CN104071354B - A kind of satellite shell and use the satellite of this housing - Google Patents
A kind of satellite shell and use the satellite of this housing Download PDFInfo
- Publication number
- CN104071354B CN104071354B CN201410229957.3A CN201410229957A CN104071354B CN 104071354 B CN104071354 B CN 104071354B CN 201410229957 A CN201410229957 A CN 201410229957A CN 104071354 B CN104071354 B CN 104071354B
- Authority
- CN
- China
- Prior art keywords
- face
- satellite
- shell
- optics load
- bottom face
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Abstract
The present invention provides a kind of satellite shell and uses the satellite of this housing, described satellite includes satellite shell and optics load, described satellite shell includes housing body, described housing body includes the first end face and the bottom face relative with described first end face, described bottom face is for being connected with external member, also include one second end face, described second end face and described first end face are respectively positioned on the same side of described bottom face, and described second end face to the distance of described bottom face less than the distance of described first end face to described bottom face；Described optics load is arranged on described second end face.It is an advantage of the current invention that the vibratory response that can either reduce satellite when launching powered phase, disclosure satisfy that again the big visual field demand of optics load.
Description
Technical field
The present invention relates to space satellite technical field, particularly relate to a kind of satellite shell and use the satellite of this housing.
Background technology
The configuration layouts of satellite be organically connected to the unit of each subsystem, instrument and parts together, a good working foundation is provided to each subsystem, constitute a complete satellite, rocket launching and the examination of the produced mechanical environment of satellite and the rocket separation can be born simultaneously.
The stationary mode that the profile of satellite shell is mainly taked by satellite determines.Spin stabilized satellite generally pylindrical such as " dfh-2 " and " dfh-2 first " satellite, its main body is cylinder.It is all cuboid that three axis stabilized satellite is generally the satellite profile such as cuboid such as " DFH-3 ", " wind and cloud one ", " resource one " and " resource two ".Gravity gradient stabilized satellite is usually dumb-bell shape, is equipped with the gravity rod such as " beacon one " satellite of certain mass on satellite top.
Dimensional turntable realizes the pitch orientation of optics load and the two-dimensional field of view demand of rotation direction.And response level that high optics load can bear is limited, existing satellite shell construction techniques not only can not meet visual field demand but also reduce vibratory response.For the satellite of three-axis stabilization, the profile of the housing of the satellite of three-axis stabilization is generally cuboid, to meet the big visual field demand of the optics load installed in dimensional turntable, then needs to be arranged on dimensional turntable top or the bottom of satellite shell cuboid.Owing to bottom is the joint face of satellite and rocket, therefore can be only installed at the top of satellite shell, its vibratory response can be very big.When satellite connects transmitting with other satellite, especially launching the satellite on top in series connection, it is more severe at rocket launching powered phase mechanical environment, and when reduction satellite series connection is launched, on the satellite shell of top satellite, the technology of optics load vibratory response is particularly important.
Visual field is required that higher dimensional turntable optics load the same with other structures of satellite must be exposed to space, cold spatial environments after standing the sunshine under high vacuum condition and entering shadow region, the highest ambient temperature reaches 500K, minimum reach 3K temperature, and change is very frequently (the sun-synchronous orbit general cycle is only about 100min), for the dimensional turntable optics load requiring significantly high image quality, will can not put up with.
Dimensional turntable optics load generally observes opaco, needs to consider the heat dissipation problem of the heat insulation and detected with high accuracy device of solar radiation for dimensional turntable optics load thermal control, so the dimensional turntable optics load thermal control being exposed to outside star needs the labyrinths such as radiant panel.
Therefore explore novel satellite configuration, effectively expand the kind of satellite load further and adapt to satellite series connection radiation pattern, the scientific application greatly improving satellite is worth.
Summary of the invention
The technical problem to be solved is to provide a kind of satellite shell and uses the satellite of this housing, and it can either reduce the satellite vibratory response when launching powered phase, disclosure satisfy that again the big visual field demand of optics load.
In order to solve the problems referred to above, the invention provides a kind of satellite shell, including housing body, described housing body includes the first end face and the bottom face relative with described first end face, described bottom face is for being connected with external device (ED), also including one second end face, described second end face and described first end face are respectively positioned on the same side of described bottom face, and described second end face to the distance of described bottom face less than the distance of described first end face to described bottom face.
Further, described first end face is parallel with described second end face, so that described satellite shell is L-shaped.
Further, being provided with perforate on described second end face, described perforate for being arranged at described second end face by external member.
The present invention also provides for a kind of satellite, including satellite shell and optics load, described satellite shell includes housing body, described housing body includes the first end face and the bottom face relative with described first end face, described bottom face is for being connected with external member, also including one second end face, described second end face and described first end face are respectively positioned on the same side of described bottom face, and described second end face to the distance of described bottom face less than the distance of described first end face to described bottom face；Described optics load is arranged on described second end face.
