CN104454240A - Ignition control circuit for booster of aircraft - Google Patents
Ignition control circuit for booster of aircraft Download PDFInfo
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- CN104454240A CN104454240A CN201410674896.1A CN201410674896A CN104454240A CN 104454240 A CN104454240 A CN 104454240A CN 201410674896 A CN201410674896 A CN 201410674896A CN 104454240 A CN104454240 A CN 104454240A
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- control circuit
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- ignition
- igniting
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Abstract
The invention relates to the field of ignition control of aircrafts, in particular to an ignition control circuit for a booster of an aircraft. The ignition control circuit for the booster of the aircraft comprises an ignition power supply control circuit A, an ignition signal control circuit and an ignition power supply control circuit B. The ignition signal control circuit sends an ignition signal to the ignition power supply control circuit B, the ignition power supply control circuit B enables an ignition power source line to be connected, and the ignition power supply control circuit A enables the ignition power source line to be connected to the booster for ignition. The ignition control circuit for the booster of the aircraft has the advantages of improving fighter plane flying safety and task reliability of the aircraft.
Description
Technical field
The present invention relates to aircraft IGNITION CONTROL field, relate to a kind of booster rocket ignition control circuit of aircraft specifically.
Background technique
At present, the aircraft aloft launched, realizes and being separated of carrier aircraft mainly through releasing type and railway separating two kinds of modes, thus realizes autonomous flight.Its middle orbit separate mode, is the thrust produced after utilizing booster rocket to light a fire, promotes aircraft at tracks travel, realize being separated with carrier aircraft machine.
In design in the past, as long as aircraft sends booster rocket fire signal, namely complete booster rocket igniting, its representative point ignition circuit is as accompanying drawing 2.This firing circuit lacks carrier aircraft signal and participates in controlling, and Security is lower, if do not possess launching condition, aircraft sends out fire signal by mistake, will light booster rocket, cause mission failure, and affect carrier aircraft flight safety.
Summary of the invention
The object of the invention is to solve the problem, a kind of booster rocket ignition control circuit of aircraft is provided.
In order to realize object of the present invention, the technical solution used in the present invention is:
A kind of booster rocket ignition control circuit of aircraft, comprise igniting electric control circuit A, fire signal control circuit and igniting electric control circuit B, fire signal control circuit sends fire signal to igniting electric control circuit B, igniting electric control circuit B cut-in point ignition source circuit, igniting electric control circuit A connects ignition circuit and lights a fire to booster rocket.
Described fire signal control circuit comprises the first relay, and the coil of the first relay accepts the control signal C1 that carrier aircraft sends and controls, and the contact of the first relay connects booster rocket fire signal, and the contact of another side connects igniting power-supplying circuit B.
Igniting electric control circuit A comprises the 4th relay, and the coil of the 4th relay accepts the control signal C2 that carrier aircraft sends and controls, the 4th relay contact connect booster rocket, the contact of another side connects igniting power-supplying circuit B.
Igniting electric control circuit B comprises the 3rd relay, and fire signal control circuit controls the coil motion of the 3rd relay, and the contact of the 3rd relay connects igniting power-supplying circuit A, and the contact of the 3rd relay another side connects power supply and ground connection respectively.
Igniting electric control circuit B also comprises the second relay, the coil of the second relay accepts the SC sigmal control that igniting signal control circuit sends, second relay contact is on one side connected with fire signal control circuit, and the contact of the second relay another side is connected with power supply.
Beneficial effect of the present invention is: improve carrier aircraft flight safety and aircraft mission reliability.
Accompanying drawing explanation
Fig. 1 is principle of the invention figure,
Fig. 2 is not for improve circuit diagram.
Embodiment
Below in conjunction with drawings and Examples, the present invention is further described:
Embodiment: see Fig. 1.
A kind of booster rocket ignition control circuit of aircraft, comprise igniting electric control circuit A, fire signal control circuit and igniting electric control circuit B, fire signal control circuit sends fire signal to igniting electric control circuit B, igniting electric control circuit B cut-in point ignition source circuit, igniting electric control circuit A connects ignition circuit and lights a fire to booster rocket 5.
