CN203225576U - Double-channel initiating explosive device igniting circuit - Google Patents
Double-channel initiating explosive device igniting circuit Download PDFInfo
- Publication number
- CN203225576U CN203225576U CN 201320098785 CN201320098785U CN203225576U CN 203225576 U CN203225576 U CN 203225576U CN 201320098785 CN201320098785 CN 201320098785 CN 201320098785 U CN201320098785 U CN 201320098785U CN 203225576 U CN203225576 U CN 203225576U
- Authority
- CN
- China
- Prior art keywords
- relay
- igniting
- power supply
- contact
- circuit
- Prior art date
- 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
Links
Images
Abstract
Disclosed is a double-channel initiating explosive device igniting circuit. The double-channel initiating explosive device igniting circuit comprises a power supply relay and two igniting relays, and the two igniting relays are in parallel connection. A movable contact of the power supply relay is connected with one end of an igniting power supply, and a normally-closed contact of the power supply relay is connected with a first movable contact of each igniting relay; the igniting relay supplies power for igniting bridges of two initiating explosive devices, each igniting relay comprises two sets of contact switches, and the connection method is that the first movable contact of each igniting relay is connected with the normally-closed contact of the power supply relay, the first normally-open contact of each igniting relay is connected with one end of the igniting bridge of each initiating explosive device, the second movable contact of each igniting relay is connected with the other end of the igniting power supply, and the second normally-open contact of each igniting relay is connected with the other end of the igniting bridge of each initiating explosive device. The double-channel initiating explosive device igniting circuit provides overall consideration of factors such as igniting circuit multistage safety insurance, igniting circuit positive-negative double control and redundancy backup output, and has high reliability and strong versatility.
Description
Technical field
The utility model relates to a kind of circuit, especially a kind of original text reliability priming system firing circuit for aircraft.
Background technology
In guided missile or other aircraft, need sometimes the two-way priming system is powered, it is quick-fried to be used for point.Domestic research about submarine navigation device priming system sparking mode at present seldom, sparking mode commonly used is the ignition mode of over-borrowing mirror guided missile also, the flight zero signal (transmitting) of the full bullet of the signal of separation connector or travel switch and firing box separation process conversion conduct when for example utilizing MISSILE LAUNCHING, and then by IGNITION CONTROL single or one group of (2) relay realization priming system circuit.
At present, on the guided missile to single priming system with the firing circuit of single relay control as shown in Figure 1, its basic principle is as follows: select single double-contact or multifinger relay, apply the mode control relay adhesive that priming system is put quick-fried instruction by the outside, igniting power supply on the bullet is inserted priming system igniting anode, for preventing that the quick-fried back of priming system moment point circuit overcurrent from may impact ignition circuit or miscellaneous equipment, increased the current-limiting resistance that can directly fuse behind the overcurrent in firing circuit.
Adopt the firing circuit of one group of (2) relay control as shown in Figure 2, mainly use different relays to carry out IGNITION CONTROL respectively to each priming system, and then the function of realization redundancy backup, its basic principle is as follows: select one group of (2) contact or multifinger relay, feeder ear and control end are together in parallel respectively, when the outside applies the quick-fried instruction of priming system point, 2 relay adhesives simultaneously, power supply on the relay contact inserts priming system igniting anode through relay, and the use of current-limiting resistance is in full accord in the firing circuit of the use of current-limiting resistance and above-mentioned single relay control.
The firing circuit simplicity of design of single relay control, but also have following problem: (1) when relay contact can not regular event or relay itself exist fault can't adhesive the time, may cause the firing circuit can't normal ignition; (2) if the asynchronous asynchronism that also may cause priming system 1,2 igniting of two groups of contact actions of relay; (3) because priming system igniting negative terminal is not controlled, the priming system existence is subjected to the unusual quick-fried possibility of unexpected point of disturbing; (4) igniting power supply anode is uncontrolled amounts, and the firing circuit level of security is lower, exists relay misoperation to do or mistake is sent out the possibility of priming system accidental ignition when priming system point is quick-fried to instruct.
The firing circuit of one group of (2) relay control has been realized two redundancy features of firing circuit, preferably resolve above-mentioned when relay contact can not regular event or relay itself exist fault can't adhesive the time, may cause the problem that firing circuit can't normal ignition, but (2), (3), (4) the three class faults that exist in the firing circuit for single relay control, above-mentioned firing circuit also can't fundamentally solve.
