CN202320802U - Nano-satellite separating and unlocking device - Google Patents
Nano-satellite separating and unlocking device Download PDFInfo
- Publication number
- CN202320802U CN202320802U CN2011203899834U CN201120389983U CN202320802U CN 202320802 U CN202320802 U CN 202320802U CN 2011203899834 U CN2011203899834 U CN 2011203899834U CN 201120389983 U CN201120389983 U CN 201120389983U CN 202320802 U CN202320802 U CN 202320802U
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- aircraft adapter
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Abstract
The utility model discloses a nano-satellite separating and unlocking device, which comprises an adapting mechanism primary aircraft adapter connected with a primary aircraft, an adapting mechanism secondary aircraft adapter connected with a secondary aircraft, a locking mechanism, a separating pop-up mechanism and an unlocking mechanism, wherein the locking mechanism locks the primary aircraft adapter and the secondary aircraft adapter, the separating pop-up mechanism is used for providing the secondary aircraft with a certain pop-up force and a pop-up direction after unlocking, and the unlocking mechanism is used for triggering the locking mechanism to remove locking. The nano-satellite separating and unlocking device has the advantages that an overall structure is of a concealed type, and the nano-satellite separating and unlocking device is compact in structure; a concealed type steel ball locking mechanism and the like are reliable in structure, simple and convenient to install and high in impact-bearing capability; a built-in separating spring is adopted, serves as pop-up power while serving as unlocking power and is favorable for control of the direction of mini-satellite separating movement, and overturning after satellite separation can be avoided; and a macromoleclar polymer is heated to generate physical state deformation so as to serve as a mode of driving the unlocking mechanism to unlock, and the generated impact is tiny.
Description
Technical field
The utility model relates to a kind of satellite separation solution locking device of receiving, and belongs to field of space technology.
Background technology
At present, at field of space technology, satellite progressively develops to miniaturization.The skin satellite and the satellite of receiving have advantages such as light weight, volume is little, cost is low, performance is high, the lead time is short, and its weight has only 10 kilograms even littler, are a kind of new trends of current space technology development, have received the generally attention of countries in the world.Therefore, a plurality of skin satellites that carry of space platform or connection and the disengagement gear between the satellite received are to be related to one of the most key factor that can the space platform flight test successful.
The small satellite mode of entering the orbit generally can be divided into two kinds: directly entered the orbit through the emission of several satellite in a rocket technology by the ground carrier rocket, perhaps carry large satellite and launch together.Along with developing rapidly of Large Spacecraft such as space shuttle, space station, receive the favor of various countries as a kind of more economic mode in rail release.At present; Ripe isolation technics is traditional band formula disengagement gear; During general assembly, release spring is fitted between the interface frame, mating frame of carrier rocket band formula disengagement gear on ground, and an end of release spring is fixed on the carrier rocket; The other end withstands on the satellite, by band formula disengagement gear satellite and carrier rocket is coupled together.When satellite and the rocket release separated, explosive bolt release, band opened, satellite and carrier rocket break away from, and compressed release spring stretches satellite is pushed away with certain speed, accomplishes separating action.The shortcoming of above-mentioned explosive bolt tripper is that the bolt explosion time can produce bigger impact and space-pollution; Also possibly produce infringement to satellite; And the oad of tripper and weight are all bigger, therefore, only are fit to being connected between carrier rocket and the large-scale satellite.So, design and a kind ofly be applicable to space platform and receive the disengagement gear that is connected of satellite and become separating of satellite at present in this technical field technical matters anxious to be solved with realizing simultaneously being connected of space platform receiving for many to realize receiving satellite.
The utility model content
The purpose of the utility model be provide in order to solve the problems of the technologies described above that a kind of size is little, in light weight, little, the flexible movements of power consumption can the implementation space platform receive satellite connection with separates release receive satellite separation solution locking device.
The utility model comprises: with the female aircraft adapter of the adaptive mechanism of female aircraft bonded assembly; With the sub-aircraft adapter of the adaptive mechanism of sub-aircraft bonded assembly; The catch gear that female aircraft adapter and sub-aircraft adapter are locked; Be used for giving after the release ejecting mechanism that separates of certain ejection power of sub-aircraft and ejection direction, be used to trigger the release mechanism that catch gear unlocks.
Said female aircraft adapter is the hollow cylinder of band base flange, on the base of the hollow cylinder of said band base flange, through screw release mechanism is installed; Said separation ejecting mechanism is installed in the hollow cylinder of said band base flange; Six circular holes that are used to install the locking steel ball of said catch gear are arranged on the same periphery of hollow cylinder inwall of said band base flange.
