CN106428651A - Space-based large-diameter multi-constrained extrasolar terrestrial planet detector structure - Google Patents
Space-based large-diameter multi-constrained extrasolar terrestrial planet detector structure Download PDFInfo
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- CN106428651A CN106428651A CN201611074527.4A CN201611074527A CN106428651A CN 106428651 A CN106428651 A CN 106428651A CN 201611074527 A CN201611074527 A CN 201611074527A CN 106428651 A CN106428651 A CN 106428651A
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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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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Abstract
The invention provides a space-based large-diameter multi-constrained extrasolar terrestrial planet detector structure. The structure comprises a platform service module, a platform propelling module, a payload, a star sensor and a platform bottom plate; the back light path part of the payload is embedded into the platform service module, the star sensor is installed on a high-rigidity back plate of the payload, therefore, the attitude measuring error is decreased, and the attitude control precision of a whole detector is improved; intra-detector subsystem single units of the detector are arranged on the obverse side of the platform bottom plate, and thrusters and air cylinders are arranged on the reverse side of the platform bottom plate. According to the space-based large-diameter multi-constrained extrasolar terrestrial planet detector structure, by means of integrated design of a load platform, the mass center of the whole detector can be lowered, and the enveloping limiting requirement of a launch vehicle fairing can be met; meanwhile, attitude sensitive devices such as the star sensor are arranged on the high-rigidity back plate of the payload, therefore, the attitude measuring error can be decreased, and the attitude control precision of the whole detector can be improved. The structure can be effectively applied to layout design of a similar detector structure with a large-diameter multi-constrained space camera.
Description
Technical field
The present invention relates to outside a kind of space-based heavy caliber multiple constraint system Terrestrial Planet Finder configuration, be the overall of detector
Design provides configuration layouts schemes, simultaneously this configuration layouts' scheme can be applicable to similar with heavy caliber multiple constraint space camera
Detector design in.
Background technology
Be outer terrestrial planet as typical detection object, carry the livable celestial body of discovery and be the significance of outer life,
It is focus and the emphasis of current research.Develop fine spectral measurement methodses, launch large space camera, research is that outer planet is big
Gas, meticulous depiction system outer planet physics and chemical characteristic, are the important directions that future space detects.
However, large space camera is many due to the big constraint of bore, it is that the overall configuration design of detector brings difficulty.According to
Analysis, detects for realizing the outer terrestrial planet of system, camera bore need to reach 3m, height 3.3m, rear light path height 1.7m, if adopted
Traditional detector platform configuration layouts detached with payload design pattern, and detector entirety envelope will be led to exceed delivery
Rocket trouserss limit, and whole device barycenter is too high.
Content of the invention
It is an object of the invention to provide outside a kind of space-based heavy caliber multiple constraint system Terrestrial Planet Finder configuration, for detect
The master-plan of device provides configuration layouts' scheme, and using payload platform integrated design, after load, light path embeds platform interior, with
When, the attitude sensor part such as star sensor being arranged at the high rigidity backboard of load, reducing attitude measurement error, thus improving
The attitude control accuracy of whole device.
The configuration of Terrestrial Planet Finder outside a kind of space-based heavy caliber multiple constraint system, including platform service cabin, platform propulsion
Cabin, payload, star sensor and platform floor, the rear light path part of payload embeds inside platform service cabin, thus real
Existing payload platform integrated design, reduces whole device envelope, reduces whole device height；Star sensor is installed on the high rigidity of payload
At backboard, thus reducing attitude measurement error, improve the attitude control accuracy of whole device；Each point of detector is arranged in platform floor front
Unit in system device, the back side is disposed with thruster and gas cylinder, and wherein gas cylinder is 4.
Preferably, platform propelling module is made up of satellite and the rocket connection ring, tank installing plate, tank and precise tracking, works as detection
When device is docked with carrier rocket, tank and precise tracking are partially submerged into inside carrier rocket Butt Section, thus reducing further
Whole device barycenter.
Preferably, described payload is space camera, and body bore reaches 3m, height 3.3m, rear light path height 1.7m,
Using payload platform integrated design.
Preferably, a diameter of 2800mm of satellite and the rocket connection ring, using 4 606L tanks, each tank diameter is about 1050mm.
Compared with prior art, the present invention has following beneficial effect：By payload platform integrated design, can be effective
Reduce whole device barycenter, meet fairing of launch vehicle envelope and limit, the attitude sensor part such as star sensor is arranged in load simultaneously
At the high rigidity backboard of lotus, attitude measurement error can be reduced, improve the attitude control accuracy of whole device.The present invention can be effectively used for class
As with heavy caliber multiple constraint space camera detector configuration layouts design in.
Brief description
The detailed description with reference to the following drawings, non-limiting example made by reading, the further feature of the present invention,
Objects and advantages will become more apparent upon：
Fig. 1 is detector overall configuration figure proposed by the present invention.
Fig. 2 is detector overall configuration exploded view proposed by the present invention.
Specific embodiment
With reference to specific embodiment, the present invention is described in detail.Following case study on implementation will be helpful to the skill of this area
Art personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the common skill to this area
For art personnel, without departing from the inventive concept of the premise, some deformation can also be made and improve.These broadly fall into this
Bright protection domain.
