CN201781320U - Power distribution control circuit - Google Patents
Power distribution control circuit Download PDFInfo
- Publication number
- CN201781320U CN201781320U CN2010201903972U CN201020190397U CN201781320U CN 201781320 U CN201781320 U CN 201781320U CN 2010201903972 U CN2010201903972 U CN 2010201903972U CN 201020190397 U CN201020190397 U CN 201020190397U CN 201781320 U CN201781320 U CN 201781320U
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- kzd1
- line bag
- normal open
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Abstract
The utility model relates to a power distribution control circuit, which comprises relays KB, Kmf1, Kmf2, Kzd1, Kzd2, Kdd1 and Kdd2, resistors and diodes, and is used for shunting, time-sharing power supply and unified power transferring and power-off for a control system and other equipment on an aerocraft. In circuit design, the logical combination of the relays is adopted to realize different functions, and the scheme is simple, so that the work of a power distribution device is very reliable. Compared with the power distribution method of the aerocraft, the utility model can realize the power supply of corresponding parts on the aerocraft, greatly increases the flexibility and safety of testing, reduces loss of components in devices on the aerocraft, solves the problems that the reliability of the whole aerocraft is reduced by additional losses brought by long-time electrifying work of the components because all the components are electrified in ground test, and simultaneously solves the problems that the troubleshooting is dangerous and inconvenient because failure equipment and normal equipment are electrified when the devices on certain aerocrafts break down.
Description
Technical field
The utility model relates to a kind of distribution control circuit, when distribution control when being mainly used in ground test and aircraft flight the distribution of each device of control system and priming system is controlled.
Background technology
Distribution system is an important component part for aircraft, and the reliability fail safe of its circuit design directly influences the success or failure of aircraft.Different loads is arranged in the aerocraft system, and as various instruments, actuator, priming system etc., when aircraft was carried out ground test, what at present the power supply of aircraft is adopted was that ground power supply is connected on the aircraft of back the i.e. whole mode of energized simultaneously of instrument.Because test event is numerous, numerous items only need be connected on the small part aircraft power supply and make that partial devices is charged can finish this project testing, all charged when being not easy to test operation and fix a breakdown, be unfavorable for the safety Design of system.
The utility model content
Technology of the present utility model is dealt with problems and is: overcome the deficiencies in the prior art, a kind of distribution control circuit is provided, by using shunt, the time sharing power supply of a large amount of electromagnetic relays realizations to various systems on the aircraft, unified commentaries on classics electricity and outage, this circuit arrangement is simple, flexible, safety, the reliability height.
Technical solution of the present utility model is: a kind of distribution control circuit comprises relay K B, Kmf1, Kmf2, Kzd1, Kzd2, Kdd1, Kdd2; One group of normal open switch of Kzd1 is with after one group of normal open switch of Kzd2 is in parallel, one end is connected to the powered battery positive bus-bar, the other end outputs to the power supply of installing on the aircraft, and is connected in series to surface power supply positive bus-bar or ground priming system positive bus-bar with one group of normal open switch of KB; It is in parallel that another of another group normal open switch and the Kzd2 of Kzd1 organized normal open switch, one group of normally closed switch of Kdd1 and one group of normally closed switch parallel connection of Kdd2, and two groups of parallel circuitss are connected between the line bag positive pole of powered battery positive bus-bar and Kzd1 and Kzd2 again; Kzd1 is in parallel with the line bag of Kzd2, and anodal the connection changeed the signal of telecommunication, and negative pole is connected to negative busbar; The positive pole of KB line bag is connected to bus control signal or priming system bus control signal, and negative pole is connected to negative busbar; Kdd1 is in parallel with the line bag of Kdd2, and negative pole is connected to negative busbar, and positive pole is connected to power-off signal, and is connected in series to the powered battery positive bus-bar with one group of normal open switch of Kdd1; Kmf1 is in parallel with the line bag of Kmf2, and negative pole is connected to negative busbar, and positive pole is connected to mould and flies signal; One group of normal open switch of Kmf1 is in parallel with one group of normal open switch of Kmf2, and another group normal open switch is also in parallel, and two parts circuit after the parallel connection is connected between powered battery positive bus-bar and surface power supply positive bus-bar or the ground priming system positive bus-bar.
