CN103308818B - Testing and verifying circuit of plugging state of flying plug of initiating explosive device on satellite - Google Patents
Testing and verifying circuit of plugging state of flying plug of initiating explosive device on satellite Download PDFInfo
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- CN103308818B CN103308818B CN201310134085.8A CN201310134085A CN103308818B CN 103308818 B CN103308818 B CN 103308818B CN 201310134085 A CN201310134085 A CN 201310134085A CN 103308818 B CN103308818 B CN 103308818B
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Abstract
The invention discloses a testing and verifying circuit of the plugging state of a flying plug of an initiating explosive device on a satellite, comprising a power distributor, a satellite-task information processing unit, a satellite-ground communication unit, a satellite meter socket of the initiating explosive device, the flying plug of the initiating explosive device and a power supply cable of the initiating explosive device, wherein the power distributor also comprises modules such as a voltage acquisition circuit, an analog-digital converter, a microprocessor, a communication module and a power supply socket of the initiating explosive device and the like. The voltage acquisition circuit acquires voltage variation before and after the flying plug of the initiating explosive device is plugged; the analog-digital converter converts the voltage quantity into digital quantity; the microprocessor converts the digital quantity into state-quantity source codes, and sends the state-quantity source codes to the satellite-task information processing unit by the communication module; the satellite-task information processing unit sends the source codes to ground testing equipment by the satellite-ground communication unit; and the ground testing equipment processes the source codes to obtain remote measurement of the plugging state of the flying plug of the initiating explosive device. The testing and verifying circuit disclosed by the invention has the advantages that the control circuit structure is simple, and the plugging state of the flying plug of the initiating explosive device can be reflected only by adding one voltage acquisition circuit and several wires and utilizing existing on-satellite equipment.
Description
Technical field
The present invention relates to a kind of satellite priming system flight plug inserting state testing authentication circuit.
Background technology
In order to the safety in satellite assembly, test, transport and storage process, the connection of priming system feed circuit must be cut off physically, therefore priming system flight plug is set.Fig. 1 is the schematic diagram of existing satellite priming system feed circuit, the positive/negative line of priming system power supply buses is all input to distributor, distributor inside arranges the break-make that ON-OFF control circuit controls priming system bus main track, priming system power supply buses main track is connected with priming system star catalogue socket input point by priming system power supply base, priming system service cable after ON-OFF control circuit, priming system star catalogue socket output point is connected with priming system anode, and priming system power supply buses negative wire is connected with priming system negative terminal by priming system power supply base, priming system service cable.Unless before the test carrying out priming system feed circuit or satellite launch, priming system flight plug is not all inserted, and by physical isolation between priming system bussed supply anode and priming system anode, prevents the possibility of by mistake detonating; Before the test carrying out priming system feed circuit or before satellite launch, plug priming system flight plug, priming system bussed supply anode and priming system anode are linked together, constitute current supply circuit, after the switch of ON-OFF control circuit is all closed, priming system detonates.
In this control circuit, priming system flight plug cannot verify its inserting state after plugging, if the grafting of priming system flight plug is bad, so priming system feed circuit can not form loop, and priming system cannot detonate, and satellite cannot work.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, propose a kind of satellite priming system flight plug inserting state testing authentication circuit, eliminate the problem that priming system flight plug inserting state cannot be tested, ensure the good connection of priming system feed circuit, for correctly detonating of priming system after satellite launch provides basis.
Technical solution of the present invention is:
A kind of satellite priming system flight plug inserting state testing authentication circuit, comprise distributor, Star Service information process unit, star ground communication unit, priming system star catalogue socket, priming system flight plug and priming system service cable, distributor comprises again voltage collection circuit, analog to digital converter, microprocessor, communication module, ON-OFF control circuit and priming system power supply base.
Voltage collection circuit gathers voltage variety before and after the grafting of priming system flight plug, described voltage variety is converted to digital quantity by analog to digital converter, described digital quantity is converted to quantity of state true form by microprocessor, and by described quantity of state true form packing, by communication module, remote measurement bag is sent to Star Service information process unit afterwards, the remote measurement bag containing priming system flight plug inserting state true form that distributor sends by Star Service information process unit packages after process, send to star ground communication unit, the remote measurement bag that Star Service information process unit exports is sent to ground checkout equipment by star ground communication unit, the power supply that priming system power supply buses main track is connected to priming system power supply base by ON-OFF control circuit is gone up on schedule, priming system power supply buses negative wire is directly connected on the negative point of power supply of priming system power supply base, the first contact of priming system power supply base is connected to by priming system service cable on the first contact of priming system star catalogue socket, the tail contact of priming system power supply base is connected to by priming system service cable on the tail contact of priming system star catalogue socket, the power supply of priming system power supply base is connected to by priming system service cable in the power supply input point of priming system star catalogue socket on schedule, the power supply of priming system power supply base is born a little and be connected with priming system between the power supply output point of priming system star catalogue socket, the first contact of priming system flight plug is communicated with tail contact, power supply input point is communicated with power supply output point.
