CN110667889B - Remote sensing satellite load adapter with flexible hinge - Google Patents
Remote sensing satellite load adapter with flexible hinge Download PDFInfo
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- CN110667889B CN110667889B CN201911246905.6A CN201911246905A CN110667889B CN 110667889 B CN110667889 B CN 110667889B CN 201911246905 A CN201911246905 A CN 201911246905A CN 110667889 B CN110667889 B CN 110667889B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/1021—Earth observation satellites
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/1021—Earth observation satellites
- B64G1/1028—Earth observation satellites using optical means for mapping, surveying or detection, e.g. of intelligence
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Abstract
The invention relates to the technical field of satellites, and provides a remote sensing satellite load adapter with a flexible hinge, which comprises: a support, a separating mechanism and a flexible hinge; the flexible hinge comprises a snake-shaped connecting piece, an elastic connecting piece, a first connecting seat and a second connecting seat; the snakelike connecting piece encloses into face of cylinder, and snakelike connecting piece meanders along the axial on face of cylinder, and the first connecting seat is connected to the first end of snakelike connecting piece, and the second connecting seat is connected to the second end. The remote sensing satellite load adapter with the flexible hinge can provide flexibility along the axial direction of the central axis of the cylindrical surface, so that the flexible hinge has unloading capacity in the direction. In addition, the snake-shaped connecting piece can prolong a force transmission path from the first connecting seat of the flexible hinge to the second connecting seat, provide axial displacement unloading capacity, provide radial rigidity and flexibility along a set circumference, provide three-dimensional displacement unloading capacity in a three-dimensional space and further meet the requirement of thermal stress release between a remote sensing satellite and a satellite platform.
Description
Technical Field
The invention relates to the technical field of satellites, in particular to a remote sensing satellite load adapter with a flexible hinge.
Background
The space remote sensing satellite can quickly and accurately observe and discover ground targets, and plays a great role in the military and civil fields. With the continuous improvement of the requirements on the ground width and the resolution of the space remote sensing camera, a long focal length, a large field of view and a large light-passing aperture become necessary trends in the development of the space remote sensing camera, so that the size and the weight of a satellite platform and the space remote sensing camera are increased, the structure light-weight design is required to reduce the weight of the satellite platform and the space remote sensing camera, after the structure light-weight design, although the specific stiffness is increased, the absolute stiffness is reduced, and the sensitivity of an optical element of the camera to stress is also rapidly increased.
In a space environment, the general temperature control range of the satellite deck is 0-25 ℃, and the general temperature control range of the space remote sensing camera is 18-22 ℃, so that the temperature difference exists between the satellite structure and the remote sensing camera. The satellite structure commonly uses the form of aluminium honeycomb panel, carbon fiber bearing section of thick bamboo, and the remote sensing camera structure commonly uses titanium alloy, and different materials lead to the coefficient of linear expansion to mismatch. The difference of temperature and material thermal characteristics causes thermal stress between the satellite structure and the remote sensing camera structure, which is a main factor influencing the imaging quality of the optical system when the satellite works in orbit.
In order to reduce the influence of thermal stress on the imaging quality of an optical system when a satellite is in orbit, a flexible structure is designed on each optical element supporting structure of a remote sensing camera, the adverse effect of the thermal stress on the optical element is released through the deformation of the flexible structure, but the current flexible structure cannot meet the connection requirement between the remote sensing camera and a satellite platform along with the increasing size of the optical element.
Disclosure of Invention
The present invention is directed to solving at least one of the problems of the prior art or the related art.
One of the objects of the invention is: the utility model provides a remote sensing satellite load adapter with flexible hinge, solves the problem that the flexible structure of remote sensing satellite load adapter that exists among the prior art can't satisfy thermal stress release between remote sensing satellite and the satellite platform.
