CN117622518A - Main structure device of spacecraft platform - Google Patents
Main structure device of spacecraft platform Download PDFInfo
- Publication number
- CN117622518A CN117622518A CN202311758468.2A CN202311758468A CN117622518A CN 117622518 A CN117622518 A CN 117622518A CN 202311758468 A CN202311758468 A CN 202311758468A CN 117622518 A CN117622518 A CN 117622518A
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- China
- Prior art keywords
- frame body
- supporting frame
- main structure
- spacecraft platform
- spacecraft
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 238000009434 installation Methods 0.000 claims abstract description 12
- 238000013461 design Methods 0.000 abstract description 10
- 230000003014 reinforcing effect Effects 0.000 abstract description 10
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 238000011161 development Methods 0.000 abstract description 3
- 230000009466 transformation Effects 0.000 abstract 1
- 239000002828 fuel tank Substances 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000003287 optical effect Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 229910000861 Mg alloy Inorganic materials 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
-
- 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
-
- 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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Details Of Aerials (AREA)
- Support Of Aerials (AREA)
Abstract
The invention discloses a main structure device of a spacecraft platform, which relates to the technical field of spacecraft structure design and comprises a supporting frame body, wherein the supporting frame body is of a cube structure; the supporting frame body comprises a plurality of cross beams and stand columns with the same number; the joint of the cross beam and the upright post is in threaded connection; the honeycomb plates are fixedly arranged on each mounting surface of the supporting frame body; the auxiliary assembly comprises a first reinforcing beam and a second reinforcing beam; the first stiffening beam and the second stiffening beam are respectively arranged on two opposite installation side surfaces of the supporting frame body through the adapter. According to the invention, through the structural design of the supporting frame body and the honeycomb plate, the main structure device of the spacecraft platform has the advantages of light weight, large bearing capacity, large capacity, easiness in transformation and high reliability, the development cost of the main structure device of the single spacecraft platform can be reduced by more than half, and the aim of mass production of the main structure device of the spacecraft platform with low cost can be finally realized through mass production.
Description
Technical Field
The invention relates to the technical field of spacecraft structure design, in particular to a main structure device of a spacecraft platform.
Background
The spacecraft structure is one of the most important subsystems in the spacecraft system, determines the configuration of the spacecraft, provides a mounting interface and support for effective loads and subsystem instruments and equipment, bears and transmits various loads (including overload, vibration, impact, noise, thermal load and the like), and plays a vital role in completing the tasks of the spacecraft. The cost of the main structure design of the spacecraft is reduced, and the development cost of the whole spacecraft is greatly reduced.
Along with the refinement and the complicacy of the spacecraft task, the requirements of the spacecraft structure on bearing capacity, transmitting section vibration response control level, on-orbit precision guarantee capacity and the like are higher than the requirements of the prior art.
Therefore, there is a need to design a spacecraft platform main structure device.
Disclosure of Invention
The invention aims to provide a main structure device of a spacecraft platform, which solves the problems in the prior art and can realize the advantages of light weight, large bearing, low cost and high reliability of the main structure device of the spacecraft platform.
In order to achieve the above object, the present invention provides the following solutions: the invention provides a main structure device of a spacecraft platform, which comprises:
the support frame body is of a cube structure; the supporting frame body comprises a plurality of cross beams and stand columns with the same number; the joint of the cross beam and the upright post is in threaded connection;
the honeycomb plates are fixedly arranged on each mounting surface of the supporting frame body;
an auxiliary assembly including a first reinforcing beam and a second reinforcing beam; the first stiffening beam and the second stiffening beam are respectively installed on two opposite installation side surfaces of the supporting frame body through the adapter.
The cross beam and the upright post are respectively provided with four pieces with the same length;
the supporting frame body further comprises two middle beams and two middle columns; the two ends of the middle beam and the middle column are arranged at the central parts of any two adjacent cross beams.
The honeycomb plate is formed by bonding and solidifying a skin and a honeycomb core.
And a heat pipe or a temperature equalizing plate is arranged in the honeycomb plate.
The first stiffening beam is a straight beam, and two ends of the straight beam are respectively arranged on the adjacent cross beam and the upright post.
The second stiffening beam is a curved beam, the curved beam is of a V-shaped structure, the center of the curved beam is arranged at the center of one upright post, and two ends of the curved beam are respectively and fixedly arranged on two cross beams adjacent to the upright post; two cross beams adjacent to the upright post are parallel to each other.
The honeycomb plates are positioned on the top surface of the supporting frame body, and satellite hoisting interfaces are arranged at four corners of the top surface of the supporting frame body;
the honeycomb plate on the bottom surface of the supporting frame body is provided with a satellite and an inter-satellite mounting interface.
