CN203461147U - Interstage separating device for aircraft - Google Patents
Interstage separating device for aircraft Download PDFInfo
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- CN203461147U CN203461147U CN201320504193.5U CN201320504193U CN203461147U CN 203461147 U CN203461147 U CN 203461147U CN 201320504193 U CN201320504193 U CN 201320504193U CN 203461147 U CN203461147 U CN 203461147U
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- interstage
- shaped charge
- linear shaped
- flexible linear
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Abstract
The utility model relates to an interstage separating device for an aircraft. The interstage separating device is mounted on an interstage housing of the aircraft, and comprises a baffle, a protection cover and a linear shaped charge component; the interstage housing comprises a weakening groove and a mounting and positioning groove; the weakening groove extends in the circumference direction along one side of the interstage housing; the mounting and positioning groove extends in the circumference direction along the other side of the interstage housing and is opposite to the weakening groove; the linear shaped charge component is positioned in the mounting and positioning groove; the protection cover is fixed on the outer side of the interstage housing, and completely covers the linear shaped charge component; the baffle is fixed on the outer side of the interstage housing; the linear shaped charge component completely falls into the projection of the baffle in the interstage housing. The functions adopt modularized design, the protection structures adopt redundant design and lightweight design, the linear shaped charge component is accurate in guiding and positioning, the mounting and the operation are convenient, the separation is reliable, the protection requirements under the action of various dynamic loads generated by explosive detonation can be met, the interstage separating device is suitable for various different requirements of dynamics and natural environment, and the whole separating device is light in weight, and easy to process, assemble and maintain.
Description
Technical field
The present invention relates to guided missile, carrier rocket inter-stage separation technology field, be specifically related to a kind of stage separation device of aircraft.
Background technology
In large-scale space transportation system, as guided missile and carrier rocket, often have that some sizes are large, the shell section of the use ZL114A material of complicated structure.Therefore, stage separation technology for ZL114A material is a very important content in multistage space transportation system design, separated synchronism is good, reliability is high and advantages of simple structure and simple because it has for linear separation device, is usually used in the separation of large-scale carrying structure.Conventional linear separation device mainly contains mild detonating fuze disengagement gear, cumulative flexible linear shaped charge disengagement gear and Expansion Tube Separating Device etc., for other two kinds of line formula disengagement gears, cumulative flexible linear shaped charge disengagement gear has good directional tagging ability, capacity usage ratio is higher, the structural materials that applicable cutting and separating is thicker.
But there is following shortcoming in existing cumulative flexible linear shaped charge stage separation device: 1. inter-stage shell section cutting and separating is mainly relied on to the effect of high speed metal jet, and utilize degree lower to shock, but ZL114A stretch ratio is lower, more responsive to shock; 2. flexible linear shaped charge assembly first assembles with protective case, then this assembly (flexible linear shaped charge assembly and protective case) is assembled on shell segment structure, and it is narrower in shell section, to weaken well width, be subject to the impact of shell segment structure and the accumulation of protective case Mismachining tolerance, bring thus the alignment degree of flexible linear shaped charge wayward, and fitting operation is loaded down with trivial details; 3. protective case structure is single, and protection effect is poor, in order to obtain good protection effect, only has the protective case of increasing scantling of structure, and the fail-safe structure weight of but bringing is thus heavier.
Summary of the invention
The technical matters that will solve of the present invention is to provide that a kind of cutting and separating is reliable, flexible linear shaped charge guide-localization accurately, fitting operation Flight Vehicle Stage Separation device easily.
In order to solve the problems of the technologies described above, technical scheme of the present invention is that a kind of stage separation device of aircraft, is arranged in aircraft interstage casings, comprises baffle plate, protective case, flexible linear shaped charge assembly;
Described interstage casings comprises along the circumferential weakening groove extending of interstage casings one side, along interstage casings opposite side, circumferentially extends and the relative installation positioning groove of described weakening groove; Described flexible linear shaped charge assembly is placed in described installation positioning groove; Described protective case is fixed on described interstage casings outside, and the completely coated described flexible linear shaped charge assembly of described protective case; Described baffle plate is fixed on described interstage casings outside, and described flexible linear shaped charge assembly falls into described baffle plate completely to the projection of described interstage casings.
