ARMY ADS-40 A-SP-2000 AIR VEHICLE FLIGHT PERFORMANCE DESCRIPTION《飞行器的飞行性能描述》.pdf

1、I FOOT-POUND 1 ADS -40A- SP 13 March 2000 CAGE Code 18876 AERONAUTICAL, DESIGN STANDARD STANDARD PRACTICE AIR VEHICLE FLIGHT PERFORMANCE DESCRIPTION AMSC N/A DISTRIBUTION STATEMENT A. Approved for public release, distribution is unlimited. Provided by IHSNot for ResaleNo reproduction or networking p

2、ermitted without license from IHS-,-,-ADS-40A-SP AERONAUTICAL DESIGN STANDARD AIR VEHICLE FLIGHT PERFORMANCE DESCRIPTION UNITED STATES ARMY AVIATION AND MISSILE COMMAND AVIATION ENGINEERING DIRECTORATE REDSTONE ARSENAL, ALABAMA Dirct$rofjAviation APPROVED . Standards Executive DATE: la Gin 11 Provid

3、ed by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Certification Record Board Date: 06 march 2000 Document Identifier and Title: ADS-40A-SP, Aeronautical Design Standard, Standard Practice, Air Vehicle Flight Performance Description Rationale for Certificatio

4、n: Decision: Alternative Action Division Chic h Concur Nonconcur 4- Date . 111 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-40A-SP CONTENTS PARAGRAPH PAGE 1.0 SCOPE 1 1.1 Purpose . 1 2.0 APPLICABLE DOCUMENTS 1 2.1 General . 1 2.2 Government do

5、cuments 1 2.3 Order of precedence . 2 3 .O DEFINITIONS . 2 3.1 Acronyms . 2 3.2 Nondimensionalization 3 4.0 GENERAL REQUIREMENTS 3 General . 3 4.1 4.1.1 Documentation content 3 4.1.2 Documentation media 4 4.1.3 Graphs and tables . 4 4.2 Configuration definition . 4 4.3 Units and sign conventions 5 4

6、.4 Nondimensional . 5 4.5 Rotor speeds . 5 4.6 Substantiation . 5 5 .O DETAILED REQUIREMENTS . 6 5.1 5.1.1 5.1.2 5.2 5.3 5.3.1 5.3.2 5.4 5.4.1 5.4.2 5.4.3 5.5 5.5.1 5.5.2 5.5.3 5.5.4 Isolated nondimensional main rotor flight performance 6 Forward flight . 6 Isolated nondimensional anti-torque system

7、 6 Installed engine performance . 7 Power available at engine output shaft . 7 Other engine parameters . 8 Vertical flight . 6 Air vehicle vertical flight performance 8 Total power required 8 Download . 9 Altitude capability 9 Air vehicle forward flight performance 9 Level flight performance 9 Rate

8、of climb 10 Ceiling 10 Rate of descent . 11 iv Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-PARAGRAPH 5.6 5.6.1 5.6.2 5.7 5.7.1 5.7.2 5.8 5.8.1 5.8.2 5.8.3 5.8.4 5.8.5 5.8.6 5.9 ADS-40A-SP CONTENTS PAGE Power breakdown . 11 Non-rotor power require

9、d . 11 Rotor power required . 11 Mission flight performance 12 Tactical missions 12 Mission radius 12 Maneuvering flight perormance 13 Required maneuvers . 13 Longitudinal acceleration . 13 Sustained load factor 13 Transient load factor . 14 Lateral acceleration 14 Directional control capability . 1

10、5 Decelerating turn 14 6.0 NOTES . 15 6.1 Application of weights and configuration 15 6.2 Documentation media 15 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-40A-SP 1. SCOPE This Standard Practice Aeronautical Design Standard specifies the fli

11、ght performance data required to document the characteristics and capabilities of an air vehicle. It is the purpose of this standard to provide a clear and complete documentation of the air vehicle flight performance at a level of detail which is consistent with the current stage of desigddevelopmen

12、t of the aircraft. The data requirements are divided into three levels: Level I, Level II, and Level III. Level I (the minimum requirement) addresses the level of detail which would be available during the late conceptual design or early preliminary design stage of the air vehicle. Level II addresse

13、s the level of detail which would be available during the late preliminary design or early detailed design stage. Level III addresses the level of detail which would be available during the late detailed design or flight test stage. Each level is intended to be consistent with the corresponding leve

14、l in ADS-1OC-SP, Air Vehicle Technical Description Selected sections of this standard may be added to or deleted. This standard is intended to prescribe a minimum quality of documentation at each Level. 1.1 Purpose. tc “1.1 Purpose“ 1 a This Standard Practice Aeronautical Design Standard is a commun

15、ications tool. It provides a standard set of data requirements to provide documentation of air vehicle flight performance. This standard contains a set of requirements designed to be tailored for each contract by the contracting agency. The tailoring process intended for this standard is the deletio

16、n of non-applicable requirements. 2. APPLICABLE DOCUMENTS tc “2.0 Definition Terms“ I)- 2.1 General. The documents listed in this section are specified in sections 3, 4, and 5 of this standard. This section does not include documents cited in other sections of this standard or recommended for additi

17、onal information or as examples. While every effort has been made to ensure the completeness of this list, documents users are cautioned that they must meet all specified requirements documents cited in sections 3, 4, and 5 of this standard, whether or not they are listed. 2.2 Government documents.

