CN103612774A - Separable micro and nano-satellite configuration - Google Patents
Separable micro and nano-satellite configuration Download PDFInfo
- Publication number
- CN103612774A CN103612774A CN201310591599.6A CN201310591599A CN103612774A CN 103612774 A CN103612774 A CN 103612774A CN 201310591599 A CN201310591599 A CN 201310591599A CN 103612774 A CN103612774 A CN 103612774A
- Authority
- CN
- China
- Prior art keywords
- propulsion module
- side plate
- satellite
- micro
- nano
- 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.)
- Granted
Links
Images
Landscapes
- Photovoltaic Devices (AREA)
Abstract
The invention discloses separable micro and nano-satellite configuration which comprises a satellite body, a plurality of separate release sub-satellites, mechanical net claws, a flexible solar cell array and a variable-structure mechanical arm. The separable micro and nano-satellite configuration has the advantages that the integral separable micro and nano-satellite configuration is in such a configuration form that a primary satellite carries the multiple sub-satellites, and functions of separately releasing and hovering the micro and nano-satellites can be realized; the efficiency of the solar cell array can be improved owing to combined configuration comprising flexible solar wings and the variable-structure mechanical arm; mechanical net claw mechanisms are carried on the micro and nano-satellites, so that a function of capturing space targets can be realized; the separable micro and nano-satellite configuration is provided with a plurality of stereoscopic vision imaging cameras, so that a stereoscopic monitoring function can be realized; attitude maneuver and attitude stabilization of the micro and nano-satellites can be implemented by the aid of a solid miniature propulsion technology, so that the sub-satellite separate release control ability can be improved; the separable micro and nano-satellite configuration is applicable to fifty-kilogram-level micro-miniature artificial earth satellites on near-earth orbits and is also applicable to micro-satellite networking, scientific detection aircrafts and relevant micro and nano-satellite space demonstration and experiments.
Description
Technical field
The invention belongs to aerospacecraft structure design field, specifically, relate to a kind of detachable micro-nano satellite configuration.
Background technology
Space Demonstrator Trials refers to the integrated advanced person's of platform via satellite testing of new technique load, the new unit product of development, makes it under space environment, verify capacity weight and the function of unit product and the engineering test of performance.Commercialization, seriation, miniaturization development along with China's micro-nano satellite, increasing novel capacity weight, unit product needed obtain technological breakthrough by the mode of space Demonstrator Trials, require that satellite configuration adapts to modularization, separable release, the lead time is short and requirement cheaply.The capacity weight of conventional satellite configuration and stand-alone device are all permanently affixed on satellite, do not have separated release function, requirement that can not meeting spatial Demonstrator Trials.Compare with domestic and international conventional satellite, detachable satellite configuration adopts the configuration form of being carried many subsatellites by female satellite, and the separation that realizes micro-nano satellite discharges, hovering function; By the flexible sun wing and change construction machine arm combination configuration, improve efficiency of solar array; On micro-nano satellite, carry mechanically-laid web pawl mechanism, the catching function of implementation space target; Many camera stereo vision imagings are set, have realized stereoscopic monitoring function; Adopt solid minisize push technology, realize attitude maneuver and the attitude stabilization of micro-nano satellite, improve the separated control ability that discharges subsatellite.
Summary of the invention
The present invention proposes a kind of detachable micro-nano satellite configuration, is applicable to the detachable micro-nano satellite configuration of 50 feather weight of near-earth orbit; The whole star of satellite is hexahedron configuration, adopts the configuration form of being carried many subsatellites by female satellite, realizes receiving that the separation of satellite discharges, hovering function; Adopt the flexible sun wing and become construction machine arm combination configuration, improve efficiency of solar array; On micro-nano satellite, carry mechanically-laid web pawl mechanism, the catching function of implementation space target; Many camera stereo vision imagings are set, have realized stereoscopic monitoring function; Adopt solid minisize push technology, realize attitude maneuver and the attitude stabilization of micro-nano satellite, improve the separated control ability that discharges subsatellite.
