DI-SESS-82291

Air Vehicle Technical Description Report for Rotorcraft and Propeller-Driven Fixed-Wing Aircraft

Specifies the technical data and supplementary technical data required for Government assessment of flight performance, stability and control, handling qualities, and related characteristics of new or derivative rotary-wing and propeller-driven fixed-wing aircraft.

Approval DateSeptember 18, 2019

AMSC Number10057

Preparing ActivityAV

Project NumberSESS-2019-013

OPR—

DTIC ApplicableNo

GIDEP ApplicableNo

Limitation—

Applicable Forms—

Approval Limitation—

Form Version—

DID Formatfree_text

963C CompliantYes

DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited.

Supersedes

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Description & Purpose

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Application & Interrelationship

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Use & Relationship

This Data Item Description (DID) specifies the technical data and supplementary technical data necessary for Government assessments of the flight performance, stability and control, handling qualities, rotor dynamics, airframe dynamics, engine/drive system response characteristics, and transportability characteristics of new design or derivative rotary-wing and propeller-driven fixed-wing aircraft. These evaluations and analyses are used to support the substantiation of aircraft airworthiness in accordance with (IAW) Army Regulation (AR) 70-62, and to support Government technical analyses IAW Federal Acquisition Regulation (FAR) 15.404-1(e).

The Air Vehicle Technical Description Report will be included in the rotorcraft's or propeller-driven aircraft's Government record of airworthiness substantiation IAW AR 70-62.

This DID is applied in the solicitation and contract for all phases of system acquisition. Sections applicable to the acquisition will be identified by the buying activity by tailoring this DID in DD Form 1423, Contract Data Requirements List (CDRL). Updates to the report will be as specified as part of the DID tailoring activity.

This DID contains the format, content, and intended use information for the data deliverable resulting from the work task described in the solicitation or contract.

Preparation Instructions

1Reference DocumentsThe applicable issue of the documents cited herein, including their approval dates and dates of any applicable amendments, notices, and revisions, shall be as specified in the solicitation or contract.

2FormatMultimedia report formatting shall be in accordance with (IAW) American National Standards Institute/National Information Standards Organization (ANSI/NISO) Z39.18.

2.1VolumesThe report shall be divided into separate volumes based on contractually-specified Data Marking IAW Defense Federal Acquisition Regulation Supplement (DFARS) 252.227-7013(f), Distribution Statement IAW Department of Defense Instruction (DODI) 5230.24, and security classification level IAW the contractually-specified Classification Guide.

2.2Report Documentation PageThe report and each separate appendix and annex shall include a Standard Form (SF) 298 Report Documentation Page.

2.3Interchange MediumThe multimedia report shall be composed and delivered in computer-readable files for inclusion in Department of Defense Model-Based Enterprise information systems. Digital file formats shall comply with open standards to future-proof file access.

2.4System of MeasurementThe Report shall use either the International System of Units (SI; meter-kilogram-second) system of measurement, the British Gravitational Units (BG; foot-slug-second) system of measurement, or SI units followed by equivalent BG units in parenthesis. The system of measurement shall be used consistently throughout the report and all attachments.

2.4.1Measurement Unit Abbreviations, Acronyms, and SymbolsAbbreviations and acronyms for units of measurement shall be IAW American Society of Mechanical Engineers (ASME) Y14.38. Letter symbols for units of measurement shall be IAW Institute of Electrical and Electronics Engineers (IEEE) Std 260.1.

2.5Engineering Design DataEngineering design data shall conform to ASME Y14.24, ASME Y14.41, and ASME Y14.100 standards for accuracy, legibility and clarity. (Engineering design data is defined IAW MIL-STD-31000, Technical Data Packages, as engineering drawings, Three Dimensional Intelligent (3Di) viewables, native Computer-Aided Design (CAD) models, neutral CAD models or a combination of these, which define the physical and/or functional requirements of an item by means of graphic and textual presentations. Engineering design data shall be included in the multimedia report as computer-readable entities IAW MIL-STD-31000. Digital formats for data exchange shall comply with open standards to future-proof access.

2.6CAD Solid ModelsNative or neutral CAD solid models shall be included in the multimedia report as computer-readable entities IAW MIL-STD-31000. Digital formats for data exchange shall comply with open standards to future-proof access.

2.7Airfoil Sections

2.7.1Section ProfilesPlots shall use an expanded vertical scale, or 'whale plot' for clarity. Each section profile shall include a table of coordinates. Not less than 50 points on both the upper and lower surfaces shall be included in the table; at least 20 of these points shall be within the first 20 percent of the airfoil chord. Point clustering shall be used to resolve curvature or sharp discontinuities in surface topology.

2.7.2Two-Dimensional (2D) CAD ModelsNative or neutral 2D CAD shrink-wrap models of airfoil sections shall be included in the multimedia report as computer-readable entities IAW MIL-STD-31000. 'Non-Uniform Rational B-Spline' (NURBS) CAD entities shall be used to digitally represent airfoil section contours for data exchange. The airfoil section profiles shall be watertight for use in creating viscous computational fluid dynamics (CFD) meshes. Digital formats for data exchange shall comply with open standards to future-proof access.

2.8Automatic Flight Control System (AFCS) Digital ModelsAFCS digital models shall include a graphical representation of the AFCS algorithmic model in MATLAB/Simulink or equivalent computer-readable format. Digital formats for data exchange shall comply with open standards to future-proof access.

2.9Animations/VideoDigital formats for animations and video shall comply with open standards to future-proof media playback.

2.10GraphsThe size and scale used for graphic presentations are a function of the data to be presented. Axis scales shall facilitate interpolation (i.e., scale increments shall facilitate reading data directly from the graph).

2.11TablesTabulated data shall consist of machine-encoded text that may be retrieved by automated information systems without the use of intermediate optical character recognition software. The exact format of the table is a function of the variables to be tabulated. Data discretization shall allow linear interpolation between points. If tabulated data are lengthy, more than 2 pages, and complicate understanding or interpretation they shall be placed at the end of the Report in numeric order.

2.11.1Mass PropertiesData shall include weights, center of gravity (CG) locations, and moments of inertia per Table I.

2.12Mathematical Symbols and EquationsFonts shall comply with open standards to future-proof computer display.

2.13Body TextThe main textual content of the report and each separate appendix and annex shall consist of machine-encoded text that may be searched and indexed by automated information systems without the use of intermediate optical character recognition software. Fonts shall comply with open standards to future-proof computer presentation.

2.14Airfoil Aerodynamic Data in C81 File FormatAmerican Standard Code for Information Interchange (ASCII) text files of tabulated airfoil nondimensional aerodynamic lift, Cl, drag, Cd, and pitching moment, Cm, data as a function of angle of attack, alpha, and Mach number, Ma, shall be included in the report as computer-readable media. The 'C81 airfoil file format' is a structured table format for airfoil aerodynamic data that is used by many rotorcraft analysis computer programs. Table II describes the C81 airfoil file format. 'Record' denotes separate lines in the file. The format does not allow blank lines between Records; hence, unused Records are not included. The file shall not contain tab characters or other unprintable characters within Record fields to the left of column 73. Data Markings or comments must be confined to the right of column 72 or below the last Record.

2.15Engine Performance DescriptionDocumentation shall include uninstalled engine static performance data referred to the International Standard Atmosphere Sea-Level Standard (ISA SLS) condition for a representative sample of applicable shaft speeds as illustrated by Table III. Power level definitions used include Maximum Continuous Power (MCP; continuous power/torque limit), Intermediate Rated Power (IRP; 30 minute power/torque limit), Maximum Rated Power (MRP; 10 minute power/torque limit), and Contingency Rated Power (CRP; 2.5 minute power/torque limit).

3ContentThe Air Vehicle Technical Description Report shall include the following:

3.1Vehicle Configuration

3.1.1Conceptual LevelThe Conceptual Level subdivision is defined IAW MIL-STD-31000 as design concepts with additional information required for analysis and evaluation.

3.1.1.1Engineering Design Data

3.1.1.1.1Inboard profile and layout views ofInboard profile and layout views of the air vehicle in vertical take-off and landing (VTOL) mode (if applicable). The views shall include overall layout, dimensions, clearances, and operating parameters (e.g., rotor shaft angle(s), fixed aerodynamic surface angle(s)).

3.1.1.1.2Views illustrating vehicles that change configurationViews illustrating vehicles that change configuration during normal flight operation (e.g., tilting rotors, wings, or ducts; movable control surfaces; variable-sweep wings; swiveling tail rotor/propulsor(s); stopped rotor(s); folded/stowed rotor(s); deployable armament and launchers).

3.1.1.1.3Views used to illustrate other modesViews used to illustrate other modes (e.g., running takeoff or landing, cruise-flight mode for a tail-sitter).

