CN102514730A - Electromechanical and thermal integrated satellite structure - Google Patents
Electromechanical and thermal integrated satellite structure Download PDFInfo
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- CN102514730A CN102514730A CN2011104329565A CN201110432956A CN102514730A CN 102514730 A CN102514730 A CN 102514730A CN 2011104329565 A CN2011104329565 A CN 2011104329565A CN 201110432956 A CN201110432956 A CN 201110432956A CN 102514730 A CN102514730 A CN 102514730A
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Abstract
An electromechanical and thermal integrated satellite structure comprises a plurality of electromechanical and thermal integrated basic structural plates, a plurality of mechanical connecting parts and a plurality of electric connecting parts. The mechanical connecting parts are connected by the basic structural plates to form a satellite structure unit with a plurality of three-dimensional spaces, and the basic structural plates are electrically connected by the electric connecting parts. A basic structure module, the mechanical connecting parts, the electric connecting parts and the like are designed in a unified standard manner, and can form satellite structures with different shapes and different sizes by means of splicing and combining, a satellite can be quickly assembled and integrated conveniently, simultaneously, thermal control and capacity of a power supply and distribution bus are taken into consideration during design of the structure, accordingly, the design of the satellite is greatly simplified, complexity of the design of the satellite can be reduced, reliability of a system is improved, and development cost can be effectively lowered.
Description
Technical field
The invention belongs to the AEROSPACE APPLICATION field, the mechanical, electrical and heating integrated multifunction structure that it is related as satellite structure, has thermal control and electrical communications ability concurrently, can simplify design of satellites, realizes the fast integration of satellite.
Background technology
The structural system of satellite is the space that each the unit parts on the satellite provide installation, support, carrying, guarantees that satellite bears the delivery environment of powered-flight phase and the pointing accuracy of unit; Heat control system is that satellite provides heating, heat-dissipation mode and means, guarantees that the temperature of satellite system remains in the reasonable range; Power supply-distribution system cable network system via satellite offers each unit with the energy, guarantees the power supply of unit.
The load-carrying construction of conventional satellite, thermal control, confession distribution are independently, disperse; Each system carries out independent design according to mission requirements; Systemic-function is single; Every satellite all needs to formulate separately the trend of various structure, thermal control and supply cable etc., and this will inevitably increase the lead time of satellite, improves the development cost of satellite.
Summary of the invention
The objective of the invention is to propose a kind of design of satellites scheme of multi-functional satellite structure module; Integrated mechanical, electrical, heating integrated multiple function; Through simple, fast speed assembly unit; Reduce satellite system design-calculated complexity, shorten the assembly and test cycle of satellite, and can effectively reduce the development cost of satellite.
For reaching above-mentioned purpose, the technical scheme that the present invention adopts is: a kind of mechanical, electrical and heating integrated satellite structure, proposed to merge the integrated multi-functional structure of physical construction, distribution transmission, warm-up control, and it is characterized in that, comprise:
Some mechanical, electrical and heating integrated basic structure plates as module the most basic among the present invention, have the ability as carrying, thermal control and distribution mains;
Some mechanical fasteners as the main accessory of satellite structure system, are used for the mutual mechanical connection of described basic structure plate;
Some electrical fittings as the attaching parts of satellite distribution mains, are used for being electrically connected between each basic structure plate;
A plurality of described basic structure plates are connected and composed the satellite structure unit with a plurality of cubic space with mechanical fastener, and being electrically connected through described electrical fitting between each basic structure plate realizes.
The medial surface of described basic structure plate is an instrument attachment face in the star, and this medial surface is designed with thermal control temperature booster and screw; The lateral surface of this basic structure plate is the attachment face of the outer instrument of star, solar array, bonded assembly mechanical fixation face between plate when also assembling simultaneously as structure, and this lateral surface mainly is provided with screw; Be provided with the interface that is electrically connected of unified standard at the inboard of this basic structure plate and the middle part of the side that is adjacent.
