CN104648693B - Satellite structure for platform and load integration - Google Patents
Satellite structure for platform and load integration Download PDFInfo
- Publication number
- CN104648693B CN104648693B CN201410809601.7A CN201410809601A CN104648693B CN 104648693 B CN104648693 B CN 104648693B CN 201410809601 A CN201410809601 A CN 201410809601A CN 104648693 B CN104648693 B CN 104648693B
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- Prior art keywords
- satellite
- bearing cylinder
- upper plate
- platform
- plate
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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
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.It is 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 moonlet modularity and standard functions extension mission requirements simultaneously.
Background technology
Satellite is typically made up of payload and satellite platform (or claiming common module).The mode that the general satellite platform of the many employings of traditional design of satellites combines from different payload meets different satellite missions.So-called satellite platform is exactly one and adapts to different payload configuration, completes respective particular flight mission, the common module that versatility is stronger.Based on this design concept, in satellite manufacture process, it is mostly to use the method for designing of black box, first produces working cell on each independent star, then, these unit are assembled in attachment structure composition satellite, and these separate units have the supporting structure of oneself and handle control circuit, and parts and control circuit cannot share, finally, make satellite structure overlapping, control component number and increase, cause the increase of satellite weight.Ground installation do so still has not big harm, but satellite is then greatly improved launch cost, reduces reliability.
The U.S. MMS satellite platform more famous than more typical example, as shown in Figure 3, whole satellite platform is made up of four sections of cabins, it is attitude control subsystem cabin 11, powerhouse dome 14 respectively, communicates and number pipe cabin 13 and propelling module 14, there is the supporting structure of oneself in each cabin and handles control circuit, and these cabins are separately fabricated, is then connected together by MMS supporting construction 16, MMS supporting construction plays and connects and the effect of transmission load, thus constitutes a complete satellite platform.Payload is connected by adapter 15 with satellite platform, and they are completely self-contained two systems, although such design 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 high-tech is very rapid, and drives satellite to develop to miniaturization.Moonlet have lightweight, volume is little, low cost, lead time are short, the big advantage of functional density high five, this employing satellite platform and the satellite of payload bay design, although the use of satellite platform can avoid the development again of safeguards system needed for different satellite, but its specific aim is poor, its load and service system subdivision design, the enveloping space and quality are the biggest, are not suitable for moonlet miniaturization, light-weighted 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 it is the load-carrying construction of payload, also it is 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, reduce volume, reduction cost.
Use the board-like structure of honeycomb interlayer, pre-buried heat pipe in plate, accomplish machine-heating integrated, design simple and convenient, improve the functional density of satellite.Finite element result shows, the version that the present invention proposes, it is possible to meet the relevant structural performance requirements 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 uses platform and load independent design, have that resource utilization is low and structural redundancy is high, cause the problems such as mass of system weight volume is big, it is provided that a kind of satellite structure for platform load integration.
For the satellite structure of platform load integration, including 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, installing Bearing 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.
Being uniformly arranged multiple upper board mount in the circumference of described Bearing cylinder, upper plate is arranged on Bearing cylinder by multiple upper board mounts.
The present invention includes that multiple side plate, the both sides of each side plate are provided with bar, makes side plate be connected with heart loaded cylinder by described bar.
Present invention additionally 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 uniformly 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 use honeycomb sandwich construction.
Beneficial effects of the present invention: the present invention is directed to platform load integration satellite structure and change traditional method for designing on Topology Structure Design, do not use the design of conventional satellite structure subdivision section, each subsystem is arranged in different satellite capsules, all of satellite capsule is combined one satellite completed of composition again, but surmount boundary between each subsystem, use resource-sharing thought, platform is accounted for as an entirety with load structure, designs a kind of multifunction structure for platform load integration satellite.
