A pneumatic separation system for multi-spacecraft separation

Abstract

The embodiment of the present application discloses a kind of pneumatic separation systems for multiple spacecraft separation, comprising: high-pressure gas cylinder, electric explosion valve, pressure reducing valve, gas cylinder, at least one electromagnetic valve and at least one pneumatic push rod;Wherein, the high-pressure gas cylinder is used to output high-pressure gas to the electric explosion valve;The electric explosion valve is used to control the on-off of itself according to working instruction, so that the high-pressure gas in the high-pressure gas cylinder is output to the pressure reducing valve;The pressure reducing valve is used to reduce the pressure of the high-pressure gas according to working instruction;The gas cylinder is used to accommodate the gas output from the second end of the pressure reducing valve;The electromagnetic valve is used to control the on-off of pipeline according to working instruction, so that the gas is output to the pneumatic push rod;The pneumatic push rod is used to output the input gas pressure as thrust, and eject spacecraft from the adapter separation cabin.The present application reduces the mass of separation mechanism, eliminates the risk of spring long-term storage relaxation;Improve the pressure stability in pneumatic push rod.

Description

Technical Field

[0001] This invention relates to the field of launch vehicle technology. More specifically, it relates to a pneumatic separation system for separating multiple spacecraft. Background Technology

[0002] Currently, in the aerospace industry, an increasing number of products require the launch of multiple spacecraft from a single launch vehicle, which involves the technology of releasing and separating multiple spacecraft on the launch vehicle.

[0003] In current mature solutions, the spacecraft adapter typically provides a separation and release mechanism for each spacecraft, often using a separation spring to provide the separation impulse and achieve spacecraft release and separation. This solution is simple in structure and low in cost, but the separation mechanism has a large mass, and the spring is susceptible to slack. Some scholars have also studied aerodynamic catapult-type spacecraft separation schemes, but their research is mostly limited to single-spacecraft release and separation schemes, without considering methods for separating multiple spacecraft or the issue of consistent separation speeds across multiple spacecraft.

[0004] This patent discloses a pneumatic separation system for separating multiple spacecraft, which can achieve the release and separation of multiple spacecraft with a small weight, and each spacecraft or each group of spacecraft can be released and separated according to the command, while taking into account the consistency of the separation speed of multiple spacecraft. Summary of the Invention

[0005] The purpose of this invention is to provide a pneumatic separation system for separating multiple spacecraft, so as to solve at least one of the problems existing in the prior art.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] This invention provides a pneumatic separation system for separating multiple spacecraft, comprising:

[0008] High-pressure gas cylinder, electric explosion valve, pressure reducing valve, gas storage cylinder, at least one solenoid valve and at least one pneumatic actuator;

[0009] in,

[0010] The high-pressure gas cylinder is used to output high-pressure gas to the electric explosion valve;

[0011] The electric explosion valve is used to control its own on / off state according to the working command, so that the high-pressure gas in the high-pressure gas cylinder is output to the pressure reducing valve.

[0012] The pressure reducing valve is used to reduce the pressure of the high-pressure gas according to the working command;

[0013] The gas storage cylinder is used to contain the gas output from the second end of the pressure reducing valve;

[0014] The solenoid valve is used to control the opening and closing of the pipeline according to the working command, so that the corresponding gas is output to the pneumatic push rod.

[0015] The pneumatic push rod is used to output the input air pressure as thrust to eject the spacecraft from the adapter separation capsule;

[0016] The first end of the electric explosion valve is connected to the high-pressure gas cylinder via a pipeline.

[0017] The second end of the electric explosion valve is connected to the first end of the pressure reducing valve via a pipeline.

[0018] The second end of the pressure reducing valve is connected to the gas storage cylinder.

[0019] The second end of the pressure reducing valve is connected to the first end of the solenoid valve via a pipeline.

[0020] The second end of the solenoid valve is connected to the pneumatic push rod.

[0021] Optionally, the system also includes an inflation valve.

[0022] The high-pressure gas cylinder is filled with high-pressure gas through the filling valve.

[0023] Optionally, the electric explosion valve can be installed on the pipeline after the high-pressure gas cylinder, or it can be integrated with the high-pressure gas cylinder.

[0024] Optionally, the system also includes a high-pressure sensor.

[0025] The high-pressure sensor is installed on the pipeline between the high-pressure gas cylinder and the electric explosion valve, or on the valve body of the electric explosion valve integrated with the high-pressure gas cylinder, to monitor the pressure inside the gas cylinder.

[0026] Optionally, the system also includes a filter.

