CN104648693A - Satellite structure for platform and load integration - Google Patents
Satellite structure for platform and load integration Download PDFInfo
- Publication number
- CN104648693A CN104648693A CN201410809601.7A CN201410809601A CN104648693A CN 104648693 A CN104648693 A CN 104648693A CN 201410809601 A CN201410809601 A CN 201410809601A CN 104648693 A CN104648693 A CN 104648693A
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- satellite
- bearing cylinder
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- upper plate
- platform
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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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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
- Buildings Adapted To Withstand Abnormal External Influences (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a satellite structure for platform and load integration, which relates to the technical field of aerospace and solves the problems of large system mass, large size and the like caused by low resource utilization rate and high structure redundancy of an existing satellite structure system adopting a method that a platform and a load are separately designed. The satellite structure comprises an upper plate, a center bearing cylinder, side plates, a docking ring and a bottom plate, wherein the docking ring is used as an assembling reference, the bottom plate is installed on the docking ring, the center bearing cylinder is installed on the bottom plate, the upper plate is installed on the center bearing cylinder, the side plates are fixed on the side surfaces of the upper plate and the bottom plate, a plurality of upper plate brackets are uniformly arranged in the circumferential direction of the center bearing cylinder, and the upper plate is installed on the center bearing cylinder through the plurality of upper plate brackets. The satellite structure has the advantages of compactness, small size, light weight, high structure function density, high rigidity, large structure safety margin and high reliability.
Description
Technical field
The present invention relates to space flight and aviation technical field.Be specifically related to a kind of structure for platform load integration satellite, the integrated highly integrated of High Performance small satellite platform and load structure can be realized, take into account different model small satellite modularization and standard functions expands mission requirements simultaneously.
Background technology
Satellite is generally made up of capacity weight and satellite platform (or claiming common module).The general satellite platform of the many employings of traditional design of satellites meets different satellite missions from the mode that different capacity weight combines.So-called satellite platform is exactly one can adapt to the configuration of different capacity weight, completes respective particular flight mission, the common module that commonality is stronger.Based on this design concept, in satellite manufacturing process, be mostly to adopt the method for designing of black box, first produce each independently working cell on star, then, be assembled in connection structure by these unit and form satellite, these separate units have oneself supporting structure and maneuvering and control circuit, and parts and control circuit cannot share, finally, make satellite structure overlapping, balancing boom number of devices increases, and causes the increase of satellite weight.Wayside equipment does like this and still has not big harm, but then greatly improves launch cost to satellite, reduces fiduciary level.
More typical example is as famous U.S. MMS satellite platform, as shown in Figure 1, whole satellite platform is made up of four sections of cabins, attitude control subsystem cabin 11, powerhouse dome 14, communication and number pipe cabin 13 and propulsion module 14 respectively, there are oneself supporting structure and maneuvering and control circuit in each cabin, and these cabins are manufactured separately, are then connected together by MMS supporting construction 16, MMS supporting construction plays and connects and the effect of transmitted load, so just constitutes a complete satellite platform.Capacity weight and satellite platform are connected by adapter 15, and they are completely independently two systems, and design although it is so can make platform adapt to different load, but also increases the enveloping space of satellite undoubtedly.
Since the mid-80, the development of the Modern Small Satellites based on hightech is very rapid, and drives satellite to develop to miniaturization.Small satellite have lightweight, volume is little, cost is low, the lead time is short, the large advantage of functional density high five, the satellite of this employing satellite platform and payload module design, although the use of satellite platform can avoid the development again of support system needed for different satellite, but its specific aim is poor, its load and service system subdivision design, the enveloping space and quality are all comparatively large, are not suitable for small satellite miniaturization, weight-saving design philosophy.
The present invention proposes the thought of a kind of satellite platform structure and the structure-integrated design of load, load structure and platform structure are bound organically in one by it, it is the load-carrying construction of capacity weight, also be satellite platform inalienable part simultaneously, same structure carries on a shoulder pole any two roles, improve the functional density collection of satellite structure, alleviate satellite quality, reduced volume, reduce costs.
