NAVY MIL-C-81950-1973 CHARTS STANDARD AIRCRAFT CHARACTERISTICS AND PERFORMANCE HELICOPTER《直升机标准的飞行特征及表现图表》.pdf

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1、MIL- C - 8195 O (AS ) 8 May 1973 MILITARY SPECIFICATION CHARTS: STANDARD AIRCRAFT CHARACTERISTICS AND PERFORMANCE, HF,LICOPTER This specification has been approved by the Naval Air Systems Comand, Department of the Navy. 1. SCOPE 1.1 . Scope - This specification governs the definitions of requiremen

2、ts for, and methods of presenting characteristics and performance for Navy helicopters. 1.2 Application - For all helicopters proposed or contracted for subsequent tg the effective date of this specification, characteristics and performance data shall be prepared and presented in accordance with the

3、 provisions of this specification and submitted to the Naval Air Systems Command, Deviations from the provisions of this specification to portray more adequately the capability of certain helicopters are permissible, but shall in all cases be approved by the Naval Air Systems Command. explained thro

4、ugh proper annotations on the data charts. Authorized devriations shall be fully 1.3 Types of Charts - Characteristics and performance data shall be presented on the following types of charts as required by the Navy, and utilizing format as provided. such charts is prohibited. Unuthorized reproducti

5、on of 1.3.1 Standard Aircraft Characteristics Charts - The Standard Aircraft Characteristics Charts are intended to proviqe staff personnel with a concise, accurate compilation of physical chaGacteristics an4 performance capabilities of a helicopter. Standardizatiod is required for convenience and t

6、o allow direct comparison with other helicopters intended for a similar mission. i 1.3.1.1 For Standard Aircraft Characteristics and Performance Charts, Plloted Aircraft 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL- C -819 50 (AS ) I MIL-F-5

7、572 Fuel; Aircraft Reciprocating Engine MIL-F- 5616 MIL- F- 5624 Fuel; Aircraft Engine, Grade JP-1 Fuel; Aircraft Turbine and Jet Engine, Grades JP-3 and JP-4 Fuel; aircraft turbine and jet engine Grade JP- 5 MIL-F-5624C MIL-STD - 210A Climatic Extremes for Military Equipment, 2 Aug 57 Air Force - N

8、avy. - Civil Aeronautical ANC-2a ANC Bulletin Ground Loads 2.2 Other Publications Air Force - Naval Technical Order AN 01-1B-40 Handbook of Weight and Balance Data AS 2694- Engines, Aircraft, Turboshaft and Turboprop, General specification Tor, 21 Jan 71 (Copies of specifications, standards, and dra

9、wings required by contractors in connection with specific procurement functions should be obtained from the procuring agency or as directed by the contracting officer. ) 3. REQU3cRMENTS . 3.1 General - Unless otherwise specified by the Navy, preparation by contractors of Charts (and revision thereto

10、) for each model shall include the preparation of photographically reproducible copy in the required types and supporting characteristics and performance data. . categories) and, in addition, satisfactory reports containing 3.1.1 - Revisions - Revisions to the charts shall be prepared and submitted

11、by the contractor throughout the life of the contract. Unless otherwise specified by the Navy, revisions are required whenever significant changes in vehicle . configuration or data occur, as for: (1) A change in vehicle dimensions (2) An accumulation of weight changes resulting in a significant per

12、formance change c Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-C-1750 75 777770b 0270623 b il I MIL-C- 81950 (AS ) (3) A change in power plant designation, augmentation, or power plant rating. The addition of external stores. (4) (5) (6) 3.1.1

13、.1 The availability of test dat.a or new test data showing significant performance change, When specifically directed by the procuring agency. Criteria - The following criteria will be used in forming a judgment as to whether a significant change in performance exists: (1) A change of 5% or more in

14、drag. (2) A change of 5% or more in specific fuel consumption. (3) A change in weight which in itself results in a change of 5% or more in mission radius or range. (4) Any combination of two or more of the above result- ing in a change of 5% or more in mission radius or range 3.1.1.2 Number - Each c

15、hart shall cover only one aircraft model. the following guide is given regarding the probable number of charts and revisions thereto which are required throughout the life of the aircraft model. required will depend on the number of aircraft changes experienced. For the information of the contractor

16、, The exact number of revisions Category of Chart Proposal Mock-up Pre Service Service . Service (Revision) Service (Revision) Re as on New Design Contract for New Aircraft Between Mock-up and First Flight Flight Tests Operational or Fleet Introduction Operational Flight Test o Basis for Data Estima

