CN103838153A - Automatic-synchronization joint-control circuit used for space - Google Patents
Automatic-synchronization joint-control circuit used for space Download PDFInfo
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- CN103838153A CN103838153A CN201210480703.XA CN201210480703A CN103838153A CN 103838153 A CN103838153 A CN 103838153A CN 201210480703 A CN201210480703 A CN 201210480703A CN 103838153 A CN103838153 A CN 103838153A
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Abstract
Disclosed is an automatic-synchronization joint-control circuit used for a space. The circuit is characterized by including a first remote-control instruction driving circuit, a second remote-control instruction driving circuit and a linkage auxiliary-control circuit. A switch of the first remote-control instruction driving circuit is a first magnetic latching relay. The first magnetic latching relay includes at least two deputy synchronous single-pole double-throw contacts. A switch of the second remote-control instruction driving circuit is a second magnetic latching relay. The linkage auxiliary-control circuit includes a forth resistor R4, a fifth resistor R5 and a capacitor C1, which are connected serially between a pole and a throw of a second deputy contact of the first magnetic latching relay. The other throw of the second deputy contact of the first magnetic latching relay is connected with a voltage-stabilizing power supply Vc. The automatic-synchronization joint-control circuit used for the space utilizes synchronization characteristics of the magnetic latching relay contacts and charging and discharging characteristics of the capacitor and during execution of an instruction, execution of another remote-control instruction is controlled synchronously through charging and discharging of the capacitor and thus objectives of joint control and synchronization are automatically achieved.
Description
Technical field
The present invention relates to the application of electronic component, particularly automatic synchronization joint control circuit for a kind of spacecraft.
Background technology
Spacecraft is in orbit time, needs ground to send out telecommand a series of to it, makes aircraft require to carry out space tasks according to ground.Spacecraft telecommand circuit is generally independently carried out, but time can increase partial function in design according to demand, as the telecommand that is mutually related exists joint control, synchronous require etc., in circuit design, must realize on request.Affected by running environment, spacecraft has specific characteristics in circuit design, need to consider the limiting factors such as reliability, security, Radiation hardness, weight, therefore on the basis of practical function, circuit should be simply, reliability is strong, there is automatic responding ability, components and parts meeting spatial environment used request for utilization.
Spacecraft is based on demand for control in-orbit, there are a large amount of instruction circuits inside, some instruction has the requirement of automatic synchronization joint control outside autonomous execution, but spacecraft is limit by self-operating environment, all has relatively high expectations for circuit weight, components and parts Radiation hardness, reliability etc.Existing space telecommand driving circuit is synchronous, joint control function generally realizes by logic chip, this kind of mode exists circuit design too complicated, components and parts Radiation hardness is poor, the problems such as single-particle inversion easily occurs and cause losing efficacy, and is applied in middle high orbit aircraft the shortcomings such as reliability is poor.
Magnetic latching relay is a kind of new type of relay developing in recent years, have highly sensitive, low in energy consumption, stable and reliable for performance, the features such as output capacity nargin is large, the life-span is long, can bear rugged environment condition, in spacecraft telecommand circuit, magnetic relay is widely applied as command switch.With general electromagnetic relay difference be, normally closed or the normally open of magnetic latching relay is the effect that relies on permanent-magnet steel, magnet steel is introduced to magnetic loop, after relay coil power-off, the state when armature of relay still can remain on coil electricity, have two states, the conversion of its on off state is to trigger and complete by the pulse electrical signal of certain width.In magnetic latching relay is general, have many secondary synchronous single-pole double-throw (SPDT)s contact, switching is respectively by same coil drive.
Summary of the invention
The problem that the present invention solves is to provide a kind of space automatic synchronization joint control circuit, and too complicated to solve existing space automatic synchronization joint control circuit design, components and parts Radiation hardness is poor, and the problems such as single-particle inversion easily occur.
