1、Designation: F3011 13Standard Specification forPerformance of Angle of Attack System1This standard is issued under the fixed designation F3011; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year of last revision. A number in
2、parentheses indicates the year of last reapproval. Asuperscript epsilon () indicates an editorial change since the last revision or reapproval.1. Scope1.1 This performance specification covers simple systemsthat provide angle-of-attack information to a pilot, aircraft, orother systems.NOTE 1More com
3、plex AoA systems can be addressed in annexes inthe future.1.2 In this performance specification, functional operationand minimum performance requirements for an angle-of-attacksystem are established.1.3 The values stated in SI units are to be regarded asstandard. No other units of measurement are in
4、cluded in thisstandard.1.4 This standard does not purport to address all of thesafety concerns, if any, associated with its use. It is theresponsibility of the user of this standard to establish appro-priate safety and health practices and determine the applica-bility of regulatory limitations prior
5、 to use.2. Referenced Documents2.1 RTCA Standard:2DO-160E Environmental Conditions and Test Proceduresfor Airborne Equipment3. Terminology3.1 Definitions:3.1.1 angle of attack, AoA, nacute angle between anaircrafts wing chord, wing mean chord, or other definedaircraft longitudinal axis, and the dire
6、ction of the relative freestream wind.3.1.2 AoA system, ncollection of components used toprovideAoAinformation to the pilot, aircraft, or other systems.3.1.2.1 DiscussionThis may include simple or complexsystems, depending on the intended use.4. General Requirements4.1 Product IdentificationOne of t
7、he major components ofan AoA system, shall be labeled with the following informa-tion:4.1.1 Part Number,4.1.2 Serial Number, and4.1.3 Manufacturers Name.4.2 Operating ConditionsThe system manufacturer shallspecify the following limitations for proper function:4.2.1 The angular operational range of t
8、he system,4.2.2 Voltage operating range (min/max), if applicable,4.2.3 Electrical load specifications, if applicable, and4.2.4 Restrictions regarding the use and application ofdeicing fluids with the system, if applicable.4.3 Installation ManualThe manufacturer of the AoAsystem shall provide an inst
9、allation manual that specifies thefollowing information so that an installer can determineappropriate use for an aircraft installation:4.3.1 A full description of the intended function of thesystem,4.3.2 An explicit compliance statement to this standard,Specification F3011,4.3.3 The operation limita
10、tions (including the items in 4.2,Operating Conditions),4.3.4 The environmental conditions (including items inSection 6, Environmental Requirements),4.3.5 Installation and calibration instructions required forsafe, accurate, and proper operation of all intended functions ofthe system, and4.3.6 Instr
11、uctions for Continued AirworthinessThe manu-facturer of the AoA system shall provide continued airworthi-ness procedures necessary to ensure safe and accurate opera-tion (calibration, alignment to aircraft, maintenance, etc.).4.4 Users ManualThe manufacturer of the AoA systemshall provide a users ma
12、nual that specifies:4.4.1 The functional operation of the system (includingitems in Section 5, Functional Requirements).4.5 It is permissible that the Installation and User Manual beone physical document so long as it clearly delineates the twosections.1This test method is under the jurisdiction of
13、ASTM Committee F39 on AircraftSystems and is the direct responsibility of Subcommittee F39.03 on Design ofAvionics Systems.Current edition approved July 1, 2013. Published July 2013. DOI: 10.1520/F3011-13.2Available from RTCA, Inc., 1150 18th St., NW, Suite 910, Washington, DC20036.Copyright ASTM In
14、ternational, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States15. Functional Requirements5.1 Basic OperationThe manufacturer shall clearlyspecify the functional characteristics of the system including:5.1.1 The resolution of the AOA indication over the speci-fied ra
15、nge. The resolution may vary over the range. The statedresolution need not be in degrees but may be in units consistentwith the indication (for example, percent of green band,number of LEDs, degrees, percent of full scale, etc.).5.1.2 The minimum accuracy of the AOA indication overthe specified rang
16、e. The accuracy may vary over the range. Forthe purposes of this standard, fluctuating indication is permis-sible in the indicated AoA information so long as it does notcreate misleading indication.5.1.3 The range of sideslip angles for which specificationsabove are valid.5.1.4 These characteristics
17、 shall be verified by test of arepresentative system. This test need not consider the effects ofinstallation on an aircraft and may be done in a wind tunnel, onan aircraft, or other testing device.5.2 Stall IndicationIf the system indicates a stall, thesystem shall clearly and intuitively indicate t