[0027] The filter is used to filter impurities from the high-pressure gas;

[0028] The filter is installed in the pipeline between the second end of the electric explosion valve and the first end of the pressure reducing valve.

[0029] Optionally, the system also includes a low-pressure sensor.

[0030] The low-pressure sensor is used to monitor the air pressure in the pipeline connecting the pressure reducing valve and the solenoid valve.

[0031] Optionally, the system further includes a safety valve.

[0032] The safety valve is used to output the low pressure to the solenoid valve according to a preset safety pressure.

[0033] The safety valve is installed in the pipeline connecting the pressure reducing valve and the solenoid valve.

[0034] Optionally, a solenoid valve controls the release and separation of one spacecraft or a solenoid valve controls the release and separation of multiple spacecraft.

[0035] Optionally, process ports are provided on the pipeline before the electric explosion valve, the pipeline between the electric explosion valve and the pressure reducing valve, the pipeline between the pressure reducing valve and the solenoid valve, and the pipeline between the solenoid valve and the pneumatic push rod, respectively, for airtightness inspection.

[0036] The beneficial effects of this invention are as follows:

[0037] This invention provides a pneumatic separation mechanism for separating multiple spacecraft. By using a pneumatic push rod instead of a spring push rod, the mass of the separation mechanism is reduced, and the risk of spring relaxation during long-term storage is eliminated. The use of a pressure reducing valve and a gas storage cylinder improves the pressure stability in the pneumatic push rod, ensuring consistent separation speed. The release and separation of each spacecraft or group of spacecraft is controlled by a solenoid valve, enabling separation based on commands. Attached Figure Description

[0038] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0039] Figure 1 An exemplary system architecture diagram is shown, in which an embodiment of the present invention can be applied. Detailed Implementation

[0040] To more clearly illustrate the present invention, the following description, in conjunction with embodiments and accompanying drawings, further explains the invention. Similar components in the drawings are indicated by the same reference numerals. Those skilled in the art should understand that the specific description below is illustrative rather than restrictive and should not be construed as limiting the scope of protection of the present invention.

[0041] This invention provides a pneumatic separation system for separating multiple spacecraft, comprising:

[0042] High-pressure gas cylinder, electric explosion valve, pressure reducing valve, gas storage cylinder, at least one solenoid valve and at least one pneumatic actuator;

[0043] in,

[0044] The high-pressure gas cylinder is used to output high-pressure gas to the electric explosion valve;

[0045] The electric explosion valve is used to control its own on / off state according to the working command, so that the high-pressure gas in the high-pressure gas cylinder is output to the pressure reducing valve.

[0046] The pressure reducing valve is used to reduce the pressure of the high-pressure gas according to the working command;

[0047] The gas storage cylinder is used to contain the gas output from the second end of the pressure reducing valve;

[0048] The solenoid valve is used to control the opening and closing of the pipeline according to the working command, so that the corresponding gas is output to the pneumatic push rod.

[0049] The pneumatic push rod is used to output the input air pressure as thrust to eject the spacecraft from the adapter separation capsule;

[0050] The first end of the electric explosion valve is connected to the high-pressure gas cylinder via a pipeline.

[0051] The second end of the electric explosion valve is connected to the first end of the pressure reducing valve via a pipeline.

[0052] The second end of the pressure reducing valve is connected to the first end of the gas storage cylinder.

[0053] The second end of the pressure reducing valve is connected to the first end of the solenoid valve via a pipeline.

[0054] The second end of the solenoid valve is connected to the pneumatic push rod.

[0055] Optionally, the system also includes an inflation valve.

[0056] The high-pressure gas cylinder is filled with high-pressure gas through the filling valve.

[0057] Optionally, the electric explosion valve can be installed on the pipeline after the high-pressure gas cylinder, or it can be integrated with the high-pressure gas cylinder.

[0058] Optionally, the system also includes a high-pressure sensor.

[0059] The high-pressure sensor is installed on the pipeline between the high-pressure gas cylinder and the electric explosion valve, or on the valve body of the electric explosion valve integrated with the high-pressure gas cylinder, to monitor the pressure inside the gas cylinder.

[0060] Optionally, the system also includes a filter.

[0061] The filter is used to filter impurities from the high-pressure gas;

[0062] The filter is installed in the pipeline between the second end of the electric explosion valve and the first end of the pressure reducing valve.

[0063] Optionally, the system also includes a low-pressure sensor.

[0064] The low-pressure sensor is used to monitor the air pressure in the pipeline connecting the pressure reducing valve and the solenoid valve.

[0065] Optionally, the system further includes a safety valve.