Adopt honeycomb interlayer board-like structure, pre-buried heat pipe in plate, accomplish machine-heating integrated, simplicity of design is convenient, improves the functional density of satellite.Finite element result shows, the version that the present invention proposes, and can meet the related structure performance requriements of satellite, the reference configuration form can developed as following related satellite.
Summary of the invention
The present invention solves the method that existing satellite structure system adopts platform and load independent design, has that resource utilization is low and structural redundancy is high, causes the problems such as mass of system weight volume is large, provides a kind of satellite structure for platform load integration.
For the satellite structure of platform load integration, comprise upper plate, Bearing cylinder, side plate, butt joint ring, base plate; Using butt joint ring as reference for assembling, mounting base on described butt joint ring, mounting center loaded cylinder on described base plate, described upper plate is arranged on Bearing cylinder, and side plate is fixed on the side of upper plate and base plate.
The circumference of described Bearing cylinder is evenly arranged multiple upper board mount, upper plate passes through multiple upper plate support installing on Bearing cylinder.
The present invention includes multiple side plate, the both sides of each side plate are provided with bar, by described bar, side plate are connected with heart loaded cylinder.
The present invention also comprises three shaft bars, side plate is three, the both sides of each side plate are provided with three bars, described three shaft bars are evenly arranged in the circumference of Bearing cylinder, the first two bar of the adjacent side in described every adjacent side plates is fixed on same shaft bar, and the 3rd bar of the adjacent side in every adjacent side plates is connected with base plate.
Base plate of the present invention and upper plate all adopt honeycomb sandwich construction.
Beneficial effect of the present invention: the present invention is directed to platform load integration satellite structure and change traditional method of designing on Topology Structure Design, do not adopt the design of conventional satellite structure subdivision section, each subsystem is arranged in different satellite capsules, all satellite capsules are combined formation satellite completed again, but surmount boundary between each subsystem, adopt resource sharing thought, platform and load structure are integrally considered, designs a kind of multifunction structure for platform load integration satellite.
The present invention, in order to solve existing employing resource sharing theory, proposes a kind of satellite structure for platform load integration, and this structure possesses following characteristics: compact conformation, volume are little, quality is light; Structure function density collection is high; Rigidity is high, and structural safety nargin is large, and reliability is high.
Accompanying drawing explanation
Fig. 1 is the decomposing schematic representation of the structure for platform load integration satellite of the present invention;
Fig. 2 is the combination schematic diagram of the structure for platform load integration satellite of the present invention;
Fig. 3 is existing U.S. MMS satellite platform STRUCTURE DECOMPOSITION schematic diagram.
Detailed description of the invention
Detailed description of the invention one, composition graphs 1 and Fig. 2 illustrate present embodiment, and for the satellite structure of platform load integration, this structure is made up of upper plate 1, Bearing cylinder 2, side plate 3, butt joint ring 7, base plate 8, three shaft bars 9 and 12 upper board mounts 10.
Using butt joint ring 7 as reference for assembling, butt joint ring 7 adopts standard satellite and the rocket interface, forms by aluminum profile extrusion; Mounting base 8 on butt joint ring 7, base plate 8 adopts honeycomb sandwich construction, and the advantage of honeycomb sandwich construction is that quality is light, stiffness-to-density ratio is high; Mounting center loaded cylinder 2 on base plate 8, Bearing cylinder 2 adopts carbon fiber composite material, and they are the main force support structure of satellite, plays again the effect of the assorted flash of light that disappears in the camera; Board mount and three shaft bars on the circumference of Bearing cylinder 2 installs 12; 12 board mount 10 installs upper plate 1, and upper plate 1 adopts honeycomb sandwich construction equally; Install three blocks of side plates, side plate 3 is fixed by screws in the side of base plate 8 and upper plate 1; By the bar 1 of every block side plate 3 both sides, bar 2 and bar 3, three blocks of side plates are connected with Bearing cylinder 2, play the effect of supplemental support.Base plate 8, upper plate 1 and three blocks of side plates 3 are for installing on-board equipment.
The both sides of each side plate 3 described in present embodiment are provided with three bars, described three shaft bars 9 are evenly arranged in the circumference of Bearing cylinder 2, the first two bar of the adjacent side in described every adjacent side plates 3 is fixed on same shaft bar 9, and the 3rd bar of the adjacent side in every adjacent side plates 3 is connected with base plate 8.
The satellite structure concrete function for platform load integration described in present embodiment comprises: bearing load, bear the load that satellite produces in terrestrial operation and transportation, bear acceleration/accel that satellite produces in emission process, vibration, impact and acoustic loads, bear the impact load that satellization authority action produces, due to the load of temperature alternating, vacuum state and change rail motion generation when bearing as being accustomed in orbit; Erecting equipment, satellite structure needs provide fixed installation interface for spaceborne instrument and equipment and keep certain precision, and the installation of satellite thermal control parts also needs to be implemented by structure, and satellite structure reply satellite borne equipment provides protection; There is provided configuration, the skeleton of satellite structure formula satellite, for whole star provides structure profile, for the connection of satellite and carrier rocket provides interface, the connection of stretching annex for satellite provides interface; Disappear parasitic light, and shield portions gas light and other veiling glare enter window glass and camera lens, utilize surface material characteristic, absorb the parasitic light entering shade to greatest extent, ensure higher signal to noise ratio.
To sum up, spaceborne integrated satellite structure had both played satellite structure platform bearing load, erecting equipment and provided the effect of configuration, played again camera structure shade and to disappear the effect of parasitic light.
Claims (5)
1., for the satellite structure of platform load integration, comprise upper plate (1), Bearing cylinder (2), side plate (3), butt joint ring (7), base plate (8); It is characterized in that, using butt joint ring (7) as reference for assembling, at the upper mounting base (8) of described butt joint ring (7), at the upper mounting center loaded cylinder (2) of described base plate (8), described upper plate (1) is arranged on Bearing cylinder (2), and side plate (3) is fixed on the side of upper plate (1) and base plate (8).
2. the satellite structure for platform load integration according to claim 1, it is characterized in that, the circumference of Bearing cylinder (2) is evenly arranged multiple upper board mount (10), upper plate (1) is arranged on Bearing cylinder (2) by multiple upper board mount (10).
3. the satellite structure for platform load integration according to claim 1 and 2, it is characterized in that, side plate (3) is for multiple, and the both sides of each side plate (3) are provided with bar, by described bar, side plate (3) is connected with heart loaded cylinder (2).
4. the satellite structure for platform load integration according to claim 3, it is characterized in that, also comprise three shaft bars (9), side plate (3) is three, the both sides of each side plate (3) are provided with three bars, described three shaft bars (9) are evenly arranged in the circumference of Bearing cylinder (2), the first two bar of the adjacent side on described every adjacent side plates (3) is fixed on same shaft bar (9), and the 3rd bar of the adjacent side in every adjacent side plates (3) is connected with base plate (8).
5. the satellite structure for platform load integration according to claim 1, is characterized in that, described base plate (8) and upper plate (1) all adopt honeycomb sandwich construction.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410809601.7A CN104648693B (en) | 2014-12-23 | 2014-12-23 | Satellite structure for platform and load integration |
| PCT/CN2014/001170 WO2016101086A1 (en) | 2014-12-23 | 2014-12-25 | Satellite structure for platform and load integration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410809601.7A CN104648693B (en) | 2014-12-23 | 2014-12-23 | Satellite structure for platform and load integration |
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| Publication Number | Publication Date |
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| CN104648693A true CN104648693A (en) | 2015-05-27 |
| CN104648693B CN104648693B (en) | 2017-01-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410809601.7A Expired - Fee Related CN104648693B (en) | 2014-12-23 | 2014-12-23 | Satellite structure for platform and load integration |
Country Status (2)
| Country | Link |
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| CN (1) | CN104648693B (en) |
| WO (1) | WO2016101086A1 (en) |
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| CN105235916A (en) * | 2015-10-27 | 2016-01-13 | 上海微小卫星工程中心 | Integration satellite compact in layout |
| CN105527685A (en) * | 2016-01-28 | 2016-04-27 | 长光卫星技术有限公司 | Main bearing member for optical minimal satellite and common structure of optical camera |
| WO2016101086A1 (en) * | 2014-12-23 | 2016-06-30 | 中国科学院长春光学精密机械与物理研究所 | Satellite structure for platform and load integration |
| CN106253967A (en) * | 2016-07-28 | 2016-12-21 | 航天东方红卫星有限公司 | It is applicable to the data maintaining method of microsatellite platform and load information integrated design |
| 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 |
| WO2017055750A1 (en) * | 2015-10-02 | 2017-04-06 | Airbus Defence And Space Sas | Satellite comprising an optical photography instrument |
| CN106742064A (en) * | 2016-11-30 | 2017-05-31 | 上海卫星工程研究所 | One kind is without the open integrative detection device configuration of deck board |
| CN106742063A (en) * | 2016-11-30 | 2017-05-31 | 上海卫星工程研究所 | Internal satellite configuration |
| CN106843248A (en) * | 2017-01-24 | 2017-06-13 | 上海航天控制技术研究所 | Unit installation deviation is estimated and modification method after a kind of satellite launch is entered the orbit |
| CN107065395A (en) * | 2017-05-24 | 2017-08-18 | 北京空间机电研究所 | A kind of shading cover structure for geostationary orbit remote sensing camera |
| CN107380483A (en) * | 2017-07-05 | 2017-11-24 | 上海宇航系统工程研究所 | A kind of spacecraft configuation |
| CN107458629A (en) * | 2017-07-05 | 2017-12-12 | 上海宇航系统工程研究所 | A kind of configuration of spacecraft load cabin |
| CN107505799A (en) * | 2017-09-18 | 2017-12-22 | 北京空间飞行器总体设计部 | A kind of load support structure for concentrating point type stress |
| CN107967393A (en) * | 2017-12-07 | 2018-04-27 | 上海宇航系统工程研究所 | A kind of spacecraft bitubular parallel-connection structure based under multi-constraint condition carries design method |
| CN108860659A (en) * | 2018-05-31 | 2018-11-23 | 北京空间飞行器总体设计部 | A kind of integrated satellite based on deployable plate phased array antenna |
| CN109795717A (en) * | 2019-03-05 | 2019-05-24 | 四川星空年代网络通信有限公司 | A kind of satellite for having automatic energy storage and utilizing |
| CN112061425A (en) * | 2020-09-08 | 2020-12-11 | 上海航天控制技术研究所 | Method for avoiding interference of earth gas light on agile small satellite star sensor |
| CN112373726A (en) * | 2020-11-24 | 2021-02-19 | 中国空间技术研究院 | Pole plate type full-electric push satellite platform structure |
| CN114408215A (en) * | 2021-12-27 | 2022-04-29 | 航天东方红卫星有限公司 | Satellite configuration suitable for quick maneuvering ultrastable imaging |
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| WO2016101086A1 (en) * | 2014-12-23 | 2016-06-30 | 中国科学院长春光学精密机械与物理研究所 | Satellite structure for platform and load integration |
| CN109795718A (en) * | 2015-10-02 | 2019-05-24 | 空客防务与空间有限公司 | Satellite including optical photography instrument |
| WO2017055750A1 (en) * | 2015-10-02 | 2017-04-06 | Airbus Defence And Space Sas | Satellite comprising an optical photography instrument |
| FR3041939A1 (en) * | 2015-10-02 | 2017-04-07 | Airbus Defence & Space Sas | SATELLITE COMPRISING OPTICAL OPTICAL INSTRUMENT |
