CN101839938A - Method for testing airplane model lightning current distribution by utilizing thermal infrared imager - Google Patents
Method for testing airplane model lightning current distribution by utilizing thermal infrared imager Download PDFInfo
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- CN101839938A CN101839938A CN201010146979A CN201010146979A CN101839938A CN 101839938 A CN101839938 A CN 101839938A CN 201010146979 A CN201010146979 A CN 201010146979A CN 201010146979 A CN201010146979 A CN 201010146979A CN 101839938 A CN101839938 A CN 101839938A
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Abstract
The invention discloses a method for testing airplane model thunder and lightning current distribution by utilizing a thermal infrared imager, comprising the following steps: utilizing a scaling airplane model to replace an airplane to test; placing the airplane model on an insulation bracket; selecting an connected electrode and a discharge electrode and an earthing position according to a thunder and lightning channel when the airplane suffers from lightning stroke; adjusting the rolling angle and infrared thermal imager position of the airplane model; shooting a test piece infrared thermal image before discharge to be used as a standard image; immediately shooting heated infrared thermal image after discharge; dividing the area in which the airplane is located into 40*40 grids; and calculating the temperature variation value of each point; analyzing the relationship of the temperature rise of a conductor and current to obtain two-dimensional current distribution on the surface of the test piece. The method has the characteristics of less equipment, low testing cost, consistence with actual conditions and higher test accuracy; the two-dimensional grids are used to show test results, and can intuitively reflect the current distribution condition. The method can be widely applied to various airplane models and relatively model tests suffered from lightning stroke.
Description
Technical field
The present invention relates to the test method that lightning current distributes, be specifically related to the test method of utilizing thermal infrared imager that the model aircraft lightning current is distributed.
Background technology
Aircraft is after being struck by lightning, because that the thunder discharge electric current has ascending velocity is fast and amplitude is big, may cause direct effects such as burning, corrode, malformation to the position of transmission lightning current.The thunder and lightning passage when aircraft is struck by lightning, its inlet point and leave a little between the flowing of electric current, and the inductance of aircraft different parts and resistance can cause each influenced making a world of difference in position.By the cranking test of simulation thunder and lightning, investigate the distribution of aircraft surfaces lightning current, reference and foundation can be provided for the lightning Protection Design of aircraft.Prior art is not owing to there is suitable test method, and existence can only distribute to the lightning current of aircraft and carry out the defective of simulation calculation.
Summary of the invention
It is few to the purpose of this invention is to provide a kind of required instrument, test method is easy, cost is low, and testing airplane model lightning current distributes comparatively accurately, and the test method of utilizing thermal infrared imager that the model aircraft lightning current is distributed of reference and foundation is provided for the lightning Protection Design of aircraft.
In order to overcome the defective of prior art, technical scheme of the present invention is to solve like this: a kind of thermal infrared imager that utilizes carries out the test method that lightning current distributes, and is undertaken by following step:
(1), use the aircraft scale model to substitute airplane complete machine as testpieces, scale model is a wooden structures, the surface is coating aluminum evenly, and model aircraft is positioned on the insulating support;
(2), the inlet point of thunder and lightning passage selects to connect the position of sparking electrode when being struck by lightning according to aircraft, again according to the thunder and lightning passage leave the point selection earthing position, the position of above-mentioned sparking electrode generally comprises head, motor head, wing wing tip, vertical fin wing tip; Ground connection correspondence position successively is ventral afterbody, ventral afterbody, opposite side wing wing tip, ventral front end, and for the aircraft of different profiles, its sparking electrode position and earthing position are variant;
(3), sparking electrode and ground wire are fixed in select location with the conductive copper adhesive tape, thermal infrared imager is fixed on the support;
(4), adjustment model roll attitude and thermal infrared imager position so that photographs best embodies the thermal-induced imagery of distribution of current in the horizontal direction,, then must be divided into test of many times and carry out if need take from a plurality of directions, a direction is only taken in each test;
(5), use impulse current generator to the discharge of test test specimen, adjust the amplitude and the duration of discharge, make test specimen that enough temperature variation be arranged but do not cause test specimen to damage, the thermal-induced imagery of taking testpieces before the discharge is taken the thermal-induced imagery after temperature raises immediately as benchmark image after the discharge;
(6), the image before the thermal-induced imagery after will discharging and the discharge is contrasted processing, the model aircraft region is divided into the grid of 40*40, regional area grid density doubles, each grid is handled by a temperature spot, with the intermediate value of each point temperature in the grid scope temperature, calculate the temperature change value that obtains each point as this temperature spot;
(7), according to the temperature rise of conductor and the relationship analysis of electric current, obtain the two-dimensional current distribution on test specimen surface;
(8) adjust sparking electrode and earthing position, the test of all positions is finished in repeating step (3)～(7);
(9) two-dimensional current distribution that finally obtains is as the reference data of aircraft lightning Protection Design and layout.
Described model aircraft is sprayed with the model aircraft of conductive coating for the surface.
The present invention compared with prior art has following characteristics:
A), device therefor is few, experimentation cost is low;
B), considered that the thunder and lightning passage goes into a little and go out multiple combination a little, more consistent with actual conditions;
C), the temperature contrast before the elimination test, the test accuracy is higher;
D), represent test findings, can intuitively embody the distribution of current situation with two-dimensional grid.
Be widely used in the lightning test of various model aircrafts.
Embodiment
Below in conjunction with embodiment summary of the invention is described further:
Embodiment 1
A kind of thermal infrared imager that utilizes carries out the test method that lightning current distributes, and is undertaken by following step:
(1), certain large transport airplane scale model of using 1: 25 substitutes airplane complete machine as testpieces, scale model is a wooden structures, the surface is coating aluminum evenly, and model aircraft is positioned on the insulating support;
The inlet point of thunder and lightning passage selects to connect the position of sparking electrode when (2), being struck by lightning according to aircraft, again according to the thunder and lightning passage leave the point selection earthing position, the position of above-mentioned sparking electrode comprises motor head, wing wing tip, the vertical fin wing tip on head, the wing; Ground connection correspondence position successively mainly comprises ventral afterbody, ventral afterbody, opposite side wing wing tip, ventral front end;
(3), sparking electrode and ground wire are fixed in select location with the conductive copper adhesive tape, thermal infrared imager is fixed on the support;
(4), adjustment model roll attitude, be that wing wing tip, earthing position are example for the opposite side wing tip with the discharge position, needing the roll angle with model aircraft be 90 degree, makes the wing direction of extension vertical with surface level.Thermal infrared imager towards the model back, is adjusted distance and made model aircraft obtain maximum demonstration in thermal-induced imagery, and this layout can obtain the distribution of current at back, if thermal imaging system then can be obtained the distribution of current of belly towards the model belly;
(5), use impulse current generator to the discharge of test test specimen, the initial current amplitude is 100A, duration 1s, discharge back testpieces surface temperature does not have significant change, progressively increases current amplitude and duration, as current amplitude 400A, during duration 5s, the testpieces surface temperature has significant change, and the thermal-induced imagery of taking testpieces before the discharge is taken the thermal-induced imagery after temperature raises immediately as benchmark image after the discharge;
(6), the model aircraft region is divided into the grid of 40*40, regional area grid density doubles, each grid is handled by a temperature spot, and the temperature that the temperature after the discharge deducts before the discharge is temperature change value, calculates the temperature change value that obtains each point;
(7), distributing from the testpieces surface temperature change obtains the two-dimensional current distribution on test specimen surface, can find out intuitively that therefrom the electric current that passes through at which position is bigger, the electric current which position is passed through is less;
(8) adjust sparking electrode and earthing position, the test of all positions is finished in repeating step (3)～(7);
(9) two-dimensional current distribution that finally obtains can be used as the reference data of aircraft lightning Protection Design and layout.
Embodiment 2
A kind of thermal infrared imager that utilizes carries out the test method that lightning current distributes, and is undertaken by following step:
(1), certain type seaplane scale model of using 1: 20 substitutes airplane complete machine as testpieces, scale model is a wooden structures, the surface is coating aluminum evenly, and model aircraft is positioned on the insulating support;
The inlet point of thunder and lightning passage selects to connect the position of sparking electrode when (2), being struck by lightning according to aircraft, again according to the thunder and lightning passage leave the point selection earthing position, the position of above-mentioned sparking electrode mainly comprises motor head, wing wing tip, the vertical fin wing tip of head, fuselage back; Ground connection correspondence position successively mainly comprises ventral afterbody, ventral afterbody, opposite side wing wing tip, ventral front end;
(3), sparking electrode and ground wire are fixed in select location with the conductive copper adhesive tape, thermal infrared imager is fixed on the support;
(4), adjustment model roll attitude, be that head, earthing position are example for the ventral afterbody with the discharge position, needing the roll angle with model aircraft be 90 degree, makes the wing direction of extension vertical with surface level.Thermal infrared imager towards the model back, is adjusted distance and made model aircraft obtain maximum demonstration in thermal-induced imagery, and this layout can obtain the distribution of current at back, if thermal imaging system then can be obtained the distribution of current of belly towards the model belly;
(5), use impulse current generator to the discharge of test test specimen, the initial current amplitude is 100A, duration 1s, discharge back testpieces surface temperature does not have significant change, progressively increases current amplitude and duration, as current amplitude 400A, during duration 3s, the testpieces surface temperature has significant change, and the thermal-induced imagery of taking testpieces before the discharge is taken the thermal-induced imagery after temperature raises immediately as benchmark image after the discharge;
(6), the model aircraft region is divided into the grid of 40*40, regional area grid density doubles, each grid is handled by a temperature spot, and the temperature that the temperature after the discharge deducts before the discharge is temperature change value, calculates the temperature change value that obtains each point;
(7), distributing from the testpieces surface temperature change obtains the two-dimensional current distribution on test specimen surface, can find out intuitively that therefrom the electric current that passes through at which position is bigger, the electric current which position is passed through is less;
(8) adjust sparking electrode and earthing position, the test of all positions is finished in repeating step (3)～(7);
(9) two-dimensional current distribution that finally obtains can be used as the reference data of aircraft lightning Protection Design and layout.
In sum, thermal infrared imager can detect the temperature on model aircraft surface intuitively, the method of existing use thermal infrared imager all is the high-temperature area in the manual observation heat picture, but for model aircraft, under conventional environment, the surface temperature before the discharge is also inhomogeneous, therefore must be by the control treatment of aircraft surfaces temperature before and after the discharge, reject the temperature contrast on the preceding model aircraft surface of discharge, just can obtain the temperature variation that aircraft surfaces produces because of conduction.
Claims (2)
1. one kind is utilized thermal infrared imager to carry out the test method that lightning current distributes, and it is characterized in that being undertaken by following step:
(1), use the aircraft scale model to substitute airplane complete machine as testpieces, scale model is a wooden structures, the surface is coating aluminum evenly, and model aircraft is positioned on the insulating support;
(2), the inlet point of thunder and lightning passage selects to connect the position of sparking electrode when being struck by lightning according to aircraft, again according to the thunder and lightning passage leave the point selection earthing position, the position of above-mentioned sparking electrode generally comprises head, motor head, wing wing tip, vertical fin wing tip; Ground connection correspondence position successively is ventral afterbody, ventral afterbody, opposite side wing wing tip, ventral front end, and for the aircraft of different profiles, its sparking electrode position and earthing position are variant;
(3), sparking electrode and ground wire are fixed in select location with the conductive copper adhesive tape, thermal infrared imager is fixed on the support;
(4), adjustment model roll attitude and thermal infrared imager position so that photographs best embodies the thermal-induced imagery of distribution of current in the horizontal direction,, then must be divided into test of many times and carry out if need take from a plurality of directions, a direction is only taken in each test;
(5), use impulse current generator to the discharge of test test specimen, adjust the amplitude and the duration of discharge, make test specimen that enough temperature variation be arranged but do not cause test specimen to damage, the thermal-induced imagery of taking testpieces before the discharge is taken the thermal-induced imagery after temperature raises immediately as benchmark image after the discharge;
(6), the image before the thermal-induced imagery after will discharging and the discharge is contrasted processing, the model aircraft region is divided into the grid of 40*40, regional area grid density doubles, each grid is handled by a temperature spot, with the intermediate value of each point temperature in the grid scope temperature, calculate the temperature change value that obtains each point as this temperature spot;
(7), according to the temperature rise of conductor and the relationship analysis of electric current, obtain the two-dimensional current distribution on test specimen surface;
(8) adjust sparking electrode and earthing position, the test of all positions is finished in repeating step (3)～(7);
(9) two-dimensional current distribution that finally obtains is as the reference data of aircraft lightning Protection Design and layout.
2. the thermal infrared imager that utilizes according to claim 1 carries out the test method that lightning current distributes, and it is characterized in that described model aircraft is sprayed with the model aircraft of conductive coating for the surface.
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| CN201010146979A CN101839938A (en) | 2010-04-15 | 2010-04-15 | Method for testing airplane model lightning current distribution by utilizing thermal infrared imager |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102087322A (en) * | 2010-11-19 | 2011-06-08 | 北京航空航天大学 | Lightning effect test device for dynamic airplane |
| CN103018645A (en) * | 2013-01-16 | 2013-04-03 | 山东大学 | Device and method for testing artificial lightning injuries of carbon fiber composite material |
| CN103048381A (en) * | 2013-01-16 | 2013-04-17 | 山东大学 | Testing device and testing method for lighting-proof damage property of fiber composite material |
| CN104020322B (en) * | 2014-06-12 | 2017-02-15 | 山东大学 | Manual lightning stroke simulating test fixture made of fiber reinforced composite material, and method |
| CN106771548A (en) * | 2016-11-18 | 2017-05-31 | 清华大学 | The device of piezo-resistance CURRENT DISTRIBUTION is tested based on infrared thermal imaging principle |
| CN106885936A (en) * | 2017-01-22 | 2017-06-23 | 华北电力大学 | The hardened structure discharge current measurement apparatus of rod based on insulation point domain combined method |
| CN107315136A (en) * | 2017-07-06 | 2017-11-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft thunder and lightning transient current is distributed test method |
| CN107807270A (en) * | 2017-11-29 | 2018-03-16 | 曲阜师范大学 | A kind of current sensing means and its detection method based on artificial intelligence |
| CN109387707A (en) * | 2017-08-07 | 2019-02-26 | 波音公司 | Large surface array of magnetic field |
| CN109781777A (en) * | 2018-12-06 | 2019-05-21 | 西安交通大学 | Non-demolition thunder and lightning flow component acts on lower carbon fibre composite temperature characteristic measuring, calibration method and test macro |
| CN112485505A (en) * | 2020-11-10 | 2021-03-12 | 电子科技大学 | High-frequency alternating current amplitude detection method based on infrared thermal imaging |
| CN114162346A (en) * | 2021-12-07 | 2022-03-11 | 上海无线电设备研究所 | Scaling aircraft surface deposition static distribution ground verification method |
| CN114236299A (en) * | 2022-02-24 | 2022-03-25 | 合肥航太电物理技术有限公司 | Infrared temperature measurement high-speed photographic imaging integrated thunder and lightning ignition source simulation device |
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2010
- 2010-04-15 CN CN201010146979A patent/CN101839938A/en not_active Withdrawn
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102087322A (en) * | 2010-11-19 | 2011-06-08 | 北京航空航天大学 | Lightning effect test device for dynamic airplane |
| CN103018645A (en) * | 2013-01-16 | 2013-04-03 | 山东大学 | Device and method for testing artificial lightning injuries of carbon fiber composite material |
| CN103048381A (en) * | 2013-01-16 | 2013-04-17 | 山东大学 | Testing device and testing method for lighting-proof damage property of fiber composite material |
| CN103048381B (en) * | 2013-01-16 | 2015-06-24 | 山东大学 | Testing device and testing method for lighting-proof damage property of fiber composite material |
| CN104020322B (en) * | 2014-06-12 | 2017-02-15 | 山东大学 | Manual lightning stroke simulating test fixture made of fiber reinforced composite material, and method |
| CN106771548A (en) * | 2016-11-18 | 2017-05-31 | 清华大学 | The device of piezo-resistance CURRENT DISTRIBUTION is tested based on infrared thermal imaging principle |
| CN106885936A (en) * | 2017-01-22 | 2017-06-23 | 华北电力大学 | The hardened structure discharge current measurement apparatus of rod based on insulation point domain combined method |
| CN107315136A (en) * | 2017-07-06 | 2017-11-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft thunder and lightning transient current is distributed test method |
| CN109387707A (en) * | 2017-08-07 | 2019-02-26 | 波音公司 | Large surface array of magnetic field |
| CN107807270A (en) * | 2017-11-29 | 2018-03-16 | 曲阜师范大学 | A kind of current sensing means and its detection method based on artificial intelligence |
| CN107807270B (en) * | 2017-11-29 | 2023-06-27 | 曲阜师范大学 | Current detection device and method based on artificial intelligence |
| CN109781777A (en) * | 2018-12-06 | 2019-05-21 | 西安交通大学 | Non-demolition thunder and lightning flow component acts on lower carbon fibre composite temperature characteristic measuring, calibration method and test macro |
| CN109781777B (en) * | 2018-12-06 | 2020-10-27 | 西安交通大学 | Method and system for measuring and calibrating temperature characteristics of carbon fiber composite material under action of nondestructive lightning current component |
| CN112485505A (en) * | 2020-11-10 | 2021-03-12 | 电子科技大学 | High-frequency alternating current amplitude detection method based on infrared thermal imaging |
| CN112485505B (en) * | 2020-11-10 | 2021-10-19 | 电子科技大学 | High-frequency alternating current amplitude detection method based on infrared thermal imaging |
| CN114162346A (en) * | 2021-12-07 | 2022-03-11 | 上海无线电设备研究所 | Scaling aircraft surface deposition static distribution ground verification method |
| CN114162346B (en) * | 2021-12-07 | 2023-11-14 | 上海无线电设备研究所 | Surface deposition static distribution ground verification method for scaled aircraft |
| CN114236299A (en) * | 2022-02-24 | 2022-03-25 | 合肥航太电物理技术有限公司 | Infrared temperature measurement high-speed photographic imaging integrated thunder and lightning ignition source simulation device |
| CN114236299B (en) * | 2022-02-24 | 2022-04-26 | 合肥航太电物理技术有限公司 | Infrared temperature measurement high-speed photographic imaging integrated thunder and lightning ignition source simulation device |
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Open date: 20100922 |