Space propulsion system device and its design method based on automatic modular separation

Abstract

This invention provides a modular, automatically separable space propulsion system device and its design method, comprising: a propellant storage and supply module connected at one end to an orbit control engine module via a first separation interface, and at the other end connected to an attitude control engine module via 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 changes, 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 separation function between the storage and supply module, the orbit control engine module, and the attitude control engine module. This invention enables the separation of the propulsion system, eliminating part of the propulsion system, reducing the overall volume and mass of extraterrestrial landing vehicles such as those for lunar and Martian missions, improving the operating efficiency of the propulsion system, and reducing energy consumption.

Description

Technical Field

[0001] This invention relates to the field of space propulsion technology, and more specifically, to a space propulsion system device and its design method based on automatically detachable modules. Background Technology

[0002] As lunar exploration programs continue to advance, establishing lunar research bases has become a goal for lunar exploration projects worldwide. Building such bases requires transporting a large amount of facilities and equipment from Earth to the Moon, where they will be assembled and constructed. Extraterrestrial landing vehicles capable of efficient transport, rapid movement on the lunar surface, and the completion of various lunar experimental missions will be one of the key research focuses for China's future lunar exploration program.

[0003] For extraterrestrial landing vehicles, propellant is a consumable and required in large quantities. The propulsion system often occupies a significant portion of the payload and volume, and the use of toxic propellants and high-pressure gases poses certain risks. Furthermore, extraterrestrial landing vehicles remain in lunar surface activity for extended periods after landing, without the need for frequent travel between the lunar surface and near-lunar orbit, thus eliminating the need for propulsion system functionality.

[0004] Designing the propulsion system as a separable configuration can significantly reduce the mass of extraterrestrial landing vehicles, improve maneuverability, and reduce energy consumption, while also avoiding the hazards of toxic propellants and high-pressure gases to the spacecraft and astronauts. Current space system separation schemes mostly involve the complete separation of the propulsion system.

[0005] Patent document CN112298617B discloses a main structure for an on-orbit separable satellite propulsion service module, comprising: a central support cylinder, an oxygen tank, two fuel tanks, two horizontal brackets, four side plates, an upper inner support plate, a lower inner support plate, a support cylinder adapter frame, and two or more connecting components; the lower end of the support cylinder adapter frame is detachably connected to the upper frame of the central support cylinder; the standard strap interface at the upper end of the support cylinder adapter frame is detachably connected to the external payload compartment via a strap; the oxygen tank, the upper inner support plate, and the lower inner support plate are all coaxially installed inside the central support cylinder; the two horizontal brackets are respectively fixed on the outer circumference of the central support cylinder; the two fuel tanks are respectively coaxially fixed in the rings of the corresponding horizontal brackets; the two sides of the horizontal brackets are integrally connected to the side walls of the central support cylinder and the upper and lower inner support plates via side plates and connecting components.

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

[0007] To address the shortcomings of existing technologies, the purpose of this invention is to provide a space propulsion system device and its design method based on automatically detachable modules.

[0008] According to the present invention, a space propulsion system device based on modular separability includes: a storage and supply module, an orbit 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 track control engine module via a first separation interface, and the other end is connected to the attitude control engine module via a second separation interface. The storage and supply module provides propellant to the track control engine module and the attitude control engine module. The track control engine module provides the thrust torque required for track changing, 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 separation function between the storage and supply module, the track control engine module, and the attitude control engine module.

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

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

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

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

[0014] Preferably, the gas-liquid pipeline connection and separation device is located 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 upstream gas to realize the connection unlocking and separation functions of the mechanical structure.

[0016] The electrical connection separation device, the mechanical structure connection unlocking device, and the mechanical structure separation device are located 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 via 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 and unlocking device.

[0018] Preferably, each device in the gas-liquid pipeline at the separation interface can achieve automatic unlocking or separation functions controlled by the system without the need for external device assistance;

[0019] Any one or more of the storage and supply module, track control engine module, and attitude control engine module can achieve pipeline separation and sealing with other modules through the separation and sealing action of the gas-liquid pipeline connection separation device at the separation interface.

[0020] Any one or more of the aforementioned storage and supply module, track control engine module, and attitude control engine module can achieve 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 aforementioned storage and supply module, orbit control engine module, and attitude control engine module can achieve the overall structural separation of the module from the spacecraft cabin surface through a gas-driven mechanical structure connection unlocking device and a mechanical structure separation device at the separation interface.

