CN105438503A - Satellite and rocket docking device - Google Patents
Satellite and rocket docking device Download PDFInfo
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- CN105438503A CN105438503A CN201510860244.1A CN201510860244A CN105438503A CN 105438503 A CN105438503 A CN 105438503A CN 201510860244 A CN201510860244 A CN 201510860244A CN 105438503 A CN105438503 A CN 105438503A
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- satellite
- rocket docking
- rocket
- frame
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/641—Interstage or payload connectors
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Abstract
The invention provides a satellite and rocket docking device, and relates to the technical field of spaceflight overall configuration. The satellite and rocket docking device comprises a main cylinder, a backland plate connecting frame and a satellite and rocket docking frame, wherein the a circular opening is formed in the bottom of the satellite and rocket docking frame; a square opening is formed in the top of the main cylinder. The satellite and rocket docking frame disclosed by the invention is suitable for a total carbon fiber composite circumference transition satellite and rocket connecting device of a grillage type configuration GEO satellite platform, uniform transition of a whole satellite mechanical load from a box-shaped grillage to a circular delivery butting ring is realized, and as a corn component of the device, the grillage type satellite configuration forms a favorable force transmitting path. The rigidity, the intensity and the stability of the whole satellite device all meet design requirements, and a solid basis is established for the configuration design of the whole satellite.
Description
Technical field
The present invention relates to a kind of space flight overall configuration technical field, particularly a kind of satellite-rocket docking device.
Background technology
Along with electric propulsion technology fast development and reach its maturity, electric propulsion technology GEO satellite is progressively applied, and protects, part becomes rail from position, north and south, realizes whole change rails and position maintenance task in-orbit to utilizing electric propulsion.The application of electric propulsion technology can significantly reduce propellant carrying amount, alleviates satellite launch weight, thus realizes an arrow double star transmitting, effectively saves launch cost.
Due to the application of electric propulsion technology, particularly adopt full electricity to push away and become rail task, GEO satellite booster agent carrying amount is significantly reduced, adopting with Bearing cylinder is the design requirement that the configurations of primary load bearing device has been not suitable with GEO satellite platform.Huge chemical propellant tank has been installed in its loaded cylinder inside of satellite platform that tradition becomes rail with chemical propulsion, due to the existence of loaded cylinder, reduces the instrument and equipment load-carrying efficiency of satellite, and brings difficulty to general assembly operation.GEO satellite platform adopts electric propulsion to realize becoming rail and position maintenance in-orbit, and eliminate chemical propulsion system, propellant is xenon and carrying amount is few, in order to promote instrument and equipment arrangement space, need cancel Bearing cylinder, using grillage as primary load bearing device.Flat-rack satellite configuration is simple, flexible, extensibility is strong, adapt to electric propulsion satellite platform feature, effectively improve satellite spatial utilization ratio, add capacity weight load-carrying capacity, but this configuration scheme exists a technical barrier, be exactly how to realize whole star mechanical loading delivers butt joint ring even transition from box grillage platform to circle.
Summary of the invention
The object of the invention is to the above-mentioned deficiency overcoming prior art, propose a kind of satellite-rocket docking device, the present invention adopts a kind of full carbon fiber composite material circumference transition satellite and the rocket connecting device being applicable to flat-rack configuration GEO satellite platform, achieve whole star mechanical loading delivers butt joint ring even transition from box grillage to circle, as device core component, this invention makes flat-rack satellite configuration form good Path of Force Transfer, rigidity, the strength and stability degree of whole star device all meet design requirement, and the Configuration Design for whole star has established solid foundation.
Above-mentioned purpose of the present invention is achieved by following technical solution:
A kind of satellite-rocket docking device, comprises main cylinder, privately plate connection box and satellite-rocket docking frame; Main cylinder is fixedly mounted on the top of satellite-rocket docking frame, and the bottom opening of satellite-rocket docking frame is circular; Plate connection box is fixedly mounted on the middle and lower part of main cylinder outer wall privately; The open top of main cylinder is square; Satellite-rocket docking frame realizes the connection with outside carrier rocket satellite support; Main cylinder realizes the connection with outside load dividing plate.
At above-mentioned a kind of satellite-rocket docking device, described satellite and the rocket connecting device height h is 500-600mm; The foursquare open top length of side L1 of main cylinder is 700-900mm; The bottom opening diameter L2 of satellite-rocket docking frame circle is 1200-1230mm.
