CN113665843A - Surround configuration for deep space exploration - Google Patents
Surround configuration for deep space exploration Download PDFInfo
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- CN113665843A CN113665843A CN202111005529.9A CN202111005529A CN113665843A CN 113665843 A CN113665843 A CN 113665843A CN 202111005529 A CN202111005529 A CN 202111005529A CN 113665843 A CN113665843 A CN 113665843A
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- 238000005192 partition Methods 0.000 claims description 9
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- 239000003380 propellant Substances 0.000 abstract description 6
- 230000009286 beneficial effect Effects 0.000 abstract description 5
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 4
- 235000017491 Bambusa tulda Nutrition 0.000 description 4
- 241001330002 Bambuseae Species 0.000 description 4
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 4
- 239000011425 bamboo Substances 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
- 238000005452 bending Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 3
- 230000004044 response Effects 0.000 description 3
- 238000001514 detection method Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 108091092878 Microsatellite Proteins 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 238000003491 array Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
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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
- B64G1/105—Space science
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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
- B64G1/105—Space science
- B64G1/1064—Space science specifically adapted for interplanetary, solar or interstellar exploration
- B64G1/1071—Planetary landers intended for the exploration of the surface of planets, moons or comets
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
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Abstract
The invention provides a circulator structure for deep space exploration, which comprises a central force bearing conical cylinder, a multi-surface cylinder, a load, a storage box, an engine, electronic equipment and an extra-cabin bearing; the load is arranged at the top of the central bearing conical cylinder, the storage box is arranged in the central bearing conical cylinder, the bottom of the storage box extends out of the bottom of the central bearing conical cylinder, and the engine is arranged at the bottom of the central bearing conical cylinder; the multi-face cylinder is arranged on the outer side of the central bearing conical cylinder, and a gap for mounting electronic equipment is formed between the multi-face cylinder and the central bearing conical cylinder; the outboard bearing is arranged on the outer wall of the central bearing conical cylinder or the multi-surface cylinder. Through the cooperation of the central bearing cone cylinder and the multi-face column body, the system dry-weight ratio of the circulator is superior to 25%, the outboard bearing installed outside the multi-face column body is beneficial to meeting the layout requirements of multi-target pointing and multi-state constraint of a deep space exploration task and load equipment thereof, a large amount of propellant is carried, and the requirements of large bearing and light weight are met.
Description
Technical Field
The invention relates to the technical field of deep space surround detector structure configurations, in particular to a surround device configuration for deep space detection.
Background
The mars detection task has long flight time, large demand for brake capture and orbital transfer speed increment, large quantity of propellants, strong engineering and scientific task demand, large quantity and mass of carried engineering and scientific loads, and harsh requirement on dry weight ratio, so that the load-bearing structural form, the layout of a large-capacity storage tank, the installation of large-mass load equipment and the control of the centroid height of the whole device become the key points of the configuration and layout design of the deep space detector.
The prior Chinese patent with publication number CN109484673A discloses a remote sensing microsatellite structure separated by a low-orbit load platform, which comprises a platform metal frame plate type structure, a load support integrated structure, a frame type separating mechanism, a plate type sun wing spreading mechanism and various devices. In the frame plate type structure, the structure is similar to the traditional bottom plate, side plate and top plate type, and all the structural plates adopt the design of thin metal plates, ribs and lightening; the whole structure takes a bottom plate as a design and assembly reference, and a main force transmission path is from the bottom plate to a side plate to a top plate to a load; the load support integrated structure is arranged on the satellite top plate; the top plate can be connected with a bracket, and the bracket can be provided with a part of the sky facing equipment and can also be connected with the solar wing; the solar wing comprises a folding fixed solar wing and a folding unfolded solar wing, and is mainly connected to a satellite side plate and a top plate support through the fixed solar wing.
The prior chinese patent publication No. CN102372092A discloses a configuration of a low-orbit remote sensing satellite, which includes: the solar cell array comprises a bottom plate, a middle plate, a top plate, a plurality of transverse side plates and a plurality of vertical side plates, wherein the bottom plate, the middle plate and the top plate are encircled into a closed space, a central bearing cylinder is arranged in the closed space, corresponding solar cell arrays are arranged on two sides of the closed space, a support rod is connected between the bottom plate and the middle plate, 4 partition plates are arranged between the middle plate and the top plate, and the partition plates are uniformly distributed; the top plate is connected with a payload cabin, and the bottom of the bottom plate is connected with an upper skirt.
