surface facility, but also avoid the danger of propellants and high-pressure gases.

[0046] Example 1

[0047] According to the present invention, a module-separable space propulsion system device is provided, such as Figure 1 As shown, it includes: a storage and supply module, a track control engine module, an attitude control engine module, a first separation interface and a second separation interface. One end of the propellant storage and supply module is connected to the track control engine module through the first separation interface, and the other end is connected to the attitude control engine module through the second separation interface. The downstream of the storage and supply module is connected to the first separation interface and the second separation interface through a pipeline. The upstream of the track control engine module is connected to the first separation interface through a pipeline. The upstream of the attitude control engine module is connected to the second separation interface through a pipeline.

[0048] The first separation interface and the second separation interface include a standardized gas-liquid pipeline connection and separation device, an electrical connection and separation device, a mechanical structure connection and unlocking device and a mechanical structure separation device. The gas-liquid pipeline connection and separation device is arranged at the pipeline connection position. The mechanical structure connection and unlocking device is a pneumatic unlocking device, and the mechanical structure separation device is a pneumatic separation device. The electrical connection and separation device, the gas-driven mechanical structure connection and unlocking device and the mechanical structure separation device are arranged on the separation interface between the storage and supply module, the orbit control engine module, the attitude control engine module and the outer side of the spacecraft cabin. Through the automatic separation process design, the automatic unlocking or separation function controlled by the system without the assistance of external devices can be realized. The storage and supply module, the orbit control engine module and the attitude control engine module are all connected to the gas-liquid pipeline connection and separation device through pipelines; the circuits are all connected to the electrical connection and separation device of the separation interface; and the mechanical structures are all fixed to the mechanical structure connection and unlocking device of the separation interface.

[0049] Each device of the gas-liquid pipeline of the separation interface can realize the automatic unlocking or separation function controlled by the system without the assistance of external devices. Any one or more modules among the storage and supply module, orbit control engine module, and attitude control engine module can realize pipeline separation and sealing with other modules through the separation and sealing action of the gas-liquid pipeline connection separation device of the separation interface. Any one or more modules among the storage and supply module, orbit control engine module, and attitude control engine module can realize unmanned automatic electrical separation of the module itself through the electrical connection separation device of the separation interface. Any one or more modules among the storage and supply module, orbit control engine module, and attitude control engine module can realize the ejection and separation of the module's own structure from the surface of the spacecraft cabin through the mechanical structure connection unlocking device and the mechanical structure separation device driven by the gas path of the separation interface.

[0050] Example 2

[0051] A design method for a module-separable space propulsion system device according to the present invention comprises the following steps:

[0052] Step S1: Determine the composition of the propulsion system and conduct modular design to minimize the connection nodes between modules. The step S1 is specifically to divide the components of the propulsion system into the storage and supply module, the orbit control engine module, and the attitude control engine module. The storage and supply module provides propellant for the downstream engine of the propulsion system, including gas cylinders, tanks and pressure reducing valves; the orbit control engine module provides the thrust torque required for orbit change, including the orbit control engine; the attitude control engine module provides the thrust torque required for attitude control, including the attitude control engine. The remaining components are distributed in the above three modules, and the modules are connected by as few pipes as possible.

[0053] Step S2: Based on the modular design results, analyze and determine the connecting pipelines between modules, the circuit connections between modules and spacecraft, and the mechanical structure connections, determine possible separation nodes, and obtain corresponding separation schemes based on the separation nodes. The step S2 includes determining the separation points of the pipelines between modules based on the pipeline connections between the propulsion system modules. The orbit control engine module is connected to the storage and supply module through a liquid circuit; the attitude control engine module is connected to the storage and supply module through a liquid circuit. The above modules are all arranged on the surface of the spacecraft, and the components in the modules are fixed to the same separation surface. The design obtains the connection fixed points of each separation surface, as well as the circuit interface, and adds the gas drive pipeline required for separation.

[0054] Step S3: Design and add a separation interface for each scheme, and determine the automatic separation process. The separation interface of step S3 includes a gas-liquid pipeline connection separation part, an electrical connection separation part, a mechanical structure connection unlocking part and a mechanical structure separation part, and a gas supply pipeline required for a mechanical structure connection unlocking device and a mechanical structure separation device is added to the storage and supply. Specifically, for the separation points of the pipelines between the modules, the gas-liquid pipeline connection separation part of the above-mentioned separation interface is arranged, so that each module can realize the function of automatically disconnecting the pipelines between other modules; for the storage and supply module, the rail control engine module and the attitude control engine module separation surface connection fixed points, the mechanical structure connection unlocking part and the mechanical structure separation part of the above-mentioned separation interface are arranged, so that each module can realize the function of mechanical structure unlocking and ejection separation driven by gas in the gas path; for the storage and supply module, the rail control engine module and the attitude control engine module separation surface circuit connection points, the electrical connection separation part of the above-mentioned separation interface is arranged, so that each module can realize the function of automatic electrical separation.

