ARMY ADS-37 A-PRF-1996 ELECTROMAGNETIC ENVIRONMENTAL EFFECTS (E3) PERFORMANCE AND VERIFICATION REQUIREMENTS《电磁环境效应的性能及检验要求》.pdf

1、ADS - 3 7A- PRF 28 MAY 1996 AERONAUTICAL DESIGN STANDARD ELECTROMAGNETIC ENVIRONMENTAL EFFECTS (E3) PERFORMANCE AND VERIFICATION REQUIREMENTS UNITED STATES ARMY AVIATION AND TROOP COMMAND ST.LOUIS, MISSOURI AVIATION RESEARCH AND DEVELOPMENT CENTER DIRECTORATE FOR ENGINEERING DISTRIBUTION STATEMENT A

2、. Approved for public release, distribution is unlimited. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-37A-PRF AERONAUTICAL DESIGN STANDARD . ELECTROMAGNETIC ENVIRONMENTAL EFFECTS (E3) PERFORMANCE AND VERIFICATION REQUIREMENTS 28 MAY 1996 UNIT

3、ED STATES ARMY AVIATION AND TROOP COMMAND ST. LOUIS, MISSIOURI AVIATION RESEARCH AND DEVELOPMENT CENTER DIRECTORATE FOR ENGINEERING PREPARED BY: APPROVED BY: , Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1 .O SCOPE. This document establishes elec

4、tromagnetic environmental effects (E3) performance and verification requirements for aircraft systems. 2.0 p. The following documents form a part of this document to the extent specified herein. STANDARDS MIL-STD-46 1D (1 1 Jan 93) Requirements for the Control of Electromagnetic Interference Emissio

5、ns and Susceptibility MIL-STD-462D(2) Measurement of Electromagnetic Interference (1 Dec 95) Characteristics MIL-STD-704E Aircraft Electrical Power Characteristics (1 May 91) (interface requirements only) MIL-STD- 1385B (1 Aug 86) Preclusion of Ordnance Hazards in Electromagnetic Fields; General Req

6、uirements for (interface requirements only) MIL-STD-1795A (20 Jun 89) Lightning Protection of Aerospace Vehicles and Hardware (for guidance only) FEDERAL AVIATION A DMINISTRA TION Advisory Circular (AC) 20-136 Protection of Aircraft ElectricaVElectronic Systems Against the Indirect Effects of Lightn

7、ing COMMERCIAL RADIO TECHNICAL COMMISS ION FOR AERONAUT ICs (R TCA) DO-l60C, change 1 (27 Sep 90) Environmental Conditions and Test Procedures for Airborne Equipment SOCIETY OF AUTOMOTIVE ENGINEERS SAE AE4L (20 Jun 78) Lightning Test Waveforms and Techniques for Aerospace Vehicles and Hardware (the

8、“Blue Book“) SAE AE4L-87-3 Rev B (Jan 89) Recommended Draft Advisory Circular- Protection of Aircraft Electrical/ Electronic Systems Against the Indirect Effects of Lightning (the “Orange Book“) 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2.1 D

9、EFINITIONS Aircraft Electromagnetic Environment (EME). The Army aircraft world-wide environment is defined in Table I, parts A and B. Lightniny Environment (Direct Effects Testing). For design and verification purposes, the natural lightning environment (which comprises a wide statistical range of c

10、urrent levels, duration, and number of strokes) is represented by current components A through D, and voltage waveforms A, B, and D as defined in paragraph 23.5 of RTCA/DO-l6OC. Guidance for application of these waveforms is also given in Section 23 of RTCA/DO-l60C. )a. Appendix III of FANAC 20-136

11、contains idealized mathematical representations of a severe natural lightning environment. Those waveforms A, B, C, and D are derived from cloud-to-ground lightning discharges. Waveform H represents the high rate-of-rise effects including those from intracloud and cloud-to-cloud discharges. These id