The inventor thinks that the satellite configuration and layout scheme in the prior art are difficult to meet the layout requirements of multi-target pointing and multi-state constraint of deep space exploration tasks and load equipment thereof, and are difficult to meet the requirements of large bearing capacity and light weight, and the improvement is needed.
Disclosure of Invention
In view of the deficiencies in the prior art, it is an object of the present invention to provide a surround configuration for deep space exploration.
The invention provides a circulator structure for deep space exploration, which comprises a central force bearing conical cylinder, a multi-surface cylinder, a load, a storage box, an engine, electronic equipment and an outboard bearing; the load is arranged at the top of the central bearing conical cylinder, the storage box is arranged in the central bearing conical cylinder, the bottom of the storage box extends out of the bottom of the central bearing conical cylinder, and the engine is arranged at the bottom of the central bearing conical cylinder; the multi-face cylinder is arranged on the outer side of the central bearing conical cylinder, and a gap for mounting electronic equipment is formed between the multi-face cylinder and the central bearing conical cylinder; the outboard bearing is arranged on the outer wall of the central bearing conical cylinder or the multi-surface cylinder.
Preferably, the multiaspect cylinder includes cylinder roof, cylinder bottom plate and a plurality of cylinder curb plate, the equal fastening installation of cylinder roof and cylinder bottom plate is on a central bearing awl section of thick bamboo, arbitrary the cylinder curb plate is equallyd divide and is connected with cylinder roof and cylinder bottom plate respectively.
Preferably, a partition board is connected between any one of the column side plates and the central bearing conical cylinder, and any one of the partition boards is located at the edge of the column side plate.
Preferably, the included angle between any two adjacent column side plates is an acute angle, a right angle or an obtuse angle.
Preferably, the outboard bearing comprises a low-gain antenna, a sensor and a load single machine, the low-gain antenna and the sensor are both arranged on a column top plate, and one or more load single machines are respectively arranged on any two column side plates which are arranged in the same direction.
Preferably, a cable for supplying power to the electronic equipment is arranged in a gap between the multi-face column body and the central bearing conical cylinder, and the cable is annularly arranged around the central axis of the central bearing conical cylinder.
Preferably, the outboard bearing comprises a high-gain antenna, the high-gain antenna is fixedly mounted on the side wall of the central bearing conical cylinder, and a notch for avoiding the high-gain antenna is formed on the multi-surface cylinder.
Preferably, the outboard bearing further comprises two solar wings, one solar wing is arranged on the outer wall of the multi-surface column body adjacent to the high-gain antenna, and the two solar wings are arranged oppositely.
Preferably, four storage tanks are arranged in the central bearing conical cylinder, and the four storage tanks are arranged in central symmetry with the central axis of the central bearing conical cylinder.
Preferably, four connecting points are arranged between the central force bearing conical cylinder and the load, and the four connecting points are arranged in central symmetry with the central axis of the central force bearing conical cylinder; and a plurality of point type connecting interfaces are uniformly arranged at the bottom of the central bearing conical cylinder.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention realizes that the dry-weight ratio of the system of the surrounding device is superior to 25 percent through the matching of the central bearing conical cylinder and the multi-surface cylinder, and the outboard bearing arranged outside the multi-surface cylinder is beneficial to meeting the layout requirements of multi-target pointing and multi-state constraint of a deep space exploration task and load equipment thereof, and carries a large amount of propellant, thereby meeting the requirements of large bearing and light weight, further being beneficial to improving the speed increment of the task and completing engineering and scientific tasks as much as possible;
2. according to the invention, the load is arranged above the central bearing cone and the four storage tanks extending out of the bottom of the central bearing cone are beneficial to reducing the height of the mass center of the full-tank state surrounding device, so that the bending moment caused by the transverse load is reduced, and the mechanical response of the load equipment in the active section can be effectively controlled;
3. the load single machine is installed through the two column side plates with the included angle being the obtuse angle, so that the multi-target pointing and installation layout constraint of the load single machine can be met, and the requirement of a complex system working mode can be met;
4. the central force bearing conical cylinder is connected with a load through four connecting points and is connected with a carrier rocket end frame through twelve point type connecting interface joints, the structure is simple, and a force transmission path is direct.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of an outboard load bearing arrangement on an outboard column side panel embodying the primary invention in a surround configuration;
FIG. 2 is a schematic diagram of the layout of an external high gain antenna embodying the present invention;
fig. 3 is a plan view of the inner structure of the surround embodying the invention.
