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CN112373727A - Separable satellite propulsion system configuration - Google Patents

Separable satellite propulsion system configuration Download PDF

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Publication number
CN112373727A
CN112373727A CN202011331164.4A CN202011331164A CN112373727A CN 112373727 A CN112373727 A CN 112373727A CN 202011331164 A CN202011331164 A CN 202011331164A CN 112373727 A CN112373727 A CN 112373727A
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CN
China
Prior art keywords
satellite
bearing cylinder
propulsion system
system configuration
orbit
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Pending
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CN202011331164.4A
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Chinese (zh)
Inventor
王敏
王伟
刘正山
胡照
彭真
韩绍欢
皮晓丽
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China Academy of Space Technology CAST
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China Academy of Space Technology CAST
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Application filed by China Academy of Space Technology CAST filed Critical China Academy of Space Technology CAST
Priority to CN202011331164.4A priority Critical patent/CN112373727A/en
Publication of CN112373727A publication Critical patent/CN112373727A/en
Pending legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/242—Orbits and trajectories
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/402—Propellant tanks; Feeding propellants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/645—Separators

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Abstract

The invention discloses a separable satellite propulsion system configuration, which can be separated from a satellite after the satellite is sent into a higher orbit and the satellite enters the orbit, thereby solving the problems that the satellite is 'dead', the in-orbit conservation efficiency of the satellite is reduced, and the precious fuel resources of the satellite are consumed. The invention provides a detachable satellite propulsion system configuration, which can be used for sending a satellite to a specified orbit and comprises a bearing cylinder, a connection and separation device and a boosting control structure, wherein the bearing cylinder is used for bearing the satellite; the connecting and separating device is arranged at the top end of the bearing cylinder and is used for connecting a satellite; and the boosting control structure is connected with the connecting and separating device and used for propelling the satellite borne by the bearing cylinder to the specified orbit, and after the satellite is propelled to the specified orbit, the boosting control structure is separated from the connecting and separating device and is separated from the satellite.