Also comprise resistance and diode; The line bag of the line bag of Kzd1, the line bag of Kdd1, KB, the line bag of Kmf1 are in parallel with diode with the resistance after one group is connected respectively, and resistance is connected with diode cathode, and diode cathode is connected with the line bag is anodal.
The utility model beneficial effect compared with prior art is:
(1) the utility model adopts the electromagnetic relay design, shunt in the time of realizing the aircraft ground test to various systems on the aircraft, time sharing power supply, reduced the loss of components and parts in the device on the aircraft, when having solved because of ground test all energising cause the components and parts excess loss brought of the work of switching on for a long time, the problem that causes the reduction of aircraft whole aircraft reliability, when having solved some device simultaneously and having broken down, faulty equipment and normal device all power up the problem that causes troubleshooting dangerous and inconvenient, simultaneously, owing to adopt the electromagnetic relay design, cost is lower and antijamming capability is strong, circuit is simple and reliable, highly versatile, all can use for distribution during for distribution and practical flight during ground test, simultaneously, the control mode of power supply and outage has as required increased the flexibility and the fail safe of test as required.
(2) since each relay all in parallel resistance and diode, play the negative peak effect that disappears, protected relay.
Description of drawings
Fig. 1 is relay tip figure of the present utility model;
Fig. 2 is a circuit theory schematic diagram of the present utility model;
Fig. 3 for the utility model to the priming system schematic diagram of powering;
Fig. 4 is the utility model priming system bus control signal schematic diagram.
Embodiment
Relay contact mask method disunity on the market, number of contacts also has multiple, but working method is identical with principle.Quantity and mask method with Fig. 1 repeat circuit contact is that example provides embodiment of the present utility model below.
As shown in Figure 1,6 contact relay contacts are divided into two groups.1,2,3 is one group, and wherein 1,2 is normally opened contact, and 2,3 is normally-closed contact; 4,5,6 is one group, and wherein 4,5 is normally opened contact, and 5,6 is normally-closed contact.
The concrete course of work of the present utility model is:
As shown in Figure 2, when usual ground experiment, to simulation power supply on the aircraft, the powered battery bus represents with+B with power distribution cabinet, and the surface power supply of power distribution cabinet is represented with+BB.
During ground simulated flight test, because there is not battery on the aircraft, thus among Fig. 2+the B bus is not charged, and the power supply that install on the aircraft this moment is realized by the KB relay.KB relay normally open contact one termination+BB bus is installed on the outside aircraft of another termination, and when the ground test macro sends the bus control signal, relay K B starts, KB normally opened contact closure, and+BB promptly begins to power to device on the aircraft.In like manner, to the power distribution circuit of priming system power supply, be about to as shown in Figure 3 and Figure 4 ,+the BB bus changes into+the DD bus, other circuit structures are all identical with relay, in order to distinguish expression, in the priming system power distribution circuit, the KB relay is represented with KD, promptly when the ground test macro sends priming system bus control signal, relay K D starts, KD normally opened contact closure, and+DD promptly begins power supply to priming system on the aircraft.
At aerocraft real in-flight, battery-powered ,+B bus is charged, during the ground test aircraft flight, needs simulation+B charged.Relay K mf1,2 normally opened contacts, one termination+B, one termination+BB, when at this moment being sent mould and flown signal by ground testing system, relay K mf1,2 starts, Kmf1,2/1,2,4,5 normally opened contact closures ,+BB is powered and guides to+the B bus on, make+the B bus is charged.
Under the charged situation of+B bus, when the ground test macro sends the commentaries on classics signal of telecommunication, relay K zd1,2 start, Kzd1,2/1,2,4,5 is closed simultaneously, (Kzd1,2/1 terminate at+B on, Kzd1,2/2 end and cut-off relay Kdd1,2/2 end is serially connected, cut-off relay Kdd1,2/3 end again with Kzd1,2 line bags "+" end connects, Kzd1,2/4 terminate at+B on, Kzd1, install on the outside aircraft of 2/5 termination), + B promptly begins power supply to device on the aircraft, simultaneously Kzd1,2/1,2 closures make+and B directly sends into relay K zd1,2 line bags "+" ends makes Kzd1 like this, 2 is in running order always, be the self-insurance state, make when aircraft flight the power supply of installing on battery is to aircraft on the aircraft can not interrupt.