Shown in the figure:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, 2 and 3, the circulator configuration for deep space exploration provided by the invention comprises a central bearing cone 1, a multi-surface column body 2, a load 3, a storage tank 4, an engine 5, electronic equipment 6 and an outboard bearing. The load 3 is tightly installed at the top of the central bearing conical cylinder 1, the storage tank 4 is installed in the central bearing conical cylinder 1, the bottom of the storage tank 4 extends out of the bottom of the central bearing conical cylinder 1, and the engine 5 is installed at the bottom of the central bearing conical cylinder 1. The multi-face column body 2 is arranged on the outer side of the central bearing conical cylinder 1, a gap for installing the electronic equipment 6 is formed between the multi-face column body 2 and the central bearing conical cylinder 1, and the outer bearing of the cabin is arranged on the outer wall of the bearing conical cylinder or the multi-face column body 2.
The whole external profile of the circulator is a non-equilateral hexagon, the dry weight ratio of the detector is better than 25% through the matching of the central bearing cone 1 structure and the multi-surface column body 2, the material consumption is less under the condition of the same bearing, the layout is compact, and the quantity and scale of products such as power supply, thermal control and the like can be saved. Therefore, the surrounding device can carry a large amount of propellant, provide task speed increment and complete engineering and scientific tasks as much as possible.
The shape of the central bearing cone cylinder 1 is a hollow cone cylinder, and the small port of the central bearing cone cylinder 1 is positioned at the upper side of the central bearing cone cylinder. Four connecting points 7 are preset on the upper side of the central bearing cone barrel 1, the four connecting points 7 are arranged in a centrosymmetric mode with the central axis of the central bearing cone barrel 1, the load 3 is directly fastened and connected with the central bearing cone barrel 1 through the four connecting points 7, and the load 3 is 1.3 ton of concentrated load 3. Twelve pitch circle joints are uniformly arranged on the bottom wall of the central bearing cone cylinder 1, the diameter of each pitch circle joint is 3124mm, and the surrounding device is connected with the carrier rocket through 12 point type connecting joints positioned at the lower end. The load 3 arranged at the top of the central bearing cone 1 can directly transmit force to the satellite-rocket connecting surface through the surrounding device structure, and the force transmission path is clear and simple.
As shown in fig. 1 and 2, the multi-face cylinder 2 is a hexahedral cylinder, the hexahedral cylinder includes a cylinder top plate 8, a cylinder bottom plate 9 and cylinder side plates 10, the cylinder top plate 8 and the cylinder bottom plate 9 are all fixedly mounted outside the central bearing conical cylinder 1 through flanges, the upper and lower sides of the cylinder side plates 10 are respectively fixedly connected with the cylinder top plate 8 and the cylinder bottom plate 9, and the cylinder side plates 10 are arranged at intervals with the central bearing conical cylinder 1. The storage tanks 4 are used for storing propellants, the capacity of each storage tank 4 is 570L, four storage tanks 4 are arranged inside the central bearing conical cylinder 1, the four storage tanks 4 are connected in parallel and tiled on the column bottom plate 9, and the four storage tanks 4 are arranged in central symmetry with the central axis of the central bearing conical cylinder 1, so that the carrying of 2480kg of propellants can be met.
The bottoms of the four storage boxes 4 extend out of the bottom of the central bearing cone barrel 1 and extend into the end frame of the launch vehicle so as to reduce the height of the integral mass center of the surround, the height of the surround is preferably 1600mm, and the top load 3 is higher than the top plate 2537 mm. The height of the mass center of the whole star is less than 750mm, so that the bending moment caused by the transverse load 3 of the active section can be reduced, and the mechanical response of the load 3 equipment in the active section can be effectively controlled; the centroid height is low, and the dynamic response amplification factor can be effectively inhibited. Therefore, the situation that the equipment on the surrounding device can safely and reliably bear the severe load 3 environment of the active section can be guaranteed.
The engine 5 is arranged at the central position of the bottom of the central bearing conical cylinder 1, the maximum thrust of the engine 5 is 3000N, and the power requirement of the operation of the surrounding device can be met.
As shown in fig. 3, in order to improve the connection stability of the multi-face column 2 and the central bearing cone 1, a partition plate 11 is connected between the column side plate 10 and the central bearing cone 1, one partition plate 11 is installed at both side edge positions of the column side plate 10, and only one partition plate 11 is located at the joint of two adjacent column side plates 10.
