NAVY MIL-E-7016 F-1976 ELECTRIC LOAD AND POWER SOURCE CAPACITY AIRCRAFT ANALYSIS OF《飞机电力负荷与电源的容量的分析》.pdf

1、-NIL-E-701bF 1b 7777906 0185741 b = xG9 . 1 . / - -. MIL-E- 7OlfiF 20 July 1976 1. SCOPE - SUPERSEDING MIL- E-007 016E(AS) 8 May 1972 MIGE-7016D(ASG) 15 April 1965 MILITARY SPECIFICATION ELECTRIC LOAD AND POWER SOURCE CAPACITY, AIRCRAFT, ANALYSIS OF This specification is approved for use by all Depa

2、rtments and Agencies of the Department of Defense. 1.1 Scope. This specification covers the methods and requirements for preparing alternating current (ac) and direct current (dc) electric load and power source capacity analyses for aircraft. 2. APPLICABLE DOCUMENTS 2.1 Issues of documents. The foll

3、owing documents, uf the issue in effect on date of invitation for bids or request for proposal, form a part of this specification to the extent specified herein: SPECIFICATIONS MILITARY MLLW-5088 - Wiring, Aerospace Vehicle Beneficial comments (recommendations, additions, deletions) and any pertinen

4、t data which my be of use in improving this document should .be addressed to: Engineering Specifications and standards Department (Code 93), Naval Air Engineering Center, Lakehurst NJ 08733, by using the self-addressed Standardization Document Improvement Pro- posal (DD Form 1426) appearing at the e

5、nd of this document or by letter. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-E-703bF 3b W 7779706 0385742 f_ MIL-E-7016 F STANDARDS MILITARY MIL-STD-7 04 - Electric Power, Aircm Characteristics and Utilization o (Copies of specifications, st

6、andards, drawings, and publications required by contractors in connection with specific procurement functions should be obtained from the procuring activity or as directed by the contracting officer. ) 3. REQUnIEMENTS 3.1 Definitions. For definitions and sample calculations applicable to this specif

7、ication, see section 6. 3.2 Report. The electric load requirements and power source capa- city shall be determined for each electric system under all operating conditions of the aircraft, and an Electric Load and Power Source Capacity Report shall be pre- pared in accrdance with the methods outlined

8、 herein. Analyses shall be made for special-purpose electric systems such as independent engine ignition and control generator systems as well as for general-purpose electric systems. 3.3 - Form. The report shall be printed entirely on 8-1/2 x 11-inch sheets or entirely on 8 x 10-1/2-fnch sheets. Al

9、l letters and numbers shall be at least O. 075 inch tall. All marking on each page shall be included in a 7-1/2 x 10- inch area. The report may be printed on one or both sides of each sheet. The report shall be printed with all marking on all pages in the normal aitude for read- ing with the long si

10、de of each sheet vertical, or with all marking on ali pages in the normal attitude for reading with the long side of each sheet horizontal (not like this specification). The report shail be assembled, and shall be bound on the side which is on the left with the assembled report closed and in the nor

11、mal attitude for reading with the front cover on top, and all pages shall be in the normal attitude for reading when the report is opened to them with the bound edge in this orientation. . 3.4 charts. 3.4.1 Arrangement. The charts shall be presented on a number of sheets as shown in the sample analy

12、ses. These sheets shall be arranged to facilitate cross-referencing from the load equipment chart to the load dysis charts. 3.4.2 Sample analyses. The sample analyses (Figures 1 through 19) illustrate a pical method for presenting data. The information entered consists of excerpts from a typical ana

13、lysis and is not a complete study of the electric power configuration of any particular aircraft. Y . . . / 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-E-7 016F 3.4.3 Numbering of pages. The pages of each complete report shall be nymbered c

14、onsecutively and each shall contain a revision number in the form of a dash number after the page number to indicate the applicability to a particular revision of the report. 3.4.4 Columns and entries. The columns and entries of each chart shall conform to the following: 3.4.4.1 Alphabetical column

15、headings. For referencing, the column headings of the charts are designated alphabetically, and this designation is continued in sequence from sheet to sheet of each complete analysis. 3.4.4.2 Columns without alphabetical designations. Columns shall be provided where indicated in the sample charts f

16、or the following types of entries: a. Item numbers: Consecutive numbers for each item of equipment which shall appear on both sides of the chart when space permits. b. - Notes: For entry of explanations, data, calcula- tions, or other miscellaneous information. 3.4.4.3 Multi-system analyses. When sp

17、ace permits, load analyses for two or more individual systems may be reported on the same group of charts, pro- vided that the individual system analyses are clearly separated and identified. 3.4.4.4 Order of charts. Charts shall be arranged in the order given in the outline of 3.5 for each source.