When abnormal conditions appear in aircraft flight, need to cut off power supply to installing on the aircraft.At this moment, control system is sent signal to cut-off relay, cut-off relay Kdd1,2 starts, Kdd1,2/2,3 disconnects, Kdd1/4,5 closures, Kdd1/5 terminates at+B on, the Kdd1/4 end is connected with Kdd1,2 line bags "+" end again, Kdd1/4,5 closures make+and B directly sends into relay K dd1,2 line bags "+" end, makes Kdd1,2 in running order always, i.e. the self-insurance state.Cut-off relay normally-closed contact Kdd1,2/2,3 is serially connected in to be changeed among electrical relay Kzd1,2 the self-keeping circuit; Kdd1,2/2,3 disconnects; cause Kzd1,2 self-keeping circuit to disconnect; Kzd1,2 loses self protective function; Kzd1,2 is not in working order; the Kzd1 of former closure, 2/4,5 disconnects, and+B no longer to device power supply on the aircraft, finish by the outage task.
The unspecified part of the utility model belongs to general knowledge as well known to those skilled in the art.
Claims (2)
1. a distribution control circuit is characterized in that: comprise relay K B, Kmf1, Kmf2, Kzd1, Kzd2, Kdd1, Kdd2; One group of normal open switch of Kzd1 is with after one group of normal open switch of Kzd2 is in parallel, and an end is connected to the powered battery positive bus-bar, and the other end is to device power supply on the aircraft, and is connected in series to surface power supply positive bus-bar or ground priming system positive bus-bar with one group of normal open switch of KB; It is in parallel that another of another group normal open switch and the Kzd2 of Kzd1 organized normal open switch, one group of normally closed switch of Kdd1 and one group of normally closed switch parallel connection of Kdd2, and two groups of parallel circuitss are connected between the line bag positive pole of powered battery positive bus-bar and Kzd1 and Kzd2 again; Kzd1 is in parallel with the line bag of Kzd2, and anodal the connection changeed the signal of telecommunication, and negative pole is connected to negative busbar; The positive pole of KB line bag is connected to bus control signal or priming system bus control signal, and negative pole is connected to negative busbar; Kdd1 is in parallel with the line bag of Kdd2, and negative pole is connected to negative busbar, and positive pole is connected to power-off signal, and is connected in series to the powered battery positive bus-bar with one group of normal open switch of Kdd1; Kmf1 is in parallel with the line bag of Kmf2, and negative pole is connected to negative busbar, and positive pole is connected to mould and flies signal; One group of normal open switch of Kmf1 is in parallel with one group of normal open switch of Kmf2, and another group normal open switch is also in parallel, and two parts circuit after the parallel connection is connected between powered battery positive bus-bar and surface power supply positive bus-bar or the ground priming system positive bus-bar.