The technical solution adopted for the present invention to solve the technical problems is: comprise satellite body, flexible solar cell array, change construction machine arm, separated subsatellite, the mechanically-laid web pawl of discharging, be characterized in, satellite body comprises platform cabin and propulsion module two parts, platform freight space is in the top of propulsion module, separated release subsatellite is arranged on four jiaos of platform ceiling board top, by locating piece and lock bolt, be connected, under disengagement gear effect, realize locking, the separated release of release, mechanically-laid web pawl is arranged on middle part, platform ceiling board top; Flexible solar cell array is fixed on the side of satellite body, becomes the another side that construction machine arm is fixed on satellite body, and becomes construction machine arm and the symmetrical installation of flexible solar cell array;
Described propellant tank adopts cross configuration flange, be connected with one end of the first propulsion module dividing plate, the second propulsion module dividing plate, the 3rd propulsion module dividing plate, the 4th propulsion module dividing plate respectively, the other end of the other end of the first propulsion module dividing plate and the second propulsion module dividing plate is connected with the positive Y side plate of propulsion module two ends respectively, the other end of the other end of the 3rd propulsion module dividing plate and the 4th propulsion module dividing plate is connected with the negative Y side plate of propulsion module two ends respectively, is bolted formation propulsion module between each plate; Thruster unit is positioned at propulsion module; On the positive Y side plate of propulsion module, have square interface, the positive Y side plate of flexible solar cell array and propulsion module is connected, and adopts in receiver and buries celestial body structure; On the negative Y side plate of propulsion module, have two square interfaces and a manhole, become construction machine arm and be arranged on the negative Y side plate of propulsion module, pinch device is embedded in the box of propulsion module side plate, and driver train is arranged on propulsion module side plate bottom;
Described carriage is fixedly mounted on platform ceiling board, and platform ceiling board and platform ceiling board are bolted and form platform cabin respectively and between the negative Y side plate of the positive Y side plate in platform cabin, platform cabin, the positive Z side plate in platform cabin, the negative Z side plate in platform cabin.
The negative Y side plate of the positive Y side plate of described propulsion module and described propulsion module is lightweight aluminium cellular composite material sandwich plate.
Described propulsion module dividing plate adopts high-strength aluminium alloy plate.
Each adapter plate of described platform cabin is lightweight aluminium cellular composite material sandwich plate.
Beneficial effect
A kind of detachable micro-nano satellite configuration that the present invention proposes, is comprised of satellite body, separated release subsatellite, mechanically-laid web pawl, flexible solar cell array, change construction machine arm; Whole satellite configuration adopts the configuration form of being carried many subsatellites by female satellite, and separated release subsatellite is connected by locating piece and lock bolt, realizes locking, the separated function that discharges, hovers of release under disengagement gear effect; Adopt the flexible sun wing and become construction machine arm combination configuration, improve efficiency of solar array; On micro-nano satellite, carry mechanically-laid web pawl mechanism, the catching function of implementation space target; Many camera stereo vision imagings are set, have realized stereoscopic monitoring function; Adopt solid minisize push technology, realize attitude maneuver and the attitude stabilization of micro-nano satellite, improve the separated control ability that discharges subsatellite.Detachable micro-nano satellite configuration is applicable to apply in 50 feather weight microminiature artificial earths satellite of near-earth orbit, also can be applicable to microsatellite networking and scientific exploration aircraft, on the surveillance satellite of following Chinese Space station, also has potential using value.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, a kind of detachable micro-nano satellite configuration of the present invention is described in further detail.
Fig. 1 is the composition schematic diagram of the detachable micro-nano satellite configuration of the present invention.
Fig. 2 is the configuration of the detachable micro-nano satellite emission state of the present invention.
Fig. 3 is the detachable micro-nano satellite of the present invention configuration of state of flight in-orbit.
In figure:
1. separated negative Y side plate 16. the 3rd propulsion module dividing plate 17. in 13. mechanically-laid web pawl 14. positive Z side plate 15. platform cabins, platform cabin, subsatellite that discharges of the negative Z side plate 10. positive Y side plate 11. platform ceiling boards 12. in platform cabin in the propellant tank 2. first propulsion module dividing plate 3. thruster unit 4. flexible solar cell array positive Y side plate of 5. propulsion module 6. second propulsion module dividing plate 7. platform ceiling board 8. carriage 9. platform cabins becomes negative Y side plate 19. the 4th propulsion module dividing plate of construction machine arm 18. propulsion modules
The specific embodiment
The present embodiment is a kind of detachable micro-nano satellite configuration.
