ASTM F2910-2014 Standard Specification for Design and Construction of a Small Unmanned Aircraft System &40 sUAS&41 《小型无人航空器系统40 sUAS41设计和制造用标准规范》.pdf

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1、Designation: F2910 14Standard Specification forDesign and Construction of a Small Unmanned AircraftSystem (sUAS)1This standard is issued under the fixed designation F2910; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year of

2、 last revision. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon () indicates an editorial change since the last revision or reapproval.1. Scope1.1 This specification defines the design, construction, andtest requirements for a small unmanned aircraft system(sUAS).

3、1.2 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 to use.2. Referenced D

4、ocuments2.1 ASTM Standards:2F2908 Specification for Aircraft Flight Manual (AFM) for aSmall Unmanned Aircraft System (sUAS)F2909 Practice for Maintenance and Continued Airworthi-ness of Small Unmanned Aircraft Systems (sUAS)F2911 Practice for Production Acceptance of a Small Un-manned Aircraft Syste

5、m (sUAS)F3002 Specification for Design of the Command and Con-trol System for Small UnmannedAircraft Systems (sUAS)F3003 Specification for Quality Assurance of a Small Un-manned Aircraft System (sUAS)F3005 Specification for Batteries for Use in Small Un-manned Aircraft Systems (sUAS)3. Terminology3.

6、1 Definitions of Terms Specific to This Standard:3.1.1 continued safe flight, na condition whereby a UA iscapable of continued safe flight, possibly using emergencyprocedures, without requiring exceptional pilot skill. Uponlanding some UA damage may occur as a result of a failurecondition.3.1.2 laun

7、ch and recovery load, nthose loads experiencedduring normal launch and recovery of the UA.3.1.3 limit load, nthose loads experienced in the normaloperation and maintenance of the UA.3.1.4 manufacturer, nentity responsible for assembly andintegration of components and subsystems to create a safeopera

8、ting sUAS.3.1.5 permanent deformation, na condition whereby a UAstructure is altered such that it does not return to the shaperequired for normal flight.3.1.6 propulsion system, nconsists of one or more powerplants (for example, a combustion engine or an electric motorand, if used, a propeller or ro

9、tor) together with the associatedinstallation of fuel system, control and electrical power supply(for example, batteries, electronic speed controls, fuel cells, orother energy supply).3.1.7 small unmanned aircraft system, sUAS, ncomposedof the small unmanned aircraft (sUA) and all required on-boards

10、ubsystems, payload, control station, other required off-boardsubsystems, any required launch and recovery equipment, andcommand and control (C2) links between the sUA and thecontrol station. For purposes of this standard sUAS is synony-mous with a small Remotely Piloted Aircraft System (sRPAS)and sU

11、Ais synonymous with a small Remotely PilotedAircraft(sRPA).3.1.8 structural failure, na condition whereby the struc-ture is not able to carry normal operating loads.3.1.9 supplier, nany entity engaged in the design andproduction of components (other than a payload which is notrequired for safe opera

12、tion of the sUAS) used on a sUAS.3.1.9.1 DiscussionWhere the supplier is not themanufacturer, the supplier can only ensure that the componentscomply with accepted consensus standards.3.2 Shall versus Should versus MayUse of the word“shall” implies that a procedure or statement is mandatory andmust b

13、e followed to comply with this standard, “should”implies recommended, and “may” implies optional at thediscretion of the supplier, manufacturer, or operator. Since“shall” statements are requirements, they include sufficientdetail needed to define compliance (for example, threshold1This specification

14、 is under the jurisdiction of ASTM Committee F38 onUnmannedAircraft Systems and is the direct responsibility of Subcommittee F38.01on Airworthiness.Current edition approved Jan. 15, 2014. Published January 2014. DOI: 10.1520/F2910-14.2For referenced ASTM standards, visit the ASTM website, www.astm.o

15、rg, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStandards volume information, refer to the standards Document Summary page onthe ASTM website.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States1values, test

16、methods, oversight, reference to other standards).“Should” statements are provided as guidance towards theoverall goal of improving safety, and could include onlysubjective statements. “Should” statements also represent pa-rameters that could be used in safety evaluations, and couldlead to developme

17、nt of future requirements. “May” statementsare provided to clarify acceptability of a specific item orpractice, and offer options for satisfying requirements.4. Applicability4.1 This standard is written for all sUAS that are permittedto operate over a defined area and in airspace authorized by anati