3.1.1.1.4Views used to document overall layoutViews used to document overall layout, dimensions, and clearances for the aircraft when folded and stowed to minimize volume required for deck or hanger parking, air and ship transport, long-term storage, etc.

3.1.1.1.1LocationsLocations shall be marked on the appropriate view(s) in the aircraft standard stationline (SL), buttline (BL), and waterline (WL) coordinate system. Marked locations shall include:

3.1.1.1.1.1Origin and orientation of the aircraft standardOrigin and orientation of the aircraft standard coordinate system.

3.1.1.1.1.2Forward and aft ends of the fuselageForward and aft ends of the fuselage, flight-ready, in-flight, and folded/stowed for storage/transport.

3.1.1.1.1.3Heights of lowest and tallest features (excludingHeights of lowest and tallest features (excluding alighting gear and rotating blades), flight-ready, in-flight, and folded/stowed for storage/transport.

3.1.1.1.1.4Lateral extent(s) of the widest features, excludingLateral extent(s) of the widest features, excluding alighting gear, rotating blades, and foldable/removable portions of fixed aerodynamic surfaces.

3.1.1.1.1.5Shaft center of rotation of each rotorShaft center of rotation of each rotor.

3.1.1.1.1.6Rotor/propulsor shaft tilt/swivel axis and the centerRotor/propulsor shaft tilt/swivel axis and the center of gravity (CG) of the tilting/swiveling mass (if applicable).

3.1.1.1.1.7Aerodynamic center for each fixed aerodynamic surfaceAerodynamic center for each fixed aerodynamic surface.

3.1.1.1.1.8Fixed aerodynamic surface tilt axis and theFixed aerodynamic surface tilt axis and the CG of the tilting mass (if applicable).

3.1.1.1.1.9Hinge line locations for aerodynamic control surfacesHinge line locations for aerodynamic control surfaces (e.g., flaps, ailerons, rudders, elevators).

3.1.1.1.1.10Fixed aerodynamic surface leading-edge flap(s) and slat(s)Fixed aerodynamic surface leading-edge flap(s) and slat(s).

3.1.1.1.1.11Fixed aerodynamic surface wingletsFixed aerodynamic surface winglets.

3.1.1.1.1.12The centerline, CG, and notional shape representationThe centerline, CG, and notional shape representation of engine(s), motor(s), transmission(s), battery(s), internal armament, and any other major items.

3.1.1.1.1.13Emergency egress openingsEmergency egress openings.

3.1.1.1.1.14Integral/bladder and discrete fuel tank(s)Integral/bladder and discrete fuel tank(s).

3.1.1.1.1.15Auxiliary fuel tank(s), internal and external, fixedAuxiliary fuel tank(s), internal and external, fixed and removable.

3.1.1.1.1.16Fueling point(s)Fueling point(s).

3.1.1.1.1.17Aerial refueling probeAerial refueling probe.

3.1.1.1.1.18Engine inlet(s) and exhaust(s)Engine inlet(s) and exhaust(s).

3.1.1.1.1.19External inlet air filtration and particle separationExternal inlet air filtration and particle separation device(s). A-kit (fixed) and B-kit (removable) components shall be clearly delineated for removable devices.

3.1.1.1.1.20External exhaust infrared and acoustic signature controlExternal exhaust infrared and acoustic signature control device(s). A-kit and B-kit components shall be clearly delineated for removable devices.

3.1.1.1.1.21Avionics and mission equipment compartment(s)Avionics and mission equipment compartment(s).

3.1.1.1.1.22Stores bay door(s), showing both open andStores bay door(s), showing both open and closed configurations.

3.1.1.1.1.23Each internal store carriage station, showing bothEach internal store carriage station, showing both deployed and retracted configurations.

3.1.1.1.1.24Each external store stationEach external store station.

3.1.1.1.1.25Sensor and weapon turret/dome(s), showing range ofSensor and weapon turret/dome(s), showing range of motion(s), if applicable.

3.1.1.1.1.26Alighting gear, showing both deployed and retractedAlighting gear, showing both deployed and retracted configurations.

3.1.1.1.1.27The ground plane (alighting gear unloaded; loadedThe ground plane (alighting gear unloaded; loaded at Maximum Ground Weight IAW SAWE RP-7; and kneeled.

3.1.1.1.1.28Aircraft folding hinge lines for storage/transportAircraft folding hinge lines for storage/transport.

3.1.1.1.1.29Any points of contact between the aircraftAny points of contact between the aircraft surface and a transport ship/aircraft loading ramp crest/toe for a 15 degree ramp inclination; alighting gear loaded at transportation configuration weight and kneeled. (Refer to 4.4 of MIL-STD-1366, Interface Standard for Transportability Criteria, transport ships, and Appendix B of MIL-STD-1791, Designing for Internal Aerial Delivery in Fixed Wing Aircraft, for transport aircraft.)

3.1.1.1.1.30Pilots' sightlines, both forward and to thePilots' sightlines, both forward and to the side.

3.1.1.1.1.31Air Data System measurement probes (e.g., pitotAir Data System measurement probes (e.g., pitot probes, pitot-static probes, static ports, thermometers).

3.1.1.1.1.32SensorsSensors.

3.1.1.1.1.33AntennasAntennas.

3.1.1.1.1.34External lights (both illumination and navigation)External lights (both illumination and navigation).

3.1.1.1.1.35Wirecutter(s)Wirecutter(s).

3.1.1.1.1.36HoistsHoists.

3.1.1.1.1.37External cargo hook(s)External cargo hook(s).

3.1.1.1.1.38Chaff and flare dispensersChaff and flare dispensers.

3.1.1.1.1.39Kittable external stores support system(s), clearly delineatingKittable external stores support system(s), clearly delineating both A-kit and B-kit components.

3.1.1.1.1.40Boundary-layer control devices (e.g., vortex generators, strakesBoundary-layer control devices (e.g., vortex generators, strakes, fences, notches, diverters).

3.1.1.1.1.41CG location(s) for associated static turnover, tip-backCG location(s) for associated static turnover, tip-back, and tip-forward limits.

3.1.1.2Tabular Data

3.1.1.2.1AirframeTables associated with the engineering design data views shall include the following data as applicable.

3.1.1.2.1.1Horizontal and vertical projected frontal areasHorizontal and vertical projected frontal areas of the complete air vehicle and the following mutually exclusive components: fuselage, boom(s), sponsons, nacelle(s), pylon(s), rotor hub fairing(s), and propeller spinner(s).

3.1.1.2.1.2Wetted outer mold line areas ofWetted outer mold line areas of the complete air vehicle and the following mutually exclusive components: fuselage, boom(s), sponsons, nacelle(s), pylon(s), rotor hub fairing(s), and propeller spinner(s).

3.1.1.2.1.3Volume coefficients of empennage surfacesVolume coefficients of empennage surfaces.

3.1.1.2.1.4Volume coefficients of canard surfacesVolume coefficients of canard surfaces.

3.1.1.2.2Stability and Control DerivativesData IAW 2.11 shall be provided for hover and cruise in the Primary Mission configuration for SDGW and MGTOWs (if different), and at the allowable minimum Landing Gross Weight(s). (Configuration and weight definitions shall be as specified in the system performance specification, or in SAWE RP-7.) The methodology used to obtain the derivatives shall be described.

3.1.1.2.3Fuel TanksTables shall include the following data:

3.1.1.2.3.1Capacities of each integral/bladder fuel tankCapacities of each integral/bladder fuel tank.

3.1.1.2.3.2Capacities of each discrete fuel tankCapacities of each discrete fuel tank.

3.1.1.2.3.3Capacities of each auxiliary fuel tankCapacities of each auxiliary fuel tank (both fixed and removable).

3.1.1.2.3.4Minimum Fuel on Deck (MFOD) quantityMinimum Fuel on Deck (MFOD) quantity for each tank. (The MFOD is defined as the sum of the minimum fuel quantity per tank that will maintain continuous fuel pickup at the aircraft's allowable extreme hover/landing-maneuver pitch and roll attitudes, and the measurement uncertainty associated with the tank's fuel quantity gauging system. Note: MFOD as defined here is different from Unusable Fuel as documented in Weight Report submittals due to variability in aircraft trim attitude.)

3.1.1.2.4Mass PropertiesData IAW 2.11.1 above shall include mass properties data for the following configurations and weights as defined in the system performance specification, or in SAWE RP-7 otherwise:

3.1.1.2.4.1Primary Mission configurationPrimary Mission configuration.

3.1.1.2.4.2The configuration used to define StructuralThe configuration used to define Structural Design Gross Weight (SDGW).

3.1.1.2.4.3Configurations used to define allowable MaximumConfigurations used to define allowable Maximum Gross Takeoff Weights (MGTOW; e.g., vertical takeoff, running takeoff, shipboard takeoff).

