1、 MIL-HDBK-704-1 9 April 2004 DEPARTMENT OF DEFENSE HANDBOOK GUIDANCE FOR TEST PROCEDURES FOR DEMONSTRATION OF UTILIZATION EQUIPMENT COMPLIANCE TO AIRCRAFT ELECTRICAL POWER CHARACTERISTICS ( PART 1 OF 8 PARTS ) This Handbook is for guidance only. Do not cite this document as a requirement. AMSC N/A A
2、REA SESSNOT MEASUREMENT SENSITIVE Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-HDBK-704-1 ii FOREWORD 1. This handbook is approved for use by all Departments and Agencies of the Department of Defense. 2. This handbook provides guidance on test
3、 procedures for demonstration of utilization equipment to determine compliance with the aircraft electrical power characteristics of MIL-STD-704. 3. MIL-HDBK-704-1 is Part 1 in a series of 8 Parts. Part 1 provides general guidance information on compliance tests, power groups, aircraft electrical op
4、erating conditions, and utilization equipment specifications. Parts 2 through Part 8 provide guidance on application of compliance tests for utilization equipment in specific power groups. These series of handbooks and MIL-STD-704 are companion documents. 4. Comments, suggestions, or questions on th
5、is document should be addressed to Commander, Naval Air Systems Command, Code 4.1.4, Highway 547, Lakehurst, NJ 08733-5100 or email to thomas.omaranavy.mil. Since contact information can change, you may want to verify the currency of this address information using the ASSIST Online database at www.d
6、odssp.daps.mil/ Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-HDBK-704-1 iii CONTENTS PARAGRAPH PAGE FOREWORD ii 1. SCOPE . 1 1.1 Scope. 1 2. APPLICABLE DOCUMENTS 1 2.1 General 1 2.2 Government documents. . 1 2.2.1 Specifications, standards and
7、 handbooks 1 3. DEFINITIONS 1 3.1 Acronyms and definitions. 1 4. GENERAL INFORMATION. 1 4.1 Utilization equipment compliance testing. . 1 4.2 Compliance tests. 1 4.3 Utilization equipment power groups. 2 4.4 Aircraft electrical operating conditions. . 2 4.5 Utilization equipment performance specific
8、ations. 2 4.5.1 Examples of utilization equipment performance requirements. . 3 4.6 Dual source utilization equipment. . 6 4.7 Transformer rectifiers units. . 6 4.8 Inverters. . 7 4.9 Compliance to aircraft electrical power characteristics demonstration test methods of MIL-HDBK-704-2 through -8. 7 4
9、.10 Stimulation and monitoring equipment. . 7 4.10.1 Stimulation equipment 7 4.10.2 Monitoring equipment. . 7 5. NOTES . 8 5.1 Intended use. . 8 5.2 Single phase test numbers. 8 5.3 Subject term (keyword) listing. 8 TABLE I. Power groups. . 9 II. Aircraft electrical power systems operating condition
10、s 9 III. Test numbering nomenclature example SAC303A. . 9 IV. Single phase, 400 Hz, 115 V, utilization equipment compliance tests. 10 V. Three phase, 400 Hz, 115 V utilization equipment compliance tests. 11 VI. Single phase, variable frequency, 115 V utilization equipment compliance tests. . 12 Prov
11、ided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-HDBK-704-1 iv CONTENTS PAGE TABLE VII. Three phase, variable frequency, 115 V utilization equipment . compliance tests. . 13 VIII. Single phase, 60 Hz, 115 V utilization equipment compliance tests 14 IX
12、. 28 VDC utilization equipment compliance tests. . 15 X. 270 VDC utilization equipment compliance tests. . 16 CONCLUDING MATERIAL 16 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-HDBK-704-1 1 1. SCOPE 1.1 Scope. This handbook provides guidance
13、on test procedures for demonstration of utilization equipment to determine compliance with the aircraft electrical power characteristics of MIL-STD-704. This handbook is for guidance only and cannot be cited as a requirement. 2. APPLICABLE DOCUMENTS 2.1 General. The documents listed below are not ne
14、cessarily all of the documents referenced herein, but are those needed to understand the information provided by this handbook. 2.2 Government documents. 2.2.1 Specifications, standards and handbooks. The following specifications, standards, and handbooks form a part of this document to the extent s
15、pecified herein. DEPARTMENT OF DEFENSE STANDARDS MIL-STD-704 DoD Interface Standard for Aircraft Electric Power Characteristics (Copies of these documents are available at http:/assist.daps.dla.mil/quicksearch/ or www.dodssp.daps.mil/or from the Standardization Document Order Desk, 700 Robbins Avenu
16、e, Building 4D, Philadelphia, PA 19111-5094.) 3. DEFINITIONS 3.1 Acronyms and definitions. The acronyms and definitions of MIL-STD-704 are applicable to this handbook. 4. GENERAL INFORMATION 4.1 Utilization equipment compliance testing. MIL-STD-704 states that equipment testing is required to demons
17、trate that utilization equipment is compatible with the electric power characteristics as defined in MIL-STD-704. MIL-STD-704 is the interface document that defines the aircraft electrical power characteristics at the input terminals to utilization equipment. The aircraft electrical system must prov
