ASTM F2585 - 08 Standard Specification for Design and Performance of Pneumatic-Hydraulic Unmanned Aircraft System (UAS) Launch System (Withdrawn 2017).pdf

《ASTM F2585 - 08 Standard Specification for Design and Performance of Pneumatic-Hydraulic Unmanned Aircraft System (UAS) Launch System (Withdrawn 2017).pdf》由会员分享，可在线阅读，更多相关《ASTM F2585 - 08 Standard Specification for Design and Performance of Pneumatic-Hydraulic Unmanned Aircraft System (UAS) Launch System (Withdrawn 2017).pdf（7页珍藏版）》请在麦多课文档分享上搜索。

1、Designation: F2585 08Standard Specification forDesign and Performance of Pneumatic-Hydraulic UnmannedAircraft System (UAS) Launch System1This standard is issued under the fixed designation F2585; the number immediately following the designation indicates the year oforiginal adoption or, in the case

2、of revision, 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 specification covers the design and performance ofunmanned aircraft system (UAS) launch

3、system operating viaa closed-loop pressurized hydraulic or pneumatic system witha hydraulic recovery, or both.1.2 In instances where the launcher and UAS manufacturerare the same entity, compliance with this specification is theresponsibility of the UAS manufacturer where applicable.1.3 This standar

4、d does not purport to address all of thesafety concerns associated with the USA launch system and itsuse. It is the responsibility of the user of this standard toestablish appropriate safety and health practices and deter-mine the applicability of regulatory limitations prior to use.2. Referenced Do

5、cuments2.1 Military Standard:2MIL-STD-882 Standard Practice for System Safety3. Terminology3.1 Definitions:3.1.1 acceleration enveloperange of launch accelerations(that is, acceleration curves) that the UAS launcher is capableof generating.3.1.2 deployed configurationUAS launchers physical ge-ometry

6、 in which it is in neutral position and ready for launchoperations. Any manufacturer-prescribed check-out tests havebeen completed when the UAS launcher is in deployedconfiguration.3.1.3 gaseous charging agentcompressible fluid that ispressurized to store the energy required for launch.3.1.4 jerkfir

7、st derivative of the acceleration curve withrespect to time; also referred to as acceleration growth rate.3.1.5 launch actuatorcylinder that accepts the gaseouscharging agent or liquid charging agent during expansion of thegaseous charging agent to move a piston; transfers gas or fluidpressure into

8、an accelerating force on the shuttle assembly.3.1.6 launch, or exit, velocityvelocity of the UA uponrelease from the launcher; UAS take-off velocity.3.1.7 launch lockmechanism that secures the shuttle as-sembly into the launch position to counter the force from fullypressurized pre-launch accumulato

9、r(s).3.1.8 launch railtrack upon which the shuttle assemblycan be accelerated prior to UA take-off.3.1.9 launch systemself-contained system capable oflaunching a UA at prescribed take-off conditions; also referredto as a launcher or catapult.3.1.10 launch weightmaximum allowable UA take-offweight no

10、t including the weight of the shuttle assembly.3.1.11 liquid charging agentincompressible fluid that canbe used to fill the pre-launch accumulators to move the piston.3.1.12 neutral positionUAS launcher system state inwhich (1) any fluids inside the pre-launch accumulators andpre-charge accumulators

11、 (if available) are at equal pressures, or(2) the system does not apply a force on the launch lockmechanism.3.1.13 power transmission mechanismused to transfer theaccelerating force from launch actuator to shuttle assembly (forexample, a shuttle assembly ram, cable and pulley system,etc.); power tra

12、nsmission mechanism may not be necessary indesigns in which the launch actuators moves the shuttleassembly directly.3.1.14 pre-charge accumulator(s)similar in design to thepre-launch accumulator; allows extra space for storing gaseouscharging agent between launches at a pressure lower thanoperating

13、pressure; also used to achieve desired pre-launchaccumulator pressures despite fluctuations in ambient tempera-tures.3.1.15 pre-launch accumulator(s)stores the energy re-quired for launch; typically consists of either (1) a cylinderwith a piston separating fluids (gaseous charging agent andliquid ch

14、arging agent) within which a compressible fluid(usually a gas) is pressurized by pumping an incompressible1This specification is under the jurisdiction of ASTM Committee F38 onUnmannedAircraft Systems and is the direct responsibility of Subcommittee F38.01on Airworthiness.Current edition approved Au

15、g. 1, 2008. Published August 2008. Originallyapproved in 2006. Last previous edition approved in 2006 as F2585 06. DOI:10.1520/F2585-08.2Available from Standardization Documents Order Desk, DODSSP, Bldg. 4,Section D, 700 Robbins Ave., Philadelphia, PA 19111-5098, http:/www.dodssp.daps.mil.Copyright

16、ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United StatesNOTICE: This standard has either been superseded and replaced by a new version or withdrawn.Contact ASTM International (www.astm.org) for the latest information1fluid (usually hydraulic) into the c