As shown in fig. 1, 2 and 3, the outboard bearing includes a high gain antenna 12, two sun wings 13, a low gain antenna 14, a sensor 15 and a load unit 16. The diameter of high gain antenna 12 is 2.5m, and high gain antenna 12 passes through support frame 17 to be installed on the lateral wall of central load cone 1, and cylinder curb plate 10 has five, and five cylinder curb plates 10 are formed with the breach that is used for dodging high gain antenna 12, and high gain antenna 12 and multiaspect cylinder 2 are conformal design, and in limited installation space scope, configured have concurrently and expand locking, two-dimentional directional high gain antenna 12 of function. And the high-gain antenna 12 is folded and pressed on the conical cylinder and the supporting frame 17 in a conventional state and can be unfolded through the motor, so that the embedded design of the large-caliber high-gain antenna 12 is met.
The two solar wings 13 are respectively and tightly mounted on the outer walls of the two oppositely arranged column side plates 10, and one solar wing 13 is adjacent to the high-gain antenna 12. The included angle between any two adjacent cylinder curb plates 10 is acute angle, right angle or obtuse angle, and the preferred contained angle between two adjacent cylinders of this application is the obtuse angle. The plurality of load single machines 17 are respectively arranged on the two column side plates 10 which are adjacently arranged and are adjacently arranged with the two solar wings 13, and the plurality of load single machines 17 respectively realize the multi-target posture pointing requirements on the ground, the sun and the mars. Both the low gain antenna 14 and the sensor 15 are mounted in plurality on the top plate 8 of the cylinder to meet the operational requirements of the surround.
Electronic equipment 6 tiling respectively on the inner wall of cylinder curb plate 10 and cylinder bottom plate 9 installs a plurality ofly, and electronic equipment 6 is the annular around central load awl section of thick bamboo 1 and arranges, still is provided with the cable in the clearance between multiaspect cylinder 2 and the central load awl section of thick bamboo 1, and the cable is the annular around the central axis of central load awl section of thick bamboo 1 and sets up. The cables comprise power supply cables, communication buses and high-frequency cables, and normal work and operation of each electronic device 6 and the extra-cabin bearing can be guaranteed.
Principle of operation
The dry-weight ratio of the whole surround is optimized by adopting the matching of the central bearing conical cylinder 1 and the multi-surface column body 2, and the height of the mass center of the whole surround can be reduced by installing the load 3 at the top of the central bearing conical cylinder 1, installing the load 3 in the central bearing conical cylinder 1 and extending out of the four storage boxes 4 at the bottom of the central bearing conical cylinder 1, so that the bending moment caused by the transverse load 3 is reduced; and a plurality of load single machines 17 arranged on the outer walls of the two adjacent column side plates 10 respectively meet the multi-target posture pointing requirements on the ground, the sun and the mars. The electronic equipment 6 and the cables which are arranged between the central bearing cone 1 and the multi-surface cylinder 2 in a surrounding shape enable the gravity distribution of the surrounding device to be more uniform.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A surround device structure for deep space exploration is characterized by comprising a central bearing conical cylinder (1), a multi-face cylinder (2), a load (3), a storage box (4), an engine (5), electronic equipment (6) and an outboard bearing;
the load (3) is arranged at the top of the central bearing conical cylinder (1), the storage box (4) is arranged in the central bearing conical cylinder (1), the bottom of the storage box (4) extends out of the bottom of the central bearing conical cylinder (1), and the engine (5) is arranged at the bottom of the central bearing conical cylinder (1);
the multi-face cylinder (2) is arranged on the outer side of the central bearing conical cylinder (1), and a gap for mounting electronic equipment (6) is formed between the multi-face cylinder (2) and the central bearing conical cylinder (1);
the outboard bearing is arranged on the outer wall of the central bearing conical cylinder (1) or the multi-surface cylinder (2).
2. A surround configuration for deep space exploration, according to claim 1, characterized in that said multi-faceted column (2) comprises a column top plate (8), a column bottom plate (9) and a plurality of column side plates (10), said column top plate (8) and said column bottom plate (9) being both tightly mounted on the central force bearing cone (1), any of said column side plates (10) being connected with the column top plate (8) and said column bottom plate (9), respectively.
3. The surround structure for deep space exploration according to claim 2, characterized in that a partition (11) is connected between any one of the column side plates (10) and the central bearing cone (1), and any one of the partitions (11) is located at the edge of the column side plate (10).
4. Surround-ing device configuration for deep space exploration, according to claim 2, characterized in that the angle between any two adjacently arranged cylinder side-plates (10) is acute, right or obtuse.
5. Surround-ing unit configuration for deep space exploration, according to claim 2, characterized in that said outboard bearing comprises a low-gain antenna (14), a sensor (15) and a load unit (16), said low-gain antenna (14) and sensor (15) being arranged on the column ceiling (8), said load unit (16) being provided with one or more of any two of the column side panels (10) arranged in phase.
