CN107757950B - High-orbit optical remote sensing satellite structure - Google Patents
High-orbit optical remote sensing satellite structure Download PDFInfo
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- CN107757950B CN107757950B CN201710829212.4A CN201710829212A CN107757950B CN 107757950 B CN107757950 B CN 107757950B CN 201710829212 A CN201710829212 A CN 201710829212A CN 107757950 B CN107757950 B CN 107757950B
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- fuel tank
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- mounting seat
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- 230000003287 optical effect Effects 0.000 title claims abstract description 15
- 239000002828 fuel tank Substances 0.000 claims abstract description 114
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 23
- 239000001301 oxygen Substances 0.000 claims abstract description 23
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 23
- 238000005192 partition Methods 0.000 claims description 13
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 8
- 230000006978 adaptation Effects 0.000 claims description 7
- 229910052751 metal Inorganic materials 0.000 claims description 4
- 239000002184 metal Substances 0.000 claims description 4
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 230000007613 environmental effect Effects 0.000 abstract description 2
- 238000009434 installation Methods 0.000 description 9
- 230000005540 biological transmission Effects 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 238000004026 adhesive bonding Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Images
Classifications
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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
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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
-
- 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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
Abstract
A high-orbit optical remote sensing satellite structure comprises a bearing cylinder (1), a fuel tank (2), an oxygen tank (3), a satellite platform (8), a solar wing (11), a load adapting structure (14), a camera (15) and the like; the oxygen box (3) is arranged in the bearing cylinder (1); each fuel tank (2) is respectively arranged on two sides of the bearing cylinder (1) through a fuel tank bracket (4) and a fuel tank top pull plate (5) which are positioned at two ends of the fuel tank (2); the bearing cylinder (1), the fuel tank (2), the oxygen tank (3), the fuel tank bracket (4) and the fuel tank top pull plate (5) are arranged in a satellite platform (8); the camera (15) is arranged on the top of the satellite platform (8) through a load adapting structure (14); the solar wings (11) are respectively arranged at two sides of the satellite platform (8). The invention realizes the reduction of the integral mass center of the satellite and the improvement of the environmental conditions of the load mounting surface, and simultaneously meets the mounting requirements of control propulsion equipment such as a fuel tank, an oxygen tank and the like.
Description
Technical Field
The invention belongs to the technical field of spacecraft structure design, and relates to a high-orbit optical remote sensing satellite structure.
Background
The high orbit optical remote sensing satellite can realize the uninterrupted observation of a certain target, and becomes an important direction for the development of the aerospace remote sensors in China along with the improvement of the earth observation system. In order to meet the development requirements in the field of high-orbit remote sensing, on the basis of the existing communication satellite platform, aiming at the remarkable characteristics of high load, high stability, rapid attitude maneuvering capability and the like of a high-orbit remote sensing satellite, a structure, propulsion, control and equal division system is modified to form the high-orbit remote sensing satellite platform which has the functional characteristics of the high-orbit satellite and the remote sensing satellite, and one of the most important design difficulties is the mounting design of a propulsion system (an oxygen box and a fuel tank), the high-stability mounting design of a camera, the mounting design of other equipment and the like.
At present, China is the first country in the world for developing high-orbit optical remote sensing satellites, and therefore platform design is also highly pioneered.
The main load of the existing high-orbit satellite platform is an antenna system, and the main equipment of a satellite control and propulsion system (an oxygen tank and a fuel tank) is arranged in a satellite bearing cylinder, and the height of the bearing cylinder is self-height. The main load of the high-orbit optical remote sensing satellite is an optical load (camera), the load weight ratio is relatively larger, if an existing high-orbit satellite platform is directly used, the overall mass center of the satellite is higher, and the mechanical environment condition of an optical load mounting surface is very severe, so that a novel satellite structure platform needs to be established, good mounting characteristics are provided for the load, and the mounting requirements of a fuel tank, an oxygen tank, a camera and other various devices are met.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the invention overcomes the defects of the prior art, provides a high-orbit optical remote sensing satellite structure, realizes the reduction of the integral mass center of the satellite and the improvement of the environmental conditions of a load mounting surface by designing an external hanging type fuel tank mounting mode, and simultaneously meets the mounting requirements of control propulsion equipment such as a fuel tank, an oxygen tank and the like.