Description

Separable satellite propulsion system configuration
Technical Field
The invention relates to the technical field of spaceflight, in particular to a separable satellite propulsion system configuration.
Background
There are two types of satellite access: one is that the carrier directly sends the satellite into the designated orbit, and the mode has higher requirements on the transport capacity and the attitude and orbit control of the carrier rocket, and the launching cost is high; the other method is that the satellite is driven into an intermediate orbit by carrying and then enters a designated orbit by depending on a self-propulsion system, and the mode needs the satellite to be separately provided with a set of propulsion system for orbital transfer. However, after the satellite is in orbit, the propulsion system becomes 'dead', the on-orbit maintenance efficiency of the satellite is reduced, the precious fuel resources of the satellite are consumed, and the on-orbit service life of the satellite is shortened.
Therefore, a low-orbit launching carrier rocket with lower cost is provided, a propulsion system is adopted to assist a satellite to realize orbit change, and when the satellite has the carrier rocket to convey to a low orbit, the propulsion system starts to play a role to change the orbit of the satellite from the low orbit satellite to a high orbit satellite.
But then the propulsion system will be disabled and unable to be separated from the satellite, making the satellite "stiff," reducing the efficiency of the satellite in-orbit conservation, or shortening the in-orbit life of the satellite.
Disclosure of Invention
The embodiment of the invention provides a separable satellite propulsion system configuration, which can be separated from a satellite after the satellite is sent into a higher orbit and the satellite enters the orbit, so that the problems that the satellite is 'dead', the in-orbit conservation efficiency of the satellite is reduced, and the precious fuel resources of the satellite are consumed are solved.
The invention provides a separable satellite propulsion system configuration which can be used for sending a satellite to a specified orbit, and comprises a bearing cylinder, a connection and separation device and a boosting control structure, wherein the bearing cylinder is used for bearing the satellite; the connecting and separating device is arranged at the top end of the bearing cylinder and is used for connecting a satellite; and the boosting control structure is connected with the connecting and separating device and used for propelling the satellite borne by the bearing cylinder to the specified orbit, and after the satellite is propelled to the specified orbit, the boosting control structure is separated from the connecting and separating device and is separated from the satellite.
In one possible implementation manner, the boosting control structure comprises a fuel path unit, an oxygen path unit and a control unit, wherein the fuel path unit comprises a plurality of combustion agent storage tanks which are arranged outside a bearing cylinder and connected with the bearing cylinder for storing fuel; the oxygen path unit comprises an oxidant storage box arranged inside the bearing cylinder; the control unit comprises a power unit, an air circuit unit, a first liquid circuit unit, a second liquid circuit unit and a main control unit, wherein the air circuit unit comprises a helium bottle connected to the bearing cylinder, the first liquid circuit unit is used for transmitting the oxidant of the oxidant storage tank, and the second liquid circuit unit is used for transmitting the fuel.
In one possible implementation, each combustion agent storage tank skirt in each combustion agent storage tank is arranged on a horizontal bracket, the horizontal bracket is fixed outside the bearing cylinder, and the top of each combustion agent storage tank is connected with the bearing cylinder through 2 combustion tank pull rods.
In a possible implementation manner, an upper lining plate is arranged at the top of the oxidant storage tank, and the upper lining plate is connected with the bearing cylinder;
and a lower lining plate is arranged at the bottom of the oxidant storage tank and connected with the bearing cylinder.
In a possible implementation mode, the bottom of the helium tank is installed on a helium tank support, and the top of the helium tank is connected to the bearing cylinder through a helium tank pull rod.
In a possible implementation manner, a plurality of support plates are arranged outside the bearing cylinder, and the support plates are distributed on two sides of the bearing cylinder and used for fixing or isolating the fuel unit, the oxygen path unit and the control unit.
In a possible implementation manner, the gas circuit unit and the main control unit are arranged diagonally.
In a possible implementation manner, the control unit further includes a plurality of groups of thrusters, and the groups of thrusters are uniformly distributed on the plurality of support plates and used for controlling the attitude of the detachable satellite propulsion system.
In a possible implementation manner, the control unit further comprises a power structure, the power structure is mounted on a power structure support, and the power structure support is arranged at the bottom of the bearing cylinder.
In the embodiment of the invention, the bearing cylinder and the boosting control structure are connected together through the connecting and separating device, and the boosting control structure is connected with the connecting and separating device and is used for propelling a satellite borne by the bearing cylinder to a specified orbit and separating the satellite from the connecting and separating device after the satellite is propelled to the specified orbit to separate from the satellite. The satellite is sent to the designated orbit and separated from the satellite, so that the stiffness of the satellite is avoided, the on-orbit position preserving efficiency of the satellite is improved, and the on-orbit service life of the satellite is prolonged.
Drawings
FIG. 1 is a schematic illustration of a configuration of a satellite of the present invention coupled to a detachable propulsion system, as provided by an embodiment of the present invention;
fig. 2 is an exploded schematic view of a configuration layout of a detachable propulsion system according to an embodiment of the present invention.
Detailed Description