The utility model content
The purpose of this utility model provides a kind of new two-way priming system firing circuit, further improves the reliability of firing circuit.
For achieving the above object, two-way priming system firing circuit of the present utility model comprises the ignition relay of a power supply relay and two parallel connections, wherein:
The moving contact of described power supply relay is connected with an end of igniting power supply, and its normally-closed contact is connected with first moving contact of ignition relay respectively;
Described ignition relay is respectively the some firebridge band power supply of two priming systems, each relay includes two cover contact switchs, its connected mode is: first moving contact of ignition relay is connected with the normally-closed contact of power supply relay respectively, first normally opened contact is connected with an end of priming system point firebridge band respectively, second moving contact is connected with the other end of igniting power supply respectively, and second normally opened contact is connected with the other end of priming system point firebridge band respectively;
Described power supply relay cuts off the power supply when receiving firing order, and described ignition relay gets when receiving a little quick-fried instruction.
Operation principle of the present utility model is, when guided missile or aircraft power on, power supply relay gets, the igniting power supply is connected with normally opened contact by the moving contact of power supply relay, this moment, the moving contact of ignition relay was in vacant state in pairs, even put quick-fried instruction by false triggering, can guarantee that also priming system can be by overdue not quick-fried.Only when the emission of guided missile or aircraft, the moving contact that the coil losing electricity of power supply relay, igniting power supply moving contact and the normally-closed contact by power supply relay is connected to ignition relay.At this moment, when ignition relay is received a little quick-fried instruction, its moving contact and normally opened contact are closed respectively, the positive and negative two ends of priming system point firebridge band and the positive and negative two ends of the power supply of lighting a fire are connected respectively, thereby put quick-fried priming system.
The utility model utilization transmits and realizes the positive control of igniting power supply, two controls are realized by the relay multiconductor again in the positive and negative two ends of igniting power supply, priming system 1,2 redundancy output have been realized, this firing circuit is by arranging the multilevel security insurance, the positive and negative two controls of firing circuit and redundancy backup are combined, improve the reliability of firing circuit, had certain practical value.
The utility model has been taken all factors into consideration the insurance of firing circuit multilevel security and aspect factors such as the positive and negative two controls of firing circuit and redundancy backup output, this ignition circuit height, highly versatile, can be widely used in the supercavity aircraft is in the various ignition circuit of representative.
Description of drawings
Fig. 1 is the firing circuit schematic diagram of single relay control;
Fig. 2 is the firing circuit schematic diagram of group relay control;
Fig. 3 is the schematic diagram of the utility model two-way priming system firing circuit.
Embodiment
As shown in Figure 4, two-way priming system firing circuit mainly comprises power supply relay K1 and two ignition relay K2, K3.Wherein, the igniting of two priming systems is controlled in K2 and K3 parallel connection respectively, and their connections in circuit are identical.For convenience of description, suppose that this circuit application is in certain supercavity aircraft.
The moving contact 11 of power supply relay K1 is connected with igniting power supply anode, and normally-closed contact 12 is connected with first moving contact 21,31 of ignition relay K2, K3 respectively, and normally opened contact 13 is unsettled.Among the figure, relay K 1 also has a cover contact switch 14,15,16 as redundancy backup, and its connected mode is identical with above-mentioned contact.The coil of relay K 1 gets electric after the supercavity aircraft enters standby condition, dead electricity when receiving firing order P.
Ignition relay K2, K3 have two cover contact switchs.Wherein, the normally-closed contact 22 of first cover in the contact switch, 32 unsettled, normally opened contact 23 and 33 is connected the anode of the some firebridge band of priming system 1 and priming system 2 respectively with R2 by current-limiting resistance R1.In the second cover contact switch of ignition relay, moving contact 24,34 is connected with the negative terminal of igniting power supply respectively, and normally-closed contact 25 and 35 is unsettled, and normally opened contact 26 and 36 is connected the negative terminal of the some firebridge band of priming system 1 and priming system 2 respectively.Relay K 2 and K3 get when receiving the quick-fried instruction of priming system point E.
Operation principle of the present utility model is as follows:
The first step: when relay K 1 coil is applied externally fed (this moment, the supercavity aircraft entered standby condition), moving contact 11 and 14 on the relay K 1 respectively with normally opened contact 13,16 adhesives, the igniting power supply exports on contact 13 and 16 through 11 on the relay K 1 and 14.