At above-mentioned a kind of satellite-rocket docking device, main cylinder comprises plane area and curved regions; Plane area comprises 4 inverted equicrural triangle planes, and equicrural triangle plane is with the foursquare open top length of side L1 of main cylinder for base, and summit is on the bottom frame of satellite-rocket docking frame circle; Remainder is the curved regions of rounding off.
At above-mentioned a kind of satellite-rocket docking device, the long L3 of waist of equicrural triangle plane is 450-600mm; Base angle D is 60-70 °.
At above-mentioned a kind of satellite-rocket docking device, plate connection box comprises loop connecting frame and auricle privately, and auricle horizontal circle is fixed on the outside of loop connecting frame.
At above-mentioned a kind of satellite-rocket docking device, loop connecting arch horizontal section is circumference shape, and wherein the long L4 of straight flange is 230-250mm; Do the vertical line of straight flange with two end points that adjacent two straight flanges are close, two vertical line joinings are the home position of circular arc, and arc angle A is 85-95 °, and arc radius R1 is 440-460mm.
At above-mentioned a kind of satellite-rocket docking device, plate connection box vertical section is oblique T-shaped privately, and plate connection box vertical dimension L8 is 40-44mm privately; Loop connecting frame and horizontal plane angle B are 65-70 °, and thickness L5 is 1.5-2.5mm; Auricle thickness L6 thickness is 2-3mm; The outermost end of auricle is 34-36mm apart from loop connecting frame L7; Outside auricle upper surface and loop connecting frame, intersection arranges the circular arc that radius R 2 is 5-7mm; Outside auricle lower surface and loop connecting frame, intersection arranges the circular arc that radius R 3 is 5-7mm; Auricle lower surface is 19-21mm apart from the lower end L9 of loop connecting frame.
At above-mentioned a kind of satellite-rocket docking device, satellite-rocket docking frame horizontal section is circular shape, and centre arranges through hole, and through-hole diameter L10 is 1170-1180mm.
At above-mentioned a kind of satellite-rocket docking device, the vertical section of satellite-rocket docking frame is special-shaped device, and wherein upper horizontal limit L11 is 2-3mm; Inner vertical limit L12 is 38-40mm; Through-hole wall is 29-30mm to inner vertical back gauge L13; Through hole wall thickness L14 is 5-7mm; Interior wing base and intersection, inner vertical limit are provided with the circular arc that radius R 4 is 9-11mm; Satellite-rocket docking frame outer wall hypotenuse and vertical direction angle C are 4-6 °; Outer wall horizontal sides L15 is long is 2-3mm, and outer wall vertical edge corner arranges the circular arc that radius R 5 is 4-5mm; Outer wall base height L16 is 4-6mm; Satellite-rocket docking frame height L17 is 55-60mm.
At above-mentioned a kind of satellite-rocket docking device, each limit of main cylinder inwall is provided with vertical setting of types reinforced rib; Main cylinder outer wall and corner are provided with the device connecting corner strip of vertical setting of types.
The present invention compared with prior art tool has the following advantages:
(1) the present invention devises a kind of open top of main cylinder first for square, the bottom opening of satellite-rocket docking frame is circular be applicable to the circumference transition satellite and the rocket connecting device that the full electricity of flat-rack configuration pushes away satellite platform, solves whole star mechanical loading delivers butt joint ring even transition from box grillage platform to circle;
(2) main cylinder of the present invention adopts the structure that plane area and curved regions combine; Plane area comprises 4 inverted equicrural triangle planes, and remainder is the curved regions of rounding off, makes that satellite and the rocket connecting device obtains rigidity, intensity is greatly improved, and improves satellite spatial utilization ratio, increases capacity weight load-carrying capacity;
(3) the present invention privately plate connection box adopt oblique T-shaped structure, under the prerequisite meeting Joint strenght, improve satellite spatial utilization ratio, reduce the weight of satellite and the rocket connecting device entirety;
(4) satellite-rocket docking frame of the present invention adopts abnormally-structured, adds the intensity of satellite-rocket docking frame, rigidity, reduces the quality of traditional satellite-rocket docking frame, be provided with fillet around the corner, reduce the difficulty of processing technology, increases capacity weight load-carrying capacity;
(5) each limit of main cylinder inwall of the present invention is provided with vertical setting of types reinforced rib; Main cylinder outer wall and corner are provided with the anatomical connectivity angle bead of vertical setting of types, improve type satellite-rocket docking device intensity, improve the reliability that type satellite-rocket docking device and external device carry out being connected.