[0066] The safety valve is used to output the low pressure to the solenoid valve according to a preset safety pressure.

[0067] The safety valve is installed in the pipeline connecting the pressure reducing valve and the solenoid valve.

[0068] Optionally, a solenoid valve controls the release and separation of one spacecraft or a solenoid valve controls the release and separation of multiple spacecraft.

[0069] Optionally, process ports are provided on the pipeline before the electric explosion valve, the pipeline between the electric explosion valve and the pressure reducing valve, the pipeline between the pressure reducing valve and the solenoid valve, and the pipeline between the solenoid valve and the pneumatic push rod, respectively, for airtightness inspection.

[0070] One specific embodiment,

[0071] like Figure 1 As shown in the figure, a pneumatic separation mechanism system for separating multiple spacecraft provided by an embodiment of the present invention includes: a high-pressure gas cylinder, an electric explosion valve, a filter, a pressure reducing valve, a gas storage cylinder, a safety valve, at least one solenoid valve, at least one pneumatic push rod, an inflation valve, a high-pressure sensor, a low-pressure sensor, pipelines, and process ports.

[0072] like Figure 1 As shown, there are 4 spacecraft, corresponding to 8 pneumatic actuators and 3 solenoid valves.

[0073] Specifically, when there are N spacecraft, there are 2N or N corresponding pneumatic actuators and at least one solenoid valve.

[0074] The high-pressure gas cylinder, electric explosion valve, filter, pressure reducing valve, gas storage cylinder, safety valve, solenoid valve, pneumatic push rod, inflation valve, high-pressure sensor, low-pressure sensor and airtight inspection port are connected by pipelines to form a complete system.

[0075] The high-pressure gas cylinder is filled with high-pressure gas through the filling valve.

[0076] The electric explosion valve is installed on the pipeline after the high-pressure gas cylinder, or it can be integrated with the gas cylinder. The electric explosion valve is normally in a closed state. When it receives a working command, it will open the valve port, allowing the high-pressure gas in the high-pressure gas cylinder to flow downstream.

[0077] The high-pressure sensor is installed on the pipeline between the high-pressure gas cylinder and the electric explosion valve or on the valve body integrated with the gas cylinder to monitor the pressure inside the high-pressure gas cylinder.

[0078] The pressure reducing valve is connected to the high-pressure gas cylinder via a pipeline and is used to reduce the pressure of the high-pressure gas according to the working instructions. The output pressure of the pressure reducing valve can be adjusted as needed.

[0079] The second end of the pressure reducing valve is connected to a gas storage cylinder, which is used to contain the gas output from the pressure reducing valve.

[0080] The second end after the pressure reducing valve is connected to a safety valve through a pipeline, which is used to determine whether the low pressure is output to the solenoid valve according to the preset safety pressure. The safety pressure of the safety valve can be adjusted as needed.

[0081] A low-pressure sensor is connected to the second end of the pressure reducing valve via a pipeline to monitor the gas pressure in the pipeline connecting the pressure reducing valve and the solenoid valve. The second end of the pressure reducing valve is connected to the first end of the solenoid valve via a pipeline to control the opening and closing of the pipeline according to the working command, so that the corresponding gas is output to the pneumatic actuator. The solenoid valve is normally in the closed state, and opens the pipeline after receiving the working command, so that the gas flows into the pneumatic actuator.

[0082] Each solenoid valve can control the release and separation of one spacecraft, such as spacecraft 1 in the embodiment, or it can control the release and separation of multiple spacecraft, such as spacecraft 2 and spacecraft 3 in the embodiment.

[0083] Pneumatic push rods are used to actuate the spacecraft during the separation process, outputting air pressure energy as thrust to eject the spacecraft from the separation capsule. Typically, both the spacecraft and the pneumatic push rod are mounted on a spacecraft mounting bracket to ensure that there is no relative displacement between them.

[0084] Before separation, the spacecraft is usually fixed to the adapter mounting bracket; during separation, the connection between the spacecraft and the spacecraft mounting bracket is disconnected by pyrotechnic devices or other mechanisms; and then it is released from the spacecraft mounting bracket under the thrust of a pneumatic push rod.

[0085] The system also has process ports in place before the electric explosion valve, between the electric explosion valve and the pressure reducing valve, between the pressure reducing valve and the solenoid valve, and between the solenoid valve and the pneumatic push rod, for airtightness checks.

[0086] The working principle of the pneumatic separation system is as follows:

[0087] In the initial state, the electric explosion valve is closed, and the solenoid valve is closed;

[0088] High-pressure gas is introduced into the high-pressure gas cylinder through the filling valve. At this time, the high-pressure gas cylinder is in a sealed state for storing high-pressure gas.

