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ASTM F2585-08

(Specification)

Standard Specification for Design and Performance of Pneumatic-Hydraulic Unmanned Aircraft System (UAS) Launch System (Withdrawn 2017)

Standard Specification for Design and Performance of Pneumatic-Hydraulic Unmanned Aircraft System (UAS) Launch System (Withdrawn 2017)

ABSTRACT
This specification covers the design and performance requirements for unmanned aircraft system (UAS) launch systems operating via a closed-loop pressurized hydraulic, or pneumatic system with a hydraulic recovery, or both, which shall include, but not be limited to, the following main components: pre-launch accumulator(s), launch actuator(s), shuttle assembly, launch rail, and launch lock. Each launcher shall undergo developmental, acceptance, and operational tests, which will be documented and presented to the UAS manufacturer upon delivery. Proper training, operations, safety precautions, and maintenance and reliability practices are detailed thoroughly herein.
SCOPE
1.1 This specification covers the design and performance of unmanned aircraft system (UAS) launch system operating via a closed-loop pressurized hydraulic or pneumatic system with a hydraulic recovery, or both.
1.2 In instances where the launcher and UAS manufacturer are the same entity, compliance with this specification is the responsibility of the UAS manufacturer where applicable.
1.3 This standard does not purport to address all of the safety concerns associated with the USA launch system and its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.
WITHDRAWN RATIONALE
This specification covered the design and performance of unmanned aircraft system (UAS) launch system operating via a closed-loop pressurized hydraulic or pneumatic system with a hydraulic recovery, or both.
Formerly under the jurisdiction of Committee F38 on Unmanned Aircraft Systems, this specification was withdrawn in July 2017 in accordance with section 10.5.3.1 of the Regulations Governing ASTM Technical Committees, which requires that standards shall be updated by the end of the eighth year since the last approval date.

General Information

Status
Withdrawn
Publication Date
31-Jul-2008
Withdrawal Date
13-Jul-2017
ICS
49.020 - Aircraft and space vehicles in general
Technical Committee
F38 - Unmanned Aircraft Systems
Drafting Committee
F38.01 - Airworthiness
Current Stage
Ref Project

Relations

Replaces
ASTM F2585-06 - Standard Specification for Design and Performance of Pneumatic-Hydraulic Unmanned Aircraft System (UAS) Launch System
Effective Date
01-Aug-2008

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ASTM F2585-08 - Standard Specification for Design and Performance of Pneumatic-Hydraulic Unmanned Aircraft System (UAS) Launch System (Withdrawn 2017)ASTM F2585-08 - Standard Specification for Design and Performance of Pneumatic-Hydraulic Unmanned Aircraft System (UAS) Launch System (Withdrawn 2017)
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ASTM F2585-08 - Standard Specification for Design and Performance of Pneumatic-Hydraulic Unmanned Aircraft System (UAS) Launch System (Withdrawn 2017)
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NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.
Contact ASTM International (www.astm.org) for the latest information
Designation:F2585 −08
Standard Specification for
Design and Performance of Pneumatic-Hydraulic Unmanned
1
Aircraft System (UAS) Launch System
This standard is issued under the fixed designation F2585; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope 3.1.5 launch actuator—cylinder that accepts the gaseous
chargingagentorliquidchargingagentduringexpansionofthe
1.1 This specification covers the design and performance of
gaseous charging agent to move a piston; transfers gas or fluid
unmanned aircraft system (UAS) launch system operating via
pressure into an accelerating force on the shuttle assembly.
a closed-loop pressurized hydraulic or pneumatic system with
3.1.6 launch, or exit, velocity—velocity of the UA upon
a hydraulic recovery, or both.
release from the launcher; UAS take-off velocity.
1.2 In instances where the launcher and UAS manufacturer
3.1.7 launch lock—mechanism that secures the shuttle as-
are the same entity, compliance with this specification is the
sembly into the launch position to counter the force from fully
responsibility of the UAS manufacturer where applicable.
pressurized pre-launch accumulator(s).
1.3 This standard does not purport to address all of the
3.1.8 launch rail—track upon which the shuttle assembly
safety concerns associated with the USA launch system and its
can be accelerated prior to UA take-off.
use. It is the responsibility of the user of this standard to
establish appropriate safety and health practices and deter-
3.1.9 launch system—self-contained system capable of
mine the applicability of regulatory limitations prior to use.
launching a UAat prescribed take-off conditions; also referred
to as a launcher or catapult.
2. Referenced Documents
3.1.10 launch weight—maximum allowable UA take-off
2
2.1 Military Standard:
weight not including the weight of the shuttle assembly.
MIL-STD-882 Standard Practice for System Safety
3.1.11 liquid charging agent—incompressible fluid that can
be used to fill the pre-launch accumulators to move the piston.
3. Terminology
3.1.12 neutral position—UAS launcher system state in
3.1 Definitions:
which (1) any fluids inside the pre-launch accumulators and
3.1.1 acceleration envelope—range of launch accelerations
pre-chargeaccumulators(ifavailable)areatequalpressures,or
(that is, acceleration curves) that the UAS launcher is capable
(2) the system does not apply a force on the launch lock
of generating.
mechanism.
3.1.2 deployed configuration—UAS launcher’s physical ge-
3.1.13 power transmission mechanism—used to transfer the
ometry in which it is in neutral position and ready for launch
acceleratingforcefromlaunchactuatortoshuttleassembly(for
operations. Any manufacturer-prescribed check-out tests have
example, a shuttle assembly ram, cable and pulley system,
been completed when the UAS launcher is in deployed
etc.); power transmission mechanism may not be necessary in
configuration.
designs in which the launch actuators moves the shuttle
3.1.3 gaseous charging agent—compressible fluid that is
assembly directly.
pressurized to store the energy required for launch.
3.1.14 pre-charge accumulator(s)—similar in design to the
3.1.4 jerk—first derivative of the acceleration curve with
pre-launch accumulator; allows extra space for storing gaseous
respect to time; also referred to as acceleration growth rate.
charging agent between launches at a pressure lower than
operating pressure; also used to achieve desired pre-launch
1
This specification is under the jurisdiction of ASTM Committee F38 on accumulator pressures despite fluctuations in ambient tempera-
UnmannedAircraftSystemsandisthedirectresponsibilityofSubcommitteeF38.01
tures.
on Airworthiness.
3.1.15 pre-launch accumulator(s)—stores the energy re-
Current edition approved Aug. 1, 2008. Published August 2008. Originally
approved in 2006. Last previous edition approved in 2006 as F2585 – 06. DOI:
quired for launch; typically consists of either (1) a cylinder
10.1520/F2585-08.
with a piston separating fluids (gaseous charging agent and
2
Available from Standardization Documents Order Desk, DODSSP, Bldg. 4,
liquid charging agent) within which a compressible fluid
Section D, 700 Robbins Ave., Philadelphia, PA 19111-5098, http://
www.dodssp.daps.mil. (usually a gas) is pressurized by pumping an incompressible
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1

---------------------- Page: 1 ----------------------
F2585−08
fluid (usually hydraulic) into the cylinder, or (2) a pressurized 4.2.1 Each pre-launch accumulator shall
...

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