CN102426310B - Novel full aircraft high-strength irradiation test method - Google Patents
Novel full aircraft high-strength irradiation test method Download PDFInfo
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- CN102426310B CN102426310B CN201110303988.5A CN201110303988A CN102426310B CN 102426310 B CN102426310 B CN 102426310B CN 201110303988 A CN201110303988 A CN 201110303988A CN 102426310 B CN102426310 B CN 102426310B
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Abstract
The invention discloses a completely new full aircraft high-strength irradiation HIRF 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 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 current injection.
Background technology
Predetermined external electromagnetic environment get off the plane must be entirely normal compatible work of performance.Therefore require, in research & development in flight, type-approval process, to carry out the full machine high-strength magnetic of aircraft irradiation test, to verify its accordance.But current 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, traditional experiment method be the radio-frequency (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 under this electromagnetic stress condition meets relevant regulations requirement.Its technological essence is that aircraft housing adds the surface induction electric current forming under electromagnetic stress effect outside, by aircraft door and window, housing bore, stitches, and the transmission of covering number of ways is coupled to interior of aircraft and is formed secondary radiation; To system/device in machine by the coupling of field-line/field-shell (electric field, magnetic field, far field, near field, induction field), line-line/line-shell/shell-shell, be coupled (capacitive character, inductive, electrical conductance, common impedance, publicly electric current) again and circuit lead on conduction be coupled, disturb responsive device, finally affect overall aircraft duty.In irradiation test, the energy of antenna transmission only has smaller portions to be radiated to be subject on test specimen, and wherein major part is reflected again, and final effect and the energy that is subject to sensitive components in test specimen be a very little part just, so cost effectiveness is extremely low.
In addition, carry out aircraft high intensity radiation and test required site facility, the superpower amplifier that produces 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; The expense of carrying out the test of high intensity radiation also up to tens0000 to millions of.
Current China's national defense mouth EMC test field, equipment/subsystem level EMC test has been carried out more fully, but platform/large system-level EMC test relatively seriously lags behind, especially high intensity radiation test is because condition restriction is almost blank, all the more impact 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 large, be subject to that test specimen operation is limited, the problem of repeated 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 Novel full aircraft high-strength irradiation test method of strong operability, make to be carried out in engineering test, and improve test efficiency, reduce costs.
The object of the invention is to be achieved through the following technical solutions:
In general, external electromagnetic field energy is entered and is subject to test specimen inner by following 4 paths:
1. penetrate aircraft skin interferencing propagation to being subject in test specimen;
2. by hole, seam handle, disturb secondary radiation to being subject in test specimen;
3. by external cable, interference and coupling conduction is entered and is subject in test specimen;
4. through sky bundle of lines, disturbing direct-coupling to enter is subject in test specimen;
Enter and be subject to the interference of test specimen inside to continue again to affect in the following manner sensitive components:
Secondary radiation is coupled on internal unit cabinet and interconnect cable;
The interference of responding on wire or circuit is directly propagated, is coupled on components and parts.
Under secondary radiation, in internal chassis surface of shell and external cable, all will produce induction current, surface of shell induction current is further by above 1., 2. path coupling and access arrangement are inner, and in external cable, induction current is further by 3. path coupling and access arrangement are inner above.
So no matter in other electromagnetic susceptibility test of which kind of level of platform/system/equipment/parts, can being subject to test specimen to regard a black box as, (not consider antenna here, during actual tests, can connect fictitious load), thereby any external electromagnetic stress all will also can only be coupled into inside with certain form (radiation or conduction) through its physical boundary------housing, external interface interconnecting cable (containing power lead) to its impact, form final effect.Any uncontinuities such as casing surface hole defect, gap all will be blocked surface induction electric current and produce secondary radiation, further on internal components housing, wire, induce interference current; Induction current in interconnecting cable flows directly into internal interface circuit by connector pin.Like this, former problem just can be simplified and converts following two large classes to: ask specified additional irradiation electromagnetic wave being subject to test specimen surface of shell, or the induction current producing on interconnecting cable.
The test specimen that is subject to of the full machine high intensity radiation test of aircraft is overall aircraft, and its physical boundary only has aircraft housing, does not consider external interface and interconnect cable thereof, the induction current that the specified additional irradiation electromagnetic wave of a demand produces at aircraft surface of shell.Therefore, as long as the electric current that aircraft surfaces loop wire is injected can reflect the maximized surface induction current that aircraft produces when meeting with incident field radiation, 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 electromagnetic irradiation coupling scheme with Injection Current coupling scheme, by aircraft surfaces loop wire, inject equivalent current, at aircraft housing, produce same Surface current distribution, allow aircraft under electromagnetic stress of equal value, thereby make aircraft produce same response.Obviously current injection is more much higher than the efficiency of Electromagnetic Field Irradiation.
Concrete grammar of the present invention is as follows:
A Novel full aircraft high-strength irradiation test method, the method comprises the steps:
1), by wire at aircraft cockpit, equipment compartment important area outside surface vertical axis around fuselage;
2), to preset low level E
outer lowelectromagnetic Field Irradiation is subject to 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), normalization measurement data is carried out to 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 corresponding high electric current of high level field intensity that obtains, realize electric current and inject to the substituting of high level irradiation, to complete the full machine high intensity radiation test of aircraft.
