CN104315932B - A kind of aircraft Initiator Safety detonation chain and the method for ignition - Google Patents
A kind of aircraft Initiator Safety detonation chain and the method for ignition Download PDFInfo
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- CN104315932B CN104315932B CN201410454194.2A CN201410454194A CN104315932B CN 104315932 B CN104315932 B CN 104315932B CN 201410454194 A CN201410454194 A CN 201410454194A CN 104315932 B CN104315932 B CN 104315932B
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Abstract
A kind of aircraft Initiator Safety detonation chain of the present invention and the method for ignition, the present invention first priming system anode and relay anode of powering of powering forbids power supply, and priming system circuit is placed in initial safe state; Priming system anode of powering is powered, and the follow-up electric power supply anode in certain hour interval starts power supply, enters for electric spark workpiece circuit the safe condition that powers on; By the open end of aircraft takeoff signal access solenoid, priming system circuit enters a released state; Aircraft and Separation signal are accessed solenoid, and priming system circuit enters secondary unlocking state; Fuze is applied to instantaneously the open end of solenoid, priming system detonates; Disconnect power anode and relay of priming system to power the power supply of anode, aircraft takeoff signal and aircraft disconnect with Separation signal, and priming system is in recovery initial safe state.The present invention, by automatic unlocking and detonation chain and Pyatyi initiation process, makes priming system detonate efficient, safe and reliable.
Description
Technical field
The present invention relates to a kind of aircraft Initiator Safety detonation chain and the method for ignition, belong to aircraft technical field of electric control.
Background technology
Aircraft is equipped with a large amount of priming system equipment, realizes operating these equipment safely and reliably, need the protection circuit that overall personnel are reasonable in design, ensure technical area, launch site testing reliable and secure, facilitate feasible.The successful Application of priming system automatic safe unlocking technology; launching site priming system operating process can be simplified; cancel face penetrate before pull up the operating procedure that short circuit plug connects true priming system; short circuit design circuit ensures that Initiator Safety is reliable simultaneously; and aircraft stops automatically recovering short-circuit protection state during flight, ensures its security.
Tradition rocket adopts the form of short circuit plug to carry out short-circuit protection to priming system, and at launching site, priming system short circuit plug number checks as a test event, and traditional rocket priming system protection exists following problem:
(1) external short circuit plug is set, faces to penetrate and pull up corresponding plug again, cause launching site complicated operation;
(2) priming system line test is complicated, and testing process is difficult to realize automation, and the launch site testing time is longer;
(3) sequential operating state feedback signal is rationally set to unlock command, improves reliability and the reasonability of short-circuit protection;
(4), after aircraft stops flight, automatically recover priming system short-circuit protection state, guarantee Security of test.
The precedent that automatic safe unlocking technology is not also applied on rocket.Successful Application automatic safe unlocking technology can solve fire-working article test complexity, and testing process is difficult to realize automation, the problem that the launch site testing time is longer.
How under the prerequisite ensureing short-circuit protection, reliability of opening a way after action also will ensure, aircraft flight also will recover short-circuit protection state after stopping simultaneously, needs feasible circuit reasonable in design to solve these problems
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, proposes a kind of aircraft Initiator Safety detonation chain and the method for ignition, by automatic unlocking and detonation chain and Pyatyi initiation process, priming system is detonated efficient, safe and reliable.