The technical scheme adopted by the invention is as follows: a high-orbit optical remote sensing satellite structure comprises a bearing cylinder, a fuel tank, an oxygen tank, a fuel tank bracket, a fuel tank top pull plate, a satellite platform, a solar wing, a load adapting structure and a camera; the oxygen box is arranged in the bearing cylinder; each fuel tank is respectively arranged on two sides of the bearing cylinder through a fuel tank bracket and a fuel tank top pull plate which are positioned at two ends of the fuel tank; the bearing cylinder, the fuel tank, the oxygen tank, the fuel tank bracket and the fuel tank top pull plate are arranged in the satellite platform; the camera is arranged on the top of the satellite platform through a load adapting structure; the solar wings are respectively arranged at two sides of the satellite platform.
The fuel tank support is of a metal reinforced flat plate structure and made of 2A14T6 and is symmetrically arranged on two sides of the bearing cylinder respectively; one side of the fuel tank bracket is provided with an arc-shaped interface which is connected with the side wall of the bearing cylinder; the middle part of the fuel tank bracket is provided with a fuel tank mounting hole, and one end of the fuel tank is mounted in the fuel tank mounting hole.
The pull plate at the top of the fuel tank is of a flat plate structure, the middle part of the pull plate is provided with a fuel tank connecting interface, and one side of the pull plate is provided with an arc-shaped interface and is connected with the side wall of the bearing cylinder; the pull plates at the top of each fuel tank are respectively and symmetrically arranged at two sides of the bearing cylinder and close to one end port of the bearing cylinder; one end of each fuel tank is connected with the pull plate at the top of the fuel tank through a fuel tank connecting interface.
The satellite platform comprises a partition plate, an outer side plate, a platform top plate, a platform bottom plate and a middle supporting plate; the four partition plates are respectively connected with the fuel tank bracket, the fuel tank top pull plate and the bearing cylinder, are symmetrically arranged at two sides of the bearing cylinder and are symmetrical about the planes of the symmetry axis of the bearing cylinder and the symmetry axis of the fuel tank; the platform top plate and the platform bottom plate are respectively arranged at two ends of the bearing cylinder; two ends of the outer side plate are respectively connected with the platform top plate and the platform bottom plate to form an octahedral structure with the platform top plate and the platform bottom plate; the middle supporting plate is of a cross supporting structure and is arranged between the partition plate and the outer side plate, and the solar wings are fixed on the middle supporting plate and the outer side plate.
The load adaptation structure is arranged in the middle of the platform top plate and is of an annular shell structure, and the camera is arranged on the load adaptation structure.
The load adapting structure comprises a box type local supporting structure, a cylinder shell external integrated mounting seat and a cylinder shell internal integrated mounting seat, wherein the cylinder shell external integrated mounting seat is mounted on the upper surface of an annular platform at the upper part of the load adapting structure and is uniformly distributed along the circumferential direction of the annular platform; the box type local supporting structure, the integrated mounting seat inside the cylinder shell and the integrated mounting seat outside the cylinder shell correspond to each other in mounting position and are mounted on the lower surface of the annular platform on the upper portion of the load adapting structure.
The camera adopts a three-point supporting form and is fixedly connected with the integrated mounting seats outside the cylinder shells, the box type local supporting structure and the integrated mounting seats inside the cylinder shells through screws.
The integrated mounting base outside the cylinder shell is of a flat plate structure, 9 camera connecting holes are distributed in the integrated mounting base, and the integrated mounting base is made of titanium alloy.
The box type local supporting structure is of an angle box structure and is connected with the lower surface of the annular platform on the upper portion of the load adapting structure and the inner wall of the side face of the load adapting structure respectively.
The integrated mounting seat inside the cylinder shell is of a block structure with reinforcing ribs inside, camera connecting holes are distributed in the integrated mounting seat, the integrated mounting seat inside the cylinder shell is located in the integrated mounting seat outside the cylinder shell, and the integrated mounting seat is made of titanium alloy.
Compared with the prior art, the invention has the advantages that:
(1) compared with the existing high-orbit satellite platform, the invention obviously reduces the height of the bearing cylinder through the external hanging configuration design of the fuel tank, the support structure design of the fuel tank, the connection design of the bearing cylinder and the like, thereby realizing the reduction of the integral mass center of the satellite and the improvement and the promotion of the load mechanical environment.