Described mechanical fastener comprises three kinds of plane connecting strap, knuckle connecting strap and full-shape connecting straps, realizes respectively that the two board planes between said basic structure plate connect, two plate is vertical connects and the vertical connection of three plates.
Described electrical fitting comprises two kinds of configurations: in-line electrical connector and L shaped electrical connector; Realize the electrically conducting between said basic structure plate; The two ends of this electrical fitting are the pin type plug, and match with the interface that is electrically connected on the described basic structure plate.
Beneficial effect of the present invention is: its design-calculated basic configuration module, mechanical fastener, electrical fitting etc. have adopted the design of unified standard; Can form the satellite configuration of difformity, different size through splicing, combination, the quick assembling of being convenient to satellite is with integrated, simultaneously because this structure is taken into account the ability of having considered thermal control and confession distribution mains in design process; Make the design of satellite obtain great simplification; A kind of basic module has been gathered three big systemic-functions, has realized integrated design mechanical, electric, thermal control, has reduced complex degree of system design; Improve system reliability, and can effectively reduce the development cost of satellite.
Description of drawings
Fig. 1 is the three-dimensional general assembly structural representation of a satellite structure embodiment of the present invention;
Fig. 2 is the three-dimensional general assembly STRUCTURE DECOMPOSITION scheme drawing of a satellite structure embodiment of the present invention;
Fig. 3 is spatial structure (inboard) scheme drawing of mechanical, electrical and heating integrated basic structure plate of the present invention;
Fig. 4 is the back view of basic structure plate shown in Figure 3;
Fig. 5 is the lateral plan of basic structure plate shown in Figure 3;
Fig. 6 is the front view of plane of the present invention connecting strap;
Fig. 7 is a left side (right side) view of Fig. 6;
Fig. 8 is the front view of knuckle connecting strap of the present invention;
Fig. 9 is the left view of Fig. 8;
Figure 10 is the birds-eye view of Fig. 8;
Figure 11 is the front view of full-shape connecting strap of the present invention;
Figure 12 is the left view of Figure 11;
Figure 13 is the birds-eye view of Figure 11;
Figure 14 is the perspective view of in-line electrical fitting of the present invention;
Figure 15 is the perspective view of L shaped electrical fitting of the present invention.
Description of reference numerals: 1-basic structure plate; The 11-structural slab is inboard is electrically connected interface; 12-thermal control heating installation power supply slot; 13-structural slab inside thread; Thermal control temperature booster on the 14-structural slab; 15-structural slab side be electrically connected interface; 16-structural slab outside screw; Connect screw between the 17-structural slab; 2-plane connecting strap; The 21-fixed orifice; 3-knuckle connecting strap; 31-strengthens the angle; The 32-fixed orifice; 4-full-shape connecting strap; 41-strengthens the angle; The 42-fixed orifice; 5-in-line electrical fitting; 6-L shape electrical fitting.
The specific embodiment
Referring to Fig. 1-Figure 10; The present invention has designed mechanical, electrical and heating integrated satellite agent structure (not containing solar array) illustrated in figures 1 and 2; The satellite structure that adopts some mechanical, electrical and heating integrated basic structure plate 1, mechanical fastener 2-4 and electrical fittings 5,6 to be assemblied to form, the inside of this satellite configuration have comprised temperature booster that thermal control uses and cable network used for distribution.
Be provided with in the inboard of basic structure plate 1 and be electrically connected interface 11, thermal control heating installation power supply slot 12, inboard screw 13 and thermal control temperature booster 14.Designed between the outside screw 16 and structural slab in the outside of basic structure plate 1 and to be connected screw 17.On each side of basic structure plate 1, be designed with and be electrically connected interface 15.Structural connection is designed to three types: plane connecting strap 2, knuckle connecting strap 3 and full-shape connecting strap 4; Electrical fitting is designed with two types: in-line electrical connector 5 and L shaped electrical connector 6, this electrical fitting 5 and 6 two ends are the pin type plug, and with described basic structure plate 1 on be electrically connected interface 11 and 15 grafting that matches.