Consult Fig. 1, Fig. 2, Fig. 3, the detachable micro-nano satellite configuration of the present invention, by satellite body, flexible solar cell array 4, change construction machine arm 17, separated release subsatellite 12 and mechanically-laid web pawl 13, formed, satellite body comprises platform cabin and propulsion module two parts, platform cabin is fixed on the top of propulsion module, separated release subsatellite 12 is arranged on four jiaos of platform ceiling board 11 tops, by locating piece, is fixedly connected with lock bolt, and realization locking under disengagement gear effect, release separation discharge; Mechanically-laid web pawl 13 is fixedly mounted on platform ceiling board 11 middle parts, top; Flexible solar cell array 4 is fixed on the side of satellite body, becomes the another side that construction machine arm 17 is fixed on satellite body, and becomes construction machine arm 17 and flexible solar cell array 4 symmetrical installation on coaxial line.
The propulsion module of satellite body is comprised of the first propulsion module dividing plate 2, the second propulsion module dividing plate 6, the 3rd propulsion module dividing plate 16, the 4th propulsion module dividing plate 19, the positive Y side plate 5 of propulsion module, the negative Y side plate 18 of propulsion module and propellant tank 1, thruster unit 3 and pipeline thereof; Platform cabin is comprised of platform ceiling board 7, platform ceiling board 11, the positive Y side plate 10 in platform cabin, the negative Y side plate 15 in platform cabin, the positive Z side plate 14 in platform cabin, the negative Z side plate 9 in platform cabin and carriage 8.Propulsion module external envelope is of a size of 500mm * 500mm * 400mm, adopts bolt to be connected each adapter plate with screw, guarantees the rigidity of propulsion module.The positive Y side plate 5 of propulsion module adopts the aluminium cellular composite material sandwich plate of the light durable that oad is 500mm * 407mm * 10mm, for flexible solar cell array 4 provides installation mechanical interface.Flexible solar cell array is arranged on the positive Y side plate of propulsion module, adopts in receiver and buries celestial body structure.The negative Y side plate 18 of propulsion module adopts the lightweight aluminium cellular composite material sandwich plate that oad is 500mm * 407mm * 10mm, become construction machine arm 17 and be arranged on the negative Y side plate of propulsion module, pinch device is embedded in the box of propulsion module side plate, driver train is arranged on propulsion module side plate bottom.Become construction machine arm tighten up external envelope under state into: 552mm * 400mm * 80mm, the external envelope under deployed condition is completely: 1382mm * 400mm * 10mm.
The first propulsion module dividing plate 2, the second propulsion module dividing plate 6, the 3rd propulsion module dividing plate 16, the 4th propulsion module dividing plate 19 are of a size of 400mm * 306mm * 3mm, adopt the thick high-strength aluminium alloy plate material of 3mm, be bolted with propellant tank 1 flange, adopt screw to connect the rigidity of guaranteeing dividing plate.Platform out of my cabin envelope is of a size of 500mm * 500mm * 300mm, adopts screw fastening to guarantee the rigidity in platform cabin.Platform ceiling board 7 is of a size of 480mm * 480mm * 15mm, adopts the aluminium cellular composite material sandwich plate of light durable, for carriage 8 provides mounting interface.Platform ceiling board 11 is of a size of 590mm * 480mm * 10mm, adopts the aluminium cellular composite material sandwich plate of light durable, for mechanically-laid web pawl 13, separated subsatellite 12 units that discharge provide mounting interface.The positive Y side plate 10 in platform cabin is all 480mm * 282mm * 10mm with negative Y side plate 15 sizes in platform cabin, adopts light durable aluminium cellular composite material sandwich plate, and the mounting interface that monitors camera unit is provided.The positive Z side plate 14 in platform cabin is all 500mm * 300mm * 10mm with negative Z side plate 9 sizes in platform cabin, adopts light durable aluminium cellular composite material sandwich plate.