Technical solution of the present invention is:
A kind of aircraft Initiator Safety detonation chain comprises: electromagnetic relay KA, electromagnetic relay KB, electromagnetic relay KC, electromagnetic relay KD, electromagnetic relay KE, detonate electromagnetic relay K1;
Electromagnetic relay KA comprises again two normally opened contact KA1, KA2, solenoid KA3; Electromagnetic relay KB comprises again two normally-closed contact KB1, KB2, solenoid KB3; Electromagnetic relay KC comprises again a normally opened contact KC1, solenoid KC3; Electromagnetic relay KD comprises again a normally-closed contact KD1, solenoid KD3; Electromagnetic relay KE comprises again a normally-closed contact KE1, solenoid KE3; The electromagnetic relay K1 that detonates comprises again a normally opened contact and solenoid;
When priming system circuit is in initial safe state:
One end of normally opened contact KA2 connects priming system and to power anode, and the other end of normally opened contact KA2 connects the one end with normally opened contact KC1; The other end of normally opened contact KC1 connects one end of the normally opened contact of the electromagnetic relay K1 that detonates, and the other end of the normally opened contact of the electromagnetic relay K1 that detonates connects one end of priming system and one end of normally-closed contact KD1 simultaneously; The other end of normally-closed contact KD1 connects one end of normally-closed contact KE1; Normally-closed contact KE1 is connected priming system and powers negative terminal with the other end of one end of priming system;
One end of the solenoid of solenoid KA3, solenoid KB3, solenoid KC3, solenoid KE3, the electromagnetic relay K1 that detonates and normally opened contact KA1 connects relay and to power anode; The other end of solenoid KA3 is in open-circuit condition; The other end of solenoid KC3 connects one end of normally-closed contact KB1, and the other end of normally-closed contact KB1 connects relay and to power negative terminal; The other end of solenoid KE3 connects one end of normally-closed contact KB2, and the other end of normally-closed contact KB2 connects relay and to power negative terminal; The other end of normally opened contact KA1 connects one end of solenoid KD3, and the other end of solenoid KD3 connects relay and to power negative terminal; The other end of solenoid of electromagnetic relay K1 of detonating is in open-circuit condition; The other end of solenoid KB3 connects relay and to power negative terminal;
When priming system circuit is in and powers on safe condition:
Be connected with one end of normally opened contact KA2 and power on priming system anode of powering; The relay be connected with solenoid KA3, solenoid KB3, solenoid KC3, solenoid KE3, the solenoid of the electromagnetic relay K1 that detonates and one end of normally opened contact KA1 anode of powering powers on;
Normally-closed contact KB1, normally-closed contact KB2 open (solenoid KB3 powers on and makes normally-closed contact KB1, normally-closed contact KB2 open), solenoid KC3, solenoid KE3 and relay negative terminal of powering is made to disconnect that (one end of normally-closed contact KB1, normally-closed contact KB2 is connected solenoid KC3, solenoid KE3 respectively, the other end connects relay and to power negative terminal, so after normally-closed contact opens, both disconnect); Other circuit connecting relation maintenance priming system circuit is in circuit connecting relation during initial safe state;
When priming system circuit is in a released state:
The open end of solenoid KA3 connects aircraft takeoff signal (solenoid KA3 be connected to aircraft takeoff signal after, solenoid KA3 is powered on); Normally opened contact KA1, KA2 close, and solenoid KD3 is powered on and one end of normally opened contact KC1 connection KA2 is powered on; Normally-closed contact KD1 opens, and one end of priming system and priming system negative terminal of powering is disconnected; Other circuit connecting relation maintenance priming system circuit is in circuit connecting relation when powering on safe condition;
When priming system circuit is in secondary unlocking state:
One end of solenoid KB3 is connected to aircraft and Separation signal, and itself and relay negative terminal of powering is disconnected; Normally-closed contact KB1, normally-closed contact KB2 are closed, and solenoid KC3, solenoid KE3 and relay negative terminal of powering is connected; Normally opened contact KC1 closed (solenoid KC3 is connected with relay feeder ear negative terminal, and KC3 powers on, and making KC1 that action occur, becoming closed by opening); Normally-closed contact KE1 opens (solenoid KE3 is connected with relay feeder ear negative terminal, and KE3 powers on, and makes KE1 that action occur, and is opened by closed becoming); Other circuit connecting relation maintenance priming system circuit is in a circuit connecting relation during released state;
When priming system circuit is in and detonates state:
The open end of solenoid K1 applies fuze instantaneously, and solenoid K1 powers up; Normally opened contact K1 transient state closes (what therefore K1 opened a way that section loads is moment fuze, thus K1 end closed instantaneously after, disconnect again), ignite priming system and realize priming system and detonate; Other circuit connecting relation maintenance priming system circuit is in circuit connecting relation during secondary unlocking state;
When priming system circuit has detonated and has recovered initial safe state:
Disconnect power anode and relay of priming system to power the power supply of anode; Aircraft takeoff signal disconnects, and open circuit is recovered in one end of solenoid KA3; Aircraft and Separation signal disconnect, and one end of solenoid KB3 is in open circuit, and circuit recovers initial safe state.
Multichannel priming system can be increased detonate, by increasing multiple electromagnetic relay K1 that detonates ... KN, KD1 ... KD1N, KE1 ... KE1N realizes initiation control.