6. A surround configuration for deep space exploration, according to claim 1, characterized in that in the gap between the multi-faceted cylinder (2) and the central messenger cone (1) there are cables for power supply to the electronic equipment (6), said cables being arranged annularly around the central axis of the central messenger cone (1).
7. A surround configuration for deep space exploration according to claim 1, characterized in that said outboard bearing comprises a high gain antenna (12), said high gain antenna (12) being mounted fast on the side wall of the central messenger cone (1), and said multi-faceted cylinder (2) being formed with a notch for avoiding the high gain antenna (12).
8. A surround-device configuration for deep space exploration, according to claim 7, characterized in that said outboard bearing further comprises two sun wings (13), one of said sun wings (13) being arranged on the outer wall of the polyhedral column (2) adjacent to the high gain antenna (12), and two of said sun wings (13) being arranged in opposition.
9. A surround configuration for deep space exploration, according to claim 1, characterized in that said tanks (4) are provided four within the central bearing cone (1) and four of said tanks (4) are arranged centrosymmetrically with respect to the central axis of the central bearing cone (1).
10. The circulator configuration for deep space exploration according to claim 1, wherein four connection points (7) are arranged between the central bearing cone cylinder (1) and the load, and the four connection points (7) are arranged in central symmetry with the central axis of the central bearing cone cylinder (1);
the bottom of the central bearing conical cylinder (1) is uniformly provided with a plurality of point type connecting interfaces.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111005529.9A CN113665843A (en) | 2021-08-30 | 2021-08-30 | Surround configuration for deep space exploration |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111005529.9A CN113665843A (en) | 2021-08-30 | 2021-08-30 | Surround configuration for deep space exploration |
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| CN113665843A true CN113665843A (en) | 2021-11-19 |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1172751A (en) * | 1996-08-05 | 1998-02-11 | 波音公司 | One piece spacecraft frame |
| CN102717901A (en) * | 2012-06-26 | 2012-10-10 | 上海卫星工程研究所 | Multi-machine combination mars probe configuration and forming method thereof |
| CN106428651A (en) * | 2016-11-29 | 2017-02-22 | 上海卫星工程研究所 | Space-based large-diameter multi-constrained extrasolar terrestrial planet detector structure |
| US20170251391A1 (en) * | 2016-02-29 | 2017-08-31 | Qualcomm Incorporated | Methods and apparatus for adaptive measurement configuration selection in a vehicular device |
| CN107792399A (en) * | 2017-09-25 | 2018-03-13 | 上海卫星工程研究所 | Tank test formula satellite platform structure |
| CN110356592A (en) * | 2019-06-28 | 2019-10-22 | 中国空间技术研究院 | It is a kind of based on an arrow double star from series connection radiation pattern full electricity push away satellite platform configuration |
| CN111891388A (en) * | 2020-07-30 | 2020-11-06 | 上海卫星工程研究所 | Compact satellite configuration suitable for multi-band detection load |
| CN112977882A (en) * | 2021-03-12 | 2021-06-18 | 上海卫星工程研究所 | High orbit satellite platform structure with central force bearing cylinder type storage boxes tiled in parallel |
-
2021
- 2021-08-30 CN CN202111005529.9A patent/CN113665843A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1172751A (en) * | 1996-08-05 | 1998-02-11 | 波音公司 | One piece spacecraft frame |
| CN102717901A (en) * | 2012-06-26 | 2012-10-10 | 上海卫星工程研究所 | Multi-machine combination mars probe configuration and forming method thereof |
| US20170251391A1 (en) * | 2016-02-29 | 2017-08-31 | Qualcomm Incorporated | Methods and apparatus for adaptive measurement configuration selection in a vehicular device |
| CN106428651A (en) * | 2016-11-29 | 2017-02-22 | 上海卫星工程研究所 | Space-based large-diameter multi-constrained extrasolar terrestrial planet detector structure |
| CN107792399A (en) * | 2017-09-25 | 2018-03-13 | 上海卫星工程研究所 | Tank test formula satellite platform structure |
| CN110356592A (en) * | 2019-06-28 | 2019-10-22 | 中国空间技术研究院 | It is a kind of based on an arrow double star from series connection radiation pattern full electricity push away satellite platform configuration |
| CN111891388A (en) * | 2020-07-30 | 2020-11-06 | 上海卫星工程研究所 | Compact satellite configuration suitable for multi-band detection load |
| CN112977882A (en) * | 2021-03-12 | 2021-06-18 | 上海卫星工程研究所 | High orbit satellite platform structure with central force bearing cylinder type storage boxes tiled in parallel |
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