18、ons governing aviation authority (GAA). It is assumed thata visual observer(s) will provide for the sense-and-avoidrequirement to prevent collisions with other aircraft and thatthe maximum range and altitude at which the sUAS can beflown at will be specified by the nations GAA. Unlessotherwise speci

19、fied by a nations GAA this standard appliesonly to UA that have a maximum takeoff gross weight of 55lb/25 kg or less.5. Requirements5.1 General:5.1.1 The sUAS shall be designed and constructed to meetsUAS limitations and performance capabilities required by thenations GAA.5.1.2 The sUA shall be desi

20、gned and constructed so that themaximum level flight speed cannot exceed the maximumairspeed authorized by the nations GAA. In addition, themaximum level flight airspeed should not exceed an airspeedthat would prevent the sUAfrom remaining within the confinesof the defined operational area without e

21、xcessive maneuveringor exceptional pilot skill.5.1.3 The sUAS shall be designed using appropriate andreasonable engineering design and verification techniques. Testshall be conducted in accordance with section 5.11 to verifythat the design requirements have been satisfied and the resultsof the tests

22、 recorded and available for future reference.5.1.4 The sUAS shall be designed and constructed toinitialize in a known, safe state when power is applied.5.1.5 The sUA should be designed and constructed tominimize the likelihood of fire, explosion, or the release ofhazardous chemicals, materials, and

23、flammable liquids orgasses, or a combination thereof, in flight or in the event of acrash, hard landing, or ground handling mishap. This includes,but is not limited to: containing the fire if the sUA crashes;protecting first responders from hazards at the crash site; use offlame resistant materials;

24、 suppression of in-flight fires; andprotection against battery-induced fires.5.1.6 During the design process, the manufacturer shalldetermine the permissible range of weight and positions of thecenter of gravity of the sUA. The sUA shall then be designedand constructed to ensure that the center of g

25、ravity remainswithin this permissible weight and range for all intendedpayloads, fuel, batteries, and other onboard items. If removing/adding ballast is permitted, the sUAS aircraft flight manualshall include instructions with respect to loading, marking, andsecuring of removable ballast and ensurin

26、g the center ofgravity remains within limits that can be controlled by thecontrol system and ensures adequate aerodynamic stability.The aircraft flight manual shall have a method to verify orcalculate CG location.5.1.7 During the design process, the manufacturer shalldetermine the maximum takeoff gr

27、oss weight and minimumoperational empty weight for the sUA.5.1.8 The sUAS should be designed and constructed tominimize injury to persons or damage to property duringoperation.5.1.8.1 Designs that use exposed, rigid sharp structuralobjects should be minimized. For those systems that mighthave compon

28、ents capable of causing injury due to misuse ormishandling, a warning/caution statement should be added tothe aircraft flight manual alerting the crew to the risk.5.1.8.2 The sUA shall be designed so that the sUA willremain controllable and predictable or capable of performing asafe recovery maneuve

29、r in the event of asymmetric deploymentof any single, normal control surface as well as high-lift/dragdevices (trailing edge flaps, leading edge flaps or slats, spoilers,flaperons, and the like).5.1.9 The sUA shall be designed and constructed so that allfasteners will remain secure over the operatio

30、nal and environ-mental range of flight conditions.5.1.10 The sUA should be designed and constructed so thatit is possible to determine quickly that all doors, panels, andhatches that can be opened are secured before takeoff.5.1.11 ConstructionIn addition to construction require-ments specified above

31、:5.1.11.1 The sUAS should incorporate materials that havethe strength, corrosion resistance, and durability characteristicsappropriate to the application in the design.5.1.11.2 Energy absorbing structure should be used wher-ever possible.5.1.11.3 Material strength design properties should be basedon

32、 analysis or testing, or both, determined by the manufacturer/supplier that confirms these material strength design propertieshave been achieved. Documentation of this analysis or testing,or both, should be recorded and available at either themanufacturers or suppliers location (as appropriate) for

33、futurereference.5.2 Structure:5.2.1 The sUA structure shall be designed and constructedso that:5.2.1.1 The structure will not fail at 1.5 times the limitloads. This shall be verified either through analysis or testing asdetermined by the manufacturer/supplier.5.2.1.2 Binding, chafing, or jamming of

34、controls do notoccur at 1.5 times the limit load threshhold. This shall beverified by test.5.2.1.3 The structure can withstand limit loads and launchand recovery loads without permanent deformation.5.2.2 The sUA and systems required for continued safeflight shall be designed and constructed to be ca

