CN202836379U - Guided missile separative signal antifault circuit - Google Patents
Guided missile separative signal antifault circuit Download PDFInfo
- Publication number
- CN202836379U CN202836379U CN 201220529468 CN201220529468U CN202836379U CN 202836379 U CN202836379 U CN 202836379U CN 201220529468 CN201220529468 CN 201220529468 CN 201220529468 U CN201220529468 U CN 201220529468U CN 202836379 U CN202836379 U CN 202836379U
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- Prior art keywords
- guided missile
- signal
- separation signal
- circuit
- diode
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- Expired - Lifetime
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Abstract
A guided missile separative signal antifault circuit is characterized by comprising a guided missile fuze supply relay and a diode. The positive end of the diode is connected with guided missile separative signals, and the negative end of the diode is connected with the positive end of a fuze supply relay coil. Two public contacts of the fuze supply relay are both connected with a power supply of a guided missile, wherein one normally open contact of the fuze supply relay is connected with fuze power signals of a guided missile initiating explosive device, and the other normally open contact of the fuze supply relay is connected with the negative end of the diode. The guided missile separative signal antifault circuit is simple in structure, small in size, light in weight, strong in generality and capable of being widely applied to the separative signal antifault design of the guided missiles of various models.
Description
Technical field
The utility model relates to a kind of control signal circuit, especially a kind of guided missile separation signal fault-proof circuit for guaranteeing guided missile Initiator Safety and flight reliability.
Background technology
Guided missile need to receive the guided missile separation signal from launching carrier before emission, this separation signal is by special-purpose circuit control guided missile priming system ignition circuit power supply.In the prior art, guided missile separation signal and ignition signal generally adopt the state of special-purpose relay circuit control guided missile priming system ignition circuit.If certain relay in the relay circuit breaks down, may cause the separation signal mistake to be sent, cause guided missile safety hidden danger.
The anti-fault of guided missile separation signal has a lot of methods, and usage comparison is to realize by multiple special purpose relay design circuit widely at present.A kind of is to adopt two above Special series relays to control by unlike signal, sends because a relay fault short circuit causes separation signal to be missed preventing, causes guided missile safety hidden danger; Another kind is to adopt more than two special-purpose signal relay in parallel to control by same signal, to prevent causing missile flight reliability hidden danger because a relay fault causes separation signal not sent.
Although anti-separation signal fault adopts the special purpose relay series-parallel connection method can guarantee the safety of guided missile separation signal, used relay is many, and volume weight is large, and reliability is low, with the volume of modern guided missile little, lightweight, highly reliable require incompatible.
The utility model content
The purpose of this utility model is to provide a kind of novel guided missile separation signal fault-proof circuit, in the situation that the false triggering of guided missile separation signal or in the missile flight process control relay fault, still can guarantee the safety of guided missile separation signal control circuit.
For achieving the above object, guided missile separation signal fault-proof circuit of the present utility model comprises guide missile fuze supply relay and a diode; The anode of described diode is connected with the guided missile separation signal, and negative terminal is connected with the anode of described fuse supply relay coil; Two common of described fuse supply relay all are connected with the power supply of guided missile, and a normally opened contact of fuse supply relay is connected with the fuse power supply signal of guided missile priming system, and another normally opened contact is connected with the negative terminal of described diode.
The utility model utilizes the fuse supply relay to increase locking circuit to connect, and what can prevent from may occurring after separation signal from sending sends equipment because of separation signal and the separation signal control appliance fault that open failure causes occurs, thereby prevents the missile flight failure.Separation signal is sent equipment to increasing a diode between separation signal control appliance (being the fuse supply relay), realizes that control appliance when the separation signal mistake is sent, can not affect launching carrier and personal safety; After separation signal is sent, can not send the equipment short circuit because of separation signal, make the separation signal control appliance for electrical short, and cause the missile flight failure.When guided missile disengaging launching carrier sends separation signal, prevent that in flight course separation signal from disconnecting and short trouble, when guided missile does not leave launching carrier, can prevent that separation signal mistake from sending fault, and circuit only need increase a diode and several wires, effectively simplify circuit design, reduced the volume weight of equipment, improved reliability.This circuit highly versatile can be widely used in the anti-accident design of separation signal of each type of missile.
Description of drawings
Fig. 1 is electrical block diagram of the present utility model.
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, guided missile separation signal fault-proof circuit of the present utility model comprises fuse supply relay N (hereinafter to be referred as relay N) and the diode M of guided missile.Its repeat circuit N is missile-borne intrinsic equipment, and improvement of the present utility model is to increase diode and some connecting lines, realizes the anti-accident design of separation signal with the simplest mode.Concrete connected mode as shown in Figure 1.The anode of diode M is connected with guided missile separation signal A, and negative terminal is connected with the coil anode B of relay N; Two common 1 of relay N, 4 are connected with the power supply D of guided missile, and the normally opened contact 3 of relay N is connected with the fuse power supply E of guided missile priming system, and another normally opened contact 6 is connected with the negative terminal (or anode of coil N) of diode M.
Operation principle of the present utility model is:
When separation signal is sent equipment output separation signal A, this signal makes the coil anode anode that drives fuse supply relay N by the separation signal B of diode by diode M, the common point 1 of fuse supply relay N was connected with normal battle 3, simultaneously common point 46 is connected with normal the battle, make power supply D and fuse power E with fuse relay N self-insurance be connected separation signal C and be connected output.If after this separation signal control appliance fault has disconnected separation signal, separation signal still can reliably be possessed, and does not affect the separation signal control appliance and normally uses this signal.
When separation signal is sent the short circuit of equipment output separation signal, fuse relay N self-insurance output, separation signal C can't pass through diode M, can prevent from causing the missile flight failure because of the short circuit of separation signal control appliance power supply.
Claims (1)
1. a guided missile separation signal fault-proof circuit is characterized in that, comprises guide missile fuze supply relay and a diode; The anode of described diode is connected with the guided missile separation signal, and negative terminal is connected with the anode of described fuse supply relay coil; Two common of described fuse supply relay all are connected with the power supply of guided missile, and a normally opened contact of fuse supply relay is connected with the fuse power supply signal of guided missile priming system, and another normally opened contact is connected with the negative terminal of described diode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220529468 CN202836379U (en) | 2012-10-17 | 2012-10-17 | Guided missile separative signal antifault circuit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220529468 CN202836379U (en) | 2012-10-17 | 2012-10-17 | Guided missile separative signal antifault circuit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202836379U true CN202836379U (en) | 2013-03-27 |
Family
ID=47948066
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220529468 Expired - Lifetime CN202836379U (en) | 2012-10-17 | 2012-10-17 | Guided missile separative signal antifault circuit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202836379U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110865317A (en) * | 2019-11-08 | 2020-03-06 | 上海航天设备制造总厂有限公司 | Rocket connector drop signal feedback sensor |
-
2012
- 2012-10-17 CN CN 201220529468 patent/CN202836379U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110865317A (en) * | 2019-11-08 | 2020-03-06 | 上海航天设备制造总厂有限公司 | Rocket connector drop signal feedback sensor |
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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 |
Granted publication date: 20130327 |
|
| CX01 | Expiry of patent term |