3.1.1.2.4.4Allowable Maximum Landing Gross Weights (e.gAllowable Maximum Landing Gross Weights (e.g., vertical landing, run-on landing, shipboard landing).

3.1.1.2.4.5Allowable Minimum Landing Gross WeightsAllowable Minimum Landing Gross Weights.

3.1.1.2.4.6All other configurations that define allowableAll other configurations that define allowable limit weights during flight.

3.1.1.2.4.7The aircraft folded and stowed forThe aircraft folded and stowed for transport/storage.

3.1.2Developmental LevelIAW MIL-STD-31000, the Developmental Level subdivision is defined as a specific design approach, the fabrication of prototype materiel for test or experimentation, and limited production. Data shall include design maturity updates to Conceptual Level data items in addition to the following items:

3.1.2.1Air Vehicle Description

3.1.2.1.1Engineering Design DataData shall include the following:

3.1.2.1.1.1Layout views showing shapes and clearancesLayout views showing shapes and clearances of engine(s), motor(s), transmission(s), battery(s), fuel cell(s), internal armament, and any other major items.

3.1.2.1.1.2View(s) of the vehicle's wetted-outer-mold lineView(s) of the vehicle's wetted-outer-mold line surface that allow cross-section profile views to be extracted at points of significant changes in shape.

3.1.2.1.1.1Dimensions, Areas, and VolumesThe following items shall be clearly noted on the appropriate engineering design data entities:

3.1.2.1.1.1.1Projected frontal areas of theProjected frontal areas of the configuration from all orthographic directions.

3.1.2.1.1.1.2Areas for wetted surfacesAreas for wetted surfaces.

3.1.2.1.1.1.3Cargo compartment dimensionsCargo compartment dimensions.

3.1.2.1.1.1.4Usable cargo compartment floor areaUsable cargo compartment floor area.

3.1.2.1.1.1.5Volume of the crew compartmentVolume of the crew compartment.

3.1.2.1.1.1.6Volume of all avionics andVolume of all avionics and mission equipment compartments.

3.1.2.1.2Tabular Data

3.1.2.1.2.1Stability and Control DerivativesData IAW 2.11 above shall include the effects of variation of configuration/mode (e.g., tilting rotor or tail sitter aircraft in VTOL or cruise mode), GW, CG location, and control surface deflections.

3.1.2.1.2.2Stores Mass PropertiesData IAW 2.11.1 above shall include data for all stores that will be mounted in carriage on fixed aerodynamic surfaces IAW the system performance specification. Discrete entries shall include all allowable permutations where items may be expended by integer values (e.g., missile load-outs for missile launchers and rocket load-outs for rocket pods). Ranges of values shall be documented for items from which mass may be consumed (effectively) continuously (e.g., fuel from external fuel tanks and ammunition rounds from external gun pods).

3.1.2.2Structure Engineering DesignData shall include scaled (not isometric) cross-sectional views. The following details and dimensions shall be included in the views:

3.1.2.2.1Wing - StructuralWing - Structural box including: box chord and thickness along the span; typical cross sections showing flaps, ailerons, slats, etc., with control-surface hinge line pivots, actuator-to-control surface pivots, and actuator-to-base pivots locations marked; engine location and centroids; dimensions, areas, and center of mass for flaps, slats, ailerons, spoilers, etc., dimensions and areas for leading edge, trailing edge, major cutouts, etc.; fences, vortex generators, winglets; fold and production joints; materials used; and high-temperature areas, with design temperatures. Areas shall be shown in square feet and identified by cross hatching or other equivalent marking.

3.1.2.2.2Empennage/Canard - EngineeringEmpennage/Canard - Engineering design data and information compatible with wing requirements in 3.1.2.2.1 above.

3.1.2.2.3Rotor - HubRotor - Hub and hinge, including method of rotor attachment, typical cross section including any balance weight, structural box, rotor chord and thickness along the span. Blade area shall be expressed in square feet and identified by cross hatching or other equivalent marking.

3.1.2.2.4Fuselage, hull, andFuselage, hull, and booms - Primary and secondary structure including bulkheads, frames, longerons and stringers, major cutouts, flooring, major fittings and splices; pressurized area including volume, materials, and high-temperature areas, with design temperatures indicated. Fuel tank areas shall be cross hatched and capacities indicated, where not shown on a separate fuel system engineering design data view. Major cutouts, weapons bays, store provisions, engine, engine compartment, access doors, alighting gear support and cutout shall be marked and labelled.

3.1.2.2.5Nacelle - PrimaryNacelle - Primary and secondary structure. Details shall be compatible with wing and fuselage requirements in 3.1.2.2.1 above and 3.1.2.2.4 above.

3.1.2.2.6Air induction systemAir induction system - For purposes of clarity, details shall be included on either a separate engineering design data unit, on the fuselage engineering design data unit, or on the nacelle engineering design data unit. Inlet design, including spike, ramp, mechanisms, etc., shall be shown. Structural details of fixed and removable air filtration systems and inlet and exhaust infrared signature control devices shall be included.

3.1.2.2.7Alighting gear -Alighting gear - Main, nose, or tail, and auxiliary gear views shall detail the gear structure, rolling stock, retracting mechanism, attachment fittings, catapult, and arrest structure. Sizes and dimensions shall be included for the rolling stock, oleo, travel, wheel travel (where different from oleo travel), and strut length from axle to centerline trunnion.

3.1.2.3Propulsion System Engineering Design DataData shall include the following:

3.1.2.3.1Engine(s)Views showing location and shape, mounts, access provisions, intake attachment station, etc., unless shown on fuselage or nacelle structural engineering design data. Bleed or bypass ducts not shown on a basic air induction engineering design data. Condition Based Maintenance (CBM) / Health and Usage Monitoring Systems (HUMS) sensor locations.

3.1.2.3.2Electrical Drive Motor(s)View showing location and shape, mounts, wiring connections, access provisions.

3.1.2.3.3Fuel System

3.1.2.3.3.1View showing tank location(s), capacities, andView showing tank location(s), capacities, and shape(s), as well as location of the major distribution system components.

3.1.2.3.3.2Views showing MFOD quantity and definingViews showing MFOD quantity and defining aircraft hover/landing maneuver attitude(s) for each tank.

3.1.2.3.4Electrical Drive SystemViews showing generators; battery location(s), capacities, and shapes; the location of the major distribution system components; and motors.

3.1.2.3.5Drive System

3.1.2.3.5.1SchematicsA schematic representation of the complete drive system and mounting configuration on aircraft shall include:

3.1.2.3.5.1.1Gear boxes and supports. EachGear boxes and supports. Each gear box shall include representations for gears, bearings, shafts, housings, and supporting structure.

3.1.2.3.5.1.2Drive shafts and supports. InterconnectingDrive shafts and supports. Interconnecting shafting shall be shown with representations for bearings and flexible couplings.

3.1.2.3.5.1.3Any other rotating elements (e.gAny other rotating elements (e.g., bearings, cooling fans, etc.).

3.1.2.3.5.1.4CBM/HUMS sensor locations, from theCBM/HUMS sensor locations, from the point(s) where the engine output shaft(s) connect to the drive system, to the point(s) of final drive output.

3.1.2.3.5.2Tabular DataDrive system data shall include the following. Tabulated data shall be referenced back to the item shown on the relevant schematic. Nominal and limit values shall be specified for powers, torques, and shaft speeds.

3.1.2.3.5.2.1Power, torque, shaft speedPower, torque, shaft speed, gear ratios, and resonant frequencies shall be tabulated for gears, shafts, and housings of the drive system. Component data shall also include CBM/HUMS sensor function, manufacturer, and part number information.

3.1.2.3.5.2.2Gear boxes and supportsGear boxes and supports. Shaft speed and number of teeth per gear shall be tabulated for each gear. Bearing type, shaft speed, number of rolling elements, diameter of the rolling elements, pitch diameter, contact angle, and which race rotates shall be tabulated for each bearing. Gear and bearing data shall also include manufacturer and part numbers.

3.1.2.3.5.2.3Drive shafts and supportsDrive shafts and supports. Bearing type, shaft speed, number of rolling elements, diameter of the rolling elements, pitch diameter, contact angle, and which race rotates shall be tabulated for each bearing. Bearing data shall also include manufacturer and part numbers.

3.1.2.3.5.2.4Any other rotating elementsAny other rotating elements. The function of each element, rotational speed, and number of blades (if applicable) shall be tabulated. Bearing type, shaft speed, number of rolling elements, diameter of the rolling elements, pitch diameter, contact angle, and which race rotates shall be tabulated for each bearing. Element data shall also include manufacturer and part numbers.

3.1.2.4Equipment Engineering Design DataData shall include views that include locations of major component, and schematics that show the functional layout of flight control, avionics, mission equipment, CBM/HUMS, data bus(es), hydraulic, pneumatic, electrical, air conditioning, anti-icing, and Aircraft Survivability Equipment (ASE) groups.

