CN104333115A - Simulated power transfer control device and power transfer control method realized by adopting same - Google Patents
Simulated power transfer control device and power transfer control method realized by adopting same Download PDFInfo
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- CN104333115A CN104333115A CN201410706622.6A CN201410706622A CN104333115A CN 104333115 A CN104333115 A CN 104333115A CN 201410706622 A CN201410706622 A CN 201410706622A CN 104333115 A CN104333115 A CN 104333115A
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Abstract
The invention discloses a simulated power transfer control device and a power transfer control method realized by adopting the device, relating to the field of power transfer control of aircrafts, and aiming at solving the problems of lack of a power transfer function in existing aircraft launching control systems and incapability of checking power supply access of a battery of an electric system. Airborne equipment disclosed by the invention is mounted on an aircraft; the airborne equipment, a power transfer control combination, a computer and a power supply source are connected with one another by cables; the power transfer control combination comprises a control switch and an indictor light. The power source signal output end of the power supply source is connected with the power source signal input end of the control switch, and the control switch is connected with the display signal input end of the indicator light. A control signal of the control switch is connected with the control signal of the computer, the power source signal output end of the control switch is connected with the power source signal input end of the airborne equipment, the detection signal output end of the airborne equipment is connected with the detection signal input end of the computer, and aircraft superposed power supply and simulated power transfer control are realized through computer control. The device and the method can be used for ground test control of the aircrafts.
Description
Technical field
The present invention relates to the implementation method that a kind of simulation turns controller for electric consumption.Particularly the simulation of a kind of aircraft launching control system to aircraft turns the implementation method of controller for electric consumption.Belong to aircraft and turn electric control field.
Background technology
At present, along with the develop rapidly of weaponry, the Test coverage face of aircraft requires the whole process that can cover aircraft operation work.
Take off at aircraft and plug off backwardness, power supply should transfer powered battery to from surface power supply, cannot authenticate to the powered battery path turning Electricity Functional and electrical system of launching control system in traditional testing process.
Summary of the invention
The present invention is to solve the validation problem lacking in existing aircraft launching control system and turn Electricity Functional and the powered battery path to electrical system.Now provide a kind of simulation to turn controller for electric consumption and adopt this device to realize turn electric control method.
A kind of simulation turns controller for electric consumption, and it comprises aircraft,
It also comprises and turns electric control combination, computer, airborne equipment and power supply,
Described airborne equipment is installed on board the aircraft,
Airborne equipment, turn electric control combination, connected by cable between computer and power supply,
Turn electric control combination and comprise control switch and indicator light,
The power supply signal input of the power supply signal output connection control switch of power supply, control switch connects indicator light display input, the control signal input/output terminal of control switch connects the input/output end of computer control signal, the power supply signal output of control switch connects the power supply signal input of airborne equipment, and the detection signal output of airborne equipment connects the detection signal input of computer.
According to a kind of simulation turn controller for electric consumption realize turn electric control method, it comprises following process:
Connect power supply by computer control control switch, power supply is that control switch is powered, and control switch energising makes indicator light display brightness, and control switch controls carry-on airborne equipment and connects, and meanwhile, computer detects airborne equipment voltage.
Beneficial effect of the present invention is: it is that control switch is powered that the present invention triggers power supply by computer control control switch, now, indicator light shows bright state, control switch carries out coincidence power supply to airborne equipment, and disconnect surface power supply, computer detects airborne equipment voltage, realizes aircraft simulation and turns electric control, and the arrangement achieves the powered battery of launching control system.It can be used in Aerospace Vehicle Shooting Range Test control.
Accompanying drawing explanation
Fig. 1 turns the structural representation of controller for electric consumption for a kind of simulation described in embodiment one.
Embodiment
Embodiment one: illustrate present embodiment with reference to Fig. 1, the one simulation described in present embodiment turns controller for electric consumption, and it also comprises and turns electric control combination 1, computer 2, airborne equipment 3 and power supply 4,
Described airborne equipment 3 is installed on board the aircraft,
Airborne equipment 3, turn electric control combination 1, connected by cable between computer 2 and power supply 4,
Turn electric control combination 1 and comprise control switch and indicator light,
The power supply signal input of the power supply signal output connection control switch of power supply 4, control switch connects indicator light display input, the control signal input/output terminal of control switch connects the input/output end of computer 2 control signal, the power supply signal output of control switch connects the power supply signal input of airborne equipment 3, and the detection signal output of airborne equipment 3 connects computer (the detection signal input of 2.
In present embodiment, turn electric control combination receiving computer control signal, the switching performing aircraft simulation supply access controls, and the form of input and output situation indicator light is shown.
Computer possesses output switch parameter and controls, inputs digital quantity detection, input analog amount ability in sampling, realizes controlling, to the qualitative and quantitative sampling interpretation of airborne equipment simulation supply power voltage power supply simulation supply access break-make.
Computer remote control connects simulation power supply, controls to connect simulation current supply circuit, carries out coincidence power supply, detect supply power voltage, meet airborne equipment electricity consumption requirement airborne equipment.
Embodiment two: a kind of simulation according to embodiment one turn controller for electric consumption realize turn electric control method, in present embodiment, control control switch by computer 2 and connect power supply 4, power supply 4 is powered for control switch, control switch energising makes indicator light display brightness, control switch controls carry-on airborne equipment 3 and connects, and meanwhile, computer 2 pairs of airborne equipment 3 voltages detect.
Claims (2)
1. simulation turns a controller for electric consumption, and it comprises aircraft, it is characterized in that, it also comprises and turns electric control combination (1), computer (2), airborne equipment (3) and power supply (4),
Described airborne equipment (3) is installed on board the aircraft,
Airborne equipment (3), turn electric control combination (1), connected by cable between computer (2) and power supply (4),
Turn electric control combination (1) and comprise control switch and indicator light,
The power supply signal input of the power supply signal output connection control switch of power supply (4), control switch connects indicator light display input, the control signal input/output terminal of control switch connects the input/output end of computer (2) control signal, the power supply signal output of control switch connects the power supply signal input of airborne equipment (3), and the detection signal output of airborne equipment (3) connects the detection signal input of computer (2).
2. a kind of simulation according to claim 1 turn controller for electric consumption realize turn electric control method, it is characterized in that, it comprises following process:
Control control switch by computer (2) and connect power supply (4), power supply (4) is powered for control switch, control switch energising makes indicator light display brightness, control switch controls carry-on airborne equipment (3) and connects, meanwhile, computer (2) detects airborne equipment (3) voltage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410706622.6A CN104333115A (en) | 2014-11-27 | 2014-11-27 | Simulated power transfer control device and power transfer control method realized by adopting same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410706622.6A CN104333115A (en) | 2014-11-27 | 2014-11-27 | Simulated power transfer control device and power transfer control method realized by adopting same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104333115A true CN104333115A (en) | 2015-02-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410706622.6A Pending CN104333115A (en) | 2014-11-27 | 2014-11-27 | Simulated power transfer control device and power transfer control method realized by adopting same |
Country Status (1)
| Country | Link |
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| CN (1) | CN104333115A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106325148A (en) * | 2016-08-09 | 2017-01-11 | 北京精密机电控制设备研究所 | Power conversion separation control and detection circuit for servo system |
| CN112531682A (en) * | 2020-11-18 | 2021-03-19 | 湖北航天技术研究院总体设计所 | Bus power supply circuit and power supply method for aircraft control system |
| 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 |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201100864Y (en) * | 2007-11-30 | 2008-08-13 | 成都建中锂电池有限公司 | Lithium battery activation detection table |
| US20090045292A1 (en) * | 2007-08-16 | 2009-02-19 | Maddali Vijay K | Engine having power bus fault short circuit control with a disconnection switch |
| CN102354773A (en) * | 2011-09-19 | 2012-02-15 | 北京电子工程总体研究所 | Li-SOCl2 battery and power supply control circuit thereof |
| CN103700902A (en) * | 2014-01-14 | 2014-04-02 | 深圳市思达仪表有限公司 | Method and device for judging and activating voltage lag of lithium thionyl chloride battery |
| CN103944250A (en) * | 2014-04-21 | 2014-07-23 | 国家电网公司 | Battery passivation preventing circuit of single-phase intelligent electric energy meter |
-
2014
- 2014-11-27 CN CN201410706622.6A patent/CN104333115A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090045292A1 (en) * | 2007-08-16 | 2009-02-19 | Maddali Vijay K | Engine having power bus fault short circuit control with a disconnection switch |
| CN201100864Y (en) * | 2007-11-30 | 2008-08-13 | 成都建中锂电池有限公司 | Lithium battery activation detection table |
| CN102354773A (en) * | 2011-09-19 | 2012-02-15 | 北京电子工程总体研究所 | Li-SOCl2 battery and power supply control circuit thereof |
| CN103700902A (en) * | 2014-01-14 | 2014-04-02 | 深圳市思达仪表有限公司 | Method and device for judging and activating voltage lag of lithium thionyl chloride battery |
| CN103944250A (en) * | 2014-04-21 | 2014-07-23 | 国家电网公司 | Battery passivation preventing circuit of single-phase intelligent electric energy meter |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106325148A (en) * | 2016-08-09 | 2017-01-11 | 北京精密机电控制设备研究所 | Power conversion separation control and detection circuit for servo system |
| CN106325148B (en) * | 2016-08-09 | 2019-08-09 | 北京精密机电控制设备研究所 | A kind of servo-system turn electrically separated control and a detection circuit |
| CN112531682A (en) * | 2020-11-18 | 2021-03-19 | 湖北航天技术研究院总体设计所 | Bus power supply circuit and power supply method for aircraft control system |
| 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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Application publication date: 20150204 |