CN203011249U - Security insurance circuit for missile booster ignition - Google Patents
Security insurance circuit for missile booster ignition Download PDFInfo
- Publication number
- CN203011249U CN203011249U CN 201220509248 CN201220509248U CN203011249U CN 203011249 U CN203011249 U CN 203011249U CN 201220509248 CN201220509248 CN 201220509248 CN 201220509248 U CN201220509248 U CN 201220509248U CN 203011249 U CN203011249 U CN 203011249U
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- CN
- China
- Prior art keywords
- control relay
- ignition
- separation signal
- signal control
- power supply
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Abstract
A security insurance circuit for missile booster ignition comprises a missile booster ignition bridge belt and an ignition power supply, and further comprises an ignition command control relay and a separation signal control relay. A normally-opened contact point of the ignition command control relay is connected with a positive end of the ignition power supply. A public contact point of the ignition command control relay is connected with a normally-opened contact point of the separation signal control relay. A public contact point of the separation signal control relay is connected with a positive end of the missile booster ignition bridge belt, and a normally-closed contact point of the separation signal control relay is connected with negative ends of the ignition power supply and the missile booster ignition bridge belt. A coil positive end of the separation signal control relay is used for receiving a separation command output by a launch carrier. The coil positive end of the ignition command control relay is used for receiving a missile booster ignition command output by a missile. The negative ends of the ignition command control relay and the separation signal control relay are connected with the negative end of the ignition power supply. The circuit is simple in structure, high in reliability and strong in generality.
Description
Technical field
The utility model relates to guided missile Initiator Safety technology, and particularly missile booster igniting security insurance realizes technology.
Background technology
Missile booster igniting security insurance realizes having a lot of methods, and using at present is to realize by the machine insurance mode more widely.
The insurance of boost motor igniting secure mechanical adopts mechanical system to realize boost motor igniting " safety " and " fight " two states, can change between two states when receiving switching signal.When the insurance of boost motor igniting secure mechanical is in a safe condition, with the propagation of explosion passage that cuts off between boost motor safe igniter and next stage Detonating fuse assembly, prevent the boost motor safe igniter mistake ignition Detonating fuse assembly that detonates, thus guarantee boost motor store, transportation and the security that detects; When the insurance of boost motor igniting secure mechanical is under battle condition, the propagation of explosion passage of boost motor safe igniter and Detonating fuse assembly will be opened, can guarantee that safety ignitor reliably ignites Detonating fuse assembly, then ignite the dividing plate ignition tube, dividing plate ignition tube output flame ignition boost igniter, the powder charge of igniter output flame ignition boost motor.
Although the insurance of boost motor igniting secure mechanical can well realize boost motor point fire safety, but realize that this function needs than the large space volume, emitter need provide higher than 2A current drives motor simultaneously, therefore the method can not satisfy GJB1188A-99 " aircraft/hanger electric connection system interface requirement " emitter of standard code and the requirement of the little spatial volume of guided missile.
The utility model content
The purpose of this utility model is to provide a kind of small volume and the high missile booster igniting security insurance circuit of reliability, this circuit comprises boost motor initiating bridge band and igniting power supply, it is characterized in that, also comprise firing command control relay and separation signal control relay, wherein: the normally opened contact of described firing command control relay is connected with the anode of described igniting power supply, and its common is connected with the normally opened contact of separation signal control relay; The common of described separation signal control relay is connected with the anode of described boost motor initiating bridge band, and its normally-closed contact is connected negative terminal and is connected with boost motor initiating bridge band with described igniting power supply; The coil anode of described separation signal control relay is connected with the separation command of launching carrier output, the anode of the coil of described firing command control relay is connected with the boost motor firing command of missile exports, and described firing command control relay is connected the coil negative terminal and all is connected with the negative terminal of described igniting power supply with the separation signal control relay.
