1.1This specification covers minimum requirements for the design of Electric Propulsion Energy Storage Systems (ESS) for General Aviation aircraft. 1.2This standard is applicable to small aeroplanes. 1.4The applicant for a design approval shall seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their small aircraft airworthiness regulations (hereinafter referred to as the Rules), refer to ASTM Committee F39 webpage (www.ASTM.org/COMITTEE/F39.htm), which includes CAA website links. 1.5UnitsThe values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems may result in nonconformance with the standard. 1.6This 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.
Battery; batteries; electric motor; electric propulsion unit; EPU; cell; cells; case; chemistry; rechargeable; anode; charge; charge rate; cycle; discharge; discharge rate; volt; voltage.
An ESS designer or manufacturer can use this standard to show a means of compliance to regulatory or other requirements. It will complement the ASTM electric propulsion system design and integration standards for General Aviation aircraft.
The title and scope are in draft form and are under development within this