17、ylinder, or (2) a pressurizedcontainer (for example, bottle) holding the gaseous chargingagent with no piston (examples of each are provided in Fig. 1).3.1.16 recoverymethod by which the shuttle assembly isreturned upon release of the UAS.3.1.17 shuttle assemblyplatform that interfaces with boththe

18、UA and the launcher.3.1.18 stowed configurationUAS launchers smallestvolumetric physical geometry in which the UAS launcher canbe transported or stored for later use.3.1.19 strokedistance traveled by the shuttle assembly asmeasured from start (pre-launch) to UA release.3.1.20 throw weighttotal weigh

19、t to be accelerated by theUAS launcher; UA weight plus shuttle assembly weight.3.1.21 UA surrogatestructure representative of the massand support point dimensions of the UA; used to interface withthe shuttle assembly during test launches.3.1.22 unmanned aircraft (UA)flight-capable portion ofthe unma

20、nned aircraft system (UAS).3.1.23 velocity enveloperange of launch velocities that theUAS launcher is capable of generating; a function of launcheracceleration and rail length.3.1.24 weight enveloperange of launch weights that theUAS launcher is capable of accelerating to the requiredtake-off veloci

21、ty.4. Design4.1 The hydraulic or pneumatic launcher with hydraulicrecovery, or both, shall include, but not be limited to, thefollowing main components: pre-launch accumulator(s),launch actuator(s), shuttle assembly, launch rail, and launchlock.4.2 Accumulator(s), Launch Actuator(s), and Power Trans

22、-mission Mechanism:4.2.1 Each pre-launch accumulator shall be capable ofpressurization to accommodate the range of ambient tempera-tures within which the UA is rated to be launched.4.2.2 Each pre-launch accumulator shall be capable ofpressurization that exceeds the maximum required pressuriza-tion o

23、f the weight and velocity envelopes by 25 %.4.2.3 The gas used as a charging agent shall be:4.2.3.1 Non-combustible or have low combustibility (forexample, nitrogen, air),4.2.3.2 Non-toxic, and4.2.3.3 Capable of pressurization via a compressor or gasbottle.4.2.4 The liquid charging agent shall have

24、a viscosity rangewith maximum fluctuation as a function of ambient tempera-ture such that:4.2.4.1 It can generate the required range of velocitieswithin the velocity envelope, or4.2.4.2 It can be heated to acceptable temperatures if ambi-ent temperatures are shown to potentially increase viscosity t

25、olevels that adversely affect the velocity envelope.4.2.5 The piping that transfers the liquid charging agentshall be designed to minimize cavitation and ensure smoothflow from the accumulators to the launch actuator.4.2.6 The launch actuator shall transfer gas pressure fromthe pre-launch accumulato

26、r(s) into an accelerating force on thepower transmission mechanism.4.2.6.1 Indirectly (that is, pre-launch accumulator transferspressure from compressed gas into fluid pressure and isconnected to the launch actuator via hydraulic pipes, or hoses,or both), or4.2.6.2 Directly (that is, pre-launch accu

27、mulator is con-nected to the launch actuator via pneumatic pipes, or hoses, orboth).4.2.7 Pressurization to control launch velocity shall beadjustable by one person via electronic or mechanical controls.FIG. 1 Examples of Launcher DesignsF2585 082Pressurization shall be displayed to the launcher ope

28、rator viaan electronic or standard pressure gauge.4.2.8 The hydraulic recovery system shall be designed to:4.2.8.1 Utilize the same actuators used to generate theaccelerating force, or4.2.8.2 Have dedicated actuators used for recovery only.4.3 Shuttle Assembly, Launch Rail, and Launch Lock:4.3.1 The

29、 shuttle assembly shall be securable in start (pre-launch) position using a launch lock mechanism when the UASlauncher is in neutral position.4.3.2 The launch lock mechanism shall be capable ofwithstanding 1.5 times the force generated by fully-pressurizedpre-launch accumulators.4.3.3 Launch shall b

30、e initiated with the release of the launchlock, allowing for acceleration of shuttle assembly (piston inthe case of ram design) and UA. Accelerating force generatedby launch actuator(s) can act on shuttle assembly directly or viapower transmission mechanism.4.3.4 The force (that is, acceleration) de

31、livered through apower transmission mechanism to the shuttle assembly:4.3.4.1 Shall be constant, or4.3.4.2 When this force is not constant, the launcher manu-facturer shall provide the operator with data showing thelauncher acceleration curve.4.3.5 The launcher system shall include a measurementdevi

32、ce(s) to monitor maximum velocity of the shuttle assembly(that is, UA exit velocity).4.3.6 Shuttle assemblies that interface with various UAplatforms shall interface with the launch rail via a common(that is, universal) design such that no structural reconfigura-tion of the launcher is required to l

33、aunch a given UA platformprovided that UA falls within the launcher velocity and weightenvelopes.4.3.7 The launcher shall be configurable so that it can beoriented azimuthally to accommodate adjustment for:4.3.7.1 Local obstacles,4.3.7.2 Prevailing wind direction, and4.3.7.3 Operational requirements