Described voltage collection circuit comprises reference voltage V cc, resistance R1, input end I1 and I2, output end vo; Reference voltage adopts the positive 5V voltage of distributor inside; Resistance R1 is that 10k Ω resistance one end is connected with Vcc, and the resistance R1 other end is connected with output end vo with input end I1 respectively; Input end I1 is connected with the first contact of priming system power supply base; Output end vo is connected with analog to digital converter; Input end I2 is connected with the tail contact of priming system power supply base and ground connection.
Described satellite priming system flight plug inserting state testing authentication circuit at least comprises a set of plugs and sockets, can also comprise and overlap plugs and sockets more, wherein, a set of plugs and sockets includes a priming system power supply base, a priming system star catalogue socket and a priming system flight plug, when described satellite priming system flight plug inserting state testing authentication circuit comprise be greater than a set of plugs and sockets time, the first contact of the priming system power supply base in first set plugs and sockets is connected with the input end I1 of voltage collection circuit, the first contact that the tail contact and second of the priming system power supply base in first set plugs and sockets overlaps the priming system power supply base in plugs and sockets is connected, the first contact of the priming system power supply base that the tail contact and the 3rd of priming system power supply base in the second cover plugs and sockets overlaps in plugs and sockets is connected, the rest may be inferred, the tail contact of priming system power supply base in last cover plugs and sockets and the input end I2 of voltage collection circuit link together.
Digital quantity D is converted to quantity of state true form Z by microprocessor, if the Vo<0.7V that digital quantity D is corresponding, Z=0, if 0.7V≤Vo<5V, Z=1.
The present invention's advantage is compared with prior art:
(1) the present invention is on the basis of existing satellite priming system feed circuit, adds priming system flight plug inserting state testing authentication function.Be connected wire by increasing a set of voltage collection circuit with several, and utilize existing equipment on star, provide a kind of satellite priming system flight plug inserting state testing authentication method.After priming system flight plug is plugged, priming system flight plug inserting state testing authentication circuit can verify priming system flight plug inserting state, effectively improves the reliability of priming system feed circuit, provides guarantee for priming system correctly detonates.
(2) control circuit principle of the present invention is simple, safe and reliable, with low cost, is not only applicable to the testing authentication of fire satellite fire work product flight plug inserting state, can also be used for other wide field.
Accompanying drawing explanation
Fig. 1 is existing satellite priming system feed circuit;
Fig. 2 is satellite priming system of the present invention flight plug inserting state testing authentication schematic block circuit diagram;
Fig. 3 is voltage collection circuit schematic diagram of the present invention.
Embodiment
As shown in Figure 2, satellite priming system flight plug inserting state testing authentication circuit of the present invention comprises distributor, Star Service information process unit, star ground communication unit, priming system star catalogue socket, priming system flight plug and priming system service cable, and distributor comprises again voltage collection circuit, analog to digital converter, microprocessor, communication module, ON-OFF control circuit and priming system power supply base.Socket in the present invention and plug all refer to the electric connector containing multiple connection contact.
Voltage collection circuit gathers voltage variety before and after the grafting of priming system flight plug, described voltage variety is converted to digital quantity by analog to digital converter, described digital quantity is converted to quantity of state true form by microprocessor, and by described quantity of state true form packing, by communication module, remote measurement bag is sent to Star Service information process unit afterwards, the remote measurement bag containing priming system flight plug inserting state true form that distributor sends by Star Service information process unit packages after process, send to star ground communication unit, the remote measurement bag that Star Service information process unit exports is sent to ground checkout equipment by star ground communication unit, the power supply that priming system power supply buses main track is connected to priming system power supply base by ON-OFF control circuit is gone up on schedule, priming system power supply buses negative wire is directly connected on the negative point of power supply of priming system power supply base, the first contact of priming system power supply base is connected to by priming system service cable on the first contact of priming system star catalogue socket, the tail contact of priming system power supply base is connected to by priming system service cable on the tail contact of priming system star catalogue socket, the power supply of priming system power supply base is connected to by priming system service cable in the power supply input point of priming system star catalogue socket on schedule, the power supply of priming system power supply base is born a little and be connected with priming system between the power supply output point of priming system star catalogue socket, the first contact of priming system flight plug is communicated with tail contact, power supply input point is communicated with power supply output point.
