Abstract: An embodiment aircraft boom includes a boom member, a vertical stabilizer, a rear landing gear, and a front landing gear. The boom member may extend in a first direction and have a front internal structural member disposed therein, where a portion of the front internal structural member is a first attachment point for a first wing. The vertical stabilizer may extend from the boom member, where the vertical stabilizer has a rear internal structural member disposed therein and extends from the boom member and through an interior of the vertical stabilizer, and where a portion of the rear internal structural member is a second attachment point for a second wing. The rear landing gear may be coupled to the rear internal structural member. The front landing gear may be coupled to the front internal structural member of the boom member.

Abstract: An embodiment aircraft boom includes a boom member, a vertical stabilizer, a rear landing gear, and a front landing gear. The boom member may extend in a first direction and have a front internal structural member disposed therein, where a portion of the front internal structural member is a first attachment point for a first wing. The vertical stabilizer may extend from the boom member, where the vertical stabilizer has a rear internal structural member disposed therein and extends from the boom member and through an interior of the vertical stabilizer, and where a portion of the rear internal structural member is a second attachment point for a second wing. The rear landing gear may be coupled to the rear internal structural member. The front landing gear may be coupled to the front internal structural member of the boom member.

Abstract: Drive system for an aircraft, including: a propeller; electric motor; transmission system for transmitting positive torque from the motor to drive the propeller and negative torque from the propeller in windmill braking state to drive the motor; interface for inputting an input; first unit for controlling torque acting on the motor; second unit for detecting rotational speed of the motor; selection unit to select an active mode from propulsion mode and recovery mode, wherein the motor generates recovery energy in the recovery mode; and management system to control energy flow in an electrical system of the aircraft, the electrical system including the motor, is controlled according to the active mode; wherein the selection unit is configured to select the active mode according to the input, rotational speed, and predefined envelope, wherein the envelope indicates a maximum positive torque and minimum negative torque that depends on the rotational speed.

Abstract: Drive system for an aircraft, including: a propeller; electric motor; transmission system for transmitting positive torque from the motor to drive the propeller and negative torque from the propeller in windmill braking state to drive the motor; interface for inputting an input; first unit for controlling torque acting on the motor; second unit for detecting rotational speed of the motor; selection unit to select an active mode from propulsion mode and recovery mode, wherein the motor generates recovery energy in the recovery mode; and management system to control energy flow in an electrical system of the aircraft, the electrical system including the motor, is controlled according to the active mode; wherein the selection unit is configured to select the active mode according to the input, rotational speed, and predefined envelope, wherein the envelope indicates a maximum positive torque and minimum negative torque that depends on the rotational speed.