It is as follows that a kind of method of ignition of aircraft Initiator Safety detonation chain comprises step:
(1) priming system anode and relay anode of powering of powering forbids power supply, and priming system circuit is placed in initial safe state;
(2) priming system anode of powering is powered, and the follow-up electric power supply anode in certain hour interval starts power supply, enters for electric spark workpiece circuit the safe condition that powers on;
(3) broken by the open circuit of aircraft takeoff signal access solenoid KA3, priming system circuit enters a released state;
(4) aircraft and Separation signal are accessed solenoid KB3, when priming system circuit enters secondary unlocking state:
(5) fuze is applied to instantaneously the open end of solenoid K1, priming system detonates;
(6) disconnect power anode and relay of priming system to power the power supply of anode, aircraft takeoff signal and aircraft disconnect with Separation signal, and priming system is in recovery initial safe state.
The present invention's beneficial effect is compared with prior art:
(1) priming system automatic safe unlocking technology can promote the use of in other aircraft project, the design of automatic unlocking circuit instead of design short circuit plug, not only simplify fire-working article test flow process, contribute to realizing test automation, save a large amount of test jobs.And implement after unlocked time is set to more late aircraft takeoff, strengthen the security of priming system design.By this Technique Popularizing on other rockets and guided missile, facilitation can be played to the automatic test of launching flow process.
(2) the priming system method of ignition of the present invention is divided into Pyatyi initiation process, respectively through initial safe, power on safety, once unblock, secondary unlocking, initiation process, according to this method process, priming system can be made to detonate safe and reliable, can not occur by mistake quick-fried, have multi-ensuring, improve the security of priming system, and then provide cost savings, improve efficiency.
(3) feedback signal of two-stage sequential action (aircraft takeoff and Separation) is rationally set to secondary unlock command by the present invention, improve the reliability of unblock, ensure that priming system normal reliable is detonated, and prior art is unlocked by one-level to realize the unblock of rocket, relative to prior art, security reliability of the present invention improves greatly, and not because added one-level unblock, and reduce operating efficiency; The present invention simultaneously, after aircraft stops flight, automatically recovers priming system short-circuit protection state, guarantees Security of test.
Accompanying drawing explanation
Fig. 1 is priming system initial safe circuit diagram of the present invention;
Fig. 2 is that priming system of the present invention powers on safety circuit schematic diagram;
Fig. 3 is priming system of the present invention release circuit schematic diagram;
Fig. 4 is priming system secondary unlocking circuit diagram of the present invention;
Fig. 5 is priming system detonation chain schematic diagram of the present invention;
Fig. 6 is the present invention's many priming systems detonation chain schematic diagram.
Detailed description of the invention
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is further described in detail.
A kind of aircraft Initiator Safety of the present invention detonation chain comprises: electromagnetic relay KA, electromagnetic relay KB, electromagnetic relay KC, electromagnetic relay KD, electromagnetic relay KE, detonate electromagnetic relay K1; Electromagnetic relay KA comprises again two normally opened contact KA1, KA2, solenoid KA3; Electromagnetic relay KB comprises again two normally-closed contact KB1, KB2, solenoid KB3; Electromagnetic relay KC comprises again a normally opened contact KC1, solenoid KC3; Electromagnetic relay KD comprises again a normally-closed contact KD1, solenoid KD3; Electromagnetic relay KE comprises again a normally-closed contact KE1, solenoid KE3; The electromagnetic relay K1 that detonates comprises again a normally opened contact and solenoid;
As shown in Figure 1, when priming system circuit is in initial safe state:
One end of normally opened contact KA2 connects priming system and to power anode, and the other end of normally opened contact KA2 connects the one end with normally opened contact KC1; The other end of normally opened contact KC1 connects one end of the normally opened contact of the electromagnetic relay K1 that detonates, and the other end of the normally opened contact of the electromagnetic relay K1 that detonates connects one end of priming system and one end of normally-closed contact KD1 simultaneously; The other end of normally-closed contact KD1 connects one end of normally-closed contact KE1; Normally-closed contact KE1 is connected priming system and powers negative terminal with the other end of one end of priming system;