18、The following Government documents, drawings, and publications form a part of this document to the extent specified herein. Unless otherwise specified, the issues are those cited in the solicitation. ADS-1OC-SP Aeronautical Design Standard, Air Vehicle Technical Description Provided by IHSNot for Re

19、saleNo reproduction or networking permitted without license from IHS-,-,-ADS-40A-SP 2.3 Order of precedence. In the event of a conflict between the text of this document and the references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applica

20、ble laws and regulations unless a specific exemption has been obtained. 3. DEFINITIONS 3.1 Acronyms.(tc “2.1 Symbols“ l 2) AEO AEI CD CH CL CN CP CPC CT CW CPh CDRL CP ECU FM GPV HOGE HIGE IAW IGE IRP KTAS L/De MAGW MCP MRP Nr OE1 OGE PMGW r R All Engines Operative All Engines Inoperative Isolated R

21、otor Propulsive Force (Drag) Coefficient (wind axis) Isolated Rotor Propulsive Force Coefficient (shaft axis) Isolated Rotor Lift Coefficient (wind axis) Yawing Moment Coefficient Engine Power or Rotor Power Coefficient Engine Power Coefficient required for VROC. Engine Power Coefficient required fo

22、r HOGE. Isolated Rotor Thrust Coefficient (along shaft) Air Vehicle Weight Coefficient Contract Data Requirements List Contingency Power (2.5-minute limit in OE1 conditions) Environmental Control Unit Figure of Merit Generalized Power Variation: (Cph-Cpc)/(O. 707C .5) Hover Out of Ground Effect Hove

23、r in Ground Effect In Accordance With In Ground Effect (Height above ground measured from extended landing gear) Intermediate Rated Power (30-minute limit) Knots True Airspeed Ratio of Lift to Equivalent Drag (Total Air Vehicle) Maximum Alternate Gross Weight Maximum Continuous Power Maximum Rated P

24、ower (10-minute limit) Rotor RPM One Engine Inoperative Out of Ground Effect Primary Mission Gross Weight Main Rotor Local Radius Main Rotor Radius Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-40A-SP ROC ROD SDGW SL SLS TOGW V VBE VBR VROC vcl

25、imb VVR VT atPP e P Q P OT 7L o Rate of Climb Rate of Descent Structural Design Gross Weight Sea Level Sea Level, Standard temperature Take-off Gross Weight Airspeed Airspeed for best endurance: the airspeed for minimum fuel flow. Airspeed for 99% of best range (high side): the higher of the two air

26、speeds at which the value of specific range is 99% of its maximum (i.e., measured on the “high side“ of the maximum). Vertical Rate of Climb Airspeed for Best Rate of Climb Rotor Tip Speed Vertical Velocity Ratio: VROC/(QR*sqrt(Cw/2) Main Rotor shaft angle with respect to wind. Main Rotor tip path p

27、lane angle w.r.t. wind. Advance Ratio, V/RR Temperature Ratio Rotor Rotational Speed Pi Air Density Geometric rotor solidity Thrust-weighted rotor solidity 3.2 Nondimensionalization. tc “2.2 Nondimensionalization“ 1 2) Dimensional forces shall be nondimensionalized by: P*R*(QR); Dimensional moments

28、shall be nondimensionalized by: p*nR3*(RR)2; Dimensional power shall be nondimensionalized by: p*nR2*(QR)3. 4. GENERAL REQUIREMENTStc “4.0 Report Organization and Format“ 1 1) 4.1 General. tc “4.1 General“ I 2) 4.1.1 Documentation content.tc “4.1.1 Report Content“ 1 3) The data shall be 3 Provided b

29、y IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-40A-SP documented as specified in this standard. (See 6.2.) The documentation shall include the following elements in the following order: Summary, Table of Contents, List of Figures, List of Tables, the main

30、 body, List of References and Appendices (if any). 4.1.2 Documentation media. (tc “4.1.2 Report Media“ I 3) The complete documentation shall be provided in the media as specified in the contract. (See 6.2.) 4.1.3 Graphs and tables.(tc “4.1.3 Graphs and Tables“ 1 3) Graphs and tables shall be present

