1、I FOOT-POUND 1 ADS-1oc-SP 13 March 2000 CAGE Code 18876 AERONAUTICAL DESIGN STANDARD STANDARD PRACTICE AIR VEHICLE TECHNICAL DESCRIPTION AMSC N/A DISTRIBUTION STATEMENT A. Approved for public release, distribution is unlimited. Provided by IHSNot for ResaleNo reproduction or networking permitted wit
2、hout license from IHS-,-,-ADS- 1 OC-SP AERONAUTICAL DESIGN STANDARD AIR VEHICLE TECHNICAL DECRIPTION UNITED STATES ARMY AVIATION AND MISSILE COMMAND AVIATION ENGINEERING DIRECTORATE REDSTONE ARSENAL, ALABAMA 1. FUNCTIONAL DIVIS1 - -. I ., SUBMITTED BY: APPROVED AMCOM and PEO, Aviation 11 Provided by
3、 IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Certification Record Specification f Board Date: O6 March 2000 I Performance Ducurnent Identifier and Title: Standard ADS- I OC-SP, Aeronautical Design Standard, Standard Practice, Air Vehicle Technical Descriptio
4、n I Interface Standard Rationale for Certification: Handbook Decision: I General Tvpe I Decision (4) I Certification _- Design Standard Test Method Standard Process Standard Handbook (non-mandatory use) I Alteniative Action I I I Concur Nonconcur JI Date . 111 Provided by IHSNot for ResaleNo reprodu
5、ction or networking permitted without license from IHS-,-,-TABLE ADS- 1 OC-SP CONTENTS PAGE 1 . SCOPE . 1 1.1 Scope 1 2 . APPLICABLE DOCUMENTS . 1 2.1 General . 1 2.2 Government documents 1 2.3 Order of precedence . 2 3 . DEFINITIONS 2 3.1 Acronyms . 2 4 . GENERAL, REQUIREMENTS . 3 4.1 Documentation
6、 . 3 4.2 Graphs 3 4.3 Tables . 3 4.4 Drawings 3 4.5 Substantiation . 3 5 . DETAILED REQUIREMENTS 4 5.1 5.1.1 5.1.2 5.2 5.2.1 5.2.2 5.3 5.3.1 5.3.2 5.3.3 5.3.4 5.4 5.5 5.6 5.7 5.8 5.9 5.10 5.11 Air vehicle dimensional data. Level I . 4 Drawings 4 Tabulated dimensions and areas . 5 Air vehicle dimensi
7、onal data, Level II . 6 Drawings 6 Airfoil drawings . 6 Air vehicle dimensional data, Level III 7 Basic drawings . 7 Structure drawings 7 Propulsion system drawings . 8 Equipment drawings . 8 Description of the rotor systems . 8 Airfoil section data . 12 Airframe aerodynamic data 13 Rotor structural
8、 dynamics data . 15 Airframe structural dynamics data . 16 Aerodynamic surface data 17 Control system data 18 Propulsion and drive system data . 20 6 . NOTES . 20 6.1 Rotor wake aerodynamic interference 20 6.2 Component aerodynamics 20 6.3 Airfoil Level III data 21 iv Provided by IHSNot for ResaleNo
9、 reproduction or networking permitted without license from IHS-,-,-TABLE I II III IV V VI VI1 VI11 IX ADS-1 OC-SP CONTENTS PAGE Aerodynamic Surfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
10、 . . . . . . . . .6 Rotor Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . , . . , . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .9 Radial Distribution of Rotor Blade Properties Units . . . . . . . .
11、1 O Rotor System Data . . . . . . . . . . . . . . . . . . . . . . 1 O Radial Distribution of Rotor Blade Properties Data . 1 1 Aerodynamics of Fuselage Data . 14 Data for Ground Resonance Model . . . . . . . . . . . . . . . .16 Surface 3-dimensional Force and Moment Data . . . . . . . . 18 Control T
12、ravel Data . . . . . . . . . . . . . . 19 O V Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AIR VEHICLE TECHNICAL DESCRIPTION 1. SCOPE 1.1 Scope. This standard practice Aeronautical Design Standard specifies the air vehicle technical data necessary
13、 to perform a detailed analysis of the performance, handling qualities, rotor dynamics, airframe dynamics, and acoustics of proposed new development or derivative rotorcraft. It is the purpose of this standard to provide a clear technical description of the proposed air vehicle and its components at
14、 a level of detail consistent with the current stage of its design. To this end, the data requirements are divided into topics and the topics are divided into three levels: Level I, Level II, and Level III. Level I (minimum) requires sufficient information to conduct a basic performance and stabilit
15、y and control analysis including the aerodynamic effects of the rotor system and the fuselage. Level II (intermediate) requires all of the data required for Level I plus additional data required for more detailed rotor and fuselage aerodynamics and a basic dynamic analysis of the rotors and the fuse
16、lage. Level III (detailed) is intended to allow a very detailed aerodynamic and dynamic analysis. This standard practice Aeronautical Design Standard is a communications tool. It is intended to provide a standard nomenclature and format for providing a technical description of the design. This stand
17、ard 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 deletion of non- applicable requirements. 2. APPLICABLE DOCUMENTS 2.1 General. The documents listed in this section are specified in section
18、s 3, 4, and 5 of this standard. This section does not include documents cited in other sections of this standard or recommended for additional 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 s
19、pecified requirements documents cited in sections 3, 4, and 5 of this standard, whether or not they are listed. 2.2 Government documents. The following Government documents, drawings, and publications form a part of this document to the extent specified herein. Unless otherwise specified, the issues
20、 are those cited in the solicitation. NACA Report 13 5 1 Theory of Self-Excited Mechanical Oscillations of Helicopter Rotors with Hinged Blades NASA TM-78627 Computer Program to Prepare Airfoil Characteristics Data for Use in Helicopter Performance Calculation 1 Provided by IHSNot for ResaleNo repro
21、duction or networking permitted without license from IHS-,-,-ADS-1 oc-SP USAATCOM TM 93-A-O04 Second Generation Comprehensive Helicopter Analysis System US AAVRADCOM-TR- 8 0-A-5,6,7 Comprehensive Analytical Model of Rotorcraft Aerodynamics and Dynamics USAAVRADCOM-TR-80-D-38A Rotorcraft Flight Simul
22、ation, Computer Program C8 1 with Datamap Interface US ARTL-TR-77-54A Rotorcraft Flight Simulation, Computer Program C81 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
23、document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 3. DEFINITIONS 3.1 Acronyms. tc “2.1 Symbols“ 12 Automatic Flight Control System coefficient of drag center of gravity coefficient of moment coefficient of lift Equivalent parasite drag area
24、Equivalent parasite lift area Equivalent Rolling Moment Volume Mach Number National Advisory Committee for Aeronautics National Aeronautics and Space Administration yaw moment equivalent volume revolutions per minute Structural Design Gross Weight To be determined Vertical Take Off and Landing Equiv
25、alent parasite side force area Three dimensional yaw angle small increment angle of attack partial derivative pitch angle 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS- 1 oc-SP 4. GENERAL REQUIREMENTS 4.1 Documentation. The report(s) prepared
26、 to satis the requirements of this standard may in general be prepared in any format as long as the requirements stated below are met. Each report shall include a table of contents, a list of symbols, a list of figures, a list of tables, and a list of references and/or bibliography. The body of each
27、 report shall be organized in essentially the same format, sequence of topics, and numbering system which is used in this standard. The air vehicle technical description shall be a single report for level I and shall be two reports for levels II and III. The two reports shall be bound separately and
28、 shall consist of the information required by: a. Paragraphs 5.0 through 5.7. b. Paragraphs 5.8 through 5.11 plus all substantiation provided in response to paragraph 4.5 below. 4.2 Graphs. The size and scale used for graphic presentations are a function of the data to be presented. The choice of pa
29、per size and scale shall be left to the offeror. All graphs shall be on a separate page (unless otherwise specified). All graphs shall be on good quality engineering graph paper with the grid retained. Odd scales (such as 7,2.5, and 3 units per division) shall not be used. The scale shall facilitate
30、 interpolation e., there shall be sufficient grid to facilitate reading information directly off the graph). 4.3 Tables. Tables shall be provided in order to give more detail than can be presented in graphic presentations and, also, to provide certain types of computer inputs. As with graphic data,
