ASTM F3322-2018 Standard Specification for Small Unmanned Aircraft System (sUAS) Parachutes.pdf

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

25、reatly affected by thedirection of travel and orientation of the sUA in relation to thePRS during deployment.3.1.12 energy measurement, nKinetic energy is calculatedas: KE = 1/2 mv2. Whereas “m” equals sUAs takeoff mass and“v” equals descent speed.3.1.13 entanglement, nunintended physical interactio

26、n ofthe parachute risers, lines, or canopy with the sUA during aPRS deployment that compromises the functionality and effec-tiveness of the PRS.3.1.14 flight-critical system, nsystem that, should it fail,will cause the sUA to no longer maintain stable flight.3.1.15 flight envelope, nrange of combina

27、tions of speed,direction of travel, altitude, roll, angle of attack, and so forthwithin which the sUA is able to be safely operated withoutexceeding its structural design load factor.3.1.16 flight termination system, FTS, ndevice or compo-nents that will disable the propulsion system of the sUA.3.1.

28、17 forebody, nobject connected to the parachutecanopy and accompanying drogue chutes, if applicable.3.1.17.1 DiscussionThe forebody shall be considered thesUA with any additional attachments (that is, parachute de-ployment system, payload, electronics, propellers, and soforth).3.1.18 full power fail

29、ure/full power cut, nsudden andimmediate loss of power function to the critical flight systemsof the sUA such as motors, electronic speed controllers (ESC),and avionics.3.1.18.1 DiscussionThrottling down the motors is not thesame as a full power cut in a test as the former gives theoperator control

30、and advance knowledge that loss of stableflight is going to occur.3.1.19 inspection, ntechnique based on visual or dimen-sional examination of an element; inspection is generallynondestructive and typically includes the use of sight, hearing,smell, touch, and taste, simple physical manipulation, mec

31、hani-cal and electrical gauging, and measurement.3.1.20 integrator, nentity responsible for the integrationof all the various parachute components, the sUA, and thetesting of the entire system.3.1.20.1 DiscussionThe integrator could also be the para-chute recovery system manufacturer or the sUA manu

32、facturer.The integrator may also work with other named third parties todelegate various tasks. Tasks the integrator has are: (1)selection and integration of the parachute components, para-chute deployment device, and any other electronics needed; (2)installation of the parachute recovery system on t

33、he sUA andworking with the sUA manufacturer to integrate the systemproperly; (3) pulling together all the various componentspecifications to be sure they meet the requirements called outin this specification; and (4) performing and coordinating witha test facility all the various flight tests called

34、 out in thisspecification.3.1.21 manual triggering device, MTD, ndevice or com-ponent that can initiate deployment of the parachute recoverysystem at the discretion of the remote pilot in command(RPIC).3.1.22 manufacturer, nentity responsible for the creationof the various components of the parachut

35、e recovery system.3.1.22.1 DiscussionThese can consist of the parachute,parachute ejection device, flight termination system, parachuteF3322 182deployment controller, or other components. There can be anynumber of manufacturers.3.1.23 mean time between critical failure, MTBCF, nthereare two criteria

36、 for reliability that are relevant for parachuterecovery systems: (1) MTBCF for positive activationtheprobability that the parachute recovery system including itsATS and FTS will open the parachute in case of emergency and(2) MTBCF for false positive eventthe probability that theparachute recovery s

37、ystem will deploy unintentionally.3.1.24 minimum deployable altitude, MDA, ndifference inaltitude from the point of failure to the point of stabilized sUAdescent under parachute; is airframe/speed dependent andcertified through testing in Section 6.3.1.25 minimum flight altitude, MFA, nminimum altit

38、udeabove ground level of the sUA in cases in which a parachuterecovery system is used for flight over people. The MFA shallbe defined per the results of testing in Section 6.3.1.26 opening shock load, nthis is the maximum loadforce under any conditions that occurs on the main parachuteduring the pro

39、cess of the parachute opening.3.1.27 operational environment, vall allowed environ-mental conditions (temperature operating range, humidityrange, dust and other debris tolerances, and so forth) that themanufacturer will define in the environmental envelope foroperation/use for the product life of th

40、e parachute recoverysystem.3.1.28 packing/parachute packing, vprocess of foldingand condensing the main canopy, connected cables, and otherattached mechanisms to fit in a design compartment of theaircraft to hold the parachute.3.1.28.1 DiscussionThe packing process shall be done insuch a fashion to

41、allow for full deployment and acceptableopening behavior in the event of parachute deployment.Parachute packing procedures shall be defined by the parachutemanufacturer in the PM.3.1.29 parachute, nany aerodynamic deceleration devicedesigned to slow the descent of sUAwhen not under stable safeflight

42、.3.1.30 parachute manual (PM), nthe minimum materialprovided from the manufacturer to the operator/owner of thesUA that discusses topics such as instructions and proceduresfor inspection, maintenance, re-pack along with any PRSlimitations in regard to operational or environmental limita-tions and ap

43、proved payloads.3.1.31 parachute maximum dynamic shock load, MDSL,nmaximum opening shock load force the parachute is ratedfor under any condition.3.1.32 parachute recovery system, PRS, nsummation ofthe components of a parachute recovery system that work toreduce descent velocity.3.1.33 pilot chute,

44、nsmaller parachute than the maincanopy that is connected to the main canopy.3.1.33.1 DiscussionThe main purpose of the pilot chute isto be deployed before the main canopy to pull the main canopyout of a container into free air to produce full canopy. The needfor a pilot chute is determined by either

45、 the parachute manu-facturer or the parachute recovery system integrator.3.1.34 Remote-Pilot-In-Command (RPIC)the person who:(1) has final authority and responsibility for the operation andsafety of the flight; (2) has been designated as pilot-in-command before or during the flight.3.1.35 “shall” ve

46、rsus “should” versus “may”, vuse of theword “shall” implies that a procedure or statement is manda-tory and shall be followed to comply with this specification,“should” implies recommended, and “may” implies optional atthe discretion of the supplier, manufacturer, or operator.3.1.35.1 DiscussionSinc

47、e “shall” statements arerequirements, they include sufficient detail needed to definecompliance (for example, threshold values, test methods,oversight, and reference to other standards). “Should” state-ments are provided as guidance towards the overall goal ofimproving safety and could include only

48、subjective statements.“Should” statements also represent parameters that could beused in safety evaluations and could lead to development offuture requirements. “May” statements are provided to clarifyacceptability of a specific item or practice and offer options forsatisfying requirements.3.1.36 sn

49、atch force, nwhen using a pilot chute for para-chute deployment, snatch force is the highest peak forceneeded to extract the parachute and risers from the holdingcanister/bay to deploy full canopy.3.1.37 stabilized descent, nthe integrator shall determinethe fall speed of the sUA when the PRS has deployed based onthe sUA maximum takeoff weight. The descent is consideredstabilized when the vertical descent rate is within 10 % of theintegrators specified fall speed at sea level conditions.3.1.38 supplier, nany entity engaged in the