In the solutions provided in the embodiments of the present application, the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In order to better understand the technical solutions, the technical solutions of the present application are described in detail below with reference to the drawings and specific embodiments, and it should be understood that the specific features in the embodiments and examples of the present application are detailed descriptions of the technical solutions of the present application, and are not limitations of the technical solutions of the present application, and the technical features in the embodiments and examples of the present application may be combined with each other without conflict.
The embodiment of the invention provides a separable satellite propulsion system structure, wherein a force bearing cylinder and a boosting control structure are connected together by a connection and separation device, and the boosting control structure is connected with the connection and separation device and used for propelling a satellite borne by the force bearing cylinder to a specified orbit, and after the satellite is propelled to the specified orbit, the force bearing cylinder is separated from the connection and separation device and separated from the satellite. The satellite is sent to the designated orbit and separated from the satellite, so that the stiffness of the satellite is avoided, the on-orbit position preserving efficiency of the satellite is improved, and the on-orbit service life of the satellite is prolonged.
The detachable satellite propulsion system configuration provided by the embodiment of the invention is further described in detail in the following with reference to the attached drawings. Referring to fig. 1, a satellite 1 is connected with a detachable satellite propulsion system 2 to form a combined structure. In an embodiment of the present invention, the coordinate system used is a detachable propulsion system body coordinate system (O-XYZ). Wherein, the origin of coordinates O corresponds to the theoretical center of the lower end frame of the bearing cylinder and the separation surface of the satellite and the rocket; z-axis: pointing to the direction close to the star body along the origin of coordinates; y-axis: parallel to the support plate direction; an X axis: in right-hand relationship with axis Z, Y, as shown in FIG. 2.
Referring to fig. 2, the detachable satellite propulsion system configuration provided by the embodiment of the present invention can be used for sending a satellite to a designated orbit, and the detachable satellite propulsion system includes a bearing cylinder 21, a connection and disconnection device, and a boosting control structure, wherein the bearing cylinder 21 is used for bearing the satellite; the connecting and separating device is arranged at the top end of the bearing cylinder 21 and is used for connecting a satellite; the boosting control structure is connected with the connecting and separating device and used for propelling the satellite borne by the bearing cylinder 21 to the designated orbit, then propelling the satellite to the designated orbit, separating the satellite from the connecting and separating device and separating the satellite. Because the satellite is sent to the designated orbit and separated from the satellite, the dead weight of the satellite can be avoided, the on-orbit position preserving efficiency of the satellite is improved, and the on-orbit service life of the satellite is prolonged.
The boosting control structure comprises a combustion path unit, an oxygen path unit and a control unit, wherein the combustion path unit comprises a plurality of combustion agent storage tanks 213, for example, 2 combustion agent storage tanks 213 are arranged outside the bearing cylinder 21, connected with the bearing cylinder 21 and used for storing fuel; the oxygen path unit comprises an oxidant storage tank 212 arranged inside the bearing cylinder 21; the control unit comprises a power unit, an air path unit 216, a first liquid path unit 217, a second liquid path unit 218 and a main control unit 219, wherein the air path unit 216 comprises a helium tank 214 connected to the bearing cylinder 21, the first liquid path unit 217 is used for transmitting an oxidant in the oxidant storage tank 212, and the second liquid path unit 217 is used for transmitting fuel.
Each combustion agent storage tank 213 skirt is arranged on the horizontal bracket 22, the horizontal bracket 22 is fixed outside the bearing cylinder 21, and the top of each combustion agent storage tank 213 is connected with the bearing cylinder 21 through 2 combustion tank pull rods 28. The plurality of combustion agent storage tanks 213 can be installed at two sides of the bearing cylinder 21 in a wall-mounted mode, and compared with a configuration scheme that the combustion tanks and the oxygen tanks are both installed in the bearing cylinder 21, the height of the bearing cylinder can be greatly reduced, and the reduction of the center of mass of a satellite and the development cost are facilitated.
The top of the oxidant storage tank 212 is provided with an upper lining plate 24, and the upper lining plate 24 is connected with the bearing cylinder 21; the bottom of the oxidant storage tank 212 is provided with a lower lining plate 25, and the lower lining plate 25 is connected with the bearing cylinder 21.
The bottom of the helium tank 214 is arranged on the helium tank support 27, and the top of the helium tank 214 is connected with the bearing cylinder 21 through the helium tank pull rod 26.
The outer side of the bearing cylinder 21 is provided with a plurality of support plates 23, and the support plates 23 are distributed on two sides of the bearing cylinder 21 and used for fixing or isolating the fuel unit, the oxygen path unit and the control unit. For example, the air path unit 216 and the main control unit 219 are diagonally arranged. Divide into the boosting structure and fire way unit, oxygen way unit and the control unit, install in the polylith backup pad, be convenient for the batch production.
The control unit further comprises a plurality of groups of thrusters 220, the plurality of groups of thrusters 220 being evenly distributed on the plurality of support plates 23 for detachable attitude control of the satellite propulsion system. The control unit further comprises a power structure 215, the power structure 215 is mounted on the power structure support 29, and the power structure support 29 is arranged at the bottom of the bearing cylinder 21. Most of single-machine equipment in the embodiment of the invention is arranged on the outer side of the star body, so that the device is high in openness and convenient to install and test.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.