18、ide power in accordance with MIL-STD-704 and the utilization equipment must perform as specified when provided input power in accordance with MIL-STD-704. MIL-HDBK-704-1 through MIL-HDBK-704-8 provide detail test methods for demonstrating compliance to MIL-STD-704. All previous editions of MIL-STD-7
19、04, which have been cited in aircraft platform or subsystem contracts, remain in effect. The applicable edition of MIL-STD-704 for utilization equipment compliance is the edition that is applicable to the aircraft platform or platform(s) in which the utilization equipment will be installed. 4.2 Comp
20、liance tests. Compliance tests are intended to give a reasonable assurance that the utilization equipment will perform as specified when installed in aircraft that are Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-HDBK-704-1 2 designed and buil
21、t to the applicable edition of MIL-STD-704 without unduly burdening the development of utilization equipment. The compliance tests simulate the range of power characteristics that utilization equipment may experience during its life. The compliance test procedures cannot simulate exactly every power
22、 condition that may be experienced by the utilization equipment. The designer/manufacturer of utilization equipment must design and build the utilization equipment to be compatible with the power characteristics defined in the applicable edition(s) of MIL-STD-704 and should not design equipment sole
23、ly based on the test procedures herein. 4.3 Utilization equipment power groups. There are seven utilization input power types defined by the different editions of MIL-STD-704. The MIL-STD-704 compliance tests are organized into power groups based on input electrical power type to utilization equipme
24、nt. The power groups are: a. Single Phase, 400 Hz, 115 Volt (AC) b. Three Phase, 400 Hz, 115 Volt (AC) c. Single Phase, Variable Frequency, 115 Volt (AC) d. Three Phase, Variable Frequency, 115 Volt (AC) e. Single Phase, 60 Hz, 115 Volt (AC) f. Direct Current, 28 Volt (DC) g. Direct Current, 270 Vol
25、t (DC) The preferable input power type for utilization equipment differs for each aircraft platform. The selection of input power type for utilization must take into consideration the aircraft power types available on the intended aircraft platform and the capacity of the electrical system on the ai
26、rcraft. All power types may not be available on an aircraft platform. 4.4 Aircraft electrical operating conditions. MIL-STD-704 defines six distinct aircraft electrical system operating conditions: (1) Normal Electrical Power, (2) Power Transfers, (3) Abnormal Electrical Power, (4) Emergency Electri
27、cal Power, (5) Engine Starting, and (6) Power Failure. The equipment performance specification must explicitly define the performance requirement of the utilization equipment for the six aircraft electrical operating conditions. 4.5 Utilization equipment performance specifications. Utilization equip
28、ment specifications should include utilization equipment performance level requirements when operating with electrical input power characteristics that fall within the six aircraft electrical operating conditions. The following are given as examples only and are not intended as recommended performan
29、ce levels for utilization equipment. Performance levels for utilization equipment for the six aircraft electrical operating conditions should based on the criticality to flight safety, mission requirements, cost, weight, and reliability; and are unique to each utilization equipment. Current distorti
30、on and current spectrum limits may be imposed to minimize undesirable current distortion draw of utilization equipment and reduce the likelihood of the equipment having an adverse effect on the electrical power characteristics of the aircraft. These current distortion limits should take into account
31、 the utilization equipment power draw, aircraft electrical system capacity and distribution characteristics, trade-offs with weight, volume, cost, and reliability that are specific to each type of equipment and aircraft. Provided by IHSNot for ResaleNo reproduction or networking permitted without li
32、cense from IHS-,-,-MIL-HDBK-704-1 3 4.5.1 Examples of utilization equipment performance requirements. a. Example 1: Flight Critical Computer and Flight Displays (1) Performance level for normal aircraft electrical operating condition - The flight critical computer and flight displays shall provide 1
33、00 percent full performance during normal aircraft electrical operation. The flight critical computer shall provide all data signals. There shall be no interruption, corruptions, or data loss. Displays shall not flicker or become distorted. The flight critical computer and flight display shall not b