As shown in Figure 1 to Figure 2, embodiments provide terrestrial planet outside a kind of space-based heavy caliber multiple constraint system to detect
The configuration of device is it is characterised in that include platform service cabin 1, platform propelling module 2, payload 3, star sensor 4 and platform floor
5, the rear light path part of payload 3 embeds inside platform service cabin 1, thus realizing payload platform integrated design, reduces whole
Device envelope, reduces whole device height；Star sensor 4 is installed at the high rigidity backboard of payload 3, thus reducing attitude measurement by mistake
Difference, improves the attitude control accuracy of whole device；Unit 6 in the arrangement detector each subsystem device of platform floor 5 front, the back side is disposed with
Thruster 7 and gas cylinder 8.
Platform propelling module 2 is made up of satellite and the rocket connection ring 9, tank installing plate 10, tank 11 and precise tracking 12, works as detection
When device is docked with carrier rocket, tank 11 and precise tracking 12 are partially submerged into inside carrier rocket Butt Section, thus further
Reduce whole device barycenter
Described payload is space camera, and body bore reaches 3m, height 3.3m, and rear light path height 1.7m, using load
Lotus platform integrated design.
The a diameter of 2800mm of satellite and the rocket connection ring, using 4 606L tanks, each tank diameter is about 1050mm.
Above the specific embodiment of the present invention is described.The invention is not limited in above-mentioned particular implementation,
Those skilled in the art can make various modifications or modification within the scope of the claims, and this has no effect on the essence of the present invention
Content.
Claims (4)
1. outside a kind of space-based heavy caliber multiple constraint system Terrestrial Planet Finder configuration it is characterised in that include platform service cabin,
Platform propelling module, payload, star sensor and platform floor, the rear light path part of payload embeds in platform service cabin
Portion, star sensor is installed at the high rigidity backboard of payload, single in the arrangement detector each subsystem device of platform floor front
Machine, the back side is disposed with thruster and gas cylinder.
2. outside a kind of space-based heavy caliber multiple constraint system according to claim 1, the configuration of Terrestrial Planet Finder designs, its
It is characterised by, platform propelling module is made up of satellite and the rocket connection ring, tank installing plate, tank and precise tracking, when detector and fortune
When carrying rocket docking, tank and precise tracking are partially submerged into inside carrier rocket Butt Section.
3. outside a kind of space-based heavy caliber multiple constraint system according to claim 1, the configuration of Terrestrial Planet Finder designs, its
It is characterised by, described payload is space camera, body bore reaches 3m, height 3.3m, and rear light path height 1.7m, using load
Lotus platform integrated design.
4. outside a kind of space-based heavy caliber multiple constraint system according to claim 2, the configuration of Terrestrial Planet Finder designs, its
It is characterised by, a diameter of 2800mm of satellite and the rocket connection ring, using 4 606L tanks, each tank diameter is about 1050mm.
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| CN201611074527.4A CN106428651A (en) | 2016-11-29 | 2016-11-29 | Space-based large-diameter multi-constrained extrasolar terrestrial planet detector structure |
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| CN201611074527.4A CN106428651A (en) | 2016-11-29 | 2016-11-29 | Space-based large-diameter multi-constrained extrasolar terrestrial planet detector structure |
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Cited By (8)
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| CN107140233A (en) * | 2017-04-07 | 2017-09-08 | 中国人民解放军国防科学技术大学 | Ground simulation satellite and the rocket integrated multi-functional structural aircraft |
| CN107819196A (en) * | 2017-09-25 | 2018-03-20 | 上海卫星工程研究所 | The three-dimensional number over the ground that points to performance constraints passes antenna arrangement system |
| CN108759868A (en) * | 2018-06-20 | 2018-11-06 | 上海卫星工程研究所 | The antenna of the quick integral type mounting structure of satellite load star is directed toward thermal deformation measurement method |
| CN111891393A (en) * | 2020-08-11 | 2020-11-06 | 中国科学院微小卫星创新研究院 | Hybrid propulsion cabin of small high-orbit satellite common platform |
| CN112208801A (en) * | 2020-10-22 | 2021-01-12 | 上海卫星工程研究所 | Mars detector double-component multi-gear thruster configuration and layout method and system |
| CN112550761A (en) * | 2020-12-21 | 2021-03-26 | 中国人民解放军国防科技大学 | Integrated truss type minisatellite main bearing structure and design optimization method |
| CN113665843A (en) * | 2021-08-30 | 2021-11-19 | 上海卫星工程研究所 | Surround configuration for deep space exploration |
| CN116781168A (en) * | 2023-06-14 | 2023-09-19 | 蓝星光域(上海)航天科技有限公司 | Integrated laser communication terminal |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107140233A (en) * | 2017-04-07 | 2017-09-08 | 中国人民解放军国防科学技术大学 | Ground simulation satellite and the rocket integrated multi-functional structural aircraft |
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| CN112550761A (en) * | 2020-12-21 | 2021-03-26 | 中国人民解放军国防科技大学 | Integrated truss type minisatellite main bearing structure and design optimization method |
| CN113665843A (en) * | 2021-08-30 | 2021-11-19 | 上海卫星工程研究所 | Surround configuration for deep space exploration |
| CN116781168A (en) * | 2023-06-14 | 2023-09-19 | 蓝星光域(上海)航天科技有限公司 | Integrated laser communication terminal |
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