3.1.2.5CAD Models

3.1.2.5.1CFD Surface GeometryDigital 3D shrink-wrap solid models of the wetted outer mold line for the complete air vehicle not including rotor, proprotor, propeller, or fan blades.

3.1.2.5.2CSM GeometryDigital CAD models shall include:

3.1.2.5.2.13D solid models of all unique3D solid models of all unique rotor, proprotor, propeller, and fan blades, including internal structure, for use in creating finite element method (FEM) meshes for 3D CSM simulations.

3.1.2.5.2.23D solid models of rotor hub3D solid models of rotor hub components, including internal structure, for use in creating FEM meshes for 3D CSM simulations.

3.1.2.5.2.3Two-dimensional (2D) models of the rotorTwo-dimensional (2D) models of the rotor blade cross-sections, including internal structure, for use in 2D sectional CSM analyses to calculate equivalent-beam properties.

3.1.3Production LevelThe Production Level subdivision is defined IAW MIL-STD-31000 as the procurement or production of an air vehicle for operational testing and fielding. Data shall include design maturity updates to Conceptual Level and Developmental Level data items.

3.2Rotor/Proprotor/Propeller/Fan Subsystem Aeromechanics DataData shall describe the rotor/proprotor/propeller/fan systems, and be divided into two categories: 1) Information that describes the total system, and 2) those properties that vary with blade radius. Radially-varying properties shall be described through plots and tables. Breakpoints for piecewise-linear sections shall be marked. Description of radially-varying properties shall progress outwards from the center of rotation to the blade tip. Three values of collective pitch (minimum, middle and maximum) shall be included to describe properties that vary with blade collective pitch. Properties that vary with operating mode (e.g., hover, cruise, climb/descent) shall be documented for each operating mode. Data shall be included for each unique system.

3.2.1Conceptual Level

3.2.1.1Commercial Item/Non-Developmental Item (CI/NDI) Propellers and Thrust-Producing FansThe following data shall be provided for third-party off-the-shelf propellers and thrust-producing fans that are to be installed onto the air vehicle without modification.

3.2.1.1.1Design DescriptionData shall include the Table IV data elements for each unique CI/NDI propeller and fan.

3.2.1.1.2Aerodynamic PerformanceCI/NDI propeller and fan performance data shall include either a Propeller Efficiency Chart or a Propeller Efficiency Table. The performance data shall present propeller efficiency factor, eta-p, as the dependent variable of independent variables standard nondimensional propeller power coefficient, CP, and standard nondimensional propeller advance ratio, J. The ranges of power coefficient and advance ratio shall cover the intended allowable operational envelope of the air vehicle.

3.2.1.2Rotor SystemData for each rotor, proprotor, propeller, and fan blade shall include the items listed in Table V. Inapplicable data items shall be omitted for developmental propeller and fan characteristics.

3.2.1.3Radial Distribution of Blade PropertiesData shall consist of the data included in Table VI for developmental articles. Items shall be omitted if invariant with radial location.

3.2.2Developmental LevelData shall include design maturity updates to Conceptual Level data items in addition to the following items:

3.2.2.1Rotor SubsystemData shall include the data listed in Table VII. The rotor subsystem data shall represent an accurate and consistent mathematical model of the design.

3.2.2.2Rotor Blade Engineering Design DataData shall include separate views of each unique rotor blade.

3.2.2.2.1Locations and DimensionsViews shall clearly note the following items in the relevant engineering design data:

3.2.2.2.1.1Value(s) of planform chord and twistValue(s) of planform chord and twist.

3.2.2.2.1.2Spanwise distribution of designated airfoil sectionsSpanwise distribution of designated airfoil sections, with transition zones clearly demarcated.

3.2.2.2.1.3Orientation of the designated airfoil section(s)Orientation of the designated airfoil section(s) with respect to (WRT) the rotor blade's spanwise axis shall be clearly marked to identify local angular rotations and linear translations required to define the geometric surface topology.

3.2.2.2.1.4The geometric treatment of surface topologyThe geometric treatment of surface topology transitions (flat-wrap, linear interpolation, etc.) between designated airfoil profiles shall be documented. (See Raymer, D. P., Aircraft Design, a Conceptual Approach, 5th ed., 2012, pp. 171-205 for additional details.)

3.2.2.3Rotor Hub

3.2.2.3.1Engineering Design DataData for each unique rotor hub region shall include views that define hub, blade, and control kinematic movement. The views shall include the following items:

3.2.2.3.1.1A vertical, longitudinal, and lateral referenceA vertical, longitudinal, and lateral reference axis system with respect to the fuselage.

3.2.2.3.1.2The location of the axis ofThe location of the axis of rotation for each hinge (actual or equivalent for rigid rotors), and the angle between the hinge-rotation axis and the reference axes.

3.2.2.3.1.3The angular range of rotation aboutThe angular range of rotation about each hinge axis (actual or equivalent for rigid rotors), and the angular location of blade-motion stops (as applicable).

3.2.2.3.1.4Both rotating and nonrotating swashplates, shownBoth rotating and nonrotating swashplates, shown perpendicular to the shaft (if applicable).

3.2.2.3.1.5The location of the centerline ofThe location of the centerline of each control link above the rotating swashplate, the length of each control link, and the angle between each control link and the reference axes (if applicable).

3.2.2.3.1.6The orientation of the blade's spanwiseThe orientation of the blade's spanwise axis with respect to the reference axes (i.e., rotor blade droop, sweep, coning, pretwist, etc.)

3.2.2.3.1.7The location and orientation of allThe location and orientation of all tension/compression and torsion spring and damper forces and torques.

3.2.2.3.1.8The location of all mechanical couplingThe location of all mechanical coupling points and the line of action of all forces through them.

3.2.2.3.1.9All rotor blade or hub mountedAll rotor blade or hub mounted vibration reduction device envelop and mounting interface definitions.

3.2.2.3.2Tabular DataTables shall include mass, moments of inertia, and stiffness and damping values for the following items. Stiffness and damping data shall include both tension/compression and torsion components. Data for all six translational and angular degrees of freedom shall be included for each item.

3.2.2.3.2.1Each hinge, coupling, joint, shank, shaftEach hinge, coupling, joint, shank, shaft, bearing, and any other mechanical components within the rotor hub. (Equivalent hinges for rigid rotors.)

3.2.2.3.2.2Each control system component, up toEach control system component, up to and including blade servo-flaps.

3.2.2.3.2.3Each blade-mounted passive vibration-reduction deviceEach blade-mounted passive vibration-reduction device.

3.2.2.3.3Graphical DataData shall include the following plots. Blade deflection limits/stops shall be demarcated on each plot.

3.2.2.3.3.1Position displacement as a function ofPosition displacement as a function of blade coning/flapping and lead-lag angular deflections for each spring and damper, including both tension/compression and torsion components.

3.2.2.3.3.2Tension/compression spring and damper forces asTension/compression spring and damper forces as a function of blade flap-wise and lead-lag-wise angular deflections for a representative selection of rotor speeds for each nonlinear damper.

3.2.2.3.3.3Torsion spring and damper torques versusTorsion spring and damper torques versus blade flap-wise and lead-lag-wise angular deflections for a representative selection of rotor speeds for each nonlinear damper.

3.2.2.4Radial Distribution of Blade PropertiesData shall include planform views that show radial variation of CG, aerodynamic reference point, shear center, tension center, pitch axis, and elastic axis. This data plus the data in Table VIII shall be documented in tables. The contractor shall describe the blade axis coordinate system. All parameters shall be measured with respect to this coordinate system.

3.2.2.5Blade Dynamic and Aeroelastic Modal Data

3.2.2.5.1Southwell (fan) plots of bladeSouthwell (fan) plots of blade resonant frequencies for fully-coupled modes showing the lowest 4Nb per revolution frequencies, including the effect of collective pitch. (Nb is defined as the number of blades per rotor). Rotor speeds shall include 0 r/min (for natural frequencies) through the maximum overspeed condition of the drive train.

3.2.2.5.2Mode shapes at design andMode shapes at design and power-on rotor rotational speed(s) for the modes identified in 3.2.2.5.1 above shall be plotted to show edgewise, flapwise, and torsional displacements for each mode shape. Descriptions shall include the method and assumed hub boundary conditions used in calculating these mode shapes.

3.2.2.5.3Mode shapes at minimum andMode shapes at minimum and maximum power-on and power-off rotor rotational speeds for the modes identified in 3.2.2.5.1 above shall be plotted to show edgewise, flapwise, and torsional displacements for each mode shape. Descriptions shall include the method and assumed hub boundary conditions used in calculating these mode shapes.