31、ed in a manner that depict and delineate the results of the documented data. a. If a graph has been constructed based on experimental information then the data points shall be included in symbol format. b. Where accuracy would be enhanced and facilitated, equations for plotted curves shall be docume

32、nted. c. The scales and grids used on graphs shall facilitate interpolation and reading of data directly from the graphs. d. The layout of graphs shall facilitate comparisons between graphs. In general, this means that all graphs which show a particular parameter shall use the exact same scale for t

33、hat parameter. As a specific example, all graphs with airspeed on the x- axis and power on the y-axis shall use the same ranges and physical lengths for each axis so that graphs can be physically overlaid to compare data. e. Tables shall be provided when more detail than can be documented in graphic

34、 presentations is desired, and also, to provide certain types of computer inputs or single point factors. As with graphic data, the exact format of the table shall be a function of the variables to be tabulated. For points representing a function, there shall be enough points tabulated to allow line

35、ar interpolation between points without introducing significant errors. 4.2 Configuration definition.(tc “4.2 Configuration Definition“ 12) At a minimum, data requested for a “range of weights and/or drag values or coefficients“ shall include the following: a. The range of weights (or the correspond

36、ing weight coefficients) shall include the minimum and the maximum flying weights for the stated atmospheric conditions. b. The range of drag values (or the corresponding drag coefficients) shall include the minimum (“clean“) and maximum (“dirty“) drag configurations which are intended for the opera

37、tion of the aircraft as defined by the system specification; it is expected 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-40A-SP that the minimum and maximum shall be a function of air vehicle weight (Le., there is limit as to how clean a hea

38、vy aircraft can be and how dirty a light aircraft can be). c. The values of weight coefficients used and the increment between them shall be “rounded“ and “convenient“ numbers (e.g., weights and their increments end in two zeros). The same concept shall apply to drag values/coefficients. 4.3 Units a

39、nd sign conventions.tc “4.3 Units and Sign Conventions“ I 2) a. The units for data documented shall conform to the following guidelines: all data typically or historically presented to the pilot in English or nautical units (e.g. altitude, rate of climb, airspeed) shall be given in that set of units

40、; all other parameters shall be given in metric units. b. The sign conventions for all forces and moments shall be defined and illustrated in the data documentation. 4.4 Nondimensional data. tc “4.4 Nondimensional“ 12 Nondimensional flight performance information shall be documented in the form of a

41、 baseline carpet plot at a constant Nr/sqrt 0 and accessory load in a specified condition for a range of Cw or CL which is sufficient to derive gross weight values from the minimum to maximum flying weights for ambient temperatures from -5“ C to 35“ C and pressure altitudes from sea level to 10000 f

42、t. Compressibility effects shall be shown in the form of additional carpet plots at sufficient values of constant Nr/sqrt 0 to represent the above temperature range. The effects of drag shall be shown in the form of carpet plots at the baseline Nr/sqrt 0 for a sufficient number of configurations. 4.

43、5 Rotor speeds.tc “4.5 Rotor Speeds“ I 2) For Levels I and II, all dimensional flight performance shall be documented for normal or design rotor speed (power on or off, as appropriate). For Level III, the dimensional documentation shall also include other allowable rotor speeds (autorotation and spe

44、cial cruise etc.). 4.6 Substantiation. tc “4.6 Substantiation“ 12) The documentation shall include a substantiation of the origin and accuracy of the flight performance data documented therein. The depth of substantiation shall be commensurate with the Level which is specified for the documentation.

45、 At a minimum, substantiation shall include a description of the methodology used to produce the data with specific reference to analytical techniques (to include actual input data and a short description), wind tunnel data, and/or flight test data, as applicable, with corrections explained in detai

46、l. The substantiation documentation shall be included in the same section with the related specific flight performance information required by this standard. 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS -40A- SP 5. DETAILED REQUIREMENTS 5.1

47、Isolated nondimensional main rotor flight performance. tc “5 .O Isolated Nondimensional Main Rotor Flight Performance“ 1 1) 5.1.1 Vertical flight.tc “5.1 Vertical Flight“ 1 2) 5.1.1.1 Level I. Isolated main rotor Figure of Merit (FM) vs blade-loading coefficient (CT/O) for OGE and 35“ C conditions s

48、hall be provided. 5.1.1.2 Level II. All Level I data plus the isolated main rotor thrust coefficient (CT) vs isolated main rotor power coefficient (Cp) in Hover Out of Ground Effect (HOGE), Hover In Ground Effect (HIGE) and Vertical Rate of Climb (VROC) Out of Ground Effect (OGE) of 500 ft/min condi

49、tions shall be provided for 35“ C (HIGE data shall be based on a rotor-hub to ground-plane distance equivalent to the air vehicle hovering with the extended landing gear height equal to 5 ft). 5.1.1.3 Level III. In addition to all Level II information, a complete description of rotor performance from HIGE at 2 ft landing gear height up to HO