The cylinder that said sub-aircraft adapter is the inner wall belt annular groove, the cylinder of said inner wall belt annular groove links to each other sub-aircraft adapter through the connecting thread at top with sub-aircraft.Upper surface in the cylinder of said inner wall belt annular groove and the release spring contact that separates ejecting mechanism; The locking steel ball of the annular groove of sub-aircraft adapter through catch gear links to each other with female aircraft adapter and and then locks with female aircraft.
Said catch gear be with female aircraft adapter and sub-aircraft adapter be linked together parts, its by locking steel ball, collar, hold out against sleeve and form, lock steel ball and be fixed on collar in six circular holes on the hollow cylinder barrel of female aircraft adapter.The locking steel ball to external moving, just in time fastens the annular groove of sub-aircraft adapter under the effect that holds out against sleeve, accomplish locking action.Holding out against sleeve can slide up and down at the inwall of female aircraft adapter, most important to the locking and the release action of whole device.
Said separation ejecting mechanism is formed by holding out against sleeve, release spring and locating dowel pin; The release that is the antithetical phrase aircraft gives the parts of certain ejection power with the control direction.Holding out against sleeve can slide up and down in the cylinder of female aircraft adapter, has the effect of locking and release simultaneously; Release spring uses locating dowel pin to be fixed on and holds out against in the sleeve, and the upper surface that separates spring during locking contacts with the inner core upper surface of sub-aircraft adapter, the effect of existing mechanism release, the power resources that eject as sub-aircraft again.
Said release mechanism is by high molecular polymer base and high molecular polymer and hold out against sleeve and form.High molecular polymer directly is fixed in the square groove of high molecular polymer base, in high molecular polymer inside heating wire is housed.Heating wire energising heating; Make the distortion of high molecular polymer generation states of matter softening; Under the effect of the elastic force of spring, hold out against sleeve and produce downward displacement; Make the catch gear release, the locking steel ball separates with the annular groove of sub-aircraft adapter, and sub-aircraft adapter pops up under the effect that separates ejecting mechanism.
The utlity model has following advantage:
1, overall structure adopts built-inly, and compact conformation has reduced the disconnector amount of parts, has alleviated weight, has dwindled volume, is applicable to receive the interface size of satellite.
2, mechanism such as built-in steel ball locking, reliable in structure, simple installation can be repeatedly used, and it is strong to carry impact capacity, little to the impact of aircraft.
3, release spring is built-in, and is favourable to the control of small satellite disengaging movement direction not only as release power but also as ejecting power, can avoid the upset after satellite separates.
4, adopt the high molecular polymer heating to produce the states of matter distortion as the mode that drives the release mechanism release, the impact of generation is small, can satisfy space platform to the skin satellite with receive being connected and separating release request of satellite.
Description of drawings
Fig. 1-the 1st, the said a kind of overall structure scheme drawing of receiving satellite separation solution locking device of the utility model;
Fig. 1-2 is the A-A direction cutaway view of Fig. 1-1;
Fig. 2-the 1st, the structural representation of the said a kind of female aircraft adapter of receiving satellite separation solution locking device of the utility model;
Fig. 2-the 2nd, the A-A direction cutaway view of Fig. 2-1;
Fig. 3-the 1st, the structural representation of the said a kind of sub-aircraft adapter of receiving satellite separation solution locking device of the utility model;
Fig. 3-the 2nd, the A-A direction cutaway view of Fig. 3-1;
Fig. 4-the 1st, the structural representation of the said a kind of catch gear of receiving satellite separation solution locking device of the utility model;
Fig. 4-the 2nd, the A-A direction cutaway view of Fig. 4-1;
Fig. 5-the 1st, the structural representation of the said a kind of separation ejecting mechanism of receiving satellite separation solution locking device of the utility model;
Fig. 5-the 2nd, the A-A direction cutaway view of Fig. 5-1;
Fig. 6-the 1st, the structural representation of the said a kind of release mechanism of receiving satellite separation solution locking device of the utility model;
Fig. 6-the 2nd, the perspective view of Fig. 6-1.