18、Where several sheets are required for a given chart, all sheets for each chart SU be grouped together in consecutive order. 3.4.4.5 Chart entries. 3.4.4.5.1 Multiple entries. When multiple entries are recorded in the electric power system analysis, the purpose and applicability of each entry shall b

19、e clearly established. in general, multiple entries are required under the following oonditions: a. Op eration at various power levels: When an equipment operates at two or more distinct power levels, the maxi- mum power requirements shall be entered first, foliowed by entries covering the lesser po

20、wer requirements. b. Special power requirements: When special power require- ments cannot be supplied to equipment terminals by the sources in the aircraft, these special requirements shall be Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-E-701

21、bF 16 9779306 0185744 1 MIL- E-7016F fully explained in notes. For example, calibration power requirements might require closer voltage tolerance than that required for normal operation. c. Multiple power sources: When an equipment requires, or is served by muitiple power sources at the same time, i

22、ts requirements shal beentered in the load dysis of each power source. Such multiple entries shall not be com- pounded in system power totals. 3.4.4.5.2 Wperating conditiondt entries. All entries shall be accurate within 5% maximum error. 3.5 Contents. The report shall consist of applicable items fr

23、om the following outline, with ac and dc analyses repeated as required for each electric power system in the aircraft: It em - I Title Page (see 3.5.1) It Table of Contents (see 3.5.2) III Introduction (see 3.5.3) A. Statement of Mission (optional) (see 3.5.3.1) B. Operating Conditions (see 3.5.3.2)

24、 C. Electric Bus Wiring Diagram (see 3.5.3.3) D. Description of Electric System Operation E. Generator Mounting and Drive Data (see 3.5.3.5) F. Power Source Output Data (see 3.5.3.6) (see 3.5.3.4) IV AC Load Analyses (see 3.5.4) A. Connected Load Chart (see 3.5.4.1) B. Load Analysis Chart (see 3.5.4

25、.2) C. Transient Analyses (see 3.5.4.3) D. Power Source Utilization Analysis Chart E. Power Source Utilization Graph (see 3.5.4.5) F. Adjusted Power Source Graph (see 3.5.4.6) A. Comected Uad Chart (see 3.5.4.1) B. Load Analysis Chart (see 3.5.4.2) C. Transient Analyses (see 3.5.4.3) D. Power Source

26、 Utilization Analysis Chart-pee (see 3.5.4.4) V DC Analyses (see 3.5.4 and 3.5.5) 3.5.4.4) 4 c) Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- , MIL-E-703bF 3b 77777Ob 0385745 3 / I , MIL-E-7016F E. Power Source Utilization Graph (see 3.5.4.5) F. A

27、djusted Power Source Graph (see 3.5.4.6) G. Battery Analysis (see 3.5.5.1) VI Starting Load Data (see 3.5.6) A. B. Engine Starting Requirements Data (see Starting Power Source Data (3.5.6.2) 3.5.6.1) VII Ground Power Analysis (see 3.5.7) Vm Summary and Conclusions (see 3.5.8) A. Summary of System An

28、alysis (see 3.5.8.1) B. Conclusions (see 3.5.8.2) Ix Notes (see 3.5.9) 3.5.1 Title Page. The title page shall include the following informa-. tion: * Report for Model * Aircraft Electric Load and Power Source Capacity Date of Report * Contract Number Prepared in accordance with MIL-E-7016F * Number

29、of pages with revision data Serial numbers of aircraft Name and address of aircraft manufacturer Security Classification *Insert any applicable term such as llPreliminaryfl, TIInterme- diate“, or ltFinalll which is specified in the contract. *Insert the model number of the aircraft. *If the report i

30、s a revision, the date of the report shall be the *E any amendment to this spec. is applicable, add: date of the revision, not the date of the original report. (insert the number of the with amendment amendment. ) Additional information may be presented on the title page at the option of the contrac

31、tor. 3.5.2 Table of contents. A table of contents shall be included listing the various parts of the report with the page numbers. a enter Figures 4 and 10. as on Exception: No entry shall be made for equipment used only during engine starting. 3.5.4.2 Load analysis charts - column G. The load analy