12、ealized waveforms can be used as the bases for either tests or analyses of the effects of a severe lightning environment on aircraft electricallelectronic systems. Test waveforms, of necessity, will be only approximations of the idealized waveforms. Results from test waveforms that deviate from the

13、idealized waveforms must therefore be analytically relatable to the idealized waveform. -. Lightning attachment zones are defined in paragraph 23.2.3 of RTCA/DO- 160C. Guidance for locating the zones on particular air vehicles is discussed in the Section 30.1 of MIL- STD- 1795. LL). The direct effec

14、ts of lightning are the burning, eroding, blasting, and structural deformation caused by lightning arc attachment, as well as the high pressure shock waves and magnetic forces produced by the associated high currents. Direct effects includes the direct coupling of lightning currents into electrical

15、wiring associated with external lighting, antennas, and other external equipment. The indirect effects are those resulting from the interaction of the electromagnetic fields accompanying lightning with electricallelectronic equipment inside the vehicle. Flightt. E3 generated anomalies involving this

16、 equipment would cause immediate or almost immediate loss of aircraft control or unsafe situations with loss of life a likely occurrence. Flicht Essential Eauipment. E3 generated anomalies involving this equipment could cause an emergency landing with possible damage to the aircraft, or would cause

17、the pilot to take other emergency action. Injury or loss of life is possible. Flight Nonessential Eauipment. E3 generated anomaIies involving this equipment would cause reduced safety through lack of redundant systems. Aircraft damage and personnel injury or loss of life unlikely. -Critical. E3 gene

18、rated anomalies involving this equipment would cause immediate or almost immediate mission abort. Injury or loss of life possible though unlikely unless the aircraft is involved in combat, in which case aircraft may not be able to return to base safely. Mission Essential Eauipment. E3 generated anom

19、alies involving this equipment would cause degraded, or lack of, mission success. During combat, aircraft and crew could be in jeopardy of loss. Mission Nonessential Eauipment. E3 generated anomalies involving this equipment would create annoyances and minor discomfort with little impact on mission

20、accomplishment. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Subsvstem. A subsystem is a major functional element of a system, usually consisting of several components that are essential to the operational completeness of the subsystem. Subsyste

21、m examples include airhune, propulsion, guidance, navigation, and communication with reference to the air vehicle as the overall system. The terms system and subsystem are often used interchangeably in defining a functional element (e.g., flight control systemsubsystem, environmental control system/

22、 subsystem, etc.) TABLE I - PART A STANDARD WORLD-WIDE ELECTROMAGNETIC RF ENVIRONMENT JEXTERNAL TO AIRCRAFT) MODULATION PARAMETERS (EXCLUDING PULSE) FIELD FREQUENCY MODULATION STRENGTH SAMPLE o TYPE (ylm RMS) FREQUENCIES .O 14- 1.99 2-19.9 20- 149.9 150-249.9 250-499.9 500-999.9 1000-1 999.9 2000-39

23、99.9 4000-7999.9 8000-9999.9 10,000-40,000 cw, AM CW, AM CW, AM, FM AM, FM AM, FM AM, FM AMYW AM, FM AM, FM AM, FM CW, FM 200 200 200 200 200 200 200 200 200 200 200 Continuous Sweep Continuous Sweep Continuous Sweep Continuous Sweep Continuous Sweep Continuous Sweep Continuous Sweep Continuous Swee

24、p Continuous Sweep Continuous Sweep Continuous Sweep NOTES: CW = Continuous Wave above 1 GHz, use a 1 MHz deviation, modulated by a 10 kHz square wave. FM = Frequency Modulation. Below 1 GHz use a 20 kHz deviation modulated by 1 kHz tone, AM = Amplitude Modulation. Modulated by 1000 Hz tone; 50% mod

