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US 12,589,868 B2Granted
Blade position control system
AssigneeTextron Innovations Inc.
InventorsLancer Drake Halcom, Kyle Thomas Cravener
Life of this patent
Estimating the term…
Abstract
An aircraft that has a blade position control system (BPCS). The BPCS includes an actuator, a multilobe component configured for at least one of longitudinal movement along a mast axis as a function of actuation of the actuator and rotational movement relative to the mast axis as a function of actuation of the actuator. Movement of the multilobe component selectively restricts at least one of pitch movement and folding of a plurality of rotor blades.
Claims17
A blade position control system (BPCS), comprising:
- an actuator;
- a multilobe component configured for at least one of longitudinal movement along a mast axis as a function of actuation of the actuator and rotational movement relative to the mast axis as a function of actuation of the actuator;
- wherein movement of the multilobe component selectively restricts folding of a plurality of rotor blades;
- and
- wherein the actuator is disposed relatively more outboard along the mast axis as compared to the multilobe component.
2 more elements
A method, comprising:
- providing a foldable rotor blade configured for selectively rotating about a pitch axis;
- disposing a multilobe component along a mast axis of a proprotor assembly;
- and
- operating an actuator to move the multilobe component along the mast axis to change a restriction associated with folding the rotor blade;
- wherein the actuator is disposed relatively more outboard along the mast axis as compared to the multilobe component.
2 more elements
An aircraft, comprising:
- a blade position control system (BPCS), comprising:
- an actuator;
- a multilobe component configured for at least one of longitudinal movement along a mast axis as a function of actuation of the actuator and rotational movement relative to the mast axis as a function of actuation of the actuator;
- wherein movement of the multilobe component selectively restricts folding of a plurality of rotor blades;
- and
- wherein the actuator is disposed relatively more outboard along the mast axis as compared to the multilobe component.
3 more elements
Dependencies are inferred from the claim text.