For addressing the above problem, the invention provides a kind of space automatic synchronization joint control circuit, comprising: the first telecommand driving circuit, the second telecommand driving circuit and interlock auxiliary control circuit; The switch of described the first telecommand driving circuit is the first magnetic latching relay, and described the first magnetic latching relay comprises at least two secondary synchronous single-pole double-throw (SPDT) contacts; The switch of described the second telecommand driving circuit is the second magnetic latching relay; Described interlock auxiliary control circuit comprises the 4th resistance R 4, the 5th resistance R 5 and a capacitor C 1 of throwing between cutter that is connected on described first magnetic latching relay the second width contact, and another of described first magnetic latching relay the second width contact thrown and met Vc (stabilized voltage supply).
Further, described the first telecommand driving circuit comprises that the first driving resistance R 1, the second driving resistance R 2, the first magnetic latching relay, the first Anti-surging diode V1, the second Anti-surging diode V2, first drive triode Q1 and the 3rd current-limiting resistance R3; Described first drives resistance R 1 to be connected with the first telecommand input port, and described first drives the other end of resistance R 1 to be connected with the base stage of the second driving resistance R 2, the first driving triode Q1 simultaneously; Described second drives the other end of resistance R 2 to be connected with the emitter of the first driving triode Q1; Described first drives the collector of triode Q1 to be connected with one end of the coil of the first magnetic latching relay, and described end is also connected with the first Anti-surging diode V1 of series connection, the negative pole of the second Anti-surging diode V2; Other one end of the coil of described the first magnetic latching relay is connected with the first Anti-surging diode V1 of the 3rd current-limiting resistance R3 and series connection, the positive pole of the second Anti-surging diode V2 simultaneously.
Further, described the second telecommand driving circuit comprises that the 6th drives resistance R 6, the 7th to drive resistance R 7, the second magnetic latching relay, the 3rd Anti-surging diode V3, the 4th Anti-surging diode V4, second to drive triode Q2 and the 8th current-limiting resistance R8; The described the 6th drives resistance R 6 to be connected with the second telecommand input port, and the described the 6th drives the other end of resistance R 6 to drive the base stage of resistance R 7, the second driving triode Q2 to be connected with the 7th simultaneously; The described the 7th drives the other end of resistance R 7 to be connected with the emitter of the second driving triode Q2; Ground connection after described emitter and first drives triode Q1 to be connected; The described the 6th drives resistance R 6 and the 7th driving resistance R 7 to connect rear in parallel with the 4th resistance R 4; Described second drives the collector of triode Q2 to be connected with one end of the coil of the second magnetic latching relay, and described end is also connected with the 3rd Anti-surging diode V3 of series connection, the negative pole of the 4th Anti-surging diode V4; Other one end of the coil of described the first magnetic latching relay is connected with the first Anti-surging diode V1 of the 8th current-limiting resistance R3 and series connection, the positive pole of the second Anti-surging diode V2 simultaneously.
Further, described the second driving triode Q2, the first driving triode Q3 are NPN type triode.
What further, capacitor C 1 and the 4th resistance R 4, the 5th resistance R 5 were worth chooses and must drive triode Q2 ON time to meet magnetic latching relay action request in telecommand 2 by assurance discharge pulse width.
Interlock auxiliary control circuit provided by the present invention utilizes the charging/discharging function of magnetic latching relay contact synchronizing characteristics and electric capacity to realize automatic synchronization joint control function.In the time that the first telecommand driving circuit instruction is carried out, coil drive command switch (i.e. the first auxiliary contact) disconnects, now, this coil also synchronously drives in the first magnetic latching relay K1 the second auxiliary contact to beat to the 5th resistance R 5 from+Vc, capacitor C 1 has been full of electricity originally under+Vc voltage, in the time that beating to the 5th resistance R 5, switch starts electric discharge, form pulse, can drive the second telecommand driving circuit response, the second telecommand driving circuit and the first telecommand driving circuit automatic synchronization joint control are carried out.
To sum up, advantage of the present invention comprises: space utilizes magnetic latching relay contact synchronizing characteristics and capacitor charge and discharge characteristic with automatic synchronization joint control circuit, in the time that a space telecontrol instruction is carried out, by the execution of another space telecontrol instruction of capacitor charge and discharge synchro control, automatically reach joint control, synchronous object.This circuit is simple in structure under the prerequisite of practical function, and volume is little, and components and parts space environment reliability is strong, and space circuit design is had to very strong specific aim and practicality.