According to missile booster igniting security insurance circuit of the present utility model, before guided missile breaks away from launching carrier, firing command control relay and N all do not work, and the normally opened contact of two relays disconnects, and the ignition circuit between igniting power supply and initiating bridge band is in off state; Simultaneously, because the normally-closed contact of two relays is connected, make positive and negative two terminal shortcircuits of boost igniter bridge band circuit, so boost igniter is in a safe condition.When launching carrier sent separation command, guided missile broke away from launching carrier, and separation signal control relay normally opened contact adhesive this moment, normally-closed contact disconnect, and boost igniter bridge band circuit is communicated with, and the boost motor ignition circuit is under battle condition.When guided missile sent the boost motor firing command, the normally opened contact adhesive of firing command control relay, normally-closed contact disconnected, and the positive and negative end of igniting power supply and boost motor initiating bridge band all is communicated with, and realized the boost motor igniting.
Technique effect of the present utility model is, a kind of new missile booster igniting security insurance technology is provided, and has replaced mechanical type insurance of the prior art with simple relay circuit, and volume reduces greatly.Simultaneously, this circuit structure is simple, and reliability is high, and highly versatile can be widely used in the boost motor igniting security insurance circuit design of each type of missile.
Description of drawings
Fig. 1 is the schematic diagram of a specific embodiment of missile booster igniting security insurance circuit.
The specific embodiment
Below describe the utility model in detail by a most preferred embodiment of the present utility model.
As shown in Figure 1, a most preferred embodiment of missile booster igniting security insurance circuit comprises boost motor initiating bridge band, igniting power supply, relay M and relay N.Wherein, relay M is the firing command control relay, and relay N is the separation signal control relay.
As shown in Figure 1, the normally opened contact 3 of firing command control relay M is connected with the anode of igniting power supply, and its common 1 is connected with the normally opened contact 6 of separation signal control relay N; The common 4 of separation signal control relay N is connected with the anode of boost motor initiating bridge band, and its normally-closed contact 5 is connected negative terminal with the igniting power supply and is connected with boost motor initiating bridge band; The coil anode of separation signal control relay N is connected with the separation command K of launching carrier, the coil anode of firing command control relay M is connected with the boost motor firing command E of guided missile, firing command control relay M be connected with separation signal control relay N the coil negative terminal all with the igniting power supply negative terminal be connected.
The function implementation procedure of above-mentioned missile booster igniting security insurance circuit is as follows:
The first step: under safe condition (as shown in Figure 1), launching carrier is not exported separation command K, and igniting power supply power positive end is connected with the normally opened contact 3 of firing command control relay M, forms between the positive and negative terminal of igniting power supply and opens circuit, and can't power; Simultaneously be connected to form short circuit between the normally-closed contact 5 by separation command control relay N and common 4 between the positive and negative terminal of boost motor initiating bridge band, the initiating bridge band can't be worked, the igniter of boost motor is in " safety " state;
Second step: when launching carrier output separation command K, normally opened contact 6 adhesives of separation command control relay N, boost motor initiating bridge band anode is connected with the normally opened contact 6 of firing command control relay N, and normally opened contact 6 is connected with the common 1 of firing command control relay M, the boost motor ignition circuit is communicated with, and boost igniter is in " fight " state;
The 3rd step: when guided missile sends boost motor firing command E, normally opened contact 3 adhesives of firing command control relay M, igniting power supply power positive end is connected with the common 1 of firing command control relay M, connect thereby make the igniting power supply be connected anode with boost motor initiating bridge band, realize the boost motor igniting.