34、.4.3.8 The launcher shall be configurable so that it can beoriented in elevation to ensure that the take-off path (angle) isconsistent with the performance of the UA.4.4 General Design and Performance:4.4.1 The launch system manufacturer shall coordinateclosely with the specific UAS manufacturers an

35、d operatorsbefore and during the design process to tailor the launch systemto the specific UA performance, structural, and operationalrequirements to include the UA:4.4.1.1 Mass,4.4.1.2 Required take-off velocity,4.4.1.3 Maximum acceleration loads, and4.4.1.4 Launch angle.4.4.2 Launchers shall be de

36、signed and classified as a func-tion of their weight, velocity and acceleration envelopes.Various UA shall be accommodated by a single launcher if thelauncher fulfills the UA requirements listed in 4.4.1.1 through4.4.1.4.4.4.3 Launcher operation shall not be dependent uponcompatibility with the UAS

37、command or control data link.4.4.4 Any resulting recoil of the launcher during the launchprocess shall be reacted by:4.4.4.1 Shock absorbers on the launcher platform,4.4.4.2 Secure grounding to prevent launcher movementunder recoil loads, or4.4.4.3 Other methods demonstrated to be able to absorbreco

38、il.4.4.5 The launcher system shall be a “closed” system withthe self-contained capability for:4.4.5.1 Power,4.4.5.2 Fluid compression, and4.4.5.3 Autonomous monitoring of launcher status.4.4.6 The launcher generator may be capable of providingexcess electrical power to other UAS systems on a conting

39、encybasis.4.4.7 Velocity envelopes shall be achieved without therequirements for rocket-assisted take-off (RATO) or otherpropulsive devices.4.4.8 The launcher system shall be designed to supportoperations in night or low light conditions.4.5 Proof of ComplianceThe manufacturer(s) of thelauncher shal

40、l coordinate with the UAS manufacturer andoperator to obtain concurrence on an acceptable means ofcompliance with these specifications in accordance with Sec-tion 5. Compliance may be proven by conservative testing withthe UA or a UA surrogate.5. Testing5.1 Each launcher that is designed and built t

41、o UASmanufacturer specifications shall be tested prior to delivery tothe UAS manufacturer.5.2 The results of any developmental or acceptance testingshall be presented to the UAS manufacturer upon launchersystem delivery.Any system modifications based on test resultsshall be documented and noted at t

42、his time.5.3 Developmental Testing:5.3.1 Where applicable as determined by the launchermanufacturer, the following test procedures shall be developedand performed on a prototype launcher in order that themanufacturer may determine the appropriateness for use, of notonly the components, but the entir

43、e system of a newly designedlauncher.5.3.1.1 Procedures to verify such design characteristics asrelevant deflections, loads, and forces that are placed on boththe launcher and the UA during operation.5.3.1.2 Procedures to determine velocity, weight, and accel-eration envelopes generated by nominal l

44、auncher operation.5.3.1.3 Procedures to allow the manufacturer to determinesuch factors as component variability and certification require-ments of components.5.3.1.4 Procedure to determine operational limits and restartcriteria related to environmental conditions (that is, criteria todetermine when

45、 previously exceeded operational and environ-mental conditions have returned to acceptable levels fornominal launcher operation).5.4 Acceptance Testing:F2585 0835.4.1 Where applicable as determined by the launchermanufacturer and UAS operator, the following test proceduresshall be developed and perf

46、ormed to determine launcherperformance prior to delivery.5.4.1.1 Pressurization TimeThe initial time required topressurize the launcher from atmospheric or neutral positionpressure to launch pressure.5.4.1.2 Reload TimeThe time to recharge the launcher forsubsequent launches.5.4.1.3 Weight (Mass) En

47、velopeThe regime of acceptableUA launch masses from minimum to maximum.5.4.1.4 Velocity EnvelopeThe regime of acceptable UAlaunch velocities from minimum to maximum.5.4.1.5 AccelerationThe acceleration curves and maxi-mum possible acceleration generated by the launcher.5.4.2 For the purposes of this

48、 testing, acceleration valuesshall be:5.4.2.1 Measured using accelerometers having a bandwidthof at least DC-100 Hz,5.4.2.2 Collected using a sampling frequency greater orequal to 500 Hz, and5.4.2.3 Determined by low pass filtered or averaged data asagreed upon between the launcher manufacturer and

49、the UASmanufacturer.5.4.3 The number of test launches with UA surrogates shallbe agreed upon between the launcher and UAS manufacturersprior to design acceptance.5.4.3.1 The final velocity of the shuttle assembly with theUA surrogate shall be demonstrated to be within predefinedlimits of the programmed take-off velocity. This velocity shallhave been previously agreed upon between UAS manufacturerand launcher manufacturer prior to initial launcher delivery.5.4.3.2 The weight of UA surrogates shall be within 65%of the actual UA.5.4.3.3 A