CN201548135U - Displacement triggering passive multifunctional non-electric detonating system - Google Patents
Displacement triggering passive multifunctional non-electric detonating system Download PDFInfo
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- CN201548135U CN201548135U CN 200920223123 CN200920223123U CN201548135U CN 201548135 U CN201548135 U CN 201548135U CN 200920223123 CN200920223123 CN 200920223123 CN 200920223123 U CN200920223123 U CN 200920223123U CN 201548135 U CN201548135 U CN 201548135U
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- explosive initiator
- primacord
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Abstract
The utility lower stage of the model discloses a displacement triggering passive multifunctional non-electric detonating system, including a mechanical detonator, a cable cutter, a manifold, explosive bolts and detonating cord components, wherein the mechanical detonator is mounted on the aircraft, the sparking pin on the mechanical detonator is connected to the wire rope, the other end of the wire rope is fixed on the upper side stage of the spacecraft; the mechanical detonator is connected to the cable cutter through a set of detonating cord components, and is connected to the explosive bolts through another group of detonating cord components by the manifold. The utility model adopts mechanical detonator, the detonation mode is simple, reliable and independent, the control system is not needed to transmit an instruction, power supply on the spacecraft is not needed to use, and the reliability of the spacecraft system is increased.
Description
Technical field
The utility model belongs to the priming system piece-rate system field of space industry, be specifically related to a kind of and aerospace craft control system fully independently displacement trigger, need not the quick-fried system of multi-functional non-fax that aerospace craft sends control instruction and the power supply that detonates is provided.
Background technology
Separating the priming system system is priming system system requisite on the aerospace craft, that realize the particular separation function.In the aerospace system design, traditional priming system piece-rate system is made up of electric initiator, the quick-fried system of non-fax and terminal firer device.Its operation principle is that control system is sent the separation command signal on the aircraft, by the priming system powered battery igniting that aircraft carries, the flashpoint initiator is according to predetermined detonation transfer route, ignite terminal firer device, finish the work and the separation function of piece-rate system priming system.The electric initiator that this kind separates the priming system system must carry out ground test before installation, after the installation, also will participate in the integration test of aircraft.
Consider that from the angle that improves the Space Vehicle System reliability aerospace craft separates the firer system must be independent fully with flight control, and do not use carry-on power supply.Therefore, original spacecraft priming system piece-rate system can not satisfy new designing requirement.Pertinent literature is not seen the report about the quick-fried piece-rate system of the independent non-fax of spacecraft by retrieval.
The utility model content
The purpose of this utility model is, overcomes the deficiencies in the prior art, provides a kind of and other system of aircraft fully independently, can realize that the displacement of reliable separation triggers the quick-fried system of passive multi-functional non-fax.
The technical solution of the utility model is: displacement triggers the quick-fried system of passive multi-functional non-fax, comprises mechanical explosive initiator, cable cutter, manifold, blasting bolt and primacord assembly; Mechanical explosive initiator is installed in the lower stage of aircraft, and the sparking pin on the mechanical explosive initiator is connected with cable wire, and the other end of cable wire is fixed on the top level of spacecraft; Mechanical explosive initiator is connected with cable cutter by one road primacord assembly, and mechanical explosive initiator links to each other with blasting bolt behind manifold by another road primacord assembly.
Described mechanical explosive initiator can normally detonate during less than 20 ° at the direction inclination angle of pulling pin.
The power of pulling pin that described mechanical explosive initiator is pulled pin is 200N～300N.
Described cable cutter can cut the cable of φ 15mm～φ 25mm.
The powder charge of described mechanical explosive initiator, cable cutter, manifold, blasting bolt and primacord assembly is the insensitiveness medicine.
Described displacement triggers the quick-fried system of passive multi-functional non-fax and adopts detonating of two-way redundancy and propagation of explosion highway route design.
Operation principle of the present utility model is: detonating of system is to be triggered by the displacement that produces in the two-stage separation process about the aerospace craft, the sparking pin that connects mechanical explosive initiator (being installed in lower stage) by the cable wire pulling of level above being installed in, when the sparking pin moves to certain stroke, two-way primacord assembly is ignited in mechanical explosive initiator work.Wherein the quick-fried cable cutter of a pass cuts off communication cable, specify separator on the blasting bolt release aircraft of ignition terminal behind the quick-fried manifold of another pass, the release of specified device mechanical interface and the disconnection of electric interfaces on the final realization aircraft, thus separation function finished.
The utility model beneficial effect compared with prior art is:
(1) because the utility model adopts mechanical explosive initiator, make detonation mode simple, reliable, independent, do not need control system to send instruction, need not use power supply on the spacecraft, increased the reliability of Space Vehicle System.System reliability of the present utility model is estimated: during reliability C=0.95, the reliability of system is R=0.998.
(2) the utility model adopts mechanical explosive initiator, and system need not tested, and removes the dependence test link of the priming system of aerospace craft electric initiating in the past from, has saved time and funds.