[0089] Before the spacecraft is ready to separate, power is supplied to the electric explosion valve. The electric explosion valve opens the valve port, and high-pressure gas flows from the high-pressure gas cylinder into the pressure reducing valve. After being depressurized, it flows into the downstream gas storage cylinder and connected pipelines.

[0090] When the spacecraft needs to be separated and released, power is supplied to the corresponding solenoid valve, the gas path of the corresponding solenoid valve is opened, and high-pressure gas flows into the corresponding pneumatic push rod;

[0091] Under the action of high-pressure gas, the pneumatic push rod generates thrust, which separates and releases the spacecraft from the adaptation separation capsule at a specified speed.

[0092] In the description of this invention, it should be noted that the terms "upper," "lower," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the invention 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, and therefore should not be construed as a limitation of the invention. Unless otherwise expressly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication between two elements. For those skilled in the art, the specific meaning of the above terms in this invention can be understood according to the specific circumstances.

[0093] It should also be noted that in the description of this invention, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0094] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. For those skilled in the art, other variations or modifications can be made based on the above description. It is impossible to exhaustively list all the implementation methods here. All obvious variations or modifications derived from the technical solutions of the present invention are still within the protection scope of the present invention.

Claims

1. A pneumatic separation system for separating multiple spacecraft, characterized in that, include: High-pressure gas cylinder, electric explosion valve, pressure reducing valve, gas storage cylinder, at least one solenoid valve and multiple pneumatic push rods; in, The high-pressure gas cylinder is used to output high-pressure gas to the electric explosion valve; The electric explosion valve is used to control its own on / off state according to the working command, so that the high-pressure gas in the high-pressure gas cylinder is output to the pressure reducing valve. The pressure reducing valve is used to reduce the pressure of the high-pressure gas according to the working command; The gas storage cylinder is used to contain the gas output from the second end of the pressure reducing valve; The solenoid valve is used to control the opening and closing of the pipeline according to the working command, so that gas is output to the pneumatic push rod. The pneumatic push rod is used to output the input air pressure as thrust to eject the spacecraft from the adapter separation capsule; The first end of the electric explosion valve is connected to the high-pressure gas cylinder via a pipeline. The second end of the electric explosion valve is connected to the first end of the pressure reducing valve via a pipeline. The second end of the pressure reducing valve is connected to the first end of the gas storage cylinder. The second end of the pressure reducing valve is connected to the first end of the solenoid valve via a pipeline. The second end of the solenoid valve is connected to the pneumatic push rod.

2. The system according to claim 1, characterized in that, The system also includes an inflation valve. The high-pressure gas cylinder is filled with high-pressure gas through the filling valve.

3. The system according to claim 1, characterized in that, The electric explosion valve is installed on the pipeline after the high-pressure gas cylinder or integrated with the high-pressure gas cylinder.

4. The system according to claim 1, characterized in that, The system also includes a high-pressure sensor. The high-pressure sensor is used to monitor the pressure inside the high-pressure gas cylinder. The high-pressure sensor is installed on the pipeline between the high-pressure gas cylinder and the electric explosion valve.

5. The system according to claim 4, characterized in that, The high-pressure sensor is installed on the valve body of the electric explosion valve, which is integrated with the high-pressure gas cylinder, to monitor the pressure inside the gas cylinder.

6. The system according to claim 1, characterized in that, The system also includes filters. The filter is used to filter impurities from the high-pressure gas; The filter is installed in the pipeline between the second end of the electric explosion valve and the first end of the pressure reducing valve.

7. The system according to claim 1, characterized in that, The system also includes a low-pressure sensor. The low-pressure sensor is used to monitor the air pressure in the pipeline connecting the pressure reducing valve and the solenoid valve.

8. The system according to claim 1, characterized in that, The system also includes a safety valve. The safety valve is used to output the gas to the solenoid valve according to a preset safety pressure. The safety valve is installed in the pipeline connecting the pressure reducing valve and the solenoid valve.

9. The system according to claim 1, characterized in that, One solenoid valve controls the release and separation of one spacecraft, or one solenoid valve controls the release and separation of multiple spacecraft.

10. The system according to claim 1, characterized in that, Process ports are provided on the pipeline before the electric explosion valve, the pipeline between the electric explosion valve and the pressure reducing valve, the pipeline between the pressure reducing valve and the solenoid valve, and the pipeline between the solenoid valve and the pneumatic push rod, respectively, for airtightness inspection.

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