[0055] The automatic separation process includes the separation order of each module and the separation order of the separation interface. The gas-liquid pipeline connection separation part is separated first, followed by the unlocking of the mechanical structure connection unlocking part, and finally the electrical connection separation part and the mechanical structure separation part are separated.

[0056] The present invention can separate the propulsion system that is no longer used for extraterrestrial landing vehicles such as the moon and Mars, and can realize the automatic separation of the propulsion system, ensure the safety of extraterrestrial landing vehicles, and improve their motion performance. It can realize the separation of modules of the propulsion system by ejection, and discard part of the propulsion system, so that the total volume and mass of the spacecraft can be reduced, and the operating efficiency of its propulsion system can be improved; the removal of redundant structures can reduce the potential risks brought by high-pressure gas and toxic propellants, which is more conducive to improving its safety during operation; the proposed separation interface and separation procedure can realize the separation of propulsion system modules under remote control without the assistance of external personnel or mechanical arms, which greatly expands the scope of application.

[0057] Example 3

[0058] This embodiment is a preferred implementation of embodiment 1. This embodiment provides a module-separable space propulsion system device, such as Figure 2 As shown, it includes a gas cylinder 1, a self-locking valve 2, a pressure reducing valve 3, a self-locking valve 4, a storage tank 5, a separation interface gas-liquid pipeline connection separation device 10, a separation interface gas-liquid pipeline connection separation device 11, a self-locking valve 6, a self-locking valve 7, an attitude control engine 8, and a track control engine 9. In addition, as Figure 2 As shown, the system device separation interface 12 respectively includes a storage and supply module mechanical structure connection unlocking device 13a, a storage and supply module mechanical structure separation device 13b, a storage and supply module electrical connection separation device, a track control engine module mechanical structure connection unlocking device 14a, a track control engine module mechanical structure separation device 14b, a track control engine module electrical connection separation device, an attitude control engine module mechanical structure connection unlocking device 15a, an attitude control engine module mechanical structure separation device 15b and an attitude control engine module electrical connection separation device.

[0059] Example 4

[0060] This embodiment is a design method of a module-separable space propulsion system device based on Embodiment 3, and is also a preferred implementation of Embodiment 2.

[0061] In this embodiment, specifically, the design method of the module-separable space propulsion system includes the following steps:

[0062] Step 1: Determine the propulsion system composition and conduct modular design to minimize the number of nodes connected between modules. First, determine the propulsion system composition. Figure 1 It is completely the same except that it does not include the separation interface gas-liquid pipeline connection separation device 10 and the separation interface gas-liquid pipeline connection separation device 11. It includes a gas cylinder 1, a self-locking valve 2, a pressure reducing valve 3, a self-locking valve 4, a storage tank 5, a self-locking valve 6, a self-locking valve 7, an attitude control engine 8, and a track control engine 9. The gas cylinder 1 is connected to the storage tank 5 through the gas pipeline, through the self-locking valve 2, the pressure reducing valve 3, and the self-locking valve 4 in sequence; the storage tank 5 is connected to the self-locking valve 4 upstream through the gas pipeline, and the self-locking valve 6 and the self-locking valve 7 are connected in parallel downstream through the liquid pipeline; the self-locking valve 6 is connected to the attitude control engine downstream through the liquid pipeline, and the self-locking valve 7 is connected to the track control engine downstream through the liquid pipeline.

[0063] The components of the propulsion system are divided into the above-mentioned storage and supply module, orbit control engine module, and attitude control engine module. The modular design should follow the following design ideas: Integrate most of the valves and pipelines into the modules, use as few pipelines as possible to connect the modules, and minimize the separation nodes, which is conducive to reducing the mass of the separation device and improving the separation reliability; on this basis, a module integrates as many components as possible, with cohesive functions, and a module realizes as many internal functions as possible, minimizing the external interfaces such as structure, gas-liquid, and electricity. The storage and supply module includes a gas cylinder 1, a self-locking valve 2, a pressure reducing valve 3, a self-locking valve 4, and a storage tank 5. The orbit control engine includes a self-locking valve 7 and an orbit control engine 9. The attitude control engine module includes a self-locking valve 6 and an attitude control engine 8. The storage and supply module is connected to the orbit control engine module and the attitude control engine module respectively through liquid pipelines. The modular propulsion system is obtained as follows Figure 1 shown.