| US10442557B2 (en) | 2015-10-02 | 2019-10-15 | Airbus Defence And Space Sas | Satellite comprising an optical photography instrument |
| CN108137170A (en) * | 2015-10-02 | 2018-06-08 | 空客防务与空间有限公司 | Include the satellite of optical photography instrument |
| EP3174794B1 (en) | 2015-10-02 | 2017-11-08 | Airbus Defence and Space SAS | Satellite comprising an optical photography instrument |
| KR101900226B1 (en) | 2015-10-02 | 2018-11-08 | 에어버스 디펜스 앤드 스페이스 에스아에스 | Satellite containing optical photographic equipment |
| CN105235916A (en) * | 2015-10-27 | 2016-01-13 | 上海微小卫星工程中心 | Integration satellite compact in layout |
| CN105235916B (en) * | 2015-10-27 | 2017-10-27 | 上海微小卫星工程中心 | A kind of integrated satellite of compact layout |
| CN105527685A (en) * | 2016-01-28 | 2016-04-27 | 长光卫星技术有限公司 | Main bearing member for optical minimal satellite and common structure of optical camera |
| CN106253967A (en) * | 2016-07-28 | 2016-12-21 | 航天东方红卫星有限公司 | It is applicable to the data maintaining method of microsatellite platform and load information integrated design |
| CN106253967B (en) * | 2016-07-28 | 2019-04-30 | 航天东方红卫星有限公司 | Data maintaining method suitable for microsatellite platform and load information integrated design |
| 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 |
| CN106742063A (en) * | 2016-11-30 | 2017-05-31 | 上海卫星工程研究所 | Internal satellite configuration |
| CN106742064A (en) * | 2016-11-30 | 2017-05-31 | 上海卫星工程研究所 | One kind is without the open integrative detection device configuration of deck board |
| CN106843248A (en) * | 2017-01-24 | 2017-06-13 | 上海航天控制技术研究所 | Unit installation deviation is estimated and modification method after a kind of satellite launch is entered the orbit |
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| CN107065395A (en) * | 2017-05-24 | 2017-08-18 | 北京空间机电研究所 | A kind of shading cover structure for geostationary orbit remote sensing camera |
| CN107065395B (en) * | 2017-05-24 | 2019-10-22 | 北京空间机电研究所 | A kind of shading cover structure for geostationary orbit remote sensing camera |
| CN107458629A (en) * | 2017-07-05 | 2017-12-12 | 上海宇航系统工程研究所 | A kind of configuration of spacecraft load cabin |
| CN107380483A (en) * | 2017-07-05 | 2017-11-24 | 上海宇航系统工程研究所 | A kind of spacecraft configuation |
| CN107380483B (en) * | 2017-07-05 | 2023-09-01 | 上海宇航系统工程研究所 | Spacecraft configuration |
| CN107505799A (en) * | 2017-09-18 | 2017-12-22 | 北京空间飞行器总体设计部 | A kind of load support structure for concentrating point type stress |
| CN107505799B (en) * | 2017-09-18 | 2020-04-10 | 北京空间飞行器总体设计部 | Concentrated point type stressed load supporting structure |
| CN107967393B (en) * | 2017-12-07 | 2021-02-26 | 上海宇航系统工程研究所 | Spacecraft double-cylinder parallel structure bearing design method based on multi-constraint condition |
| CN107967393A (en) * | 2017-12-07 | 2018-04-27 | 上海宇航系统工程研究所 | A kind of spacecraft bitubular parallel-connection structure based under multi-constraint condition carries design method |
| CN108860659A (en) * | 2018-05-31 | 2018-11-23 | 北京空间飞行器总体设计部 | A kind of integrated satellite based on deployable plate phased array antenna |
| CN109795717A (en) * | 2019-03-05 | 2019-05-24 | 四川星空年代网络通信有限公司 | A kind of satellite for having automatic energy storage and utilizing |
| CN112061425A (en) * | 2020-09-08 | 2020-12-11 | 上海航天控制技术研究所 | Method for avoiding interference of earth gas light on agile small satellite star sensor |
| CN112373726A (en) * | 2020-11-24 | 2021-02-19 | 中国空间技术研究院 | Pole plate type full-electric push satellite platform structure |
| CN114408215A (en) * | 2021-12-27 | 2022-04-29 | 航天东方红卫星有限公司 | Satellite configuration suitable for quick maneuvering ultrastable imaging |
| CN114408215B (en) * | 2021-12-27 | 2024-02-09 | 航天东方红卫星有限公司 | Satellite configuration suitable for rapid maneuvering ultra-stable imaging |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2016101086A1 (en) | 2016-06-30 |
| CN104648693B (en) | 2017-01-11 |
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