CN101995192A - Head-body separation device with guide function - Google Patents
Head-body separation device with guide function Download PDFInfo
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- CN101995192A CN101995192A CN2010102637815A CN201010263781A CN101995192A CN 101995192 A CN101995192 A CN 101995192A CN 2010102637815 A CN2010102637815 A CN 2010102637815A CN 201010263781 A CN201010263781 A CN 201010263781A CN 101995192 A CN101995192 A CN 101995192A
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- push rod
- aircraft
- cylinder body
- rear end
- thrust
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Abstract
The invention provides a head-body separation device with a guide function, comprising a guide assembly and a thrust assembly, wherein the guide assembly and the thrust assembly are arranged in a cylinder body and respectively comprise a guide push rod and a thrust spring which are arranged in the cylinder body; the front end of the guide push rod extends out of a front cover of the cylinder body and is used as a thrust end pushing against the head, namely the rear end of an aircraft, a piston which is matched with the inner diameter of the cylinder body is arranged at the rear end of the guide push rod, a compression spring which is arranged in a cylinder body chamber is arranged between the piston and a rear cover of the cylinder body, and the rear cover of the cylinder is fixed on the inner wall of a separation body through a base. The maximum stroke L of the guide push rod is smaller than the maximum compression amount 5mm-10mm of the spring. The maximum stroke L of the guide push rod is greater than the maximum length H about 5mm-10mm of a protruding structure on the rear end surface of the aircraft. The front end of the guide push rod is sunk in a groove at the rear end of the aircraft.
Description
Technical field
The present invention relates to a kind of rear end face with body separator, particularly aircraft of guide function has a body separator of protrusion, belongs to a body isolating construction technical field, is specially to separate and incorporate body separator of guide function.
Background technology
For aircraft being transported to predetermined spatial domain, carrier rocket adopts the connected mode of multi-stage engine series connection more.After rocket separated the predetermined spatial domain of arrival step by step, aircraft was implemented a body with vehicle and is separated.For reducing the quality of aircraft, increase range, usually the part-structure spare of aircraft and attitude control engine are extend in the chorista and (be installed in the rear end face of aircraft).Be the influence of the separation interference in the minimizing separation process, avoid the protrusion of chorista collision aircraft rear end simultaneously, the general employing at parting surface installation separating mechanism and guiding mechanism to the aircraft flight attitude.Take two to overlap the scheme that mechanisms' (separating mechanism and guiding mechanism) design respectively, inevitably increased the architecture quality of aircraft and chorista, reduced the range of vehicle, can not adapt to a body separation requirement of long drive journey aircraft.
Summary of the invention
The object of the present invention is to provide an a kind of body separator with guide function, this device is an one with separation function and guide function collection, and simple in structure, light weight can satisfy a body separation requirement.
Technical scheme of the present invention: the body separator with guide function of the present invention comprises guidance set, thrust assembly, and its guidance set and thrust assembly are installed in the cylinder body, comprises the guiding push rod and the thrust spring that are installed in the cylinder body; The front end of guiding push rod stretches out the cylinder body protecgulum, as withstanding on the thrust end that head is the aircraft rear end, the piston that the rear end is and cylinder diameter mates of guiding push rod is placed the compression spring in the cylinder chamber between piston and cylinder body bonnet, the bonnet of cylinder body is fixed on the chorista inwall by pedestal.
The range L of described guiding push rod is less than the maximum compressibility 5mm～10mm of spring.
The range L of described guiding push rod is greater than the about 5mm～10mm of maximum length H of aircraft rear end face projective structure spare.
The front end of described guiding push rod sinks in the groove of aircraft rear end.
Technique effect of the present invention is embodied in: with separation function and the integrated design of guide function, realized rapid, the reliable separation of vehicle head body with the frame mode of miniaturization.Maximum height according to aircraft rear end protrusion designs the range of protection push rod and the maximum compressibility of spring, thus the structural member of protection aircraft rear end.
Just can realize various separating rates and separate the guiding stroke range with the initial compression amount by the performance parameter of adjusting spring.
The groove constraint guiding push rod of aircraft rear end guarantees that the separation attitude of aircraft and chorista can not twist.The present invention efficiently solves the separation protection question in the separation process of aircraft head body, its structure height integrated optimization, simple, function independent, light weight.
Description of drawings
Fig. 1 has the structural representation of a body separator of guide function for the present invention.
Fig. 2 is the scheme of installation of the present invention and aircraft and chorista.
The specific embodiment
The present invention is further detailed explanation below in conjunction with accompanying drawing and example.