The detachable micro-nano satellite configuration of the present invention fitting process:
Propellant tank 1 adopts cross configuration flange, combine assembling with the first propulsion module dividing plate 2, the second propulsion module dividing plate 6, the 3rd propulsion module dividing plate 16, the 4th propulsion module dividing plate 19 successively, one end of one end of the first propulsion module dividing plate 2 and the second propulsion module dividing plate 6 is fixedly connected with the positive Y side plate of propulsion module 5 two ends respectively, one end of one end of the 3rd propulsion module dividing plate 16 and the 4th propulsion module dividing plate 19 is fixedly connected with the negative Y side plate of propulsion module 18 two ends respectively, between each adapter plate, by bolt and screw, connects and composes propulsion module; Thruster unit 3 is fixedly mounted in propulsion module; On the positive Y side plate 5 of propulsion module, have square interface, flexible solar cell array 4 is installed, on the negative Y side plate 18 of propulsion module, open two square interfaces and a manhole installation change construction machine arm 17.
Platform cabin is fixed on the top of propulsion module, and carriage 8 is installed on platform ceiling board 7; Carriage 8 is connected with platform ceiling board 11; Between platform ceiling board 7 and platform ceiling board 11, be separately installed with the positive Y side plate 10 in platform cabin, the negative Y side plate 15 in platform cabin, the negative Z side plate 9 in platform cabin, the positive Z side plate 14 in platform cabin, each is installed between side plate and is connected with screw by bolt.
Finally assemble flexible solar cell array 4; Become the another side that construction machine arm 17 is arranged on the satellite body that flexible solar cell array 4 is relative, and become construction machine arm 17 and the symmetrical installation of flexible solar cell array 4 coaxial lines, mechanically-laid web pawl 13 is arranged on platform ceiling board 11 middle parts; Four separated subsatellites 12 that discharge are arranged on respectively quadripolar corners position on platform ceiling board 11, form separation type micro-nano satellite configuration.
Claims (4)
1. a detachable micro-nano satellite configuration, comprise satellite body, flexible solar cell array, change construction machine arm, separated subsatellite, the mechanically-laid web pawl of discharging, it is characterized in that: satellite body comprises platform cabin and propulsion module two parts, platform freight space is in the top of propulsion module, separated release subsatellite is arranged on four jiaos of platform ceiling board top, by locating piece and lock bolt, be connected, under disengagement gear effect, realize locking, the separated release of release, mechanically-laid web pawl is arranged on middle part, platform ceiling board top; Flexible solar cell array is fixed on the side of satellite body, becomes the another side that construction machine arm is fixed on satellite body, and becomes construction machine arm and the symmetrical installation of flexible solar cell array;
Described propellant tank adopts cross configuration flange, be connected with one end of the first propulsion module dividing plate, the second propulsion module dividing plate, the 3rd propulsion module dividing plate, the 4th propulsion module dividing plate respectively, the other end of the other end of the first propulsion module dividing plate and the second propulsion module dividing plate is connected with the positive Y side plate of propulsion module two ends respectively, the other end of the other end of the 3rd propulsion module dividing plate and the 4th propulsion module dividing plate is connected with the negative Y side plate of propulsion module two ends respectively, is bolted formation propulsion module between each plate; Thruster unit is positioned at propulsion module; On the positive Y side plate of propulsion module, have square interface, the positive Y side plate of flexible solar cell array and propulsion module is connected, and adopts in receiver and buries celestial body structure; On the negative Y side plate of propulsion module, have two square interfaces and a manhole, become construction machine arm and be arranged on the negative Y side plate of propulsion module, pinch device is embedded in the box of propulsion module side plate, and driver train is arranged on propulsion module side plate bottom;
Described carriage is fixedly mounted on platform ceiling board, and platform ceiling board and platform ceiling board are bolted and form platform cabin respectively and between the negative Y side plate of the positive Y side plate in platform cabin, platform cabin, the positive Z side plate in platform cabin, the negative Z side plate in platform cabin.
2. detachable micro-nano satellite configuration according to claim 1, is characterized in that: the negative Y side plate of the positive Y side plate of described propulsion module and described propulsion module is lightweight aluminium cellular composite material sandwich plate.
3. detachable micro-nano satellite configuration according to claim 1, is characterized in that: described propulsion module dividing plate adopts high-strength aluminium alloy plate.
4. detachable micro-nano satellite configuration according to claim 1, is characterized in that: each adapter plate of described platform cabin is lightweight aluminium cellular composite material sandwich plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310591599.6A CN103612774B (en) | 2013-11-20 | 2013-11-20 | A kind of detachable micro-nano satellite configuration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310591599.6A CN103612774B (en) | 2013-11-20 | 2013-11-20 | A kind of detachable micro-nano satellite configuration |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103612774A true CN103612774A (en) | 2014-03-05 |
| CN103612774B CN103612774B (en) | 2015-12-09 |
Family
ID=50163504
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310591599.6A Expired - Fee Related CN103612774B (en) | 2013-11-20 | 2013-11-20 | A kind of detachable micro-nano satellite configuration |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103612774B (en) |
Cited By (33)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103935529A (en) * | 2014-04-29 | 2014-07-23 | 上海卫星工程研究所 | Rapid response satellite structure |
| CN103963999A (en) * | 2014-04-08 | 2014-08-06 | 北京控制工程研究所 | Locking and disconnecting device of thrust vector adjustment mechanism |
| CN104071354A (en) * | 2014-05-28 | 2014-10-01 | 上海微小卫星工程中心 | Satellite casing and satellite using same |
| CN104108476A (en) * | 2014-06-24 | 2014-10-22 | 上海宇航系统工程研究所 | Multifunctional solar wing for satellite |
| 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 |
| CN104554826A (en) * | 2014-12-01 | 2015-04-29 | 南京理工大学 | Separate-orbit CubeSat launching device |
| CN104816842A (en) * | 2015-05-18 | 2015-08-05 | 湖北航天技术研究院总体设计所 | Micro/nano-satellite multi-star adaption portion deploy device and application |
| CN105035360A (en) * | 2015-07-31 | 2015-11-11 | 上海卫星工程研究所 | Cabin-segmentation type separable platform configuration based on four-point connection |
| CN105292523A (en) * | 2015-10-27 | 2016-02-03 | 浙江大学 | Separating device and satellite and rocket separating device with buffering structure |
| CN105416610A (en) * | 2014-09-17 | 2016-03-23 | 波音公司 | Space structure deployment system |
| CN105444811A (en) * | 2015-11-30 | 2016-03-30 | 上海卫星工程研究所 | Detachable minor planet detector |
| CN105501471A (en) * | 2015-12-16 | 2016-04-20 | 上海卫星工程研究所 | Configuration of satellite loaded with large deployable antenna with double reflecting surfaces |
| CN105799954A (en) * | 2014-12-31 | 2016-07-27 | 上海新跃仪表厂 | Space-based modular aircraft for conducting decentralized deployment on micro-nano load and orbital transfer guidance method of modular aircraft |
| CN105836162A (en) * | 2016-05-25 | 2016-08-10 | 南京理工大学 | Braking-sail deorbiting device for micro/nano satellite |
| CN105905316A (en) * | 2016-05-10 | 2016-08-31 | 中国人民解放军国防科学技术大学 | Multi-functional bulkhead structure for microsatellite system |
| CN106516172A (en) * | 2016-11-23 | 2017-03-22 | 上海卫星工程研究所 | Device for multi-satellite on-orbit release of micro-nano satellite |
| CN106697336A (en) * | 2016-12-07 | 2017-05-24 | 上海宇航系统工程研究所 | Multi-plate compressing and releasing system |
| CN106986050A (en) * | 2017-03-31 | 2017-07-28 | 西北工业大学 | A kind of many cubes of star combining structures and its changing method |
| CN107487457A (en) * | 2016-06-09 | 2017-12-19 | 波音公司 | Can stacked flat satellite |
| CN108349596A (en) * | 2015-06-22 | 2018-07-31 | 世界卫星有限公司 | Payload distribution system |
| CN108438254A (en) * | 2018-04-18 | 2018-08-24 | 北京空间技术研制试验中心 | Spacecraft system and dispositions method |
| CN108639386A (en) * | 2018-03-29 | 2018-10-12 | 北京空间技术研制试验中心 | Space Rescue Vehicle and the spacecraft for including the rescue flight device |
| CN108674692A (en) * | 2018-04-04 | 2018-10-19 | 南京理工大学 | A kind of remote sensing microsatellite |