Claims (9)

1.一种可分离卫星推进系统构型，其特征在于，用于将卫星送到指定轨道，包括：1. A detachable satellite propulsion system configuration is characterized in that, for sending the satellite to a designated orbit, comprising: 承力筒(21)，用于承载卫星；The bearing cylinder (21) is used to carry the satellite; 连接分离装置，设置在所述承力筒(21)顶端，用于连接所述卫星；A connection and separation device, arranged at the top of the bearing cylinder (21), is used to connect the satellite; 助推控制结构，与所述连接分离装置连接，用于将所述承力筒(21)所承载的卫星推进到指定轨道，在将所述卫星推进到所述指定轨道后，与所述连接分离装置分离，以脱离所述卫星。A booster control structure, connected with the connection and separation device, used to propel the satellite carried by the bearing cylinder (21) to a designated orbit, and connected to the satellite after the satellite is propelled to the designated orbit The separation device separates to disengage the satellite. 2.如权利要求1所述的可分离卫星推进系统构型，其特征在于，所述助推控制结构包括：2. The detachable satellite propulsion system configuration of claim 1, wherein the boost control structure comprises: 燃路单元，包括多个燃烧剂贮箱(213)设置于所述承力筒(21)外部，与所述承力筒(21)相连，用于存储燃料；A fuel circuit unit, comprising a plurality of combustion agent storage tanks (213) disposed outside the bearing cylinder (21), connected to the bearing cylinder (21), and used for storing fuel; 氧路单元，包括氧化剂贮箱(212)设置于所述承力筒(21)内部；an oxygen circuit unit, including an oxidant storage tank (212) disposed inside the bearing cylinder (21); 控制单元，包括动力单元以及气路单元(216)、第一液路单元(217)、第二液路单元(218)和主控单元(219)，所述气路单元(216)包括氦气瓶(214)连接在所述承力筒(21)上，所述第一液路单元(217)用于传输所述氧化剂贮箱(212)的氧化剂，所述第二液路单元(217)用于传输燃料。A control unit, comprising a power unit and a gas circuit unit (216), a first liquid circuit unit (217), a second liquid circuit unit (218) and a main control unit (219), the gas circuit unit (216) comprising helium gas The bottle (214) is connected to the bearing cylinder (21), the first liquid circuit unit (217) is used to transmit the oxidant in the oxidant storage tank (212), and the second liquid circuit unit (217) Used to transport fuel. 3.如权利要求2所述的可分离卫星推进系统构型，其特征在于，每个燃烧剂贮箱(213)中的每个燃烧剂贮箱(213)裙边设置在水平托架(22)上，所述水平托架(22)固定在所述承力筒(21)的外部，所述每个燃烧剂贮箱(213)顶部通过2个燃箱拉杆(28)与所述承力筒(21)连接。3. The detachable satellite propulsion system configuration of claim 2, wherein each of the combustion agent tanks (213) in each of the combustion agent tanks (213) is skirted on the horizontal bracket (22) ), the horizontal bracket (22) is fixed on the outside of the bearing cylinder (21), and the top of each combustion agent storage tank (213) is connected to the bearing through two fuel tank tie rods (28). The cartridge (21) is connected. 4.如权利要求2所述的可分离卫星推进系统构型，其特征在于，所述氧化剂贮箱(212)的顶部设置有上内衬板(24)，所述上内衬板(24)与所述承力筒(21)相连；4. The detachable satellite propulsion system configuration according to claim 2, wherein the top of the oxidizer tank (212) is provided with an upper inner lining plate (24), the upper inner lining plate (24) connected with the bearing cylinder (21); 所述氧化剂贮箱(212)的底部设置有下内衬板(25)，所述下内衬板(25)与所述承力筒(21)相连。The bottom of the oxidant storage tank (212) is provided with a lower inner lining plate (25), and the lower inner lining plate (25) is connected with the bearing cylinder (21). 