1、Designation: F2911 14Standard Practice forDesign and Production/Building of Multiple Copies of SmallUnmanned Aircraft Systems (sUAS)1This standard is issued under the fixed designation F2911; the number immediately following the designation indicates the year oforiginal adoption or, in the case of r
2、evision, the year of 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 standard defines the production acceptance require-ments for a small unmanned aircraft syste
3、m (sUAS).1.2 This standard is applicable to sUAS that comply withdesign, construction, and test requirements identified in Speci-fication F2910. No sUAS may enter production until suchcompliance is demonstrated.1.3 This standard does not purport to address all of thesafety concerns, if any, associat
4、ed 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 Documents2.1 ASTM Standards:2F2585 Specification for Design and Performance ofPneumatic-Hy
5、draulic Unmanned Aircraft System (UAS)Launch SystemF2908 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)F2910 Specification for Design, Construction, and Tes
6、t of aSmall Unmanned Aircraft System (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. Terminology3.1 Definitions of Terms Specific to This Standard:3.1.1 manufacturer, nen
7、tity responsible for assembly andintegration of components and subsystems to create a safeoperating sUAS. The builder of kit built systems provided bya manufacturer must conform to the manufacturers assemblyand test instructions without deviation in order for that kit-builtsystem to meet this standa
8、rd.3.1.2 propulsion system, nconsists of one or more powerplants (for example, a combustion engine or an electric motorand, if used, a propeller or rotor) together with the associatedinstallation of fuel system, control and electrical power supply(for example, batteries, electronic speed controls, f
9、uel cells, orother energy supply).3.1.3 small unmanned aircraft system, sUAS, ncomposedof the small unmanned aircraft (sUA) and all required on-boardsubsystems, payload, control station, other required off-boardsubsystems, any required launch and recovery equipment, andcommand and control (C2) links
10、 between the UA and thecontrol station. For purposes of this standard sUAS is synony-mous with a small Remotely Piloted Aircraft System (sRPAS)and sUAis synonymous with a small Remotely PilotedAircraft(sRPA).3.1.4 supplier, nany entity engaged in the design andproduction of components (other than a
11、payload which is notrequired for safe operation of the sUAS) used on a sUAS.3.1.4.1 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 pr
12、ocedure or statement is mandatory andmust be 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
13、 (for example, thresholdvalues, test 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 ev
14、aluations, and couldlead to development of future requirements. “May” statementsare provided to clarify acceptability of a specific item orpractice, and offer options for satisfying requirements.1This test method is under the jurisdiction of ASTM Committee F38 onUnmannedAircraft Systems and is the d
15、irect responsibility of Subcommittee F38.01on Airworthiness.Current edition approved Jan. 15, 2014. Published January 2014. DOI: 10.1520/F2911-14.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStandards
16、 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 States14. Applicability4.1 This standard is written for all sUAS that are permittedto operate over a defined
17、 area and in airspace defined by anations 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 a sUAS can be flownwill be specified by the n
18、ations GAA. Unless otherwisespecified by a nations GAA this standard applies only to UAthat have a maximum take off gross weight of 55 lb/25 kg orless.5. Requirements5.1 Production:5.1.1 General:5.1.1.1 The manufacturer is responsible for a product thatcomplies with accepted consensus standards at t
19、he time ofdelivery and is demonstrated as fit and safe for flight. ForsUAS assembled from components provided by a supplier, thesupplier shall provide detailed instructions to the manufacturerconcerning the assembly and test of those components. Thecomponents supplied by a supplier shall include a d
20、eclarationthat the components have been designed and manufactured inaccordance with an accepted consensus standard and that thecomponents, when assembled, tested, and maintained in accor-dance with the suppliers instructions, meet the safety stan-dards implied by the applicable consensus standards.
21、If re-quired by a nations GAA, the manufacturer/supplier shall alsocomply with any requirements for compliance with any appli-cable technical standard orders for specific components orsystems, or both.5.1.1.2 The manufacturer is responsible for ensuring that thesUAS has been assembled in accordance
22、with the componentsuppliers instructions and complies with Specification F2910.5.1.1.3 Compliance with Quality Assurance StandardQuality assurance shall be exercised across production inaccordance with Specification F3003.5.1.2 StructuresUAS airframe structures shall meet therequirements specified i
23、n Specification F2910. sUAS structuresusing materials that have no applicable certified materialcharacteristics shall be demonstrated to be suitable for themission involved.5.1.2.1 Material procurementComponents used shall beconsistent and uncontrolled variation or substitution shall beavoided.5.1.2
24、.2 Assembly practicesConsistent, accepted practicesand assembly using materials such as epoxy, CA cements, shallbe applied in accordance with product suppliers data sheets forsafety and acceptable results.5.1.2.3 ToolingMolds, tooling, and jigs shall be used thatproduce an airframe which conforms to
25、 the engineering designin terms of part fit, assembly tolerances, defect size, and otherrequirements documented in the design.5.1.2.4 Fastening and joiningMechanical componentssuch as fittings, pushrods, rotor structures and fittings shall beproperly secured using safety wire, thread locking adhesiv
26、es,crimping, welding or other effective means of restrainingmechanical components.5.1.2.5 LubricationWhere lubrication of fittings is used,the manufacturer shall ensure that the lubricant used is appro-priate to the application, thermal range and predicted load.5.1.3 Propulsion:5.1.3.1 Motor/engine
27、mountingConsistent, accepted prac-tices and assembly using materials such as epoxy, CA cements,and the like shall be applied in accordance with productsuppliers data sheets for safety and acceptable results.5.1.3.2 SecurityMotor/engine/propeller mounting shall beverified to meet manufacturer/supplie