| CN109484673A (en) * | 2018-12-24 | 2019-03-19 | 深圳航天东方红海特卫星有限公司 | A kind of payload platform separate type remote sensing micro satellite configuration and its assembly method |
| CN109703784A (en) * | 2019-01-10 | 2019-05-03 | 深圳航天东方红海特卫星有限公司 | Microsatellite based on the comprehensive cabinet of integrated electric |
| CN109850190A (en) * | 2019-02-02 | 2019-06-07 | 中国人民解放军国防科技大学 | Space shape following capture net |
| CN110092013A (en) * | 2019-02-21 | 2019-08-06 | 上海卫星工程研究所 | High split-phase motor bearing structure |
| CN110416775A (en) * | 2019-06-03 | 2019-11-05 | 中国航天时代电子有限公司 | A kind of electromechanics mating interface and the in-orbit restructural aircraft unit based on the interface |
| CN110830103A (en) * | 2019-08-30 | 2020-02-21 | 中国西安卫星测控中心 | Centralized thrust type deployment method for space satellite constellation |
| CN111417575A (en) * | 2017-12-01 | 2020-07-14 | 帝奥瑞波特有限公司 | Method for the secure release of satellites in earth orbit |
| CN111891392A (en) * | 2020-08-11 | 2020-11-06 | 中国科学院微小卫星创新研究院 | Near space continuous flight pico-nano satellite |
| CN111994307A (en) * | 2020-08-21 | 2020-11-27 | 上海利正卫星应用技术有限公司 | Main and sub-satellite system suspension type sub-satellite connecting structure plate |
| CN112777001A (en) * | 2021-01-25 | 2021-05-11 | 中国人民解放军国防科技大学 | Micro-nano satellite accompanied with orbit entry |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3544041A (en) * | 1967-11-07 | 1970-12-01 | Communications Satellite Corp | Deployable flexible solar array |
| US3559919A (en) * | 1967-06-22 | 1971-02-02 | Bolkow Gmbh | Active communication satellite |
| 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 |
| CN103129751A (en) * | 2013-01-18 | 2013-06-05 | 上海卫星工程研究所 | Design method and system of spacecraft based on split-type configuration |
-
2013
- 2013-11-20 CN CN201310591599.6A patent/CN103612774B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3559919A (en) * | 1967-06-22 | 1971-02-02 | Bolkow Gmbh | Active communication satellite |
| US3544041A (en) * | 1967-11-07 | 1970-12-01 | Communications Satellite Corp | Deployable flexible solar array |
| 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 |
| CN103129751A (en) * | 2013-01-18 | 2013-06-05 | 上海卫星工程研究所 | Design method and system of spacecraft based on split-type configuration |
Cited By (52)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103963999A (en) * | 2014-04-08 | 2014-08-06 | 北京控制工程研究所 | Locking and disconnecting device of thrust vector adjustment mechanism |
| CN103963999B (en) * | 2014-04-08 | 2016-02-10 | 北京控制工程研究所 | A kind of thrust vectoring regulating mechanism locking and expanding unit |
| CN103935529B (en) * | 2014-04-29 | 2018-01-12 | 上海卫星工程研究所 | A kind of quick response satellite structure |
| CN103935529A (en) * | 2014-04-29 | 2014-07-23 | 上海卫星工程研究所 | Rapid response satellite structure |
| CN104071354A (en) * | 2014-05-28 | 2014-10-01 | 上海微小卫星工程中心 | Satellite casing and satellite using same |
| CN104071354B (en) * | 2014-05-28 | 2016-07-20 | 上海微小卫星工程中心 | A kind of satellite shell and use the satellite of this housing |
| CN104108476A (en) * | 2014-06-24 | 2014-10-22 | 上海宇航系统工程研究所 | Multifunctional solar wing for satellite |
| CN104108476B (en) * | 2014-06-24 | 2016-07-06 | 上海宇航系统工程研究所 | A kind of satellite multifunctional solar wing |
| CN105416610A (en) * | 2014-09-17 | 2016-03-23 | 波音公司 | Space structure deployment system |
| CN105416610B (en) * | 2014-09-17 | 2018-06-05 | 波音公司 | Space structure body deployment system |
| 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 |
| CN104554826A (en) * | 2014-12-01 | 2015-04-29 | 南京理工大学 | Separate-orbit CubeSat launching device |