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

[0023] Step S1: Determine the composition of the propulsion system 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: 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, identify possible separation nodes, and obtain the corresponding separation schemes based on the separation nodes;

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

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

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

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

[0029] The remaining components are distributed in the storage and supply module, the track control engine module, and the attitude control engine module, with as few pipelines as possible used between the modules.

[0030] Preferably, step S2 includes determining the separation points of the pipelines between the modules based on the pipeline connections between the propulsion system modules. The orbit control engine module and the storage and supply module are connected by a liquid circuit; the attitude control engine module and the storage and supply module are connected by a liquid circuit. Each module is arranged on the surface of the spacecraft, and the components within the module are fixed on the same separation surface. The connection and fixing points of each separation surface and the circuit interface are designed, and the gas drive pipeline required for separation is added.

[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 includes the separation order of each module and the separation order of the separation interface. The separation of the gas-liquid pipeline connection is performed first, followed by the unlocking of the mechanical structure connection, and finally the separation of the electrical connection and the mechanical structure.

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

[0034] 1. This invention enables the separation of the propulsion system, eliminating part of the propulsion system, thereby reducing the overall volume and mass of extraterrestrial landing vehicles such as those used on the moon and Mars, improving the operating efficiency of the propulsion system and reducing energy consumption.

[0035] 2. This invention eliminates redundant structures such as gas cylinders, storage tanks, and engines, reducing the potential risks to spacecraft and astronauts from high-pressure gases and toxic propellants, and is more conducive to improving the safety and reliability of its operation.

[0036] 3. The separation interface and separation program proposed in this invention can realize the separation of propulsion system modules by remote control without the need for external personnel or robotic arms, which greatly expands the scope of application.

[0037] 4. The gas-driven mechanical structure connection and unlocking device and the mechanical structure separation device used in this invention adopt an upstream gas source of the propulsion system, which reduces energy consumption and increases separation reliability. Attached Figure Description

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

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

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

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

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

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

[0044] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0045] In recent years, with the further development of my country's lunar exploration program, the concept of a manned lunar laboratory with its own landing capability has been proposed. The propulsion system is a key component of the landing capability, but it is no longer used after landing. The propulsion system not only occupies a significant portion of the lunar facility's payload and volume, but also poses certain risks due to the use of toxic propellants and high-pressure gases. Separating the propulsion system after landing would not only greatly reduce the mass of the lunar facility but also avoid the dangers of propellants and high-pressure gases.

[0046] Example 1

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

[0048] The first and second separation interfaces include standardized gas-liquid pipeline connection and separation devices, electrical connection and separation devices, mechanical structure connection and unlocking devices, and mechanical structure separation devices. The gas-liquid pipeline connection and separation devices are located at the pipeline connection points. The mechanical structure connection and unlocking devices are pneumatic unlocking devices, and the mechanical structure separation devices are also pneumatic separation devices. The electrical connection and separation devices, the gas-driven mechanical structure connection and unlocking devices, and the mechanical structure separation devices are located on the separation interface between the storage and supply module, the orbital control engine module, the attitude control engine module, and the outer side of the spacecraft cabin. Through an automated separation process design, automatic unlocking or separation functions controlled by the system can be achieved without external device assistance. The storage and supply module, the orbital control engine module, and the attitude control engine module are all connected to the gas-liquid pipeline connection and separation devices via pipelines; the electrical circuits are all connected to the electrical connection and separation devices at the separation interface; and the mechanical structures are all fixed to the mechanical structure connection and unlocking devices at the separation interface.

[0049] Each device in the gas-liquid pipeline of the separation interface can achieve automatic unlocking or separation controlled by the system without the need for external assistance. Any one or more modules among the storage and supply module, orbit control engine module, and attitude control engine module can achieve pipeline separation and sealing with other modules through the separation and sealing action of the gas-liquid pipeline connection separation device at the separation interface. Any one or more modules among the storage and supply module, orbit control engine module, and attitude control engine module can achieve unmanned automatic electrical separation of the module itself through the electrical connection separation device at the separation interface. Any one or more modules among the storage and supply module, orbit control engine module, and attitude control engine module can achieve the overall structural separation of the module from the spacecraft cabin surface through the gas-driven mechanical structure connection unlocking device and mechanical structure separation device at the separation interface.

[0050] Example 2

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

[0052] Step S1: Determine the propulsion system structure and implement modular design to minimize connection nodes between modules. Specifically, Step S1 involves dividing the propulsion system into three modules: a supply and storage module, an orbit control engine module, and an attitude control engine module. The supply and storage module provides propellant to the downstream engines of the propulsion system, including gas cylinders, tanks, and pressure reducing valves. The orbit control engine module provides the thrust torque required for orbit changes and includes the orbit control engine. The attitude control engine module provides the thrust torque required for attitude control and includes the attitude control engine. The remaining components are distributed within these three modules, with minimal piping connections between modules.