Accompanying drawing explanation
fig. 1 is space provided by the invention automatic synchronization joint control circuit theory diagrams;
Fig. 2 is that space provided by the invention automatic synchronization joint control circuit is carried out oscillogram.
Embodiment
As shown in Figure 1, space provided by the invention is made up of telecommand driving circuit and interlock auxiliary control circuit with automatic synchronization joint control circuit.Telecommand driving circuit is divided into the first telecommand driving circuit and two parts of the second telecommand driving circuit, the first telecommand driving circuit is connected with aircraft telecommand receiving-member with the second telecommand driving circuit input interface, can directly receive surface instruction, the second telecommand driving circuit has from main control function.According to aircraft demand, the second telecommand driving circuit, need to synchronize with the first telecommand driving circuit joint control execution on the basis of main control, for realizing this function, has added interlock auxiliary control circuit on the second telecommand driving circuit driving circuit.
Particularly, automatic synchronization joint control circuit for space provided by the invention, comprising: the first telecommand driving circuit, the second telecommand driving circuit and interlock auxiliary control circuit; The switch of described the first telecommand driving circuit is the first magnetic latching relay, and described the first magnetic latching relay comprises at least two secondary synchronous single-pole double-throw (SPDT) contacts; The switch of described the second telecommand driving circuit is the second magnetic latching relay; Described interlock auxiliary control circuit comprises the 4th resistance R 4, the 5th resistance R 5 and a capacitor C 1 of throwing between cutter that is connected on described first magnetic latching relay the second width contact, and another of described first magnetic latching relay the second width contact thrown and met Vc (stabilized voltage supply).
Wherein, described the first telecommand driving circuit comprises that the first driving resistance R 1, the second driving resistance R 2, the first magnetic latching relay, the first Anti-surging diode V1, the second Anti-surging diode V2, first drive triode Q1 and the 3rd current-limiting resistance R3; Described first drives resistance R 1 to be connected with the first telecommand input port, and described first drives the other end of resistance R 1 to be connected with the base stage of the second driving resistance R 2, the first driving triode Q1 simultaneously; Described second drives the other end of resistance R 2 to be connected with the emitter of the first driving triode Q1; Described first drives the collector of triode Q1 to be connected with one end of the coil of the first magnetic latching relay, and described end is also connected with the first Anti-surging diode V1 of series connection, the negative pole of the second Anti-surging diode V2; Other one end of the coil of described the first magnetic latching relay is connected with the first Anti-surging diode V1 of the 3rd current-limiting resistance R3 and series connection, the positive pole of the second Anti-surging diode V2 simultaneously.
Described the second telecommand driving circuit comprises that the 6th drives resistance R 6, the 7th to drive resistance R 7, the second magnetic latching relay, the 3rd Anti-surging diode V3, the 4th Anti-surging diode V4, second to drive triode Q2 and the 8th current-limiting resistance R8; The described the 6th drives resistance R 6 to be connected with the second telecommand input port, and the described the 6th drives the other end of resistance R 6 to drive the base stage of resistance R 7, the second driving triode Q2 to be connected with the 7th simultaneously; The described the 7th drives the other end of resistance R 7 to be connected with the emitter of the second driving triode Q2; Ground connection after described emitter and first drives triode Q1 to be connected; The described the 6th drives resistance R 6 and the 7th driving resistance R 7 to connect rear in parallel with the 4th resistance R 4; Described second drives the collector of triode Q2 to be connected with one end of the coil of the second magnetic latching relay, and described end is also connected with the 3rd Anti-surging diode V3 of series connection, the negative pole of the 4th Anti-surging diode V4; Other one end of the coil of described the first magnetic latching relay is connected with the first Anti-surging diode V1 of the 8th current-limiting resistance R3 and series connection, the positive pole of the second Anti-surging diode V2 simultaneously.
The first magnetic latching relay K1 has the magnetic latching relay of many auxiliary contacts in being, switching is respectively by same coil drive.Electric capacity capacitor C 1 is nonpolarity high frequency organic media electric capacity, and specific inductive capacity is high, volume is little, broad application temperature range, frequency stability are good, on spacecraft, is widely used.Interlock auxiliary control circuit utilizes the charging/discharging function of magnetic latching relay contact synchronizing characteristics and electric capacity to realize synchronous joint control function, in the time that steering order 1 instruction is carried out, coil drive command switch (i.e. the first auxiliary contact) disconnects, now, this coil also synchronously drives in K1 the second auxiliary contact to beat to resistance R 5 from+Vc, and capacitor C 1 has been full of electricity originally under+Vc voltage, in the time that beating to R5, switch starts electric discharge, form pulse, can drive telecommand 2 Circuit responces, reach automatic synchronization joint control function.
