1、Designation: F 2585 06Standard Specification forDesign and Performance of Pneumatic-Hydraulic UnmannedAircraft System (UAS) Launch System1This standard is issued under the fixed designation F 2585; the number immediately following the designation indicates the year oforiginal adoption or, in the cas
2、e of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon (e) indicates an editorial change since the last revision or reapproval.1. Scope1.1 This specification covers the design and performance ofunmanned aircraft system (UAS) laun
3、ch 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 stan
4、dard 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 and health practices and determine the applica-bility of regulatory limitations prior to use.2. Terminology2.1 Definition
5、s:2.1.1 acceleration enveloperange of launch accelerations(that is, acceleration curves) that the UAS launcher is capableof generating.2.1.2 deployed configurationUAS launchers physical ge-ometry in which it is in neutral position and ready for launchoperations. Any manufacturer-prescribed check-out
6、 tests havebeen completed when the UAS launcher is in deployedconfiguration.2.1.3 gaseous charging agentcompressible fluid that ispressurized to store the energy required for launch.2.1.4 jerkfirst derivative of the acceleration curve withrespect to time; also referred to as acceleration growth rate
7、.2.1.5 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.2.1.6 launch, or exit, velocityvelocity of the UA uponrelea
8、se from the launcher; UAS take-off velocity.2.1.7 launch lockmechanism that secures the shuttle as-sembly into the launch position to counter the force from fullypressurized pre-launch accumulator(s).2.1.8 launch railtrack upon which the shuttle assemblycan be accelerated prior to UA take-off.2.1.9
9、launch systemself-contained system capable oflaunching a UA at prescribed take-off conditions; also referredto as a launcher or catapult.2.1.10 launch weightmaximum allowable UA take-offweight not including the weight of the shuttle assembly.2.1.11 liquid charging agentincompressible fluid that canb
10、e used to fill the pre-launch accumulators to move the piston.2.1.12 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 lockmechani
11、sm.2.1.13 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 shuttleassembl
12、y directly.2.1.14 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 te
13、mpera-tures.2.1.15 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 incompressibl
14、efluid (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).2.1.16 recoverymethod by which the shuttle assembly isreturned upon release of the UAS.2.1.17 shuttle assemblyp
15、latform that interfaces with boththe UA and the launcher.2.1.18 stowed configurationUAS launchers smallestvolumetric physical geometry in which the UAS launcher canbe transported or stored for later use.1This specification is under the jurisdiction of ASTM Committee F38 onUnmannedAircraft Systems an
16、d is the direct responsibility of Subcommittee F38.01on Airworthiness.Current edition approved Dec. 1, 2006. Published January 2007.1Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.2.1.19 strokedistance traveled by the shuttle assembl
17、y asmeasured from start (pre-launch) to UA release.2.1.20 throw weighttotal weight to be accelerated by theUAS launcher; UA weight plus shuttle assembly weight.2.1.21 UA surrogatestructure representative of the massand support point dimensions of the UA; used to interface withthe shuttle assembly du
18、ring test launches.2.1.22 unmanned aircraft (UA)flight-capable portion ofthe unmanned aircraft system (UAS).2.1.23 velocity enveloperange of launch velocities thatthe UAS launcher is capable of generating; a function oflauncher acceleration and rail length.2.1.24 weight enveloperange of launch weigh
19、ts that theUAS launcher is capable of accelerating to the requiredtake-off velocity.3. Design3.1 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, la
20、unch rail, and launchlock.3.2 Accumulator(s), Launch Actuator(s), and Power Trans-mission Mechanism:3.2.1 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.3.2.2 Each pre-launch accumulator shal
21、l be capable ofpressurization that exceeds the maximum required pressuriza-tion of the weight and velocity envelopes by 25 %.3.2.3 The gas used as a charging agent shall be:3.2.3.1 Non-combustible or have low combustibility (forexample, nitrogen, air),3.2.3.2 Non-toxic, and3.2.3.3 Capable of pressur
22、ization via a compressor or gasbottle.3.2.4 The liquid charging agent shall have a viscosity rangewith maximum fluctuation as a function of ambient tempera-ture such that:3.2.4.1 It can generate the required range of velocitieswithin the velocity envelope, or3.2.4.2 It can be heated to acceptable te
23、mperatures if ambi-ent temperatures are shown to potentially increase viscosity tolevels that adversely affect the velocity envelope.3.2.5 The piping that transfers the liquid charging agentshall be designed to minimize cavitation and ensure smoothflow from the accumulators to the launch actuator.3.
