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US 10,183,746 B2Granted
Aircraft with independently controllable propulsion assemblies
AssigneeBell Helicopter Textron Inc.
InventorsJohn Richard McCullough, Paul K. Oldroyd
Life of this patent
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Abstract
In some embodiments, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, a flight control system operably associated with the distributed propulsion system and a pod assembly selectively attachable to the flying frame. The distributed propulsion system includes a plurality of propulsion assemblies that are independently controlled by the flight control system, thereby enabling the flying frame to have a vertical takeoff and landing mode and a forward flight mode.
Claims20
An aircraft comprising:
- an airframe having first and second wing members with at least two pylons extending generally perpendicularly therebetween;
- a distributed propulsion system including at least two propulsion assemblies attached to the first wing and at least two propulsion assemblies attached to the second wing;
- a flight control system operably associated with the distributed propulsion system and operable to independently control a rotor speed and a thrust vector of each of the propulsion assemblies, the airframe, the distributed propulsion system and the flight control system forming a flying frame;
- and
- a pod assembly selectively attachable to and detachable from the flying frame,
- wherein, the flying frame is operable for flight both with the pod assembly and without the pod assembly;
- wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode, and
- wherein, each propulsion assembly includes an engine, a power source and an electronics node disposed within a nacelle, a plurality of rotor blades coupled to a rotor hub, and a thrust vectoring control assembly, the rotor hub coupled to the engine, the electronics node operable to communicate with the flight control system and the thrust vectoring control assembly operable to tilt the rotor hub and the rotor blades relative to a nacelle axis to change a direction of the thrust vector.
5 more elements
A method of operating an aircraft comprising:
- providing a flying frame including an airframe having first and second wing members with at least two pylons extending generally perpendicularly therebetween, a distributed propulsion system including at least two propulsion assemblies attached to the first wing and at least two propulsion assemblies attached to the second wing and a flight control system operably associated with the distributed propulsion system;
- selectively attaching the flying frame to a pod assembly;
- independently controlling a rotor speed and a thrust vector of each of the propulsion assemblies with the flight control system;
- lifting the pod assembly into the air in a vertical takeoff and landing mode of the aircraft;
- transitioning the aircraft between the vertical takeoff and landing mode and a forward flight mode;
- and
- transporting the pod assembly in the forward flight mode of the aircraft;
- wherein, the flying frame is operable for flight both with the pod assembly and without the pod assembly;
- and
- wherein, each propulsion assembly includes an engine, a power source and an electronics node disposed within a nacelle, a plurality of rotor blades coupled to a rotor hub, and a thrust vectoring control assembly, the rotor hub coupled to the engine, the electronics node operable to communicate with the flight control system and the thrust vectoring control assembly operable to tilt the rotor hub and the rotor blades relative to a nacelle axis to change a direction of the thrust vector.
7 more elements
Dependencies are inferred from the claim text.