Accompanying drawing explanation
Fig. 1 is satellite-rocket docking device composition diagram of the present invention;
Fig. 2 is satellite-rocket docking device birds-eye view of the present invention;
Fig. 3 is satellite-rocket docking device front elevation of the present invention;
Fig. 4 is the present invention's plate connection box birds-eye view privately;
Fig. 5 is the present invention's plate connection box vertical section schematic diagram privately;
Fig. 6 is satellite-rocket docking frame birds-eye view of the present invention;
Fig. 7 is satellite-rocket docking frame vertical section schematic diagram of the present invention.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail:
Be illustrated in figure 1 satellite-rocket docking device composition diagram, as seen from the figure, comprise main cylinder 1, privately plate connection box 2 and satellite-rocket docking frame 3; Main cylinder 1 is fixedly mounted on the top of satellite-rocket docking frame 3, and the bottom opening of satellite-rocket docking frame 3 is circular; Plate connection box 2 is fixedly mounted on the middle and lower part of main cylinder 1 outer wall privately; The open top of main cylinder 1 is square; Satellite-rocket docking frame 3 realizes the connection with outside carrier rocket satellite support; Main cylinder 1 realizes the connection with outside load dividing plate.
The each limit of main cylinder 1 inwall is provided with vertical setting of types reinforced rib; Main cylinder 1 outer wall and corner are provided with the device connecting corner strip of vertical setting of types.
Be illustrated in figure 2 satellite-rocket docking device birds-eye view, as seen from the figure, described satellite and the rocket connecting device height h is 500-600mm; The foursquare open top length of side L1 of main cylinder 1 is 700-900mm; The bottom opening diameter L2 of satellite-rocket docking frame 3 circle is 1200-1230mm.
Be illustrated in figure 3 satellite-rocket docking device front elevation, as seen from the figure, main cylinder 1 comprises plane area and curved regions; Plane area comprises 4 inverted equicrural triangle planes, and equicrural triangle plane is with the foursquare open top length of side L1 of main cylinder 1 for base, and summit is on the bottom frame of satellite-rocket docking frame 3 circle; Remainder is the curved regions of rounding off.
The long L3 of waist of equicrural triangle plane is 450-600mm; Base angle D is 60-70 °.
Be illustrated in figure 4 plate connection box birds-eye view privately, as seen from the figure, plate connection box 2 comprises loop connecting frame 4 and auricle 5 privately, and auricle 5 horizontal circle is fixed on the outside of loop connecting frame 4.
Loop connecting frame 4 over water plane section is circumference shape, and wherein the long L4 of straight flange is 230-250mm; Do the vertical line of straight flange with two end points that adjacent two straight flanges are close, two vertical line joinings are the home position of circular arc, and arc angle A is 85-95 °, and arc radius R1 is 440-460mm.
Be illustrated in figure 5 plate connection box vertical section schematic diagram privately, as seen from the figure, plate connection box 2 vertical section is oblique T-shaped privately, and plate connection box 2 vertical dimension L8 is 40-44mm privately; Loop connecting frame 4 and horizontal plane angle B are 65-70 °, and thickness L5 is 1.5-2.5mm; Auricle 5 thickness L6 thickness is 2-3mm; The outermost end of auricle 5 is 34-36mm apart from loop connecting frame 4L7; Outside auricle 5 upper surface and loop connecting frame 4, intersection arranges the circular arc that radius R 2 is 5-7mm; Outside auricle 5 lower surface and loop connecting frame 4, intersection arranges the circular arc that radius R 3 is 5-7mm; Auricle 5 lower surface is 19-21mm apart from the lower end L9 of loop connecting frame 4.
Be illustrated in figure 6 satellite-rocket docking frame birds-eye view, as seen from the figure, satellite-rocket docking frame 3 horizontal section is circular shape, and centre arranges through hole, and through-hole diameter L10 is 1170-1180mm.
Be illustrated in figure 7 satellite-rocket docking frame vertical section schematic diagram, as seen from the figure, the vertical section of satellite-rocket docking frame 3 is special-shaped device, and wherein upper horizontal limit L11 is 2-3mm; Inner vertical limit L12 is 38-40mm; Through-hole wall is 29-30mm to inner vertical back gauge L13; Through hole wall thickness L14 is 5-7mm; Interior wing base and intersection, inner vertical limit are provided with the circular arc that radius R 4 is 9-11mm; Satellite-rocket docking frame 3 outer wall hypotenuse and vertical direction angle C are 4-6 °; Outer wall horizontal sides L15 is long is 2-3mm, and outer wall vertical edge corner arranges the circular arc that radius R 5 is 4-5mm; Outer wall base height L16 is 4-6mm; The high L17 of satellite-rocket docking frame 3 is 55-60mm.
The main design thought of satellite-rocket docking device is: the mating interface providing satellite and carrier rocket; The main bearer path of satellite load is provided; For satellite primary load bearing dividing plate, privately plate, monopropellant tank bottom bracket provide interface; Centered by satellite-rocket docking device and primary load bearing dividing plate, be connected with other various plate or lever apparatus, form the main device of satellite.In order to alleviate satellite-rocket docking installation weight as far as possible, main cylinder device adopts full composite material device form, realizes the square configuration to rounded transitional.
This device forms primarily of main cylinder 1, privately plate connection box 2, satellite-rocket docking frame 3.
1, main cylinder 1
Main cylinder 1 upper end is square, and lower end is circular, and circumference transition phase thickness is even, smooth transition, integrally formed, as shown in Figure 1.Inwardly closing up in main cylinder 1 upper end, forms in-flanges.Bottom is conic tube, and be connected with interface frame, mating frame, connection mode is spirally connected for splicing+pad, and the conic tube be connected with interface frame, mating frame need carry out thickening reinforcement.Square frame corner, upper end, owing to easily producing defective workmanship, need adopt metal to strengthen angle box and carry out reinforcement.
2, reinforced rib
For increasing circumference transition apparatus local stability, arrange 12 reinforced ribs at main cylinder 4 planar delta transition phases respectively, reinforced rib adopts the full carbon fiber multilayer laying in hat section.
Circumference transition satellite and the rocket connecting device composition as shown in Figure 1, forms primarily of main cylinder, privately plate connection box, satellite-rocket docking frame and relevant connecting corner strip and embedded part.Circumference transition apparatus upper port is connected with 4 pieces of primary load bearing dividing plates by 40 M6 screws, and upper surface is formed to in-flanges by carbon fiber laying, and at uniform 40 mounting holes of square end surface, each mounting hole all adopts reinforcement angle box to carry out reinforcement.
Satellite-rocket docking frame provide with launch vehicle interface, with ground supports equipment interface, 1194A standard interface according to CZ-3B designs, open the hole of 44 φ 6.2mm, for satellite and ground supports equipment connection, interface frame, mating frame and carbon fiber main cylinder adopt glue connection added bolt connection.Privately plate connection box by 48 M5 screws and satellite privately plate be connected.
Circumference transition apparatus arrange with primary load bearing dividing plate, to floor, electronic compartment dividing plate, etc. the connecting interface of mount board, the connecting interface with monopropellant tank bottom bracket is set simultaneously.
3. plate connection box 2 privately
Plate connection box 2 is for connecting satellite body plate privately privately, by 48 M5 screws and satellite privately plate be connected.
4. satellite-rocket docking frame 3
Satellite-rocket docking frame 3 is for being connected with carrier rocket satellite support, and itself and launch vehicle interface adapt to the carrier rocket satellite and the rocket interface of international standard.
The content be not described in detail in specification sheets of the present invention belongs to the known technology of those skilled in the art.
Claims (10)
1. a satellite-rocket docking device, is characterized in that: comprise main cylinder (1), privately plate connection box (2) and satellite-rocket docking frame (3); Main cylinder (1) is fixedly mounted on the top of satellite-rocket docking frame (3), and the bottom opening of satellite-rocket docking frame (3) is circular; Plate connection box (2) is fixedly mounted on the middle and lower part of main cylinder (1) outer wall privately; The open top of main cylinder (1) is square; Satellite-rocket docking frame (3) realizes the connection with outside carrier rocket satellite support; Main cylinder (1) realizes the connection with outside load dividing plate.
2. a kind of satellite-rocket docking device according to claim 1, is characterized in that: described satellite and the rocket connecting device height h is 500-600mm; The foursquare open top length of side L1 of main cylinder (1) is 700-900mm; The bottom opening diameter L2 of satellite-rocket docking frame (3) circle is 1200-1230mm.
3. a kind of satellite-rocket docking device according to claim 1, is characterized in that: main cylinder (1) comprises plane area and curved regions; Plane area comprises 4 inverted equicrural triangle planes, and equicrural triangle plane is with the foursquare open top length of side L1 of main cylinder (1) for base, and summit is on the bottom frame that satellite-rocket docking frame (3) is circular; Remainder is the curved regions of rounding off.
4. a kind of satellite-rocket docking device according to claim 3, is characterized in that: the long L3 of waist of equicrural triangle plane is 450-600mm; Base angle D is 60-70 °.
5. a kind of satellite-rocket docking device according to claim 1, it is characterized in that: plate connection box (2) comprises loop connecting frame (4) and auricle (5) privately, and auricle (5) horizontal circle is fixed on the outside of loop connecting frame (4).
6. a kind of satellite-rocket docking device according to claim 4, is characterized in that: loop connecting frame (4) over water plane section is circumference shape, and wherein the long L4 of straight flange is 230-250mm; Do the vertical line of straight flange with two end points that adjacent two straight flanges are close, two vertical line joinings are the home position of circular arc, and arc angle A is 85-95 °, and arc radius R1 is 440-460mm.
7. a kind of satellite-rocket docking device according to claim 4, it is characterized in that: plate connection box (2) vertical section is oblique T-shaped privately, plate connection box (2) vertical dimension L8 is 40-44mm privately; Loop connecting frame (4) and horizontal plane angle B are 65-70 °, and thickness L5 is 1.5-2.5mm; Auricle (5) thickness L6 thickness is 2-3mm; The outermost end of auricle (5) is 34-36mm apart from loop connecting frame (4) L7; Auricle (5) upper surface and intersection, loop connecting frame (4) outside arrange the circular arc that radius R 2 is 5-7mm; Auricle (5) lower surface and intersection, loop connecting frame (4) outside arrange the circular arc that radius R 3 is 5-7mm; Auricle (5) lower surface is 19-21mm apart from the lower end L9 of loop connecting frame (4).
8. a kind of satellite-rocket docking device according to claim 1, it is characterized in that: satellite-rocket docking frame (3) horizontal section is circular shape, and centre arranges through hole, through-hole diameter L10 is 1170-1180mm.
9. a kind of satellite-rocket docking device according to claim 7, is characterized in that: the vertical section of satellite-rocket docking frame (3) is special-shaped device, and wherein upper horizontal limit L11 is 2-3mm; Inner vertical limit L12 is 38-40mm; Through-hole wall is 29-30mm to inner vertical back gauge L13; Through hole wall thickness L14 is 5-7mm; Interior wing base and intersection, inner vertical limit are provided with the circular arc that radius R 4 is 9-11mm; Satellite-rocket docking frame (3) outer wall hypotenuse and vertical direction angle C are 4-6 °; Outer wall horizontal sides L15 is long is 2-3mm, and outer wall vertical edge corner arranges the circular arc that radius R 5 is 4-5mm; Outer wall base height L16 is 4-6mm; Satellite-rocket docking frame (3) high L17 is 55-60mm.
