Multivariable airspeed and flight path angle control of a co-axial rotary wing aircraft with a pusher-propeller
AssigneeLockheed Martin Corporation
InventorNavid Dadkhah Tehrani
Life of this patent
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Abstract
Systems and methods for controlling a coaxial rotary-wing aircraft including a co-axial main rotor assembly and a pusher-propeller. One system includes an electronic controller configured to receive a reference velocity of the aircraft and receive a reference flight path angle of the aircraft. The electronic controller is also configured to simultaneously control the co-axial main rotor assembly and the pusher-propeller based on the reference velocity of the aircraft and the reference flight path angle of the aircraft, by simultaneously generating a commanded thrust of the pusher-propeller and a commanded thrust of the co-axial main rotor assembly using a multiple input, multiple output algorithm applying dynamic inversion.
Claims20
A system for controlling an aircraft including a co-axial main rotor assembly and a pusher-propeller, the system comprising:
- an electronic controller configured to:
- receive a reference velocity of the aircraft;
- receive a reference flight path angle of the aircraft;
- and
- simultaneously control the co-axial main rotor assembly and the pusher-propeller based on the reference velocity of the aircraft and the reference flight path angle of the aircraft, by simultaneously generating a commanded thrust of the pusher-propeller and a commanded thrust of the co-axial main rotor assembly using a multiple input, multiple output algorithm applying dynamic inversion, wherein the dynamic inversion outputs the commanded thrust of the pusher-propeller and the commanded thrust of the co-axial main rotor.
A method of controlling an aircraft including a co-axial main rotor assembly and a pusher-propeller, the method comprising:
- receiving, with an electronic controller, a reference velocity of the aircraft;
- receiving, with the electronic controller, a reference flight path angle of the aircraft;
- and
- simultaneously controlling, with the electronic controller, the co-axial main rotor assembly and the pusher-propeller based on the reference velocity of the aircraft and the reference flight path angle of the aircraft by simultaneously generating a commanded thrust of the pusher-propeller and a commanded thrust of the co-axial main rotor assembly using a multiple input, multiple output algorithm applying dynamic inversion, wherein the dynamic inversion outputs the commanded thrust of the pusher-propeller and the commanded thrust of the co-axial main rotor.
A non-transitory computer readable medium storing instructions, executable by an electronic processor, to perform a set of functions, the set of functions comprising:
- simultaneously controlling a co-axial main rotor assembly and a pusher-propeller of an aircraft based on a reference velocity of the aircraft and a reference flight path angle of the aircraft using a multiple input, multiple output algorithm applying dynamic inversion, wherein the dynamic inversion outputs the commanded thrust of the pusher-propeller and the commanded thrust of the co-axial main rotor.
Dependencies are inferred from the claim text.