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.
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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.
2. Referenced Documents (purchase separately) The documents listed below are referenced within the subject standard but are not provided as part of the standard.
MIL-STD-882 Standard Practice for System Safety
atapult; launch; take-off; UA; UAS; unmanned aircraft system; UAS (Unmanned Aircraft System); Unmanned Aircraft System (UAS);
ICS Number Code 49.020 (Aircraft and space vehicles in general)
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Citing ASTM Standards
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