10. a kind of satellite-rocket docking device according to claim 1, is characterized in that: each limit of main cylinder (1) inwall is provided with vertical setting of types reinforced rib; Main cylinder (1) outer wall and corner are provided with the device connecting corner strip of vertical setting of types.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510860244.1A CN105438503B (en) | 2015-11-30 | 2015-11-30 | A kind of satellite-rocket docking device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510860244.1A CN105438503B (en) | 2015-11-30 | 2015-11-30 | A kind of satellite-rocket docking device |
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| CN105438503A true CN105438503A (en) | 2016-03-30 |
| CN105438503B CN105438503B (en) | 2018-02-09 |
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| CN201510860244.1A Active CN105438503B (en) | 2015-11-30 | 2015-11-30 | A kind of satellite-rocket docking device |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106015238A (en) * | 2016-06-02 | 2016-10-12 | 北京航空航天大学 | Rotation driving docking mechanism with fault tolerance characteristic |
| CN107380487A (en) * | 2017-06-06 | 2017-11-24 | 上海卫星工程研究所 | Integration side turns round satellite and the rocket connection ring |
| CN109050989A (en) * | 2018-08-29 | 2018-12-21 | 上海宇航系统工程研究所 | A kind of double star point type adapter |
| CN109481864A (en) * | 2017-09-11 | 2019-03-19 | 江苏中豪神庞科技有限公司 | A kind of people's air defense special filtering absorber inlet/outlet air diffuser integral connecting structure |
| CN113911393A (en) * | 2021-09-29 | 2022-01-11 | 北京空间飞行器总体设计部 | Cone-prism transition type honeycomb interlayer bearing cylinder structure |
| CN114394259A (en) * | 2021-12-28 | 2022-04-26 | 航天东方红卫星有限公司 | Main load-bearing structure of satellite with satellite-rocket four-point connection |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6286787B1 (en) * | 1999-07-09 | 2001-09-11 | Aero Astro, Inc. | Small satellite GEO-to-LEO orbit transfer vehicle |
| CN101381003A (en) * | 2008-09-19 | 2009-03-11 | 航天东方红卫星有限公司 | Main load-carrying structure of spacecraft |
| CN102009746A (en) * | 2010-11-08 | 2011-04-13 | 航天东方红卫星有限公司 | Octagonal battery-equipped array upright post micro satellite configuration |
| CN103963997A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Small satellite polygonal force bearing barrel |
| CN204056318U (en) * | 2014-07-15 | 2014-12-31 | 上海微小卫星工程中心 | A kind of satellite structure being applicable to GNSS LEO occultation |
| CN104443431A (en) * | 2014-10-23 | 2015-03-25 | 上海卫星工程研究所 | Triangular satellite configuration and system and assembly method |
-
2015
- 2015-11-30 CN CN201510860244.1A patent/CN105438503B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6286787B1 (en) * | 1999-07-09 | 2001-09-11 | Aero Astro, Inc. | Small satellite GEO-to-LEO orbit transfer vehicle |
| CN101381003A (en) * | 2008-09-19 | 2009-03-11 | 航天东方红卫星有限公司 | Main load-carrying structure of spacecraft |
| CN102009746A (en) * | 2010-11-08 | 2011-04-13 | 航天东方红卫星有限公司 | Octagonal battery-equipped array upright post micro satellite configuration |
| CN103963997A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Small satellite polygonal force bearing barrel |
| CN204056318U (en) * | 2014-07-15 | 2014-12-31 | 上海微小卫星工程中心 | A kind of satellite structure being applicable to GNSS LEO occultation |
| CN104443431A (en) * | 2014-10-23 | 2015-03-25 | 上海卫星工程研究所 | Triangular satellite configuration and system and assembly method |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106015238A (en) * | 2016-06-02 | 2016-10-12 | 北京航空航天大学 | Rotation driving docking mechanism with fault tolerance characteristic |
| CN107380487A (en) * | 2017-06-06 | 2017-11-24 | 上海卫星工程研究所 | Integration side turns round satellite and the rocket connection ring |
| CN107380487B (en) * | 2017-06-06 | 2020-11-24 | 上海卫星工程研究所 | Integrated square-to-round satellite-rocket connecting ring |
| CN109481864A (en) * | 2017-09-11 | 2019-03-19 | 江苏中豪神庞科技有限公司 | A kind of people's air defense special filtering absorber inlet/outlet air diffuser integral connecting structure |
| CN109050989A (en) * | 2018-08-29 | 2018-12-21 | 上海宇航系统工程研究所 | A kind of double star point type adapter |
| CN113911393A (en) * | 2021-09-29 | 2022-01-11 | 北京空间飞行器总体设计部 | Cone-prism transition type honeycomb interlayer bearing cylinder structure |
| CN114394259A (en) * | 2021-12-28 | 2022-04-26 | 航天东方红卫星有限公司 | Main load-bearing structure of satellite with satellite-rocket four-point connection |
| CN114394259B (en) * | 2021-12-28 | 2023-07-14 | 航天东方红卫星有限公司 | Main bearing structure of satellite-rocket four-point connection satellite |
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|---|---|
| CN105438503B (en) | 2018-02-09 |
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