CN203951254U - One comes off to power and disconnects control circuit - Google Patents

One comes off to power and disconnects control circuit Download PDF

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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
Application number
CN201420129385.7U
Other languages
Chinese (zh)
Inventor
苗露
刘明
雒宝鹏
胡涛
徐峥峣
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Beijing Research Institute of Mechanical and Electrical Technology
Original Assignee
Beijing Research Institute of Mechanical and Electrical Technology
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Beijing Research Institute of Mechanical and Electrical Technology filed Critical Beijing Research Institute of Mechanical and Electrical Technology
Priority to CN201420129385.7U priority Critical patent/CN203951254U/en
Application granted granted Critical
Publication of CN203951254U publication Critical patent/CN203951254U/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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

One comes off to power and disconnects control circuit
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).
CN201420129385.7U 2014-03-21 2014-03-21 One comes off to power and disconnects control circuit Expired - Lifetime CN203951254U (en)

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
CN203951254U true CN203951254U (en) 2014-11-19

Family

ID=51893271

Family Applications (1)

Application Number Title Priority Date Filing Date
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
CN (1) CN203951254U (en)

Cited By (3)

* Cited by examiner, † Cited by third party
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

Cited By (3)

* Cited by examiner, † Cited by third party
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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