3.2.2.6Rotor Subsystem Material DataData shall include details on materials used in the rotor blade and hub components for 3D CSM analysis using the FEM, and 2D cross-sectional analysis in conjunction with the data described in 3.1.2.5.2 above.

3.2.2.7Rotor Blade Track and BalanceData shall include the data described in Table IX.

3.2.2.8Ground Resonance ModelData shall include items IAW Table X for the range of potential ground operating conditions. Data shall include vehicle inertia and main rotor speed for conditions of alighting-gear unloading of 0 to 99.99 percent airborne, in increments of 20 percent gear unloading. Definitions and discussion of these data shall be IAW National Advisory Committee for Aeronautics (NACA) Technical Report NACA-TR-1351. Blade damper properties shall be described over the allowable operational range of temperatures, frequencies, and amplitudes. Effective hub parameters shall be included for body modes with the largest structurally-significant resonant amplitudes. Data shall also include plots of tire/oleo stiffness and damping versus load.

3.2.3Production LevelData shall include design maturity updates to Conceptual Level and Developmental Level data items.

3.3Fixed Aerodynamic Surface Aeromechanics DataData for each non-rotating aerodynamic surface shall include the following.

3.3.1Conceptual Level

3.3.1.1GeometryData for each fixed aerodynamic surface (excluding rotor blades) shall include the items in Table XI.

3.3.1.2AerodynamicsData for each fixed aerodynamic surface (excluding rotor blades) shall include the items in Table XII.

3.3.2Developmental LevelData shall include design maturity updates to Conceptual Level data items, in addition to the following items:

3.3.2.1Engineering Design DataData shall include views showing separate planform layout for each unique fixed aerodynamic surface.

3.3.2.1.1Locations and DimensionsThe following items shall be clearly annotated on the appropriate views:

3.3.2.1.1.1Value(s) of planform chord, twist, sweepValue(s) of planform chord, twist, sweep, dihedral/anhedral, and the spanwise distribution of designated airfoil sections.

3.3.2.1.1.2Orientation of the designated airfoil section(s)Orientation of the designated airfoil section(s) WRT the fixed aerodynamic surface's spanwise-axis shall be clearly demarcated to identify local angular rotations and linear translations required to define the geometric surface topology.

3.3.2.1.1.3Spanwise distribution of designated airfoil sectionsSpanwise distribution of designated airfoil sections, with transition zones clearly demarcated.

3.3.2.1.1.4The geometric treatment of surface topologyThe geometric treatment of surface topology transitions (flat-wrap, linear interpolation, etc.) between designated airfoil profiles shall be documented. (See Raymer, D. P., Aircraft Design, A Conceptual Approach, 5th ed., 2012, pp. 171-205, for additional detail.)

3.3.2.1.1.5Spanwise variation in airfoil section aerodynamicSpanwise variation in airfoil section aerodynamic reference point.

3.3.2.1.1.6Spanwise variation in airfoil section centerSpanwise variation in airfoil section center of mass.

3.3.2.1.1.7Spanwise variation in the elastic axisSpanwise variation in the elastic axis.

3.3.2.1.1.8Spanwise variation in the tension centerSpanwise variation in the tension center (neutral axis).

3.3.2.2Spanwise Distribution of PropertiesAerodynamic and structural dynamics data shall consist of the data required by Table XIII. The contractor shall describe the blade axis coordinate system. All parameters shall be measured with respect to this blade axis coordinate system.

3.3.2.3AerodynamicsThe 3D lift, drag, and pitching moment coefficients (as a function of angle of attack and control surface (flap, aileron, slat, etc.) position) of each of the fixed aerodynamic surfaces shall be documented to include stall and any reasonable area of negative angle of attack operation of the surface (e.g., download in hover, vertical flight, etc.).

3.3.2.4Control Surface DescriptionData for each control surface shall include items as specified in Table XIV:

3.3.2.5Dynamic and Aeroelastic Modal DataData shall include the following:

3.3.2.5.1Natural frequencies and generalized modal massesNatural frequencies and generalized modal masses for structurally significant modes shall be tabulated. The associated mode shapes shall be plotted to show edgewise, flatwise, and torsional displacements of each mode shape. Documentation shall include a complete description of the method used, including all assumed boundary conditions, in calculating the mode shapes.

3.3.2.5.2Damping coefficient and variation in frequencyDamping coefficient and variation in frequency of each mode versus rotor speed and equivalent air speed shall be plotted.

3.3.2.5.3Outputs from dynamic and aeroservoelastic analysesOutputs from dynamic and aeroservoelastic analyses, including root locus plots, Bode plots, Nyquist plots, or other stability presentation forms.

3.3.3Production LevelData shall include design maturity updates to Conceptual Level and Developmental Level data items.

3.4Airfoil Aerodynamics

3.4.1Conceptual Level

3.4.1.1Aerodynamic PropertiesData at the Conceptual Level shall include conceptual design surrogate models of the sectional Cl, Cd, and Cm characteristics of each airfoil section as a function of Ma and Reynolds number, Re, in graphic or tabular form. The maximum Mach number (Mamax) for each airfoil section shall be determined by considering the specific application (e.g., rotor blade tip versus root, fixed aerodynamic surface, low speed (incompressible) aerodynamic environment, etc.). The minimum and maximum Reynolds number limits, (Remin and Remax, respectively) shall be based on the application(s) and the aerodynamic characteristics of the airfoil section (e.g., laminar flow airfoil, drag or stall characteristics significantly influenced by laminar-turbulent transition or shock-induced transition, small vehicle size, etc.) The range of alpha shall be prescribed by the application (e.g., 180 degrees to +180 degrees for regions of a rotor blade that experience reverse flow, or a wing that is subject to rotor downwash impingement; -20 degrees to +20 degrees for a tail surface not subject to rotor wake impingement, or a conventional fixed-wing aircraft; etc.) Coefficient Cm shall be referenced to the quarter chord location aft of the airfoil's leading edge. The surrogate models shall quantitatively describe the following relationships:

3.4.1.1.1Cl vs alpha for Ma = 0 toCl vs alpha for Ma = 0 to Mamax and Re = Remin to Remax

3.4.1.1.2Cd vs alpha for Ma = 0 toCd vs alpha for Ma = 0 to Mamax and Re = Remin to Remax

3.4.1.1.3Cm vs. alpha for Ma = 0 toCm vs. alpha for Ma = 0 to Mamax and Re = Remin to Remax

3.4.1.1.4Cd vs. cl for Ma = 0 toCd vs. cl for Ma = 0 to Mamax and Re = Remin to Remax

3.4.1.1.5Cm vs. cl for Ma = 0 toCm vs. cl for Ma = 0 to Mamax and Re = Remin to Remax

3.4.1.1.6DiscussionA narrative describing the conceptual design airfoil model shall be included, including the data basis for the model. The procedure by which the model was derived from the data basis shall be described. Details of any adjustments or optimizations made to the model in relation to the data basis shall be described.

3.4.2Developmental LevelData shall include design maturity updates to Conceptual Level data items in addition to the following items:

3.4.2.1Engineering Design DataData shall include views of each airfoil section used on the air vehicle IAW 2.7.1 above. The following items shall be shown on each view:

3.4.2.1.1Camber lineCamber line.

3.4.2.1.2Chord lineChord line.

3.4.2.1.3Aerodynamic center (Any range ofAerodynamic center (Any range of variation shall be demarcated, if applicable).

3.4.2.1.4Center of sectional massCenter of sectional mass.

3.4.2.1.5Tension center (neutral axis)Tension center (neutral axis).

3.4.2.1.6Shear center (flexural center)Shear center (flexural center).

3.4.2.1.7Torsion centerTorsion center.

3.4.2.1.8Elastic centerElastic center.

3.4.2.1.9Trailing-edge reflex angleTrailing-edge reflex angle.

3.4.2.1.10Trailing-edge trim tab deflection angleTrailing-edge trim tab deflection angle.

3.4.2.1.11Trailing-edge trim wedge angleTrailing-edge trim wedge angle.

3.4.2.2Airfoil Section 2D CAD2D CAD shrink-wrap models of each airfoil section used on the air vehicle IAW 2.7.2 shall be included in the report.

