A dual-safe fuze incorporating electrical and/or mechanical fuzing for unmanned aerial system (UAS) drone applications includes an electrical power source configured to initiate a munition, and circuitry. The electrical and mechanical circuitry is positioned between the electrical power source and the munition for controlling the initiation of the munition via the electrical power source. The circuitry is configured to initiate the munition from an unmanned aerial vehicle (UAV). The circuitry positioned between the electrical power source and the munition includes a nose-proximity fuze circuit, a body-proximity fuze circuit, a shear lanyard safety circuit, and combinations thereof.

The technology subject of the present application generally concerns an aerial munition unit comprising a proximity fuze functionality and an impact fuze functionality, selectable by a crew member of an aircraft bearing the munition, after the aircraft has taken off and prior to munition release, to render active or operable the proximity fuze functionality or the impact fuze functionality.