US 2022/0177123 A1 · CONTROL DEVICE FOR ELECTRIC VERTICAL TAKEOFF AND LANDING AIRCRAFT

Abstract

A control device controls an electric drive system mounted on an electric vertical takeoff and landing aircraft with a rotor, and including a drive motor that turns the rotor. The control device controls the electric drive system to operate selectively in any one operation mode of at least two operation modes: a normal mode and a functional test mode. In the normal mode, the control device controls the drive motor in accordance with a command from a body control device that controls the flight of the electric vertical takeoff and landing aircraft. In the functional test mode, the control device controls the drive motor in accordance with a command sent from outside according to a functional test program, or in accordance with the functional test program preset in the control device.

Claims19

Dependent claims

A control device for controlling an electric drive system mounted on an electric vertical takeoff and landing aircraft including a rotor, the electric drive system including a drive motor configured to turn the rotor, wherein

the control device controls the electric drive system to operate selectively in any one operation mode included in at least two operation modes:
a normal mode and a functional test mode,
in the normal mode, the control device controls the drive motor in accordance with a command from a body control device configured to control flight of the electric vertical takeoff and landing aircraft, and
in the functional test mode, the control device controls the drive motor in accordance with a command sent from outside according to a functional test program, or in accordance with the functional test program preset in the control device.

1 more element

A control device for an electric vertical takeoff and landing aircraft including a plurality of electric drive systems each including a drive motor configured to turn a rotor, wherein

the plurality of electric drive systems include a system under test being the electric drive system under test, and an opposite system being the electric drive system at a position opposite the system under test as the electric vertical takeoff and landing aircraft is viewed in a vertical direction, and when the system under test is subjected to a functional test including turning the rotor, the control device performs balance control processing for controlling the drive motors in the system under test and the opposite system to an identical rotation speed, and controlling rotational directions of the drive motors to opposite directions.

Dependencies are inferred from the claim text.

Control device for electric vertical takeoff and landing aircraft

Life of this patent

Control device for electric vertical takeoff and landing aircraft

Life of this patent

Abstract

Claims19