[0064] Step 2: According to the modular design results, analyze and determine the connection pipelines between modules, the circuit connection between modules and spacecraft, and the mechanical structure connection, determine the possible separation nodes, and obtain possible separation schemes based on the separation nodes. The pipeline connections between the above-mentioned propulsion system modules include the liquid pipelines between the storage and supply module and the orbital control engine module, and the liquid pipelines between the storage and supply module and the orbital control engine module. Based on this, it is determined that the separation point of the pipelines between modules is located in the above-mentioned two sections of liquid pipelines. The configuration method of the above-mentioned pipelines between modules and within modules should be noted to avoid mutual interference between pipelines during separation. The above-mentioned modules are arranged on the surface of the spacecraft, and the components in the modules are fixed on the same separation surface to achieve the overall separation of each module. Mechanical and thermodynamic analysis is carried out on each separation surface and the surface of the spacecraft, and the connection fixed points of each separation surface and the corresponding separation points are designed, and gas drive pipelines are added in the storage and supply module. The circuit interface between the separation surface and the spacecraft is set according to the electrical interface requirements of each module.

[0065] In this embodiment, it is necessary to consider the separation scheme of the three parts including the storage and supply module, the track control engine module, and the attitude control engine module, and design the three modules to be separated separately. The above separation surface is a hard thin plate structure, and each module component is firmly fixed on the separation surface and can realize the ejection function without deformation.

[0066] Step 3: Design and add separation interfaces for each solution and determine the separation process. In this embodiment, the separation interface includes a gas-liquid pipeline connection separation device, an electrical connection separation device, a mechanical structure connection unlocking device and a mechanical structure separation device. The mechanical structure connection unlocking device uses a number of pneumatic separation nuts, and the mechanical structure separation device uses a number of pneumatic push rods. The gas-liquid pipeline connection separation device uses a number of liquid floating disconnects, and the electrical connection separation device uses a number of circuit floating disconnects. The structural schematic diagram of the separation interface gas-liquid pipeline separation connection device is shown in FIG. Figure 3 shown.

[0067] The liquid circuit floating disconnector separation interface specifically corresponds to the gas-liquid pipeline connection and separation device 10 and the separation interface gas-liquid pipeline connection and separation device 11, which are respectively composed of a liquid circuit floating disconnector active end 16, a liquid circuit floating disconnector passive end 17, and a sealing device 18. Before the propulsion system is separated, the liquid circuit floating disconnector active end 16 is connected to the liquid circuit floating disconnector passive end 17, and the liquid circuit is sealed by the sealing device 18.

[0068] like Figure 4 The schematic diagram of the installation position of the gas-liquid pipeline separation connection device, electrical separation device, mechanical structure connection unlocking device and mechanical structure separation device at the separation interface shown in the figure, the gas-liquid pipeline connection separation device and the electrical connection separation device adopt active-passive structure, and the active control end and the passive device part are respectively located on both sides of the separation site. The mechanical structure connection unlocking device and the mechanical structure separation device adopt active-passive structure, and the main control end is located on the storage and supply module, and is driven by the low-pressure gas source downstream of the pressure reducing valve: the gas enters the air cavity of the mechanical structure connection unlocking device, driving the separation nut structure to unlock the petals; the gas enters the air cavity of the mechanical structure separation device, pushing the piston rod to move to achieve ejection separation.

[0069] The pipeline connection separation device 10a and the pipeline connection separation device 11a of the separation interface 12 are respectively arranged at the separation points between the liquid pipelines of the storage and supply module and the rail control engine module, and at the separation points between the liquid pipelines of the storage and supply module and the attitude control engine module.

[0070] Between the separation surfaces of each module and the cabin, for the fixed points and corresponding separation points of the separation surface of the storage and supply module, the mechanical structure connection unlocking device 13a of the storage and supply module and the mechanical structure separation device 13b of the separation interface 12 are arranged; for the fixed points and corresponding separation points of the separation surface of the track control engine module, the mechanical structure connection unlocking device 14a of the track control engine module and the mechanical structure separation device 14b of the track control engine module are arranged; for the fixed points and corresponding separation points of the separation surface of the attitude control engine module, the mechanical structure connection unlocking device 15a of the attitude control engine module and the mechanical structure separation device 15b of the attitude control engine module are arranged. Each mechanical structure separation device and the mechanical structure connection unlocking device are connected to the gas pipeline between the pressure reducing valve 3 and the self-locking valve 4 of the storage and supply module through a driving gas path.