The specific embodiment
Below in conjunction with accompanying drawing and embodiment the utility model is described in detail.Shown in Fig. 1-1, Fig. 1-2; The utility model comprises: with the female aircraft adapter 1 of the adaptive mechanism of female aircraft bonded assembly; With the sub-aircraft adapter 2 of the adaptive mechanism of sub-aircraft bonded assembly; With the catch gear 3 that female aircraft adapter 1 and sub-aircraft adapter 2 lock, what be used for giving after the release certain ejection power of sub-aircraft and ejection direction separates ejecting mechanism 4, is used to trigger the release mechanism 5 that catch gear 3 unlocks.
Shown in Fig. 2-1, Fig. 2-2, said female aircraft adapter 1 has mounting hole for the hollow cylinder of band base flange on the base flange, can adapter 1 be linked to each other with female aircraft through screw.The size and dimension of female aircraft adapter 1 need not depend on female aircraft main body structure; The size of its base is generally suitable with the female aircraft interface surface size that links to each other, and on the base of the hollow cylinder of said band base flange, through screw release mechanism 5 is installed; In the hollow cylinder of said band base flange, be equipped with and separate ejecting mechanism 4; Six circular holes that are used to install the locking steel ball 3-1 of catch gear 3 are arranged on the same periphery of hollow cylinder inwall of said band base flange.
The utility model with the female aircraft adapter 1 of female aircraft bonded assembly in; Habitual inner clip head formula project organization before not having to adopt; And female aircraft adapter 1 is designed to a hollow cylinder form of being with base; This structure is easy to female aircraft adapter 1 is connected on female aircraft through screw, and the barycenter of the whole disengagement gear of also easy assurance and the barycenter of female aircraft are on same straight line.
Shown in Fig. 3-1, Fig. 3-2, sub-aircraft adapter 2 is the cylinder of inner wall belt annular groove, upper surface in the cylinder of said inner wall belt annular groove and the release spring contact that separates ejecting mechanism 4; The cylinder of said inner wall belt annular groove links to each other sub-aircraft adapter 2 through the screw thread at top with sub-aircraft.The size and dimension of sub-aircraft adapter 2 need not depend on sub-aircraft main body structure, and its overall dimensions is generally little than the sub-aircraft interface surface size that links to each other.The locking steel ball 3-1 of the annular groove of sub-aircraft adapter 2 through catch gear 3 link to each other with female aircraft adapter 1 and and then lock with female aircraft; The in-to-in annular groove of sub-aircraft adapter 2 can link to each other with six locking steel balls that circumferentially are uniformly distributed with; Lock steel ball along the circumference well-distributed for 6 and be installed on the barrel of female aircraft adapter 1, can in the circular hole of barrel, move freely.Holding out against sleeve 3-3 can slide by easy on and off in the inside of female aircraft adapter 1, and the position of restriction steel ball guarantees the effective action of catch gear.Make locking steel ball 3-2 to external moving when upwards holding out against, steel ball just in time is stuck in the inside ringed groove of sub-aircraft adapter 2, mechanism accomplishes locking action; Lose bearing force if hold out against sleeve 3-3 from high molecular polymer; Hold out against sleeve 3-3 and under the effect of spring, produce downward displacement; Sub-aircraft adapter 2 is separated with the locking steel ball; Then aircraft adapter 2 upwards separates under the effect that separates ejecting mechanism 4 together with sub-aircraft, accomplishes the release action.
The utility model with the sub-aircraft adapter 2 of sub-aircraft bonded assembly in, habitual inner clip head formula project organization before equally also not having to adopt, but sub-aircraft adapter 2 is designed to the drum forms of a top band connecting thread.Such structure design is easy to sub-aircraft adapter 2 and sub-aircraft are passed through the screw thread direct connection together, has saved and has used the loaded down with trivial details of screw, and the barycenter of the whole disengagement gear of also easy assurance and the barycenter of female aircraft are on same straight line.
Shown in Fig. 4-1, Fig. 4-2; Catch gear 3 be with female aircraft adapter 1 and sub-aircraft adapter 2 be linked together parts; Its by locking steel ball 3-1, collar 3-2, hold out against sleeve 3-3 and form, lock steel ball 3-1 and be fixed on collar 3-2 in six circular holes on the hollow cylinder barrel of female aircraft adapter 1.Locking steel ball 3-1 to external moving, just in time fastens the annular groove of sub-aircraft adapter 2 under the effect that holds out against sleeve 3-3, accomplish locking action.Holding out against sleeve 3-3 can slide up and down at the inwall of female aircraft adapter 1, most important to the locking and the release action of whole device.