To achieve the object, the present invention provides a remote sensing satellite load adapter with a flexible hinge, comprising:
a support for fixing the remote sensing camera;
the separation mechanism is fixed with the support at a first end and fixed with a satellite platform of the remote sensing satellite at a second end, and is used for unlocking between the support and the satellite platform after the satellite enters the orbit;
the flexible hinge comprises a snake-shaped connecting piece, an elastic connecting piece, a first connecting seat and a second connecting seat;
the plurality of snake-shaped connecting pieces surround a cylindrical surface, the snake-shaped connecting pieces meander along the axial direction of the cylindrical surface, the first ends of the snake-shaped connecting pieces are connected with the first connecting seat, and the second ends of the snake-shaped connecting pieces are connected with the second connecting seat.
In one embodiment, the support member is a support ring, a plurality of first mounting interfaces are uniformly distributed on the support ring, and a plurality of second mounting interfaces are uniformly distributed on the support ring, the first mounting interfaces are used for mounting the separation mechanism, and the second mounting interfaces are used for mounting the flexible hinge.
In one embodiment, the detachment mechanism first end is secured to the first mounting interface by a first fastener, the flexible hinge first end is secured to the second mounting interface by a first fastener, the detachment mechanism second end is secured to the satellite platform by a second fastener, and the flexible hinge second end is secured to the satellite platform by a second fastener.
In one embodiment, the number of the serpentine connectors is multiple, and the serpentine connectors are uniformly distributed along the cylindrical surface.
In one embodiment, the first connecting seat and the second connecting seat are both in a plane plate shape, the first connecting seat and the second connecting seat are parallel, and the elastic connecting piece is perpendicular to the first connecting seat and the second connecting seat.
The technical scheme of the invention has the following advantages: the remote sensing satellite load adapter with the flexible hinge can provide flexibility along the axial direction of the central shaft of the cylindrical surface, so that the flexible hinge has unloading capacity in the direction. In addition, the snake-shaped connecting piece can prolong a force transmission path from the first connecting seat of the flexible hinge to the second connecting seat, provide axial (axial to the central axis of the cylindrical surface) displacement unloading capacity, provide radial rigidity and flexibility along a set circumference, provide three-dimensional displacement unloading capacity in a three-dimensional space, and further meet the requirement of thermal stress release between a remote sensing satellite and a satellite platform.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a perspective view of a flexible hinge according to an embodiment of the present invention;
FIG. 2 is a schematic front view of a flexible hinge according to an embodiment of the present invention;
FIG. 3 is a schematic cross-sectional view taken at A-A in FIG. 2;
FIG. 4 is a schematic top view of a flexible hinge according to an embodiment of the present invention;
FIG. 5 is a schematic bottom view of a flexible hinge according to an embodiment of the present invention;
FIG. 6 is a schematic side view of a telemetry satellite load adapter with a flexible hinge according to an embodiment of the invention;
FIG. 7 is a schematic bottom view of a telemetry satellite load adapter with a flexible hinge according to an embodiment of the invention;
FIG. 8 is a schematic top view of a support in a telemetry satellite load adapter with a flexible hinge according to an embodiment of the invention;
FIG. 9 is a schematic bottom view of a support in a telemetry satellite load adapter having a flexible hinge according to an embodiment of the invention;
FIG. 10 is a schematic side view of a support in a telemetry satellite load adapter having a flexible hinge according to an embodiment of the invention;
in the figure: 1. a support member; 101. a boss; 102. a first mounting interface; 103. a second mounting interface; 104. lightening holes; 105. reinforcing ribs; 2. a flexible hinge; 201. a first connecting seat; 202. a second connecting seat; 204. a serpentine connector; 3. a separating mechanism; 4. a first fastener; 5. a second fastener.
Detailed Description
The embodiments of the present invention will be described in further detail with reference to the drawings and examples. The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention.
In the description of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "connected" and "connected" are to be interpreted broadly, e.g., as being fixed or detachable or integrally connected; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Referring to fig. 1 to 5, the flexible hinge of the embodiment includes a plurality of serpentine connectors 204, a first connector block 201 and a second connector block 202. The plurality of serpentine connectors 204 surround a cylindrical surface, and the serpentine connectors 204 meander along the axial direction of the cylindrical surface; the first connecting seat 201 is connected to the first end of the serpentine connector 204, the second connecting seat 202 is connected to the second end of the serpentine connector 204, and the first connecting seat 201 and the second connecting seat 202 are disposed at two ends of the serpentine connector 204 along the axial direction of the cylindrical surface.
