CN203951254U - One comes off to power and disconnects control circuit - Google Patents
One comes off to power and disconnects control circuit Download PDFInfo
- Publication number
- CN203951254U CN203951254U CN201420129385.7U CN201420129385U CN203951254U CN 203951254 U CN203951254 U CN 203951254U CN 201420129385 U CN201420129385 U CN 201420129385U CN 203951254 U CN203951254 U CN 203951254U
- Authority
- CN
- China
- Prior art keywords
- connector
- power supply
- control relay
- control
- separation
- 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
- 238000000926 separation method Methods 0.000 claims abstract description 35
- 238000006243 chemical reaction Methods 0.000 abstract description 5
- 238000000034 method Methods 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000007613 environmental effect Effects 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000009993 protective function Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
Abstract
The utility model proposes one come off power supply disconnect control circuit, comprise control relay, separation connector and umbilical connector, the coil anode of control relay is connected with surface power supply power positive end with umbilical connector by separation connector, contact and a control anode of control relay also connects, the output contact of control relay is connected with the positive busbar of bus, the coil negative terminal of control relay is connected with bus negative rail by separation connector jumper, bus negative rail is connected with surface power supply power supply negative terminal with umbilical connector by separation connector.The utility model is by a relay and separation connector wiring design, can realize reliable power supply, the mode simultaneously separating by electric connector machinery is carried out conversion and control, and the physics of having realized circuit disconnects, avoid short trouble hidden danger, reduced flight risk.
Description
Technical field
The utility model relate to one come off power supply disconnect control circuit, belong to electronic technology field.
Background technology
Continental rise, carrier-borne aircraft, be generally designed with one-level boost motor and second-class cabin body more, and one-level boost motor separates with second-class cabin body completing after boost phase flight, and second-class cabin body completes follow-up flight.At one-level boost motor afterbody, umbilical connector is set, completes electric, interconnection of signals between aircraft and firing box, when vehicle launch with firing box on umbilical connector separate along cabin body axial direction.Between the body of I and II cabin, separation connector is set, completes the transmission of Power supply, separation connector signal, boost motor signal and connection.After the body axial separation of Ti Yan cabin, I and II cabin, separation connector is retained on second-class cabin body, and separation connector is opened with one-level Booster separation.Because supply line in separation connector is connected with aircraft bus, once the fault of being short-circuited may cause whole aircraft abnormal electrical power supply, cause the aircraft cannot normal flight.
The supply line that comes off using at present takes the method for cable protective to protect more, and the physics of not realizing circuit disconnects, and gives aircraft flight with hidden danger.Another kind of common method is series diode on the line, and the method can ensure the safety of signal, but is applicable to little electric current supply line more.Because this method for designing is comparatively harsh to diode index request, requiring that large, the resistance to environmental index of volume as most in utilizing high power diode is low and environmental resistance, volume modern supersonic aircraft are little, lightweight, highly reliable is incompatible.
Utility model content
The purpose of this utility model is to overcome prior art deficiency, provides a kind of physics that can realize circuit to disconnect, avoid the power supply that comes off of short trouble hidden danger, reduction flight risk to disconnect control circuit.
Technical solution of the present utility model: one comes off to power and disconnects control circuit, comprise control relay, separation connector and umbilical connector, the coil anode of control relay is connected with surface power supply power positive end with umbilical connector by separation connector, the contact of control relay and control anode also connect, the output contact of control relay is connected with the positive busbar of bus, the coil negative terminal of control relay is connected with bus negative rail by separation connector jumper, bus negative rail is connected with surface power supply power supply negative terminal with umbilical connector by separation connector.
The utility model beneficial effect compared with prior art:
(1) the utility model is by a relay and separation connector wiring design, can realize reliable power supply, the mode simultaneously separating by electric connector machinery is carried out conversion and control, and the physics of having realized circuit disconnects, avoid short trouble hidden danger, reduced flight risk;
(2) the utility model highly versatile, can be widely used in various aircraft and come off in electric power system.
Brief description of the drawings
Fig. 1 is the utility model electrical block diagram.
Embodiment
Below in conjunction with accompanying drawing and instantiation, the utility model is elaborated.
The utility model as shown in Figure 1, comprises control relay K1, separation connector X2, umbilical connector X1 and wiring.6 wiring of control relay K1 coil anode are connected with surface power supply power positive end by separation connector X2, umbilical connector X1.A contact 5 of control relay K1 and control relay K1 coil anode 6 also connect, and output contact 1,4 connects the positive busbar of bus.The coil negative terminal 7 of control relay K1 is connected with bus negative rail by separation connector X2 jumper, and bus negative rail is connected with surface power supply power supply negative terminal with umbilical connector X1 by separation connector X2.