Catch gear 3 can carry load very big in the emission process and impulsive force; Through suitably design and test; Can guarantee enough coupling mechanism forces, can guarantee that again the release flexible movements are reliable, form in the time of can also preventing to separate and separate impulsive force or impact inertia; So that realize the accurate control of separating force; Can avoid excessive coupling mechanism force to form obstacle, when release, can not produce space debris or other pollutants like this, also can any infringement not arranged the capacity weights such as scientific instrument in female aircraft or the sub-aircraft to the release action.
Shown in Fig. 5-1, Fig. 5-2, separate ejecting mechanism 4 and form by holding out against sleeve 3-3, release spring 4-1 and locating dowel pin 4-2; The release that is the antithetical phrase aircraft gives the parts of certain ejection power with the control direction.Holding out against sleeve 3-1 can slide up and down in the cylinder of female aircraft adapter 1, has the effect of locking and release simultaneously; Release spring 4-1 uses locating dowel pin 4-2 to be fixed on and holds out against in the sleeve 3-3, and the upper surface that separates spring 4-1 during locking contacts with the inner core upper surface of sub-aircraft adapter 2, the effect of existing mechanism release, the power resources that eject as sub-aircraft again.
Shown in Fig. 6-1, Fig. 6-2, release mechanism 5 is to be used to make catch gear 3 to change into released state by locking state.Said release mechanism 5 is by high molecular polymer base 5-1 and high molecular polymer 5-2 and hold out against sleeve 3-3 and form.High molecular polymer 5-2 is the core component of whole release mechanism; Release mechanism 5 is again the whole core component of receiving satellite separation solution locking device; It is to realize the key of release that high molecular polymer 5-2 receives thermogenetic states of matter distortion situation, and the data that draw the deflection of high molecular polymer through experiment satisfy the smooth action of release mechanism fully.High molecular polymer 5-2 directly is fixed in the square groove of high molecular polymer base 5-1, in high molecular polymer inside heating wire is housed.Heating wire energising heating; Make the distortion of high molecular polymer generation states of matter softening; Under the effect of the elastic force of spring, hold out against sleeve 3-3 and produce downward displacement, make the catch gear release, the locking steel ball separates with the annular groove of sub-aircraft adapter 2; Sub-aircraft adapter 2 pops up under the effect that separates ejecting mechanism 4, accomplishes the release action.Release mechanism 5 in the utility model is to cause release mechanism through the states of matter variation of controlling high molecular polymer as propulsive effort to move, and makes the steel ball of chucking aircraft carry out release.This release mechanism is installed in the inside that connects the female aircraft adapter of aircraft, and is simple in structure, the release reliable in action.Can replace existing complicated heavy electro-mechanical device fully, realize micro-miniaturisation, lightweight, increase the reliability and the manoevreability of spacecraft.
Present embodiment adopts the release mechanism 5 of new high molecular polymer formula separation solution lock technology; Can separate the release action with activated with energy with less power; Reduce the weight and volume of disengagement gear effectively, overcome the obstacle of coupling mechanism force, produce excessive impact when avoiding separating.The separation solution locking device of present embodiment adopts high-strength aluminum alloy material, can be with the weight control of whole disengagement gear in 100g.
The release ECU of the utility model adopts the little direct supply direct supply of energy consumption.
The above; Be merely the specific embodiment of the utility model; But the protection domain of the utility model is not limited thereto; Any technical personnel of being familiar with the present technique field is in the utility model scope of disclosure, and the variation that can expect easily or replacement all should be encompassed in the protection domain of the utility model claim.
