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US 9,317,042 B2Granted
Pitch feedback control splitting for helicopters with redundant actuators
AssigneeSikorsky Aircraft Corporation
InventorsAaron L. Greenfield, Ole Wulff, Matthew A. White
Life of this patent
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Abstract
Embodiments are directed to generating, by a processing device, a feedback command for an aircraft based on a reference input and an output response of the aircraft, and analyzing, by the processing device, the feedback command to allocate control to a plurality of control surfaces over a plurality of separate frequency bands.
Claims22
A method comprising:
- generating, by a processing device, a feedback command for an aircraft based on a difference between a reference input and an actual output response of the aircraft;
- analyzing, by the processing device, the feedback command to allocate control to a plurality of control surfaces over a plurality of separate frequency bands;
- applying an equivalence filter to the control that converts control of a first of the plurality of control surfaces into an equivalent amount of control in a second of the plurality of control surfaces to enable allocation over dynamically equivalent control surfaces;
- and
- applying an inversion of the equivalence filter to re-allocate control in an opposite or second direction.
2 more elements
An apparatus for use in a rotorcraft, the apparatus comprising:
- at least one processor;
- and
- memory having instructions stored thereon that, when executed by the at least one processor, cause the apparatus to:
- generate a feedback command for the rotorcraft based on a difference between a reference input and an actual output response of the rotorcraft;
- analyze the feedback command to allocate control to a plurality of control surfaces over a plurality of separate frequency bands;
- apply an equivalence filter to the control that converts control of a first of the surfaces into an equivalent amount of control in a second of the surfaces to enable allocation over dynamically equivalent control surfaces;
- and
- apply an inversion of the equivalence filter to re-allocate control in an opposite or second direction.
5 more elements
A co-axial rotorcraft comprising:
- a control computer configured to:
- generate a feedback command for the rotorcraft based on a difference between a reference input derived from a pilot command and an actual output response of the rotorcraft;
- analyze the feedback command to allocate a first portion of a control to an elevator control surface and a second portion of the control to a main rotor cyclic control surface;
- apply an equivalence filter to the control that converts control of the elevator control surface into an equivalent amount of control in the main rotor cyclic control surface to enable allocation over dynamically equivalent control surfaces;
- and
- apply an inversion of the equivalence filter to re-allocate control in an opposite or second direction.
3 more elements
Dependencies are inferred from the claim text.