After the circuit design of utilizing the utility model can realize umbilical connector and powers up to bussed supply power supply by the conversion of control relay, the power supply of realizing is to the reliable power supply of bus, carry-on power supply passes through the positive negative rail of bus after bussed supply simultaneously, that contact 5 by control relay K1 and relay K 1 are controlled anode 6 and connect, can realize self protective function.After aircraft one the second-order separation, by the separation of separation connector X2, disconnect relay K 1 and control the wiring of negative terminal 7 and bus negative rail, control relay K1 recovers normally open, and disconnection comes off being connected to bussed supply loop and the positive busbar of bus.The contact 2 of control relay K1 is vacant contact, and the contact 3 of control relay K1 gathers bus voltage signal.
The utility model operation principle:
The transmitting preparatory stage, ground fire control system is powered to aircraft by umbilical connector X1 and separation connector X2, come off and be switched to control anode 6 and the contact 5 of control relay K1 to bussed supply D (+), the control negative terminal 7 that comes off and be connected to bus negative rail to the negative D (-) of bussed supply by umbilical connector X1 and separation connector X2 and be switched to control relay K1 through the wire of separation connector X2 cross-over connection; Now the control positive and negative terminal 6,7 of control relay K1 is effectively connected, and realizes action conversion self-insurance, and the surface power supply power connection that comes off is to bus busbar.
Vehicle launch, carry-on battery activated, battery is to bussed supply, and ground fire control system is cancelled power supply D (+), D (-), and bus is powered separately by carry-on battery, and the contact 4,5 of control relay K1 is connected.Simultaneously bussed supply is also remained on and is come off in the supply line of bus by the contact 5 of the relay K 1 connected.Booster separation after vehicle launch, separation connector X2 separately, control end negative terminal 7 circuits of the control relay K1 connecting by separation connector X2 disconnect, control relay K1 discharges conversion, cut-out comes off to the supply line of bus, avoids long transmission line transmission and separation connector to be in for a long time supply line's short trouble hidden danger of bringing in the exposed and strong vibration environment of high temperature.
The unspecified part of the utility model is known to the skilled person technology.
Claims (1)
1. the power supply that comes off disconnects control circuit, it is characterized in that: comprise control relay (K1), separation connector (X2) and umbilical connector (X1), the coil anode (6) of control relay (K1) is connected with surface power supply power positive end with umbilical connector (X1) by separation connector (X2), the contact (5) of control relay (K1) and control anode (6) also connect, the output contact (1 of control relay (K1), 4) be connected with the positive busbar of bus, the coil negative terminal (7) of control relay (K1) is connected with bus negative rail by separation connector (X2) jumper, bus negative rail is connected with surface power supply power supply negative terminal with umbilical connector (X1) by separation connector (X2).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201420129385.7U CN203951254U (en) | 2014-03-21 | 2014-03-21 | One comes off to power and disconnects control circuit |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201420129385.7U CN203951254U (en) | 2014-03-21 | 2014-03-21 | One comes off to power and disconnects control circuit |
Publications (1)
Publication Number | Publication Date |
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CN203951254U true CN203951254U (en) | 2014-11-19 |
Family
ID=51893271
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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CN201420129385.7U Expired - Lifetime CN203951254U (en) | 2014-03-21 | 2014-03-21 | One comes off to power and disconnects control circuit |
Country Status (1)
Country | Link |
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CN (1) | CN203951254U (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN108945530A (en) * | 2018-06-15 | 2018-12-07 | 上海卫星工程研究所 | A kind of satellite and the rocket separation Design of Signal and its analogy method |
CN111323735A (en) * | 2020-03-03 | 2020-06-23 | 北京中科宇航技术有限公司 | Multi-stage rocket separation electric connector insertion state detection device and rocket thereof |
CN113044229A (en) * | 2021-03-26 | 2021-06-29 | 北京理工大学 | Modular integrated control system on air-drop type aircraft |
-
2014
- 2014-03-21 CN CN201420129385.7U patent/CN203951254U/en not_active Expired - Lifetime
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN108945530A (en) * | 2018-06-15 | 2018-12-07 | 上海卫星工程研究所 | A kind of satellite and the rocket separation Design of Signal and its analogy method |
CN111323735A (en) * | 2020-03-03 | 2020-06-23 | 北京中科宇航技术有限公司 | Multi-stage rocket separation electric connector insertion state detection device and rocket thereof |
CN113044229A (en) * | 2021-03-26 | 2021-06-29 | 北京理工大学 | Modular integrated control system on air-drop type aircraft |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
C14 | Grant of patent or utility model | ||
GR01 | Patent grant |