Further, described optics load is arranged on described second end face by a dimensional turntable.
Further, the side intersected with described second end face being provided with perforate, having the unit of visual field demand, to be arranged at satellite shell internal and be positioned under the second end face, described in there is the unit of visual field demand lean out from described perforate, to be operated.
Further, the unit with visual field demand of described satellite is arranged on the bottom face corresponding with described second end face, to be operated.
Further, the high-power unit of described satellite is arranged on the one side all intersected with described first end face and the second end face, is beneficial to the heat radiation of described high-power unit.
Further, described first end face is parallel with described second end face, so that described satellite shell is L-shaped.
Further, being provided with perforate on described second end face, described perforate for being arranged at described second end face by optics load.
It is an advantage of the current invention that:
(1) satellite shell has the first end face and the second end face, second end face to the distance of bottom face less than the distance of the first end face to bottom face, the optics load being arranged on the second end face height of center of mass on satellite is reduced, thus reducing the vibratory response when satellite launch powered phase of the optics load.
(2) owing to the second end face 13 is exposed end face, so meeting the demand of the big visual field of optics load.
(3) satellite period in-orbit, existence due to the one side all intersected with described first end face and the second end face 13 of described satellite shell, no matter then inertial orientation or absolute orientation under sun-synchronous orbit, sunlight all can be blocked for optics load in side, it is thus possible to guarantee that optics load is not alternately affected by the temperature of illumination shade for a long time, a good low temperature space environment steady in a long-term is provided for optics load, it is simple to the autonomous temperature control of camera under meeting mechanical condition, thus accurately image.
(4) effectively expanding the kind of satellite load, and adapt to series connection radiation pattern, the scientific application greatly improving satellite is worth.
Accompanying drawing explanation
Fig. 1 is the structural representation of satellite shell of the present invention；
Fig. 2 is the structural representation of satellite of the present invention；
Fig. 3 is another structural representation of satellite of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, the detailed description of the invention of a kind of satellite shell provided by the invention and the satellite using this housing is elaborated.
Referring to Fig. 1, satellite shell 10 of the present invention includes the first end face 11 and the bottom face 12 relative with described first end face 11.
Described bottom face 12 is for being connected with external device (ED) (not indicating in accompanying drawing).Described external device (ED) can be rocket, and when satellite launch, described bottom face 12 is connected with described rocket, described bottom face 12 and described Separation after entering satellite orbit.Described external device (ED) can also be another satellite, and when the multiple satellite series connection of needs, described bottom face 12 is connected with another satellite.
Described satellite shell 10 also includes one second end face 13.Described second end face 13 and described first end face 11 are respectively positioned on the same side of described bottom face 12, and described second end face 13 arrives the distance distance less than described first end face 11 to described bottom face 12 of described bottom face 12.Preferably, described first end face 11 is parallel with described second end face 13, so that described satellite shell 10 is L-shaped.
Further, in this embodiment, being provided with perforate 14 on described second end face 13, described perforate 14 for being arranged at described second end face 13 by external device (ED).In other detailed description of the invention, described second end face 13 is not provided with perforate, but by fixing component, described external device (ED) is fixed on described second end face 13.Described satellite shell 10 is formed by connecting by the cellular board of multi-disc different specification size, can pass through securing member general in prior art and connect between described cellular board.
Referring to Fig. 2, the present invention also provides for a kind of satellite, and described satellite includes satellite shell 10 and optics load 20.Described satellite shell 10 is identical with above-mentioned satellite shell 10 structure, is not repeated herein.
Described optics load 20 is arranged on described second end face 13.Further, described optics load 20 is arranged on described second end face 13 by a dimensional turntable 30, and the perforate 14 that described dimensional turntable 30 can be passed through on the second end face 13 is arranged on the second end face 13, but also can pass through perforate 14 and be connected with inside satellite component.Further, described first end face 11 is parallel with described second end face 13, so that described satellite shell 10 is L-shaped.In this embodiment, described optics load 20 can be space camera.
Owing to the second end face 13 arrives the distance distance less than the first end face 11 to bottom face 12 of bottom face 12, so, described optics load 20 is arranged on the second end face 13, reduces the optics load 20 height of center of mass on satellite, thus reducing the optics load 20 vibratory response when satellite launch.Simultaneously as the second end face 13 is exposed end face, so meet the demand of the big visual field of optics load 20.
Satellite is period in-orbit, existence due to the one side 15 all intersected with described first end face 11 and the second end face 13 of described satellite shell 10, no matter then inertial orientation or absolute orientation under sun-synchronous orbit, sunlight all can be blocked for optics load 20 in side 15, alternately do not affected by the temperature of illumination shade it is thus possible to guarantee that optics load 20 is long-term, a good low temperature space environment steady in a long-term is provided for optics load 20 under meeting mechanical condition, it is easy to the autonomous temperature control of camera, thus accurately image.