The structural slab inboard is electrically connected interface 11 and structural slab side and is electrically connected interface 15 and has identical physical construction and electric signal definition, and its electric signal can be designed with power supply buses of satellite, the power power-supply of electric heater, General Electric's signals such as data bus of system.Wherein, the structural slab inboard is electrically connected in the interface 11 except that the power power-supply of electric heater, all is electrically connected interface 15 with the structural slab side and directly is electrically connected.Between a plurality of basic structure plates 1, be connected with L shaped electrical fitting 6 with in-line electrical fitting 5 shown in Figure 14, can realize distribution and the connection of data bus in the whole satellite structure through Figure 13.Simultaneously, design is electrically connected the suitable electric coupler of interface 11 with the structural slab inboard, the relay switch of control electric heater capacity power supply is arranged in the unit indoor design on the used unit of satellite; When each unit is installed on this multifunction structure, can realize that then data between each satellite unit connect and the confession distribution of system.
In addition, the structural slab inboard is electrically connected interface 11 and 12 of thermal control heating installation power supply slots are electrically connected, and it connects signal is the power power-supply signal of electric heater.Basic structure plate 1 inboard temperature booster 14 can be connected with its power supply slot 12 as required, and the temperature booster 14 that is connected to power supply slot 12 heats and stop heating according to the needs that fly in the satellite application process.Power supply slot 12 will be connected on the unit above the satellite, the on-off that unit can control heater.
Can make up through connecting screw 17 between the structural slab on its outside between a plurality of basic structure plates 1, constitute bigger installation load-carrying construction.Its structure type capable of being combined can be through selecting various structure attaching parts 2,3 or 4, the flat board connection in the realization plane, the vertical connection between flat board, the vertical connection between three plates.
Inside satellite or outside unit/instrument of installing etc. can be locked through inboard screw 13 on the basic structure plate 1 or outside screw 16.
Multifunction structure of the present invention according to the satellite configuration that task is confirmed, is at first confirmed the quantity of selected basic structural elements 1, various mechanical fastener and electrical fitting when concrete the application, can splice apace and assembling according to the design-calculated satellite configuration.Through changing the quantity of used basic structure plate 1, can adjust the size of satellite agent structure very easily.
Only the above; Be merely preferred embodiment of the present invention, when can not limiting the scope that the present invention implements, so the displacement of the change of numerical value or equivalent elements such as with this; Or, all should still belong to the category that patent of the present invention contains according to equalization variation and modification that claim of the present invention is done.
Claims (5)
1. mechanical, electrical and heating integrated satellite structure has proposed to merge the integrated multi-functional structure of physical construction, distribution transmission, warm-up control, it is characterized in that, comprises:
Some mechanical, electrical and heating integrated basic structure plates as module the most basic among the present invention, have the ability as carrying, thermal control and distribution mains;
Some mechanical fasteners as the main accessory of satellite structure system, are used for the mutual mechanical connection of described basic structure plate;
Some electrical fittings as the attaching parts of satellite distribution mains, are used for being electrically connected between each basic structure plate;
A plurality of described basic structure plates are connected and composed the satellite structure unit with a plurality of cubic space with mechanical fastener, and being electrically connected through described electrical fitting between each basic structure plate realizes.
2. mechanical, electrical and heating integrated satellite structure according to claim 1 is characterized in that, the medial surface of described basic structure plate is an instrument attachment face in the star, and this medial surface is designed with thermal control temperature booster and screw; The lateral surface of this basic structure plate is the attachment face of the outer instrument of star, solar array, bonded assembly mechanical fixation face between plate when also assembling simultaneously as structure, and this lateral surface mainly is provided with screw; Be provided with the interface that is electrically connected of unified standard at the inboard of this basic structure plate and the middle part of the side that is adjacent.
3. mechanical, electrical and heating integrated satellite structure according to claim 1; It is characterized in that; Described mechanical fastener comprises three kinds of plane connecting strap, knuckle connecting strap and full-shape connecting straps, realizes respectively that the two board planes between said basic structure plate connect, two plate is vertical connects and the vertical connection of three plates.