Wherein, the value of capacitor C 1 is relevant actuation time to the response time of driving circuit and magnetic latching relay, and what capacitor C 1 and resistance R 4, resistance R 5 were worth chooses and must drive triode Q2 ON time to meet magnetic latching relay action required pulse width in telecommand 2 by assurance discharge pulse width second.
Fig. 2 is the execution oscillogram of the side circuit built according to circuit theory in Fig. 1, as can be seen from Figure 2, after the telecommand 1 drive waveforms input of the first telecommand driving circuit, the drive waveforms of the synchronous instruction 2 of the second telecommand driving circuit input and instruction 1 is given in capacitor C 1 synchronous discharge, and the synchronous joint control of telecommand 2 circuit and instruction 1 is carried out.
Space is few, lightweight by automatic synchronization joint control circuit elements number of devices, volume is little, automatic fast response time, and components and parts do not use logic chip, only uses the basic devices such as electric capacity, resistance, relay.The anti-radiation property of foundation class components and parts is strong, reliability is high, is widely used in aircraft, has passed through the checking in-orbit of basic, normal, high each orbiter, is specially adapted to the requirement of space environment, in spacecraft circuit design, has wide practical use.
A kind of space of the present invention has been arranged in high orbit satellite model with automatic synchronization joint control circuit, and fly in-orbit 2 years with this satellite, in 2 years, this circuit has been followed ground remote control instruction and has repeatedly been carried out, all carry out normally, can verify practicality and the reliability of this circuit.
Although the present invention with preferred embodiment openly as above; but it is not for limiting the present invention; any those skilled in the art without departing from the spirit and scope of the present invention; can utilize method and the technology contents of above-mentioned announcement to make possible variation and modification to technical solution of the present invention; therefore; every content that does not depart from technical solution of the present invention; any simple modification, equivalent variations and the modification above embodiment done according to technical spirit of the present invention, all belong to the protection domain of technical solution of the present invention.
Claims (5)
1. an automatic synchronization joint control circuit for space, is characterized in that, comprising: the first telecommand driving circuit, the second telecommand driving circuit and interlock auxiliary control circuit; The switch of described the first telecommand driving circuit is the first magnetic latching relay, and described the first magnetic latching relay comprises at least two secondary synchronous single-pole double-throw (SPDT) contacts; The switch of described the second telecommand driving circuit is the second magnetic latching relay; Described interlock auxiliary control circuit comprises the 4th resistance R 4, the 5th resistance R 5 and a capacitor C 1 of throwing between cutter that is connected on described first magnetic latching relay the second width contact, and another of described first magnetic latching relay the second width contact thrown and met stabilized voltage supply Vc.
2. according to automatic synchronization joint control circuit for a kind of space claimed in claim 1, it is characterized in that, described the first telecommand driving circuit comprises that the first driving resistance R 1, the second driving resistance R 2, the first magnetic latching relay, the first Anti-surging diode V1, the second Anti-surging diode V2, first drive triode Q1 and the 3rd current-limiting resistance R3; Described first drives resistance R 1 to be connected with the first telecommand input port, and described first drives the other end of resistance R 1 to be connected with the base stage of the second driving resistance R 2, the first driving triode Q1 simultaneously; Described second drives the other end of resistance R 2 to be connected with the emitter of the first driving triode Q1; Described first drives the collector of triode Q1 to be connected with one end of the coil of the first magnetic latching relay, and described end is also connected with the first Anti-surging diode V1 of series connection, the negative pole of the second Anti-surging diode V2; Other one end of the coil of described the first magnetic latching relay is connected with the first Anti-surging diode V1 of the 3rd current-limiting resistance R3 and series connection, the positive pole of the second Anti-surging diode V2 simultaneously.