| CN105799954A (en) * | 2014-12-31 | 2016-07-27 | 上海新跃仪表厂 | Space-based modular aircraft for conducting decentralized deployment on micro-nano load and orbital transfer guidance method of modular aircraft |
| CN105799954B (en) * | 2014-12-31 | 2018-06-05 | 上海新跃仪表厂 | Space-based disperses the modular aircraft for disposing micro-nano load and its becomes rail method of guidance |
| CN104816842A (en) * | 2015-05-18 | 2015-08-05 | 湖北航天技术研究院总体设计所 | Micro/nano-satellite multi-star adaption portion deploy device and application |
| CN108349596B (en) * | 2015-06-22 | 2021-07-16 | 世界卫星有限公司 | Payload distribution system |
| CN108349596A (en) * | 2015-06-22 | 2018-07-31 | 世界卫星有限公司 | Payload distribution system |
| CN105035360A (en) * | 2015-07-31 | 2015-11-11 | 上海卫星工程研究所 | Cabin-segmentation type separable platform configuration based on four-point connection |
| CN105292523A (en) * | 2015-10-27 | 2016-02-03 | 浙江大学 | Separating device and satellite and rocket separating device with buffering structure |
| CN105444811B (en) * | 2015-11-30 | 2018-08-10 | 上海卫星工程研究所 | Detachable asteroid detection device |
| CN105444811A (en) * | 2015-11-30 | 2016-03-30 | 上海卫星工程研究所 | Detachable minor planet detector |
| CN105501471A (en) * | 2015-12-16 | 2016-04-20 | 上海卫星工程研究所 | Configuration of satellite loaded with large deployable antenna with double reflecting surfaces |
| CN105905316A (en) * | 2016-05-10 | 2016-08-31 | 中国人民解放军国防科学技术大学 | Multi-functional bulkhead structure for microsatellite system |
| CN105836162A (en) * | 2016-05-25 | 2016-08-10 | 南京理工大学 | Braking-sail deorbiting device for micro/nano satellite |
| CN107487457A (en) * | 2016-06-09 | 2017-12-19 | 波音公司 | Can stacked flat satellite |
| CN107487457B (en) * | 2016-06-09 | 2022-07-12 | 波音公司 | Stacked satellite system, launching method thereof and method for manufacturing satellite |
| CN106516172A (en) * | 2016-11-23 | 2017-03-22 | 上海卫星工程研究所 | Device for multi-satellite on-orbit release of micro-nano satellite |
| CN106516172B (en) * | 2016-11-23 | 2019-06-07 | 上海卫星工程研究所 | A kind of device for the more star On-orbit releases of micro-nano satellite |
| CN106697336B (en) * | 2016-12-07 | 2019-02-01 | 上海宇航系统工程研究所 | A kind of more plate compression release systems |
| CN106697336A (en) * | 2016-12-07 | 2017-05-24 | 上海宇航系统工程研究所 | Multi-plate compressing and releasing system |
| CN106986050A (en) * | 2017-03-31 | 2017-07-28 | 西北工业大学 | A kind of many cubes of star combining structures and its changing method |
| CN111417575A (en) * | 2017-12-01 | 2020-07-14 | 帝奥瑞波特有限公司 | Method for the secure release of satellites in earth orbit |
| US11066194B2 (en) | 2017-12-01 | 2021-07-20 | D-ORBIT S.p.A. | Method for the safe release of artificial satellites in earth's orbit |
| CN111417575B (en) * | 2017-12-01 | 2021-07-23 | 帝奥瑞波特有限公司 | Method for the secure release of satellites in earth orbit |
| CN108639386A (en) * | 2018-03-29 | 2018-10-12 | 北京空间技术研制试验中心 | Space Rescue Vehicle and the spacecraft for including the rescue flight device |
| CN108674692A (en) * | 2018-04-04 | 2018-10-19 | 南京理工大学 | A kind of remote sensing microsatellite |
| CN108438254A (en) * | 2018-04-18 | 2018-08-24 | 北京空间技术研制试验中心 | Spacecraft system and dispositions method |
| CN109484673A (en) * | 2018-12-24 | 2019-03-19 | 深圳航天东方红海特卫星有限公司 | A kind of payload platform separate type remote sensing micro satellite configuration and its assembly method |
| CN109703784A (en) * | 2019-01-10 | 2019-05-03 | 深圳航天东方红海特卫星有限公司 | Microsatellite based on the comprehensive cabinet of integrated electric |
| CN109703784B (en) * | 2019-01-10 | 2022-06-03 | 深圳航天东方红海特卫星有限公司 | Microsatellite with integrated electronic integrated case as main body |
| CN109850190B (en) * | 2019-02-02 | 2020-09-18 | 中国人民解放军国防科技大学 | Space shape following capturing device |
| CN109850190A (en) * | 2019-02-02 | 2019-06-07 | 中国人民解放军国防科技大学 | Space shape following capture net |