The present invention is to solve existing employing resource-sharing theory, it is proposed that a kind of satellite structure for platform load integration, this structure possesses following characteristics: compact conformation, volume are little, light weight；Structure function density collection is high；Rigidity is high, and structural safety nargin is big, 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, combining Fig. 1 and Fig. 2 present embodiment is described, for the satellite structure of platform load integration, this structure is gone up board mounts 10 with 12 formed by upper plate 1, Bearing cylinder 2, side plate 3, butt joint ring 7,8, three shaft bar 9 of base plate.
Using butt joint ring 7 as reference for assembling, butt joint ring 7 uses standard satellite and the rocket interface, forms by aluminum profile extrusion；Mounting base 8 on butt joint ring 7, base plate 8 uses honeycomb sandwich construction, and the advantage of honeycomb sandwich construction is light weight, specific stiffness height；Installing Bearing cylinder 2 on base plate 8, Bearing cylinder 2 uses carbon fibre composite, and they are the main force support structure of satellite, plays the effect of the miscellaneous flash of light that disappears the most in the camera；Board mount and three shaft bars on installing 12 in the circumference of Bearing cylinder 2；Installing upper plate 1 on 12 on board mount 10, upper plate 1 uses honeycomb sandwich construction equally；Installing three blocks of side plates, side plate 3 is fixed by screws in base plate 8 and the side of upper plate 1；By bar 1, bar 2 and the bar 3 of every block of side plate 3 both sides, three blocks of side plates are connected with Bearing cylinder 2, play the effect that auxiliary supports.Base plate 8, upper plate 1 and three blocks of side plates 3 are used 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 uniformly 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 includes: bear load, bear the load that satellite produces in terrestrial operation and transportation, bear acceleration that satellite produces in emission process, vibrate, impact and acoustic loads, bear the shock loading that satellization authority action produces, the load produced when bearing as being accustomed in orbit due to the motion of temperature alternating, vacuum state and change rail；Installation equipment, satellite structure needs to provide fixed installation interface for spaceborne instrument and equipment and keep certain precision, and the installation of satellite thermal control parts is also required to be implemented by structure, and satellite structure reply satellite borne equipment provides protection；Thering is provided configuration, the skeleton of satellite structure formula satellite, provide structure profile for whole star, the connection for satellite and carrier rocket provides interface, and the connection stretching adnexa for satellite provides interface；Disappear veiling glare, and shield portions gas light and other veiling glare enter window glass and camera lens, utilizes surfacing characteristic, absorbs the veiling glare having been enter into shade to greatest extent, it is ensured that higher signal to noise ratio.
To sum up, spaceborne integration satellite structure had both played satellite structure platform and has born load, installation equipment and provide the effect of configuration, plays again camera structure shade and disappears the effect of veiling glare.
Claims (3)
1. for the satellite structure of platform load integration, including 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,
The upper mounting base (8) of described butt joint ring (7), installs Bearing cylinder (2) on described base plate (8),
Described upper plate (1) is arranged on Bearing cylinder (2), and side plate (3) is fixed on upper plate (1) and base plate
(8) side；Also including three shaft bars (9), side plate (3) is three, each side plate (3)
Both sides are provided with three bars, and described three shaft bars (9) are uniformly 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),
3rd bar of the adjacent side in every adjacent side plates (3) is connected with base plate (8).
Satellite structure for platform load integration the most according to claim 1, it is characterised in that
Being uniformly arranged multiple upper board mount (10) in the circumference of Bearing cylinder (2), upper plate (1) is by multiple
Upper board mount (10) is arranged on Bearing cylinder (2).
