CN105738657A - Aircraft measurement and control system automatic power supply device - Google Patents
Aircraft measurement and control system automatic power supply device Download PDFInfo
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- CN105738657A CN105738657A CN201610090470.0A CN201610090470A CN105738657A CN 105738657 A CN105738657 A CN 105738657A CN 201610090470 A CN201610090470 A CN 201610090470A CN 105738657 A CN105738657 A CN 105738657A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R1/00—Details of instruments or arrangements of the types included in groups G01R5/00 - G01R13/00 and G01R31/00
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Abstract
An aircraft measurement and control system automatic power supply device is characterized in that the voltage of an aircraft power supply is introduced in a signal conditioning unit as a trigger signal, when an aircraft is electrified, the trigger signal forms a working voltage via the voltage conversion of the signal conditioning unit, and the working voltage activates a control power supply unit to work; a remote measurement battery pack is switched on to start to supply power to a measurement control combination, while a power supply conversion unit converts the power supply of the remote measurement battery pack into a low volt voltage to supply power to a time delay power supply unit; when the aircraft is powered off, the trigger signal is a low voltage signal, forms a starting signal of the time delay power supply unit, starts the unit to output a voltage of a certain value in a time delay manner, and is used as the working voltage of the control power supply unit to activate a control unit to work, and the control power supply unit supplies power to the remote measurement battery pack. According to the working states of the aircraft power supply, the power on-off of an aircraft measurement and control system can be controlled automatically, after being faulted to be powered off, the aircraft power supply still can work continuously, thereby guaranteeing the integrity and reliability of the remote measurement data.
Description
Technical field
The present invention relates to aircraft power supply technique field, particularly relate to a kind of measurement and control system of aircraft automatic power supply device.
Background technology
Measurement and control system of aircraft is used for gathering each system of aircraft and ambient parameter, the real-time or postmortem analysis data for each system of aircraft；If power down fault occurs in aircraft, the data that can measurement and control system of aircraft collect the power down moment are most important.Traditional measurement and control system of aircraft electric power system is made up of remote measurement set of cells and power switch, generally will turn electric switch and be arranged on aircraft casing, turns electric switch access remote measurement by connection battery-powered.But in product actual flying test, carrier aircraft is connected before taking off and is turned electric switch, and battery-powered beginning of remote measurement is powered for measurement and control system of aircraft, and battery capacity surplus is relatively big, and then causes that aircraft volume and weight is relatively big, adds research and development of products cost.Meanwhile, the installation turning electric switch affects the population structure of aircraft, even affects the indicators of overall performance of aircraft, too increases the triviality of measurement and control system of aircraft design to a certain extent and launches operation complexity.
Summary of the invention
Technical problem solved by the invention is in that to provide a kind of measurement and control system of aircraft automatic power supply device, to solve the shortcoming in above-mentioned background technology.
Technical problem solved by the invention realizes by the following technical solutions:
A kind of measurement and control system of aircraft automatic power supply device, including aircraft power, signal condition unit, power conversion unit, control power supply unit, time delay power supply unit and remote measurement set of cells, wherein, aircraft power is connected with signal condition unit, signal condition unit is connected with controlling power supply unit, simultaneously remote measurement set of cells, power conversion unit and time delay power supply unit Access Control power supply unit；Carrying out practically mode is as follows:
Signal condition unit introduces aircraft power voltage as triggering signal, and after aircraft powers on, this triggering signal is changed through signal condition cell voltage, form running voltage, running voltage activates and controls power supply unit work, connects remote measurement set of cells, starts as observing and controlling associating power supply；And remote measurement battery power is converted to low volt voltage by power conversion unit, power for time delay power supply unit, when after aircraft power-off, signal condition unit cannot form running voltage from aircraft power conversion, now, triggering signal is low voltage signal, constitute the enabling signal of time delay power supply unit, start the voltage of this unit time delay output certain value, control unit work is activated as the running voltage controlling power supply unit, after time delay certain time, time delay power supply unit quits work, whole electric supply installation power-off.
In the present invention, signal condition unit introduces aircraft power voltage as triggering signal, and when triggering signal when 18V ~ 36V, observing and controlling combination starts to access aircraft power and powers, when triggering signal≤8V, then continue to access remote measurement by time delay power supply unit battery-powered.
In the present invention, the low volt voltage that remote measurement battery power is changed by power conversion unit is 10.5V.
In the present invention, signal condition unit includes resistance, diode.
In the present invention, control power supply unit is ON-OFF control circuit, is provided with electromagnetic relay in ON-OFF control circuit, and electromagnetic relay input connects remote measurement battery power, and observing and controlling combination connected by electromagnetic relay outfan；Apply driving voltage, armature movement in electromagnetic relay, the input of electric conduction magnetic relay and outfan at electromagnetic relay line bag two ends, for observing and controlling associating power supply simultaneously.
In the present invention, time delay power supply unit includes LM555 intervalometer, resistance and electric capacity, trigger signal after signal condition unit, be incorporated into LM555 intervalometer, utilize the operating characteristic of intervalometer, when triggering signal and being low voltage signal (i.e. aircraft power down), starting LM555 intervalometer timing function to power to realize time delay, timing is realized by the resistance of resistance and electric capacity.
