CN110160414A - A kind of igniting bussed supply control circuit - Google Patents
A kind of igniting bussed supply control circuit Download PDFInfo
- Publication number
- CN110160414A CN110160414A CN201810945585.2A CN201810945585A CN110160414A CN 110160414 A CN110160414 A CN 110160414A CN 201810945585 A CN201810945585 A CN 201810945585A CN 110160414 A CN110160414 A CN 110160414A
- Authority
- CN
- China
- Prior art keywords
- relay
- contact
- igniting
- control
- bus
- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
Abstract
A kind of igniting bussed supply control circuit, including ignition battery control relay, travel switch and ignition battery.The ignition battery control relay is magnetic latching relay, and two groups of contacts are connected with the igniting positive and negative line of bus respectively, the on-off of control igniting bus and electrical fire battery；The excitation of relay prime is connected with the control signal of ground fire control system, and the excitation of relay rear class is connected with travel switch, and before MISSILE LAUNCHING, the control signal control ignition battery control relay of fire control system disconnects igniting bussed supply route；After MISSILE LAUNCHING, the flight zero signal control ignition battery control relay that travel switch issues connects the power supply line of igniting bus.Circuit structure of the present invention is simple, versatile, can be widely applied in the power supply control of each type of missile igniting bus, realizes that igniting bus is securely and reliably powered, improves the safety and reliability of priming system ignition control route on bullet.
Description
Technical field
The invention patent relates to a kind of control signal circuits, and in particular to a kind of igniting bussed supply control circuit.
Background technique
Priming system igniting is as the key link during Missile Experiment on bullet, and safety and reliability is for flying
The success or failure of row test and the safety of testing crew are most important.The control design case of priming system ignition circuit requires priming system point on bullet
Fire should be controlled by multiple controlling elements, form series control relationship, when only controlling elements reach control condition, priming system point
Ignition circuit ability normal power supply, to guarantee priming system firing circuit safety.Meanwhile ignition circuit power supply peace is being improved as far as possible
While full property, the balance between safety and reliability need to be grasped, controlling elements are rationally set, reaches reliability and safety
Between balance.Direct sources of the igniting bus as priming system priming supply, the safety and reliability for bussed supply of lighting a fire
It is most important.Therefore, it is necessary to which designing control circuit ensures that igniting bus is securely and reliably powered.
At present in current version, igniting bussed supply does not use control circuit mostly, and MISSILE LAUNCHING stage ignition battery swashs
Bus of lighting a fire after work charges, and there are some potential safety problemss.In addition, being mostly using control circuit in igniting bussed supply
Using single control signal control electromagnetic relay by the way of realize, during missile flight control signal lines be surprisingly shorted or
It is interfered, is easy to cause bussed supply abnormal, the reliability of bussed supply is not high.
Summary of the invention
The present invention need to solve technical problem and be to provide a kind of safe and reliable igniting bussed supply control circuit.
In order to solve the above technical problems, taking technical solution the present invention provides a kind of igniting bussed supply control circuit
It is as follows:
A kind of igniting bussed supply control circuit, including ignition battery control relay, travel switch and ignition battery, institute
Stating ignition battery control relay is magnetic latching relay, and two groups of contacts are connected with the igniting positive and negative line of bus respectively, control point
The on-off of fiery bus and electrical fire battery；The excitation of relay prime is connected with the control signal of ground fire control system, relay rear class
Excitation is connected with travel switch, and before MISSILE LAUNCHING, the control signal control ignition battery of fire control system controls relay cut-off point
Fiery bussed supply route；After MISSILE LAUNCHING, the flight zero signal control ignition battery control relay that travel switch issues is connect
The power supply line of logical igniting bus.
Further, the first contact of the relay of the ignition battery control relay is connected with the anode of ignition battery, after
The 4th contact of electric appliance is connected with the cathode of ignition battery, and relay third contact is just being connected with igniting bus, and relay the 6th touches
Point connects with igniting bus negative, and relay prime excitation anode is connected with the control signal of fire control system, the excitation of relay prime
Negative terminal is connected with flight zero point earth signal, and relay rear class excitation anode is connected with travel switch, and relay rear class motivates negative terminal
With bus it is connected.
Emit the preparation stage, fire control system is sent with disconnecting Onboard battery power supply instruction and the corresponding flight zero point of the instruction
Signal, ignition battery controls the first contact of the relay of relay, the second contact of relay is connected, the first contact of the relay, after
Electric appliance third contact disconnects, and the 4th contact of relay, the 5th contact of relay are connected, the 4th contact of relay, relay the 6th
Contact disconnects；MISSILE LAUNCHING stage, ignition battery activation light a fire be in off state between bus and ignition battery at this time；It leads
After bullet transmitting, travel switch issues flight zero signal, and ignition battery control relay rear class excitation positive and negative terminal is effectively connected, point
Thermoelectricity pond controls the actuating of relay, and the first contact of the relay, relay third are connected, the 4th contact of relay, relay the 6th
Contact is connected.