17、ted Estimated Est imt e d Flight Test Flight Test Flight Te s t of Service Aircraft Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-C - 81950 (AS ) 3.2 on the charts shall be substantiated by reports which shall be submitted with the charts. The

18、reports may be in legible rough draft form utilizing the contractors work-sheet copy, but they shall be complete and shall contain a list of adequate references, authority, and justification for all data used. Contractors are free to use calculation methods of their own selection, but such methods s

19、hall be fully explained, and sample calculations shall be given. Calculations shall be presented in sufficient detail to permit ready review and check of conclusions, and to enable additional calculations to be made by the procuring agency .as required. Substantiating Data - All data presented 362.1

20、 Basic Aerodynamic Data - Prior to preparation of the formal Substantiating Data Report, the approval of the Navy shall be obtained for the data which will form the basis for the Standard Aircraft Characteristics charts. These basic data, including adequate calculations and material for verification

21、 shall include: (1) Low speed drag data itemized according to various aircraft components (fuselage, hub, etc) (2) Fuselage characteristics, Plots of angle of attack vs CL if non-linear, show values for 15 blade elements (deg . ) i. c - chord; if not constant, show values for 15 blade elements (ft .

22、 ) j, m =.mass of blade per foot of radius (slugs/ft. ); if not constant, show values for i5 blade elements k. %=% mg (r-c)dr = f:rst weight moment of blade 1. Ih j m(r-c)2dr = mass moment of inertia of blade about flapping hinge (lb, -ft , )* R .c about flapping hinge (slug-ft 2 )* m. 63 = effectiv

23、e pitch flap.coupling angle n. K = effective spring constant about flapping hinge (ft. -lbs/RAD. ) o. p. U= effective solidity ratio if different from IC2 = effective damping constant about flapping hinge bC/WR 4. (S)R)n = hover tip speed (ft./sec.) r. Local airfoil section-_of blade; if not constan

24、t, show values for i5 blade elements S. CL, CD, CM, vs d vS. Mach NO.: for M = .9 and O 5 Ct 180 where applicable; for each new airfoil. t. CI;, CD vs O for inboard spar U. Percent overlap and projected disc area for tandem helicopter v. Correction factors furnished to airfoil data to allow for any

25、required adjustment of profile drag, profile torque and induced torque. * f no flapping hinges, show moments about center of rotation. - 8 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-i MIL-C-1950 75 9 9799906 0270b24 1 - - - MIL-C - 81950 (AS ) D

26、ata, not accepted by the Navy shall be replaced after conference with the contractor by similar data to be designated by the Navy. 3.2.2 Substantiating Performance Data Report - The Basic Aerodvnamic Data (Para. 3.2.1) shall, after verification _- - and approval of“ the procuring service, form the b

27、asis for the detailed preparation of the formal substantiating data report. These data shall be expanded as necessary and used to pregare the detailed performance data required to substantiate the validity of the Standard Aircraft Characteristics charts. 3.2.3 Revisions - The substantiating data rep

28、ort shall be revised under the same criteria as the charts (see para. 3.1.1). 3.2,4 - Text - The arrangement of %he substantiat- ing data report shall be as contained in Appendix II. 3.3 Standards - Characteristics and performance data shall be based on practical engineering analysis which produce r

29、esults consistent with flight test results of vehicles of like types using standard operating procedures. 3.3.1- Basis for Data - All characteristics and performance data shall be based on the latest reliable aerodynamic, power plant and weight information available, given shall include the effect o

30、n weight and/or performance of a11 authorized contract and service changes, together with important changes assured of authorization but pending at the date of chart issue. The information 3.3.1.1 Changes in Characteristics - Changes in aircraft characteristics which do not result in a significant p

31、erformance change (para. 3.1.1.1) need not be justification for a revision by the contractor. shall be notified by correspondence so that proper notation may be appended to the published chart. However, the prockring agency 3.3.1.2 Flight Tests - Latest approved flight test data shall be used, as so

32、on as available, as a basis for performance. be preferred, contractor flight test results shall be considered, pr Ovide d : While official military flight test results are to (i) The contractor submits his method of flight test, instrumentation used, and analysis leading to reduction of test-results

33、 to standard for review and approval by the Navy. 9 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-C-81950 75 m 997990b 0290b25 3 E MIL-C - 81950 (AS ) (2) Specific “raw“ test data and data reduced to standard conditions are provided the Navy fo