2. a kind of distribution control circuit according to claim 1 is characterized in that: also comprise resistance and diode; The line bag of the line bag of Kzd1, the line bag of Kdd1, KB, the line bag of Kmf1 are in parallel with diode with the resistance after one group is connected respectively, and resistance is connected with diode cathode, and diode cathode is connected with the line bag is anodal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201903972U CN201781320U (en) | 2010-05-10 | 2010-05-10 | Power distribution control circuit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201903972U CN201781320U (en) | 2010-05-10 | 2010-05-10 | Power distribution control circuit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201781320U true CN201781320U (en) | 2011-03-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010201903972U Expired - Lifetime CN201781320U (en) | 2010-05-10 | 2010-05-10 | Power distribution control circuit |
Country Status (1)
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| CN (1) | CN201781320U (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102931628A (en) * | 2012-11-14 | 2013-02-13 | 北京电子工程总体研究所 | Protection circuit suitable for initiating explosive device on two-stage ignition bomb |
| CN104583074A (en) * | 2012-06-21 | 2015-04-29 | 萨基姆防务安全公司 | Electric circuit for cutting off an electric power supply having transistors and fuses |
| CN105305595A (en) * | 2015-12-01 | 2016-02-03 | 中国航天科技集团公司第四研究院第四十一研究所 | Power distribution self holding circuit applied to missile-borne equipment |
| CN106549497A (en) * | 2016-11-21 | 2017-03-29 | 北京航天自动控制研究所 | A kind of isolation power-off control circuit suitable for multi-user operation |
| CN106602567A (en) * | 2016-11-21 | 2017-04-26 | 北京航天自动控制研究所 | A reversible power-switching control circuit based on magnetic latching relays |
| CN106646078A (en) * | 2016-11-21 | 2017-05-10 | 北京航天自动控制研究所 | Intelligent detection circuit suitable for redundant magnetic latching supply and distribution lines |
| CN106712273A (en) * | 2016-11-21 | 2017-05-24 | 北京航天自动控制研究所 | Multi-margin redundant control power supply and distribution circuit based on magnetic latching relays |
| CN110034607A (en) * | 2019-04-25 | 2019-07-19 | 北京航天自动控制研究所 | Based on de- survey hair control power-off protection method, system and the storage medium for plugging off and falling |
| CN112786384A (en) * | 2021-02-04 | 2021-05-11 | 湖北三江航天红峰控制有限公司 | Missile-borne switching-off control device based on electromagnetic relay |
-
2010
- 2010-05-10 CN CN2010201903972U patent/CN201781320U/en not_active Expired - Lifetime
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104583074A (en) * | 2012-06-21 | 2015-04-29 | 萨基姆防务安全公司 | Electric circuit for cutting off an electric power supply having transistors and fuses |
| CN102931628A (en) * | 2012-11-14 | 2013-02-13 | 北京电子工程总体研究所 | Protection circuit suitable for initiating explosive device on two-stage ignition bomb |
| CN102931628B (en) * | 2012-11-14 | 2014-11-26 | 北京电子工程总体研究所 | Protection circuit suitable for initiating explosive device on two-stage ignition bomb |
| CN105305595A (en) * | 2015-12-01 | 2016-02-03 | 中国航天科技集团公司第四研究院第四十一研究所 | Power distribution self holding circuit applied to missile-borne equipment |
| CN106646078A (en) * | 2016-11-21 | 2017-05-10 | 北京航天自动控制研究所 | Intelligent detection circuit suitable for redundant magnetic latching supply and distribution lines |
| CN106602567A (en) * | 2016-11-21 | 2017-04-26 | 北京航天自动控制研究所 | A reversible power-switching control circuit based on magnetic latching relays |
| CN106549497A (en) * | 2016-11-21 | 2017-03-29 | 北京航天自动控制研究所 | A kind of isolation power-off control circuit suitable for multi-user operation |
| CN106712273A (en) * | 2016-11-21 | 2017-05-24 | 北京航天自动控制研究所 | Multi-margin redundant control power supply and distribution circuit based on magnetic latching relays |
| CN106549497B (en) * | 2016-11-21 | 2019-02-15 | 北京航天自动控制研究所 | A kind of isolation power-off control circuit suitable for multi-user operation |
| CN106712273B (en) * | 2016-11-21 | 2019-05-24 | 北京航天自动控制研究所 | A kind of more nargin Redundant Control power supply and distribution circuits based on magnetic latching relay |
| CN106646078B (en) * | 2016-11-21 | 2019-07-12 | 北京航天自动控制研究所 | A kind of traversal detection method keeping power and distribution supply cable suitable for redundancy magnetic |
| CN110034607A (en) * | 2019-04-25 | 2019-07-19 | 北京航天自动控制研究所 | Based on de- survey hair control power-off protection method, system and the storage medium for plugging off and falling |
| CN112786384A (en) * | 2021-02-04 | 2021-05-11 | 湖北三江航天红峰控制有限公司 | Missile-borne switching-off control device based on electromagnetic relay |
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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: 20110330 |
|
| CX01 | Expiry of patent term |