[0071] Between the separation surfaces of each module and the cabin, for the circuit interface between the separation surface of the storage and supply module and the spacecraft, an electrical connection and separation device for the storage and supply module is arranged; for the circuit interface between the separation surface of the orbit control engine module and the spacecraft, an electrical connection and separation device for the orbit control engine module is arranged; for the circuit interface between the separation surface of the attitude control engine module and the spacecraft, an electrical connection and separation device for the attitude control engine module is arranged.

[0072] On the basis of determining the separation device, the separation program is designed. The separation of the propulsion system involves three aspects of separation: structure, gas-liquid pipeline, and electrical. Each item has different requirements for separation control and timing. Structural separation involves the control of pyrotechnic devices, and the separation of gas-liquid pipelines involves the safety of propellants and high-pressure gases. Electrical connection is the key to achieving separation control. Only when the three separation devices are properly matched can the separation process be completed safely and smoothly. For the overall separation procedure of the propulsion system, an automatic separation solution is adopted.

[0073] In the automatic separation mode, the separation process is executed according to the program. First, the propulsion system pipeline is unlocked and separated, then the propulsion system module structure is unlocked, and finally the unlocked propulsion system module is separated from the spacecraft and disengaged to a safe distance. The whole process is unmanned. When separating, follow the principle of unlocking first and then separating. For the separation of gas and liquid pipelines, when different unlocking schemes are involved at the same time, motor unlocking separation and pneumatic separation nut and other separation methods with greater impact are prioritized as the last step to be implemented. In the mechanical structure unlocking and separation link, a symmetrical ejection separation scheme should be adopted to reduce the impact of impulse or uneven mass distribution during separation on the stability and safety of lunar facilities.

[0074] In this embodiment, the separation procedure is carried out according to the following process:

[0075] 1) First, the pipeline connection separation device 10a and the pipeline connection separation device 11a at the separation interface are controlled to separate and seal the liquid and pipelines.

[0076] 2) After confirming that the pipeline to be separated is successfully separated and sealed, control the storage and supply module mechanical structure connection unlocking device 13a, the orbit control engine module mechanical structure connection unlocking device 14a and the attitude control engine module mechanical structure connection unlocking device 15a to unlock the connection between the separation surface of the storage and supply module, the orbit control engine module and the attitude control engine module and the mechanical structure of the spacecraft surface.

[0077] 3) After confirming that all mechanical structure connection unlocking devices are unlocked successfully, control the mechanical structure separation device 13b of the storage and supply module, the mechanical structure separation device 14b of the orbit control engine module, and the mechanical structure separation device 15b of the attitude control engine module to separate the mechanical structure, and make the separation surfaces of the storage and supply module, orbit control engine module, and attitude control engine module be synchronously separated from the spacecraft surface through the push rod action. At the same time, send a signal to control the electrical connection separation device of the storage and supply module, the electrical connection separation device of the orbit control engine module, and the electrical connection separation device of the attitude control engine module to synchronously separate the circuit interface between the separation surfaces of the storage and supply module, orbit control engine module, and attitude control engine module and the spacecraft surface.

[0078] Based on this, the initial propulsion system of this embodiment is formed as follows after the design method of the module-separable space propulsion system is described. Figure 1 The module-based separable space propulsion system device is shown, wherein a separation interface gas-liquid pipeline connecting the separation device 10 and a separation interface gas-liquid pipeline connecting the separation device 11 are added.

[0079] The gas-liquid pipeline connecting the separation device 10 is connected to the separation interface gas-liquid pipeline connecting the separation device 11 and the tank 5 upstream through a liquid pipeline, and is connected to the attitude control engine 8 downstream through a liquid pipeline; the gas-liquid pipeline connecting the separation device 11 is connected to the separation interface gas-liquid pipeline connecting the separation device 10 and the tank 5 upstream through a liquid pipeline, and is connected to the track control engine 9 downstream through a liquid pipeline.

[0080] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0081] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A module-separable space propulsion system device, characterized in that: include: Storage and supply module, orbit control engine module, attitude control engine module, first separation interface and second separation interface; One end of the propellant storage and supply module is connected to the orbit control engine module through a first separation interface, and the other end is connected to the attitude control engine module through a second separation interface; the storage and supply module provides propellant to the orbit control engine module and the attitude control engine module, the orbit control engine module provides the thrust torque required for orbit change, and the attitude control engine module provides the thrust torque required for attitude control; the first separation interface and the second separation interface provide the storage and supply module, the orbit control engine module, and the attitude control engine module with the function of separation between modules.

