ASTM F3322-2018 Standard Specification for Small Unmanned Aircraft System (sUAS) Parachutes.pdf
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1、Designation: F3322 18Standard Specification forSmall Unmanned Aircraft System (sUAS) Parachutes1This standard is issued under the fixed designation F3322; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year of last revision. A
2、 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 covers the design and manufacturerequirements for deployable parachutes of small unmannedaircraft (sUA). This speci
3、fication defines the design,fabrication, and test requirements of installable, deployableparachute recovery systems (PRS) that are designed to beintegrated into a sUA to lessen the impact energy of the systemshould the sUA fail to sustain normal stable safe flight.Compliance with this specification
4、is intended to support anapplicant in obtaining permission from a civil aviation author-ity (CAA) to fly a sUA over people.1.2 This specification is applicable to the design,construction, and test of deployable parachute recovery sys-tems that may be incorporated into the system or structure, orboth
5、, of sUA seeking civil aviation authority (CAA) approvalin the form of technical standard orders (TSO), flightcertificates, flight waivers, flight permits, or other like docu-mentation.1.3 UnitsThe values stated in inch-pound units are to beregarded as the standard. The values given in parentheses a
6、remathematical conversions to SI units that are provided forinformation only and are not considered standard.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
7、, health, and environmental practices and deter-mine the applicability of regulatory limitations prior to use.1.5 This international standard was developed in accor-dance with internationally recognized principles on standard-ization established in the Decision on Principles for theDevelopment of In
8、ternational Standards, Guides and Recom-mendations issued by the World Trade Organization TechnicalBarriers to Trade (TBT) Committee.2. Referenced Documents2.1 Federal Standards:214 CFR Part 107 Small Unmanned Aircraft SystemsMIL-STD-1629A Procedures for Performing a FailureMode, Effects, and Critic
9、ality Analysis3. Terminology3.1 Definitions of Terms Specific to This Standard:3.1.1 abstain, vbefore starting a particular test method,the unmanned aircraft (UA) manufacturer or designated opera-tor shall choose to enter the test or decline to perform the testand any abstention shall be granted bef
10、ore the test begins.3.1.1.1 DiscussionThe test form shall be clearly markedas such, indicating that the manufacturer acknowledges theomission of the performance data while the test method wasavailable at the test time.3.1.2 acceptable entanglement, ninteraction of the para-chute canopy, risers, or l
11、ines with the sUA that does not reducethe effectiveness of the parachute recovery system.3.1.3 applicant/proponent, nperson or organization re-sponsible for seeking the approval to operate and operating asmall unmanned aircraft (sUA).3.1.3.1 DiscussionThe applicant/proponent may be one ofthe followi
12、ng entities: manufacturer, operator, or originalequipment manufacturer (OEM).3.1.4 autonomous triggering system, ATS, ndevice orcomponents independent from any flight critical system of thesUA that will detect and initiate parachute deployment upondetection of a critical failure of the sUA in flight
13、.3.1.5 ballistic ejection, nejection of the parachute recov-ery system into free air with the use of springs, pyrotechnic gasgenerators, or the use of inert gases or compressed air.3.1.5.1 DiscussionHazardous materials laws (for airtransportation, for proper handling, storage, etc.) may apply1This s
14、pecification is under the jurisdiction of ASTM Committee F38 onUnmannedAircraft Systems and is the direct responsibility of Subcommittee F38.01on Airworthiness.Current edition approved Sept. 1, 2018. Published September 2018. DOI:10.1520/F3322-18.2Available from U.S. Government Printing Office, Supe
15、rintendent ofDocuments, 732 N. Capitol St., NW, Washington, DC 20401-0001, http:/www.access.gpo.gov.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United StatesThis international standard was developed in accordance with internationally recognized
16、 principles on standardization established in the Decision on Principles for theDevelopment of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.1when using hazardous materials such as pyrotechnic devices,cold gas g
17、enerators, or compressed CO2for a ballistic para-chute.3.1.6 bill of materials, BOM, nspecific list of all compo-nents defined by this specification that make up the parachuterecovery system.3.1.7 canopy filling/inflamation time, ntime from canopy(line) stretch to the first full open canopy position
18、.3.1.8 critical number motor failure, CNMF, nnumber ofmotors required to remove a sUA from stable flight. Thesubject motors shall be adjacent to one another in cases inwhich more than one motor is being tested. In the case of anodd number of motors, the number of “failure” motors shall berounded up
19、to the next even number. If the integrator candemonstrate that the sUA being tested with the PRS needs tohave thrust cut from more motors than defined in the examplebelow in order to remove the aircraft from stable flight it is upto the integrator to define the number of motors to reachCNMF. Refer t
20、o Section 6 for testing.Examples ofCNMF4 Rotor 6 Rotor 8 RotorImmediate Lossof Thrust on aminimum of oneor more motorsImmediate Lossof Thrust on aminimum twoadjacent motorsImmediate Lossof Thrust on aminimum ofthree adjacentmotors3.1.9 declaration of compliance, nmechanism for thor-ough self-assessm
21、ent and validation of compliance with thisspecification in which specific reporting or testing protocols arenot listed.3.1.9.1 DiscussionThe integrator will keep documentationto support any declarations of compliance. The followinginformation shall be retained on file at the manufacturersfacility fo
22、r as long as systems remain in service: (1) technicaldata that defines the parachute recovery systems installation inthe aircraft; (2) technical data that define the components,assemblies, and fabrication of the system; and (3) engineeringanalyses and test data prepared for qualification with thissp
23、ecification.3.1.10 demonstration, na practical exhibition of how thePRS or components, or both, work.3.1.11 descent rate, nfinal steady state rate of decreasingvertical altitude of the sUA at sea level conditions.3.1.11.1 DiscussionIt shall be noted that horizontal speedand the calculation of horizo
24、ntal impact should be consideredbased on the worst-case scenario but for the purpose of thisspecification it is not used as a determining factor. Thehorizontal impact can be influenced by the construction ordeconstruction of the combination of wind or the pendulumeffect, or both, both of which are g
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