[0053] Step S2: Based on the modular design results, analyze and determine the connecting pipelines between modules, the electrical connections between modules and the spacecraft, and the mechanical structural connections. Identify possible separation nodes and obtain corresponding separation schemes based on these nodes. Step S2 includes determining the separation points of the pipelines between propulsion system modules based on the pipeline connections. The orbit control engine module and the storage and supply module are connected via a liquid circuit; the attitude control engine module and the storage and supply module are also connected via a liquid circuit. All the above modules are arranged on the spacecraft surface, and the components within the modules are fixed to the same separation surface. The connection and fixing points of each separation surface, as well as the circuit interfaces, are designed, and the gas-driven pipelines required for separation are added.

[0054] Step S3: Design and add separation interfaces for each scheme, and determine the automatic separation process. The separation interface in Step S3 includes a gas-liquid pipeline connection separation section, an electrical connection separation section, a mechanical structure connection unlocking section, and a mechanical structure separation section. A gas supply pipeline for the mechanical structure connection unlocking device and the mechanical structure separation device is added to the storage and supply module. Specifically, at the separation points of the pipelines between the modules, the gas-liquid pipeline connection separation section of the above-mentioned separation interface is arranged, enabling each module to automatically disconnect from the pipelines of other modules. At the fixed connection points of the separation surfaces of the storage and supply module, the track control engine module, and the attitude control engine module, the mechanical structure connection unlocking section and the mechanical structure separation section of the above-mentioned separation interface are arranged, enabling each module to achieve mechanical structure unlocking and ejection separation driven by gas. At the electrical connection points of the separation surfaces of the storage and supply module, the track control engine module, and the attitude control engine module, the electrical connection separation section of the above-mentioned separation interface is arranged, enabling each module to achieve automatic electrical separation.

[0055] The defined automatic separation process includes the separation sequence of each module and the separation sequence of the separation interfaces. The separation of the gas-liquid pipeline connection is prioritized, followed by the unlocking of the mechanical structure connection, and finally the separation of the electrical connection and the mechanical structure.

[0056] This invention enables the separation of unused propulsion systems from lunar, Martian, and other extraterrestrial landers. It allows for automatic separation of the propulsion system, ensuring the safety of the lander and improving its maneuverability. The invention achieves modular jettisoning of the propulsion system, reducing the overall size and mass of the spacecraft and improving its operational efficiency. The removal of redundant structures reduces the potential risks posed by high-pressure gases and toxic propellants, further enhancing operational safety. The proposed separation interface and procedure allow for remote control of the propulsion system modules without the need for external personnel or robotic arms, significantly expanding its application scope.

[0057] Example 3

[0058] This embodiment is a preferred implementation of Embodiment 1. This embodiment provides a space propulsion system device based on modular separable components, 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 gas-liquid pipeline connection and separation device 10 at the separation interface, a gas-liquid pipeline connection and separation device 11 at the separation interface, a self-locking valve 6, a self-locking valve 7, an attitude control engine 8, and a track control engine 9. In addition, such as... Figure 2 As shown, the system device separation interface 12 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 for a modularly 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 for the modularly separable space propulsion system includes the following steps:

[0062] Step 1: Determine the propulsion system structure and perform modular design to minimize the number of connection nodes between modules. First, determine the propulsion system structure; in this example, the basic propulsion system and... Figure 1 Except for the absence of the separation interface gas-liquid pipeline connection separation device 10 and the separation interface gas-liquid pipeline connection separation device 11, they are completely identical. They include 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 via a gas pipeline, sequentially passing through the self-locking valve 2, the pressure reducing valve 3, and the self-locking valve 4. Upstream of the storage tank 5 is a gas pipeline connecting to the self-locking valve 4, and downstream is a liquid pipeline connecting the self-locking valve 6 and the self-locking valve 7 in parallel. Downstream of the self-locking valve 6 is a liquid pipeline connecting to the attitude control engine, and downstream of the self-locking valve 7 is a liquid pipeline connecting to the track control engine.