28、r specified torque levelsand security.5.1.3.3 Dynamic balancingPrior to installation, propellersor rotors or rotor blades shall be statically and dynamicallybalanced per design specification.5.1.3.4 Propulsion batteriesFor electric propulsionsystems, provisions in Specification F3005 shall apply.5.1
29、.4 SystemsSystems that can be shown not to be im-pacted by, or to impact on, other subsystems may be demon-strated independent of all-up functional verification of systems.For example, a launch sub system that has no interface with theflight control system may be demonstrated to meet functional-ity
30、with an airframe or a dummy airframe.5.1.5 Payload:5.1.5.1 PhysicalPayload(s) shall be mounted in the man-ner specified by the sUAS design or manufacturers instruc-tions (or both) with attention given to proper shock andvibration attenuations. Current draw from primary powersystems (batteries, gener
31、ators, and so forth) shall be verifiedduring production and functionality of circuit protection andfusing shall also be verified. If the manufacturer allowspayloads to be installed post-production, then specific require-ments for the design installation, and test of these typepayloads shall be speci
32、fied in the aircraft flight manualdeveloped in accordance with Specification F2908 or themaintenance and continued airworthiness documentation de-veloped in accordance with Practice F2909. Maximum safegross weight of the system shall be determined and payloadweight shall not result in a gross weight
33、 that exceeds maximumdetermined safe gross weight.5.1.5.2 Effect on CG locationPayloads shall be located asspecified by the sUAS designer and center of gravity for eachaircraft shall be verified with payload installed. This shallinclude center of gravity changes due to fuel consumption orin-flight o
34、ffloaded payloads, or both.5.1.5.3 Accountability for system design changesNochange in physical location of components may be madewithout engineering definition of the impact of such change onflight performance or electronic or electrical compatibility ofcommand and control systems that are impacted
35、 by suchchange. Where a change in systems performance is predictedfor such physical change, the change shall be validated toascertain that system functionality will remain within specifi-cation limits. When such changes are made to accommodateissues such as unavailability of parts or material, those
36、 changesshall be documented in an engineering change order (ECO)using manufacturers normally accepted format andprocessing/storage procedures.5.1.6 Ground Support Equipment:F2911 1425.1.6.1 Control stationThe control station may be assimple as a commercial off the shelf transmitter or as complexas a
37、 mobile shelter complete with control displays, C2 linkreceivers, warning devices, recording equipment, batterycharging, independent electrical power and so forth. Whateverthe production system, it shall be demonstrated as part ofproduction acceptance to comply with the specifications of thesystem d
38、esign and integration and suppliers specifications forthe equipment used. The requirement is to ensure a consistent,known configuration that does not introduce errors in operationof the sUAS that can lead to degradation of the system or sUASflight safety. Production verification shall include verifi
39、cationof the product for each control station produced to ensure thatthe sUAS will be controlled as required to comply with sUASoperational standards consistently.5.1.6.2 Launch and recovery systems (if required)Thelaunch and recovery system may be as simple as hand launchor as complex as a bungee,
40、pneumatic or hydraulic launcher.Whatever the production system, it shall be demonstrated tocomply with the specifications of the system design andintegration and suppliers specifications for the equipment used.The requirement is to ensure a consistent, known configurationthat does not introduce erro
41、rs in operation of the sUAS that canlead to system degradation, crew safety or sUAS flight safety.Production verification shall include verification of the productfor each launch and recovery system produced to ensure thatthe sUAS will be launched safely within the launch envelopespecified by manufa
42、cturer If applicable the launch system shallmeet the requirements of F2585.5.1.7 System Level:5.1.7.1 Configuration management planThe sUAS manu-facturer shall develop a configuration management plan toensure that a standard configuration for each sUAS is estab-lished and maintained and to provide o
43、bjective evidence ofproduction conformance to specifications and continued effec-tiveness of the quality management system.5.1.7.2 Product specificationThe sUAS characteristicsshall be documented in a product specification in the manu-facturers normal accepted format. In this specification, thesUAS
44、standard configuration shall be defined to provide a basisfor product verification testing.5.1.7.3 Product verification planA product verificationplan shall be developed to ensure the following activities areincluded in the formal verification testing of the sUAS requiredin 5.1.7.4.(1) Engineering d
45、esignThe production of the sUAS shallbe based on the standard configuration report and releasedengineering data (that is, drawings, processes, specifications,and so forth) in the manufacturers normal accepted format thatare specifically associated with that configuration. Designmodifications require
46、d to meet production contingencies shallbe documented in an ECO for that change and the change shallbe identified by serial number block.(2) Assembly instructionsAppropriate assembly instruc-tions in the manufacturers normal accepted format shall beused to assure the uniformity and repeatability of
47、productionprocesses.(3) ToolingTooling appropriate to the sUAS design shallbe used to assure control of critical dimensions and therepeatability of production from unit to unit.(4) Material inspectionManufacturers shall ensure thatsuppliers of material items (raw material, components, andassemblies)
48、 are in compliance with consensus standards forthose material items. Incoming materials and equipment to beinstalled in the sUAS shall be inspected for proper configura-tion and quality of workmanship before their use. Inspectionsmay be performed at the suppliers location or the manufac-turers locat
49、ion or both.(5) In-process inspectionWhen appropriate, subassem-blies of the sUAS shall be inspected (for proper configurationand quality of workmanship) before installation into the nexthigher assembly. Production plans shall delineate product flowwith appropriate in-process inspection points identified.5.1.7.4 Design validationA formal validation of the sUAScomponent or system design shall be performed by the sUASsupplier or manufacturer in accordance with requirements inSpecification F2910.5.2 System Level Production Acceptance:5.2.1