32、sis charts are used to determine the total load requirements for each condition under which the aircraft operates. The operating conditions listed in the following paragraphs are considered typical for most military aircraft. The conditions shall be reported and analyzed in the order corresponding t

33、o a typical operation of the particular aircraft. Special conditions applicable shall be reported in additional operating condition columns. The charts for each operating condition shall be designated G1, G2, G3 . . . consecutively for a normal operating sequence. See Figures 5 and 11 for sample loa

34、d analysis charts, I dition existing when electric components are being repaired, checked or tested, and electric power is supplied by internal or external power source(s). The electric loads reported shall include the maximum power requirements of all loads or groups of loads which may be operated

35、simultaneously during maintenance operations. 3.5.4.2.2 Calibration. Calibration is that period when equipment is beix checked for- accuracy or recalibrated. Exception: The condition of calibration may be omitted when each electric equipment in the aircraft can be calibrated with, (1) power having t

36、he characteristics specified in M.L-STD-704, and (2) the ground power source required for the ground maintenance Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-E-7016F condition is also adequate for calibration power. in lieu of the Y!alibration

37、fl entries, a statement that both of the above requirements have been fulfilled shall be included in the notes. 3.5.4.2.3 Loading and preparation. Loading and preparation is that con- dition between securing and starting. Operations performed during this period may consist of hoisting, fueling, ligh

38、ting, radio communications, heating, cooking, etc. During this period, power is supplied by an auxiliary power unit, internai batteries, or an external power source. 3.5.4.2.4 Start and warmup, Start and warmup is that condition from pre- paration for starting to taxiing. An example of an engine sta

39、rting analysis is given in Figure 16, Exceptions: a. Equipment warmup: If certain equipments require extended or otherwise special warmup prior to routine flight operations, the addi- tional condition of flEquipment warmupfl shall be reported. b. Electric-powered start: For aircraft utiliz- ing elec

40、tric power for engine starting, a separate detailed analysis shall be made to define starter input power requirements. When the main engines are started by exter- nal electric power only, the starter load shall not be entered in this column. 3.5.4.2.5 - Taxi. Taxi is that condition from the aircraft

41、s first move- ment under its own power to the start of the takeoff run, and from completion of landing rollout .to engine shutdown. 3.5.4.2.6 Takeoff and climb. Takeoff and climb is that condition com- mencing with the takeoff run and ending with the aircraft leveled-off and set for cruising. 3.5.4.

42、2.7 Cruise. Cruise is that condition during which the aircraft is in level flight but is not in. a combat-ready condition. 3.5.4.2.8 Cruise-combat. Cruise-combat is that condition during which the aircraft is performing its combat missions in a combat-ready or actual combat condition. 3.5.4.2.9 Land

43、ing. Landing is that condition between entering into the base leg of a landing approach and completion of rollout. 9 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3.5.4.2.10 Emergency. Emergency is any period of flight during which the normal sourc

44、es of power are inoperative. During this period, loads essential to safety of flight under any flight condition are transferred to an alternate source of power. These loads are listed in the emergency column, and the total load require- ments are analyzed with respect to the alternate power source.

45、Possible categories of essential electric loads are flight instruments, surface controls, engine controls, and fuel boost systems. If the emergency power source is a battery, see 3.5.5.1. Exception: For rotary wing aircraft having at least two separate primary sources driven by the rotor transmissio

46、n and at least two secondary sources, where a single primary or secondary source can supply all essentid loadss the emergency condi- tion shall be omitted and replaced by analyses of the loads and source capacities remaining after a single failure for each type of power source. 3.5.4.2.11 Mission co

47、mpletion. Mission completion power is defined as minimum electric power required to enable an aircraft to complete its mission. The requirement for this power may occur during any period of the flight. For a multi- engine aircraft the load shall be compared to the power source capacity remaining aft

48、er loss of any one generating or conversion system. For a multi-roleaircraft, the mission requiring most electric power shall be chosen for analysis. 3.5.4.2.12 Additional columns. Additional columns may be used as re- quired to report special operating conditions which may materially affect the loa

49、d analysis by indicating conditions more critical than those specified. These condi- tions might include any of the following: Ground Alert Equipment Warmup Idle Descent Hovering Loiter Jato or Rocket Ignition Launch 3.5.4.2.13 Combination of columns. Where load requirements for one operating condition as specified under 3.5.4.2.12 are identical to those of one or more other conditions, they may be combined into a single column with a suitabl