(2) The whole satellite adopts an octahedral configuration, so that the structural size of the satellite is effectively controlled while the installation requirements of a fuel tank, an oxygen tank, a solar wing, a data transmission antenna and other various devices are met, and the carrying envelope requirement is met; the structure form of the whole star octahedron box body meets the requirements of external hanging type installation and carrying envelope of the fuel tank and the installation requirements of solar wings, data transmission antennas and other equipment. Through designing three point support formula high stable load adaptation structure, realize the high stable installation of camera.
(3) Through three point support formula high stable load adaptation structure, can fully adapt to three-point optical camera load adaptation support demand, satisfy rigidity, intensity, stability support requirement simultaneously, realized the high stable installation of camera.
Drawings
FIG. 1 is an outer profile of the invention in the form of a whole star structure;
FIG. 2 is an internal structure of the present invention in the form of a whole star structure;
FIG. 3 shows the installation of the externally-hung fuel tank of the bearing cylinder of the present invention;
FIG. 4 is a top strap of the fuel tank of the present invention;
FIG. 5 is a fuel tank support of the present invention;
FIG. 6 is an outer profile of the high stability load adapting structure of the present invention;
FIG. 7 is the internal structure of the cartridge shell of the high stability load adapting structure of the present invention;
FIG. 8 is a box type partial support structure of the present invention;
FIG. 9 is a view of the cartridge housing external integrated titanium alloy mount of the present invention;
fig. 10 is an internally integrated titanium alloy mount of the cartridge housing of the present invention.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1, 2 and 3, the high-orbit optical remote sensing satellite structure comprises a force bearing cylinder 1, a fuel tank 2, an oxygen tank 3, a fuel tank bracket 4, a fuel tank top pull plate 5, a satellite platform 8, a solar wing 11, a load adapting structure 14 and a camera 15; the oxygen box 3 is arranged in the bearing cylinder 1; each fuel tank 2 is respectively arranged on two sides of the bearing cylinder 1 through a fuel tank bracket 4 and a fuel tank top pull plate 5 which are positioned at two ends of the fuel tank 2; the bearing cylinder 1, the fuel tank 2, the oxygen tank 3, the fuel tank bracket 4 and the fuel tank top pull plate 5 are arranged in a satellite platform 8; the camera 15 is mounted on top of the satellite platform 8 through a load adapting structure 14; the solar wings 11 are respectively installed at both sides of the satellite platform 8.
As shown in fig. 5, the fuel tank support 4 is of a metal reinforced flat plate structure, is made of 2a14T6, and is symmetrically installed on two sides of the bearing cylinder 1 respectively; one side of the fuel tank bracket 4 is an arc-shaped interface which is connected with the side wall of the bearing cylinder 1; the middle part of the fuel tank bracket 4 is provided with a fuel tank mounting hole, and one end of the fuel tank 2 is mounted in the fuel tank mounting hole.
As shown in fig. 4, the fuel tank top pulling plate 5 is a flat plate structure, the middle part is provided with a fuel tank connecting interface 9, and one side is provided with an arc interface and is connected with the side wall of the bearing cylinder 1; the top pull plates 5 of each fuel tank are respectively and symmetrically arranged at two sides of the bearing cylinder 1 and close to one end port of the bearing cylinder 1; one end of each fuel tank 2 is connected with the fuel tank top pulling plate 5 through a fuel tank connecting interface 9.
The satellite platform 8 comprises a partition plate 7, an outer side plate 12, a platform top plate 13, a platform bottom plate 10 and a middle supporting plate 20; the four partition plates 7 are respectively connected with the fuel tank bracket 4, the fuel tank top pull plate 5 and the bearing cylinder 1, are symmetrically arranged at two sides of the bearing cylinder 1 and are symmetrical about the planes passing through the symmetry axis of the bearing cylinder 1 and the symmetry axis of the fuel tank 2; the platform top plate 13 and the platform bottom plate 10 are respectively arranged at two ends of the bearing cylinder 1; the two ends of the outer side plate 12 are respectively connected with the platform top plate 13 and the platform bottom plate 10, and form an octahedral structure with the platform top plate 13 and the platform bottom plate 10; the middle support plate 20 is a cross support structure and is installed between the partition plate 7 and the outer side plate 12, and the solar wing 11 is fixed on the middle support plate 20 and the outer side plate 12.