24、2.6 The launch actuator shall transfer gas pressure fromthe pre-launch accumulator(s) into an accelerating force on thepower transmission mechanism.3.2.6.1 Indirectly (that is, pre-launch accumulator transferspressure from compressed gas into fluid pressure and isconnected to the launch actuator via
25、 hydraulic pipes, or hoses,or both), or3.2.6.2 Directly (that is, pre-launch accumulator is con-nected to the launch actuator via pneumatic pipes, or hoses, orboth).3.2.7 Pressurization to control launch velocity shall beadjustable by one person via electronic or mechanical controls.Pressurization s
26、hall be displayed to the launcher operator viaan electronic or standard pressure gauge.3.2.8 The hydraulic recovery system shall be designed to:3.2.8.1 Utilize the same actuators used to generate theaccelerating force, or3.2.8.2 Have dedicated actuators used for recovery only.3.3 Shuttle Assembly, L
27、aunch Rail, and Launch Lock:3.3.1 The shuttle assembly shall be securable in start (pre-launch) position using a launch lock mechanism when the UASlauncher is in neutral position.3.3.2 The launch lock mechanism shall be capable ofwithstanding 1.5 times the force generated by fully-pressurizedpre-lau
28、nch accumulators.FIG. 1 Examples of Launcher DesignsF25850623.3.3 Launch shall be 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 direct
29、ly or viapower transmission mechanism.3.3.4 The force (that is, acceleration) delivered through apower transmission mechanism to the shuttle assembly:3.3.4.1 Shall be constant, or3.3.4.2 When this force is not constant, the launcher manu-facturer shall provide the operator with data showing thelaunc
30、her acceleration curve.3.3.5 The launcher system shall include a measurementdevice(s) to monitor maximum velocity of the shuttle assembly(that is, UA exit velocity).3.3.6 Shuttle assemblies that interface with various UAplatforms shall interface with the launch rail via a common(that is, universal)
31、design such that no structural reconfigura-tion of the launcher is required to launch a given UA platformprovided that UA falls within the launcher velocity and weightenvelopes.3.3.7 The launcher shall be configurable so that it can beoriented azimuthally to accommodate adjustment for:3.3.7.1 Local
32、obstacles,3.3.7.2 Prevailing wind direction, and3.3.7.3 Operational requirements.3.3.8 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.3.4 General Design and Performance:3.4.1 The launch sy
33、stem manufacturer shall coordinateclosely with the specific UAS manufacturers and operatorsbefore and during the design process to tailor the launch systemto the specific UA performance, structural, and operationalrequirements to include the UA:3.4.1.1 Mass,3.4.1.2 Required take-off velocity,3.4.1.3
34、 Maximum acceleration loads, and3.4.1.4 Launch angle.3.4.2 Launchers shall be designed 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 3.4.1.1 through3.4.1.4
35、.3.4.3 Launcher operation shall not be dependent uponcompatibility with the UAS command or control data link.3.4.4 Any resulting recoil of the launcher during the launchprocess shall be reacted by:3.4.4.1 Shock absorbers on the launcher platform,3.4.4.2 Secure grounding to prevent launcher movementu
36、nder recoil loads, or3.4.4.3 Other methods demonstrated to be able to absorbrecoil.3.4.5 The launcher system shall be a “closed” system withthe self-contained capability for:3.4.5.1 Power,3.4.5.2 Fluid compression, and3.4.5.3 Autonomous monitoring of launcher status.3.4.6 The launcher generator may
37、be capable of providingexcess electrical power to other UAS systems on a contingencybasis.3.4.7 Velocity envelopes shall be achieved without therequirements for rocket-assisted take-off (RATO) or otherpropulsive devices.3.4.8 The launcher system shall be designed to supportoperations in night or low
38、 light conditions.3.5 Proof of ComplianceThe manufacturer(s) of thelauncher shall coordinate with the UAS manufacturer andoperator to obtain concurrence on an acceptable means ofcompliance with these specifications in accordance with Sec-tion 4. Compliance may be proven by conservative testing witht
39、he UA or a UA surrogate.4. Testing4.1 Each launcher that is designed and built to UASmanufacturer specifications shall be tested prior to delivery tothe UAS manufacturer.4.2 The results of any developmental or acceptance testingshall be presented to the UAS manufacturer upon launchersystem delivery.