Further, travel switch third contact is connected with relay rear class excitation anode, the second contact of travel switch
Connect bus, after MISSILE LAUNCHING, the travel switch combination button pop-up, travel switch third contact and the second contact of travel switch
It connects and issues flight zero signal.
The control signal of magnetic latching relay prime excitation of the present invention is issued by fire control system, controls the contact shape of relay
State, so that igniting bussed supply route is in off state.Rear class excitation is controlled by travel switch, and after missile takeoff, stroke is opened
It closes and issues flight zero signal, relay contact acts, and igniting two buss lines are in the conductive state.Meanwhile prime excitation control
The positive and negative end of signal separates with separation connector and is in vacant state, is surprisingly done even if controlling signal in flight course
It disturbs and is also possible to prevent relay misoperation work, effectively improve the reliability of igniting bussed supply.The circuit by magnetic keep after
The on-off of the contacts status control igniting bussed supply route of electric appliance, the control signal of relay is respectively by fire control system and stroke
Switch provides, and effectively improves the safety and reliability of bussed supply, securely and reliably lights a fire and provide for priming system on bullet
Powerful guarantee.
Figure of description
Fig. 1 is the electrical block diagram of the invention patent.
Specific embodiment
The present invention includes ignition battery control relay 14, travel switch 15 and ignition battery 16, the ignition battery control
Relay 14 processed is magnetic latching relay, and two groups of contacts are connected with the igniting positive and negative line of bus respectively, control igniting bus and electricity
The on-off in thermoelectricity pond；The excitation of relay prime is connected with the control signal of ground fire control system, the excitation of relay rear class and stroke
Switch 15 is connected, and before MISSILE LAUNCHING, the control signal control ignition battery control relay 14 of fire control system disconnects igniting bus
Power supply line；After MISSILE LAUNCHING, the flight zero signal control ignition battery control relay 14 that travel switch 15 issues is connected
The power supply line of igniting bus.
Carry out the present invention will be described in detail patent below by way of a most preferred embodiment.
As shown in Figure 1, the igniting bussed supply control circuit of the invention patent include JMX-3125 ignition battery control after
Electric appliance 14,3KX5-2 travel switch 15 and ignition battery 16 etc..The ignition battery control relay 14 is magnetic latching relay,
The first contact of the relay 1 is connected with the anode of ignition battery 16；The 4th contact 4 of relay is connected with the cathode of ignition battery 16；
Relay third contact 3 is just being connected with igniting bus；The 6th contact 6 of relay connects with igniting bus negative；Relay prime swashs
It encourages anode 7 to be connected with the control signal of fire control system, receives and disconnect Onboard battery instruction；Before flight zero point earth signal and relay
Grade excitation negative terminal 8 is connected；Relay rear class excitation anode 9 is connected with travel switch contact 3；Relay rear class motivate negative terminal 10 with
Bus it is connected；The second contact of travel switch 12 meets bus+28.5V.
Emit the preparation stage, disconnection Onboard battery power supply instruction is sent on bullet by separation connector for fire control system and this refers to
Corresponding flight zero point earth signal is enabled, ignition battery controls the first contact of the relay 1 of relay 14, the second contact of relay 2
It connects, the first contact of the relay 1, relay third contact 3 disconnect, and the 4th contact 4 of relay, the 5th contact 5 of relay are connected,
The 4th contact 4 of relay, the 6th contact 6 of relay disconnect, and the connection lighted a fire between bus and ignition battery 16 is in breaking shape
State.MISSILE LAUNCHING stage, ignition battery 16 activate, and light a fire be still in off state between bus and ignition battery 16 at this time,
Bus of lighting a fire is not charged, it is ensured that the priming system on bullet without work is without priming supply at this stage.After MISSILE LAUNCHING, stroke is opened
The pop-up of 15 combination buttons is closed, travel switch third contact 13 and the second contact of travel switch 12, which are connected, issues flight zero point 28.5V
Signal.Ignition battery control 14 rear class of relay excitation positive and negative terminal is effectively connected, and ignition battery controls relay 14 and acts, relay
The first contact of device 1, relay the 3rd 3 are connected, and the 4th contact 4 of relay, the 6th contact 6 of relay are connected, and igniting bus is positive and negative
Line is connected with 16 positive and negative electrode of ignition battery respectively, bus normal power supply of lighting a fire.At the same time, umbilical connector after MISSILE LAUNCHING
It disconnecting, the ignition battery connected by umbilical connector controls 14 prime of relay and the control signal of positive and negative terminal is motivated to disconnect,
It can effectively avoid during missile flight relay caused by the factors such as route accidental short circuit and line-hit at umbilical connector
Device malfunction, improves the reliability of igniting bussed supply.
Claims (3)
1. a kind of igniting bussed supply control circuit, which is characterized in that control relay (14), travel switch including ignition battery
(15) and ignition battery (16), ignition battery control relay (14) is magnetic latching relay, two groups of contacts respectively with
The positive and negative line of bus of lighting a fire is connected, the on-off of control igniting bus and electrical fire battery；The excitation of relay prime and ground fire control system
Control signal be connected, relay rear class excitation is connected with travel switch (15), before MISSILE LAUNCHING, the control signal of fire control system
It controls ignition battery control relay (14) and disconnects igniting bussed supply route；After MISSILE LAUNCHING, what travel switch (15) issued
Flight zero signal controls the power supply line that igniting bus is connected in ignition battery control relay (14).
