CN105292523A - Separating device and satellite and rocket separating device with buffering structure - Google Patents
Separating device and satellite and rocket separating device with buffering structure Download PDFInfo
- Publication number
- CN105292523A CN105292523A CN201510708786.7A CN201510708786A CN105292523A CN 105292523 A CN105292523 A CN 105292523A CN 201510708786 A CN201510708786 A CN 201510708786A CN 105292523 A CN105292523 A CN 105292523A
- Authority
- CN
- China
- Prior art keywords
- satellite
- pull bar
- flange
- damper element
- disengagement gear
- 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.)
- Pending
Links
Landscapes
- Vibration Dampers (AREA)
Abstract
The invention discloses a separating device with a buffering structure. The separating device comprises a main body component, a separating component, pull rods and a pull rod cutting mechanism, wherein the pull rods are connected with the main body component and the separating component and press the main body component on the supporting surface of the separating component. A satellite is provided with a flange, and the ends, connected with the main body component, of the pull rods penetrate from one side of the flange and are locked through fasteners on the other side of the flange. The separating device is characterized in that buffering parts are installed on the side, with the fasteners fixed, of the flange, directly face the ends of the pull rods and are used for preventing half broken pull rods from exiting from the flange. The invention further discloses a satellite and rocket separating device with the buffering structure. According to the invention, the buffering parts are arranged at the ends of the pull rods for absorbing impact generated when the pull rods are broken, a separating buffering device is fixed through a pure mechanical structure, the shock absorbing and buffering effect is remarkable, the structure is simple, installation is convenient, the work is stable, and the development cost is low.
Description
Technical field
The present invention relates to aviation aircraft separation buffer technical field, particularly a kind of disengagement gear with buffer structure and satellite and the rocket disengagement gear.
Background technology
Spacecraft applies a large amount of firer's disengagement gear, as explosive bolt, release screw bolt, pin drift, separation nut, cutter etc., for performing the key operations such as stage separation, release portion assembly, startup or closed portion subsystem, satellite and the rocket separation, solar wing spreading.
Firer's disengagement gear is using the high pressure gas of the priming system of self-contained impact blast generation as power, along with the release of structure predetermincd tension and structural impact during action, these load are passed to each position of spacecraft with stress wave form by structure, the temporary impact response that structure can be caused violent, form severe firer's shock environment, show acceleration amplitude up to 3 × 10
2~ 3 × 10
5g, time length are usually in 20ms, and frequency domain is 10
2~ 10
6hz, the characteristic of acceleration responsive time history thermal agitation.
Firer impacts can when not destroying spacecraft structure, the equipment being provided with shock-sensitive element (as relay, crystal oscillator, pottery, epoxy material, glass hard brittle material, welded joint, welding lead and microelectronic chip etc.) to inside has a negative impact (as fragile member fragmentation, relay flutter, wire break cause short circuit, electronic machine inefficacy in short-term etc.), directly affect the performance of spacecraft.NASA once added up all flight failures between 1963-1985, through failure analysis, directly impacted relevant to firer, accounted for 71.6% for 63 times.In the whole abortive launch of the 1983-1998 U.S., impact relevant to the firer that piece-rate system produces, account for 22.7% for 5 times.Therefore adopt the spacecraft of firer to increase safety method, slow down the impact of firer, protection spacecraft is without prejudice.
In order to solve the problem, researcher is had to set up buffer structure to satellite disengagement gear in prior art, publication number is that the Chinese patent literature of CN104071356A discloses a kind of satellite and the rocket separation transition shock absorber, the linkage interface of traditional satellite and carrier rocket is divided into lower terminal pad and upper terminal pad and cross supporting frame by this device, the lower terminal pad of this device is connected with carrier rocket, it has priming system mounting hole and pressure hole, release spring push rod top; Upper terminal pad is connected with satellite joint, it has priming system and dodges hole and 6 bolt connecting holes; A rigid transition structure and cross supporting frame is increased between lower terminal pad and upper terminal pad, owing to adding a terminal pad, thus add the decrement of impact load when the satellite and the rocket are separated, between upper and lower terminal pad, increase again the distance that rigid transition structure adds shock wave transmission simultaneously, reduce the impact on satellite.This device can realize satellite system irrespective of size buffering, can ensure that satellite whole star rigidity is substantially constant simultaneously, meet the designing requirement of satellite fundamental frequency.
Although said structure has certain buffering effect, in actual use, need to be arranged between satellite and separation member, this produces certain impact to the installation strength of satellite and separation member, reduces the stability of satellite.
Summary of the invention
The invention discloses a kind of disengagement gear with buffer structure, effectively reduced the impact produced between pull bar main element breaking moment and separating component by buffer structure, prevent from causing damage to main element.
A kind of disengagement gear with buffer structure, comprise main element, separating component, pull bar and pull bar shoutoff mechanism, described pull bar connects main element and separating component and is pressed on the bearing surface of separating component by main element, described satellite is provided with flange, one end that described pull bar is connected with main element is passed from the side of this flange and is locked by fastener at the opposite side of flange, described flange is fixed with fastener side and is provided with damper element, and described damper element just exits described flange to the end of described pull bar for the half pull bar blocking disconnection.
When pull bar shoutoff mechanism cuts off pull bar, the pulling force abrupt release of pull bar, the acceleration/accel that the pull bar of cut-out is huge acts on damper element, and impact and be buffered part absorption, main element starts to be separated under the effect of ejecting mechanism with separating component simultaneously.
Pull bar shoutoff mechanism commonly adopts priming system, and cut-off velocity is fast, easy to use.Titanium bar often selected by pull bar, also can adopt other metals.
In order to make, damper element is stable to be installed and location, and preferably, described flange is fixed with and is sleeved on the protective case that described pull bar stretches out flange portion, it is interior between the bottom and the end of pull bar of protective case that described damper element is arranged on protective case.The effect of protective case, mainly in order to locate damper element better, makes it fully can absorb the impact of pull bar disconnection.
The optional type of the material of damper element, shape, structure is a lot, in the present invention, in order to improve buffering effect, preferably, described damper element is the cellular cylinder that multiple hollow six prisms are spliced, and the length direction of described hollow six prisms is identical with the length direction of pull bar.The damper element of said structure has certain intensity, and simultaneously due to its hollow structure, less volume just can the fine enormous impact that must absorb pull bar, the material selection intensity of damper element or durable good 3003/5052 aluminium foil.
Conveniently install, preferably, described fastener is nut, and described pull bar is provided with the screw thread with nut screw connection.Nut locking, easy to operate, easy for removal and installation.Described nut adopts locking double nuts.Described fastener can also be that pull bar is fixed on the structure on flange by other.
The end of described pull bar can have certain gap with damper element, but in order to improve buffering effect, preferably, end and the described damper element of described pull bar push against.Installation requirement is reached by adjustment protective case and damper element height.
The effect having applicable absorption to make described damper element and impact, preferably, the length ratio of the most width position of the hexagonal side length of described hollow six prisms and pull bar cross-sectional plane is 1:6 ~ 1:3.If ratio is excessive, then the cross-sectional plane of six prisms is excessive, causes to absorb impact completely; And ratio is too small, the deleterious that absorption can be made again to impact, makes main element still be impacted.The structure of described damper element is relevant with buffering effect, for skin Nano satellite, the wall thickness of arbitrary hollow six prisms of described cellular cylinder is 0.05 ~ 0.2mm, and the height of cellular cylinder is 8 ~ 12mm, when described cellular cylinder is cylinder, its diameter is 8 ~ 12mm.The structure of all hollow six prisms of described cellular cylinder can be identical, center of can also being arranged to diminishes gradually to the length of side of external hollow six prism, namely central hollow six prismatic cross-sectional is comparatively large, arrangement is more sparse, become intensive to the periphery gradually, the position that damper element and titanium bar can be made directly to contact so is set there is good buffering effect, ensure again the intensity of damper element entirety simultaneously, thus when limited height, more impact energy can be absorbed.
The invention also discloses a kind of satellite and the rocket disengagement gear with buffer gear, structure is simple, easy for installation, reliable, can absorb impulsive force when pull bar is cut off by actv., thus make pull bar depart from satellite and to cause damage to satellite.
A kind of satellite and the rocket disengagement gear with buffer gear, comprise satellite, be separated base plate, pull bar and pull bar shoutoff mechanism, described pull bar connects satellite and is separated base plate and is pressed on by satellite on the bearing surface of separation base plate, described satellite is provided with flange, one end that described pull bar is connected with satellite is passed from the side of this flange and is locked by fastener at the opposite side of flange, the side that described flange is fixed with fastener is provided with damper element, and described damper element just exits described flange to the end of described pull bar for the half pull bar blocking disconnection.
When pull bar shoutoff mechanism (such as priming system) cuts off pull bar (such as titanium bar), the pulling force abrupt release of pull bar, the pull bar cut off acts on damper element with the acceleration/accel of about 186000g (the skin satellite for common), and damper element absorbs, satellite starts to be separated simultaneously.
Steadily be separated to make satellite, reduce impact when being separated, preferably, described separation base plate is fixed with at least one pair of satellite supporting seat, the end face of described satellite supporting seat is the bearing surface supporting satellite, and arbitrary pair of satellite supporting seat is positioned opposite between two, and described pull bar is provided with at least one pair of, often pair of pull bar is arranged in arbitrary pair of satellite supporting seat respectively, and the bearing surface that every root pull bar stretches out corresponding satellite supporting seat is connected with satellite.Damper element one_to_one corresponding pull bar is arranged, more than one pair of the pull bar pulling force can dividing equally satellite and the impact be separated, and satellite is separated more steady.
In order to simplified structure, it is too much that pull bar should not be arranged, make satellite stressed by arranging more satellite supporting seat simultaneously evenly, preferably, it is two right that described satellite supporting seat is provided with, and described pull bar is provided with a pair.
Described pull bar is titanium bar, and described pull bar shoutoff mechanism adopts priming system.Titanium bar intensity is high, and proportion is little, and elite titanium bar matches with priming system, titanium bar cut off after fracture smooth, during separation titanium bar fracture can not hook satellite and affect satellite be separated.Adopt priming system to cut off titanium bar, disconnect rapidly, and impact very little to satellite.Pull bar can also be alloy steel 40Cr, stainless steel 304.
During installation; first being installed by priming system is separated on base plate; the lower end of titanium bar is fixed on and is separated on base plate; then corresponding titanium bar is passed from the hole two flanges of satellite; titanium bar upper end is screwed in until compressed by satellite with nut; damper element is placed in protective case, is buckled in titanium bar upper end, then with screw, protective case is fixed on flange.During separation, titanium bar cuts off by priming system; titanium bar is broken into two joints; the tightening force abrupt release of titanium bar, lower half titanium bar is stayed and is separated on base plate, and impulsive force absorbs by being separated base plate; the impulsive force of the upper half titanium bar is absorbed by damper element and protective case; there is plastic deformation in damper element, absorb a large amount of impacts under huge impact force action, and the upper half titanium bar is owing to there being the fastening effect of nut; protective case and flange can not be departed from, can be separated together along with satellite.
Beneficial effect of the present invention:
The present invention absorbs impact when pull bar disconnects by arranging damper element in the end of pull bar, and fix separation buffer device by pure physical construction, effectively, structure is simple, and easy for installation, working stability, development cost is low for shock-absorbing buffering.
Accompanying drawing explanation
Fig. 1 is the perspective view of the satellite and the rocket disengagement gear with buffer gear of the present invention.
Fig. 2 is the perspective view of another angle of satellite and the rocket disengagement gear with buffer gear of the present invention.
Fig. 3 is the structural representation of protective case of the present invention.
Fig. 4 is the sectional structure schematic diagram of Fig. 3 on A-A direction.
Fig. 5 is the structural representation of another angle of protective case of the present invention.
Fig. 6 is the sectional structure schematic diagram of Fig. 5 on B-B direction.
Fig. 7 is the structural representation of damper element of the present invention.
Fig. 8 is the birds-eye view of Fig. 7.
Fig. 9 is the connection diagram of protective case and pull bar.
Figure 10 is the sectional structure schematic diagram of Fig. 9 on C-C direction.
Detailed description of the invention
As shown in Fig. 1 ~ 10, the disengagement gear with buffer structure of the present embodiment is applied in the satellite and the rocket disengagement gear in satellite and the rocket separation, comprise: satellite 1, be separated base plate 2, two protective cases 3, two damper elements 4, two titanium bars 5, four nuts 6, four screws 7, four bullet pads and plain cushion, priming system 8, satellite ejecting mechanism 9 and four satellite supporting seats 10, each damper element 4 is placed in a protective case 3, satellite 1 is provided with two flanges 101 connecting titanium bar 5, the protective case 3 that damper element 4 is housed is contained on satellite flange 101, nut 6 adopts pairs of anti-loose nut structure.
The diameter of the titanium bar 5 of the present embodiment is 4mm, and damper element 4 is the cellular cylinder of hollow six prism compositions, and be highly 10mm, diameter is 10mm, and hollow six prismatic cross-sectional are regular hexagon, and the length of side is 1.5mm, and the wall thickness of hollow six prisms is 0.04 ~ 0.2mm.
When the present embodiment is installed; first priming system 8 and satellite supporting seat 10 being arranged on is separated on base plate 2; the lower end of titanium bar 5 is fixed on and is separated on base plate 2; the upper end of titanium bar 5 is passed from the hole the flange 101 of satellite; titanium bar 5 upper end is screwed in until be pressed on satellite supporting seat 10 by satellite 1 with nut 6; damper element 4 is placed in protective case, is buckled in titanium bar 5 upper end, then with screw 7, protective case 3 is fixed on flange 101.During separation, titanium bar 5 cuts off by priming system; 5 sections, titanium bar becomes two joints; the tightening force abrupt release of titanium bar 5, lower half-section titanium bar 5 is stayed and is separated on base plate 2, and impulsive force absorbs by being separated base plate 2; the impulsive force of upper half-section titanium bar 5 is absorbed by damper element 4 and protective case 3; there is plastic deformation in damper element 4, absorb a large amount of impacts under huge impact force action, and upper half-section titanium bar 5 is owing to there being the fastening effect of nut 6; the mounting hole of protective case 3 and flange 101 can not be departed from, can be separated together along with satellite.
When priming system 8 cuts off titanium bar 5, the pulling force abrupt release of titanium bar 5, the present embodiment is skin Nano satellite, and the titanium bar 5 of cut-out acts on damper element 4 and protective case 3 with the acceleration/accel of about 186000g, and is buffered part 4 and protective case absorption, and satellite starts to be separated simultaneously.
Conveniently install, two pairs of protective cases 3 and damper element 4 are arranged symmetrically with on satellite.By being arranged symmetrically with, damper element 4 and protective case 3 absorb huge impact, and the device in protection satellite, also prevents titanium bar 5 from departing from Satellite To Satellite simultaneously and cause damage.
Claims (9)
1. the disengagement gear with buffer structure, comprise main element, separating component, pull bar and pull bar shoutoff mechanism, described pull bar connects main element and separating component and is pressed on the bearing surface of separating component by main element, described satellite is provided with flange, one end that described pull bar is connected with main element is passed from the side of this flange and is locked by fastener at the opposite side of flange, it is characterized in that, described flange is fixed with fastener side and is provided with damper element, described damper element just exits described flange to the end of described pull bar for the half pull bar blocking disconnection.