Voltage collection circuit comprises reference voltage V cc, resistance R1, input end I1 and I2, output end vo; Reference voltage adopts the positive 5V voltage of distributor inside; Resistance R1 is that 10k Ω resistance one end is connected with Vcc, and the resistance R1 other end is connected with output end vo with input end I1 respectively; Input end I1 is connected with the first contact of priming system power supply base; Output end vo is connected with analog to digital converter; Input end I2 is connected with the tail contact of priming system power supply base and ground connection.
To comprise the satellite priming system flight plug inserting state testing authentication circuit of two cover plugs and sockets.Wherein, a set of plugs and sockets includes a priming system power supply base, a priming system star catalogue socket and a priming system flight plug; The first contact of the priming system power supply base in first set plugs and sockets is connected with the input end I1 of voltage collection circuit, the first contact that the tail contact and second of the priming system power supply base in first set plugs and sockets overlaps the priming system power supply base in plugs and sockets is connected, and the tail contact of priming system power supply base in the second cover plugs and sockets and the input end I2 of voltage collection circuit link together.
The course of work of circuit of the present invention is: under default conditions, and priming system flight plug is non-inserting state, when before needs test priming system feed circuit or satellite launch, plugs two priming system flight plugs.No matter priming system flight plug whether grafting, after satellite powers up, voltage collection circuit gathers voltage Vo, if priming system flight plug is not inserted or grafting is bad, input end I1 and I2 is state of insulation, and Vo is reference voltage V cc, i.e. 5V; If the grafting of priming system flight plug is intact, input end I1 and I2 is conducting state, and Vo is ground, i.e. 0V.The voltage Vo collected is passed to analog to digital converter by voltage collection circuit; Voltage Vo is converted to digital quantity D by analog to digital converter, then passes to microprocessor; Digital quantity D is converted to quantity of state true form Z by microprocessor, if the Vo<0.7V that digital quantity D is corresponding, Z=0, if 0.7V≤Vo<5V, Z=1, microprocessor forms remote measurement bag together with other remote measurements of true form Z and distributor, then sends to Star Service information process unit by communication module.The identification of Star Service information process unit judges the remote measurement bag of distributor, then ground checkout equipment is sent to by star ground communication unit, after ground checkout equipment receives distributor remote measurement bag, decoding obtains the remote measurement of priming system flight plug inserting state, if Z=0, be decoded as non-grafting, if Z=1 is decoded as grafting.
The content be not described in detail in instructions of the present invention belongs to the known technology of those skilled in the art.
Claims (4)
1. a satellite priming system flight plug inserting state testing authentication circuit, it is characterized in that comprising distributor, Star Service information process unit, star ground communication unit, priming system star catalogue socket, priming system flight plug and priming system service cable, distributor comprises again voltage collection circuit, analog to digital converter, microprocessor, communication module, ON-OFF control circuit and priming system power supply base;
Voltage collection circuit gathers voltage variety before and after the grafting of priming system flight plug, described voltage variety is converted to digital quantity by analog to digital converter, described digital quantity is converted to quantity of state true form by microprocessor, and by described quantity of state true form packing, by communication module, remote measurement bag is sent to Star Service information process unit afterwards, the remote measurement bag containing priming system flight plug inserting state true form that distributor sends by Star Service information process unit packages after process, send to star ground communication unit, the remote measurement bag that Star Service information process unit exports is sent to ground checkout equipment by star ground communication unit, the power supply that priming system power supply buses main track is connected to priming system power supply base by ON-OFF control circuit is gone up on schedule, priming system power supply buses negative wire is directly connected on the negative point of power supply of priming system power supply base, the first contact of priming system power supply base is connected to by priming system service cable on the first contact of priming system star catalogue socket, the tail contact of priming system power supply base is connected to by priming system service cable on the tail contact of priming system star catalogue socket, the power supply of priming system power supply base is connected to by priming system service cable in the power supply input point of priming system star catalogue socket on schedule, the power supply of priming system power supply base is born a little and be connected with priming system between the power supply output point of priming system star catalogue socket, the first contact of priming system flight plug is communicated with tail contact, power supply input point is communicated with power supply output point.
2. a kind of satellite priming system flight plug inserting state testing authentication circuit according to claim 1, is characterized in that: described voltage collection circuit comprises reference voltage V cc, resistance R1, input end I1 and I2, output end vo; Reference voltage adopts the positive 5V voltage of distributor inside; Resistance R1 is 10k Ω resistance, and one end is connected with Vcc, and the resistance R1 other end is connected with output end vo with input end I1 respectively; Input end I1 is connected with the first contact of priming system power supply base; Output end vo is connected with analog to digital converter; Input end I2 is connected with the tail contact of priming system power supply base and ground connection.