2. The module-separable space propulsion system device according to claim 1 is characterized in that: The downstream of the storage and supply module is connected to the first separation interface and the second separation interface through a pipeline; The upstream of the rail control engine module is connected to the first separation interface through a pipeline; The upstream of the attitude control engine module is connected to the second separation interface through a pipeline.

3. The module-separable space propulsion system device according to claim 1 is characterized in that: The first separation interface and the second separation interface include a standardized gas-liquid pipeline connection and separation device, an electrical connection and separation device, a mechanical structure connection and unlocking device, and a mechanical structure separation device.

4. The module-separable space propulsion system device according to claim 1 is characterized in that: The gas-liquid pipeline connection and separation device is arranged at the pipeline connection position; The mechanical structure connection unlocking device is a pneumatic unlocking device, and the mechanical structure separation device is a pneumatic separation device; The electrical connection and separation device, the gas-driven mechanical structure connection and unlocking device and the mechanical structure separation device are arranged between the storage and supply module, the orbit control engine module, the attitude control engine module and the outer side of the spacecraft cabin.

5. The module-separable space propulsion system device according to claim 4 is characterized in that: The storage and supply module, the track control engine module and the attitude control engine module are all connected to the gas-liquid pipeline connection and separation device through pipelines; the circuits are all connected to the electrical connection and separation device; and the mechanical structures are all fixed to the mechanical structure connection unlocking device.

6. The module-separable space propulsion system device according to claim 1 is characterized in that: Each device of the gas-liquid pipeline of the separation interface can realize the automatic unlocking or separation function controlled by the system without the assistance of external devices; Any one or more of the storage and supply module, the track control engine module, and the attitude control engine module can be separated and sealed from the pipelines of other modules through the gas-liquid pipeline connection separation device of the separation interface; Any one or more of the storage and supply module, the track control engine module, and the attitude control engine module can realize unmanned automatic electrical separation of the module itself through the electrical connection separation device of the separation interface; Any one or more of the storage and supply module, orbit control engine module, and attitude control engine module can realize the ejection and separation of the module's own structure from the surface of the spacecraft cabin through the gas-driven mechanical structure connection unlocking device and the mechanical structure separation device at the separation interface.

7. A method for designing a module-separable space propulsion system device according to any one of claims 1 to 6, characterized in that: The design method of the module-separable space propulsion system device includes the following steps: Step S1: Determine the propulsion system composition and modularize it, dividing the propulsion system components into the storage and supply module, the orbit control engine module, and the attitude control engine module; Step S2: According to the modular design results, analyze and determine the connection pipelines between modules, the circuit connection between the modules and the spacecraft, and the mechanical structure connection, determine the possible separation nodes, and obtain the corresponding separation plan according to the separation nodes; Step S3: Design and add a separation interface for each solution and determine the automatic separation process.

8. The design method of the module-separable space propulsion system device according to claim 1 is characterized in that: The storage and supply module provides propellant to the downstream engines of the propulsion system, including gas cylinders, tanks and pressure relief valves; The orbit control engine module provides the thrust torque required for orbit change, including the orbit control engine; The attitude control engine module provides the thrust torque required for attitude control, including attitude control engines; The remaining components are distributed in the storage and supply module, the track control engine module, and the attitude control engine module, and the modules are connected by as few pipes as possible.

9. The design method of the module-separable space propulsion system device according to claim 1 is characterized in that: The step S2 includes determining the separation points of the pipelines between the modules according to the pipeline connections between the propulsion system modules. The orbit control engine module is connected to the storage and supply module through a liquid circuit; the attitude control engine module is connected to the storage and supply module through a liquid circuit. Each module is arranged on the surface of the spacecraft, and the components in the module are fixed on the same separation surface. The fixed connection points of each separation surface and the circuit interface are designed, and the gas drive pipeline required for separation is added.

10. The design method of the module-separable space propulsion system device according to claim 1 is characterized in that: The separation interface in step S3 includes a gas-liquid pipeline connection and separation part, an electrical connection and separation part, a mechanical structure connection and unlocking part, and a mechanical structure separation part, and a gas supply pipeline required for a mechanical structure connection and unlocking device and a mechanical structure separation device is added to the storage and supply; The automatic separation process is determined, including the separation order of each module and the separation order of the separation interface, with priority given to the separation of the gas-liquid pipeline connection separation part, followed by the unlocking of the mechanical structure connection unlocking part, and finally the separation of the electrical connection separation part and the separation of the mechanical structure separation part.

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