ASTM_F_2585_-_08.pdf

Designation:F258508Standard 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 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 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 standard 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 Documents2.1 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 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 jerkfirst 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 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 accumulator(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 not 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(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 transmission 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 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 charging 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 Aug.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,SectionD,700RobbinsAve.,Philadelphia,PA19111-5098,http:/www.dodssp.daps.mil.Copyright ASTM International,100 Barr Harbor Drive,PO Box C700,West Conshohocken,PA 19428-2959.United States1 fluid(usually hydraulic)into the cylinder,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 UA and the launcher.3.1.18 stowed configurationUAS launchers smallestvolumetric physical geometry in which the UAS launcher canbe transpo