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ASTM F2585-06

(Specification)

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

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

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.
This standard does not purport to address all of the safety concerns, if any, associated with 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.

General Information

Status
Historical
Publication Date
30-Nov-2006
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

Replaced By
ASTM F2585-08 - Standard Specification for Design and Performance of Pneumatic-Hydraulic Unmanned Aircraft System (UAS) Launch System (Withdrawn 2017)
Effective Date
01-Aug-2008

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ASTM F2585-06 - Standard Specification for Design and Performance of Pneumatic-Hydraulic Unmanned Aircraft System (UAS) Launch SystemASTM F2585-06 - Standard Specification for Design and Performance of Pneumatic-Hydraulic Unmanned Aircraft System (UAS) Launch System
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ASTM F2585-06 - Standard Specification for Design and Performance of Pneumatic-Hydraulic Unmanned Aircraft System (UAS) Launch System
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NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.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: F 2585 – 06
Standard Specification for
Design and Performance of Pneumatic-Hydraulic Unmanned
1
Aircraft System (UAS) Launch System
This standard is issued under the fixed designation F 2585; 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 (e) indicates an editorial change since the last revision or reapproval.
1. Scope 2.1.8 launch rail—track upon which the shuttle assembly
can be accelerated prior to UA take-off.
1.1 This specification covers the design and performance of
2.1.9 launch system—self-contained system capable of
unmanned aircraft system (UAS) launch system operating via
launching a UAat prescribed take-off conditions; also referred
a closed-loop pressurized hydraulic or pneumatic system with
to as a launcher or catapult.
a hydraulic recovery, or both.
2.1.10 launch weight—maximum allowable UA take-off
1.2 In instances where the launcher and UAS manufacturer
weight not including the weight of the shuttle assembly.
are the same entity, compliance with this specification is the
2.1.11 liquid charging agent—incompressible fluid that can
responsibility of the UAS manufacturer where applicable.
be used to fill the pre-launch accumulators to move the piston.
1.3 This standard does not purport to address all of the
2.1.12 neutral position—UAS launcher system state in
safety concerns, if any, associated with its use. It is the
which (1) any fluids inside the pre-launch accumulators and
responsibility of the user of this standard to establish appro-
pre-chargeaccumulators(ifavailable)areatequalpressures,or
priate safety and health practices and determine the applica-
(2) the system does not apply a force on the launch lock
bility of regulatory limitations prior to use.
mechanism.
2. Terminology
2.1.13 power transmission mechanism—used to transfer the
acceleratingforcefromlaunchactuatortoshuttleassembly(for
2.1 Definitions:
example, a shuttle assembly ram, cable and pulley system,
2.1.1 acceleration envelope—range of launch accelerations
etc.); power transmission mechanism may not be necessary in
(that is, acceleration curves) that the UAS launcher is capable
designs in which the launch actuators moves the shuttle
of generating.
assembly directly.
2.1.2 deployed configuration—UAS launcher’s physical ge-
2.1.14 pre-charge accumulator(s)—similar in design to the
ometry in which it is in neutral position and ready for launch
pre-launch accumulator; allows extra space for storing gaseous
operations. Any manufacturer-prescribed check-out tests have
charging agent between launches at a pressure lower than
been completed when the UAS launcher is in deployed
operating pressure; also used to achieve desired pre-launch
configuration.
accumulator pressures despite fluctuations in ambient tempera-
2.1.3 gaseous charging agent—compressible fluid that is
tures.
pressurized to store the energy required for launch.
2.1.15 pre-launch accumulator(s)—stores the energy re-
2.1.4 jerk—first derivative of the acceleration curve with
quired for launch; typically consists of either (1) a cylinder
respect to time; also referred to as acceleration growth rate.
with a piston separating fluids (gaseous charging agent and
2.1.5 launch actuator—cylinder that accepts the gaseous
liquid charging agent) within which a compressible fluid
chargingagentorliquidchargingagentduringexpansionofthe
(usually a gas) is pressurized by pumping an incompressible
gaseous charging agent to move a piston; transfers gas or fluid
fluid (usually hydraulic) into the cylinder, or (2) a pressurized
pressure into an accelerating force on the shuttle assembly.
container (for example, bottle) holding the gaseous charging
2.1.6 launch, or exit, velocity—velocity of the UA upon
agent with no piston (examples of each are provided in Fig. 1).
release from the launcher; UAS take-off velocity.
2.1.16 recovery—method by which the shuttle assembly is
2.1.7 launch lock—mechanism that secures the shuttle as-
returned upon release of the UAS.
sembly into the launch position to counter the force from fully
2.1.17 shuttle assembly—platform that interfaces with both
pressurized pre-launch accumulator(s).
the UA and the launcher.
2.1.18 stowed configuration—UAS launcher’s smallest
1
This specification is under the jurisdiction of ASTM Committee F38 on
volumetric physical geometry in which the UAS launcher can
UnmannedAircraftSystemsandisthedirectresponsibilityofSubcommitteeF38.01
be transported or stored for later use.
on Airworthiness.
Current edition approved Dec. 1, 2006. Published January 2007.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
1

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1.4.2 This specification neither purports to address UAS operating with approval to use ADS-B or secondary surveillance radar transponders, nor does it purport to solve ID needs of UAS for all operations.  
1.4.3 In particular, this specification does not purport to address identification needs for UAS that are not participating in Remote ID or operators that purposefully circumvent Remote ID.  
1.5 The values stated in SI units are to be regarded as standard. The values given in parentheses after SI units are provided for information only and are not considered standard.  
1.5.1 Units of measurement included in this specification:    
m  
meters  
deg, °  
degrees of latitude and longitude, compass direction  
s  
seconds  
Hz  
Hertz (frequency)  
dBm  
decibel-milliwatts (radio frequency power)  
ppm  
parts per million (radio frequency variation)  
μs  
microseconds  
ms  
milliseconds  
1.6 Table of Contents:    
Title  
Section  
Scope  
1  
Referenced Documents  
2  
Terminology  
3  
Remote ID and Network Interoperability Conceptual Overview  
4  
Performance Requirements  
5  
TEST METHODS  
Scope  
6  
Significance and Use  
7  
Hazards  
8  
Test Units  
9  
Procedure  
10  
Precision and Bias  
11  
Product Marking  
12  
Packaging and Package Marking  
13  
Keywords  
14  
ANNEX A1—Broadcast Authentication Verifier Service  
Annex A1  
ANNEX A2—Network Remote ID Interoperability Requirements, APIs, and Testing  
Annex A2  
ANNEX A3—Tables of Values  
Annex A3  
ANNEX A4—USS-DSS and USS-USS OpenAPI YAML Description  
Annex A4  
ANNEX A5—Number Registrar Management Policy  
Annex A5  
APPENDIX X1—Performance Characteristics  
Appendix X1  
APPENDIX X2—List of Subcommittee Participants and Contributors  
Appendix X2  
APPENDIX X3—Background Information  
Appendix X3  
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1.8 This international standard was developed in accordance with internationally recognized principles on standardization established in the D...

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