3.4.2.3AerodynamicsCoefficients Cl, Cd, and Cm of each airfoil section as a function of Ma and Re shall be described in graphic and tabular form. The data shall be representative of airfoil force and moment coefficients for two-dimensional flow at aerodynamic full-scale. Mamax for each airfoil section shall be determined by considering the specific application (e.g., rotor blade tip versus root, fixed aerodynamic surface, low speed (incompressible) aerodynamic environment, etc.). Remin and Remax shall be based on the application(s) and the aerodynamic characteristics of the airfoil section (e.g., laminar flow airfoil, drag or stall characteristics significantly influenced by laminar-turbulent transition or shock-induced transition, small vehicle size, etc.) Alpha shall be prescribed by the application (e.g., 180 degrees to +180 degrees for regions of a rotor blade that experience reverse flow, or a wing that is subject to rotor downwash impingement; -20 degrees to +20 degrees for a tail surface not subject to rotor wake impingement, or a conventional fixed-wing aircraft; etc.) Coefficient Cm shall be referenced to the quarter chord location aft of the airfoil's leading edge. The plots and tables should describe the following relationships:

3.4.2.3.1Cl vs. alpha for representative values of MaCl vs. alpha for representative values of Ma and Re,

3.4.2.3.2Cd vs. alpha for representative values of MaCd vs. alpha for representative values of Ma and Re,

3.4.2.3.3Cm vs. alpha for representative values of MaCm vs. alpha for representative values of Ma and Re,

3.4.2.3.4Cl vs. Ma and Re for representative valuesCl vs. Ma and Re for representative values of alpha,

3.4.2.3.5Cd vs. Ma and Re for representative valuesCd vs. Ma and Re for representative values of alpha,

3.4.2.3.6Cm vs. Ma and Re for representative valuesCm vs. Ma and Re for representative values of alpha,

3.4.2.3.7Cd vs. Cl for representative values of MaCd vs. Cl for representative values of Ma and Re, and

3.4.2.3.8Cm vs. Cl for representative values of MaCm vs. Cl for representative values of Ma and Re.

3.4.2.3.9DiscussionA complete description of the source of the data, including a description of any adjustments, shall be included. The procedure by which the data are obtained shall be described. Corrections shall include adjustments to data to account for Re effects such as geometrical scale differences, surface roughness, laminar-turbulent flow transition location and behavior; corrections for wind tunnel effects such as wall corrections; etc.

3.4.3Production LevelData shall include design maturity updates to Conceptual Level and Developmental Level data items.

3.5Airframe AeromechanicsData shall include the following for all normal modes of flight. The data shall be documented in the wind-axis coordinate system. The wind-axis coordinate system and force and moment sign conventions shall be described WRT the aircraft coordinate system. Coordinates for aerodynamic reference point(s) (point(s) at which aerodynamic forces and moments are defined to be acting) shall be documented. A complete description of the source of the data, including a description of any adjustments, shall be included. The procedure by which the data are obtained shall be described. Corrections shall include adjustments to data to account for Re effects such as geometrical scale differences, surface roughness, laminar-turbulent flow transition location and behavior; corrections for wind tunnel effects such as wall corrections; etc.

3.5.1Conceptual Level

3.5.1.1Fuselage AerodynamicsData shall include items IAW Table XV. For the purposes of this paragraph, the fuselage shall be defined in such a way as to exclude all items in 3.2 and 3.3 above. The characteristic dynamic pressures, areas, and length scales used for nondimensionalization shall be documented.

3.5.1.2Drag BuildupData shall include analysis of the drag of each component of the airframe from both the downward vertical direction for hover and vertical flight calculations, and from the longitudinal and lateral directions for yaw angles of 0 degrees (forward flight), +/-90 degrees (sideward flight), and 180 degrees (rearward flight). For purposes of this data, a component shall be any item on the air vehicle which contributes more than two percent of the total drag or that cannot be conveniently combined with another item. Drag from excrescences, surface roughness, leakage, interference, and scrubbing shall be included as separate items. Tabulated data shall include a list of the drag items, horizontal and vertical 3D nondimensional drag coefficients, CD, horizontal and vertical equivalent flat plate drag areas, and a description of the source of the drag estimate. The characteristic dynamic pressures and areas used for nondimensionaliztion of forces and calculation of equivalent flat plate drag areas shall be documented. Drag values shall not incorporate effects of rotor/propeller thrust recovery. Rotor/propeller thrust recovery factors used in performance calculations shall be itemized separately. Documentation shall include a description of the wake model used to substantiate interference predictions. A low-fidelity approximation of rotor wake velocities can be calculated by vector addition of twice the rotor's induced-inflow velocity from momentum theory and the freestream velocity. More sophisticated wake models may be used for interference calculations for increased fidelity.

3.5.2Developmental LevelData shall include design maturity updates to Conceptual Level data items in addition to the following items:

3.5.2.1Airframe AerodynamicsData shall include nondimensionalized aerodynamic forces and moments generated by the entire airframe (both excluding and including fixed aerodynamic surfaces) in graphic and tabular form. The characteristic dynamic pressure and length scales used in the nondimensionaliztion shall be described. The force and moment data shall include a matrix of yaw and pitch angles with a range to sufficiently cover the expected flight envelope that includes rotor/propeller wash aerodynamic interactions. The numerical methodology to be used to interpolate between data points shall be specified and described by the contractor. Drag values shall not incorporate effects of rotor/propeller thrust recovery. Rotor/propeller thrust recovery factors used in performance calculations shall be itemized separately. Documentation shall include a description of the rotor wake model used to substantiate interference predictions. A low-fidelity approximation of rotor wake velocities can be calculated by vector addition of twice the rotor's induced-inflow velocity from momentum theory and the freestream velocity. More sophisticated wake models may be used for interference calculations for increased fidelity.

3.5.2.2Component AerodynamicsData shall include airframe nondimensionized aerodynamic forces and moments generated with each of the major components removed separately, in graphic and tabular format. The characteristic dynamic pressure and length scales used in the nondimensionaliztion shall be described. The categorization of 'major components' is left to the discretion of the contractor. Items typically tested in a component buildup (e.g., fuselage, wings, stores, alighting gear, stabilizing surfaces) shall be sufficient for characterization. The force and moment data shall include a matrix of yaw and pitch angles with a range to sufficiently cover the expected flight envelope that includes rotor/propeller wash aerodynamic interactions. The numerical methodology to be used to interpolate between data points shall be specified and described by the contractor. Drag values shall not incorporate effects of rotor/propeller thrust recovery. Rotor/propeller thrust recovery factors used in performance calculations shall be itemized separately. Documentation shall include a description of the wake model used to substantiate interference predictions. A low-fidelity approximation of rotor wake velocities can be calculated by vector addition of twice the rotor's induced-inflow velocity from momentum theory and the freestream velocity. More sophisticated wake models may be used for interference calculations for increased fidelity.

3.5.2.3Airframe Structural DynamicsData shall include a description of the airframe structure. The operational configuration, weight, and loading shall be for the Primary Mission as specified in the contract.

3.5.2.3.1FEM ModelData shall include a FEM model of the aircraft airframe. Documentation shall include the following items associated with the model:

3.5.2.3.1.1Engineering design data views of theEngineering design data views of the model, including elements representing the fuselage, rotor pylons, empennage, wings, store support pylons, and stores, as applicable to the design.

3.5.2.3.1.2SL, BL, and WL coordinates forSL, BL, and WL coordinates for each node of each element.

3.5.2.3.1.3Mass and stiffness properties of eachMass and stiffness properties of each FEM element.

3.5.2.3.1.4Euler angle orientation of each FEMEuler angle orientation of each FEM element.

3.5.2.3.2Dynamic and Aeroelastic Modal DataData shall include a detailed FEM model of the airframe (including any fixed aerodynamic surfaces such as wings and stabilizers). Data shall also include all information required to replicate the following modal data:

3.5.2.3.2.1Generalized Masses, Frequencies, and DampingGeneralized masses, frequencies, and damping of each airframe mode up to 4Nb per revolution.

3.5.2.3.2.2Modal Displacements at Each Rotor HubModal displacements at each rotor hub employing six degrees of freedom at each mode (linear translations and angular rotations in a Cartesian coordinate system).

3.5.2.3.2.3Modal Displacements at Locations on the AirframeModal displacements at the following locations on the airframe:

3.5.2.3.2.3.1Pilot and co-pilot positionsPilot and co-pilot positions.

3.5.2.3.2.3.2Stores stationsStores stations.

3.5.2.3.2.3.3Points at which wing stabilizing surfacesPoints at which wing stabilizing surfaces and store support pylons are attached.

3.5.2.3.2.3.4Points at which vibration absorbers andPoints at which vibration absorbers and isolation devices are attached.

3.5.2.3.2.3.5Points at which narrow field ofPoints at which narrow field of regard sensor and illumination devices are attached.

3.5.2.3.2.3.6Selected points at which specified forcesSelected points at which specified forces may act (for example, forces to be used to simulate shake test or for other known excitations).

3.5.2.4Airframe-Mounted Absorbers and IsolatorsData shall include the following data for airframe-mounted absorbers and isolators:

3.5.2.4.1The stiffness, mass, and damping propertiesThe stiffness, mass, and damping properties for vibration devices such as airframe-mounted absorbers, isolators and hub-mounted absorbers.

3.5.2.4.2The SL, BL, and WL coordinatesThe SL, BL, and WL coordinates for the points of connection of vibration devices to the airframe.