Beneficial effect: cancel in the present invention and traditional turn electric switch, to evade the negative effect installing the structure to aircraft and indicators of overall performance turning electric switch；Simultaneously according to the duty of aircraft power, can automatically control the power on/off of measurement and control system of aircraft, it is ensured that after aircraft power fault power down, measurement and control system of aircraft still continuous firing at least 2min, ensure that the integrity of telemetry and reliability, meanwhile, reduce the manual operation in vehicle launch, optimize system design, and reduce the design capacity of remote measurement set of cells, reduce volume, alleviate remote measurement battery weight, reduce R&D costs.
Accompanying drawing explanation
Fig. 1 is the flow chart of presently preferred embodiments of the present invention.
Detailed description of the invention
For the technological means making the present invention realize, creation characteristic, reach purpose and effect and be easy to understand, below in conjunction with being specifically illustrating, the present invention is expanded on further.
A kind of measurement and control system of aircraft automatic power supply device referring to Fig. 1, including aircraft power, signal condition unit, power conversion unit, control power supply unit, time delay power supply unit and remote measurement set of cells, wherein, signal condition unit introduces aircraft power voltage as triggering signal, if this triggering signal is when 18V ~ 36V, observing and controlling combination starts to access aircraft power and powers, if during this triggering signal≤8V, then continues to access the battery-powered at least 2min of remote measurement by time delay power supply unit；Carrying out practically mode is as follows:
Signal condition unit introduces aircraft power supply voltage, as triggering signal, to nurse one's health triggering signal, converts the running voltage controlling power supply unit to；After control power supply unit receives running voltage, access remote measurement set of cells, battery-powered for remote measurement；And remote measurement battery power is converted to 10.5V by power conversion unit, power for time delay power supply unit, time delay power supply unit receives a startup voltage≤8V(and triggers signal when being low level) after, start-up study function of supplying power, giving to control power supply unit and provide running voltage, controlling power supply unit is the battery-powered at least 2min of remote measurement.
In the present embodiment, signal condition unit includes resistance, diode.
In the present embodiment, control power supply unit is ON-OFF control circuit, is provided with electromagnetic relay in ON-OFF control circuit, and electromagnetic relay input connects remote measurement battery power, and observing and controlling combination connected by electromagnetic relay outfan；Apply driving voltage, armature movement in electromagnetic relay, the input of electric conduction magnetic relay and outfan at electromagnetic relay line bag two ends, for observing and controlling associating power supply simultaneously.
In the present embodiment, time delay power supply unit includes LM555 intervalometer, resistance and electric capacity, trigger signal after signal condition unit, be incorporated into LM555 intervalometer, utilize the operating characteristic of intervalometer, when triggering signal and being low voltage signal (i.e. aircraft power down), starting LM555 intervalometer timing function to power to realize time delay, timing is realized by the resistance of appropriate design resistance and electric capacity.
The ultimate principle of the present invention and principal character and advantages of the present invention have more than been shown and described.Skilled person will appreciate that of the industry; the present invention is not restricted to the described embodiments; described in above-described embodiment and description is that principles of the invention is described; without departing from the spirit and scope of the present invention; the present invention also has various changes and modifications, and these changes and improvements both fall within the claimed scope of the invention.Claimed scope is defined by appending claims and equivalent thereof.
Claims (6)
1. a measurement and control system of aircraft automatic power supply device, including aircraft power, signal condition unit, power conversion unit, control power supply unit, time delay power supply unit and remote measurement set of cells, it is characterized in that, aircraft power is connected with signal condition unit, signal condition unit is connected with controlling power supply unit, simultaneously remote measurement set of cells, power conversion unit and time delay power supply unit Access Control power supply unit；Carrying out practically mode is as follows:
Signal condition unit introduces aircraft power voltage as triggering signal, and after aircraft powers on, this triggering signal is changed through signal condition cell voltage, form running voltage, running voltage activates and controls power supply unit work, connects remote measurement set of cells, starts as observing and controlling associating power supply；And remote measurement battery power is converted to low volt voltage by power conversion unit, power for time delay power supply unit, when after aircraft power-off, signal condition unit cannot form running voltage from aircraft power conversion, now, triggering signal is low voltage signal, constitute the enabling signal of time delay power supply unit, start the voltage of this unit time delay output certain value, control unit work is activated as the running voltage controlling power supply unit, after time delay certain time, time delay power supply unit quits work, whole electric supply installation power-off.
2. a kind of measurement and control system of aircraft automatic power supply device according to claim 1, it is characterized in that, signal condition unit introduces aircraft power voltage as triggering signal, when triggering signal when 18V ~ 36V, observing and controlling combination starts to access aircraft power and powers, when triggering signal≤8V, then continue to access remote measurement by time delay power supply unit battery-powered.
3. a kind of measurement and control system of aircraft automatic power supply device according to claim 1, it is characterised in that the low volt voltage that remote measurement battery power is changed by power conversion unit is 10.5V.
4. a kind of measurement and control system of aircraft automatic power supply device according to claim 1, it is characterised in that signal condition unit includes resistance, diode.
5. a kind of measurement and control system of aircraft automatic power supply device according to claim 1, it is characterized in that, control power supply unit is ON-OFF control circuit, electromagnetic relay it is provided with in ON-OFF control circuit, electromagnetic relay input connects remote measurement battery power, and observing and controlling combination connected by electromagnetic relay outfan；Apply driving voltage, armature movement in electromagnetic relay, the input of electric conduction magnetic relay and outfan at electromagnetic relay line bag two ends, for observing and controlling associating power supply simultaneously.
6. a kind of measurement and control system of aircraft automatic power supply device according to claim 1, it is characterized in that, time delay power supply unit includes LM555 intervalometer, resistance and electric capacity, trigger signal to introduce after signal condition unit to LM555 intervalometer, when triggering signal and being low voltage signal, start LM555 intervalometer timing function and power to realize time delay.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610090470.0A CN105738657A (en) | 2016-02-18 | 2016-02-18 | Aircraft measurement and control system automatic power supply device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610090470.0A CN105738657A (en) | 2016-02-18 | 2016-02-18 | Aircraft measurement and control system automatic power supply device |
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| CN105738657A true CN105738657A (en) | 2016-07-06 |
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| CN201610090470.0A Pending CN105738657A (en) | 2016-02-18 | 2016-02-18 | Aircraft measurement and control system automatic power supply device |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107799838A (en) * | 2017-09-15 | 2018-03-13 | 江西洪都航空工业集团有限责任公司 | A kind of lithium-ion electric pool manager |
| CN114167835A (en) * | 2021-11-19 | 2022-03-11 | 湖北航天技术研究院总体设计所 | Automatic measurement, launch and control device and system of aircraft |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201374586Y (en) * | 2009-02-24 | 2009-12-30 | 北京国电智深控制技术有限公司 | Dual power supply switcher |
| CN201378751Y (en) * | 2009-03-20 | 2010-01-06 | 上海宝钢设备检修有限公司 | Backup power supply of crane data acquisition recording device |
| CN201789331U (en) * | 2010-08-06 | 2011-04-06 | 四川长虹电器股份有限公司 | Aircraft engine power system |
| CN102447302A (en) * | 2010-09-30 | 2012-05-09 | 苏州捷泰科信息技术有限公司 | Main-standby power supply switching control method and device |
| CN102868212A (en) * | 2011-07-05 | 2013-01-09 | 罗斯蒙特航天公司 | Power supply system for an electronic flight bag |
| CN103036303A (en) * | 2012-12-10 | 2013-04-10 | 江西洪都航空工业集团有限责任公司 | Power supply switching circuit of test equipment |
| CN204089325U (en) * | 2014-08-18 | 2015-01-07 | 江西洪都航空工业集团有限责任公司 | The novel power supply circuits of a kind of flight control system |
| CN204231006U (en) * | 2014-06-26 | 2015-03-25 | 航科院（北京）科技发展有限公司 | For the outage detection protection system of aircraft data recording equipment |
-
2016
- 2016-02-18 CN CN201610090470.0A patent/CN105738657A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201374586Y (en) * | 2009-02-24 | 2009-12-30 | 北京国电智深控制技术有限公司 | Dual power supply switcher |
| CN201378751Y (en) * | 2009-03-20 | 2010-01-06 | 上海宝钢设备检修有限公司 | Backup power supply of crane data acquisition recording device |
| CN201789331U (en) * | 2010-08-06 | 2011-04-06 | 四川长虹电器股份有限公司 | Aircraft engine power system |
| CN102447302A (en) * | 2010-09-30 | 2012-05-09 | 苏州捷泰科信息技术有限公司 | Main-standby power supply switching control method and device |
| CN102868212A (en) * | 2011-07-05 | 2013-01-09 | 罗斯蒙特航天公司 | Power supply system for an electronic flight bag |
| CN103036303A (en) * | 2012-12-10 | 2013-04-10 | 江西洪都航空工业集团有限责任公司 | Power supply switching circuit of test equipment |
| CN204231006U (en) * | 2014-06-26 | 2015-03-25 | 航科院（北京）科技发展有限公司 | For the outage detection protection system of aircraft data recording equipment |
| CN204089325U (en) * | 2014-08-18 | 2015-01-07 | 江西洪都航空工业集团有限责任公司 | The novel power supply circuits of a kind of flight control system |
Non-Patent Citations (1)
| Title |
|---|
| 张文锦: "测控***的掉电保护设计", 《测控技术与设备》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107799838A (en) * | 2017-09-15 | 2018-03-13 | 江西洪都航空工业集团有限责任公司 | A kind of lithium-ion electric pool manager |
| CN114167835A (en) * | 2021-11-19 | 2022-03-11 | 湖北航天技术研究院总体设计所 | Automatic measurement, launch and control device and system of aircraft |
| CN114167835B (en) * | 2021-11-19 | 2023-08-18 | 湖北航天技术研究院总体设计所 | Automatic test, launch and control device and system for aircraft |
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Application publication date: 20160706 |
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