As shown in fig. 6 and 7, the load adapting structure 14 is mounted in the middle of the platform top plate 13 and is an annular shell structure, and the camera 15 is mounted on the load adapting structure 14. The load adapting structure 14 comprises a box type local supporting structure 16, a cylinder shell external integrated mounting seat 17 and a cylinder shell internal integrated mounting seat 18, wherein the cylinder shell external integrated mounting seat 17 is mounted on the upper surface of an annular platform on the upper part of the load adapting structure 14 and is uniformly distributed along the circumferential direction of the annular platform; the box type local supporting structure 16 and the cylinder shell internal integrated mounting seat 18 correspond to the cylinder shell external integrated mounting seat 17 in mounting positions and are mounted on the lower surface of the annular platform on the upper part of the load adapting structure 14. The camera 15 is fixedly connected with the integrated mounting seat 17 outside the cylinder shell, the box type local supporting structure 16 and the integrated mounting seat 18 inside the cylinder shell through screws in a three-point supporting mode.
As shown in fig. 8-10, the integrated mounting seat 17 outside the cylindrical shell is a flat plate structure, and 9 camera connecting holes are distributed on the mounting seat. The box type local supporting structure 16 is a corner box structure, and is connected with the lower surface of the annular platform on the upper part of the load adapting structure 14 and the inner wall of the side surface of the load adapting structure 14 respectively for supporting. The integrated mounting base 18 inside the cylinder shell is of a block structure with reinforcing ribs inside, camera connecting holes are distributed in the block structure, and the integrated mounting base 18 inside the cylinder shell is located in the integrated mounting base 17 outside the cylinder shell.
The concrete composition is as follows:
1) height of whole star centroid
The height of the satellite bearing cylinder 1 is 1979mm, which is reduced by over 1000mm compared with the conventional high-orbit satellite platform, so that the center of mass height of the whole satellite in a filling state can be controlled at 1200 mm.
2) Fuel tank and oxygen tank mounting method
The satellite propulsion system mainly comprises a fuel tank 2 and an oxygen tank 3, wherein the oxygen tank 3 is arranged in a bearing cylinder 1 and is basically consistent with the installation form of the oxygen tank of the traditional high-orbit satellite platform (the oxygen tank 3 and the fuel tank 2 are both arranged in the bearing cylinder 1).
The fuel tank 2 is divided into two parts which are respectively arranged outside the bearing cylinder 1 and on the east and west sides of the star body, and the fuel tank 2 is arranged on the two sides of the bearing cylinder 1 through a fuel tank bracket 4 and a fuel tank top pull plate 5.
The fuel tank support 4 is designed to be of a metal reinforced structure, bending rigidity of the support is provided through reinforcement height, the whole weight of the support is reduced by 70% compared with that of a solid structure, 2A14T6 is selected as a material, and the support is manufactured in an integral machining mode. The fuel tank bracket 4 provides a connecting interface 6 with the fuel tank and is respectively in threaded connection with the bearing cylinder 1, the partition plate 7 and two outer side plates 12 which form a rectangle with the partition plate 7.
The fuel tank top pulling plate 5 restrains the transverse displacement of the fuel tank and releases the longitudinal displacement so as to improve the transverse supporting rigidity without introducing redundant restraint, and avoids deformation mismatching under severe mechanical environment, thereby causing the damage of a satellite structure or the fuel tank. The fuel tank top pulling plate 5 is provided with a fuel tank connecting interface 9, and is in threaded connection with the central bearing cylinder 1, the partition plate 7 and two outer side plates 12 which form a rectangle with the partition plate 7.
3) Octahedral platform structure form
The satellite platform 8 adopts an octahedral structure, so that the installation requirements of the bearing cylinder externally-hung fuel tank are met, and the space is utilized to provide sufficient installation space for the solar wings 11 and other equipment.
