CN107797467A - System Zero magnitude control device during a kind of generalization - Google Patents
System Zero magnitude control device during a kind of generalization Download PDFInfo
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- CN107797467A CN107797467A CN201710831656.1A CN201710831656A CN107797467A CN 107797467 A CN107797467 A CN 107797467A CN 201710831656 A CN201710831656 A CN 201710831656A CN 107797467 A CN107797467 A CN 107797467A
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- Prior art keywords
- control circuit
- zero magnitude
- switch
- control
- relay
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
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- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Feedback Control In General (AREA)
Abstract
The invention belongs to ground simulation experimental technique field, and in particular to Zero magnitude control device of being united during aircraft generalization.The device includes first control circuit, second control circuit, the 3rd control circuit, relay module and master switch.Its repeat circuit module includes common switch and two relays arranged side by side.One of relay joins the when system Zero magnitude control module to form first control circuit with shared switch series, another relay joins the when system Zero magnitude control module to form second control circuit with shared switch series, while the when system Zero magnitude control module of the 3rd control circuit is formed with common switch, two controlling switches arranged side by side of the 3rd control circuit and master switch.The present invention change prior art can not compatible different aircraft when unite Zero magnitude control the problem of, avoid design iterations, saved hardware resource, reduce cost, there is larger actual application value.
Description
Technical field
The invention belongs to ground simulation experimental technique, and in particular to Zero magnitude control dress of being united during aircraft generalization
Put.
Background technology
Critical point of the zero point of being united during aircraft for vehicle launch State Transferring, therefore Zero magnitude control of being united during aircraft is winged
The key link of row device ground simulation test, the control instruction send it is whether normal aircraft can be determined whether by launching before
State is smoothly transferred to state after transmitting.System zero signal break-make when conventional test methods are carried out using single large current load switch
Control, Zero magnitude control principle of uniting during due to different aircraft it is different, it is necessary to according to Flight Vehicle Design it is specific when unite zero
Point control device, expends resource and manpower, cost are higher.
The content of the invention
The purpose of the present invention is：Zero magnitude control of being united when providing a kind of high integrated level, the generalization that compatibility is good, cost is low fills
Put.
The technical scheme is that：System Zero magnitude control device during a kind of generalization, it includes first control circuit, second
Control circuit, the 3rd control circuit, relay module and master switch, wherein, relay module includes common switch and two simultaneously
The relay of row, one of relay join the when system Zero magnitude control module to form first control circuit with shared switch series, separately
One relay join with shared switch series to be formed second control circuit when unite Zero magnitude control module, while with common switch, the
Three controlling switches arranged side by side of control circuit two and master switch form the when system Zero magnitude control module of the 3rd control circuit.
3rd control circuit two of which controlling switch arranged side by side is two single-pole single-throw switch (SPST)s.
The common switch for two relay interior lines of control bag simultaneously whether powered double-point double-throw switch.
Three control circuits include corresponding supervisory circuit, and whether system zero point sends during monitoring.
First control circuit also includes the supervisory circuit being connected with relay.
Common switch is connected by connector with PCI midget relays.
The solution have the advantages that：The present invention changes prior art and can not united Zero magnitude control during compatible different aircraft
The problem of, design iterations are avoided, have saved hardware resource；The Automation Design avoids zero point control of being united when caused by control manually
The mistake hair of system；Real-time Monitoring Design provides effective foundation for experiment troubleshooting.In summary, manpower and materials have been saved in the invention,
It ensure that the security reliability and Development Schedule of experiment.
Brief description of the drawings
The circuit theory diagrams of system Zero magnitude control device when Fig. 1 is generalization of the present invention.
Embodiment
The present invention will be further described with reference to the accompanying drawings and examples：
Referring to Fig. 1, it is the circuit theory diagrams of the present invention.Apparatus of the present invention include first control circuit, the second control
Circuit, the 3rd control circuit, PCI midget relays, relay module and master switch.Wherein, relay module includes sharing and opened
Pass and two relays arranged side by side.The common switch for two relay interior lines of control bag simultaneously whether powered DPDT
Switch, and common switch is connected by connector with PCI midget relays, when common switch and relay disconnect, passes through PCI
System zero point Automated condtrol when midget relay can be realized.