Satellite structure for platform load integration the most according to claim 1, it is characterised in that
Described base plate (8) and upper plate (1) all use 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104648693A CN104648693A (en) | 2015-05-27 |
| CN104648693B true CN104648693B (en) | 2017-01-11 |
Family
ID=53240425
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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 |
|---|---|
| CN (1) | CN104648693B (en) |
| WO (1) | WO2016101086A1 (en) |
Families Citing this family (26)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104648693B (en) * | 2014-12-23 | 2017-01-11 | 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 |
| FR3041939B1 (en) | 2015-10-02 | 2017-10-20 | Airbus Defence & Space Sas | SATELLITE COMPRISING OPTICAL OPTICAL INSTRUMENT |
| 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 |
| CN106218921B (en) * | 2016-07-25 | 2018-10-09 | 西北工业大学 | A kind of arresting agency and method of flexible expandable collision triggering |
| 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 |
| 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 |
| CN106843248B (en) * | 2017-01-24 | 2019-05-31 | 上海航天控制技术研究所 | The estimation of single machine installation deviation and modification method after a kind of satellite launch is entered the orbit |
| 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 |
| CN107380483B (en) * | 2017-07-05 | 2023-09-01 | 上海宇航***工程研究所 | Spacecraft configuration |
| CN107458629A (en) * | 2017-07-05 | 2017-12-12 | 上海宇航***工程研究所 | A kind of configuration of spacecraft load cabin |
| 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***工程研究所 | Spacecraft double-cylinder parallel structure bearing design method based on multi-constraint condition |
| 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 |
| CN112061425B (en) * | 2020-09-08 | 2022-04-08 | 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 |
| CN112373726B (en) * | 2020-11-24 | 2022-07-05 | 中国空间技术研究院 | Pole plate type full-electric push satellite platform structure |
| CN112498742B (en) * | 2021-01-13 | 2022-07-19 | 北京工商大学 | Electronic cabin adopting food steamer type closed box structure |
| 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 |
| CN113911397B (en) * | 2021-09-30 | 2024-04-02 | 北京空间飞行器总体设计部 | Truss type optical remote sensing load cabin main structure |
| CN114162350B (en) * | 2021-12-01 | 2023-09-29 | 上海宇航***工程研究所 | Main structure of sun alignment orientation device suitable for space station |
| 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 |
| CN115743602A (en) * | 2022-09-28 | 2023-03-07 | 北京微纳星空科技有限公司 | Satellite platform |
| CN116513487B (en) * | 2023-07-05 | 2023-09-15 | 北京未来宇航空间科技研究院有限公司 | Multifunctional upper-level configuration and space carrier |
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| US4009851A (en) * | 1974-12-23 | 1977-03-01 | Rca Corporation | Spacecraft structure |
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| ES2115192T3 (en) * | 1994-01-28 | 1998-06-16 | Finmeccanica Spa | STRUCTURAL ADAPTER FOR THE LOAD COMPARTMENT OF A CONVEYOR ROCKET. |
| US6131857A (en) * | 1998-10-30 | 2000-10-17 | Hebert; Barry Francis | Miniature spacecraft |
| US6206327B1 (en) * | 1999-03-31 | 2001-03-27 | Lockheed Martin Corporation | Modular spacecraft bus |
| FR2959490B1 (en) * | 2010-04-28 | 2012-07-13 | Astrium Sas | SATELLITE HAVING A SIMPLIFIED, ALLEGE AND ECONOMIC STRUCTURE AND ITS IMPLEMENTING METHOD |
| CN102009746B (en) * | 2010-11-08 | 2012-11-14 | 航天东方红卫星有限公司 | Octagonal battery-equipped array upright post micro satellite configuration |
| US8915472B2 (en) * | 2012-05-11 | 2014-12-23 | The Boeing Company | Multiple space vehicle launch system |
| CN102717899B (en) * | 2012-06-26 | 2014-10-29 | 上海卫星工程研究所 | Venus probe configuration |
| US9296493B2 (en) * | 2013-02-28 | 2016-03-29 | The Boeing Company | Spacecraft with open sides |
| CN104648693B (en) * | 2014-12-23 | 2017-01-11 | 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 |
-
2014
- 2014-12-23 CN CN201410809601.7A patent/CN104648693B/en not_active Expired - Fee Related
- 2014-12-25 WO PCT/CN2014/001170 patent/WO2016101086A1/en active Application Filing
Also Published As
| Publication number | Publication date |
|---|---|
| WO2016101086A1 (en) | 2016-06-30 |
| CN104648693A (en) | 2015-05-27 |
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Granted publication date: 20170111 Termination date: 20211223 |