(3) because the utility model adopts mechanical explosive initiator, therefore do not have antistatic, preventing RF problem, security of system is good.
(4) at aerospace craft up and down in the separation of two-stage, displacement of the present utility model triggers the quick-fried system of passive multi-functional non-fax and adopts detonating of two-way redundancy and propagation of explosion highway route design, has increased the reliability that aircraft separates.
Description of drawings
Fig. 1 is the quick-fried system schematic of passive multi-functional non-fax for displacement triggers.
Fig. 2 is that two groups of redundant each other displacements trigger the quick-fried system schematic of passive multi-functional non-fax.
The specific embodiment
The utility model is described in further detail below in conjunction with accompanying drawing.
As shown in Figure 1, for displacement of the present utility model triggers the quick-fried system of passive multi-functional non-fax, comprise mechanical explosive initiator 1, cable cutter 2, manifold 3, blasting bolt 4 and primacord assembly 5.
Mechanical explosive initiator 1 is installed in the lower stage of aircraft, and the sparking pin on the mechanical explosive initiator 1 is connected with cable wire, and the other end of cable wire is fixed on the top level of spacecraft; Mechanical explosive initiator 1 is connected with cable cutter 2 by one group of primacord assembly 5; Mechanical explosive initiator 1 links to each other with four groups of blasting bolts 4 behind manifold 3 by another group primacord assembly 5.
After the sparking pin of mechanical explosive initiator 1 is drawn out, the output detonation of starting working, by two-way primacord assembly 5 propagation of explosions: the quick-fried cable cutter 2 of a pass wherein, cut off and carry-on communication cable; The blasting bolt 4 of terminal is ignited in the quick-fried manifold of another pass 3 backs.
In the present embodiment, 20 ° at the inclination angle of the direction of pulling pin, the power of pulling pin is 300N; The cable φ 25mm of cutting.
In the present embodiment, the powder charge of mechanical explosive initiator 1, cable cutter 2, manifold 3, blasting bolt 4 and primacord assembly 5 is the insensitiveness medicine.When produce in the separation process of spacecraft the superior and the subordinate be displaced to setpoint distance after, the sparking pin of mechanical explosive initiator 1 is drawn out, thereby triggers whole system work, realizes separation function.
As shown in Figure 1, for displacement of the present utility model triggers the quick-fried system of passive multi-functional non-fax, comprise mechanical explosive initiator 1, cable cutter 2, manifold 3, blasting bolt 4 and primacord assembly 5.
Mechanical explosive initiator 1 is installed in the lower stage of aircraft, and the sparking pin on the mechanical explosive initiator 1 is connected with cable wire, and the other end of cable wire is fixed on the top level of spacecraft; Mechanical explosive initiator 1 is connected with cable cutter 2 by one group of primacord assembly 5; Mechanical explosive initiator 1 links to each other with four groups of blasting bolts 4 behind manifold 3 by another group primacord assembly 5.
After the sparking pin of mechanical explosive initiator 1 is drawn out, the output detonation of starting working, by two-way primacord assembly 5 propagation of explosions: the quick-fried cable cutter 2 of a pass wherein, cut off and carry-on communication cable; The blasting bolt 4 of terminal is ignited in the quick-fried manifold of another pass 3 backs.
In the present embodiment, 15 ° at the inclination angle of the direction of pulling pin, the power of pulling pin is 200N; The cable φ 15mm of cutting.
In the present embodiment, the powder charge of mechanical explosive initiator 1, cable cutter 2, manifold 3, blasting bolt 4 and primacord assembly 5 is the insensitiveness medicine.When produce in the separation process of spacecraft the superior and the subordinate be displaced to setpoint distance after, the sparking pin of mechanical explosive initiator 1 is drawn out, thereby triggers whole system work, realizes separation function.
As shown in Figure 2, for displacement of the present utility model triggers the quick-fried system of passive multi-functional non-fax, whole system uses detonating of two-way redundancy and propagation of explosion route.
Comprise two groups of mechanical explosive initiators 1, cable cutter 2, two groups of manifolds 3, four groups of blasting bolts 4 and the primacord assembly 5 that works the effect of connection.
Mechanical explosive initiator 1 is installed in the lower stage of aircraft, and the sparking pin on the mechanical explosive initiator 1 is connected with cable wire, and the other end of cable wire is fixed on the top level of spacecraft.Mechanical explosive initiator 1 is connected with cable cutter 2 by one group of primacord assembly 5; Mechanical explosive initiator 1 links to each other with four groups of blasting bolts 4 behind manifold 3 by another group primacord assembly 5.
After the sparking pin of mechanical explosive initiator 1 is drawn out, the output detonation of starting working, by two-way primacord assembly 5 propagation of explosions: the quick-fried cable cutter 2 of a pass wherein, cut off and carry-on communication cable; The blasting bolt 4 of terminal is ignited in the quick-fried manifold of another pass 3 backs.