One end of the solenoid of solenoid KA3, solenoid KB3, solenoid KC3, solenoid KE3, the electromagnetic relay K1 that detonates and normally opened contact KA1 connects relay and to power anode; The other end of solenoid KA3 is in open-circuit condition; The other end of solenoid KC3 connects one end of normally-closed contact KB1, and the other end of normally-closed contact KB1 connects relay and to power negative terminal; The other end of solenoid KE3 connects one end of normally-closed contact KB2, and the other end of normally-closed contact KB2 connects relay and to power negative terminal; The other end of normally opened contact KA1 connects one end of solenoid KD3, and the other end of solenoid KD3 connects relay and to power negative terminal; The other end of solenoid of electromagnetic relay K1 of detonating is in open-circuit condition; The other end of solenoid KB3 connects relay and to power negative terminal;
As shown in Figure 2, when priming system circuit is in and powers on safe condition:
Be connected with one end of normally opened contact KA2 and power on priming system anode of powering; The relay be connected with solenoid KA3, solenoid KB3, solenoid KC3, solenoid KE3, the solenoid of the electromagnetic relay K1 that detonates and one end of normally opened contact KA1 anode of powering powers on;
Normally-closed contact KB1, normally-closed contact KB2 open (solenoid KB3 powers on and makes normally-closed contact KB1, normally-closed contact KB2 open), solenoid KC3, solenoid KE3 and relay negative terminal of powering is made to disconnect that (one end of normally-closed contact KB1, normally-closed contact KB2 is connected solenoid KC3, solenoid KE3, the other end connects relay and to power negative terminal, so after normally-closed contact opens, both disconnect); Other circuit connecting relation maintenance priming system circuit is in circuit connecting relation during initial safe state;
As shown in Figure 3, when priming system circuit is in a released state:
The open end of solenoid KA3 connects aircraft takeoff signal (solenoid KA3 be connected to aircraft takeoff signal after, solenoid KA3 is powered on); Normally opened contact KA1, KA2 close, and solenoid KD3 is powered on and one end of normally opened contact KC1 connection KA2 is powered on; Normally-closed contact KD1 opens, and one end of priming system and priming system negative terminal of powering is disconnected; Other circuit connecting relation maintenance priming system circuit is in circuit connecting relation when powering on safe condition;
As shown in Figure 4, when priming system circuit is in secondary unlocking state:
One end of solenoid KB3 is connected to aircraft and Separation signal, and itself and relay negative terminal of powering is disconnected; Normally-closed contact KB1, normally-closed contact KB2 are closed, and solenoid KC3, solenoid KE3 and relay negative terminal of powering is connected; Normally opened contact KC1 closed (solenoid KC3 is connected with relay feeder ear negative terminal, and KC3 powers on, and making KC1 that action occur, becoming closed by opening); Normally-closed contact KE1 opens (solenoid KE3 is connected with relay feeder ear negative terminal, and KE3 powers on, and makes KE1 that action occur, and is opened by closed becoming); Other circuit connecting relation maintenance priming system circuit is in a circuit connecting relation during released state;
As shown in Figure 5, when priming system circuit is in and detonates state:
The open end of solenoid K1 applies fuze instantaneously, and solenoid K1 powers up; Normally opened contact K1 transient state closes (what therefore K1 opened a way that section loads is moment fuze, thus K1 end closed instantaneously after, disconnect again), ignite priming system and realize priming system and detonate; Other circuit connecting relation maintenance priming system circuit is in circuit connecting relation during secondary unlocking state;
When priming system circuit has detonated and has recovered initial safe state:
Disconnect power anode and relay of priming system to power the power supply of anode; Aircraft takeoff signal disconnects, and open circuit is recovered in one end of solenoid KA3; Aircraft and Separation signal disconnect, and one end of solenoid KB3 is in open circuit, and circuit recovers initial safe state.
As shown in Figure 6, the present invention can also increase multichannel priming system and detonate, by increasing multiple electromagnetic relay K1 that detonates ... KN, KD1 ... KD1N, KE1 ... KE1N realizes initiation control.
It is as follows that a kind of method of ignition of aircraft Initiator Safety detonation chain comprises step:
(1) priming system anode and relay anode of powering of powering forbids power supply, and priming system circuit is placed in initial safe state;
(2) priming system anode of powering is powered, and the follow-up electric power supply anode in certain hour interval starts power supply, enters for electric spark workpiece circuit the safe condition that powers on;
(3) broken by the open circuit of aircraft takeoff signal access solenoid KA3, priming system circuit enters a released state;
(4) aircraft and Separation signal are accessed solenoid KB3, when priming system circuit enters secondary unlocking state:
(5) fuze is applied to instantaneously the open end of solenoid K1, priming system detonates;
(6) disconnect power anode and relay of priming system to power the power supply of anode, aircraft takeoff signal and aircraft disconnect with Separation signal, and priming system is in recovery initial safe state.