4. mechanical, electrical and heating integrated satellite structure according to claim 1; It is characterized in that; Described electrical fitting comprises two kinds of configurations: in-line electrical connector and L shaped electrical connector; Realize the electrically conducting between said basic structure plate, the two ends of this electrical fitting are the pin type plug, and match with the interface that is electrically connected on the described basic structure plate.
5. mechanical, electrical and heating integrated satellite structure according to claim 1; It is characterized in that, through the unit that uses on mechanical, electrical and heating integrated basic structure plate, mechanical fastener and each member of electrical fitting Rapid Realization satellite and the satellite, the quick assembling of instrument and equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104329565A CN102514730A (en) | 2011-12-21 | 2011-12-21 | Electromechanical and thermal integrated satellite structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104329565A CN102514730A (en) | 2011-12-21 | 2011-12-21 | Electromechanical and thermal integrated satellite structure |
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| CN102514730A true CN102514730A (en) | 2012-06-27 |
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| CN2011104329565A Pending CN102514730A (en) | 2011-12-21 | 2011-12-21 | Electromechanical and thermal integrated satellite structure |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102795350A (en) * | 2012-07-06 | 2012-11-28 | 中国航天科技集团公司第五研究院第五一三研究所 | Physical discrete type satellite system structure |
| CN102837831A (en) * | 2012-09-18 | 2012-12-26 | 西北工业大学 | In-orbit replacing device for modularized spacecraft composition module |
| CN102975867A (en) * | 2012-11-13 | 2013-03-20 | 上海微小卫星工程中心 | Satellite module and modularized satellite |
| CN103010487A (en) * | 2012-10-17 | 2013-04-03 | 浙江大学 | Heat control device and heat control method of pico-satellite in isothermal design |
| CN104290920A (en) * | 2014-10-08 | 2015-01-21 | 上海微小卫星工程中心 | Modular reconfigurable micro-nano satellite structure |
| CN104715080A (en) * | 2013-12-11 | 2015-06-17 | 北京空间技术研制试验中心 | Spacecraft equipment installation fastener design method |
| CN105035365A (en) * | 2015-07-31 | 2015-11-11 | 上海卫星工程研究所 | Satellite temperature control method allowing rapid responding and multi-orbit adaption |
| CN106528976A (en) * | 2016-11-01 | 2017-03-22 | 中国人民解放军国防科学技术大学 | Integrated design method for multifunctional aerospace structure with force-power integration function |
| CN106844835A (en) * | 2016-12-13 | 2017-06-13 | 航天恒星科技有限公司 | The integrated design method and device of a kind of thermal protection structure |
| IT201700091364A1 (en) * | 2017-08-07 | 2019-02-07 | Lettich Silvio | STRUCTURED SET TO CREATE SATELLITE STRUCTURES |
| CN111071482A (en) * | 2019-11-27 | 2020-04-28 | 西北工业大学 | Standardized and modularized cube star unit and method |
| CN111409878A (en) * | 2020-03-19 | 2020-07-14 | 上海卫星工程研究所 | Open type assembled module platform cabin structure |
| CN113022888A (en) * | 2021-05-28 | 2021-06-25 | 北京最终前沿深空科技有限公司 | Satellite structure and satellite assembly method |
| CN113772122A (en) * | 2021-09-06 | 2021-12-10 | 中国科学院微小卫星创新研究院 | Module unit for satellite |
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| JPH09132198A (en) * | 1995-11-07 | 1997-05-20 | Nec Corp | Artificial satellite electronic apparatus arrangement structure |
| US20050230558A1 (en) * | 2002-10-24 | 2005-10-20 | Shinichi Nakasuka | Artificial satellite |