40、Any system modifications based on test resultsshall be documented and noted at this time.4.3 Developmental Testing:4.3.1 Where applicable as determined by the launchermanufacturer, the following test procedures shall be developedand performed on a prototype launcher in order that themanufacturer may
41、 determine the appropriateness for use, of notonly the components, but the entire system of a newly designedlauncher.4.3.1.1 Procedures to verify such design characteristics asrelevant deflections, loads, and forces that are placed on boththe launcher and the UA during operation.4.3.1.2 Procedures t
42、o determine velocity, weight, and accel-eration envelopes generated by nominal launcher operation.4.3.1.3 Procedures to allow the manufacturer to determinesuch factors as component variability and certification require-ments of components.4.3.1.4 Procedure to determine operational limits and restart
43、criteria related to environmental conditions (that is, criteria todetermine when previously exceeded operational and environ-mental conditions have returned to acceptable levels fornominal launcher operation).4.4 Acceptance Testing:4.4.1 Where applicable as determined by the launchermanufacturer and
44、 UAS operator, the following test proceduresshall be developed and performed to determine launcherperformance prior to delivery.4.4.1.1 Pressurization TimeThe initial time required topressurize the launcher from atmospheric or neutral positionpressure to launch pressure.4.4.1.2 Reload TimeThe time t
45、o recharge the launcher forsubsequent launches.4.4.1.3 Weight (Mass) EnvelopeThe regime of acceptableUA launch masses from minimum to maximum.4.4.1.4 Velocity EnvelopeThe regime of acceptable UAlaunch velocities from minimum to maximum.4.4.1.5 AccelerationThe acceleration curves and maxi-mum possibl
46、e acceleration generated by the launcher.F25850634.4.2 For the purposes of this testing, acceleration valuesshall be:4.4.2.1 Measured using accelerometers having a bandwidthof at least DC-100 Hz,4.4.2.2 Collected using a sampling frequency greater orequal to 500 Hz, and4.4.2.3 Determined by low pass
47、 filtered or averaged data asagreed upon between the launcher manufacturer and the UASmanufacturer.4.4.3 The number of test launches with UA surrogates shallbe agreed upon between the launcher and UAS manufacturersprior to design acceptance.4.4.3.1 The final velocity of the shuttle assembly with the
48、UA 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.4.4.3.2 The weight of UA surrogates shall be within 65%of the
49、 actual UA.4.4.3.3 Aerodynamic forces (lift, thrust, drag) associatedwith the launch of the actual UA shall be estimated byconservative analysis or data from the UAS manufacturer andincorporated into the launchers designated velocity envelope.4.5 Operational Testing:4.5.1 The launcher manufacturer shall develop specificoperational tests along with maximum intervals for these teststo be performed that will allow the UAS operator to determinewhether the launcher is performing within prescribed limits.4.5.2 All operational tests, except those necessarily rec
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