Referring to Fig. 2 and Fig. 3, further, the side 16 intersected with described second end face 13 is provided with at least one perforate 17.The unit 40 with visual field demand is arranged at satellite shell 10 inside and is positioned at the second end face 13 times.The described unit 40 with visual field demand leans out from described perforate 17, to be operated.The unit 40 with visual field demand of described satellite can also be arranged on the bottom face 12 corresponding with described second end face 13 to be operated.The position that arranges of the unit 40 with visual field demand of satellite of the present invention all disclosure satisfy that the demand of its visual field and is all located at the bottom of satellite, thus reducing the vibratory response when satellite launch of the unit 40 with visual field demand.
Further, the high-power unit (not indicating in accompanying drawing) of described satellite is arranged on the side 15 all intersected with described first end face 11 and the second end face 13, is beneficial to the heat radiation of described high-power unit.In prior art, plate type box body structure satellite is typically all and unit is installed on star inner bottom plating or pendant in can on the dividing plate of load, be so then be main by radiation heat transfer for the sinking path of unit.And satellite of the present invention can by long-term high-power unit (such as power-supply controller of electric) pendant on side 15.Owing to task points to requirement, this side 15 be all the time facing to the best radiating surface in deep cooling space, is directly installed on this side 15 by long-term high-power unit to be the heat sink conception of the best.Simultaneously for short-term job unit and small-power unit then still traditionally scheme be arranged in satellite capsule, carry out heat radiation by radiation heat transfer and guarantee temperature.
The above is only the preferred embodiment of the present invention; it should be pointed out that, for those skilled in the art, under the premise without departing from the principles of the invention; can also making some improvements and modifications, these improvements and modifications also should be regarded as protection scope of the present invention.
Claims (7)
1. a satellite, including satellite shell and optics load, it is characterized in that, described satellite shell includes housing body, described housing body includes the first end face and the bottom face relative with described first end face, and described bottom face, for being connected with external member, also includes one second end face, described second end face and described first end face are respectively positioned on the same side of described bottom face, and described second end face to the distance of described bottom face less than the distance of described first end face to described bottom face；Described optics load is arranged on described second end face.
2. satellite according to claim 1, it is characterised in that described optics load is arranged on described second end face by a dimensional turntable.
3. satellite according to claim 1, it is characterized in that, the side intersected with described second end face is provided with perforate, the unit with visual field demand is arranged at satellite shell inside and is positioned under the second end face, the described unit with visual field demand leans out from described perforate, to be operated.
4. satellite according to claim 1, it is characterised in that the unit with visual field demand of described satellite is arranged on the bottom face corresponding with described second end face, to be operated.
5. satellite according to claim 1, it is characterised in that the high-power unit of described satellite is arranged on the one side all intersected with described first end face and the second end face, is beneficial to the heat radiation of described high-power unit.
6. satellite according to claim 1, it is characterised in that described first end face is parallel with described second end face, so that described satellite shell is L-shaped.
7. satellite according to claim 1, it is characterised in that be provided with perforate on described second end face, described perforate for being arranged at described second end face by optics load.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410229957.3A CN104071354B (en) | 2014-05-28 | 2014-05-28 | A kind of satellite shell and use the satellite of this housing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410229957.3A CN104071354B (en) | 2014-05-28 | 2014-05-28 | A kind of satellite shell and use the satellite of this housing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104071354A CN104071354A (en) | 2014-10-01 |
| CN104071354B true CN104071354B (en) | 2016-07-20 |
Family
ID=51593037
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410229957.3A Active CN104071354B (en) | 2014-05-28 | 2014-05-28 | A kind of satellite shell and use the satellite of this housing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104071354B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104787359B (en) * | 2014-12-30 | 2018-01-19 | 上海新跃仪表厂 | A kind of miniaturized surveillance satellite configuration |