[0063] The propulsion system is divided into three modules: the gas supply module, the orbit control engine module, and the attitude control engine module. Modular design should follow these principles: integrate most valves and pipelines into modules, minimize pipeline connections between modules, reduce separation nodes to reduce the weight of separation devices and improve separation reliability; furthermore, integrate as many components as possible within a module, achieving functional cohesion, and implement as many internal functions as possible within a module, minimizing external interfaces such as structural, gas-hydraulic, and electrical interfaces. The gas supply module includes gas cylinder 1, self-locking valve 2, pressure reducing valve 3, self-locking valve 4, and gas tank 5; the orbit control engine module includes self-locking valve 7 and orbit control engine 9; and the attitude control engine module includes self-locking valve 6 and attitude control engine 8. The gas supply module is connected to the orbit control engine module and attitude control engine module via hydraulic pipelines. The resulting modular propulsion system is shown below. Figure 1 As shown.

[0064] Step 2: Based on the modular design results, analyze and determine the inter-module connection pipelines, the electrical connections between modules and the spacecraft, and the mechanical structural connections. Identify possible separation points and derive possible separation schemes based on these points. The pipeline connections between the aforementioned propulsion system modules include the liquid pipelines between the storage and supply module and the orbital control engine module, as well as the liquid pipelines between the storage and supply module and the orbital control engine module. Accordingly, the separation points of the inter-module pipelines are located in the aforementioned two liquid pipeline sections. Attention should be paid to the configuration of the pipelines between and within the modules to avoid interference between pipelines during separation. All the aforementioned modules are arranged on the spacecraft surface, and the components within the modules are fixed to the same separation surface, achieving overall separation of the modules. Mechanical and thermodynamic analyses are performed on each separation surface and the spacecraft surface to design the connection and fixing points of each separation surface, as well as the corresponding separation points. Gas-driven pipelines are added to the storage and supply module. Electrical interfaces between the separation surface and the spacecraft are set according to the electrical interface requirements of each module.

[0065] In this embodiment, a separation scheme is required for the three components: the aforementioned storage and supply module, the track control engine module, and the attitude control engine module. The three modules are designed for separate separation. The separation surface is a rigid thin-plate structure, with each module component firmly fixed to the separation surface, enabling it to perform a launch and throw 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 several pneumatic separation nuts, and the mechanical structure separation device uses several pneumatic push rods. The gas-liquid pipeline connection separation device uses several liquid circuit floating disconnectors, and the electrical connection separation device uses several circuit floating disconnectors. A schematic diagram of the gas-liquid pipeline separation connection device at the separation interface is shown below. Figure 3 As shown.

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

[0068] like Figure 4 The diagram shows the installation positions of the gas-liquid pipeline separation connection device, electrical separation device, and mechanical structure connection unlocking device. The gas-liquid pipeline separation device and the electrical connection separation device adopt an active-passive structure, with the active control end and the passive device located on opposite sides of the separation point. The mechanical structure connection unlocking device also adopts an active-passive structure, with the main control end located on the storage and supply module. Driven by a low-pressure gas source downstream of the pressure reducing valve, gas enters the gas chamber of the mechanical structure connection unlocking device, driving the separation nut structure to separate and unlock; gas enters the gas chamber of the mechanical structure separation device, pushing the piston rod to achieve spring-throw separation.

[0069] The separation points between the hydraulic lines of the storage and supply module and the track control engine module, and the separation points between the hydraulic lines of the storage and supply module and the attitude control engine module, are respectively provided with the above-mentioned separation interface 12, with pipe connection separation device 10a and pipe connection separation device 11a.

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

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

[0072] Based on the determined separation device, the separation procedure is designed. Propulsion system separation involves three aspects: structural, gas-liquid piping, and electrical. Each aspect has different control and timing requirements. Structural separation involves the control of the pyrotechnic devices, gas-liquid piping separation involves the safety of the propellant and high-pressure gas, and electrical connections are crucial for achieving separation control. Proper matching of these three separation devices is essential to ensure the safe and successful completion of the separation process. An automatic separation scheme is adopted for the overall propulsion system separation procedure.

[0073] In automatic separation mode, the separation process is executed according to a program. First, the propulsion system piping is unlocked and separated, then the propulsion system module structure is unlocked, and finally the unlocked propulsion system module separates from the spacecraft and detaches to a safe distance. The entire process is unmanned. During separation, the principle of unlocking before separation is followed. For gas-liquid piping separation, when different unlocking schemes are involved, motor unlocking and separation are prioritized, with pneumatic separation nuts and other high-impact methods implemented last. In the mechanical structure unlocking and separation stage, a symmetrical jettison separation scheme should be adopted to reduce the impact of uneven impulse or mass distribution during separation on the stability and safety of lunar surface facilities.