2. a kind of igniting bussed supply control circuit according to claim 1, which is characterized in that the ignition battery control
The first contact of the relay (1) of relay (14) is connected with the anode of ignition battery (16), the 4th contact (4) of relay and igniting
The cathode of battery (16) is connected, and relay third contact (3) is just being connected with igniting bus, the 6th contact (6) of relay and igniting
Bus negative connects, and relay prime excitation anode (7) is connected with the control signal of fire control system, and relay prime motivates negative terminal
(8) it is connected with flight zero point earth signal, relay rear class excitation anode (9) is connected with travel switch (15), and relay rear class swashs
Negative terminal (10) is encouraged with bus to be connected；
Emit the preparation stage, fire control system is sent to be believed with disconnecting Onboard battery power supply instruction and the corresponding flight zero point of the instruction
Number, ignition battery controls the first contact of the relay (1) of relay (14), the second contact of relay (2) is connected, relay first
Contact (1), relay third contact (3) disconnect, and the 4th contact (4) of relay, the 5th contact (5) of relay are connected, relay
4th contact (4), the 6th contact (6) of relay disconnect；MISSILE LAUNCHING stage, ignition battery (16) activation, bus of lighting a fire at this time
Off state is between ignition battery (16)；After MISSILE LAUNCHING, travel switch (15) issues flight zero signal, ignition power
Pond controls relay (14) rear class excitation positive and negative terminal and connects, and ignition battery controls relay (14) movement, the first contact of the relay
(1), relay third (3) is connected, and the 4th contact (4) of relay, the 6th contact (6) of relay are connected.
3. a kind of igniting bussed supply control circuit according to claim 2, which is characterized in that the travel switch third
Contact (13) and relay rear class excitation anode (7) are connected, and the second contact of travel switch (12) connects bus, after MISSILE LAUNCHING, institute
The pop-up of travel switch (15) combination button is stated, travel switch third contact (13) and the second contact of travel switch (12), which are connected, to be issued
Flight zero signal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810945585.2A CN110160414A (en) | 2018-08-20 | 2018-08-20 | A kind of igniting bussed supply control circuit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810945585.2A CN110160414A (en) | 2018-08-20 | 2018-08-20 | A kind of igniting bussed supply control circuit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110160414A true CN110160414A (en) | 2019-08-23 |
Family
ID=67645133
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810945585.2A Pending CN110160414A (en) | 2018-08-20 | 2018-08-20 | A kind of igniting bussed supply control circuit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110160414A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110855126A (en) * | 2019-11-20 | 2020-02-28 | 天津津航计算技术研究所 | Take self preservation function's isolation power supply output 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 |
Citations (5)
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|---|---|---|---|---|
| FR2801263A1 (en) * | 1999-11-19 | 2001-05-25 | Siemens Automotive Sa | Fail-safe shaft lock, for vehicle steering column or gearbox shaft, has lock motor circuits isolated except when vehicle is being entered or left |
| CN202304642U (en) * | 2011-10-24 | 2012-07-04 | 北京航天长征飞行器研究所 | Ignition circuit with interlocking input and output |
| CN203011249U (en) * | 2012-09-28 | 2013-06-19 | 北京机电工程研究所 | Security insurance circuit for missile booster ignition |
| CN203225576U (en) * | 2013-03-05 | 2013-10-02 | 北京机电工程研究所 | Double-channel initiating explosive device igniting circuit |
| CN206321146U (en) * | 2016-12-23 | 2017-07-11 | 湖北三江航天红峰控制有限公司 | A kind of priming system firing circuit |
-
2018
- 2018-08-20 CN CN201810945585.2A patent/CN110160414A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2801263A1 (en) * | 1999-11-19 | 2001-05-25 | Siemens Automotive Sa | Fail-safe shaft lock, for vehicle steering column or gearbox shaft, has lock motor circuits isolated except when vehicle is being entered or left |
| CN202304642U (en) * | 2011-10-24 | 2012-07-04 | 北京航天长征飞行器研究所 | Ignition circuit with interlocking input and output |
| CN203011249U (en) * | 2012-09-28 | 2013-06-19 | 北京机电工程研究所 | Security insurance circuit for missile booster ignition |
| CN203225576U (en) * | 2013-03-05 | 2013-10-02 | 北京机电工程研究所 | Double-channel initiating explosive device igniting circuit |
| CN206321146U (en) * | 2016-12-23 | 2017-07-11 | 湖北三江航天红峰控制有限公司 | A kind of priming system firing circuit |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110855126A (en) * | 2019-11-20 | 2020-02-28 | 天津津航计算技术研究所 | Take self preservation function's isolation power supply output circuit |
| CN110855126B (en) * | 2019-11-20 | 2021-12-31 | 天津津航计算技术研究所 | Take self preservation function's isolation power supply output 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 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190823 |
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| WD01 | Invention patent application deemed withdrawn after publication |