18、he approach, ortrend, to critical AOA, considering use of color, size ofindication, and other human factors aspects as applicable.5.3 Startup of Electronically Driven SystemsIf an AoAsystem is electronically driven, it shall meet all performancerequirements within 3 min of power application unless t
19、hesystem suppresses the indication, or clearly indicates an invalidindication, until performance requirements are met.5.4 Accessibility of ControlsAdjustments not normallymade during flight (for example, setup, calibration, etc.) shallnot be accessible from the top-level user interface (that is, the
20、remust be a menu or special entry that requires a deliberate actionto enter setup mode).5.5 SoftwareIf the system uses software, it shall functionas described in the systems user manual. The softwareconfiguration shall be controlled by the manufacturer. Therevision level shall reside on, or in, the
21、product such that a usercan view it.6. Environmental Requirements6.1 The system shall meet the following parameters speci-fied by the manufacturer:6.1.1 Operating Temperature RangeThe temperaturerange that the system correctly functions and is not adverselyaffected at standard pressure.6.1.2 Storage
22、/Survival Temperature RangeThe tempera-ture range across which the system is exposed and notpermanently damaged.6.1.3 Operating Humidity RangeThe non-condensing hu-midity range at standard temperature and pressure that thesystem correctly functions, and is not adversely affected.6.1.4 Operating Alti
23、tude RangeThe altitude range that thesystem correctly functions and is not adversely affected atstandard temperature.6.1.5 Operating Airspeed RangeThe airspeed range thatthe system correctly functions and is not adversely affected.6.1.6 PrecipitationThe precipitation conditions for whichthe system p
24、roperly functions and is not adversely affected. Ata minimum, the system shall correctly function and not beadversely affected during flight through rain.6.2 IcingThe system shall not be permanently damagedwhen icing occurs on system components that are designed tobe exposed to environments external
25、 to the aircraft.6.3 Deicing FluidsIf deicing fluids are permitted by themanufacturer, the system shall not be negatively affected by theuse of deicing fluids or the application of these fluids frompressure sprayers.6.4 Emissions of RF EnergyThe system shall not be thesource of objectionable interfe
26、rence, under operating condi-tions at any frequencies used on aircraft.6.4.1 The performance levels in DO-160E (or later), Section21.0, Category M, for conducted and radiated RF emissionsmeet the requirements above.6.5 Electrical Power InputIf the system uses electricalpower from the aircraft, it sh
27、all function throughout the entirevoltage operating range specified by the manufacturer.6.6 Power Input Abnormal Surge VoltageIf the systemuses direct current (dc) electrical power from the aircraft, itshall pass the following:6.6.1 With the equipment operating at its maximum operat-ing voltage, app
28、ly to the positive (dc) input lead voltage surgesof two times maximum operating voltage 0/+5 % Vdc for 100ms. The rise time shall be less than or equal to 1 ms and the falltime shall be less than or equal to within 5 ms. Apply eachvoltage surge three times at 10-s, or less, intervals. Followingthis
29、test, the system shall operate normally.6.6.2 The required surge voltages as measured at the inputterminals of the unit under test (UUT) shall be achievedregardless of the required surge current.7. Keywords7.1 aircraft; angle-of-attack system; AoAF3011 132ASTM International takes no position respect
30、ing the validity of any patent rights asserted in connection with any item mentionedin this standard. Users of this standard are expressly advised that determination of the validity of any such patent rights, and the riskof infringement of such rights, are entirely their own responsibility.This stan
31、dard is subject to revision at any time by the responsible technical committee and must be reviewed every five years andif not revised, either reapproved or withdrawn. Your comments are invited either for revision of this standard or for additional standardsand should be addressed to ASTM Internatio
32、nal Headquarters. Your comments will receive careful consideration at a meeting of theresponsible technical committee, which you may attend. If you feel that your comments have not received a fair hearing you shouldmake your views known to the ASTM Committee on Standards, at the address shown below.
33、This standard is copyrighted by ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959,United States. Individual reprints (single or multiple copies) of this standard may be obtained by contacting ASTM at the aboveaddress or at 610-832-9585 (phone), 610-832-9555 (fax), or serviceastm.org (e-mail); or through the ASTM website(www.astm.org). Permission rights to photocopy the standard may also be secured from the ASTM website (www.astm.org/COPYRIGHT/).F3011 133
