CN105857646A - Spherical locking separating mechanism - Google Patents
Spherical locking separating mechanism Download PDFInfo
- Publication number
- CN105857646A CN105857646A CN201610215432.3A CN201610215432A CN105857646A CN 105857646 A CN105857646 A CN 105857646A CN 201610215432 A CN201610215432 A CN 201610215432A CN 105857646 A CN105857646 A CN 105857646A
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- China
- Prior art keywords
- connecting shaft
- aircraft
- launching tube
- separating mechanism
- bearing shell
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pivots And Pivotal Connections (AREA)
- Automatic Assembly (AREA)
Abstract
The invention relates to a spherical locking separating mechanism. The spherical locking separating mechanism comprises a casing, an aircraft connecting shaft, a pair of bearing bushes, a launcher barrel connecting shaft, and a plurality of steel balls, wherein the casing is fixedly connected with a tail seat of a tail pushing type launcher; a first end of the aircraft connecting shaft is arranged in the casing, and a second end of the aircraft connecting shaft extends out of the casing to be connected with the tail of the launched aircraft; the bearing bushes are arranged between the casing and the aircraft connecting shaft and are fixedly connected with the casing through a first connecting fitting; a first end of the launcher barrel connecting shaft is arranged in the aircraft connecting shaft and is fixedly connected with the aircraft connecting shaft through a second connecting fitting, and a second end of the aircraft connecting shaft extends out of the first end of the aircraft connecting shaft, and is connected with the tail of the launcher barrel of the tail pushing type launcher; the steel balls are arranged on the aircraft connecting shaft and are in contact with the aircraft connecting shaft, the launcher barrel connecting shaft and the bearing bushes. The spherical locking separating mechanism disclosed by the invention meets fuel gas sealing requirements in a launching process, and intensity and rigidity requirements under the axial high g-loading condition of a transport working mode, realizes automatic unlocking under the transient condition of a launching working mode, and guarantees smooth separation of the aircraft and the launcher barrel.
Description
Technical field
The present invention relates to a kind of separating mechanism, specifically refer to a kind of novel spherical locking separating mechanism, belong to the technical field of vehicle launch barrel structure design.
Background technology
In the technical field of vehicle launch barrel structure design, it is little that gas piston tail pushing-type discharger has launching tube radial dimension, and the car launcher bicycle amount of shooting is big, and boosting stroke is long, there is the advantages such as good ejection trajectory performance, be the most gradually applied in the structure design of vehicle launch cylinder.
As it is shown in figure 1, be the structural representation of tail pushing-type discharger in prior art, it includes annular emission cylinder 10, and gas generator 20, tailstock 30 and the aircraft 40 that is launched being installed on successively in annular emission cylinder 10.
The structure being had due to tail pushing-type discharger is special, in order to meet gas sealing requirement, in described emission process, tailstock 30 must be close to the inwall motion of launching tube 10, and the most traditional lever, bolt-type and magnesium ribbon formula locking separating mechanism all can not meet its Structural Design Requirement.
Based on above-mentioned, need badly at present and propose a kind of novel ball locking separating mechanism being applied to tail pushing-type discharger.
Summary of the invention
It is an object of the invention to provide a kind of spherical locking separating mechanism, the gas sealing requirement in emission process can be met, and the strength and stiffness requirement under the biggest overload condition of comfortable property, it is achieved launch the automatic unlocking under operating mode transient condition, it is ensured that aircraft is smoothly detached with launching tube.
For achieving the above object, the present invention provides a kind of spherical locking separating mechanism, and it is applied to tail pushing-type discharger, specifically comprises: housing, in cylinder, fixes with the tailstock of tail pushing-type discharger and is connected；Aircraft connecting shaft, in cylinder, the first end of this aircraft connecting shaft is arranged in housing, and the second end of this aircraft connecting shaft stretches out housing and is connected with the afterbody of the aircraft being launched；A pair bearing shell, in semi-cylindrical, this pair bearing shell connects and is formed cylindrical and be arranged between housing and aircraft connecting shaft, and is fixedly connected with the casing by the first connector；Launching tube connecting shaft, in cylinder, first end of this launching tube connecting shaft is arranged in aircraft connecting shaft, and be connected by the second connector and aircraft connecting shaft are fixing, second end of this launching tube connecting shaft stretches out from the end of aircraft connecting shaft, and is connected with the afterbody of the launching tube of tail pushing-type discharger；Multiple steel balls, are arranged in aircraft connecting shaft, and are connected by contacting with aircraft connecting shaft, launching tube connecting shaft and bearing shell.
Along the circumferential direction being evenly arranged with multiple radial direction circular hole in described aircraft connecting shaft, peripherally disposed on the inwall of described bearing shell have an annular recess, and this groove is corresponding with the size and location of each radial direction circular hole.
In each radial direction circular hole that multiple steel balls are correspondingly arranged in aircraft connecting shaft respectively, and between the groove and the outer wall of launching tube connecting shaft of bearing shell, to block steel ball.
Further, the outer wall of aircraft connecting shaft is along the circumferential direction uniformly arranged four radially circular holes, four steel balls of corresponding arranging, is separately positioned in each radial direction circular hole, and contacts with the groove of bearing shell and the outer wall of launching tube connecting shaft.
The first described connector is multiple attachment screw, and the circumferencial direction along housing and a pair bearing shell is uniformly arranged, to be fixedly connected with the casing by a pair bearing shell.
The second described connector is a shear screw, is arranged on aircraft connecting shaft and the circumferencial direction of launching tube connecting shaft, to be connected fixing to aircraft connecting shaft and launching tube connecting shaft.
Described spherical locking separating mechanism is in comfortable property when transshipping the most greatly, relative motion is not had between tailstock and the launching tube of tail pushing-type discharger, aircraft connecting shaft is under the locking effect of steel ball, bearing shell and launching tube connecting shaft, it is impossible to carry out axially-movable.
When described spherical locking separating mechanism is in separation operating mode, relative motion is there is between tailstock and the launching tube of tail pushing-type discharger, the tailstock of tail pushing-type discharger drives aircraft connecting shaft move and cut off the second connector so that launching tube connecting shaft is extracted from aircraft connecting shaft；Each steel ball rolls out in the radial direction circular hole of aircraft connecting shaft, separates with bearing shell；Aircraft connecting shaft is extracted from bearing shell, it is achieved separate between aircraft with launching tube.
In sum, spherical locking separating mechanism of the present invention, before aircraft separates in launching tube and extracts, it is possible to ensures do not have relative motion between aircraft connecting shaft and bearing shell and housing, meets the gas sealing requirement in emission process.
Spherical locking separating mechanism of the present invention, moreover it is possible to meet the strength and stiffness requirement under the biggest overload condition of comfortable property, can realize launching the automatic unlocking under operating mode transient condition, so that it is guaranteed that aircraft is smoothly detached with launching tube.
Accompanying drawing explanation
Fig. 1 is the structural representation of tail pushing-type discharger of the prior art；
Fig. 2 a is the scheme of installation of the spherical locking separating mechanism in the present invention and tail pushing-type discharger；
Fig. 2 b is the cross-sectional view of the spherical locking separating mechanism in the present invention；
Fig. 3 is the structural representation separating initial time of the spherical locking separating mechanism in the present invention；
Fig. 4 is the structural representation separating finish time of the spherical locking separating mechanism in the present invention.
Detailed description of the invention
Below in conjunction with Fig. 1～Fig. 4, describe a preferred embodiment of the present invention in detail.
As shown in Figure 1, Figure 2 shown in a and Fig. 2 b, the spherical locking separating mechanism that the present invention provides, it is applied to tail pushing-type discharger, specifically comprises: housing 6, in cylinder, fixing with the tailstock 30 of tail pushing-type discharger is connected；Aircraft connecting shaft 1, in cylinder, the first end of this aircraft connecting shaft 1 is arranged in housing 6, and the second end of this aircraft connecting shaft 1 stretches out housing 6 and is connected with the afterbody of the aircraft 40 being launched；A pair bearing shell 2, in semi-cylindrical, this pair bearing shell 2 connects and is formed cylindrical and be arranged between housing 6 and aircraft connecting shaft 1, and is connected by the first connector is fixing with housing 6；Launching tube connecting shaft 7, in cylinder, first end of this launching tube connecting shaft 7 is arranged in aircraft connecting shaft 1, and be connected by the second connector is fixing with aircraft connecting shaft 1, second end of this launching tube connecting shaft 7 stretches out from the end of aircraft connecting shaft 1, and is connected with the afterbody of the launching tube 10 of tail pushing-type discharger；Multiple steel balls 5, are arranged in aircraft connecting shaft 1, and are connected by contacting with aircraft connecting shaft 1, launching tube connecting shaft 7 and bearing shell 2.
As shown in Figure 4, described aircraft connecting shaft 1 being along the circumferential direction evenly arranged with multiple radial direction circular hole 8, peripherally disposed on the inwall of described bearing shell 2 have an annular recess 9, and this groove 9 is corresponding with the size and location of each radial direction circular hole 8.
In each radial direction circular hole 8 that multiple steel balls 5 are correspondingly arranged in aircraft connecting shaft 1 respectively, and between the groove 9 and the outer wall of launching tube connecting shaft 7 of bearing shell 2, its motion is limited in order to block steel ball 5, make aircraft connecting shaft 1 under the locking effect of steel ball 5, bearing shell 2 and launching tube connecting shaft 7, it is impossible to carry out axially-movable.
In the present embodiment, the outer wall of aircraft connecting shaft 1 is along the circumferential direction uniformly arranged four radially circular holes 8, four steel balls 5 of corresponding arranging, it is separately positioned in four radial direction circular holes 8, and contact with the groove 9 of bearing shell 2 and the outer wall of launching tube connecting shaft 7, between the most adjacent two steel balls 5, be spaced 90 °.
The first described connector is multiple attachment screws 3, and the circumferencial direction along housing 6 and a pair bearing shell 2 is uniformly arranged, and to be connected fixing with housing 6 for a pair bearing shell 2, thus fixes the relative position between a pair bearing shell 2 and housing 6.
In the present embodiment, arranging four attachment screws 3, the circumferencial direction along housing 6 and a pair bearing shell 2 is uniformly arranged, the most each two, is spaced 180 ° between the most adjacent two attachment screws 3.
The second described connector is a shear screw 4, it is arranged on aircraft connecting shaft 1 and the circumferencial direction of launching tube connecting shaft 7, to be connected fixing with launching tube connecting shaft 7 for aircraft connecting shaft 1, thus fixing relative position between aircraft connecting shaft 1 with launching tube connecting shaft 7.
As shown in Figure 2 b, described spherical locking separating mechanism is in comfortable property when transshipping the most greatly, does not has relative motion between tailstock 30 and the launching tube 10 of tail pushing-type discharger.Now, in each radial direction circular hole 8 that multiple steel balls 5 are correspondingly arranged in aircraft connecting shaft 1 respectively, and between the groove 9 and the outer wall of launching tube connecting shaft 7 of bearing shell 2, thus block steel ball 5 and limit its radial motion.Therefore, aircraft connecting shaft 1 is under the locking effect of steel ball 5, bearing shell 2 and launching tube connecting shaft 7, it is impossible to carry out axially-movable.
When described spherical locking separating mechanism is in separation operating mode, as shown in Figure 3, separating initial time, the tailstock 30 of tail pushing-type discharger promotes aircraft 40 to travel forward, and and launching tube 10 between occur relative motion, the tailstock 30 of tail pushing-type discharger drives aircraft connecting shaft 1 to move and cuts off the second connector 4 so that launching tube connecting shaft 7 is extracted from aircraft connecting shaft 1.Now, each steel ball 5 is all no longer influenced by the launching tube connecting shaft 7 radial constraint to it.As shown in Figure 4, separate finish time, i.e. promote aircraft 40 to arrive the moment that the nozzle of launching tube 10 clashes into buffer, under the effect of impulsive force when tailstock 30, each steel ball 5 all rolls out in the radial direction circular hole 8 of aircraft connecting shaft 1, thus separates with bearing shell 2；Aircraft connecting shaft 1 is owing to losing the steel ball 5 constraint to it, and extracts from bearing shell 2, to realize being smoothly detached between aircraft 40 and launching tube 10.
In sum, owing to present invention employs spherical locking separating mechanism, before aircraft separates in launching tube and extracts, between aircraft connecting shaft and bearing shell and housing, there is no relative motion all the time, thus the gas sealing requirement meeting and ensure that in emission process；And the strength and stiffness requirement under the biggest overload condition of comfortable property can be met, can realize launching the automatic unlocking under operating mode transient condition, so that it is guaranteed that aircraft is smoothly detached with launching tube.
Although present disclosure has been made to be discussed in detail by above preferred embodiment, but it should be appreciated that the description above is not considered as limitation of the present invention.After those skilled in the art have read foregoing, multiple amendment and replacement for the present invention all will be apparent from.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (8)
1. a spherical locking separating mechanism, is applied to tail pushing-type discharger, it is characterised in that comprise:
Housing (6), in cylinder, fixes with the tailstock (30) of tail pushing-type discharger and is connected；
Aircraft connecting shaft (1), in cylinder, the first end of this aircraft connecting shaft (1) is arranged in housing (6), and the second end of this aircraft connecting shaft (1) stretches out housing (6) and is connected with the afterbody of the aircraft (40) being launched；
A pair bearing shell (2), in semi-cylindrical, this pair bearing shell (2) connects and is formed cylindrical and be arranged between housing (6) and aircraft connecting shaft (1), and is connected by the first connector and housing (6) are fixing；
Launching tube connecting shaft (7), in cylinder, first end of this launching tube connecting shaft (7) is arranged in aircraft connecting shaft (1), and be connected by the second connector and aircraft connecting shaft (1) are fixing, second end of this launching tube connecting shaft (7) stretches out from the end of aircraft connecting shaft (1), and is connected with the afterbody of the launching tube (10) of tail pushing-type discharger；
Multiple steel balls (5), are arranged in aircraft connecting shaft (1), and are connected by contacting with aircraft connecting shaft (1), launching tube connecting shaft (7) and bearing shell (2).
Spherical locking separating mechanism the most as claimed in claim 1, it is characterized in that, multiple radial direction circular hole (8) along the circumferential direction it is evenly arranged with in described aircraft connecting shaft (1), peripherally disposed on the inwall of described bearing shell (2) have an annular recess (9), and this groove (9) is corresponding with the size and location of each radial direction circular hole (8).
Spherical locking separating mechanism the most as claimed in claim 2, it is characterized in that, in each radial direction circular hole (8) that multiple steel balls (5) are correspondingly arranged in aircraft connecting shaft (1) respectively, and it is positioned between the groove (9) of bearing shell (2) and the outer wall of launching tube connecting shaft (7), to block steel ball (5).
Spherical locking separating mechanism the most as claimed in claim 3, it is characterized in that, the outer wall of aircraft connecting shaft (1) is along the circumferential direction uniformly arranged four radially circular holes (8), four steel balls (5) are separately positioned in each radial direction circular hole (8) by correspondence, and contact with the groove (9) of bearing shell (2) and the outer wall of launching tube connecting shaft (7).
Spherical locking separating mechanism the most as claimed in claim 1, it is characterized in that, the first described connector is multiple attachment screw (3), and the circumferencial direction along housing (6) and a pair bearing shell (2) is uniformly arranged, to be connected fixing to a pair bearing shell (2) and housing (6).
Spherical locking separating mechanism the most as claimed in claim 1, it is characterized in that, the second described connector is a shear screw (4), it is arranged on aircraft connecting shaft (1) and the circumferencial direction of launching tube connecting shaft (7), to be connected fixing to aircraft connecting shaft (1) and launching tube connecting shaft (7).
Spherical locking separating mechanism the most as claimed in claim 3, it is characterized in that, described spherical locking separating mechanism is in comfortable property when transshipping the most greatly, relative motion is not had between tailstock (30) and the launching tube (10) of tail pushing-type discharger, aircraft connecting shaft (1) is under the locking effect of steel ball (5), bearing shell (2) and launching tube connecting shaft (7), it is impossible to carry out axially-movable.
Spherical locking separating mechanism the most as claimed in claim 3, it is characterized in that, when described spherical locking separating mechanism is in separation operating mode, relative motion is there is between tailstock (30) and the launching tube (10) of tail pushing-type discharger, the tailstock (30) of tail pushing-type discharger drives aircraft connecting shaft (1) move and cut off shear screw (4) so that launching tube connecting shaft (7) is extracted from aircraft connecting shaft (1)；
Each steel ball (5) rolls out in the radial direction circular hole (8) of aircraft connecting shaft (1), separates with bearing shell (2)；Aircraft connecting shaft (1) is extracted from bearing shell (2), it is achieved separate between aircraft (40) with launching tube (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610215432.3A CN105857646B (en) | 2016-04-08 | 2016-04-08 | A kind of spherical locking separating mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610215432.3A CN105857646B (en) | 2016-04-08 | 2016-04-08 | A kind of spherical locking separating mechanism |
Publications (2)
| Publication Number | Publication Date |
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| CN105857646A true CN105857646A (en) | 2016-08-17 |
| CN105857646B CN105857646B (en) | 2017-11-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610215432.3A Active CN105857646B (en) | 2016-04-08 | 2016-04-08 | A kind of spherical locking separating mechanism |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347711A (en) * | 2016-09-08 | 2017-01-25 | 北京理工大学 | Self-stabilizing launching device for probe launching from lunar surface |
| CN106347679A (en) * | 2016-08-30 | 2017-01-25 | 陕西千山航空电子有限责任公司 | Throwing separating mechanism for civil aircraft |
| CN107458627A (en) * | 2017-08-09 | 2017-12-12 | 北京特种机械研究所 | A kind of detector is pyrolyzed latch mechanism |
| CN107816914A (en) * | 2017-10-31 | 2018-03-20 | 北京理工大学 | A kind of detention hood separator based on big momentum collision brake buffering |
| CN109159908A (en) * | 2018-08-13 | 2019-01-08 | 上海机电工程研究所 | A kind of double guide rail ejection mechanisms of single lifting |
| CN112124611A (en) * | 2020-08-22 | 2020-12-25 | 西安科为实业发展有限责任公司 | Shelling and separating system and method for cylindrical jet type folding wing aircraft |
| CN112693639A (en) * | 2021-01-06 | 2021-04-23 | 湖北航天技术研究院总体设计所 | Energy storage type ejection sealing protection device and aircraft launching method |
| CN113295368A (en) * | 2021-04-29 | 2021-08-24 | 中国航天空气动力技术研究院 | Launching mechanism for backward separation wind tunnel release model test |
| CN115140320A (en) * | 2022-08-18 | 2022-10-04 | 北京中科宇航技术有限公司 | Pneumatic separation unlocking device and system |
| CN117699067A (en) * | 2024-02-06 | 2024-03-15 | 北京爱思达航天科技有限公司 | Double-motor driving action pin puller |
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| CN105253331A (en) * | 2015-09-10 | 2016-01-20 | 北京空间飞行器总体设计部 | Force-limited compaction releasing mechanism |
| CN105277049A (en) * | 2015-10-27 | 2016-01-27 | 贵州航天天马机电科技有限公司 | Perpendicular positioning device for carrier rocket and use method of perpendicular positioning device |
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| CN202320802U (en) * | 2011-10-13 | 2012-07-11 | 孟宪红 | Nano-satellite separating and unlocking device |
| CN103204237A (en) * | 2013-03-19 | 2013-07-17 | 北京航空航天大学 | Aerial propelling device suitable for amphibious unmanned aerial vehicle |
| CN105035368A (en) * | 2015-07-31 | 2015-11-11 | 上海卫星工程研究所 | Low-impact unlocking device allowing in-track repeated use and utilization method |
| CN105253331A (en) * | 2015-09-10 | 2016-01-20 | 北京空间飞行器总体设计部 | Force-limited compaction releasing mechanism |
| CN105277049A (en) * | 2015-10-27 | 2016-01-27 | 贵州航天天马机电科技有限公司 | Perpendicular positioning device for carrier rocket and use method of perpendicular positioning device |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347679A (en) * | 2016-08-30 | 2017-01-25 | 陕西千山航空电子有限责任公司 | Throwing separating mechanism for civil aircraft |
| CN106347711A (en) * | 2016-09-08 | 2017-01-25 | 北京理工大学 | Self-stabilizing launching device for probe launching from lunar surface |
| CN107458627A (en) * | 2017-08-09 | 2017-12-12 | 北京特种机械研究所 | A kind of detector is pyrolyzed latch mechanism |
| CN107816914A (en) * | 2017-10-31 | 2018-03-20 | 北京理工大学 | A kind of detention hood separator based on big momentum collision brake buffering |
| CN109159908A (en) * | 2018-08-13 | 2019-01-08 | 上海机电工程研究所 | A kind of double guide rail ejection mechanisms of single lifting |
| CN112124611A (en) * | 2020-08-22 | 2020-12-25 | 西安科为实业发展有限责任公司 | Shelling and separating system and method for cylindrical jet type folding wing aircraft |
| CN112124611B (en) * | 2020-08-22 | 2023-11-28 | 西安科为实业发展有限责任公司 | Shelling separation system and method for cylindrical jet type folding wing aircraft |
| CN112693639A (en) * | 2021-01-06 | 2021-04-23 | 湖北航天技术研究院总体设计所 | Energy storage type ejection sealing protection device and aircraft launching method |
| CN113295368A (en) * | 2021-04-29 | 2021-08-24 | 中国航天空气动力技术研究院 | Launching mechanism for backward separation wind tunnel release model test |
| CN115140320A (en) * | 2022-08-18 | 2022-10-04 | 北京中科宇航技术有限公司 | Pneumatic separation unlocking device and system |
| CN117699067A (en) * | 2024-02-06 | 2024-03-15 | 北京爱思达航天科技有限公司 | Double-motor driving action pin puller |
| CN117699067B (en) * | 2024-02-06 | 2024-06-25 | 北京爱思达航天科技有限公司 | Double-motor driving action pin puller |
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