4) High-stability camera mounting mode
The camera 15 is mounted with the satellite platform 8 by means of a load-adapting structure 14. The load adapting structure 14 is provided with an interface for connecting with the camera 15 and the satellite platform 8 respectively. The load adapting structure 14 is a cartridge type structure. The camera 15 is supported at three points to reduce the influence of deformation and vibration of the platform. Therefore, a box type local supporting structure 16, a cylinder shell external integrated mounting seat 17 and a cylinder shell internal integrated mounting seat 18 are designed on the upper end face of the load adapting structure 14 corresponding to the three camera supporting points so as to meet the requirements of high rigidity, high strength and high stable support. The outer integrated mounting seat 17 of the cylinder shell and the inner integrated mounting seat 18 of the cylinder shell are made of titanium alloy.
The box type local supporting structure 16 is constructed by 3mm-5mm composite material mould pressing materials, the local rigidity and the strength are obviously improved through local closing, and meanwhile, the weight cost of integral reinforcement is avoided.
Corresponding to 9 connecting points of each camera mounting seat, a cylinder shell external integrated support 17 and a cylinder shell internal integrated mounting seat 18 are designed on the upper surface and the lower surface of the load adapting structure 14, and the characteristics of low expansion, high strength and high rigidity of the titanium alloy are fully exerted. And by means of combining gluing and screwing, the camera connecting point, the load adapting structure body and the box type local supporting structure form a whole, and the integrated design of the supporting rigidity, the strength and the stability of the camera 15 is realized.
The present invention has not been described in detail, partly as is known to the person skilled in the art.
Claims (6)
1. A high-orbit optical remote sensing satellite structure is characterized by comprising a bearing cylinder (1), a fuel tank (2), an oxygen tank (3), a fuel tank support (4), a fuel tank top pull plate (5), a satellite platform (8), a solar wing (11), a load adapting structure (14) and a camera (15); the oxygen box (3) is arranged in the bearing cylinder (1); the two fuel tanks (2) are respectively arranged on two sides of the bearing cylinder (1) through fuel tank brackets (4) positioned at two ends of the fuel tanks (2) and fuel tank top pull plates (5); the bearing cylinder (1), the fuel tank (2), the oxygen tank (3), the fuel tank bracket (4) and the fuel tank top pull plate (5) are arranged in a satellite platform (8); the camera (15) is arranged on the top of the satellite platform (8) through a load adapting structure (14); the solar wings (11) are respectively arranged at two sides of the satellite platform (8);
the fuel tank top pull plate (5) is of a flat plate structure, the middle part of the fuel tank top pull plate is provided with a fuel tank connecting interface (9), and one side of the fuel tank top pull plate is provided with an arc-shaped interface and is connected with the side wall of the bearing cylinder (1); the two fuel tank top pull plates (5) are respectively and symmetrically arranged at two sides of the bearing cylinder (1) and close to one end port of the bearing cylinder (1); one end of each fuel tank (2) is connected with a fuel tank top pulling plate (5) through a fuel tank connecting interface (9);
the load adapting structure (14) comprises a box type local supporting structure (16), a cylinder shell external integrated mounting seat (17) and a cylinder shell internal integrated mounting seat (18), wherein the cylinder shell external integrated mounting seat (17) is mounted on the upper surface of an annular platform at the upper part of the load adapting structure (14) and is uniformly distributed along the circumferential direction of the annular platform; the box type local supporting structure (16), the integrated mounting seat (18) inside the cylinder shell and the integrated mounting seat (17) outside the cylinder shell are arranged at the corresponding positions and are arranged on the lower surface of the annular platform at the upper part of the load adapting structure (14);
the camera (15) is fixedly connected with the external integrated mounting seat (17), the box type local supporting structure (16) and the internal integrated mounting seat (18) of the cylinder shell respectively through screws in a three-point supporting mode;
the satellite platform (8) comprises a partition plate (7), an outer side plate (12), a platform top plate (13), a platform bottom plate (10) and a middle supporting plate (20); the four partition plates (7) are respectively connected with the fuel tank bracket (4), the fuel tank top pull plate (5) and the bearing cylinder (1), are symmetrically arranged at two sides of the bearing cylinder (1) and are symmetrical about the planes passing through the symmetry axis of the bearing cylinder (1) and the symmetry axis of the fuel tank (2); the platform top plate (13) and the platform bottom plate (10) are respectively arranged at two ends of the bearing cylinder (1); two ends of the outer side plate (12) are respectively connected with the platform top plate (13) and the platform bottom plate (10) to form an octahedral structure with the platform top plate (13) and the platform bottom plate (10); the middle supporting plate (20) is of a cross supporting structure and is arranged between the partition plate (7) and the outer side plate (12), and the solar wing (11) is fixed on the middle supporting plate (20) and the outer side plate (12).