The invention discloses the following technical effects: according to the invention, through the structural design of the supporting frame body and the honeycomb plate, the spacecraft platform main structure device has the advantages of light weight, large bearing capacity and high reliability, the development cost of a single spacecraft platform main structure device can be reduced by 50% to 70%, and the aim of mass production of the low-cost spacecraft platform main structure device can be finally realized through mass production.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is an exploded view of a unitary structure;
FIG. 2 is a schematic view of a support frame;
FIG. 3 is a schematic diagram of a honeycomb panel structure;
FIG. 4 is a schematic view of a cross beam or column structure;
FIG. 5 is a schematic view of the overall structure of the present invention when applied to a satellite;
FIG. 6 is a schematic view of the overall structure of the lunar surface detector according to the present invention;
FIG. 7 is a schematic structural view of a spacecraft platform main structure device when the invention is applied to a lunar surface detector;
wherein, 1, support the frame body; 11. a cross beam; 12. a column; 13. a center sill; 14. a center column; 15. a satellite hoisting interface; 2. a honeycomb panel; 3. a first reinforcing beam; 4. and a second reinforcing beam.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
The invention provides a main structure device of a spacecraft platform, which comprises:
the support frame body 1, the support frame body 1 is of a cube structure; the supporting frame body 1 comprises a plurality of cross beams 11 and upright posts 12 with the same number; the joint of the cross beam 11 and the upright post 12 is in threaded connection;
the honeycomb plate 2 is fixedly arranged on each installation surface of the supporting frame body 1;
an auxiliary assembly comprising a first reinforcing beam 3 and a second reinforcing beam 4; the first reinforcing beam 3 and the second reinforcing beam 4 are respectively arranged on two opposite installation side surfaces of the supporting frame body 1 through the adapter.
The cross beam 11 and the upright post 12 are respectively provided with four pieces with the same length;
the supporting frame body 1 also comprises two middle beams 13 and two middle columns 14; the center sill 13 and the center pillar 14 are installed at the center of any two adjacent cross members 11.
The honeycomb panel 2 is formed by bonding and curing a skin and a honeycomb core.
The honeycomb plate 2 is internally provided with a heat pipe or a temperature equalizing plate.
The first stiffening beam 3 is a straight beam, and two ends of the straight beam are respectively arranged on the adjacent cross beam 11 and the upright post 12.
The second stiffening beam 4 is a curved beam, the curved beam is of a V-shaped structure, the center of the curved beam is arranged at the center of a stand column 12, and two ends of the curved beam are respectively and fixedly arranged on two cross beams 11 adjacent to the stand column 12; the two cross beams 11 adjacent to the upright 12 are parallel to each other.
The honeycomb plate 2 positioned on the top surface of the supporting frame body 1 and four corners of the top surface of the supporting frame body 1 are provided with satellite hoisting interfaces 15;
the honeycomb plate 2 supporting the bottom surface of the frame body 1 is provided with a satellite and an inter-satellite mounting interface.
In one embodiment of the invention, the spacecraft platform main structure device is applied to satellites with a total weight of less than 500 Kg) or deep space probes; the device provides reasonable overall configuration and equipment layout space for the whole spacecraft, and combines the single unit and the part assembly equipment of each functional chain into a whole, so that the device can bear the mechanical environment of ground assembly integrated test, launching section, on-orbit separation, landing and other working conditions.
In one embodiment of the present invention, the cross member 11, the upright 12, the center sill 13 and the center pillar 14 are all aluminum alloy metal structures.
Furthermore, if the middle beam needs to be further lightened to improve the rigidity, the middle beam can be replaced by magnesium alloy, carbon fiber and other materials.
In one embodiment of the present invention, the center sill 13 and the center pillar 14 are symmetrically mounted with two sets on the same mounting surface.
In one embodiment of the present invention, when the main structural device of the spacecraft platform is applied to a satellite, a fuel tank (which has large weight, large volume, and layout position affecting the center of mass of the whole satellite and affecting the attitude control of the satellite) needs to be integrally installed in the main structural device of the spacecraft platform, and at this time, the fuel tank needs to be fixedly installed on a cross beam, a stand column 12, a center sill 13 and a stand column in the supporting frame 1, so as to improve the supporting strength.
Further, as shown in fig. 5, when the device is applied to a satellite, a coordinate system is defined as shown in the following figure, wherein +x direction is a satellite flight direction, +z plane is opposite to ground, and-Z plane is back ground when the satellite is in orbit. The honeycomb boards 2 on two sides of the Y direction are satellite radiating surfaces, heat pipes and temperature equalizing boards are embedded in the honeycomb boards, a solar sailboard and a fixing component thereof are arranged on the outer side of the +Y-plane honeycomb board 2, and a sailboard driving mechanism, a driving control box, a storage battery and an inertial navigation component are arranged in the honeycomb boards; the outer side of the Y-plane honeycomb panel 2 is also provided with a solar sailboard and a fixing assembly thereof, and a sailboard driving mechanism is arranged inside the solar sailboard. A wide-field camera and a narrow-field camera are arranged on the outer side of the honeycomb panel 2 in the +X direction; the X-direction honeycomb panel 2 is equipped with a momentum flywheel and a propeller. The outside of the +Z-plane honeycomb panel 2 is provided with a measurement and control antenna, and the outside of the-Z-plane honeycomb panel 2 is provided with a measurement and control antenna, a orbit determination antenna, a star sensor and a sun sensor. Each honeycomb panel 2 is fixed by a screw to the main structure link.
In one embodiment of the invention, when equipment with larger installation mass and certain installation precision requirement in the main structure device of the spacecraft platform is directly connected with the main structure frame through the secondary structure, the installation strength and rigidity of the equipment are ensured, and other box equipment and lighter equipment are directly installed on the honeycomb plate 2. The square frame structure can fully consider the factors such as equipment function requirement, field requirement, weight distribution, cable trend, installation process and the like in equipment layout, so that the square frame structure can meet the final task requirement.
In one embodiment of the present invention, the honeycomb panel 2 is internally provided with heat pipes to meet the internal temperature equalization and heat dissipation requirements of the heat control scheme, which is beneficial to the integrated design of the heat control of the structure.
In one embodiment of the invention, the side surface of the supporting frame body can be provided with a solar wing sail panel of an energy system and a driving device installation and fixing interface thereof.
In one embodiment of the invention, the coordinate direction of the device coincides with the coordinate defining direction of the carrier (rocket or lander).
In one embodiment of the present invention, as shown in fig. 6, when the apparatus is applied to a lunar surface detector, the definition coordinate system is shown in the following figure, the +z direction is the forward direction of the detector movement, the +y is the left direction, -Y is the right direction, +x is the bottom direction, and the-X direction is the top surface. The left and right honeycomb plates 2 in the Y direction are provided with solar wing sailboards and fixing assemblies thereof. The X-top honeycomb panel 2 is a radiating surface, inside which heat pipes are embedded, and the outer surface is provided with OSR (glass secondary surface mirror also called optical solar mirror, optical solar reflector, OSR) components. The +Z direction honeycomb plate 2 is provided with a navigation camera and an obstacle avoidance camera.
Further, as shown in fig. 7, the moving system of the detector adopts a four-wheel differential system, the wheel sets and the main structure are installed on the left side and the right side of the main structure through an integrated installation design, and the differential and the main structure are also subjected to an integrated installation design, so that the installation precision of the differential can be ensured, and the mechanical rigidity of the main structure is improved. Each honeycomb panel 2 is fixed to the main structure by screws.
In the description of the present invention, it should be understood that the terms "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present invention, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present invention. The above embodiments are only illustrative of the preferred embodiments of the present invention and are not intended to limit the scope of the present invention, and various modifications and improvements made by those skilled in the art to the technical solutions of the present invention should fall within the protection scope defined by the claims of the present invention without departing from the design spirit of the present invention.
Claims (7)
1. A spacecraft platform main structure device, comprising:
the support frame body (1), wherein the support frame body (1) is of a cube structure; the supporting frame body (1) comprises a plurality of cross beams (11) and upright posts (12) with the same number; the joint of the cross beam (11) and the upright post (12) is in threaded connection;
the honeycomb plates (2) are fixedly arranged on the mounting surfaces of the supporting frame body (1);
an auxiliary assembly comprising a first stiffening beam (3) and a second stiffening beam (4); the first stiffening beam (3) and the second stiffening beam (4) are respectively arranged on two opposite installation side surfaces of the supporting frame body (1) through the adapter.
2. A spacecraft platform main structure assembly according to claim 1, wherein: the cross beam (11) and the upright posts (12) are respectively provided with four pieces with the same length;
the supporting frame body (1) further comprises two middle beams (13) and two middle columns (14); the two ends of the middle beam (13) and the middle column (14) are arranged at the central parts of any two adjacent cross beams (11).
3. A spacecraft platform main structure assembly according to claim 1, wherein: the honeycomb plate (2) is formed by bonding and solidifying a skin and a honeycomb core.
4. A spacecraft platform main structure assembly according to claim 1, wherein: and a heat pipe or a temperature equalizing plate is arranged in the honeycomb plate (2).
5. A spacecraft platform main structure assembly according to claim 1, wherein: the first stiffening beam (3) is a straight beam, and two ends of the straight beam are respectively arranged on the adjacent cross beam (11) and the upright post (12).
6. A spacecraft platform main structure assembly according to claim 1, wherein: the second stiffening beam (4) is a curved beam, the curved beam is of a V-shaped structure, the center of the curved beam is arranged at the center of one upright post (12), and two ends of the curved beam are respectively and fixedly arranged on two cross beams (11) adjacent to the upright post (12); two cross beams (11) adjacent to the upright (12) are parallel to each other.
7. A spacecraft platform main structure assembly according to claim 1, wherein: the honeycomb plates (2) are positioned on the top surface of the supporting frame body (1), and satellite hoisting interfaces (15) are arranged at four corners of the top surface of the supporting frame body (1);
the honeycomb plate (2) on the bottom surface of the supporting frame body (1) is provided with a satellite and an inter-satellite mounting interface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311758468.2A CN117622518B (en) | 2023-12-20 | 2023-12-20 | Main structure device of spacecraft platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311758468.2A CN117622518B (en) | 2023-12-20 | 2023-12-20 | Main structure device of spacecraft platform |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117622518A true CN117622518A (en) | 2024-03-01 |
| CN117622518B CN117622518B (en) | 2024-08-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311758468.2A Active CN117622518B (en) | 2023-12-20 | 2023-12-20 | Main structure device of spacecraft platform |
Country Status (1)
| Country | Link |
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| CN (1) | CN117622518B (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102975867A (en) * | 2012-11-13 | 2013-03-20 | 上海微小卫星工程中心 | Satellite module and modularized satellite |
| CN103303494A (en) * | 2013-05-30 | 2013-09-18 | 西北工业大学 | Novel nano satellite structure with self-carrying launching function |
| CN103863577A (en) * | 2014-02-25 | 2014-06-18 | 上海微小卫星工程中心 | Frame panel type satellite configuration and modular satellite |
| CN104401508A (en) * | 2014-10-27 | 2015-03-11 | 北京空间飞行器总体设计部 | Cross bracing main structure for spacecraft |
| CN107554818A (en) * | 2017-09-20 | 2018-01-09 | 上海微小卫星工程中心 | Satellite main force support structure |
| CN109941459A (en) * | 2019-03-21 | 2019-06-28 | 哈尔滨工业大学 | A kind of satellite configuration and satellite |
| CN112208792A (en) * | 2019-07-12 | 2021-01-12 | 北京前沿探索深空科技有限公司 | Satellite standard structure and frame construction |
| CN219219721U (en) * | 2023-01-09 | 2023-06-20 | 河北建设集团股份有限公司 | Building engineering building climbing frame |
| CN116552807A (en) * | 2023-05-05 | 2023-08-08 | 中国人民解放军63601部队 | Cabin structural satellite |
| CN220147585U (en) * | 2023-06-02 | 2023-12-08 | 中国星网网络创新研究院有限公司 | Satellite structure of assembly tiling layout |
-
2023
- 2023-12-20 CN CN202311758468.2A patent/CN117622518B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102975867A (en) * | 2012-11-13 | 2013-03-20 | 上海微小卫星工程中心 | Satellite module and modularized satellite |
| CN103303494A (en) * | 2013-05-30 | 2013-09-18 | 西北工业大学 | Novel nano satellite structure with self-carrying launching function |
| CN103863577A (en) * | 2014-02-25 | 2014-06-18 | 上海微小卫星工程中心 | Frame panel type satellite configuration and modular satellite |
| CN104401508A (en) * | 2014-10-27 | 2015-03-11 | 北京空间飞行器总体设计部 | Cross bracing main structure for spacecraft |
| CN107554818A (en) * | 2017-09-20 | 2018-01-09 | 上海微小卫星工程中心 | Satellite main force support structure |
| CN109941459A (en) * | 2019-03-21 | 2019-06-28 | 哈尔滨工业大学 | A kind of satellite configuration and satellite |
| CN112208792A (en) * | 2019-07-12 | 2021-01-12 | 北京前沿探索深空科技有限公司 | Satellite standard structure and frame construction |
| CN219219721U (en) * | 2023-01-09 | 2023-06-20 | 河北建设集团股份有限公司 | Building engineering building climbing frame |
| CN116552807A (en) * | 2023-05-05 | 2023-08-08 | 中国人民解放军63601部队 | Cabin structural satellite |
| CN220147585U (en) * | 2023-06-02 | 2023-12-08 | 中国星网网络创新研究院有限公司 | Satellite structure of assembly tiling layout |
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| Publication number | Publication date |
|---|---|
| CN117622518B (en) | 2024-08-16 |
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