Modular rotorcraft and system for air-delivered effects or sensor payloads

A tactically deployable rotorcraft for targeted delivery of effects and/or sensors, comprising:

• a body housing an energy subsystem, a propulsion and flight control subsystem, and a payload compartment for holding a mission computer, payload controller, communication components, multi-modal sensors, and a modular effect or sensor payload, the body having a generally cylindrical outline and a plurality of arm-rotor niches in the generally cylindrical outline;
• and
• a plurality of arm-rotor assemblies pivotably mounted to the body, each arm-rotor assembly including an articulating arm and a rotor at a distal end of the articulating arm, each arm-rotor assembly being pivotable between (1) a closed position in a corresponding arm-rotor niche and within the generally cylindrical outline of the body, and (2) an open position extending from the body with the rotor oriented for controlled and stable flight at relative angular offset to both the body and other coordinated rotors, the rotors being powered by the energy subsystem and controlled by the propulsion and flight control subsystem to provide powered flight of the rotorcraft to a target location for delivery of the effect or sensor payload,
• the payload controller being capable of automatically adapting and tailoring mission, flight, and autonomous employment characteristic of the rotorcraft based on the equipped effect or sensor payload,
• wherein, for each of the arm-rotor assemblies in the open position:
• the arm of the arm-rotor assembly extends in a forward direction having a non-zero angle ψ relative to a transverse direction perpendicular to an axis of the rotorcraft;
• and
• the rotor of the arm-rotor assembly is configured to be canted about an arm axis at a non-zero angle φ from a plane of the arm, the angles ψ and φ both being in a range of 0 to 45 degrees.