3. according to automatic synchronization joint control circuit for a kind of space claimed in claim 2, it is characterized in that, described the second telecommand driving circuit comprises that the 6th drives resistance R 6, the 7th to drive resistance R 7, the second magnetic latching relay, the 3rd Anti-surging diode V3, the 4th Anti-surging diode V4, second to drive triode Q2 and the 8th current-limiting resistance R8; The described the 6th drives resistance R 6 to be connected with the second telecommand input port, and the described the 6th drives the other end of resistance R 6 to drive the base stage of resistance R 7, the second driving triode Q2 to be connected with the 7th simultaneously; The described the 7th drives the other end of resistance R 7 to be connected with the emitter of the second driving triode Q2; Ground connection after described emitter and first drives triode Q1 to be connected; The described the 6th drives resistance R 6 and the 7th driving resistance R 7 to connect rear in parallel with the 4th resistance R 4; Described second drives the collector of triode Q2 to be connected with one end of the coil of the second magnetic latching relay, and described end is also connected with the 3rd Anti-surging diode V3 of series connection, the negative pole of the 4th Anti-surging diode V4; Other one end of the coil of described the first magnetic latching relay is connected with the first Anti-surging diode V1 of the 8th current-limiting resistance R3 and series connection, the positive pole of the second Anti-surging diode V2 simultaneously.
4. according to automatic synchronization joint control circuit for a kind of space claimed in claim 3, it is characterized in that, described second to drive triode Q2, first to drive triode Q3 be NPN type triode, and the model that drives triode Q2, Q3 is chosen according to driving signal voltage and relay coil to move required current value.
5. according to automatic synchronization joint control circuit for a kind of space claimed in claim 3, it is characterized in that, what capacitor C 1 and the 4th resistance R 4, the 5th resistance R 5 were worth chooses and must drive triode Q2 ON time to meet magnetic latching relay action request in telecommand 2 by assurance discharge pulse width.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210480703.XA CN103838153B (en) | 2012-11-23 | 2012-11-23 | Space automatic synchronization joint control circuit |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210480703.XA CN103838153B (en) | 2012-11-23 | 2012-11-23 | Space automatic synchronization joint control circuit |
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| CN103838153A true CN103838153A (en) | 2014-06-04 |
| CN103838153B CN103838153B (en) | 2016-08-24 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112366792A (en) * | 2020-11-25 | 2021-02-12 | 上海空间电源研究所 | Space S4R system charging auxiliary switching circuit and S4R system with same |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004221985A (en) * | 2003-01-15 | 2004-08-05 | Tamagawa Seiki Co Ltd | Relay latching circuit |
| CN101728123A (en) * | 2009-09-29 | 2010-06-09 | 艾默生网络能源有限公司 | Drive circuit of magnetic latching relay |
| WO2011010996A1 (en) * | 2009-07-21 | 2011-01-27 | Hewlett-Packard Development Company, L.P. | Latching relay control circuitry |
| CN201781285U (en) * | 2010-08-13 | 2011-03-30 | 广东三怡电器有限公司 | Permanent magnet vacuum switch type inrush current free low voltage reactive power compensation device |
-
2012
- 2012-11-23 CN CN201210480703.XA patent/CN103838153B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004221985A (en) * | 2003-01-15 | 2004-08-05 | Tamagawa Seiki Co Ltd | Relay latching circuit |
| WO2011010996A1 (en) * | 2009-07-21 | 2011-01-27 | Hewlett-Packard Development Company, L.P. | Latching relay control circuitry |
| CN101728123A (en) * | 2009-09-29 | 2010-06-09 | 艾默生网络能源有限公司 | Drive circuit of magnetic latching relay |
| CN201781285U (en) * | 2010-08-13 | 2011-03-30 | 广东三怡电器有限公司 | Permanent magnet vacuum switch type inrush current free low voltage reactive power compensation device |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112366792A (en) * | 2020-11-25 | 2021-02-12 | 上海空间电源研究所 | Space S4R system charging auxiliary switching circuit and S4R system with same |
| CN112366792B (en) * | 2020-11-25 | 2022-10-21 | 上海空间电源研究所 | Space S4R system charging auxiliary switching circuit and S4R system with same |
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| CN103838153B (en) | 2016-08-24 |
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