| CN110092013A (en) * | 2019-02-21 | 2019-08-06 | 上海卫星工程研究所 | High split-phase motor bearing structure |
| CN110416775A (en) * | 2019-06-03 | 2019-11-05 | 中国航天时代电子有限公司 | A kind of electromechanics mating interface and the in-orbit restructural aircraft unit based on the interface |
| CN110830103B (en) * | 2019-08-30 | 2020-12-08 | 中国西安卫星测控中心 | Centralized thrust type deployment method for space satellite constellation |
| CN110830103A (en) * | 2019-08-30 | 2020-02-21 | 中国西安卫星测控中心 | Centralized thrust type deployment method for space satellite constellation |
| CN112977883A (en) * | 2020-08-11 | 2021-06-18 | 中国科学院微小卫星创新研究院 | Thin atmosphere flying pico-nano satellite |
| CN111891392B (en) * | 2020-08-11 | 2021-03-26 | 中国科学院微小卫星创新研究院 | Near space continuous flight pico-nano satellite |
| CN111891392A (en) * | 2020-08-11 | 2020-11-06 | 中国科学院微小卫星创新研究院 | Near space continuous flight pico-nano satellite |
| CN112977883B (en) * | 2020-08-11 | 2023-10-17 | 中国科学院微小卫星创新研究院 | Thin atmospheric flight pico-nano satellite |
| CN111994307A (en) * | 2020-08-21 | 2020-11-27 | 上海利正卫星应用技术有限公司 | Main and sub-satellite system suspension type sub-satellite connecting structure plate |
| CN112777001A (en) * | 2021-01-25 | 2021-05-11 | 中国人民解放军国防科技大学 | Micro-nano satellite accompanied with orbit entry |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103612774B (en) | 2015-12-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103612774A (en) | Separable micro and nano-satellite configuration | |
| CN108674692B (en) | Remote sensing microsatellite | |
| US10017279B2 (en) | Space vehicle comprising posts for forming a stack, stack comprising at least two such vehicles placed in a launcher, and method for releasing the vehicles | |
| CN104443431B (en) | Triangle satellite configuration | |
| US10196143B2 (en) | System and method for modular unmanned aerial system | |
| CN102495621B (en) | Satellite and launch vehicle integrated aerospace system | |
| EP3524520B1 (en) | Solar powered airplane | |
| EP1924495B1 (en) | Modular articulated-wing aircraft | |
| Cook et al. | ISS interface mechanisms and their heritage | |
| CN111003211B (en) | Spacecraft configuration capable of being assembled and expanded in orbit | |
| CN104590585B (en) | Space vehicle based on station two device is served in-orbit and safeguards system and method | |
| US20080179453A1 (en) | Modular airship system and method | |
| US20090302166A1 (en) | Space station, launch vehicle, and method of assembly | |
| CN104943864A (en) | Long-airborne-period combined stratosphere aircraft system scheme based on solar unmanned aerial vehicles | |
| CN106628252B (en) | It is a kind of that orbit aerocraft structure is stayed based on parallel configuration's payload adapter | |
| US20190276129A1 (en) | Modular payload airframe section | |
| CN105416616A (en) | Novel space station extravehicular inspection maintenance unit | |
| CN104340379A (en) | Spaceship whole-journey escape tower and fairing reutilization device combination | |
| CN111038744B (en) | Active capture type spacecraft docking system | |
| WO2012011965A2 (en) | Capsule system, service module, and reuseable reentry payload and docking module | |
| WO2007065175A2 (en) | Reusable space launch, orbital, and re-entry vehicle | |
| EP2799335B1 (en) | A modular aircraft | |
| EA035209B1 (en) | Space platform | |
| CN113148241B (en) | Series load adapter | |
| CN109018341A (en) | It is a kind of can launch mission load land and water landing unmanned plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | 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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151209 Termination date: 20191120 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |