CN102426310A - Novel full aircraft high-strength irradiation test method - Google Patents
Novel full aircraft high-strength irradiation test method Download PDFInfo
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- CN102426310A CN102426310A CN2011103039885A CN201110303988A CN102426310A CN 102426310 A CN102426310 A CN 102426310A CN 2011103039885 A CN2011103039885 A CN 2011103039885A CN 201110303988 A CN201110303988 A CN 201110303988A CN 102426310 A CN102426310 A CN 102426310A
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Abstract
The invention discloses a completely new full aircraft high-strength irradiation test method. Based on an electromagnetic effect produced to an aircraft by an external electromagnetic environment and response of functional performance of the aircraft to electromagnetic stress, the invention provides a method for determining equivalent effect and response produced by the aircraft to different external electromagnetic stresses; a plurality of wires surrounding the surface of the aircraft are used as a sensor to actually measure induction current of the current on the surface of a shell of the aircraft in a loop under a low-level irradiation field; then the induction current corresponding to a high-level irradiation field is extrapolated by using linear relation between high level and low level; an equivalent amount of the induction current obtained by the extrapolation is injected into the loop to produce the same surface induction current distribution as the irradiation field on the aircraft shell; and the aircraft is kept under the equivalent electromagnetic stress to finish high-strength irradiation test. In the method, the field is substituted by a path, and an electromagnetic irradiation coupling mode is substituted by an injection current coupling mode, so that the test efficiency is obviously increased, and the test expense is reduced.
Description
Technical field
The invention belongs to the electromagnetic compatibility test field, relate in particular to the new method of the full machine high intensity radiation test of aircraft, i.e. aircraft surfaces loop wire electric current implantttion technique.
Background technology
The predetermined external electromagnetic environment get off the plane must be entirely normal compatible work of performance.Therefore require in aircraft research and development, type-approval process, to carry out the full machine high-strength magnetic of aircraft irradiation test, to verify its accordance.But present actual conditions are also not have job facilities can completely carry out this type of test.
In the full machine high intensity radiation test of aircraft; The traditional experiment method be the RF energy of the high power amplifier HPA in broadband output through antenna with free space travelling plane wave form; Uniform irradiation is in aircraft, and whether the duty of monitoring aircraft meets the relevant regulations requirement under this electromagnetic stress condition.Its technological essence is that the aircraft housing adds the surface induction electric current that forms under the electromagnetic stress effect outside, and through aircraft door and window, housing bore seam, the transmission of covering number of ways is coupled to interior of aircraft and is formed secondary radiation; System/device in the machine is coupled through the conduction on field-line/field-shell coupling (electric field, magnetic field, far field, near field, induction field), line-line/line-shell/shell-shell coupling (capacitive character, inductive, electrical conductance, common impedance, public vagabond current) and the circuit lead again; Disturb responsive device, finally influence the overall aircraft duty.The energy of antenna emission has only smaller portions to be radiated to receive on the test specimen in the irradiation test, and wherein major part is reflected again, and final effect and the energy that receives sensitive components in the test specimen be a very little part just, so cost effectiveness is extremely low.
In addition, carry out the required site facility of aircraft high intensity radiation test, the superpower amplifier that produces the high-energy electromagnetic field generally needs the input of hundreds of up to ten million Renminbi; High energy electromagnetic radiation is the problem that must pay attention to the threat of the health of testing crew, life and to the pollution of periphery electromagnetic environment; Carry out high intensity radiation test cost also up to tens0000 to millions of.
Present China's national defense mouth EMC test field; Equipment/subsystem level EMC test has been carried out relatively fully; But platform/big system-level EMC test relatively seriously lags behind; Especially high intensity radiation test is because condition restriction almost is blank, all the more influence restricted China's weaponry research and development, equip process.
Therefore need a kind of alternate test, carry out the full machine high intensity radiation test of aircraft.
Summary of the invention
In the full machine high intensity radiation test of existing aircraft; Proof stress produce cost big, receive that the test specimen operation is limited, the problem of repeated relatively poor, the low inferior technology that is difficult to overcome of test cost effectiveness of test findings, economy, safe aspect; The object of the present invention is to provide a kind of full machine high intensity radiation of type aircraft test method of strong operability; Make to be able to carry out test on the engineering, and improve test efficiency, reduce cost.
The objective of the invention is to realize through following technical scheme:
Generally speaking, the external electromagnetic field energy gets into through following 4 paths and receives test specimen inner:
1. penetrate aircraft skin interferencing propagation to receiving in the test specimen;
2. disturb secondary radiation to receiving in the test specimen through hole, seam handle;
3. get into the interference and coupling conduction through external cable and receive in the test specimen;
4. disturb directly to be coupled into through day bundle of lines and receive in the test specimen;
Entering receives the inner interference of test specimen to continue to influence in the following manner sensitive components again:
Secondary radiation is coupled on internal unit cabinet and the interconnect cable;
The interference of responding on lead or the circuit is directly propagated, is coupled on the components and parts.
Under secondary radiation; All will produce induction current in internal chassis surface of shell and the external cable; The surface of shell induction current further by top 1., 2. path coupling and access arrangement are inner, induction current is further by top 3. path coupling and access arrangement inside in the external cable.
So no matter in other electromagnetic susceptibility test of which kind of level of platform/system/equipment/parts; Can (not consider antenna here receiving test specimen to regard a black box as; Can connect fictitious load during actual tests); Can only------housing, external interface interconnecting cable (containing power lead) be coupled into inside with certain form (radiation or conduction), form final effect through its physical boundary thereby any external electromagnetic stress is all incited somebody to action also its influence.Any uncontinuities such as casing surface hole defect, slit all will be blocked the surface induction electric current and produce secondary radiation, further on internal components housing, lead, induce interference current; Induction current in the interconnecting cable then flows directly into the internal interface circuit through connector pin.Like this, former problem just can be simplified and converts following two big types to: ask the specified irradiation electromagnetic wave that adds receiving the test specimen surface of shell, or the induction current that produces on the interconnecting cable.
The test specimen that receives of the full machine high intensity radiation test of aircraft is an overall aircraft, and its physical boundary has only the aircraft housing, does not consider external interface and interconnect cable thereof, the specified induction current that adds the irradiation electromagnetic wave in the generation of aircraft surface of shell of a demand.Therefore, as long as the electric current that the aircraft surfaces loop wire is injected can reflect the maximum surface induction electric current that aircraft is produced when meeting with the incident field radiation, promptly injection current is the faradic envelope of radiation field, just can think the two equivalence.
Ultimate principle of the present invention is exactly to substitute the electromagnetic irradiation coupling scheme with the injection current coupling scheme; Inject equivalent current through the aircraft surfaces loop wire; Produce same surface current at the aircraft housing and distribute, let aircraft be under the electromagnetic stress of equal value, thereby make aircraft produce same response.Obviously the electric current implantttion technique is more much higher than the efficient of electromagnetic field irradiation.
Concrete grammar of the present invention is following:
The full machine high intensity radiation of a kind of type aircraft test method, this method comprises the steps:
1), with lead at aircraft cockpit, equipment compartment important area outside surface vertical axis around fuselage;
2), with preset low level E
Outer lowElectromagnetic field irradiation receives test specimen;
3), measure induction current I in each surperficial loop wire
Table low
4), repeat above step 1)～3) to test full frequency band scanning survey;
5), measurement data is to the outside irradiation field normalization I of unit
Table low/ E
Outer low
6), the normalization measurement data is carried out linear extrapolation to the high level field intensity of code requirement
I
Table high=E
Outer high* I
Table low/ E
Outer low
7), keep surperficial link position constant, simultaneously to each surperficial loop wire implantation step 6) the pairing high electric current of high level field intensity that obtains, realize that electric current injects to the substituting of high level irradiation, to accomplish the full machine high intensity radiation test of aircraft.
During low level irradiation; Laying some different azimuth conduction loop wires at the area-of-interest outside surface around aircraft (selects suitable wire diameter and thickness of insulating layer to constitute the about 50 ohm microstrip line of characteristic impedance jointly with aircraft surfaces, better matees with the measuring receiver of termination; Select the suitable loop wire number of turns can the surperficial loop wire detection sensitivity of corresponding raising and reduce the injection current power level), with it as the sensor measurement irradiation induction current that surperficial induced current produces in loop wire (just can comprehensive, completely reflect the coupled relation between itself and the aircraft surfaces electric current with 2 orthogonal surperficial loop wires in theory) of getting off the plane.
The full machine high intensity radiation of a kind of type aircraft test method of strong operability provided by the invention; Utilize " aircraft surfaces loop wire electric current implantttion technique "; Substitute the highly difficult high intensity radiation test that to carry out because of condition is limited at present; Make to be able on the engineering carry out this type of test, and significantly improve test efficiency, reduction testing expenses.
Embodiment
Through the practical implementation flow process the present invention is done further detailed description below:
Embodiment
Carrying out aircraft surfaces loop wire electric current when injecting alternate test, need obtain the corresponding magnitude relationship between irradiation field intensity and the surperficial loop wire electric current of injection with measurement method, i.e. transfer function values, normally some data are right.Roughly be divided into for two steps: the one, low level coupling test LLCT (Low Level Coupling Test), the 2nd, high level injection test HLIT (High Level Injection Test).Experiment process is: at important area vertical axis such as aircraft cockpit, equipment compartments around fuselage; Or right (left side) the crossing fuselage in a preceding left side (right side) back lays some 50 ohm of leads; Carry out low level irradiation earlier; Measure the induction current in each surperficial loop wire, obtain the transition function between the induction current in irradiation field intensity and the surperficial loop wire.Utilize induction current in the high level irradiation field surperficial loop wire down of the linear relationship extrapolation standard-required between the high-low level, promptly direct injected value of current.Keep surperficial link position constant at last; Surperficial loop wire is injected above-mentioned corresponding current value; Generate the induction current distribution that comprehensive simulated substitutes the aircraft surfaces under the high level irradiation field, let aircraft be under the electromagnetic stress of equal value, thereby make aircraft produce same response.Induction step is following:
1), at important area outside surface vertical axis such as aircraft cockpit, equipment compartments around fuselage, or right (left side) the crossing fuselage in a preceding left side (right side) back lays some 50 ohm of leads;
2), with preset low level E
Outer lowElectromagnetic field irradiation receives test specimen;
3), measure induction current I in each surperficial loop wire
Table low
4), repeat above step 1)～3) to test full frequency band scanning survey;
5), measurement data is to the outside irradiation field normalization I of unit
Table low/ E
Outer low
6), the normalization measurement data is carried out linear extrapolation to the high level field intensity of code requirement
I
Table high=E
Outer high* I
Table low/ E
Outer low
7), keep surperficial link position constant, simultaneously to each surperficial loop wire implantation step 6) the high level energy that obtains, realize that electric current injects the substituting of high level irradiation, and accomplishes test.
The basic point of aircraft surfaces loop wire electric current implantttion technique is " external electromagnetic environment EME (electromagnetic radiation) stress is to the equivalence response of the galvanomagnetic effect of equal value and the aircraft merit performance of aircraft generation " in the EMC test; Thinking be " for obtain aircraft to outside electromagnetic environment EME stress etc. valence effect and response; obtain to add electromagnetic stress and the irradiation transport function relation between the induction current that produces in the surperficial loop wire of getting off the plane with measurement method; be converted into injection current intensity to former EME stress power level, thus the realization alternate test.
Claims (4)
1. the full machine high intensity radiation of type aircraft test method, this method step is following:
1), with lead at aircraft cockpit, equipment compartment important area outside surface around fuselage;
2), with preset low level E
Outer lowElectromagnetic field irradiation receives test specimen;
3), measure induction current I in each surperficial loop wire
Table low
4), repeat above step 1)～3) to test full frequency band scanning survey;
5), measurement data is to the outside irradiation field normalization I of unit
Table low/ E
Outer low
6), the normalization measurement data is carried out linear extrapolation to the high level field intensity of code requirement, obtain testing the pairing high electric current of needed high level field intensity:
I
Table high=E
Outer high* I
Table low/ E
Outer low
7) keep surperficial link position constant, simultaneously to each surperficial loop wire implantation step 6) the pairing high electric current of high level field intensity that obtains, realize that electric current injects to the substituting of high level irradiation, to accomplish the full machine high intensity radiation test of aircraft.
2. the full machine high intensity radiation of a kind of type aircraft according to claim 1 test method; It is characterized in that: the common microstrip line that constitutes 50 ohm characteristic impedance of said lead and aircraft surfaces; Help the impedance matching with the termination measuring receiver, thereby improve the stable and consistent property of measurement data.
3. the full machine high intensity radiation of a kind of type aircraft according to claim 1 test method is characterized in that: increase conductor loop around the number of turns can improve detection sensitivity and reduce injection current intensity.
4. the full machine high intensity radiation of a kind of type aircraft according to claim 1 test method; It is characterized in that: saidly try to achieve the irradiation field intensity with measurement method and have corresponding magnitude relationship with injecting between the surperficial loop wire electric current; It is transfer function values; And the induction current that high and low level irradiation field produces in the aircraft surfaces loop wire is the linear ratio relation, and reciprocity is also true.
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103033708A (en) * | 2012-12-13 | 2013-04-10 | 中国航空无线电电子研究所 | Plane whole-machine high-strength illumination testing method |
| CN103616595A (en) * | 2013-11-29 | 2014-03-05 | 中国航空无线电电子研究所 | Backflow channel arrangement method in airplane surface current injection test |
| CN105044494A (en) * | 2015-06-29 | 2015-11-11 | 中国航空无线电电子研究所 | Surface current injection measurement method used for electromagnetic compatibility test |
| CN105184108A (en) * | 2015-10-27 | 2015-12-23 | 上海无线电设备研究所 | Composite cabin inner field strength calculation method under HIRF condition |
| CN107153167A (en) * | 2016-03-02 | 2017-09-12 | 陕西飞机工业（集团）有限公司 | A kind of aircraft magnetic field ground test method |
| CN109387707A (en) * | 2017-08-07 | 2019-02-26 | 波音公司 | Large surface array of magnetic field |
| CN109655670A (en) * | 2018-11-21 | 2019-04-19 | 上海无线电设备研究所 | The high high radiation field effect test system and test method that low level directly drives |
| CN110991110A (en) * | 2019-11-27 | 2020-04-10 | 中国电子产品可靠性与环境试验研究所（（工业和信息化部电子第五研究所）（中国赛宝实验室）） | Airplane high-altitude electromagnetic pulse environment risk analysis method and device and computer equipment |
| CN111327378A (en) * | 2019-11-19 | 2020-06-23 | 北京空间技术研制试验中心 | EMC analysis method for spacecraft rendezvous and take-around flight |
| CN113030590A (en) * | 2021-02-24 | 2021-06-25 | 中国人民解放军陆军工程大学 | Large-current injection equivalent substitution irradiation test method for shielded wire coupling channel |
| CN113899923A (en) * | 2021-10-18 | 2022-01-07 | 中国人民解放军军事科学院国防工程研究院工程防护研究所 | System and method for simulating environment of HEMP radiation field and injection energy synchronous loading test |
| CN114167148A (en) * | 2021-12-03 | 2022-03-11 | 中国工程物理研究院流体物理研究所 | System for simulating X-ray irradiation satellite to generate electromagnetic field |
| CN116879664A (en) * | 2023-09-06 | 2023-10-13 | 合肥航太电物理技术有限公司 | Low-level direct drive testing device and testing method for high-intensity radiation field |
| CN116973672A (en) * | 2023-09-25 | 2023-10-31 | 合肥航太电物理技术有限公司 | Low-level scanning current testing device and testing method thereof |
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Cited By (21)
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| CN103033708A (en) * | 2012-12-13 | 2013-04-10 | 中国航空无线电电子研究所 | Plane whole-machine high-strength illumination testing method |
| CN103616595A (en) * | 2013-11-29 | 2014-03-05 | 中国航空无线电电子研究所 | Backflow channel arrangement method in airplane surface current injection test |
| CN103616595B (en) * | 2013-11-29 | 2015-12-02 | 中国航空无线电电子研究所 | Return flow line method to set up in a kind of aircraft surfaces pulse current injectingt test |
| CN105044494A (en) * | 2015-06-29 | 2015-11-11 | 中国航空无线电电子研究所 | Surface current injection measurement method used for electromagnetic compatibility test |
| CN105184108A (en) * | 2015-10-27 | 2015-12-23 | 上海无线电设备研究所 | Composite cabin inner field strength calculation method under HIRF condition |
| CN107153167A (en) * | 2016-03-02 | 2017-09-12 | 陕西飞机工业（集团）有限公司 | A kind of aircraft magnetic field ground test method |
| CN107153167B (en) * | 2016-03-02 | 2019-12-24 | 陕西飞机工业（集团）有限公司 | Aircraft magnetic field ground test method |
| CN109387707A (en) * | 2017-08-07 | 2019-02-26 | 波音公司 | Large surface array of magnetic field |
| CN109655670A (en) * | 2018-11-21 | 2019-04-19 | 上海无线电设备研究所 | The high high radiation field effect test system and test method that low level directly drives |
| CN109655670B (en) * | 2018-11-21 | 2021-04-02 | 上海无线电设备研究所 | Low-level direct-drive high-intensity radiation field effect test system and test method |
| CN111327378A (en) * | 2019-11-19 | 2020-06-23 | 北京空间技术研制试验中心 | EMC analysis method for spacecraft rendezvous and take-around flight |
| CN110991110A (en) * | 2019-11-27 | 2020-04-10 | 中国电子产品可靠性与环境试验研究所（（工业和信息化部电子第五研究所）（中国赛宝实验室）） | Airplane high-altitude electromagnetic pulse environment risk analysis method and device and computer equipment |
| CN110991110B (en) * | 2019-11-27 | 2021-12-07 | 中国电子产品可靠性与环境试验研究所（（工业和信息化部电子第五研究所）（中国赛宝实验室）） | Airplane high-altitude electromagnetic pulse environment risk analysis method and device and computer equipment |
| CN113030590A (en) * | 2021-02-24 | 2021-06-25 | 中国人民解放军陆军工程大学 | Large-current injection equivalent substitution irradiation test method for shielded wire coupling channel |
| CN113899923A (en) * | 2021-10-18 | 2022-01-07 | 中国人民解放军军事科学院国防工程研究院工程防护研究所 | System and method for simulating environment of HEMP radiation field and injection energy synchronous loading test |
| CN113899923B (en) * | 2021-10-18 | 2024-02-23 | 中国人民解放军军事科学院国防工程研究院工程防护研究所 | HEMP radiation field and injection energy synchronous loading test environment simulation system and method |
| CN114167148A (en) * | 2021-12-03 | 2022-03-11 | 中国工程物理研究院流体物理研究所 | System for simulating X-ray irradiation satellite to generate electromagnetic field |
| CN116879664A (en) * | 2023-09-06 | 2023-10-13 | 合肥航太电物理技术有限公司 | Low-level direct drive testing device and testing method for high-intensity radiation field |
| CN116879664B (en) * | 2023-09-06 | 2023-11-24 | 合肥航太电物理技术有限公司 | Low-level direct drive testing device and testing method for high-intensity radiation field |
| CN116973672A (en) * | 2023-09-25 | 2023-10-31 | 合肥航太电物理技术有限公司 | Low-level scanning current testing device and testing method thereof |
| CN116973672B (en) * | 2023-09-25 | 2023-12-29 | 合肥航太电物理技术有限公司 | Low-level scanning current testing device and testing method thereof |
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