| CN107168006B (en) * | 2017-06-12 | 2019-06-04 | 上海微小卫星工程中心 | Big breadth optical imaging system based on rotation |
| CN107168005B (en) * | 2017-06-12 | 2019-10-01 | 上海微小卫星工程中心 | Big breadth optical imaging method based on rotation |
| CN108820263B (en) * | 2018-06-19 | 2020-03-06 | 上海卫星工程研究所 | Mixed nested layered stepped satellite platform configuration |
| CN109343297A (en) * | 2018-10-25 | 2019-02-15 | 中国科学院西安光学精密机械研究所 | A kind of passive thermal control type lunar surface camera and imaging method |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5067672A (en) * | 1989-04-24 | 1991-11-26 | Alcatel Espace | Method of placing a geostationary telecommunicaiton satellite in orbit |
| US5169094A (en) * | 1990-02-26 | 1992-12-08 | Aerospatiale Societe Nationale Industrielle | Geostationary earth observation satellite incorporating liquid propellant apogee maneuver system and hollow antennas |
| EP1022219A2 (en) * | 1999-01-21 | 2000-07-26 | DaimlerChrysler Aerospace AG | Payload carrier for space stations |
| CN1994822A (en) * | 2005-12-31 | 2007-07-11 | 启碁科技股份有限公司 | Satellite acceptor shell and forming method |
| CN102372092A (en) * | 2010-08-17 | 2012-03-14 | 上海卫星工程研究所 | Configuration for low-earth-orbit remote sensing satellite and mounting method thereof |
| CN103264774A (en) * | 2013-04-24 | 2013-08-28 | 上海卫星工程研究所 | Mini probe for Mars orbits |
| CN103612774A (en) * | 2013-11-20 | 2014-03-05 | 西北工业大学 | Separable micro and nano-satellite configuration |
| EP2716549A2 (en) * | 2012-10-05 | 2014-04-09 | Thales | Satellite with deployable payload modules |
-
2014
- 2014-05-28 CN CN201410229957.3A patent/CN104071354B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5067672A (en) * | 1989-04-24 | 1991-11-26 | Alcatel Espace | Method of placing a geostationary telecommunicaiton satellite in orbit |
| US5169094A (en) * | 1990-02-26 | 1992-12-08 | Aerospatiale Societe Nationale Industrielle | Geostationary earth observation satellite incorporating liquid propellant apogee maneuver system and hollow antennas |
| EP1022219A2 (en) * | 1999-01-21 | 2000-07-26 | DaimlerChrysler Aerospace AG | Payload carrier for space stations |
| CN1994822A (en) * | 2005-12-31 | 2007-07-11 | 启碁科技股份有限公司 | Satellite acceptor shell and forming method |
| CN102372092A (en) * | 2010-08-17 | 2012-03-14 | 上海卫星工程研究所 | Configuration for low-earth-orbit remote sensing satellite and mounting method thereof |
| EP2716549A2 (en) * | 2012-10-05 | 2014-04-09 | Thales | Satellite with deployable payload modules |
| CN103264774A (en) * | 2013-04-24 | 2013-08-28 | 上海卫星工程研究所 | Mini probe for Mars orbits |
| CN103612774A (en) * | 2013-11-20 | 2014-03-05 | 西北工业大学 | Separable micro and nano-satellite configuration |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104071354A (en) | 2014-10-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104071354B (en) | A kind of satellite shell and use the satellite of this housing | |
| CN103662088B (en) | A kind of star sensor thermal control layout method of GEO orbiter | |
| CN110395411A (en) | A kind of low rail remote sensing micro-nano satellite and its Thermal design | |
| CN104157977B (en) | 3-RPS Three dimensional rotation type parallel antenna structure system | |
| EP3808664B1 (en) | Toroidal support structures | |
| US10351266B2 (en) | Attitude determination and control system (ADCS), sun sensor, and star tracker | |
| CN104029828B (en) | Thermal insulation device for engine of detector | |
| JP2016529165A (en) | Heat dissipation system for mounted devices | |
| CN102588716A (en) | Satellite-remote sensor flexible heat sinking joint | |
| CN205633087U (en) | Multi -angle oblique photography stabilizes mounting structure | |
| CN106516166A (en) | Dynamic and static isolating type structure of satellite | |
| CN103500749A (en) | Thermoelectric refrigerating ultra-long linear array InGaAs detector encapsulation structure | |
| KR20130058250A (en) | Floating appratus for generating electricity with thermoelectric element | |
| CN107284692B (en) | A kind of pyrolysis coupling expandable truss system suitable for space plate aerial | |
| CN107792400B (en) | Satellite external-pasting heat pipe mounting structure with deformation isolation function | |
| CN107444677B (en) | Optical-mechanical-thermal integrated structure for multi-load high-precision splicing | |
| CN207985196U (en) | A kind of unmanned plane of taking photo by plane convenient for adjusting camera | |
| CN104691790B (en) | High accuracy Light deformation star sensor mounting bracket | |
| CN207424495U (en) | optical, mechanical and electronic integration space camera | |
| CN109067340A (en) | Tracing type photovoltaic plate system | |
| CN109975830B (en) | In-orbit thermal deformation suppression system for GEO satellite optical remote sensing instrument | |
| CN205404936U (en) | Use micro mirror unit and satellite heat accuse mechanism of ultra -thin PCB as basement | |
| CN106291866A (en) | A kind of applicable moon base mechanics and the mirror support mechanism of the temperature difference | |
| CN106714504A (en) | Remote radio unit, mounting element, and radio-frequency communication system | |
| CN209462480U (en) | A kind of high-definition television protective shell |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |