CN103280665A - Electrical connector forced separation device for separation of spacecrafts - Google Patents
Electrical connector forced separation device for separation of spacecrafts Download PDFInfo
- Publication number
- CN103280665A CN103280665A CN2013101609667A CN201310160966A CN103280665A CN 103280665 A CN103280665 A CN 103280665A CN 2013101609667 A CN2013101609667 A CN 2013101609667A CN 201310160966 A CN201310160966 A CN 201310160966A CN 103280665 A CN103280665 A CN 103280665A
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- separation
- screw barrel
- swivel nut
- stay cord
- spacecrafts
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Abstract
The invention provides an electrical connector forced separation device for the separation of spacecrafts. The device comprises a pin puller, a screw barrel, a stay cord, a cord end and a locking nut, and peripheral equipment is an electrical connector, wherein the pin puller is a threaded rod, and an external thread is arranged at one end of the threaded rod; the screw barrel is also a cylinder, a thread is machined on the inner wall of one end of the screw barrel, and a round hole communicated with an inner cavity of the screw barrel is machined in the bottom surface of the other end of the screw barrel; one end of the stay cord is fixedly arranged in the screw barrel through the cord end, and the other end of the stay cord penetrates through the inner cavity of the screw barrel, extends from the round hole in the other end of the screw barrel, and is connected with the electrical connector; the locking nut and the screw barrel are sequentially sleeved on the end part of the pin puller, and are matched with the thread of the pin puller respectively; and after the length and the tightness of the stay cord are adjusted, the locking nut is tightened and locked close to the screw barrel. The device can work after the spacecrafts are mechanically separated, and the working time of the device is the same as the normal electrical separation working time of the spacecrafts, so that influence on the separation speed and the separation posture after the mechanical separation of the spacecrafts is avoided, and the separation reliability and safety of the spacecrafts are improved.
Description
Technical field
The present invention relates to a kind of spacecraft separation connector and take off device by force, be applicable to that the pressure when the electric connector electricity separates fault between spacecraft separates, belong to the spacecraft technology field.
Background technology
Between carrier rocket and the satellite, between the spacecraft adjacent compartment section of being formed by a plurality of cabins section of rail flight, except mechanical connection, toward contact need realize between rocket and the satellite by electric connector, communicating to connect between the spacecraft adjacent compartment section.When between rocket and the satellite, when needing to separate between the spacecraft adjacent compartment section, before machinery separates, need to finish electricity and separate.Generally, the electricity separation realizes by the electricity separation kinetic energy that electric connector self has usually between spacecraft.If the electricity separation is broken down between spacecraft in the rail flight course, may the aerial mission of spacecraft be impacted, even cause the failure of spacecraft flight task.Therefore, electricity separation backup design measure is the link that the Space Vehicle System reliability design need be paid close attention between spacecraft.
Patent " a kind of satellite and the rocket separation connector separation method of redundancy backup " (patent No.: CN201010272668.3) related a kind of satellite and the rocket separation connector separation method, utilize after the satellite and the rocket release that the thrust of cut spring realizes that the pressure of electric connector separates between the satellite and the rocket.This method existing questions is: the electricity separation between the satellite and the rocket occurs in the separation process of satellite and the rocket machinery, the separating force part of cut spring will be separated for the pressure of electric connector between the satellite and the rocket, therefore, satellite will be affected with respect to relative separation speed and the attitude of rocket, thereby influence the precision that satellite is entered the orbit; In addition, because the spring thrust that this method needs to separate by the device arrow realizes that the pressure of electric connector separates, therefore, the installation direction of electric connector should be consistent with the installation direction of device arrow cut spring, thereby limited other possible installation directions of electric connector.
Summary of the invention
In view of this, the invention provides a kind of spacecraft separation connector and take off device by force, can occur realizing when electricity separates fault forcing to separate at spacecraft.
A kind of spacecraft separation connector takes off device by force, and this takes off device by force and comprises pin removal, swivel nut, stay cord, fag end and stop nut, and ancillary equipment is electric connector; Wherein pin removal is that an end has externally threaded threaded rod; Swivel nut also is cylinder, and one end inwall is processed with screw thread, and other end bottom surface is processed with the circular hole that communicates with the swivel nut inner chamber;
Relation is installed: an end of stay cord is fixed in the swivel nut by fag end, the other end of stay cord passes the inner chamber of swivel nut and is passed by the circular hole of the swivel nut other end, be connected with electric connector then, stop nut and swivel nut are sleeved on the end of pin removal successively, and stop nut and swivel nut respectively with the threaded engagement of pin removal, after the length and elasticity of good stay cord to be regulated, tighten stop nut locking near swivel nut.
Beneficial effect:
(1) the present invention can work after spacecraft machinery separates again, and is identical opportunity with spacecraft normal electrical mask work, therefore do not influence separating rate, attitude after spacecraft machinery separates, improved reliability and fail safe that spacecraft separates;
(2) installation of the present invention is not limited by the spacecraft detaching direction, and is only relevant with the electric connector installation direction, and namely this device scope of application is more extensive;
(3) pulling rope length that is connected with electric connector of the present invention can be by the screw thread precession depth adjustment between swivel nut and the pin removal, can effectively reduce in the manufacturing process in pulling rope length and the installation process to taking off the control requirement of device installation site precision by force.
Description of drawings
Fig. 1 takes off the structure chart of device by force for spacecraft separation connector of the present invention.
Fig. 2 takes off the fundamental diagram of device by force for spacecraft separation connector of the present invention.
Wherein, 1-pin removal, 2-swivel nut, 3-stay cord, 4-fag end, 5-stop nut
Embodiment
Below in conjunction with the accompanying drawing embodiment that develops simultaneously, describe the present invention.
As shown in Figure 1, the invention provides a kind of spacecraft separation connector and take off device by force, this takes off device by force and comprises pin removal 1, swivel nut 2, stay cord 3, fag end 4 and stop nut 5, and ancillary equipment is electric connector.
Wherein pin removal 1 is that an end has externally threaded threaded rod.
Relation is installed: an end of stay cord 3 is fixed in the swivel nut 2 by fag end 4, the other end of stay cord 3 is penetrated by the inner chamber of swivel nut 2 and is passed by the circular hole of swivel nut 2 other ends, be connected (concrete type of attachment needs the interface shape otherwise designed according to electric connector) then with electric connector, stop nut 5 and swivel nut 2 are sleeved on the end of pulling pin of pin removal 1 successively, and stop nut 5 and swivel nut 2 be pin removal 1 threaded engagement respectively, after the length and elasticity of good stay cord 3 to be regulated, tighten locking near swivel nut 2 stop nut 5.
Operation principle: as shown in Figure 2, when the spacecraft separation connector takes off by force, pin removal 1 action, pin removal 1 is pulled pin and is shunk and certain convergent force is provided, pin removal 1 contraction process medium pulling rope 3 tensionings of pulling pin, and the pull-out force that pin removal 1 is produced is passed to electric connector, thereby electric connector is forced to break away from, by length and the degree of tightness of swivel nut 2 with the screw thread precession depth adjustment stay cord 3 of pin removal 1.
Above-mentioned pin removal 1 also can be electrodynamic type pin removal or firer's formula pin removal.
In sum, more than be preferred embodiment of the present invention only, be not for limiting protection scope of the present invention.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (2)
1. a spacecraft separation connector takes off device by force, it is characterized in that, this takes off device by force and comprises pin removal (1), swivel nut (2), stay cord (3), fag end (4) and stop nut (5), and ancillary equipment is electric connector; Wherein pin removal (1) is that an end has externally threaded threaded rod; Swivel nut (2) also is cylinder, and one end inwall is processed with screw thread, and other end bottom surface is processed with the circular hole that communicates with swivel nut (2) inner chamber;
Relation is installed: an end of stay cord (3) is fixed in the swivel nut (2) by fag end (4), the other end of stay cord (3) passes the inner chamber of swivel nut (2) and is passed by the circular hole of swivel nut (2) other end, be connected with electric connector then, stop nut (5) and swivel nut (2) are sleeved on the end of pin removal (1) successively, and stop nut (5) and swivel nut (2) respectively with the threaded engagement of pin removal (1), after the length and elasticity of good stay cord to be regulated (3), tighten locking near swivel nut (2) stop nut (5).
2. spacecraft separation connector as claimed in claim 1 takes off device by force, it is characterized in that, described pin removal (1) is electrodynamic type pin removal or firer's formula pin removal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013101609667A CN103280665A (en) | 2013-05-03 | 2013-05-03 | Electrical connector forced separation device for separation of spacecrafts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013101609667A CN103280665A (en) | 2013-05-03 | 2013-05-03 | Electrical connector forced separation device for separation of spacecrafts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103280665A true CN103280665A (en) | 2013-09-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013101609667A Pending CN103280665A (en) | 2013-05-03 | 2013-05-03 | Electrical connector forced separation device for separation of spacecrafts |
Country Status (1)
| Country | Link |
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| CN (1) | CN103280665A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108910093A (en) * | 2018-06-15 | 2018-11-30 | 上海卫星工程研究所 | A kind of separate type monitoring camera surface separation experimental rig |
| CN109273921A (en) * | 2018-09-20 | 2019-01-25 | 贵州航天电器股份有限公司 | A kind of umbilical connector that can be taken off by force |
| CN109827690A (en) * | 2019-03-09 | 2019-05-31 | 雷义 | A kind of de- pull out force test device |
| CN111750039A (en) * | 2020-06-11 | 2020-10-09 | 上海卫星工程研究所 | Mechanical separation steel lock mechanism of spacecraft separation plug and installation method |
| CN112615209A (en) * | 2021-02-04 | 2021-04-06 | 北京星际荣耀空间科技股份有限公司 | Carrier rocket and ground rope and cable connecting assembly thereof |
| CN112758360A (en) * | 2020-12-29 | 2021-05-07 | 上海卫星工程研究所 | Fixed star cabin signal transmission device and butt joint method |
| RU2779975C1 (en) * | 2022-03-28 | 2022-09-16 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка | Device for transmitting electrical signals from the electrical system of the launcher to the electrical system of the separated object |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3043925A (en) * | 1958-09-25 | 1962-07-10 | Cannon Electric Co | Electrical connector with multiple release mechanism |
| CN201859989U (en) * | 2010-10-27 | 2011-06-08 | 中航光电科技股份有限公司 | Separable connector with pulling rope |
-
2013
- 2013-05-03 CN CN2013101609667A patent/CN103280665A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3043925A (en) * | 1958-09-25 | 1962-07-10 | Cannon Electric Co | Electrical connector with multiple release mechanism |
| CN201859989U (en) * | 2010-10-27 | 2011-06-08 | 中航光电科技股份有限公司 | Separable connector with pulling rope |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108910093A (en) * | 2018-06-15 | 2018-11-30 | 上海卫星工程研究所 | A kind of separate type monitoring camera surface separation experimental rig |
| CN109273921A (en) * | 2018-09-20 | 2019-01-25 | 贵州航天电器股份有限公司 | A kind of umbilical connector that can be taken off by force |
| CN109827690A (en) * | 2019-03-09 | 2019-05-31 | 雷义 | A kind of de- pull out force test device |
| CN111750039A (en) * | 2020-06-11 | 2020-10-09 | 上海卫星工程研究所 | Mechanical separation steel lock mechanism of spacecraft separation plug and installation method |
| CN112758360A (en) * | 2020-12-29 | 2021-05-07 | 上海卫星工程研究所 | Fixed star cabin signal transmission device and butt joint method |
| CN112615209A (en) * | 2021-02-04 | 2021-04-06 | 北京星际荣耀空间科技股份有限公司 | Carrier rocket and ground rope and cable connecting assembly thereof |
| RU2779975C1 (en) * | 2022-03-28 | 2022-09-16 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка | Device for transmitting electrical signals from the electrical system of the launcher to the electrical system of the separated object |
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130904 |