Described flexible linear shaped charge assembly comprises cumulative flexible linear shaped charge and rubber sheath, and described cumulative flexible linear shaped charge is fixed in rubber sheath by adhesion agent.
Described interstage casings adopts ZL114A material.
Described baffle plate comprises the first plate, the second plate and the 3rd plate that vertical and integral type connects successively; On described the first plate, have several fastener mounting holes, baffle plate is realized and being connected of interstage casings by screw by these fastener mounting holes; The face of described the second plate is mutually vertical with the face of described interstage casings; Described the 3rd even interval of plate has a plurality of pressure relief vents.
Beneficial effect of the present invention:
Each Functional Design modularization of disengagement gear of the present invention, current design manual of protective structures redundant and lightweight, flexible linear shaped charge assembly guide-localization are accurate, fitting operation is convenient, separated reliable, separation applicable to baroque employing ZL114A material inter-stage shell section, can meet the requirement of shelter bear the various dynamic load effects that powder charge detonation produces, can adapt to various mechanics and natural environment requirement, to meet the object of full bullet/arrow complex environment adaptive capacity, lightweight, the easy processing of whole disengagement gear, easy assembling, easy-maintaining.
Accompanying drawing explanation
Fig. 1 is the inter-stage shell section schematic diagram of the stage separation device of a kind of aircraft of application the present invention;
Fig. 2 is the schematic diagram after the stage separation device of a kind of aircraft of inter-stage shell section application the present invention;
Fig. 3 is baffle arrangement schematic diagram in the stage separation device of a kind of aircraft of the present invention.
In figure: 1-interstage casings, 2-baffle plate fastener, 3-baffle plate, 4-protective case fastener, 5-protective case, 6-flexible linear shaped charge assembly, 7-installs positioning groove, and 8-weakens groove, 9-pressure relief vent, 10-fastener mounting hole.
The specific embodiment
Below in conjunction with drawings and Examples, the present invention is described further.
The stage separation device of a kind of aircraft of the present invention, is arranged in aircraft interstage casings 1 as shown in Figure 1, comprises baffle plate fastener 2, baffle plate 3, protective case fastener 4, protective case 5, flexible linear shaped charge assembly 6;
Described interstage casings 1 comprises along the circumferential weakening groove 8 extending of interstage casings one side, along interstage casings opposite side, circumferentially extends and the installation positioning groove 7 relative with described weakening groove 8;
Described interstage casings 1 adopts ZL114A material;
Described flexible linear shaped charge assembly 6 is placed in described installation positioning groove 7; Described flexible linear shaped charge assembly 6 comprises cumulative flexible linear shaped charge and rubber sheath, and described cumulative flexible linear shaped charge is fixed in rubber sheath by adhesion agent;
Described protective case 5 is fixed on described interstage casings 1 outside by protective case fastener 4, and the completely coated described flexible linear shaped charge assembly 6 of described protective case 5;
Described baffle plate 3 is fixed on described interstage casings 1 outside by baffle plate fastener 2, and described flexible linear shaped charge assembly 6 falls into described baffle plate 3 completely to the projection of described interstage casings 1; Described baffle plate fastener 2 and protective case fastener 4 can be all screws.
Particularly, described baffle plate 3 comprises the first plate, the second plate and the 3rd plate that vertical and integral type connects successively; On described the first plate, have several fastener mounting holes 10, baffle plate 3 is realized and being connected of interstage casings 1 by baffle plate fastener 2 by these fastener mounting holes 10; The face of described the second plate is mutually vertical with the face of described interstage casings 1; Described the 3rd even interval of plate has a plurality of pressure relief vents 9.
Baffle plate 3 and protective case 5 form the dual-protection structure of disengagement gear; by design dual-protection structure; can effectively stop the detonation product that produces after disengagement gear work (solid residue that particularly detonation produces) to enter baffle plate 3 side areas; in addition; discontinuity surface in the middle of dual-protection structure can weaken blast impulse wave intensity by actv., thereby alleviates the adverse effect of blast impulse to fail-safe structure.Pressure relief vent 9 on baffle plate 3 is for the detonation gas of releasing, and can also play the effect of loss of weight simultaneously.
Concrete installation process is as follows: flexible linear shaped charge assembly 6 is pushed away in the installation positioning groove 7 being put in inter-stage shell section 1; protective case 5 is connected with inter-stage shell section 1 by protective case fastener 4; baffle plate 3 is connected with inter-stage shell section 1 by baffle plate fastener 2, has just completed so like this installation of cumulative flexible linear shaped charge stage separation device and shell segment structure.
Claims (4)
1. a stage separation device for aircraft, is arranged in aircraft interstage casings, it is characterized in that: comprise baffle plate, protective case, flexible linear shaped charge assembly;
Described interstage casings comprises along the circumferential weakening groove extending of interstage casings one side, along interstage casings opposite side, circumferentially extends and the relative installation positioning groove of described weakening groove; Described flexible linear shaped charge assembly is placed in described installation positioning groove; Described protective case is fixed on described interstage casings outside, and the completely coated described flexible linear shaped charge assembly of described protective case; Described baffle plate is fixed on described interstage casings outside, and described flexible linear shaped charge assembly falls into described baffle plate completely to the projection of described interstage casings.
2. according to stage separation device claimed in claim 1, it is characterized in that: described flexible linear shaped charge assembly comprises cumulative flexible linear shaped charge and rubber sheath, described cumulative flexible linear shaped charge is fixed in rubber sheath by adhesion agent.
3. according to stage separation device claimed in claim 1, it is characterized in that: described interstage casings adopts ZL114A material.
4. according to stage separation device claimed in claim 1, it is characterized in that: described baffle plate comprises the first plate, the second plate and the 3rd plate that vertical and integral type connects successively; On described the first plate, have several fastener mounting holes, baffle plate is realized and being connected of interstage casings by screw by these fastener mounting holes; The face of described the second plate is mutually vertical with the face of described interstage casings; Described the 3rd even interval of plate has a plurality of pressure relief vents.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320504193.5U CN203461147U (en) | 2013-08-19 | 2013-08-19 | Interstage separating device for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320504193.5U CN203461147U (en) | 2013-08-19 | 2013-08-19 | Interstage separating device for aircraft |
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| Publication Number | Publication Date |
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| CN203461147U true CN203461147U (en) | 2014-03-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201320504193.5U Expired - Lifetime CN203461147U (en) | 2013-08-19 | 2013-08-19 | Interstage separating device for aircraft |
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| CN (1) | CN203461147U (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104833277A (en) * | 2015-04-29 | 2015-08-12 | 北京威标至远科技发展有限公司 | Cutting device for missile stage separation |
| CN105486523A (en) * | 2014-10-13 | 2016-04-13 | 北京宇航系统工程研究所 | Allowance test assessment method for mild detonation fuse separation device |
| CN105571632A (en) * | 2014-10-09 | 2016-05-11 | 北京宇航系统工程研究所 | Mild detonation fuse separation device design verification test method |
| CN107031871A (en) * | 2016-10-14 | 2017-08-11 | 北京宇航系统工程研究所 | A kind of cutting separator of fiber-reinforced composite materials structures |
| CN108801082A (en) * | 2018-04-28 | 2018-11-13 | 长沙金信诺防务技术有限公司 | A kind of the stage separation device and installation method of multistep rocket |
| CN109856177A (en) * | 2017-11-30 | 2019-06-07 | 中国飞机强度研究所 | A kind of aircraft protective cover thermal release experimental rig |
| CN111717421A (en) * | 2020-06-04 | 2020-09-29 | 天津爱思达航天科技有限公司 | Radome fairing based on orthogonal grid structure |
| CN112109926A (en) * | 2020-08-31 | 2020-12-22 | 南京理工大学 | Explosive cutting and separating device for rapid cabin opening of aircraft |
| CN112298621A (en) * | 2020-10-30 | 2021-02-02 | 中国运载火箭技术研究院 | Separation shell of spacecraft separation device |
| CN112407342A (en) * | 2020-11-06 | 2021-02-26 | 北京宇航系统工程研究所 | Expansion pipe recess board isolating construction |
| CN112455728A (en) * | 2020-10-30 | 2021-03-09 | 中国运载火箭技术研究院 | Separation device for an aerospace vehicle |
| CN113566659A (en) * | 2020-04-29 | 2021-10-29 | 大连理工大学 | Horizontal-longitudinal separation integrated interstage linear separation device and application thereof |
| CN113581498A (en) * | 2021-06-23 | 2021-11-02 | 北京宇航系统工程研究所 | Explosion impact resistant and inward cutting separating device |
| CN113865445A (en) * | 2021-08-31 | 2021-12-31 | 北京宇航系统工程研究所 | Network separation device without booster node |
| CN115655770A (en) * | 2022-12-12 | 2023-01-31 | 四川航天川南火工技术有限公司 | Quantifiable energy-gathering cutting cable separation performance acceptance device and method |
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2013
- 2013-08-19 CN CN201320504193.5U patent/CN203461147U/en not_active Expired - Lifetime
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105571632A (en) * | 2014-10-09 | 2016-05-11 | 北京宇航系统工程研究所 | Mild detonation fuse separation device design verification test method |
| CN105571632B (en) * | 2014-10-09 | 2018-05-18 | 北京宇航系统工程研究所 | A kind of mild detonating fuze separator design evaluation test method |
| CN105486523A (en) * | 2014-10-13 | 2016-04-13 | 北京宇航系统工程研究所 | Allowance test assessment method for mild detonation fuse separation device |
| CN105486523B (en) * | 2014-10-13 | 2018-03-16 | 北京宇航系统工程研究所 | A kind of mild detonating fuze separator allowance test wire examination method |
| CN104833277A (en) * | 2015-04-29 | 2015-08-12 | 北京威标至远科技发展有限公司 | Cutting device for missile stage separation |
| CN107031871A (en) * | 2016-10-14 | 2017-08-11 | 北京宇航系统工程研究所 | A kind of cutting separator of fiber-reinforced composite materials structures |
| CN107031871B (en) * | 2016-10-14 | 2019-11-29 | 北京宇航系统工程研究所 | A kind of cutting separator of fiber-reinforced composite materials structures |
| CN109856177B (en) * | 2017-11-30 | 2021-04-20 | 中国飞机强度研究所 | Aircraft safety cover thermal separation test device |
| CN109856177A (en) * | 2017-11-30 | 2019-06-07 | 中国飞机强度研究所 | A kind of aircraft protective cover thermal release experimental rig |
| CN108801082A (en) * | 2018-04-28 | 2018-11-13 | 长沙金信诺防务技术有限公司 | A kind of the stage separation device and installation method of multistep rocket |
| CN113566659A (en) * | 2020-04-29 | 2021-10-29 | 大连理工大学 | Horizontal-longitudinal separation integrated interstage linear separation device and application thereof |
| CN113566659B (en) * | 2020-04-29 | 2024-01-16 | 大连理工大学 | Transverse-longitudinal separation integrated interstage line type separation device and application thereof |
| CN111717421A (en) * | 2020-06-04 | 2020-09-29 | 天津爱思达航天科技有限公司 | Radome fairing based on orthogonal grid structure |
| CN112109926A (en) * | 2020-08-31 | 2020-12-22 | 南京理工大学 | Explosive cutting and separating device for rapid cabin opening of aircraft |
| CN112298621A (en) * | 2020-10-30 | 2021-02-02 | 中国运载火箭技术研究院 | Separation shell of spacecraft separation device |
| CN112455728A (en) * | 2020-10-30 | 2021-03-09 | 中国运载火箭技术研究院 | Separation device for an aerospace vehicle |
| CN112407342A (en) * | 2020-11-06 | 2021-02-26 | 北京宇航系统工程研究所 | Expansion pipe recess board isolating construction |
| CN112407342B (en) * | 2020-11-06 | 2022-03-04 | 北京宇航系统工程研究所 | Expansion pipe recess board isolating construction |
| CN113581498A (en) * | 2021-06-23 | 2021-11-02 | 北京宇航系统工程研究所 | Explosion impact resistant and inward cutting separating device |
| CN113865445A (en) * | 2021-08-31 | 2021-12-31 | 北京宇航系统工程研究所 | Network separation device without booster node |
| CN113865445B (en) * | 2021-08-31 | 2022-12-27 | 北京宇航系统工程研究所 | Network separation device without booster node |
| CN115655770A (en) * | 2022-12-12 | 2023-01-31 | 四川航天川南火工技术有限公司 | Quantifiable energy-gathering cutting cable separation performance acceptance device and method |
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Granted publication date: 20140305 |
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| CX01 | Expiry of patent term |