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

[0075] 1) First, control the pipeline connection separation device 10a and pipeline connection separation device 11a at the separation interface to perform liquid pipeline separation and sealing.

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

[0077] 3) After confirming that all mechanical structure connection unlocking devices have been successfully unlocked, 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 perform mechanical structure separation. Through push rod action, the separation surfaces of the storage and supply module, orbit control engine module, and attitude control engine module are synchronously separated from the spacecraft surface. Simultaneously, send signals to control the electrical connection separation devices of the storage and supply module, orbit control engine module, and attitude control engine module to synchronously separate the circuit interfaces between the separation surfaces of the storage and supply module, orbit control engine module, and attitude control engine module and the spacecraft surface.

[0078] Accordingly, the initial propulsion system configuration of this embodiment, after being processed by the design method of the modularly separable space propulsion system, forms as follows: Figure 1 The diagram shows a modular, separable space propulsion system. It includes a separation interface gas-liquid pipeline connecting separation device 10 and a separation interface gas-liquid pipeline connecting separation device 11.

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

[0080] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0081] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A modularly separable space propulsion system device, characterized in that, include: Storage and supply module, track control engine module, attitude control engine module, first separation interface and second separation interface; One end of the supply module is connected to the track control engine module via a first separation interface, and the other end is connected to the attitude control engine module via a second separation interface. The supply module provides propellant to the track control engine module and the attitude control engine module. The track control engine module provides the thrust torque required for track changing, and the attitude control engine module provides the thrust torque required for attitude control. The first and second separation interfaces provide the separation function between the supply module, the track control engine module, and the attitude control engine module. Any of the aforementioned storage and supply module, track control engine module, and attitude control engine module can achieve pipeline separation and sealing with other modules through the separation and sealing action of the gas-liquid pipeline connection separation device at the separation interface; Any of the aforementioned storage and supply module, track control engine module, and attitude control engine module can achieve unmanned automatic electrical separation of the module itself through the electrical connection separation device at the separation interface; Any of the aforementioned storage and supply module, orbit control engine module, and attitude control engine module can achieve the overall structural separation of the module from the spacecraft cabin surface through a gas-driven mechanical structure connection unlocking device and a mechanical structure separation device at the separation interface.

2. The modularly separable space propulsion system device according to claim 1, characterized in that, The downstream of the storage and supply module is connected to the first separation interface and the second separation interface via pipelines; The upstream of the track control engine module is connected to the first separation interface via a pipeline; The attitude control engine module is connected to the second separation interface via a pipeline.

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

4. The modularly separable space propulsion system device according to claim 1, characterized in that, The gas-liquid pipeline connection and separation device is located 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 separation device, the gas-driven mechanical structure connection unlocking device, and the mechanical structure separation device are located 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 modularly separable space propulsion system device according to claim 4, 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 via pipelines, and their circuits are all connected to the electrical connection and separation device. Their mechanical structures are all fixed to the mechanical structure connection and unlocking device.

6. A design method for a modularly separable space propulsion system device according to any one of claims 1 to 5, characterized in that, The design method includes the following steps: Step S1: Determine the composition of the propulsion system 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: 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, identify possible separation nodes, and obtain the corresponding separation schemes based on the separation nodes; Step S3: Design and add separation interfaces for each separation scheme, and determine the automatic separation process.

7. The design method according to claim 6, characterized in that, The storage and supply module provides propellant to the downstream engines of the propulsion system, including gas cylinders, storage tanks, and pressure reducing valves; The track control engine module provides the thrust torque required for track changing, including the track 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 storage and supply module, the track control engine module, and the attitude control engine module.

8. The design method according to claim 6, characterized in that, Step S2 includes determining the separation points of the pipelines between the modules based on the pipeline connections between the propulsion system modules. The orbit control engine module and the storage and supply module are connected by a liquid circuit; the attitude control engine module and the storage and supply module are connected by a liquid circuit. Each module is arranged on the surface of the spacecraft, and the components within the module are fixed on the same separation surface. The connection and fixing points of each separation surface and the circuit interface are designed, and the gas drive pipeline required for separation is added.

9. The design method according to claim 6, characterized in that, The separation interface in step S3 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, and the gas supply pipeline required for the mechanical structure connection unlocking device and the mechanical structure separation device is added to the storage and supply module. The automatic separation process includes the separation order of each module and the separation order of the separation interface. The separation of the gas-liquid pipeline connection separation device is performed first, followed by the unlocking of the mechanical structure connection unlocking device, and finally the separation of the electrical connection separation device and the mechanical structure separation device.

Images