The coil that described fire signal control circuit comprises the first relay 1, first relay 1 accepts the control signal C1 that carrier aircraft sends and controls, and the contact of the first relay 1 connects booster rocket fire signal, and the contact of another side connects igniting power-supplying circuit B.
The coil that igniting electric control circuit A comprises the 4th relay the 4, four relay 4 accepts the control signal C2 that carrier aircraft sends and controls, the 4th relay 4 contact connect booster rocket, the contact of another side connects igniting power-supplying circuit B.
Igniting electric control circuit B comprises the 3rd relay 3, fire signal control circuit controls the coil motion of the 3rd relay 3,3rd relay 3 contact on one side connects igniting power-supplying circuit A, and the contact of the 3rd relay 3 another side connects power supply and ground connection respectively.
Igniting electric control circuit B also comprises the second relay 2, the coil of the second relay 2 accepts the SC sigmal control that igniting signal control circuit sends, second relay 2 contact is on one side connected with fire signal control circuit, and the contact of the second relay 2 another side is connected with power supply.
Working principle of the present invention is: booster rocket igniting electric line A, and when carrier aircraft sends control signal C1, the 4th relay 4 completes contact conversion, connects booster rocket igniting electric line A; Booster rocket fire signal circuit, completes contact conversion when the first relay 1 receives the control signal C2 that carrier aircraft sends, connect booster rocket fire signal circuit; Now aircraft sends booster rocket fire signal, and trigger the second relay 2 and the 3rd relay 3 action, the second relay 2 keeps the 3rd relay 3 continuous firing, completes contact conversion, connects booster rocket igniting electric line A; Complete last booster rocket 5 to light a fire task.
The present invention when any one does not send at carrier aircraft control signal C1, C2, even if aircraft sends booster rocket fire signal by mistake, also cannot complete booster rocket 5 and light a fire, ensure that the safety of carrier aircraft.
Embodiments of the invention announce be one of preferred embodiment also; but be not limited thereto; those of ordinary skill in the art; very easily according to above-described embodiment; understand spirit of the present invention; and make different amplifications and change, but only otherwise depart from spirit of the present invention, all in protection scope of the present invention.
Claims (5)
1. the booster rocket ignition control circuit of an aircraft, comprise igniting electric control circuit A, fire signal control circuit and igniting electric control circuit B, it is characterized in that: fire signal control circuit sends fire signal to igniting electric control circuit B, igniting electric control circuit B cut-in point ignition source circuit, igniting electric control circuit A connects ignition circuit and lights a fire to booster rocket.
2. the booster rocket ignition control circuit of a kind of aircraft according to claim 1, it is characterized in that: described fire signal control circuit comprises the first relay, the coil of the first relay accepts the control signal C1 that carrier aircraft sends and controls, the contact, one side of the first relay connects booster rocket fire signal, and the contact of another side connects igniting power-supplying circuit B.
3. the booster rocket ignition control circuit of a kind of aircraft according to claim 2, it is characterized in that: igniting electric control circuit A comprises the 4th relay, the coil of the 4th relay accepts the control signal C2 that carrier aircraft sends and controls, the contact on one side of the 4th relay connects booster rocket, and the contact of another side connects igniting power-supplying circuit B.
4. the booster rocket ignition control circuit of a kind of aircraft according to claim 3, it is characterized in that: igniting electric control circuit B comprises the 3rd relay, fire signal control circuit controls the coil motion of the 3rd relay, 3rd relay contact on one side connects igniting power-supplying circuit A, and the contact of the 3rd relay another side connects power supply and ground connection respectively.