35、pable ofsupporting flight loads predicted by analysis or flight test to beencountered throughout the proposed flight envelope to includeatmospheric gusts or evasive maneuvering loads, or both.5.2.3 The sUA and systems required for continued safeflight shall be designed and constructed to withstand n

36、ormalF2910 142landing impact loads without damage that would affect safetyof flight of subsequent flights unless it can be maintained,repaired, and inspected as per procedures that will ensurecontinued safe operation.5.2.4 The manufacturer shall develop and provide instruc-tions to ensure any damage

37、 caused by shipping or handling areidentified prior to flight. These instructions should normally bepart of the pre-flight inspection procedures in the aircraft flightmanual but may be included in other instructions as deemednecessary by the manufacturer.5.3 Propulsion:5.3.1 The propulsion system (i

38、ncluding batteries for electricpower plants) shall be designed and constructed to:5.3.1.1 Operate throughout the flight envelope,5.3.1.2 Conform to the installation instructions provided bythe propulsion system supplier, and5.3.1.3 Have a positive means to cut off ignition or fuel flowboth in-flight

39、 and on the ground.5.3.2 Propulsion system controls and displays at the controlstation shall be designed and constructed to be adequate tocontrol the propulsion system safely under all operatingconditions as determined by the manufacturer or the enginesupplier, or both. Examples include:5.3.2.1 Abil

40、ity to be able to observe whether engine is on oroff (corroborated by multiple sensors).5.3.2.2 Ability to command the engine off quickly.5.3.2.3 Ability to have a multi-step safeguard in turning theengine on or off.5.3.2.4 Vital engine instruments as determined by the manu-facturer or engine suppli

41、er/manufacturer, or both, as necessaryto properly control the engine such as: fuel flow and pressure,RPM, manifold pressure, carburetor icing detector, exhausttemperature, and cylinder head temperature for combustionengines and current, temperature, etc for electric propulsion (orother parameters ap

42、plicable to the propulsion system design).NOTE 1May not be applicable for rotorcraft or manually controlledsUAS using simple model aircraft radio control equipment.5.3.3 Propellers:5.3.3.1 All propellers should be non-metallic.5.3.3.2 Propellers (both fixed and variable pitch) should bedesigned to h

43、ave adequate structural strength.5.3.3.3 Provisions shall be made to ensure that the propul-sion system shaft and propeller rotational speed do not exceedthe value specified by the supplier.5.3.4 The propulsion system should be designed to mini-mize failure for reasons other than insufficient fuel o

44、r electricalpower and to support normal operations throughout the antici-pated lifecycle of the system or until reaching themanufacturer/supplier-determined inspection or replacementinterval.5.3.5 Fuel and Oil SystemsFor sUA using a combustionpropulsion system:5.3.5.1 The fuel and oil systems shall

45、be designed andconstructed to be capable of supplying fuel and oil to the powerplant throughout the entire flight envelope at the required rateand pressure specified by the propulsion system supplier;5.3.5.2 The fuel and oil systems shall be designed so thatthere is a means of determining the amount

46、 of fuel and oil onboard when the UA is on the ground, whether via internal sUAsystems or external means;5.3.5.3 Piping, fittings, valves, O-rings, and gaskets usedshall be resistant to deterioration caused by fuel, oil, andlubricating grease;5.3.5.4 Each fuel system and oil system shall be designed

47、 tobe able to withstand 1.5 limit loads; and5.3.5.5 Each fuel system (excluding bladder type systems)shall be designed so that it is vented to the atmosphere and canbe drained when the aircraft is on the ground.5.3.6 CoolingNot all sUA require a cooling system.However, if one is necessary the follow

48、ing requirements apply:5.3.6.1 The cooling system shall be designed and con-structed to ensure adequate cooling of the power plant at thehighest ambient temperatures expected during maximum climbrate and cruise operations of the sUA.5.3.6.2 The cooling system should be designed and con-structed so t

49、hat any air induction system filters can beinspected, serviced, or replaced, or a combination thereof, aspart of routine maintenance as specified by the manufacturer.5.3.6.3 Where necessary to maintain a safe operatingtemperature, naturally aspirated cooling shall be supplementedby an appropriate cooling method.5.3.7 The exhaust system shall be designed and constructedto ensure that hot exhaust gases do not impinge directly onnearby unprotected surfaces.5.3.8 For combustion engine power plants, the system shallinclude:5.3.8.1 An ignition switch incorporated into