3.5.2.4.3Engineering design data views that clearlyEngineering design data views that clearly define the specific configuration and installation of all vibration absorption and isolation devices.

3.5.3Production LevelData shall include design maturity updates to Conceptual Level and Developmental Level data items.

3.6Control Subsystem

3.6.1Conceptual Level

3.6.1.1General DesignData shall include a general description of the flight control system (FCS) concept (e.g., digital optical, electrical (digital and/or analog), mechanical, hydraulic, pneumatic). The description shall include details of the various modes of operation and the theory of operation. The description shall include details of any unusual or difficult design features and problems. The description of stability augmentation systems (SAS) and stability augmentation control systems (SCAS) shall include the type of system (e.g. fly-by-wire, fly-by-light, electrical, mechanical), type of augmentation (e.g. electronic, fluidic, hybrid), augmentation modes, anticipated redundancy, control authority limits, sensors, servos, and rotor and control surface implementation(s).

3.6.2Developmental LevelData shall include design maturity updates to Conceptual Level data items in addition to the following items:

3.6.2.1Control TravelData for control travel and sign convention IAW Table XVI shall be included. Contractor Furnished Information (CFI) is used here for situations where units are design dependent. Equivalent quantities may be required for applications such as the flight controls for an unmanned air vehicle (UAV) that does not use sticks, pedals, levers, etc. (NOTE: Rotor blade feathering angles are defined as theta-f = theta-0 - theta-1c cos psi - theta-1s sin psi, measured at the 75% rotor radius station of the blade.)

3.6.2.2Control Subsystem DescriptionThe technical description of the total control subsystem shall include the following:

3.6.2.2.1Type of system: Linkage descriptionType of system: Linkage description (e.g., digital optical, electrical (digital and/or analog), mechanical, hydraulic, pneumatic), boost system, trim system, backup control system(s), level of augmentation (i.e., SAS, SCAS, etc.), unique or nonstandard features (e.g., control mixing and nonlinearities such as actuator rate, electronic amplifier saturation, and actuator position limits).

3.6.2.2.2A description of any interfacesA description of any interfaces between the flight control computer(s) and control-actuating mechanisms, to include type(s) of data bus(es).

3.6.2.2.3A detailed algebraic representation ofA detailed algebraic representation of mechanical control system dynamics, to include mass and stiffness properties and nonlinear effects such as friction and hysteresis.

3.6.2.2.4Augmentation system: Axes augmented, typeAugmentation system: Axes augmented, type of hardware (mechanical, electrical, fluidic, hybrid), type of augmentation (e.g., rate command, attitude command, use of feed forward and feedback loops), actuator functional installation (e.g., parallel, series), actuator type (e.g., electrical, electro-hydraulic), augmentation modes and the methodology used for activating and selecting (switching) modes, authority limits, sensors.

3.6.2.2.5Cockpit/Control station controls: Configuration (e.gCockpit/Control station controls: Configuration (e.g., conventional, side-arm), control travels, pilot/operator station arrangement (e.g., side-by-side, tandem, staggered).

3.6.2.2.6Method and description of rotor-controlMethod and description of rotor-control mechanization (e.g., Individual Blade Control (IBC), swashplate/swashplate-type (rise-and-fall, collective-sleeve, etc.)).

3.6.2.2.7Description of the coupling betweenDescription of the coupling between rotor-shaft tilt and control inputs (for applicable configurations).

3.6.2.2.8Descriptions of any rotor-to-rotor controlDescriptions of any rotor-to-rotor control couplings (e.g., differential cyclic, main-rotor collective to tail-rotor collective).

3.6.2.2.9An algebraic/kinematic model of theAn algebraic/kinematic model of the relationship between the cockpit/control station controls and any fixed aerodynamic surfaces linked to them, along with a brief description of any augmentation systems.

3.6.2.2.10Details of inceptor force -Details of inceptor force - displacement and frequency response characteristics for all operational modes of active control inceptors.

3.6.2.2.1LinkagesData shall describe control linkages between the cockpit/control-station and the ultimate control-actuating mechanism(s) in each of the following formats:

3.6.2.2.1.1Block diagram(s) to include: cockpit/control-stationBlock diagram(s) to include: cockpit/control-station controls; bungee springs; force-feel systems (including break-out forces and gradients); control system stiffnesses, control mixing; boost/AFCS servos; devices to transfer controls between fixed and rotating systems (e.g., swashplate, electrical slip ring, hydraulic/pneumatic rotary union); rotor-blade-control mechanisms (e.g., pitch link and horn, servo-flap/-tab); fixed-aerodynamic-surface control mechanisms (e.g., flap, aileron, slat, brake, elevator, rudder, stabilator); rotor-shaft tilt mechanisms; engine-nacelle tilt mechanisms; sensors which drive servos; pylon coupling; control inputs from augmentation systems in the rotating frame (e.g., stabilizer bar, control gyro); and non-unity gearing in the control-linkage servos and resulting rotor-blade feathering angles.

3.6.2.2.1.2Algebraic representation of items inAlgebraic representation of items in the block diagram(s), particularly transfer functions for: control mixing; augmentation systems; control linkages; sensors; servos; non-unity gearing; and stabilization or control augmentation loops.

3.6.2.3Engine Fuel Control DescriptionData that describes the operation of the engine fuel control system shall include:

3.6.2.3.1A block diagram of the engineA block diagram of the engine fuel control system, along with an algebraic representation of each component of the system.

3.6.2.3.2Definition of partial- or full-authority electronicDefinition of partial- or full-authority electronic fuel control shall include a description of input and output interface parameters, control loops (including speed control, feed-forward compensation, and torque output limiting), gains, and time constants.

3.6.2.3.3A description of any interfaces betweenA description of any interfaces between the flight control computer(s) and the engine(s), to include type of data bus(es).

3.6.2.4AFCS Digital ModelData as follows shall be included, along with an AFCS algorithmic model:

3.6.2.4.1Timing delays due to sensorTiming delays due to sensor nonlinearities, management and transfer of sensor data to/from the AFCS, and AFCS computational processing.

3.6.2.4.2Interface Definition: A listing ofInterface Definition: A listing of all AFCS input and output parameters, with a description of each parameter's function, variable type, and engineering units.

3.6.2.4.3Data Files: Files with initializationData Files: Files with initialization parameters, gains, and time constants that are accessed by the AFCS algorithmic model.

3.6.2.5Aircraft Configuration/Trim MethodologyData shall include the following items.

3.6.2.5.1A description of any automatedA description of any automated aircraft configuration and trim schemes implemented by the control system. This shall include scheduled trim targets, aircraft configuration states (e.g., wing sweep, engine speed scheduling, transmission speed scheduling, rotor tilt scheduling, rotor stop-and-fold, tail-sitter conversion between takeoff, cruise, and alighting modes), control mixing to achieve desired lift and thrust, drag minimization, etc.

3.6.2.5.2A general control system layoutA general control system layout or series of layouts showing rotors, control surfaces, engine(s), actuation systems, feel systems, pilot's controls, and control panel organization. Illustrations of means of providing redundancy and emergency provisions. Layouts including wiring schematics for all electrical and electronic portions of the FCS, and attendant electrical, hydraulic, and pneumatic power inputs to the FCS. Data bus type(s) shall be identified on the wiring schematics.

3.6.2.5.3Block diagrams of the FCSBlock diagrams of the FCS, including: transfer or describing functions; identified normal control paths; redundancy; manual overrides; emergency provisions; and location and type of sensors and control devices used.

3.6.2.5.4Mathematical models of the FCSMathematical models of the FCS, the unaugmented aircraft, and any other data required to simulate FCS operation during steady and maneuvering flight for calculation of rotor and control surface trim settings, engine shaft speed, rotor shaft speed(s) and tilt(s), jet thrust, and any other design-specific component used to exert control over aircraft flight behavior.

3.6.3Production LevelData shall include design maturity updates to Conceptual Level and Developmental Level data items.

3.7Propulsion and Drive Subsystem

3.7.1Conceptual Level

3.7.1.1Engine Performance DescriptionDocumentation shall include uninstalled minimum specification engine static performance data IAW 2.15 above.

3.7.1.1.1Commercial Item/Non-Developmental Item (CI/NDI) EnginesDocumentation shall be IAW 3.8.1.3 below for CI/NDI third-party off-the-shelf engine(s) integrated onto the air vehicle.

3.7.1.2Air Induction and Exhaust System LossesData shall include inlet ram pressure recovery efficiency and power losses such as: engine inlet air filtration; particle separation; and inlet and exhaust infrared and acoustic signature suppression. Documentation shall include detailed descriptions of any variation of losses with air vehicle operating condition if required for flight performance analysis (e.g., selectable particle filter bypass, active signature controls).

