Abstract: The present invention is directed to systems and methods for managing thermal energy of an electric vertical takeoff and landing aircraft. The system comprises of a multilayer laminate that includes a rigid layer and an insulation layer. The multilayer laminate may be laid on a structural element of an aircraft. The aircraft comprises an active component.

Abstract: Braking systems and methods for an electrical vertical takeoff and landing aircraft are provided. A braking system may contain a pilot control device, brakes, wheels, sensors, and a controller. Pilot controls the pilot control device to transmit information to the controller such that the aircraft will slow down.

Abstract: A system for rolling landing gear is illustrated. System includes a skid component attached to an aircraft and comprising at least a skid tube oriented laterally to a longitudinal axis of the aircraft. System also includes at least a wheel journaled on a rotational fulcrum and at least a biasing means attaching the rotational fulcrum to the skid tube, wherein the biasing means comprises at least a leaf spring and exerts a recoil force resisting upward displacement of the rotational fulcrum with respect to the skid tube.

Abstract: An aircraft having reverse thrust capabilities, the aircraft includes a fuselage, a plurality of flight components configured to enable the aircraft at a low-speed flight mode, a pilot control, a sensor, an energy source, and a flight controller configured to receive the aircraft datum from the sensor at an initial time, wherein the initial time occurs when at least a flight component of the plurality of flight components produces a positive thrust, initiate a reverse thrust command as a function of the aircraft datum at a subsequent time wherein the reverse thrust command causes the at least a flight component of the plurality of flight components to produce a negative thrust, and the subsequent time occurs temporally after the initial time, and command the at least a flight component of the plurality of flight components to enter a speed reversal region.

Abstract: Braking systems and methods for an electrical vertical takeoff and landing aircraft are provided. A braking system may contain a pilot control device, brakes, wheels, sensors, and a controller. Pilot controls the pilot control device to transmit information to the controller such that the aircraft will slow down.

Abstract: An aircraft having reverse thrust capabilities includes a fuselage, a plurality of flight components, a pilot control located within the fuselage, a sensor attached to the pilot control configured to detect an aircraft datum from the pilot control, and a flight controller, located within the fuselage, the flight controller configured to receive the aircraft datum from the sensor, and initiate a reverse torque command of a flight component of the plurality of flight components as a function of the aircraft datum.

Abstract: An aircraft having reverse thrust capabilities includes a fuselage, a plurality of flight components, a pilot control located within the fuselage, a sensor attached to the pilot control configured to detect an aircraft datum from the pilot control, and a flight controller, located within the fuselage, the flight controller configured to receive the aircraft datum from the sensor, and initiate a reverse torque command of a flight component of the plurality of flight components as a function of the aircraft datum.

Abstract: A system for rolling landing gear is illustrated. System includes a skid component attached to an aircraft and comprising at least a skid tube oriented laterally to a longitudinal axis of the aircraft. System also includes at least a wheel journaled on a rotational fulcrum and at least a biasing means attaching the rotational fulcrum to the skid tube, wherein the biasing means comprises at least a leaf spring and exerts a recoil force resisting upward displacement of the rotational fulcrum with respect to the skid tube.

Abstract: A system for rolling landing gear includes a skid component attached to an aircraft, wherein the skid component further comprises a first skid tube oriented laterally to a longitudinal axis of the axis, a second skid tube oriented laterally to the longitudinal axis of the aircraft, wherein the second skid tube is parallel to the first skid tube, a first wheel journaled on a first rotational fulcrum, a second wheel journaled on a second rotational fulcrum, a first biasing means attaching the first rotational fulcrum to the first skid tube, and a second biasing means attaching the second rotational fulcrum to the second skid tube, wherein the first biasing means and second biasing means exert a recoil force resisting upward displacement of the first rotational fulcrum and second rotational fulcrum with respect to the first skid tube and second skid tube.