25、ulation 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE I -PART B PULSE MODULATION PARAMETERS FREQUENCY MHz) 2-24.9 150-249.0 250- 499.9 500-999.9 1000-1999.9 2000-3999.9 4000-7999.9 8000-9999.9 10,000-40,000 PW u SEC) 833.3 20.0-25.0 25.0-33

26、.0 33.0 1 .o-2.0 1 .o 1 .o-2.0 1 .o 1 .o PRF 3 O0 300 o 200-3 1 O 100-300 670- 1 O00 250-600 250 150-250 1 O00 PEAK FIELD (Vlm RMS) 204 3 120 2830 3480 8420 21270 21270 2 1270 6892 AVERAGE FIELD (V/mRMS) 102 200 200 244 200 336 336 336 200 SAMPLE FREOUENCIES 24 4 6 3 1 3 1 2 6 NOTES: PRF = Pulse Rep

27、etition Frequency PW = Pulse Width AVERAGE FIELD = PEAK FIELD * SQRT(PW*PRF) 3.1 Safetv Marpins. E3 safety margins shall be established for subsystems and equipment assigned to criticality types which would result in a catastrophic failure if susceptible to E3. Flight subsystems and equipment shall

28、have a safety margin of at least 6 dB. The safety margin for electroexplosive devices (EEDs) shall be 16.5 dB. 3.2 Electromagnetic Interference EMI). All equipment and subsystems shall meet the requirements of MIL-STD-461 as modified by this document: 3.2.1. CElOl, CE102, CSlO1, CS114, CS115, CS116,

29、 RElOl, RE102, RSlOl and RS103 apply to ali equipment and subsystems. 3.2.2. CE106 shall apply to all antenna connected receivers and their associated amplifiers or pre- amplifiers. CE106 shall also apply for all transmitters, with their associated amplifiers or pre-amplifiers, in their standby or n

30、on-transmitting mode. Where testing to the CE106 requirement cannot be performed, the requirements of RE102 shall be met with the receiver, transmitter (in the standby or non-transmitting mode) or amplifier and associated antenna tested together. 3.2.3. CE106 shall apply to all antenna connected tra

31、nsmitters and associated amplifiers or preamplifiers in their transmit mode(s). Where testing to the CE106 requirement cannot be performed, the requirements of RE103 shall apply. 3.2.4. RS103 limits shall be changed to the levels and modulations specified in Table I, parts A and B. 3.3 Electromagnet

32、ic Compatibilitv EMC). EMC is required among all subsystems and equipment internal to a system as well as between the aircraft and supporting subsystems external to the aircraft such as ground support equipment (GSE). All subsystems and equipment shall meet specified performance requirements when op

33、erated simultaneously with any single or multiple combination of subsystems and equipments. This requirement applies for all specified modes of operation for each subsystem and equipment. A minimum 16.5 dB safety margin shall be provided for all EEDs. 5 Provided by IHSNot for ResaleNo reproduction o

34、r networking permitted without license from IHS-,-,-3.4 fijlw) . The aircraft shall meet all performance requirements necessary to complete its mission during and after exposure to friendly and hostile electromagnetic emitters as defined by the Army World Wide Environment specified in Table I, parts

35、 A and B. This includes satisfactory performance of Built-In-Test (BIT) checks as well as satisfactory performance when electromagnetic energy may be coupled to the aircraft through ground support equipment, aerial refuelers, and any other equipment external to the aircraft. 3.5 Electromapetic Pulse

36、 (EMPI. Aircraft subsystems, and equipment shall be protected such that exposure to the EMP threat will not cause permanent damage or hazardous temporary upset to flight critical functions. Mission critical functions shall be similarly protected so as to not lessen the probability of mission complet

37、ion. The EMF environment shall be as defined in figure 1. FIELD STRENGTH (V/m) 60000 El (t) = O when t50 = Eoi x kl (e - e -blt) when O0 50000 40000 30000 20000 1 O000 O O 10 20 30 40 50 60 70 80 90 100 TIME (Nanoseconds) Figure 1. Default free-field EMP environment 3.6 Radiation Hazards. Ordnance,

