1、Designation: F2911 141Standard Practice forProduction Acceptance of Small Unmanned Aircraft System(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 revision, the year of last re
2、vision. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon () indicates an editorial change since the last revision or reapproval.1NOTECorrected title editorially in March 2014.1. Scope1.1 This standard defines the production acceptance require-ments for a small unma
3、nned aircraft system (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 concern
4、s, 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 Documents2.1 ASTM Standards:2F2585 Specification for Design and Perform
5、ance ofPneumatic-Hydraulic 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, Co
6、nstruction, and Test 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.
7、1 manufacturer, nentity 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
8、to meet this standard.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, electroni
9、c speed controls, fuel 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
10、 control (C2) links 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 compon
11、ents (other than a 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
12、” implies that a procedure 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 t
13、o define compliance (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 b
14、e used in safety evaluations, and couldlead to development of future requirements. “May” statements1This test method 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, 20
15、14. Published January 2014. DOI: 10.1520/F2911-14E01.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStandards volume information, refer to the standards Document Summary page onthe ASTM website.Copyrigh
16、t ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States1are 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
17、operate over a defined 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
18、 be specified by the nations 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 co
19、nsensus standards at the 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 supp
20、lier shall include a declarationthat 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
21、 consensus standards. 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 as
22、sembled in accordance 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 there
23、quirements specified in 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
24、 shall beavoided.5.1.2.2 Assembly practicesConsistent, accepted practicesand assembly using materials such as epoxy, CAcements, 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 airfr
25、ame which conforms to 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, t
26、hread locking adhesives,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:
27、5.1.3.1 Motor/engine 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
28、 manufacturer/supplier 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
29、F3005 shall apply.5.1.4 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
30、 meet functional-ity 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 powersyst
31、ems (batteries, generators, 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 typepa
32、yloads shall be specified 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 res
33、ult in a gross weight 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 cons
34、umption orin-flight offloaded 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 syst
35、ems that are impacted 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 par
36、ts or material, those changesshall be documented in an engineering change order (ECO)F2911 1412using manufacturers normally accepted format andprocessing/storage procedures.5.1.6 Ground Support Equipment:5.1.6.1 Control stationThe control station may be assimple as a commercial off the shelf transmi
37、tter or as complexas a 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 specifi
38、cations of thesystem design 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 verificatio
39、n shall include verificationof 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
40、 complex as a bungee, 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 d
41、oes not introduce errors 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 envel
42、opespecified by manufacturer 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 maint
43、ained and to provide objective 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 s
44、pecification, thesUAS 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
45、.7.4.(1) Engineering designThe 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. Desig
46、nmodifications required 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
47、 and repeatability of 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, comp
48、onents, andassemblies) 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 th
49、e manufac-turers location 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 validationAformal 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 Pr