34、e damaged or cause an unsafe condition. The flight critical computer and flight display shall not cause the aircraft electrical power to degrade beyond the limits of the applicable edition(s) of MIL-STD-704. Total current distortion shall be less than 12 percent for steady state normal aircraft elec
35、trical operation. (2) Performance level for power transfer aircraft electrical operating condition - The flight critical computer and flight displays shall provide 100 percent full performance before, during, and after power transfer. The flight critical computer and flight displays shall provide th
36、e same performance level for power transfer aircraft electrical operating conditions as for normal electrical operating conditions. (3) Performance level for abnormal aircraft electrical operating condition - The flight critical computer and flight displays shall provide 100 percent full performance
37、 during abnormal electrical operation. The flight critical computer and flight displays shall provide the same performance level for abnormal aircraft electrical operating conditions as for normal electrical operating conditions. (4) Performance level for emergency aircraft electrical operating cond
38、ition - The flight critical computer and flight displays shall provide 100 percent full performance during emergency electrical operation. The flight critical computer and flight displays shall provide the same performance level for emergency aircraft electrical operating conditions as for normal el
39、ectrical operating conditions. (5) Performance level for starting aircraft electrical operating condition - The flight critical computer and flight displays shall provide 100 percent full performance during emergency electrical operation. The flight critical computer and flight displays shall provid
40、e the same performance level for starting aircraft electrical operating conditions as for normal electrical operating conditions. (6) Performance level for power failure aircraft electrical operating condition - The flight critical computer and flight displays are allowed to shutdown for power failu
41、res greater than 50 milliseconds. For power failure less than seven seconds, the flight critical computer and flight displays shall automatically return to 100 percent full performance within one second after power is restored. There shall be no corruption, or data loss due to the power failure. The
42、 flight critical computer and flight display shall not be damaged or cause an unsafe condition. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-HDBK-704-1 4 b. Example 2: Mission Data Storage Device and Mission Displays (1) Performance level for
43、normal aircraft electrical operating condition - The mission data storage device and mission displays shall provide 100 percent full performance during normal aircraft electrical operation. The mission data storage device and mission displays shall provide all data signals. There shall be no interru
44、ption, corruptions, or data loss. Displays shall not flicker or become distorted. The mission data storage device and mission displays shall not be damaged or cause an unsafe condition. The mission data storage device and mission displays shall not cause the aircraft electrical power to degrade beyo
45、nd the limits of the applicable edition(s) of MIL-STD-704. Total current distortion shall be less than 12 percent for steady state normal aircraft electrical operation. (2) Performance level for power transfer aircraft electrical operating condition - The mission data storage device and mission disp
46、lays may momentarily interrupt during power transfer. The mission data storage device and mission displays shall automatically return to 100 percent full performance within 5 seconds after the power returns to within normal limits. There shall be no corruption, or data loss. The mission data storage
47、 device and mission displays shall not be damaged or cause an unsafe condition due to the power transfer. The mission data storage device and mission displays shall not cause the aircraft electrical power to degrade beyond the limits of the applicable edition(s) of MIL-STD-704. (3) Performance level
48、 for abnormal aircraft electrical operating condition - The mission data storage device and mission displays may momentarily interrupt during abnormal aircraft electrical operation. The mission data storage device and mission displays shall automatically return to normal operation within 5 seconds a
49、fter the aircraft electrical system operation returns to normal. There shall be no corruption or data loss. Displays may flicker or become distorted, but must still be readable. The mission data storage device and mission displays shall not be damaged or cause an unsafe condition. (4) Performance level for emergency aircraft electrical operating c