3. a kind of satellite priming system flight plug inserting state testing authentication circuit according to claim 2, it is characterized in that: described satellite priming system flight plug inserting state testing authentication circuit at least comprises a set of plugs and sockets, can also comprise and overlap plugs and sockets more, wherein, a set of plugs and sockets includes a priming system power supply base, a priming system star catalogue socket and a priming system flight plug, when described satellite priming system flight plug inserting state testing authentication circuit comprise be greater than a set of plugs and sockets time, the first contact of the priming system power supply base in first set plugs and sockets is connected with the input end I1 of voltage collection circuit, the first contact that the tail contact and second of the priming system power supply base in first set plugs and sockets overlaps the priming system power supply base in plugs and sockets is connected, the first contact of the priming system power supply base that the tail contact and the 3rd of priming system power supply base in the second cover plugs and sockets overlaps in plugs and sockets is connected, the rest may be inferred, the tail contact of priming system power supply base in last cover plugs and sockets and the input end I2 of voltage collection circuit link together.
4. a kind of satellite priming system flight plug inserting state testing authentication circuit according to claim 1, it is characterized in that: digital quantity D is converted to quantity of state true form Z by microprocessor, if the Vo<0.7V that digital quantity D is corresponding, Z=0, if 0.7V≤Vo<5V, Z=1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310134085.8A CN103308818B (en) | 2013-04-17 | 2013-04-17 | Testing and verifying circuit of plugging state of flying plug of initiating explosive device on satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310134085.8A CN103308818B (en) | 2013-04-17 | 2013-04-17 | Testing and verifying circuit of plugging state of flying plug of initiating explosive device on satellite |
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| Publication Number | Publication Date |
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| CN103308818A CN103308818A (en) | 2013-09-18 |
| CN103308818B true CN103308818B (en) | 2015-07-08 |
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| CN201310134085.8A Active CN103308818B (en) | 2013-04-17 | 2013-04-17 | Testing and verifying circuit of plugging state of flying plug of initiating explosive device on satellite |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103595034B (en) * | 2013-10-23 | 2017-01-04 | 航天东方红卫星有限公司 | A kind of closed-loop surge elimination circuit |
| CN106292360B (en) * | 2016-08-12 | 2019-04-09 | 北京航天长征飞行器研究所 | Telemetry system on a kind of aircraft based on number bus |
| CN106873705A (en) * | 2016-12-29 | 2017-06-20 | 北京空间飞行器总体设计部 | A kind of retrievable satellite method of controlling security |
| CN109345534B (en) * | 2018-11-23 | 2022-03-15 | 江西洪都航空工业集团有限责任公司 | Method for jointly analyzing digital quantity state quantity of telemetering data of imaging seeker |
| CN110320437A (en) * | 2019-07-01 | 2019-10-11 | 江西洪都航空工业集团有限责任公司 | A kind of two-way priming system plug connection status recognition methods |
| CN111123166B (en) * | 2019-10-25 | 2023-01-03 | 江西洪都航空工业集团有限责任公司 | Improve initiating explosive device plug connection state automatic identification circuit of test security |
| CN111323735B (en) * | 2020-03-03 | 2022-02-15 | 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 |
| CN115579251B (en) * | 2022-11-24 | 2023-03-10 | 上海航天空间技术有限公司 | Working method of travel switch star catalogue system and satellite testing device |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000280999A (en) * | 1999-03-30 | 2000-10-10 | Nec Eng Ltd | Interface checker |
| JP2001186617A (en) * | 1999-12-27 | 2001-07-06 | Nippon Anzen Hosho Keibi Kk | Monitoring system for transmission line |
| CN101598759A (en) * | 2009-07-23 | 2009-12-09 | 航天东方红卫星有限公司 | A kind of detection method of electric connectors of satellite ground power supply and distribution test equipment |
-
2013
- 2013-04-17 CN CN201310134085.8A patent/CN103308818B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000280999A (en) * | 1999-03-30 | 2000-10-10 | Nec Eng Ltd | Interface checker |
| JP2001186617A (en) * | 1999-12-27 | 2001-07-06 | Nippon Anzen Hosho Keibi Kk | Monitoring system for transmission line |
| CN101598759A (en) * | 2009-07-23 | 2009-12-09 | 航天东方红卫星有限公司 | A kind of detection method of electric connectors of satellite ground power supply and distribution test equipment |
Non-Patent Citations (2)
| Title |
|---|
| 环境减灾-1A、1B卫星供配电测试系统设计;阎梅芝 等;《航天器工程》;20100331;第19卷(第2期);第113-120页 * |
| 箭上火工品自动测试方案及实现方法;刘晓燕 等;《弹箭与制导学报》;20091031;第29卷(第5期);第232-234 * |
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| CN103308818A (en) | 2013-09-18 |
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