The content be not described in detail in description of the present invention belongs to the known technology of professional and technical personnel in the field.
Claims (3)
1. an aircraft Initiator Safety detonation chain, is characterized in that comprising: electromagnetic relay KA, electromagnetic relay KB, electromagnetic relay KC, electromagnetic relay KD, electromagnetic relay KE, detonate electromagnetic relay K1; Electromagnetic relay KA comprises again two normally opened contact KA1, KA2, solenoid KA3; Electromagnetic relay KB comprises again two normally-closed contact KB1, KB2, solenoid KB3; Electromagnetic relay KC comprises again a normally opened contact KC1, solenoid KC3; Electromagnetic relay KD comprises again a normally-closed contact KD1, solenoid KD3; Electromagnetic relay KE comprises again a normally-closed contact KE1, solenoid KE3; The electromagnetic relay K1 that detonates comprises again a normally opened contact and solenoid;
When priming system circuit is in initial safe state:
One end of normally opened contact KA2 connects priming system and to power anode, and the other end of normally opened contact KA2 connects the one end with normally opened contact KC1; The other end of normally opened contact KC1 connects one end of the normally opened contact of the electromagnetic relay K1 that detonates, and the other end of the normally opened contact of the electromagnetic relay K1 that detonates connects one end of priming system and one end of normally-closed contact KD1 simultaneously; The other end of normally-closed contact KD1 connects one end of normally-closed contact KE1; Normally-closed contact KE1 is connected priming system and powers negative terminal with the other end of priming system;
One end of the solenoid of solenoid KA3, solenoid KB3, solenoid KC3, solenoid KE3, the electromagnetic relay K1 that detonates and normally opened contact KA1 connects relay and to power anode; The other end of solenoid KA3 is in open-circuit condition; The other end of solenoid KC3 connects one end of normally-closed contact KB1, and the other end of normally-closed contact KB1 connects relay and to power negative terminal; The other end of solenoid KE3 connects one end of normally-closed contact KB2, and the other end of normally-closed contact KB2 connects relay and to power negative terminal; The other end of normally opened contact KA1 connects one end of solenoid KD3, and the other end of solenoid KD3 connects relay and to power negative terminal; The other end of solenoid of electromagnetic relay K1 of detonating is in open-circuit condition; The other end of solenoid KB3 connects relay and to power negative terminal;
When priming system circuit is in and powers on safe condition:
The priming system be connected with one end of normally opened contact KA2 anode of powering powers on; The relay be connected with solenoid KA3, solenoid KB3, solenoid KC3, solenoid KE3, the solenoid of the electromagnetic relay K1 that detonates and one end of normally opened contact KA1 anode of powering powers on;
Normally-closed contact KB1, normally-closed contact KB2 open, and solenoid KC3, solenoid KE3 and relay negative terminal of powering is disconnected; Other circuit connecting relation maintenance priming system circuit is in circuit connecting relation during initial safe state;
When priming system circuit is in a released state:
The open end of solenoid KA3 connects aircraft takeoff signal; Normally opened contact KA1, KA2 close, and solenoid KD3 is powered on and one end of normally opened contact KC1 connection KA2 is powered on; Normally-closed contact KD1 opens, and one end of priming system and priming system negative terminal of powering is disconnected; Other circuit connecting relation maintenance priming system circuit is in circuit connecting relation when powering on safe condition;
When priming system circuit is in secondary unlocking state:
One end of solenoid KB3 is connected to aircraft and Separation signal, and itself and relay negative terminal of powering is disconnected; Normally-closed contact KB1, normally-closed contact KB2 are closed, and solenoid KC3, solenoid KE3 and relay negative terminal of powering is connected; Normally opened contact KC1 closes; Normally-closed contact KE1 opens; Other circuit connecting relation maintenance priming system circuit is in a circuit connecting relation during released state;
When priming system circuit is in and detonates state:
The open end of solenoid of electromagnetic relay K1 of detonating applies fuze instantaneously, and the solenoid of the electromagnetic relay K1 that detonates powers up; The normally opened contact transient state of solenoid of electromagnetic relay K1 of detonating closes, and ignites priming system and realizes priming system and detonate; Other circuit connecting relation maintenance priming system circuit is in circuit connecting relation during secondary unlocking state;
When priming system circuit has detonated and has recovered initial safe state:
Disconnect power anode and relay of priming system to power the power supply of anode; Aircraft takeoff signal disconnects, and open circuit is recovered in one end of solenoid KA3; Aircraft and Separation signal disconnect, and one end of solenoid KB3 is in open circuit, and circuit recovers initial safe state.