3.7.1.3Drive System Power Take-Off Requirements and LossesData shall include descriptions of all power take-off (PTO) requirements and losses occurring between engine output shaft(s) and rotor shaft(s), clearly identified as 'generator losses,' 'accessory losses,' 'drive system losses,' 'anti-torque branch losses,' 'propulsor branch losses,' and all other significant power sinks as necessary for clarity. Documentation shall include a description of any variation of losses with each associated air vehicle operating condition when necessary for the analysis of air vehicle flight performance.

3.7.1.4Drive System Shaft Speed SchedulingData shall include a description of drive system shaft speed scheduling as a function of flight condition. Documentation shall also include the ratio of speed controlled by variable speed engine(s) versus variable speed transmission(s) as a function of flight condition. Data shall include table(s) of engine and transmission output shaft speed as a function of flight condition.

3.7.2Developmental LevelData shall include design maturity updates to Conceptual Level data items in addition to the following items:

3.7.2.1Engine Performance DescriptionData describing engine performance shall include:

3.7.2.1.1An engine cycle model that satisfiesAn engine cycle model that satisfies the documentation requirements of Society of Automotive Engineers, International, Aerospace Standard SAE AS681, Gas Turbine Engine Performance Presentation for Computer Programs.

3.7.2.1.2A model of the engine electronicA model of the engine electronic fuel controller in electronic format, including: input files of gains; time constants and initialization parameters that are accessed by the model; and a listing of all input and output parameters, with a description of each parameter's function, variable type and engineering units.

3.7.2.1.3A description of engine instrumentation, includingA description of engine instrumentation, including measurements of temperatures, pressures, flows, and vibrations.

3.7.2.1.4Descriptions of engine inlet temperature riseDescriptions of engine inlet temperature rise and engine performance degradation due to hot gas ingestion from: recirculated engine exhaust during hover-in-ground-effect; and rocket and missile launches (single through ripple launches).

3.7.2.2Engine Thermodynamic DescriptionData that describe engine thermodynamic and dynamic responses shall include:

3.7.2.2.1A block diagram of engine componentsA block diagram of engine components (inlet, duct, compressor, combustor, turbine stages, and exhaust), along with an algebraic representation for each component of the block diagram. Documentation shall include one-dimensional thermodynamic equations, tables, or maps used to quantify the quasi-steady flow, pressure, temperature, or power (as appropriate) for each system component. SAE AS755, Aircraft Propulsion System Performance Station Designation, is recommended as guidance for standardized nomenclature.

3.7.2.2.2Transfer functions that approximate the lagTransfer functions that approximate the lag in dynamic response of key engine parameters, such as gas generator speed, power turbine speed and power turbine output shaft torque, to fuel flow.

3.7.2.3Engine and Drive Train DynamicsData shall include a block diagram of the engine(s) and drive train components, along with an algebraic representation (rotating moment of inertia, stiffness, resonance frequency, and output shaft speed(s)) of each component of the block diagram).

3.7.2.4Drive System Torque/Power LimitsData for torque/power limits shall include MCP, IRP, MRP, and CRP IAW 2.15 above for the following drive system components, on a per-item basis:

3.7.2.4.1Uninstalled engine mechanical limit(s)Uninstalled engine mechanical limit(s).

3.7.2.4.2Installed engine output shaft limit(s)Installed engine output shaft limit(s).

3.7.2.4.3Rotor shaft limit(s)Rotor shaft limit(s).

3.7.2.4.4Intermediate drive system component limitsIntermediate drive system component limits of sufficient detail to identify performance limiters for discrete flight states.

3.7.3Production LevelData shall include design maturity updates to Conceptual Level and Developmental Level data items.

3.8Substantiating Documentation for Data Verification and ValidationAll Air Vehicle Technical Description data shall be categorized as either Basic Description Data or Derived Data for the purpose of documenting data verification and validation.

3.8.1Basic Description DataBasic Description Data shall consist of either physical dimensions under the direct control of the designer, well-documented properties of common materials (e.g., Young's Modulus for 2024-T6 aluminum), or model specification data for NDI/CI (e.g., commercial or government-furnished propellers or engines that are integrated into a developmental item).

3.8.1.1Substantiating Documentation for Basic Description DataSubstantiation may be included either through reference to documents otherwise available to the United States Government with Government Purpose Rights (GPR) or less data restrictions, or attached as appendices with contractually-specified Data Markings IAW DFARS 252.227-7013(f). Substantiating documentation with data rights more restrictive than GPR shall be segregated into stand-alone annexes with contractually-specified Data Markings IAW DFARS 252.227-7013(f). Substantiating documentation with security classification markings higher than the Air Vehicle Technical Description Report shall be segregated into stand-alone annexes with contractually-specified Data Markings.

3.8.1.2Substantiating Documentation of Engineering Design DataDocumentation substantiating validation of engineering design data as accurate, adequate, and complete for its intended use(s) IAW MIL-STD-31000 shall be appended to the Report.

3.8.1.3Type Certificate Data Sheet (TCDS) and Supplemental Type Certificate (STC)Basic Description Data shall also include applicable design TCDSs and STCs for Commercial Item/Non-Developmental Item (CI/NDI) rotorcraft, aircraft, unmanned aircraft systems, propellers, and engines that have been certificated by aviation regulatory authorities (e.g., United States Federal Aviation Administration (FAA), European Aviation Safety Agency (EASA)). A copy of the contemporaneous TCDSs and STCs applicable to the proposed design shall be attached to the Air Vehicle Technical Description Report as appendices.

3.8.2Derived DataDerived Data shall consist of any properties of the proposed design which are the result of physical laws acting on the design (e.g., aerodynamic force and moment data, structural stiffness and damping, composite material stress-strain behavior, etc.).

3.8.2.1Substantiating Documentation for Derived DataSubstantiating documentation for Developmental Level and Production Level Derived Data shall be included in the report either through reference to documents otherwise available to the United States Government with GPR or less data restrictions, or attached as appendices to the report with contractually-specified Data Markings IAW DFARS 252.227-7013(f). Substantiating documentation with data rights more restrictive than GPR shall be segregated into stand-alone annexes with contractually-specified Data Markings IAW DFARS 252.227-7013(f). Substantiating documentation with security classification markings higher than the Air Vehicle Technical Description Report shall be segregated into stand-alone annexes with contractually-specified Data Markings.

3.8.2.2Substantiating Documentation for Experimental DataSubstantiating documentation for data derived from experiments (including flight tests) shall include both qualitative and quantitative descriptions of data acquisition processes, associated measurement uncertainties, and assessments of uncertainty propagation for any subsequent calculations required to generate reported data. The term measurement uncertainty is used here as described in industry standards ASME PTC 19.1 and ASME PTC 19.22. The term uncertainty propagation is used here as described in industry standards ISO/IEC Guides 98-1 through 98-4.

3.8.2.3Substantiating Documentation for Computer-Aided Engineering (CAE) DataCAE is used here as the subset of Modeling and Simulation (M&S) that includes first-principles-based computational physics and engineering, such as CFD, comprehensive aeroelastic analysis, CSM, CEA, etc. Verification and Validation processes and uncertainty quantification for CAE-based analyses are used here as described in industry standards AIAA G-077, ASME V&V 10, ASME V&V 10.1, ASME V&V 20, and SAE J 2940.

3.8.2.3.1Substantiating Documentation for CAE ToolsSubstantiating documentation for data calculated by CAE tools shall include documentation of software and computational hardware sufficient for data traceability and assurance in the event of discovery of technical bugs (e.g., the 1994 Intel Pentium central processing unit (CPU) Floating Point Division (FDIV) bug). Substantiating system documentation shall include:

3.8.2.3.1.1Identification of software tools by productIdentification of software tools by product name, version name and number(s), and developer/publisher,

3.8.2.3.1.2Identification of the computer system usedIdentification of the computer system used to execute the software, including identification of hardware (including model and generation of the CPU(s), and graphical processing unit(s), (GPU).

3.8.2.3.1.3Identification of the operating systems andIdentification of the operating systems and utility software, including identification by developer/publisher, specific product name, and version name and number(s).

3.8.2.3.1.4Description of any modified stock softwareDescription of any modified stock software or internally-developed software, to include qualitative and quantitative details of the V&V processes used to assure correct software functionality and applicability of the software for calculation of the Derived Data.

3.8.2.3.2Substantiating Documentation for CAE ModelsSubstantiating documentation for data derived from CAE models shall include descriptions of the models, sources and quality of data used to create the models, and qualitative and quantitative details of the V&V processes used to assure appropriateness and applicability of the numerical models for calculation of the Derived Data.

3.8.2.3.3Substantiating Documentation for CAE SimulationsSimulation as used here describes the exercise of the CAE model by the CAE tool to calculate the Derived Data. Substantiating documentation for data derived from CAE simulations shall include a detailed description of the how the simulation was exercised, and quantitative assessments of numerical uncertainty for the Derived Data.