31、the exact format of the table is a function of the variables to be tabulated. For computer input tables, there shall be enough points tabulated to allow linear interpolation between points without introducing significant errors. 4.4 Drawings. Drawings of the entire air vehicle (e.g., 3 view, inboard
32、 profile) shall be accurately scaled and the scale shall be called out on each drawing. The scales used shall be integer multiples of scales found on a conventional engineers scale (10, 20, 30, 40, 50, 60). In addition to printed copies, the drawing geometry shall be provided in International Graphi
33、cs Exchange Standard (IGES) format. and 4.5 Substantiation. All of the air vehicle technical description data shall be divided into two parts: basic description and derived data. The basic description shall consist of physical dimensions under the direct control of the designer or well-documented pr
34、operties of standard materials (e.g., Youngs Modulus for 2024-T6). Derived data shall consist of any properties of the proposed design which are the result of physical laws operating on the design (e.g., airfoil section data or the stiffness and damping of a complex structure). The basic description
35、 data shall require no substantiation. The derived data shall be substantiated for levels II and III. This substantiation shall be complete and copies of any references (or the referenced portion(s) thereof) shall be appended. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted wi
36、thout license from IHS-,-,-5. DETAILED REQUIREMENTS 5.1 Air vehicle dimensional data, Level I. Level I data shall be IAW 5.1.2, 5.1.2.1,and5.1.2.2. 5.1.1, 5.1.1.1, 5.1.1.2, 5.1.1 Drawings. A set of 3-view, inboard profile and foldedstowed engineering drawings of the air vehicle shall be provided. Ai
37、r vehicles which change configuration during normal operation (e.g., tilting rotors or wings, stopped rotors, stowed rotors) shall be shown in vertical take-off mode for the basic drawings with supplemental drawings showing other modes (e.g., short takeoff, cruise, foldedstowed). These supplemental
38、drawings shall emphasize overall dimensions, clearances, and operating parameters (e.g., rotor shaft angle). 5.1.1.1 Locations. The following stationline, buttline, and waterline locations (inches) shall be clearly labeled on the appropriate drawing(s): a. b. C. d. e. f. g- h. The origin of the fuse
39、lage reference system. Forward and aft ends of the fuselage. Each rotor hub. Aerodynamic center for each aerodynamic surface. Rotor shaft tilt axis and the center of gravity of the tilting mass (if applicable). The ground plane (landing gear unloaded; loaded at Structural Design Gross Weight (SDGW);
40、 and kneeled if applicable). Each external store station. The air vehicle center of gravity (cg) location(s) which are most critical for static turnover, tipback and tipforward. 5.1.1.2 Dimensions. The following dimensions (in inches or degrees) shall be documented on the appropriate drawing(s): a.
41、The radius of each unique rotor. b. The angle of incidence (with respect to the fuselage reference waterline planekenterline plane) of the aerodynamic reference line of each non-rotating aerodynamic surface. c. The longitudinal and lateral shaft tilt angles or angular range (with respect to a vertic
42、al axis perpendicular to the reference waterline plane) of each unique rotor shall be indicated. 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-1 OC-SP d. e. f. g. h. 1. The static and dynamic (rotors turning) clearances of the most critical r
43、otor blade(s) with respect to the rest of the air vehicle and/or the ground plane (landing gear loaded at SDGW). The most critical static turnover, tipback and tipforward angles. The air vehicle overall length, width and height (rotors on and off). The maximum airfiame width, landing gear retracted
44、and extended (without aerodynamic surfaces). The static and dynamic (limit sink speed landing) clearances of the most critical non- rotating components with respect to the ground or deck for the most critical operating condition(s) including slope landings and rolling decks. Cargo compartment, door,
45、 and ramp dimensions. 5.1.2 Tabulated Dimensions and Areas. 5.1.2.1 Airframe. The dimensions required on the drawings shall be tabulated in a compact format for easy reference. All angles shall be in degrees and linear dimensions shall be converted into feet, except for clearances in inches. The fol
46、lowing items (feet or feet2) shall be added to this table. a. Horizontal and/or vertical distance(s) between rotors. b. Landing gear track and tread (feet) plus the stationline and buttline location of the center of each ground contact patch (inches). c. Cargo compartment floor area. d. Wetted areas
47、 of the following mutually exclusive components: fuselage, sponsons, nacelle(s), pylon(s), and spinner(s)/hub fairing(s). 5.1.2.2 Aerodynamic Surfaces. As a minimum, the data per Table I shall be tabulated for each aerodynamic surface (excluding rotor blades). 5 Provided by IHSNot for ResaleNo repro
48、duction or networking permitted without license from IHS-,-,-ADS- 1 oc-SP ITEM UNITS Planform area (exposed and theoretical) feet“ - span feet Aspect ratio (theoretical) - i I Chord (tip and root) I feet I Orientation w.r.t. fuselage reference system degrees Thickness (tip and root) percent of chord
49、 Airfoil section(s) - Control surface, flap or leading edge device area feet“ I Sweep anale of quarter chord I degrees I Control surface, flap or leading edge device span Control surface, flap or leading edge device chord percent of span percent of chord 5.2 Air vehicle dimensional data, Level II. The requirements of Level I shall be provided wit