The serpentine connector 204 of the flexible hinge can provide flexibility along the axis of the cylindrical surface, so that the flexible hinge has unloading capability in the direction. In addition, the snake-shaped connecting piece 204 can prolong the force transmission path from the first connecting seat 201 of the flexible hinge to the second connecting seat 202, provide the axial (axial direction of the central axis of the cylindrical surface) displacement unloading capacity, provide the radial rigidity and flexibility along the set circumference, and provide the three-direction displacement unloading capacity in the three-dimensional space, thereby meeting the requirement of thermal stress release between the remote sensing satellite and the satellite platform.
The number of the serpentine connectors 204 may be one, or may be any number, for example, in fig. 1, the number of the serpentine connectors 204 is obviously more than three. It should be noted that the serpentine connectors 204 may be uniformly distributed along the cylindrical surface, or may be approximately uniformly distributed.
The structural forms of the first connecting seat 201 and the second connecting seat 202 are not limited, as long as the flexible hinge and the to-be-connected component can be connected. For example, when a flexible hinge is used for the connection between the telemetric camera and the satellite platform, the first connection socket 201 is connected to the support of the telemetric camera and the second connection socket 202 is connected to the satellite platform. In this case, the first and second connection holders 201 and 202 may each have a plate-shaped structure.
Of course, since the application of the flexible hinge is not limited herein, it can also be applied to other occasions where flexible connection is needed, and the structural forms of the first connecting seat 201 and the second connecting seat 202 are correspondingly changed. For example, the first connecting seat 201 and/or the second connecting seat 202 may also adopt a block structure, a strip structure, and the like.
According to an embodiment of the invention, referring to fig. 6 and 7, a telemetry satellite load adapter with a flexible hinge is provided, comprising a support 1, a decoupling mechanism 3 and a flexible hinge 2. Wherein, the support 1 is used for fixing the remote sensing camera; the first end of the separating mechanism 3 is fixed with the support 1, and the second end is fixed with a satellite platform of the remote sensing satellite and used for unlocking between the support and the satellite platform after the satellite enters the orbit. The first end of the flexible hinge 2 is fixed with the support part 1, the second end is fixed with the satellite platform, and the support part 1 is flexibly connected with the satellite platform. Wherein the flexible hinge 2 is of the above-mentioned type.
Furthermore, the telemetry satellite load adapter with the flexible hinge has the advantages that the snake-shaped connecting piece 204 can provide flexibility along the axial direction of the central axis of the cylindrical surface, so that the flexible hinge has unloading capacity in the direction. In addition, the snake-shaped connecting piece 204 can prolong the force transmission path from the first connecting seat 201 of the flexible hinge to the second connecting seat 202, provide the axial (axial direction of the central axis of the cylindrical surface) displacement unloading capacity, provide the radial rigidity and flexibility along the set circumference, and provide the three-direction displacement unloading capacity in the three-dimensional space, thereby meeting the requirement of thermal stress release between the remote sensing satellite and the satellite platform.
This kind of remote sensing satellite load adapter with flexible hinge connects satellite platform and remote sensing camera through support piece 1, separating mechanism 3 and flexible hinge 2, and separating mechanism 3 can provide higher connection rigidity in the launch process, and the remote sensing satellite moves in the orbit and when the orbit operation, and separating mechanism 3 unblocks, and then connects through flexible hinge 2 between satellite platform and the remote sensing camera, releases the thermal stress between satellite platform and the remote sensing camera. Because the separating mechanism 3 and the flexible hinge 2 are not directly connected with the remote sensing satellite, the installation position of the remote sensing camera can be conveniently adjusted, and the installation precision of the remote sensing camera is ensured.
Wherein, the separation mechanism 3 refers to a mechanism which can realize the unlocking between the support 1 and the satellite platform. Specifically, in the launching process of the remote sensing satellite, the separation mechanism 3 is connected with the support member 1 and the satellite platform; when the remote sensing satellite enters the orbit and operates in the orbit, the separating mechanism 3 is unlocked, and the separating mechanism 3 does not limit the remote sensing camera on the support 1 any more.