2. The structure of claim 1, wherein the structure comprises: the fuel tank support (4) is of a metal reinforced flat plate structure and made of 2A14T6 and is symmetrically arranged on two sides of the bearing cylinder (1) respectively; one side of the fuel tank bracket (4) is provided with an arc-shaped interface which is connected with the side wall of the bearing cylinder (1); the middle part of the fuel tank bracket (4) is provided with a fuel tank mounting hole, and one end of the fuel tank (2) is arranged in the fuel tank mounting hole.
3. The structure of claim 2, wherein the structure comprises: the load adaptation structure (14) is arranged in the middle of the platform top plate (13) and is of an annular shell structure, and the camera (15) is arranged on the load adaptation structure (14).
4. The structure of claim 3, wherein the structure comprises: the integrated mounting seat (17) outside the cylinder shell is of a flat plate structure, 9 camera connecting holes are distributed in the integrated mounting seat, and the integrated mounting seat is made of titanium alloy.
5. The structure of claim 4, wherein the structure comprises: the box type local supporting structure (16) is of a corner box structure and is respectively connected with the lower surface of the upper annular platform of the load adapting structure (14) and the inner wall of the side surface of the load adapting structure (14).
6. An optical remote sensing satellite structure of high orbit according to claim 4 or 5, characterized in that: the barrel shell internal integrated mounting seat (18) is of a block structure with reinforcing ribs inside, camera connecting holes are distributed in the block structure, the barrel shell internal integrated mounting seat (18) is located in the barrel shell external integrated mounting seat (17), and the barrel shell internal integrated mounting seat is made of titanium alloy.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710829212.4A CN107757950B (en) | 2017-09-14 | 2017-09-14 | High-orbit optical remote sensing satellite structure |
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| CN201710829212.4A CN107757950B (en) | 2017-09-14 | 2017-09-14 | High-orbit optical remote sensing satellite structure |
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| CN109484673B (en) * | 2018-12-24 | 2022-04-22 | 深圳航天东方红海特卫星有限公司 | Load platform separated remote sensing micro satellite configuration and assembly method thereof |
| CN109823576B (en) * | 2019-02-20 | 2020-11-24 | 上海卫星工程研究所 | Bearing connection structure for planetary lander |
| CN110450981A (en) * | 2019-08-14 | 2019-11-15 | 上海卫星工程研究所 | Deployable separate type satellite platform and its assembly application method |
| CN111059206A (en) * | 2019-12-28 | 2020-04-24 | 中国科学院沈阳自动化研究所 | Piezoelectric active vibration damper of flexible solar wing supporting structure |
| CN111891386B (en) * | 2020-06-30 | 2022-04-08 | 北京空间飞行器总体设计部 | Three-dimensional modular structure for supporting multiple loads |
| CN112373727A (en) * | 2020-11-24 | 2021-02-19 | 中国空间技术研究院 | Separable satellite propulsion system configuration |
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| CN102372092A (en) * | 2010-08-17 | 2012-03-14 | 上海卫星工程研究所 | Configuration for low-earth-orbit remote sensing satellite and mounting method thereof |
| CN104058102B (en) * | 2014-06-26 | 2016-07-27 | 上海卫星工程研究所 | Eight bar interconnection system noncontact satellite platform configuration and assembly methods |
| EP3095714A1 (en) * | 2015-05-19 | 2016-11-23 | Airbus DS GmbH | Modular satellite |
| CN106218920A (en) * | 2016-06-30 | 2016-12-14 | 中国空间技术研究院 | Satellite Vibration isolating device and method |
| CN106516167B (en) * | 2016-11-03 | 2019-05-03 | 上海卫星工程研究所 | The high-precision repropellenting method of high rail parallel connection tiling tank satellite |
| CN106742063A (en) * | 2016-11-30 | 2017-05-31 | 上海卫星工程研究所 | Internal satellite configuration |
| CN106379561B (en) * | 2016-12-07 | 2019-05-28 | 上海宇航系统工程研究所 | A kind of storage of space-oriented fuel can in-orbit extension spacecraft |
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