2. as claimed in claim 1 with the disengagement gear of buffer structure; it is characterized in that; described flange is fixed with and is sleeved on the protective case that described pull bar stretches out flange portion, it is interior between the bottom and the end of pull bar of protective case that described damper element is arranged on protective case.
3., as claimed in claim 1 with the disengagement gear of buffer structure, it is characterized in that, described damper element is the cellular cylinder that multiple hollow six prisms are spliced, and the length direction of described hollow six prisms is identical with the length direction of pull bar.
4., as claimed in claim 1 with the disengagement gear of buffer structure, it is characterized in that, described fastener is nut, and described pull bar is provided with the screw thread with nut screw connection.
5., as claimed in claim 1 with the disengagement gear of buffer structure, it is characterized in that, end and the described damper element of described pull bar push against.
6. as claimed in claim 3 with the disengagement gear of buffer structure, it is characterized in that, the length ratio of the most width position of the hexagonal side length of described hollow six prisms and pull bar cross-sectional plane is 1:6 ~ 1:3.
7. the satellite and the rocket disengagement gear with buffer gear, comprise satellite, be separated base plate, pull bar and pull bar shoutoff mechanism, described pull bar connects satellite and is separated base plate and is pressed on by satellite on the bearing surface of separation base plate, described satellite is provided with flange, one end that described pull bar is connected with satellite is passed from the side of this flange and is locked by fastener at the opposite side of flange, it is characterized in that, the side that described flange is fixed with fastener is provided with damper element, and described damper element just exits described flange to the end of described pull bar for the half pull bar blocking disconnection.
8. as claimed in claim 7 with the satellite and the rocket disengagement gear of buffer gear, it is characterized in that, described separation base plate is fixed with at least one pair of satellite supporting seat, the end face of described satellite supporting seat is the bearing surface supporting satellite, arbitrary pair of satellite supporting seat is positioned opposite between two, described pull bar is provided with at least one pair of, and often pair of pull bar is arranged in arbitrary pair of satellite supporting seat respectively, and the bearing surface that every root pull bar stretches out corresponding satellite supporting seat is connected with satellite.
9. as claimed in claim 8 with the satellite and the rocket disengagement gear of buffer gear, it is characterized in that, it is two right that described satellite supporting seat is provided with, and described pull bar is provided with a pair.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510708786.7A CN105292523A (en) | 2015-10-27 | 2015-10-27 | Separating device and satellite and rocket separating device with buffering structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510708786.7A CN105292523A (en) | 2015-10-27 | 2015-10-27 | Separating device and satellite and rocket separating device with buffering structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105292523A true CN105292523A (en) | 2016-02-03 |
Family
ID=55190510
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510708786.7A Pending CN105292523A (en) | 2015-10-27 | 2015-10-27 | Separating device and satellite and rocket separating device with buffering structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105292523A (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043744A (en) * | 2016-07-11 | 2016-10-26 | 上海宇航系统工程研究所 | Point type satellite and rocket connection unlocking mechanism |