2. a kind of aircraft Initiator Safety detonation chain according to claim 1, is further characterized in that: increase multichannel priming system and detonate, by increasing multiple electromagnetic relay K1 that detonates ... KN, normally-closed contact KD1 ... KD1N, KE1 ... KE1N realizes initiation control.
3., based on a method of ignition for aircraft Initiator Safety detonation chain according to claim 1, it is characterized in that step is as follows:
(1) priming system anode and relay anode of powering of powering forbids power supply, and priming system circuit is placed in initial safe state;
(2) priming system anode of powering is powered, and the follow-up electric power supply anode in certain hour interval starts power supply, enters for electric spark workpiece circuit the safe condition that powers on;
(3) broken by the open circuit of aircraft takeoff signal access solenoid KA3, priming system circuit enters a released state;
(4) aircraft and Separation signal are accessed solenoid KB3, when priming system circuit enters secondary unlocking state:
(5) fuze is applied to instantaneously the open end of the solenoid of the electromagnetic relay K1 that detonates, priming system detonates;
(6) disconnect power anode and relay of priming system to power the power supply of anode, aircraft takeoff signal and aircraft disconnect with Separation signal, and priming system is in recovery initial safe state.
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| CN201410454194.2A CN104315932B (en) | 2014-09-05 | 2014-09-05 | A kind of aircraft Initiator Safety detonation chain and the method for ignition |
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| CN201410454194.2A CN104315932B (en) | 2014-09-05 | 2014-09-05 | A kind of aircraft Initiator Safety detonation chain and the method for ignition |
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| CN104315932B true CN104315932B (en) | 2016-02-10 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
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| CN106595409B (en) * | 2016-11-15 | 2018-05-08 | 深圳市航天新源科技有限公司 | Priming system detonation constant current ignition module |
| 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 |
| CN107891993B (en) * | 2017-08-30 | 2020-12-29 | 陕西千山航空电子有限责任公司 | Safety testing method for trigger logic of detonating device |
| CN108761139B (en) * | 2018-06-19 | 2020-11-10 | 上海微小卫星工程中心 | Initiating explosive device equivalent device capable of continuously detonating and adjusting resistance value |
| CN108832958A (en) * | 2018-08-16 | 2018-11-16 | 中国人民解放军63620部队 | Take off signal shunt |
| CN109204893B (en) * | 2018-09-07 | 2021-01-05 | 北京空间技术研制试验中心 | Design method of high-reliability spacecraft and carrier rocket electrical interface |
| CN109646836B (en) * | 2018-12-06 | 2021-09-14 | 上海机电工程研究所 | Unmanned aerial vehicle carries fire extinguishing bomb activation circuit |
| CN110716518B (en) * | 2019-10-11 | 2021-12-07 | 北京航天长征飞行器研究所 | High-reliability compatible initiating explosive device control platform with multiple bus communication mechanisms |
| CN111504139B (en) * | 2020-04-16 | 2022-05-24 | 北京航天自动控制研究所 | High-power battery activation system |
| CN112130505A (en) * | 2020-09-27 | 2020-12-25 | 山东航天电子技术研究所 | Initiating explosive device ignition control circuit and method thereof |
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| US3700968A (en) * | 1971-01-20 | 1972-10-24 | Messerschmitt Boelkow Blohm | Electric fuse circuit |
| CN102122276B (en) * | 2011-01-31 | 2013-02-06 | 哈尔滨工业大学 | Double-processor borne computer |
| CN203385335U (en) * | 2013-06-27 | 2014-01-08 | 桂林航天电子有限公司 | Intelligent ignition controller of initiating explosive device |
| CN103644786B (en) * | 2013-12-03 | 2015-04-08 | 桂林航天电子有限公司 | High-voltage ignition relay and operating method thereof |
| 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 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
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| CN104315932A (en) | 2015-01-28 |
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