34、r approval prior to use in chart preparation. 3.3.1.3 Guarantees - The data quoted need not necessarily reflect contractors guarantees. 3.3.2 Limitat ions - Perf ormance data shall fall within all established limitations on the vehicle and its components, except as specifically provided herein. 3.34

35、3 Aircraft Condition - Performance shall be presented in such a manner as to show clearly the applicable aerodynamic configuration, power plant, and loading information. Aircraft configurations shall include the installation of complete service equipment applicable to that particular air- craft mode

36、l for the mission concerned. No special sealing of doors or cracks, filling of seams, waxing, or polishing shall be allowed. rotatable enclosures, bomb bay doors, etc., in position of least drag, retractable enclosures and wheels in retracted or closed position, and external bombs or other armament

37、in position for each loading condition, as noted. only those for which service approval has been obtained. Flight performance shall be presented with guns, Fuel loadings shall comprise 3.3.4 Atmosphere - Performance shall be based on the latest approved standard atmospheric tables as specified by th

38、e Navy. 3.3.4.1 Standard Day - Unless otherwise specified, performance shall be based on the ICAO standard atmosphere (59OF .La). 3.3.4.2 Non-Standard Day - Unless otherwise specified, non-standard day performance shall be based on MIL-STD-210A Tropical (89.8O S .L. ) and not (lO3OF S.L. ) condition

39、s . 3.4 Definitions - The following definitions are used for the various data on the charts and shall be strictly adhered to. 3.4.1 Weights - Weights used in preparation of and presented on the charts shall conform with the following. 3.4.1.1 Empty - The empty weight condition The shall be as-define

40、d in the model detail specification. empty weight to be used in preparation of the SAC Chart shall be the latest available estimated, calculated or actual empty weight. _- . .I 10 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-C-41950 75 E 9999

41、906 0290626 5 E MIL-C-81950(AS ) 1 3.4.1.2 Basic - The basic weight shall be as defined in the Handbook of Weigh and Balance Data, AN 01-1B-40, i.e., the empty weight of paragraph 3.4.1.1 plus trapped fuel and oil and all fixed armament and equipment for normal operation. 3.4.1.3 Operating - The bas

42、ic weight of paragraph 3,4,1.2 plus crew, engine oil and any special equipment required for the mission, including any weapon racks or pylons not included in basic weight. mo, payload (bombs, rockets, troops, cargo, etc. ), or auxiliary fuel tanks if such tanks are to be dropped during flight. Does

43、not include usable fuel, 3.4.1.4 Combat - The weight over the target for the mission presented; i-.e, the operating weight of paragraph 3.4.1.3 plus fuel, munition (including missile ordnance) used for air-to-air combat but without bombs, missiles (used for attack of surface targets), torpedoes, min

44、es, cargo or droppable tanks unless otherwise noted. 3.4.1.4.1 as follows: Fuel Load - The fuel load is determined (1) Except for attack helicopters with external drop tanks, the fuel load shall be 6% of initial fuel. helicopters with and without external tanks ) , (Includes (2) For attack helicopte

45、rs with external drop tanks, fuel load shall be 60% of initial fuel load, or full internal fuel less drop tanks, whichever is less. 3.4.1.5 Takeoff - Defined a3 the total weight of the helicopter for the mission presented; i.e, the operating weight of paragraph 3.4.1.3 plus the mission fuel and payl

46、oad and any auxiliary t-anks to be dropped during flight. The takeoff weight normally shall be determined prior to the start of the engines except in specially approved cases when weight expended during taxi and take-off are excluded, Take-off weight shall not exceed maxhum take-off weight. 3.4.1.5.

47、1 Maximum Take-off - Maximum take-off weight is the greatest weight Tor take-off established by Technical Orders, design requirements, or other specific recommendations of the Navy, 3.4.1.5.2 Overload - Unless specifically directed by the Navy, the maximum (overload) take-off weight shall not exceed

48、 the least weight determined by t_he following: Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-C-L950 75 W 799790b 029Ob27 7 (a) The weight of the vehicle fully loaded with fuel, oil, bombs 5nd cargo to capacity for which space and/or tankage is

49、 normally provided. Bearing capacity for the floor and/or supporting structure shall not be exceeded. The expendable weight of ATD (Auxiliary Thrust Devices ) and water used for take-off may be added to the quoted maximum take-off weight provided the criteria of paragraph 3,4.1.5.1.1(b) is satisfied and a-qualif$ng note appears on the chart. The vehicle and its components (rotor, landing gear, supporting structure