During low level irradiation, at the area-of-interest outside surface around aircraft, laying some different azimuth conduction loop wires (selects suitable wire diameter and thickness of insulating layer jointly to form the microstrip line of approximately 50 ohm of characteristic impedances with aircraft surfaces, better mates 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 Injection Current power level), using 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 aircraft surfaces electric current with 2 orthogonal surperficial loop wires in theory) of getting off the plane.
A kind of Novel full aircraft high-strength irradiation test method of strong operability provided by the invention, utilize " aircraft surfaces loop wire current injection ", substitute the highly difficult high intensity radiation test that cannot carry out because condition is limited at present, make to be carried out this type of in engineering and test, and significantly improve test efficiency, reduction testing expenses.
Embodiment
Below by concrete implementing procedure, the present invention is described in further detail:
Embodiment
When carrying out aircraft surfaces loop wire electric current injection alternate test, need to obtain irradiation field intensity and inject the corresponding magnitude relationship between surperficial loop wire electric current, i.e. transfer function values, normally some data pair with measurement method.Roughly be divided into two steps: the one, low level coupling measurement 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 front left (right side) rear right (left side) crossing fuselage lays some 50 ohm of wires, first carry out low level irradiation, measure the induction current in each surperficial loop wire, obtain the transition function between induction current in irradiation field intensity and surperficial loop wire.Utilize induction current in the surperficial loop wire under the high level irradiation field of linear relationship between low and high level extrapolation standard-required, i.e. direct injected value of current.Finally keep surperficial link position constant, effects on surface loop wire injects above-mentioned corresponding current value, generate the induction current distribution that comprehensive simulated substitutes the aircraft surfaces under high level irradiation field, allow aircraft under electromagnetic stress of equal value, thereby make aircraft produce same response.Induction step is as follows:
1), at important area outside surface vertical axis such as aircraft cockpit, equipment compartments around fuselage, or front left (right side) rear right (left side) crossing fuselage lays some 50 ohm of wires;
2), to preset low level E
outer lowelectromagnetic Field Irradiation is subject to 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), normalization measurement data is carried out to 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 electric current and inject the substituting of high level irradiation, complete test.
In EMC test, the basic point of aircraft surfaces loop wire current injection is " galvanomagnetic effect of equal value that external electromagnetic environment EME (electromagnetic radiation) stress produces aircraft and the response of the equivalence of aircraft merit performance ", thinking be " for obtain aircraft to outside electromagnetic environment EME stress etc. valence effect and response; with measurement method, obtain the transport function relation that additional electromagnetic stress and irradiation are got off the plane between the induction current producing in surperficial loop wire; former EME stress power level is converted into Injection Current intensity, thereby realizes alternate test.
Claims (3)
1. a Novel full aircraft high-strength irradiation test method, the method step is as follows:
1), by wire in aircraft cockpit, equipment compartment important area outside surface vertical axis or front left rear right or front right rear left around fuselage;
2), to preset low level E
outer lowelectromagnetic Field Irradiation is subject to 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), normalization measurement data is carried out to linear extrapolation to the high level field intensity of code requirement, obtain testing the corresponding 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 corresponding high electric current of high level field intensity that obtains, realize electric current and inject to the substituting of high level irradiation, to complete the full machine high intensity radiation test of aircraft.
2. a kind of Novel full aircraft high-strength irradiation test method according to claim 1, it is characterized in that: the common microstrip line that forms 50 ohm characteristic impedance of described wire and aircraft surfaces, be conducive to the impedance matching with termination measuring receiver, thereby improve the stable and consistent of measurement data.
3. a kind of Novel full aircraft high-strength irradiation test method according to claim 1, is characterized in that: increase conductor loop around the number of turns can improve detection sensitivity and reduce Injection Current intensity.
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| CN201110303988.5A CN102426310B (en) | 2011-10-09 | 2011-10-09 | Novel full aircraft high-strength irradiation test method |
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| CN102426310B true CN102426310B (en) | 2014-03-19 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103033708B (en) * | 2012-12-13 | 2014-11-05 | 中国航空无线电电子研究所 | Plane whole-machine high-strength illumination testing method |
| 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 |
| 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 |
| US10677612B2 (en) * | 2017-08-07 | 2020-06-09 | The Boeing Company | Large surface magnetic field sensor array |
| 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 |
| 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 |
| CN113030590B (en) * | 2021-02-24 | 2023-05-09 | 中国人民解放军陆军工程大学 | High-current injection equivalent substitution irradiation test method for shielded wire coupling channel |
| 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 |
| 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 |
| 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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| JPS63152201A (en) * | 1986-12-17 | 1988-06-24 | Nissan Motor Co Ltd | High frequency current injection device |
| JP3394202B2 (en) * | 1999-01-13 | 2003-04-07 | 太陽誘電株式会社 | Method and apparatus for measuring electromagnetic field intensity and method and apparatus for measuring current-voltage distribution |
| CN101191806B (en) * | 2006-11-29 | 2011-03-30 | 比亚迪股份有限公司 | Apparatus and method for testing automobile electromagnetic sensitivity |
| CN102183696B (en) * | 2011-03-03 | 2013-03-27 | 中国航空无线电电子研究所 | Surface current injection method substituted for electromagnetic compatibility radiation test |
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