A relay in relay module join with shared switch series to be formed first control circuit when unite Zero magnitude control
Module, it combines corresponding supervisory circuit, realize to aircraft when unite Zero magnitude control；Another relay and shared switch series
Connection forms the when system Zero magnitude control module of second control circuit, and second control circuit also includes one and relay and common switch
The supervisory circuit of connection, its combine corresponding supervisory circuit realize to aircraft when unite Zero magnitude control；With second control circuit
The relay of connection forms the 3rd control with common switch, two controlling switches arranged side by side of the 3rd control circuit and master switch simultaneously
The when system Zero magnitude control module of circuit.3rd controlling switch arranged side by side of control circuit two is two single-pole single-throw switch (SPST)s, and point
Supervisory circuit is not connected with it.The when system Zero magnitude control module of 3rd control circuit combines the supervisory circuit and realized to aircraft
When unite Zero magnitude control.
In addition, the respective supervisory circuit of first, second and third control circuit is mutually independent and connection controls what is each connected
Aircraft.
During generalization of the present invention during system Zero magnitude control device real work：
(a) during first control circuit during system Zero magnitude control：
As shown in figure 1, first close master switch S1, be closed again common switch S2, relay line bag 2 is powered, relay 22,
3 contact adhesives, electrically comprehensive control combination busbar 28V is into connector A 1 core, zero point of being united when sending 28V by connector A 4 cores
Control instruction is to aircraft, so as to realize the design requirement of first control circuit；
(b) during second control circuit during system Zero magnitude control：
As shown in figure 1, connector C 5 cores, with being structurally connected, connector C 8 cores combine repeat circuit with electrically comprehensive control
The negative connection of line bag, first close master switch S1, be closed again common switch S2, relay line bag 1 is powered, 6,7 points of disconnections of relay,
So that electric electricity under comprehensive control combination repeat circuit line bag, system Zero magnitude control is instructed to aircraft during so as to send 28V, realizes second
The design requirement of control circuit；
(c) during three control circuits during system Zero magnitude control：
As shown in figure 1, first closing master switch S1, then it is respectively closed common switch S2 and switch S3, switch S4, relay 1
Line band is electric, 2,3 contact adhesives of relay 1, system zero point instruction 1 when 4 points in connector C send multiple aircraft formation, by Fig. 1
System zero point instruction 2, zero point of being united when sending multiple aircraft formation by 4 points of connector E in Fig. 1 when 4 points of connector D send multiple aircraft formation
Instruction 3.Common switch S2 and switch S3, switch S4 are first closed, master switch S1 is closed again and setting for the 3rd control circuit can be achieved
Meter demand.
The present invention adds automatic control function again on the basis of design requirement is met, is needed manually during control manual
Break-make control is carried out to common switch S2, Automated condtrol is only needed the connector B connecting node control devices in Fig. 1, node
The Automated condtrol of system zero point when control device is realized by software control PCI midget relays.
In addition, the connector B in Fig. 1 is connected to node control equipment by the present invention, as priority closure master switch S1, share
When switching S2, relay line bag 1 is powered, and 2,3 electric shock adhesives of relay 1,28V high level is delivered to connector B 7 cores, patched
Part B 9 cores ground connection, node device are acquired by PCI analog acquisition card to the switching value, so as to reach to automation
The real-time monitoring purpose of control.
The setting and output of constant pressure source are completed, puts through different switches, on-off model is measured by universal meter, so as to real
The Autonomous test of the existing present invention.As shown in figure 1, by connector B connecting nodes control device (midget relay containing PCI and PCI moulds
Analog quantity capture card), connector A, C, D, E are connected into different aircraft, corresponding switch is put through according to experiment process and is flown
Unite during device Zero magnitude control, will respectively be switched off after off-test, close constant pressure source.
Claims (5)
1. Zero magnitude control device of being united during a kind of generalization, it is characterised in that including first control circuit, second control circuit, the
Three control circuits, relay module and master switch, wherein, relay module includes common switch and two relays arranged side by side,
One of relay and shared switch series join to be formed first control circuit when unite Zero magnitude control module, another relay with
Common switch connect to be formed second control circuit when unite Zero magnitude control module, while with common switch, the 3rd control circuit two
Individual controlling switch arranged side by side and master switch form the when system Zero magnitude control module of the 3rd control circuit.
2. Zero magnitude control device of being united during generalization according to claim 1, it is characterised in that the 3rd control circuit, wherein
Two-way controlling switch arranged side by side is two single-pole single-throw switch (SPST)s.
3. Zero magnitude control device of being united during generalization according to claim 1, it is characterised in that the common switch is simultaneously
Two relay interior lines of control bag whether powered double-point double-throw switch.
4. Zero magnitude control device of being united during generalization according to claim 1, it is characterised in that three control circuits include
Corresponding supervisory circuit, whether system zero point sends during monitoring.
5. Zero magnitude control device of being united during generalization according to claim 1, it is characterised in that common switch passes through connector
It is connected with PCI midget relays.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710831656.1A CN107797467A (en) | 2017-09-15 | 2017-09-15 | System Zero magnitude control device during a kind of generalization |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710831656.1A CN107797467A (en) | 2017-09-15 | 2017-09-15 | System Zero magnitude control device during a kind of generalization |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107797467A true CN107797467A (en) | 2018-03-13 |
Family
ID=61531840
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710831656.1A Pending CN107797467A (en) | 2017-09-15 | 2017-09-15 | System Zero magnitude control device during a kind of generalization |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107797467A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1596195A (en) * | 1978-04-24 | 1981-08-19 | Fieldtech Ltd | Passenger-address and passenger entertainment system |
| JPH11243353A (en) * | 1998-02-26 | 1999-09-07 | Toshiba Corp | Automatic relay station selecting device |
| CN101848339A (en) * | 2010-05-11 | 2010-09-29 | 航天科工深圳（集团）有限公司 | Aerial photographing control device for unmanned helicopter |
| CN103529780A (en) * | 2013-09-26 | 2014-01-22 | 内蒙航天动力机械测试所 | Multifunctional controller for data acquisition system |
| CN104196635A (en) * | 2014-08-18 | 2014-12-10 | 江西洪都航空工业集团有限责任公司 | Novel roll booster ignition circuit |
| CN104407529A (en) * | 2014-11-27 | 2015-03-11 | 江西洪都航空工业集团有限责任公司 | Method for realizing time system zero-clock |
| CN104895700A (en) * | 2015-04-15 | 2015-09-09 | 北京航天自动控制研究所 | Low delay ignition confirmation system and confirmation method applied to rocket ground information fusion |
| CN204790615U (en) * | 2015-07-15 | 2015-11-18 | 江西洪都航空工业集团有限责任公司 | A composite control ware for aircraft emulation is experimental |
| CN106094564A (en) * | 2016-06-08 | 2016-11-09 | 江西洪都航空工业集团有限责任公司 | A kind of multi-aircraft cooperative combat Simulation Control device |
-
2017
- 2017-09-15 CN CN201710831656.1A patent/CN107797467A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1596195A (en) * | 1978-04-24 | 1981-08-19 | Fieldtech Ltd | Passenger-address and passenger entertainment system |
| JPH11243353A (en) * | 1998-02-26 | 1999-09-07 | Toshiba Corp | Automatic relay station selecting device |
| CN101848339A (en) * | 2010-05-11 | 2010-09-29 | 航天科工深圳（集团）有限公司 | Aerial photographing control device for unmanned helicopter |
| CN103529780A (en) * | 2013-09-26 | 2014-01-22 | 内蒙航天动力机械测试所 | Multifunctional controller for data acquisition system |
| CN104196635A (en) * | 2014-08-18 | 2014-12-10 | 江西洪都航空工业集团有限责任公司 | Novel roll booster ignition circuit |
| CN104407529A (en) * | 2014-11-27 | 2015-03-11 | 江西洪都航空工业集团有限责任公司 | Method for realizing time system zero-clock |
| CN104895700A (en) * | 2015-04-15 | 2015-09-09 | 北京航天自动控制研究所 | Low delay ignition confirmation system and confirmation method applied to rocket ground information fusion |
| CN204790615U (en) * | 2015-07-15 | 2015-11-18 | 江西洪都航空工业集团有限责任公司 | A composite control ware for aircraft emulation is experimental |
| CN106094564A (en) * | 2016-06-08 | 2016-11-09 | 江西洪都航空工业集团有限责任公司 | A kind of multi-aircraft cooperative combat Simulation Control device |
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Application publication date: 20180313 |
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