| CN101128092A (en) * | 2007-09-29 | 2008-02-20 | 航天东方红卫星有限公司 | Mechanical, electrical and heating integrated electronic enclosure |
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2011
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH09132198A (en) * | 1995-11-07 | 1997-05-20 | Nec Corp | Artificial satellite electronic apparatus arrangement structure |
| US20050230558A1 (en) * | 2002-10-24 | 2005-10-20 | Shinichi Nakasuka | Artificial satellite |
| CN101128092A (en) * | 2007-09-29 | 2008-02-20 | 航天东方红卫星有限公司 | Mechanical, electrical and heating integrated electronic enclosure |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102795350A (en) * | 2012-07-06 | 2012-11-28 | 中国航天科技集团公司第五研究院第五一三研究所 | Physical discrete type satellite system structure |
| CN102795350B (en) * | 2012-07-06 | 2014-08-13 | 中国航天科技集团公司第五研究院第五一三研究所 | Physical discrete type satellite system structure |
| CN102837831A (en) * | 2012-09-18 | 2012-12-26 | 西北工业大学 | In-orbit replacing device for modularized spacecraft composition module |
| CN103010487A (en) * | 2012-10-17 | 2013-04-03 | 浙江大学 | Heat control device and heat control method of pico-satellite in isothermal design |
| CN103010487B (en) * | 2012-10-17 | 2015-04-29 | 浙江大学 | Heat control device and heat control method of pico-satellite in isothermal design |
| CN102975867A (en) * | 2012-11-13 | 2013-03-20 | 上海微小卫星工程中心 | Satellite module and modularized satellite |
| CN102975867B (en) * | 2012-11-13 | 2014-12-31 | 上海微小卫星工程中心 | Satellite module and modularized satellite |
| CN104715080A (en) * | 2013-12-11 | 2015-06-17 | 北京空间技术研制试验中心 | Spacecraft equipment installation fastener design method |
| CN104290920A (en) * | 2014-10-08 | 2015-01-21 | 上海微小卫星工程中心 | Modular reconfigurable micro-nano satellite structure |
| CN105035365A (en) * | 2015-07-31 | 2015-11-11 | 上海卫星工程研究所 | Satellite temperature control method allowing rapid responding and multi-orbit adaption |
| CN106528976A (en) * | 2016-11-01 | 2017-03-22 | 中国人民解放军国防科学技术大学 | Integrated design method for multifunctional aerospace structure with force-power integration function |
| CN106528976B (en) * | 2016-11-01 | 2017-08-01 | 中国人民解放军国防科学技术大学 | A kind of multifunctional space structure-integrated design method of resultant force Electricity Functional |
| CN106844835A (en) * | 2016-12-13 | 2017-06-13 | 航天恒星科技有限公司 | The integrated design method and device of a kind of thermal protection structure |
| IT201700091364A1 (en) * | 2017-08-07 | 2019-02-07 | Lettich Silvio | STRUCTURED SET TO CREATE SATELLITE STRUCTURES |
| WO2019030787A1 (en) * | 2017-08-07 | 2019-02-14 | LETTICH, Silvio | Structured set to make satellite structures |
| CN111071482A (en) * | 2019-11-27 | 2020-04-28 | 西北工业大学 | Standardized and modularized cube star unit and method |
| CN111071482B (en) * | 2019-11-27 | 2021-04-02 | 西北工业大学 | Standardized and modularized cube star unit and method |
| CN111409878A (en) * | 2020-03-19 | 2020-07-14 | 上海卫星工程研究所 | Open type assembled module platform cabin structure |
| CN111409878B (en) * | 2020-03-19 | 2021-08-24 | 上海卫星工程研究所 | Open type assembled module platform cabin structure |
| CN113022888A (en) * | 2021-05-28 | 2021-06-25 | 北京最终前沿深空科技有限公司 | Satellite structure and satellite assembly method |
| CN113022888B (en) * | 2021-05-28 | 2021-08-10 | 北京最终前沿深空科技有限公司 | Satellite structure and satellite assembly method |
| CN113772122A (en) * | 2021-09-06 | 2021-12-10 | 中国科学院微小卫星创新研究院 | Module unit for satellite |
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Application publication date: 20120627 |