In one embodiment, the support 1 is a support ring. Taking a hexagonal support ring as an example, please refer to fig. 8 to 10, a plurality of first mounting interfaces 102 are uniformly distributed on the support ring, and a plurality of second mounting interfaces 103 are uniformly distributed on the support ring, the first mounting interfaces 102 are used for mounting the separation mechanism 3, and the second mounting interfaces 103 are used for mounting the flexible hinge 2. Of course, the support ring may have any other shape than hexagonal, and the support 1 may have other shapes than circular, as long as the installation of the telemetric camera and the distribution of the detaching mechanism 3 and the flexible hinge 2 are satisfied. For example, the supporting member may be in the form of a supporting plate, or the supporting member may be in the form of a supporting block or the like.
In fig. 8 and 9, the support ring is a hexagonal ring, and the number of the first mounting interfaces 102 and the second mounting interfaces 103 is three, respectively, and the support ring is alternately arranged at the corners of the hexagonal ring. Namely, the lower end surface of the support ring has six mounting points, three mounting points which are uniformly distributed in a 120-degree circumference are used as mounting mechanical interfaces of the flexible hinge 2, and the three mounting mechanical interfaces are also called as a second mounting interface 103; the other three mounting points which are uniformly distributed in a 120-degree circumference are used as mechanical mounting interfaces of the separating mechanism 3, and the three mechanical mounting interfaces are also the first mechanical mounting interface. In this case, the number of the first mounting interfaces 102 and the second mounting interfaces 103 is multiple, and the first mounting interfaces and the second mounting interfaces are uniformly distributed along the support ring, so that the stress balance between the support member 1 and the satellite platform can be ensured. In addition, since the first mounting interfaces 102 and the second mounting interfaces 103 are alternately arranged at the corners of the hexagonal ring, the first mounting interfaces 102 and the second mounting interfaces 103 are easy to position, and the problem that the first mounting interfaces 102 and the second mounting interfaces 103 are not easy to deviate in position in the machining process is solved. Moreover, after the separating mechanism 3 at the first mounting interface 102 is unlocked, the remote sensing satellite load adapter with the flexible hinge realizes static support through the three-point flexible hinge 2, and releases thermal stress between the satellite and the remote sensing camera.
Of course, the number and distribution of the first and second mounting interfaces 102 and 103 are not limited by the examples herein. For example, the number of the first mounting interfaces 102 and the second mounting interfaces 103 may be any number, and the distribution of the first mounting interfaces 102 and the second mounting interfaces 103 may be adjusted according to the structure of the satellite platform and the support 1. Also, the first mounting interface 102 and the second mounting interface 103 are not necessarily provided alternately.
In one embodiment, the detachment mechanism 3 is secured at a first end to the first mounting interface 102 by a first fastener 4, and the flexible hinge 2 is secured at a first end to the second mounting interface 103 by a first fastener 4. The second end of the separating mechanism 3 is fixed on the satellite platform through a second fastener 5, and the second end of the flexible hinge 2 is fixed on the satellite platform through the second fastener 5.
In one embodiment, the first fastener 4 and the second fastener 5 are both screws of QJ2582-M5 and titanium alloy gaskets of GB/T848 φ 5. Taking the flexible hinge 2 as an example, the first end of the flexible hinge 2 is fixed to the second mounting interface 103 through the screws of the QJ2582-M5 and the titanium alloy gasket of the GB/T848 Φ 5, and the second end is fixed to the satellite platform through the screws of the QJ2582-M5 and the titanium alloy gasket of the GB/T848 Φ 5. The screw of QJ2582-M5 and the titanium alloy gasket of GB/T848 phi 5 can be subjected to surface black anodizing treatment.