Claims (1)
1. receive satellite separation solution locking device for one kind; It is characterized in that; Comprise: with the female aircraft adapter of the adaptive mechanism of female aircraft bonded assembly, with the sub-aircraft adapter of the adaptive mechanism of sub-aircraft bonded assembly, the catch gear that female aircraft adapter and sub-aircraft adapter are locked; Be used for giving after the release ejecting mechanism that separates of certain ejection power of sub-aircraft and ejection direction, be used to trigger the release mechanism that catch gear unlocks;
Said female aircraft adapter is the hollow cylinder of band base flange, on the base of the hollow cylinder of said band base flange, through screw release mechanism is installed; Said separation ejecting mechanism is installed in the hollow cylinder of said band base flange; Six circular holes that are used to install the locking steel ball of said catch gear are arranged on the same periphery of hollow cylinder inwall of said band base flange;
The cylinder that said sub-aircraft adapter is the inner wall belt annular groove, the cylinder of said inner wall belt annular groove links to each other sub-aircraft adapter through the connecting thread at top with sub-aircraft; Upper surface in the cylinder of said inner wall belt annular groove and the release spring contact that separates ejecting mechanism; The locking steel ball of the annular groove of sub-aircraft adapter through catch gear link to each other with female aircraft adapter and and then lock with female aircraft;
Said catch gear be with female aircraft adapter and sub-aircraft adapter be linked together parts, its by locking steel ball, collar, hold out against sleeve and form, lock steel ball and be fixed on collar in six circular holes on the hollow cylinder barrel of female aircraft adapter; The locking steel ball to external moving, just in time fastens the annular groove of sub-aircraft adapter under the effect that holds out against sleeve, accomplish locking action; Holding out against sleeve can slide up and down at the inwall of female aircraft adapter;
Said separation ejecting mechanism is formed by holding out against sleeve, release spring and locating dowel pin; Holding out against sleeve can slide up and down in the cylinder of female aircraft adapter, and release spring uses locating dowel pin to be fixed on and holds out against in the sleeve, and the upper surface that separates spring during locking contacts with the inner core upper surface of sub-aircraft adapter;
Said release mechanism is by high molecular polymer base and high molecular polymer and hold out against sleeve and form.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203899834U CN202320802U (en) | 2011-10-13 | 2011-10-13 | Nano-satellite separating and unlocking device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203899834U CN202320802U (en) | 2011-10-13 | 2011-10-13 | Nano-satellite separating and unlocking device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202320802U true CN202320802U (en) | 2012-07-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2011203899834U Expired - Fee Related CN202320802U (en) | 2011-10-13 | 2011-10-13 | Nano-satellite separating and unlocking device |
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| Country | Link |
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| CN (1) | CN202320802U (en) |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103010489A (en) * | 2012-12-26 | 2013-04-03 | 浙江大学 | Novel separation mechanism device for controlling nano-satellite and separation method of separation mechanism device |
| CN103010488A (en) * | 2012-11-27 | 2013-04-03 | 中国人民解放军国防科学技术大学 | Micro-nano satellite unlocking and separating device |
| CN103474846A (en) * | 2013-09-04 | 2013-12-25 | 航天东方红卫星有限公司 | Inter-satellite power supplying device |
| CN103615450A (en) * | 2013-12-02 | 2014-03-05 | 北京化工大学 | Spacecraft unlocking and separating device |
| CN103738509A (en) * | 2014-01-21 | 2014-04-23 | 北京航空航天大学 | Novel multi-satellite separating, unlocking and releasing device |
| CN103982101A (en) * | 2014-05-16 | 2014-08-13 | 上海宇航系统工程研究所 | Locking-unlocking screw and cabin door unlocking device |
| CN104908045A (en) * | 2015-05-11 | 2015-09-16 | 上海宇航系统工程研究所 | Space mechanical arm capable of conducting automatic locking and releasing |
| CN105857646A (en) * | 2016-04-08 | 2016-08-17 | 上海机电工程研究所 | Spherical locking separating mechanism |
| CN106184828A (en) * | 2016-08-12 | 2016-12-07 | 上海卫星工程研究所 | It is applied to the double super satellite platform of principal and subordinate's noncontact repeat to lock unlocking mechanism |