5.如权利要求2所述的可分离卫星推进系统构型，其特征在于，所述氦气瓶(214)底部安装在氦气瓶支架(27)上，所述氦气瓶(214)顶部通过氦气瓶拉杆(26)连接在所述承力筒(21)。5. The detachable satellite propulsion system configuration according to claim 2, wherein the bottom of the helium cylinder (214) is mounted on the helium cylinder bracket (27), and the top of the helium cylinder (214) The bearing cylinder (21) is connected to the bearing cylinder (21) through a helium cylinder pull rod (26). 6.如权利要求2～4任一项所述的可分离卫星推进系统构型，其特征在于，所述承力筒(21)外侧设置有多个支撑板(23)，所述多个支撑板(23)分布在所述承力筒(21)的两侧，用于固定或隔离所述燃料单元和所述氧路单元以及所述控制单元。6. The detachable satellite propulsion system configuration according to any one of claims 2 to 4, wherein a plurality of support plates (23) are provided on the outside of the bearing cylinder (21), and the plurality of supports Plates (23) are distributed on both sides of the bearing cylinder (21) for fixing or isolating the fuel unit, the oxygen circuit unit and the control unit. 7.如权利要求6所述的可分离卫星推进系统构型，其特征在于，所述气路单元(216)和所述主控单元(219)呈斜对角布置。7. The detachable satellite propulsion system configuration according to claim 6, characterized in that, the gas circuit unit (216) and the main control unit (219) are arranged diagonally. 8.如权利要求7所述的可分离卫星推进系统构型，其特征在于，所述控制单元还包括多组推力器(220)，所述多组推力器(220)均匀分布在所述多个支撑板(23)，用于所述可分离卫星推进系统的姿态控制。8. The detachable satellite propulsion system configuration according to claim 7, wherein the control unit further comprises a plurality of sets of thrusters (220), and the multiple sets of thrusters (220) are evenly distributed among the multiple sets of thrusters (220). A support plate (23) is used for attitude control of the detachable satellite propulsion system. 9.如权利要求8所述的可分离卫星推进系统构型，其特征在于，所述控制单元还包括动力结构(215)，所述动力结构(215)安装在动力结构支架(29)上，所述动力结构支架(29)设置在所述承力筒(21)底部。9. The detachable satellite propulsion system configuration according to claim 8, wherein the control unit further comprises a power structure (215), the power structure (215) being mounted on the power structure bracket (29), The power structure bracket (29) is arranged at the bottom of the bearing cylinder (21).
CN202011331164.4A 2020-11-24 2020-11-24 Separable satellite propulsion system configuration Pending CN112373727A (en)

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CN114229040A (en) * 2021-12-17 2022-03-25 中国长城工业集团有限公司 Separable independent propulsion cabin system
CN118372986A (en) * 2024-06-25 2024-07-23 上海卫星互联网研究院有限公司 Mother satellite and son-mother satellite assembly

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CN112298617A (en) * 2020-09-29 2021-02-02 北京空间飞行器总体设计部 On-orbit separable satellite propulsion service cabin main structure

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114229040A (en) * 2021-12-17 2022-03-25 中国长城工业集团有限公司 Separable independent propulsion cabin system
CN114229040B (en) * 2021-12-17 2024-09-20 中国长城工业集团有限公司 Separable independent propulsion cabin system
CN118372986A (en) * 2024-06-25 2024-07-23 上海卫星互联网研究院有限公司 Mother satellite and son-mother satellite assembly

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