In one embodiment, the middle of each side length of the support ring is provided with a boss 101, the surfaces of all the bosses 101 are coplanar, and the bosses 101 are used for fixing the telemetric camera. For the support ring with the hexagonal shape, six bosses 101 are designed on the upper end face of the support ring to serve as mechanical interfaces connected with the remote sensing camera, the coplanarity of the bosses 101 meets the precision requirement of the remote sensing camera, and the mounting precision of the remote sensing camera is guaranteed. The requirement on the coplanarity of the mounting surface of the remote sensing camera is better than 0.05 mm. As can be seen from fig. 8, six bosses 101 are provided corresponding to the middle of each side length of the hexagonal support ring. Of course, the number and distribution of the bosses 101 are not limited, and they may be adjusted correspondingly to different support ring forms as long as the fixing requirements of the remote sensing camera are met.
As can be seen from fig. 10, the support member 1 is provided with lightening holes 104. And in order to secure the structural rigidity of the stay 1, a reinforcing rib 105 may be provided at the lightening hole 104.
In one embodiment, the material of the support 1 is the same as the material of the housing of the remote sensing camera. For example, when the material of the housing of the remote sensing camera is titanium alloy, the material of the support 1 is also titanium alloy. In this case, the coefficients of linear expansion of the remote sensing camera and the support 1 are matched, and thermal stress between the support 1 and the remote sensing camera can be prevented.
In one embodiment, referring to fig. 6, the flexible hinge 2 is fixed to the support 1 at a first end and fixed to a satellite deck of the satellite platform at a second end. Moreover, the flexible hinge 2 includes a first connecting seat 201 and a second connecting seat 202, the first connecting seat 201 is fixed to the support member 1, the second connecting seat 202 is fixed to the satellite platform, and a serpentine connecting member 204 is disposed between the first connecting seat 201 and the second connecting seat 202. Wherein the serpentine connector 204 ensures the flexibility of the flexible hinge 2 along the longitudinal direction of fig. 1, providing a force transmission path along the axis of the serpentine connector 204, providing axial unloading capability.
Mounting holes are formed on both the first and second connection holders 201 and 202. The mounting holes on the first connecting base 201 are used for matching with the corresponding mounting holes on the supporting member 1 to meet the connection requirement. Similarly, the mounting holes on the second connector holder 202 mate with corresponding mounting holes on the satellite platform to meet the installation requirements. As can be seen from fig. 8 and 9, a plurality of mounting holes are formed in the support 1, regardless of the first mounting interface 102, the second mounting interface 103, or the boss 101.
Besides, the separating mechanism 3 can select mature goods shelf products which meet the requirements of axial rigidity and radial rigidity and can be unlocked reliably. According to the different separation principles, the separation mechanism 3 is divided into an explosive bolt type, a separation nut type and a memory alloy pin pulling type separation mechanism 3. Since the separating mechanism 3 adopts a mature product structure in the prior art, the structural form of the separating mechanism 3 will not be described in detail here.
Further, the flexible hinge 2 and the separating mechanism 3 are mounted on the supporting member 1 in the form of a structure as shown in fig. 6 and 7. It can be seen from fig. 6 that the top of the first connecting seat 201 of the flexible hinge 2 abuts against the bottom of the support ring, and the mounting holes on the first connecting seat 201 and the mounting holes on the second mounting interface 103 correspond, so that when the first fastening member 4 comprises a screw and a gasket, the screw passes through the mounting holes on the first connecting seat 201 and the second mounting interface 103 and is fixed.
During remote sensing satellite assembly, the load adapter and the satellite cabin plate are connected and fixed through the second fastening piece 5, and specifically, the flexible hinge 2 and the separating mechanism 3 are fixedly connected with the satellite cabin plate through the second fastening piece 5. The remote sensing camera is then fitted to the load adapter, in particular fixed to the support 1. In the satellite launching section, the separating mechanism 3 is in a locking state, high connection rigidity is provided for the remote sensing camera, and the remote sensing camera is prevented from being damaged by large overload. After the satellite enters the orbit, the separating mechanism 3 receives the instruction to separate, and three flexible hinges 2 are statically and fixedly supported between the satellite cabin plate and the load adapter. When the rail temperature changes, thermal stress generated by mismatching of the remote sensing satellite and the remote sensing camera in radial and axial thermal deformation is released through deformation of the flexible hinge 2. Through the load adapter, the static support of the remote sensing camera on the remote sensing satellite can be realized, the thermal stress caused by the rail temperature change is effectively released, and the excellent imaging quality of the remote sensing camera is ensured.