| CN106052490A (en) * | 2016-07-11 | 2016-10-26 | 上海宇航系统工程研究所 | Satellite-rocket point type connection and separation module and device |
| CN106143954A (en) * | 2016-07-11 | 2016-11-23 | 上海宇航系统工程研究所 | Point type connects tripper |
| CN106482970A (en) * | 2016-09-30 | 2017-03-08 | 北京强度环境研究所 | A kind of spacecraft Explosive separation guide type safe retrieving assay device |
| CN106481633A (en) * | 2016-11-02 | 2017-03-08 | 北京空间机电研究所 | A kind of low impact high-mechanic firer's release screw bolt |
| CN107054700A (en) * | 2017-03-30 | 2017-08-18 | 哈尔滨工业大学（威海） | A kind of satellite and the rocket separation locking releasing device |
| CN107837857A (en) * | 2017-12-11 | 2018-03-27 | 贵州大学 | A kind of colliery is with the cinder mashing device detachably used |
| CN109050987A (en) * | 2018-08-08 | 2018-12-21 | 上海宇航系统工程研究所 | One discharge plate chain type satellite and the rocket connection solution lock machine |
| CN110884694A (en) * | 2019-11-04 | 2020-03-17 | 上海宇航系统工程研究所 | Compressing and releasing mechanism capable of reducing spacecraft envelope |
| CN112373734A (en) * | 2020-11-24 | 2021-02-19 | 东方红卫星移动通信有限公司 | Low-orbit satellite group emission satellite-arrow separation unlocking module and satellite-arrow separation method |
| CN113280695A (en) * | 2021-06-10 | 2021-08-20 | 北京星途探索科技有限公司 | But single face reassembling type disengaging structure device |
| CN114963892A (en) * | 2021-02-19 | 2022-08-30 | 北京九天微星科技发展有限公司 | Connecting and unlocking device suitable for multi-satellite separation |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03148400A (en) * | 1989-11-02 | 1991-06-25 | Natl Space Dev Agency Japan<Nasda> | Combining/removing method of satellite, rocket, and apogee-kick engine |
| 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 |
| CN103318425A (en) * | 2013-06-25 | 2013-09-25 | 上海宇航系统工程研究所 | Tie rod type connecting and unlocking device |
| CN103612774A (en) * | 2013-11-20 | 2014-03-05 | 西北工业大学 | Separable micro and nano-satellite configuration |
| CN104071356A (en) * | 2014-05-23 | 2014-10-01 | 北京空间飞行器总体设计部 | Satellite-rocket separation transition buffering device |
| CN104290927A (en) * | 2014-09-12 | 2015-01-21 | 上海卫星工程研究所 | One-way impact isolating device for satellite |
| CN104527997A (en) * | 2015-01-20 | 2015-04-22 | 浙江大学 | Synchronizing device used for being connected with and unlocking satellite |
-
2015
- 2015-10-27 CN CN201510708786.7A patent/CN105292523A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03148400A (en) * | 1989-11-02 | 1991-06-25 | Natl Space Dev Agency Japan<Nasda> | Combining/removing method of satellite, rocket, and apogee-kick engine |
| 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 |
| 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 |
| CN103318425A (en) * | 2013-06-25 | 2013-09-25 | 上海宇航系统工程研究所 | Tie rod type connecting and unlocking device |
| CN103612774A (en) * | 2013-11-20 | 2014-03-05 | 西北工业大学 | Separable micro and nano-satellite configuration |
| CN104071356A (en) * | 2014-05-23 | 2014-10-01 | 北京空间飞行器总体设计部 | Satellite-rocket separation transition buffering device |
| CN104290927A (en) * | 2014-09-12 | 2015-01-21 | 上海卫星工程研究所 | One-way impact isolating device for satellite |
| CN104527997A (en) * | 2015-01-20 | 2015-04-22 | 浙江大学 | Synchronizing device used for being connected with and unlocking satellite |
Non-Patent Citations (1)
| Title |
|---|
| 刘荣强等: "腿式着陆器缓冲材料缓冲特性及其表征方法研究", 《宇航学报》 * |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106052490A (en) * | 2016-07-11 | 2016-10-26 | 上海宇航系统工程研究所 | Satellite-rocket point type connection and separation module and device |
| CN106143954A (en) * | 2016-07-11 | 2016-11-23 | 上海宇航系统工程研究所 | Point type connects tripper |
| CN106043744A (en) * | 2016-07-11 | 2016-10-26 | 上海宇航系统工程研究所 | Point type satellite and rocket connection unlocking mechanism |
| CN106482970A (en) * | 2016-09-30 | 2017-03-08 | 北京强度环境研究所 | A kind of spacecraft Explosive separation guide type safe retrieving assay device |
| CN106481633B (en) * | 2016-11-02 | 2019-04-09 | 北京空间机电研究所 | A kind of low impact high-mechanic firer's release screw bolt |
| CN106481633A (en) * | 2016-11-02 | 2017-03-08 | 北京空间机电研究所 | A kind of low impact high-mechanic firer's release screw bolt |
| CN107054700A (en) * | 2017-03-30 | 2017-08-18 | 哈尔滨工业大学（威海） | A kind of satellite and the rocket separation locking releasing device |
| CN107837857A (en) * | 2017-12-11 | 2018-03-27 | 贵州大学 | A kind of colliery is with the cinder mashing device detachably used |
| CN109050987A (en) * | 2018-08-08 | 2018-12-21 | 上海宇航系统工程研究所 | One discharge plate chain type satellite and the rocket connection solution lock machine |
| CN110884694A (en) * | 2019-11-04 | 2020-03-17 | 上海宇航系统工程研究所 | Compressing and releasing mechanism capable of reducing spacecraft envelope |
| CN110884694B (en) * | 2019-11-04 | 2023-04-11 | 上海宇航系统工程研究所 | Can reduce compressing tightly release mechanism of spacecraft envelope |
| CN112373734A (en) * | 2020-11-24 | 2021-02-19 | 东方红卫星移动通信有限公司 | Low-orbit satellite group emission satellite-arrow separation unlocking module and satellite-arrow separation method |
| CN112373734B (en) * | 2020-11-24 | 2022-02-15 | 东方红卫星移动通信有限公司 | Low-orbit satellite group emission satellite-arrow separation unlocking module and satellite-arrow separation method |
| CN114963892A (en) * | 2021-02-19 | 2022-08-30 | 北京九天微星科技发展有限公司 | Connecting and unlocking device suitable for multi-satellite separation |
| CN113280695A (en) * | 2021-06-10 | 2021-08-20 | 北京星途探索科技有限公司 | But single face reassembling type disengaging structure device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105292523A (en) | Separating device and satellite and rocket separating device with buffering structure | |
| US10480603B2 (en) | Shock absorber based on the cutting, inward-folding and crushing of composite tube | |
| US20110000155A1 (en) | Cable End Anchorage With Overload Protection | |
| US9440664B2 (en) | Compact buffer having overload protection | |
| CN203806137U (en) | Multi-rotor shock-absorbing landing stand | |
| CN109440635B (en) | Horizontal anisotropic rigidity shock insulation support | |
| RU2493413C2 (en) | Device to suppress transverse forces by separation of reactive jet acting at jet engine nozzle, and jet engine nozzle | |
| CN104632976A (en) | Elastic-plastic energy-absorption buffer component | |
| CN201859488U (en) | Crash protecting component for flight recorder | |
| CN113431208A (en) | CSIPs-steel composite structure energy-consuming type anti-seismic node | |
| CN210800478U (en) | Vibration isolation and impact resistance device for small electronic equipment | |
| CN109703731B (en) | Buffer structure, buffering energy-absorbing recovery unit and aircraft | |
| KR102353950B1 (en) | Earthquake-resistant structures of photovoltaic power generation facilities | |
| CN111395845B (en) | Spring fixing device for shock-proof safety bin and mounting method thereof | |
| CN114291304B (en) | One-way impact isolation device suitable for microsatellite | |
| CN204692427U (en) | A kind of elastoplasticity energy-absorbing buffering assembly | |
| CN113719575A (en) | Damper | |
| CN113550641A (en) | Three-dimensional shock isolation device and manufacturing method thereof | |
| CN110030308A (en) | One kind can restore shock resistance mixing every vibration absorber and oscillation damping method | |
| CN115163714B (en) | Adjustable explosive impact vibration damper for initiating explosive device products | |
| CN108871065B (en) | Space effective load compressing and releasing device suitable for lunar surface environment | |
| CN212099323U (en) | Unmanned aerial vehicle protective structure | |
| CN210191240U (en) | Impact overload protection device for explosion-proof seat | |
| CN213407738U (en) | Shock-absorbing undercarriage structure of flight model airplane | |
| JP2001151200A (en) | Shock absorbing device for stacking base |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160203 |
|
| RJ01 | Rejection of invention patent application after publication |