As shown in Figure 1, the body separator with guide function of the present invention comprises guidance set, thrust assembly, and guidance set and thrust assembly are installed in the cylinder body 1, and guiding push rod 2 and thrust spring 3 are installed in the cylinder body 1; The front end 2a of guiding push rod 2 stretches out cylinder body 1 protecgulum 1a, as withstanding on the thrust end that head is aircraft 4 rear ends, the rear end of guiding push rod 2 is the piston 2b that mate with cylinder body 1 internal diameter, place compression spring 3 in the cylinder chamber between piston 2b and cylinder body 1 bonnet 1b, the bonnet 1b of cylinder body 1 is fixed on the chorista 5 by pedestal 6.
Further, the range L of described guiding push rod 2 is less than the about 5mm～10mm of the maximum compressibility of spring 3.
Further, the range L of described guiding push rod 2 is greater than the about 5mm～10mm of maximum length H of the structural member 7 of aircraft rear end face projection.
Preferably, the front end 2a of described guiding push rod 2 sinks in the groove 4a of aircraft 4 rear ends.
Fig. 2 is the scheme of installation of the present invention and aircraft and chorista:
Fig. 2 provides is aircraft and the part of rotary body after chorista links to each other, general, and aircraft and chorista composition surface periphery have and be no less than 4 same body separators.As shown in the figure, the cylinder body 1 bonnet 1b of of the present invention body separator is fixed on the chorista 5 by pedestal 6, after body (being aircraft and chorista) docked, the front end 2a of guiding push rod 2 sank in the groove 4a of aircraft 4 rear ends, and compression spring 3 is in compressive state.
The body time of releasing, the constraint cancellation, the potential energy of compression spring 3 is converted into the kinetic energy that aircraft 4 separates with chorista 5 by guiding push rod 2.In the body separation process; in the stroke range of guiding push rod 2; because the range L of guiding push rod 2 is less than the maximum height H of the structural member 7 of the maximum compressibility of spring 3, the aircraft 4 rear end projectioies range L less than guiding push rod 2; the groove 4a constraint guiding push rod 2 of aircraft 4 rear ends; the separation attitude of aircraft 4 and chorista 5 can not twisted, thereby the structural member 7 of protection aircraft 4 rear end projectioies is not collided.
In conversion process of energy, because quality, the quality of chorista 5 and the structural member 7 maximum height H of aircraft 4 rear end projectioies of aircraft 4 are constant, body separating rate depends on the proper property parameter and the decrement thereof of spring 3, therefore just can obtain different body separating rates by the spring 3 of selecting the different performance parameter.
Claims (4)
1. the body separator with guide function comprises guidance set, thrust assembly, and it is characterized in that: guidance set and thrust assembly are installed in the cylinder body (1), comprises the guiding push rod (2) and the thrust spring (3) that are installed in the cylinder body (1); The front end (2a) of guiding push rod (2) stretches out cylinder body (1) protecgulum (1a), as withstanding on the thrust end that head is aircraft (4) rear end, the rear end of guiding push rod (2) is the piston (2b) that mates with cylinder body (1) internal diameter, place compression spring (3) in the cylinder chamber between piston (2b) and cylinder body (1) bonnet (1b), the bonnet (1b) of cylinder body (1) is fixed on chorista (5) inwall by pedestal (6).
2. the body separator with guide function according to claim 1 is characterized in that: the range L of guiding push rod (2) is less than the maximum compressibility 5mm～10mm of spring (3).
3. the body separator with guide function according to claim 1 and 2 is characterized in that: the range L of guiding push rod (2) is greater than the about 5mm～10mm of maximum length H of aircraft rear end face projective structure spare.
4. the body separator with guide function according to claim 1 and 2 is characterized in that: the front end (2a) of guiding push rod (2) sinks in the groove (4a) of aircraft (4) rear end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010263781 CN101995192B (en) | 2010-08-24 | 2010-08-24 | Head-body separation device with guide function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010263781 CN101995192B (en) | 2010-08-24 | 2010-08-24 | Head-body separation device with guide function |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101995192A true CN101995192A (en) | 2011-03-30 |
| CN101995192B CN101995192B (en) | 2013-07-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010263781 Expired - Fee Related CN101995192B (en) | 2010-08-24 | 2010-08-24 | Head-body separation device with guide function |
Country Status (1)
| Country | Link |
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| CN (1) | CN101995192B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102494565A (en) * | 2011-11-11 | 2012-06-13 | 中国航天科技集团公司第四研究院第四十一研究所 | Separation mechanism of oriented rocket nose body |
| CN103940306A (en) * | 2014-05-14 | 2014-07-23 | 晋西工业集团有限责任公司 | Rocket projectile separating mechanism |
| CN104457447A (en) * | 2014-11-06 | 2015-03-25 | 北京航天长征飞行器研究所 | Device for accelerating separation of head and body of aircraft |
| CN110017738A (en) * | 2019-02-13 | 2019-07-16 | 北京蓝箭空间科技有限公司 | Pneumatic separation system and carrier rocket for carrier rocket |
| CN110949692A (en) * | 2019-11-13 | 2020-04-03 | 北京机械设备研究所 | Mechanical separation mechanism and mechanical separation system |
| CN113899260A (en) * | 2021-10-25 | 2022-01-07 | 航天科工火箭技术有限公司 | Axial separation device of fairing and carrier rocket |
| CN115127407A (en) * | 2022-08-10 | 2022-09-30 | 北京凌空天行科技有限责任公司 | Rocket hood separator based on spring |
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| US6142424A (en) * | 1995-01-10 | 2000-11-07 | Aerospatiale Societe Nationale Industrielle | Method of steering a vehicle and vehicle allowing implementation of the method |
| US6659393B1 (en) * | 1999-06-04 | 2003-12-09 | Nammo Raufoss As | Retarding and lock apparatus and method for retardation and interlocking of elements |
| RU2304236C1 (en) * | 2006-03-23 | 2007-08-10 | Федеральное государственное унитарное предприятие "Московский институт теплотехники" | Device for locking article parts detachable during operation |
| CN101151503A (en) * | 2005-04-08 | 2008-03-26 | 雷斯昂公司 | Separable structure material |
| CN201488656U (en) * | 2009-08-06 | 2010-05-26 | 中国航天科工集团第三总体设计部 | Locking and separating device |
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2010
- 2010-08-24 CN CN 201010263781 patent/CN101995192B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6142424A (en) * | 1995-01-10 | 2000-11-07 | Aerospatiale Societe Nationale Industrielle | Method of steering a vehicle and vehicle allowing implementation of the method |
| US6659393B1 (en) * | 1999-06-04 | 2003-12-09 | Nammo Raufoss As | Retarding and lock apparatus and method for retardation and interlocking of elements |
| CN101151503A (en) * | 2005-04-08 | 2008-03-26 | 雷斯昂公司 | Separable structure material |
| RU2304236C1 (en) * | 2006-03-23 | 2007-08-10 | Федеральное государственное унитарное предприятие "Московский институт теплотехники" | Device for locking article parts detachable during operation |
| CN201488656U (en) * | 2009-08-06 | 2010-05-26 | 中国航天科工集团第三总体设计部 | Locking and separating device |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102494565A (en) * | 2011-11-11 | 2012-06-13 | 中国航天科技集团公司第四研究院第四十一研究所 | Separation mechanism of oriented rocket nose body |
| CN102494565B (en) * | 2011-11-11 | 2013-10-23 | 中国航天科技集团公司第四研究院第四十一研究所 | Separation mechanism of oriented rocket nose body |
| CN103940306A (en) * | 2014-05-14 | 2014-07-23 | 晋西工业集团有限责任公司 | Rocket projectile separating mechanism |
| CN103940306B (en) * | 2014-05-14 | 2016-05-11 | 晋西工业集团有限责任公司 | A kind of rocket projectile separating mechanism |
| CN104457447A (en) * | 2014-11-06 | 2015-03-25 | 北京航天长征飞行器研究所 | Device for accelerating separation of head and body of aircraft |
| CN104457447B (en) * | 2014-11-06 | 2017-05-10 | 北京航天长征飞行器研究所 | Device for accelerating separation of head and body of aircraft |
| CN110017738A (en) * | 2019-02-13 | 2019-07-16 | 北京蓝箭空间科技有限公司 | Pneumatic separation system and carrier rocket for carrier rocket |
| CN113607006A (en) * | 2019-02-13 | 2021-11-05 | 蓝箭航天空间科技股份有限公司 | Pneumatic separation system for interstage separation in launch vehicles |
| CN110949692A (en) * | 2019-11-13 | 2020-04-03 | 北京机械设备研究所 | Mechanical separation mechanism and mechanical separation system |
| CN113899260A (en) * | 2021-10-25 | 2022-01-07 | 航天科工火箭技术有限公司 | Axial separation device of fairing and carrier rocket |
| CN113899260B (en) * | 2021-10-25 | 2023-01-20 | 航天科工火箭技术有限公司 | Axial separation device of fairing and carrier rocket |
| CN115127407A (en) * | 2022-08-10 | 2022-09-30 | 北京凌空天行科技有限责任公司 | Rocket hood separator based on spring |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101995192B (en) | 2013-07-17 |
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