The remote sensing satellite load adapter with the flexible hinge can meet the requirements of high connection rigidity of the satellite platform and the remote sensing camera in the satellite launching section, static support of the satellite platform and the remote sensing camera after the satellite is in orbit and effective release of thermal stress, ensures that the in-orbit imaging quality of the high-resolution remote sensing satellite is not influenced by temperature, and has universality for the remote sensing camera with the quality within 300 kg.
The above embodiments are merely illustrative of the present invention and are not to be construed as limiting the invention. Although the present invention has been described in detail with reference to the embodiments, it should be understood by those skilled in the art that various combinations, modifications or equivalents may be made to the technical solution of the present invention without departing from the spirit and scope of the technical solution of the present invention, and the technical solution of the present invention is covered by the claims of the present invention.
Claims (4)
1. A remote sensing satellite load adapter with a flexible hinge, comprising:
a support for fixing the remote sensing camera;
the separation mechanism is fixed with the support at a first end and fixed with a satellite platform of the remote sensing satellite at a second end, and is used for unlocking between the support and the satellite platform after the satellite enters the orbit;
the flexible hinge is connected with the supporting piece and the satellite platform and comprises a snake-shaped connecting piece, an elastic connecting piece, a first connecting seat and a second connecting seat;
the plurality of the snake-shaped connecting pieces enclose a cylindrical surface, the snake-shaped connecting pieces meander along the axial direction of the cylindrical surface, the first ends of the snake-shaped connecting pieces are connected with the first connecting seat, and the second ends of the snake-shaped connecting pieces are connected with the second connecting seat;
the number of the snake-shaped connecting pieces is multiple, and the snake-shaped connecting pieces are uniformly distributed along the cylindrical surface.
2. The remote sensing satellite load adapter with flexible hinge of claim 1, wherein the support is a support ring, a plurality of first mounting interfaces are evenly distributed on the support ring, and a plurality of second mounting interfaces are evenly distributed on the support ring, the first mounting interfaces are used for mounting the detaching mechanism, and the second mounting interfaces are used for mounting the flexible hinge.
3. The remote sensing satellite load adapter with a flexible hinge of claim 2, wherein the decoupling mechanism first end is secured to the first mounting interface by a first fastener, the flexible hinge first end is secured to the second mounting interface by a first fastener, the decoupling mechanism second end is secured to the satellite platform by a second fastener, and the flexible hinge second end is secured to the satellite platform by a second fastener.
4. The remote sensing satellite load adapter with flexible hinge of claim 1, wherein the first and second connection seats are each planar plate-shaped, and the first and second connection seats are parallel, the resilient connector is perpendicular to the first and second connection seats.
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| CN201911246905.6A CN110667889B (en) | 2019-12-09 | 2019-12-09 | Remote sensing satellite load adapter with flexible hinge |
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| CN201911246905.6A CN110667889B (en) | 2019-12-09 | 2019-12-09 | Remote sensing satellite load adapter with flexible hinge |
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| CN110667889B true CN110667889B (en) | 2020-04-07 |
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| JP5862484B2 (en) * | 2012-06-29 | 2016-02-16 | 三菱電機株式会社 | Mirror support structure |
| CN104443436B (en) * | 2014-10-23 | 2017-05-03 | 上海卫星工程研究所 | Micro-vibration parallel connection vibration isolation device for satellite control moment gyro group |
| CN105717607A (en) * | 2016-04-01 | 2016-06-29 | 中国科学院光电研究院 | Four-point flexible supporting device for optical load |
| CN105857642A (en) * | 2016-04-13 | 2016-08-17 | 中国人民解放军国防科学技术大学 | Folding beam structure-based multi-degree of freedom passive vibration isolation device for spacecraft flywheel |
| CN106742083B (en) * | 2016-11-09 | 2019-01-08 | 上海卫星工程研究所 | A kind of free attachment device of face default value unloading based on in-orbit flexible release |
| CN108508570A (en) * | 2018-03-19 | 2018-09-07 | 长光卫星技术有限公司 | Multiaxis flexible supporting device of the aspect than rectangular mirror |
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