38、fuel, and personnel shall be protected fiom any form of hazardous electromagnetic energy. Specific requirements are as follows: 3.6.1 :I. The HERO requirements for the aircraft shall be in accordance with the interface requirements specified in MIL-STD-1385 except that the minimum field strength sha

39、ll be 200 V/m. All modes of operation including packaging, handling, storage, transportation, checkout, loadinghnloading, and the in-flight configuration shall meet this requirement. Ordnance subsystems shall not be subject to inadvertent ignition or dudding caused by the external environment. The o

40、rdnance shall be considered adequately designed in accordance with these requirements if, in the specified environment, the appropriate stimuli do not exceed the following in any EED in the aircraft: Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fo

41、r Hazards: A 16.5 decibel (dB) margin shall be demonstrated as defined by: 0.15 MNFC oy 0.15 MNFV. (0.15)2 MNFP or (0.15)2 MNFE. For Performance Degradation: A 6.9 dB margin shall be demonstrated as defined by: 0.45 MNFC 0 0.45 MNFV. (0.45)2 MNFP or (0.45)* MNFE. where: MNFC = Maximum No Fire Curren

42、t MNFV = Maximum No Fire Voltage MNFP = Maximum No Fire Power MNFE = Maximum .No Fire Energy 3.6.2 bn. Fuels shall not be inadvertently ignited by the radiated electromagnetic environments of Table I, parts A and B. 3.6.3 Hazards of Electromametic Radiation to Personnel (HERPI. Appropriate measures

43、shall be implemented to prevent inadvertent exposure of personnel to electromagnetic levels higher than the maximum permissible exposure (MPE) levels specified in Tables II and III. For pulsed fields, additional requirements for O. 1 to 300,000 MHz are as follows: a. The peak electric field shall no

44、t exceed 100 kV/m for any pulse. b. For pulse widths less than 100 milliseconds with a pulse repetition period of at least 100 milliseconds, the peak power density for any single pulse shall not exceed the power density in Tables II and III modified as follows: Peak Maximum Permissible Exposure (MPE

45、) = (MPE x Avg time) / (5 x pulse width). Averaging time is from the tables with the same dimension as pulse width. If the pulse width exceeds 1 O0 milliseconds, the pulse repetition period is less than 1 O0 milliseconds, or there are more than 5 pulses during the averaging time, then the total “ene

46、rgy” density (pulse power density integrated over time) during any 100 millisecond period shall not exceed: (MPE x Avg time) / 5. 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Table II. Maximum permissible exposure for controlled environments Ele

47、ctric Field Strength (E) (VJm) . 614 614 1842if 61.4 61.4 Frequency Range (MHz) 0.003 - 0.1 0.1 - 3.0 3 - 30 30 - 100 100 - 300 300 - 3000 3000 - 15000 15000 - 300000 Magnetic Field Strength (H) Power Density (S) E-Field, H-Field 2 (mW/cm ) (Am 163 (1 00, 1000000)* 16.3lf (100,10000/ft)* (900/f , 1

48、OOOO/f2)* 16.3if 16.3if (1 .o, 1 0000/ft)* 0.163 1 .o fi300 10 Frequency Range (MHz) 0.003 - 0.1 0.1 - 100 I I I I 10 Maximum Current (mA) Through both feet Through each foot Contact 2000f 1000f 1000f 200 1 O0 1 O0 Averaging or S (minutes) 6 6 6 6 6 6 6 6 1 6000/F.2 * These plane-wave equivalent pow

49、er density values, although not appropriate for near-field conditions, are commonly used as a convenient comparison with MPEs at higher frequencies and are displayed on some instruments in use. 8 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Table III. Maximum permissible exposure for uncontrolled environments 3000 - 15000 15000 - 300000 fl1500 9