Claims (1)
1. a missile booster igniting security insurance circuit, comprise boost motor initiating bridge band and igniting power supply, it is characterized in that, also comprises firing command control relay and separation signal control relay, wherein:
The normally opened contact of described firing command control relay is connected with the anode of described igniting power supply, and its common is connected with the normally opened contact of separation signal control relay;
The common of described separation signal control relay is connected with the anode of described boost motor initiating bridge band, and its normally-closed contact is connected negative terminal and is connected with boost motor initiating bridge band with described igniting power supply;
The coil anode of described separation signal control relay is connected with the separation command of launching carrier output, the anode of the coil of described firing command control relay is connected with the boost motor firing command of missile exports, and described firing command control relay is connected the coil negative terminal and all is connected with the negative terminal of described igniting power supply with the separation signal control relay.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220509248 CN203011249U (en) | 2012-09-28 | 2012-09-28 | Security insurance circuit for missile booster ignition |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220509248 CN203011249U (en) | 2012-09-28 | 2012-09-28 | Security insurance circuit for missile booster ignition |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203011249U true CN203011249U (en) | 2013-06-19 |
Family
ID=48602838
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220509248 Expired - Lifetime CN203011249U (en) | 2012-09-28 | 2012-09-28 | Security insurance circuit for missile booster ignition |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203011249U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104196635A (en) * | 2014-08-18 | 2014-12-10 | 江西洪都航空工业集团有限责任公司 | Novel roll booster ignition circuit |
| CN107844085A (en) * | 2017-12-15 | 2018-03-27 | 西安航天动力测控技术研究所 | Digital safety mechanism status conversion equipment |
| CN108469763A (en) * | 2018-03-20 | 2018-08-31 | 南京壹诺为航空科技有限公司 | A kind of multi-rotor unmanned aerial vehicle loading point fire launching control system |
| CN109488487A (en) * | 2018-11-14 | 2019-03-19 | 南京云睿航天科技有限公司 | A kind of solid engines safety ignition circuit |
| CN109765059A (en) * | 2018-12-10 | 2019-05-17 | 北京强度环境研究所 | A kind of firing box front auxiliary strut disengagement time-ordered measurement method |
| CN109780945A (en) * | 2017-11-13 | 2019-05-21 | 北京机电工程研究所 | A kind of judgment method of STT missile starting point |
| CN110160414A (en) * | 2018-08-20 | 2019-08-23 | 北京机电工程研究所 | A kind of igniting bussed supply control circuit |
| CN114111485A (en) * | 2021-10-29 | 2022-03-01 | 湖北三江航天红林探控有限公司 | Self-resetting electric detonator protection circuit structure and detonation device comprising same |
-
2012
- 2012-09-28 CN CN 201220509248 patent/CN203011249U/en not_active Expired - Lifetime
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104196635A (en) * | 2014-08-18 | 2014-12-10 | 江西洪都航空工业集团有限责任公司 | Novel roll booster ignition circuit |
| CN104196635B (en) * | 2014-08-18 | 2016-02-10 | 江西洪都航空工业集团有限责任公司 | A kind of booster rocket firing circuit |
| CN109780945A (en) * | 2017-11-13 | 2019-05-21 | 北京机电工程研究所 | A kind of judgment method of STT missile starting point |
| CN109780945B (en) * | 2017-11-13 | 2021-05-11 | 北京机电工程研究所 | Judging method of missile control starting point |
| CN107844085A (en) * | 2017-12-15 | 2018-03-27 | 西安航天动力测控技术研究所 | Digital safety mechanism status conversion equipment |
| CN108469763A (en) * | 2018-03-20 | 2018-08-31 | 南京壹诺为航空科技有限公司 | A kind of multi-rotor unmanned aerial vehicle loading point fire launching control system |
| CN110160414A (en) * | 2018-08-20 | 2019-08-23 | 北京机电工程研究所 | A kind of igniting bussed supply control circuit |
| CN109488487A (en) * | 2018-11-14 | 2019-03-19 | 南京云睿航天科技有限公司 | A kind of solid engines safety ignition circuit |
| CN109488487B (en) * | 2018-11-14 | 2021-10-22 | 苏州裕谦信息科技有限公司 | Solid engine safety ignition circuit |
| CN109765059A (en) * | 2018-12-10 | 2019-05-17 | 北京强度环境研究所 | A kind of firing box front auxiliary strut disengagement time-ordered measurement method |
| CN109765059B (en) * | 2018-12-10 | 2021-06-11 | 北京强度环境研究所 | Method for measuring disengagement time sequence of front auxiliary support of launching box |
| CN114111485A (en) * | 2021-10-29 | 2022-03-01 | 湖北三江航天红林探控有限公司 | Self-resetting electric detonator protection circuit structure and detonation device comprising same |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130619 |