Second step: when the supercavity aircraft is launched, firing order P makes the coil losing electricity of relay K 1, contact 11 and 14 on the relay K 1 disconnects with 13 and 16 respectively, this moment, the moving point 21 and 31 of relay K 2, K3 was delivered in the igniting power supply just respectively, the negative moving point 24 and 34 that remains at relay K 2, K3 of igniting power supply.
The 3rd step: when relay K 2, K3 coil are applied the quick-fried instruction of priming system point E, relay K 2, K3 adhesive, its moving contact respectively with the normally opened contact adhesive, just deliver to the some firebridge band of priming system 1 and priming system 2 behind the decent current-limiting resistance of igniting power supply, the negative some firebridge band that connects priming system 1 and priming system 2 of igniting power supply is born, and realizes the redundancy backup of igniting.
Above-mentioned firing circuit has been taken all factors into consideration the insurance of firing circuit multilevel security and aspect factors such as the positive and negative two controls of firing circuit and redundancy backup output, this ignition circuit height, highly versatile, can be widely used in the supercavity aircraft is in the various ignition circuit of representative.
Claims (3)
1. a two-way priming system firing circuit is characterized in that, comprises the ignition relay of a power supply relay and two parallel connections, wherein:
The moving contact of described power supply relay is connected with an end of igniting power supply, and its normally-closed contact is connected with first moving contact of ignition relay respectively;
Described ignition relay is respectively the some firebridge band power supply of two priming systems, each relay includes two cover contact switchs, its connected mode is: first moving contact of ignition relay is connected with the normally-closed contact of power supply relay respectively, first normally opened contact is connected with an end of priming system point firebridge band respectively, second moving contact is connected with the other end of igniting power supply respectively, and second normally opened contact is connected with the other end of priming system point firebridge band respectively;
Described power supply relay cuts off the power supply when receiving firing order, and described ignition relay gets when receiving a little quick-fried instruction.
2. circuit as claimed in claim 1 is characterized in that, the moving contact of described power supply relay is connected with the anode of igniting power supply, and second moving contact of described ignition relay is connected with the negative terminal of igniting power supply.
3. circuit as claimed in claim 1 is characterized in that, is provided with current-limiting resistance between first normally opened contact of described priming system point firebridge band and ignition relay or second normally opened contact.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320098785 CN203225576U (en) | 2013-03-05 | 2013-03-05 | Double-channel initiating explosive device igniting circuit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320098785 CN203225576U (en) | 2013-03-05 | 2013-03-05 | Double-channel initiating explosive device igniting circuit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203225576U true CN203225576U (en) | 2013-10-02 |
Family
ID=49252566
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320098785 Expired - Lifetime CN203225576U (en) | 2013-03-05 | 2013-03-05 | Double-channel initiating explosive device igniting circuit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203225576U (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103997031A (en) * | 2014-05-16 | 2014-08-20 | 上海微小卫星工程中心 | Initiating explosive device control circuit and controller using same |
| CN104407524A (en) * | 2014-10-10 | 2015-03-11 | 中国航天科技集团公司第四研究院第四十一研究所 | Far-end time synchronization igniting control circuit used for launch control equipment and control method thereof |
| CN105514979A (en) * | 2015-11-30 | 2016-04-20 | 上海卫星工程研究所 | Satellite power distribution system with high electromagnetic compatibility |
| CN106643349A (en) * | 2016-11-24 | 2017-05-10 | 江西洪都航空工业集团有限责任公司 | Automatic triggering type ignition circuit |
| CN106786392A (en) * | 2016-12-15 | 2017-05-31 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aero-engine ignition power cutting circuit |
| CN107168164A (en) * | 2017-05-27 | 2017-09-15 | 国家电网公司 | The live double authoring systems of Practical training equipment safety |
| CN109578147A (en) * | 2018-10-31 | 2019-04-05 | 四川泛华航空仪表电器有限公司 | A kind of igniter being automatically repaired |
| 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 |