5. the booster rocket ignition control circuit of a kind of aircraft according to claim 4, it is characterized in that: igniting electric control circuit B also comprises the second relay, the coil of the second relay accepts the SC sigmal control that igniting signal control circuit sends, second relay contact is on one side connected with fire signal control circuit, and the contact of the second relay another side is connected with power supply.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410674896.1A CN104454240B (en) | 2014-11-24 | 2014-11-24 | A kind of booster rocket ignition control circuit of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410674896.1A CN104454240B (en) | 2014-11-24 | 2014-11-24 | A kind of booster rocket ignition control circuit of aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104454240A true CN104454240A (en) | 2015-03-25 |
| CN104454240B CN104454240B (en) | 2016-04-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410674896.1A Active CN104454240B (en) | 2014-11-24 | 2014-11-24 | A kind of booster rocket ignition control circuit of aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN104454240B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104895700A (en) * | 2015-04-15 | 2015-09-09 | 北京航天自动控制研究所 | Low delay ignition confirmation system and confirmation method applied to rocket ground information fusion |
| CN108678874A (en) * | 2018-04-04 | 2018-10-19 | 湖北三江航天红峰控制有限公司 | A kind of priming system 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 |
| CN111023897A (en) * | 2019-12-30 | 2020-04-17 | 北京旋极信息技术股份有限公司 | Ignition device and fire control system |
| CN111911318A (en) * | 2020-06-28 | 2020-11-10 | 南京云睿航天科技有限公司 | Solid engine ignition circuit with feedback |
| CN111946491A (en) * | 2020-07-14 | 2020-11-17 | 上海机电工程研究所 | Wireless induction type ignition and speed measuring device between aircraft cabins |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS58158355A (en) * | 1982-03-16 | 1983-09-20 | Matsushita Electric Ind Co Ltd | Controller for ignition of rocket |
| US5742609A (en) * | 1993-06-29 | 1998-04-21 | Kondrak; Mark R. | Smart canister systems |
| CN102767446A (en) * | 2012-06-05 | 2012-11-07 | 北京航空航天大学 | Rocket-mounted control circuit for solid/liquid power sounding rocket |
| CN204253212U (en) * | 2014-11-24 | 2015-04-08 | 江西洪都航空工业集团有限责任公司 | A kind of booster rocket ignition control circuit of aircraft |
-
2014
- 2014-11-24 CN CN201410674896.1A patent/CN104454240B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS58158355A (en) * | 1982-03-16 | 1983-09-20 | Matsushita Electric Ind Co Ltd | Controller for ignition of rocket |
| US5742609A (en) * | 1993-06-29 | 1998-04-21 | Kondrak; Mark R. | Smart canister systems |
| CN102767446A (en) * | 2012-06-05 | 2012-11-07 | 北京航空航天大学 | Rocket-mounted control circuit for solid/liquid power sounding rocket |
| CN204253212U (en) * | 2014-11-24 | 2015-04-08 | 江西洪都航空工业集团有限责任公司 | A kind of booster rocket ignition control circuit of aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 黄少波等: "空空导弹发动机点火系统安全性设计", 《航空兵器》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104895700A (en) * | 2015-04-15 | 2015-09-09 | 北京航天自动控制研究所 | Low delay ignition confirmation system and confirmation method applied to rocket ground information fusion |
| CN108678874A (en) * | 2018-04-04 | 2018-10-19 | 湖北三江航天红峰控制有限公司 | A kind of priming system 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 |
| CN111023897A (en) * | 2019-12-30 | 2020-04-17 | 北京旋极信息技术股份有限公司 | Ignition device and fire control system |
| CN111023897B (en) * | 2019-12-30 | 2022-04-08 | 北京旋极信息技术股份有限公司 | Ignition device and fire control system |
| CN111911318A (en) * | 2020-06-28 | 2020-11-10 | 南京云睿航天科技有限公司 | Solid engine ignition circuit with feedback |
| CN111946491A (en) * | 2020-07-14 | 2020-11-17 | 上海机电工程研究所 | Wireless induction type ignition and speed measuring device between aircraft cabins |
| CN111946491B (en) * | 2020-07-14 | 2023-02-28 | 上海机电工程研究所 | Wireless induction type ignition and speed measuring device between aircraft cabins |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104454240B (en) | 2016-04-20 |
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