In the present embodiment, 15 ° at the inclination angle of the direction of pulling pin, the power of pulling pin is 200N; The cable Φ 15mm of cutting.In the present embodiment, the powder charge of mechanical explosive initiator 1, cable cutter 2, manifold 3, blasting bolt 4 and primacord assembly 5 is the insensitiveness medicine.
When produce in the separation process of spacecraft the superior and the subordinate be displaced to certain distance after, the sparking pin of mechanical explosive initiator 1 is drawn out, thereby triggers whole system work, realizes separation function.
The utility model is by the surface separation verification experimental verification, and the piece-rate system function is normal, and dependable performance has realized and independently requirement of spacecraft control.
Certainly, under the situation that does not change its function, the equivalent transformation that carries out or alternative also falls into protection domain of the present utility model to each building block of the present utility model, position relation and connected mode.The undocumented technology of the utility model belongs to techniques well known.
Claims (6)
1. displacement triggers the quick-fried system of passive multi-functional non-fax, it is characterized in that: comprise mechanical explosive initiator (1), cable cutter (2), manifold (3), blasting bolt (4) and primacord assembly (5); Mechanical explosive initiator (1) is installed in the lower stage of aircraft, and the sparking pin on the mechanical explosive initiator (1) connects cable wire, and the other end of cable wire is fixed on the top level of spacecraft; Mechanical explosive initiator (1) is connected with cable cutter (2) by one group of primacord assembly (5), links to each other with blasting bolt (4) behind manifold (3) by another group primacord assembly (5).
2. the displacement according to claim 1 triggers the quick-fried system of passive multi-functional non-fax, it is characterized in that: described mechanical explosive initiator (1) can normally detonate during less than 20 ° at the direction inclination angle of pulling pin.
3. the displacement according to claim 1 triggers the quick-fried system of passive multi-functional non-fax, and it is characterized in that: the power of pulling pin that described mechanical explosive initiator (1) is pulled pin is 200N～300N.
4. the displacement according to claim 1 triggers the quick-fried system of passive multi-functional non-fax, and it is characterized in that: described cable cutter (2) can cut the cable of φ 15mm～φ 25mm.
5. the displacement according to claim 1 triggers the quick-fried system of passive multi-functional non-fax, and it is characterized in that: the powder charge of described mechanical explosive initiator (1), cable cutter (2), manifold (3), blasting bolt (4) and primacord assembly (5) is the insensitiveness medicine.
6. the displacement according to claim 1 triggers the quick-fried system of passive multi-functional non-fax, and it is characterized in that: described displacement triggers the quick-fried system of passive multi-functional non-fax, adopts detonating and the propagation of explosion highway route design of two-way redundancy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200920223123 CN201548135U (en) | 2009-09-28 | 2009-09-28 | Displacement triggering passive multifunctional non-electric detonating system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200920223123 CN201548135U (en) | 2009-09-28 | 2009-09-28 | Displacement triggering passive multifunctional non-electric detonating system |
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| Publication Number | Publication Date |
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| CN201548135U true CN201548135U (en) | 2010-08-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 200920223123 Expired - Lifetime CN201548135U (en) | 2009-09-28 | 2009-09-28 | Displacement triggering passive multifunctional non-electric detonating system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103678942A (en) * | 2013-12-31 | 2014-03-26 | 北京宇航系统工程研究所 | Reliability evaluation method for non-electric explosion propagation firer system |
| CN106382859A (en) * | 2016-09-07 | 2017-02-08 | 中国航天科技集团公司川南机械厂 | Hot working sequential controlled opening ignition spreading device |
| CN113804060A (en) * | 2021-08-30 | 2021-12-17 | 四川航天川南火工技术有限公司 | Self-defined combined non-electric network booster structure of multi-input multi-output booster route |
-
2009
- 2009-09-28 CN CN 200920223123 patent/CN201548135U/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103678942A (en) * | 2013-12-31 | 2014-03-26 | 北京宇航系统工程研究所 | Reliability evaluation method for non-electric explosion propagation firer system |
| CN103678942B (en) * | 2013-12-31 | 2017-01-25 | 北京宇航系统工程研究所 | Reliability evaluation method for non-electric explosion propagation firer system |
| CN106382859A (en) * | 2016-09-07 | 2017-02-08 | 中国航天科技集团公司川南机械厂 | Hot working sequential controlled opening ignition spreading device |
| CN106382859B (en) * | 2016-09-07 | 2018-06-22 | 中国航天科技集团公司川南机械厂 | A kind of igniting scattering mechanism that opens the cabin of firer's timing control |
| CN113804060A (en) * | 2021-08-30 | 2021-12-17 | 四川航天川南火工技术有限公司 | Self-defined combined non-electric network booster structure of multi-input multi-output booster route |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20100811 |