| CN106628255A (en) * | 2016-12-28 | 2017-05-10 | 中国科学院长春光学精密机械与物理研究所 | Rotary unlocking type unfolding mechanism |
| CN106742081A (en) * | 2016-11-29 | 2017-05-31 | 航天东方红卫星有限公司 | A kind of separating mechanism based on rotation pressure ring unblock |
| CN108482715A (en) * | 2018-04-17 | 2018-09-04 | 中国科学院西安光学精密机械研究所 | A kind of space unlocking device for locking with unlock expansion function |
| CN113175848A (en) * | 2021-04-28 | 2021-07-27 | 北京星途探索科技有限公司 | Fairing separating mechanism |
| CN113218255A (en) * | 2021-04-28 | 2021-08-06 | 北京星途探索科技有限公司 | Separation mechanism with adjustable radome separation power |
| CN113340159A (en) * | 2021-06-10 | 2021-09-03 | 北京星途探索科技有限公司 | Self-adjusting type rotating throwing fairing separating mechanism |
| CN113772114A (en) * | 2021-10-18 | 2021-12-10 | 贵州航天天马机电科技有限公司 | Aircraft adapter and manufacturing method thereof |
| CN113883972A (en) * | 2021-10-29 | 2022-01-04 | 北京星途探索科技有限公司 | Interstage separation device suitable for small-diameter missile aircraft |
-
2011
- 2011-10-13 CN CN2011203899834U patent/CN202320802U/en not_active Expired - Fee Related
Cited By (25)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103010488A (en) * | 2012-11-27 | 2013-04-03 | 中国人民解放军国防科学技术大学 | Micro-nano satellite unlocking and separating device |
| CN103010488B (en) * | 2012-11-27 | 2015-01-21 | 中国人民解放军国防科学技术大学 | Micro-nano satellite unlocking and separating device |
| CN103010489B (en) * | 2012-12-26 | 2014-12-31 | 浙江大学 | Novel separation mechanism device for controlling nano-satellite and separation method of separation mechanism device |
| CN103010489A (en) * | 2012-12-26 | 2013-04-03 | 浙江大学 | Novel separation mechanism device for controlling nano-satellite and separation method of separation mechanism device |
| CN103474846A (en) * | 2013-09-04 | 2013-12-25 | 航天东方红卫星有限公司 | Inter-satellite power supplying device |
| CN103474846B (en) * | 2013-09-04 | 2015-08-19 | 航天东方红卫星有限公司 | A kind of star electric supply installation |
| CN103615450A (en) * | 2013-12-02 | 2014-03-05 | 北京化工大学 | Spacecraft unlocking and separating device |
| CN103738509A (en) * | 2014-01-21 | 2014-04-23 | 北京航空航天大学 | Novel multi-satellite separating, unlocking and releasing device |
| CN103982101B (en) * | 2014-05-16 | 2016-07-06 | 上海宇航系统工程研究所 | Locking unlocks screw and hatch door locking-unlocking device |
| CN103982101A (en) * | 2014-05-16 | 2014-08-13 | 上海宇航系统工程研究所 | Locking-unlocking screw and cabin door unlocking device |
| CN104908045B (en) * | 2015-05-11 | 2016-10-26 | 上海宇航系统工程研究所 | A kind of auto lock and the space manipulator of release |
| CN104908045A (en) * | 2015-05-11 | 2015-09-16 | 上海宇航系统工程研究所 | Space mechanical arm capable of conducting automatic locking and releasing |
| CN105857646A (en) * | 2016-04-08 | 2016-08-17 | 上海机电工程研究所 | Spherical locking separating mechanism |
| CN106184828A (en) * | 2016-08-12 | 2016-12-07 | 上海卫星工程研究所 | It is applied to the double super satellite platform of principal and subordinate's noncontact repeat to lock unlocking mechanism |
| CN106184828B (en) * | 2016-08-12 | 2018-08-03 | 上海卫星工程研究所 | Locking unlocking mechanism is repeated applied to the non-contact double super satellite platforms of principal and subordinate |
| CN106742081A (en) * | 2016-11-29 | 2017-05-31 | 航天东方红卫星有限公司 | A kind of separating mechanism based on rotation pressure ring unblock |
| CN106628255B (en) * | 2016-12-28 | 2023-03-24 | 中国科学院长春光学精密机械与物理研究所 | Rotary unlocking type unfolding mechanism |
| CN106628255A (en) * | 2016-12-28 | 2017-05-10 | 中国科学院长春光学精密机械与物理研究所 | Rotary unlocking type unfolding mechanism |
| CN108482715A (en) * | 2018-04-17 | 2018-09-04 | 中国科学院西安光学精密机械研究所 | A kind of space unlocking device for locking with unlock expansion function |
| CN108482715B (en) * | 2018-04-17 | 2023-09-01 | 中国科学院西安光学精密机械研究所 | Space locking unlocking device with unlocking and unfolding functions |
| CN113218255A (en) * | 2021-04-28 | 2021-08-06 | 北京星途探索科技有限公司 | Separation mechanism with adjustable radome separation power |
| CN113175848A (en) * | 2021-04-28 | 2021-07-27 | 北京星途探索科技有限公司 | Fairing separating mechanism |
| CN113340159A (en) * | 2021-06-10 | 2021-09-03 | 北京星途探索科技有限公司 | Self-adjusting type rotating throwing fairing separating mechanism |
| CN113772114A (en) * | 2021-10-18 | 2021-12-10 | 贵州航天天马机电科技有限公司 | Aircraft adapter and manufacturing method thereof |
| CN113883972A (en) * | 2021-10-29 | 2022-01-04 | 北京星途探索科技有限公司 | Interstage separation device suitable for small-diameter missile aircraft |
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