| CN112650192A (en) * | 2020-11-05 | 2021-04-13 | 北京电子工程总体研究所 | General explosion simulator for initiating explosive devices |
-
2013
- 2013-03-05 CN CN 201320098785 patent/CN203225576U/en not_active Expired - Lifetime
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103997031A (en) * | 2014-05-16 | 2014-08-20 | 上海微小卫星工程中心 | Initiating explosive device control circuit and controller using same |
| CN104407524A (en) * | 2014-10-10 | 2015-03-11 | 中国航天科技集团公司第四研究院第四十一研究所 | Far-end time synchronization igniting control circuit used for launch control equipment and control method thereof |
| CN104407524B (en) * | 2014-10-10 | 2017-02-01 | 中国航天科技集团公司第四研究院第四十一研究所 | Far-end time synchronization igniting control circuit used for launch control equipment and control method thereof |
| CN105514979A (en) * | 2015-11-30 | 2016-04-20 | 上海卫星工程研究所 | Satellite power distribution system with high electromagnetic compatibility |
| CN105514979B (en) * | 2015-11-30 | 2019-05-17 | 上海卫星工程研究所 | The satellite distribution system of high electrical-magnetic compatibility energy |
| CN106643349B (en) * | 2016-11-24 | 2018-12-14 | 江西洪都航空工业集团有限责任公司 | A kind of automatic trigger firing circuit |
| CN106643349A (en) * | 2016-11-24 | 2017-05-10 | 江西洪都航空工业集团有限责任公司 | Automatic triggering type ignition circuit |
| CN106786392B (en) * | 2016-12-15 | 2018-08-24 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aero-engine ignition power cutting circuit |
| CN106786392A (en) * | 2016-12-15 | 2017-05-31 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aero-engine ignition power cutting circuit |
| CN107168164A (en) * | 2017-05-27 | 2017-09-15 | 国家电网公司 | The live double authoring systems of Practical training equipment safety |
| CN107168164B (en) * | 2017-05-27 | 2023-06-02 | 国家电网公司 | Safety double-authorization system for field training equipment |
| 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 |
| CN109578147A (en) * | 2018-10-31 | 2019-04-05 | 四川泛华航空仪表电器有限公司 | A kind of igniter being automatically repaired |
| CN109578147B (en) * | 2018-10-31 | 2022-01-11 | 四川泛华航空仪表电器有限公司 | Ignition device capable of automatically repairing |
| CN112650192A (en) * | 2020-11-05 | 2021-04-13 | 北京电子工程总体研究所 | General explosion simulator for initiating explosive devices |
| CN112650192B (en) * | 2020-11-05 | 2021-12-07 | 北京电子工程总体研究所 | General explosion simulator for initiating explosive devices |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203225576U (en) | Double-channel initiating explosive device igniting circuit | |
| CN103956822B (en) | A kind of satellite power system of fast integration | |
| CN104895700B (en) | A kind of low time delay ignition confirming system and confirmation method of arrow ground information fusion | |
| CN203011249U (en) | Security insurance circuit for missile booster ignition | |
| CN101776427A (en) | Multipath electric detonator priming device with self test and line fault test function and method | |
| CN206321146U (en) | A kind of priming system firing circuit | |
| CN103997031A (en) | Initiating explosive device control circuit and controller using same | |
| CN109391131A (en) | A kind of submodule of MMC valve by-pass switch driving device | |
| CN109795720B (en) | Detonation control design method of initiating explosive device for spacecraft cabin separation | |
| CN201488662U (en) | Complete round test safety control circuit | |
| CN203205850U (en) | Breaker tripping coil protector for | |
| CN109659916A (en) | A kind of multifunctional safe circuit and its control method | |
| CN203951254U (en) | One comes off to power and disconnects control circuit | |
| CN105305595B (en) | A kind of distribution holding circuit applied to airborne equipment | |
| CN109318714A (en) | Electric automobile high-voltage distribution system power-on and power-off control method | |
| CN106229570A (en) | A kind of double cell handoff-security control system and method for handover control thereof | |
| CN104196635B (en) | A kind of booster rocket firing circuit | |
| CN203445612U (en) | Multipath continuous heavy current pulse output control circuit | |
| CN109818569B (en) | Parallel type turn-off system for photovoltaic module and method for restarting after turn-off | |
| CN203444275U (en) | Detonation control circuit based on 1553B bus | |
| CN202304642U (en) | Ignition circuit with interlocking input and output | |
| CN104485706B (en) | Discharge circuit for lithium battery pack | |
| CN208421605U (en) | A kind of general-purpose aircraft store Combinations putting control system | |
| CN104037935B (en) | A kind of Double Power Switch Controller of band short circuit tripping protection | |
| CN202836379U (en) | Guided missile separative signal antifault circuit |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20131002 |
|
| CX01 | Expiry of patent term |