Aircraft brake actuator thermal insulator and tangential movement compensator
AssigneeHoneywell International Inc.
InventorsJames N. Quitmeyer, Donald J. Christensen, Kellan P. Geck
Life of this patent
Estimating the term…
Abstract
An aircraft brake actuation system includes an actuator for selectively moving to a position that corresponds to a commanded brake force. A cap assembly is coupled to the end of the actuator and is configured to engage an aircraft brake element and supply the commanded brake force to one or more aircraft wheels. The cap assembly is constructed of a low thermal conductivity material and has thermal resistance grooves formed therein. The cap assembly is also configured to compensate for certain undesired tangential movements that may occur during an aircraft brake cycle.
Claims26
An aircraft brake actuation system, comprising:
- a control circuit configured to selectively supply brake force motor command signals representative of a commanded brake force;
- a motor coupled to receive the brake force motor command signals from the control circuit and operable, in response thereto, to supply a rotational drive force;
- an actuator coupled to receive the rotational drive force from the motor and configured, upon receipt thereof, to move to a position that corresponds to the commanded brake force;
- and
- a cap assembly coupled to the actuator and configured to engage an aircraft brake element and supply the commanded brake force thereto, the cap assembly including:
- a main body having a first end and a second end, the main body first end coupled to the actuator, the main body second end having a cavity formed therein, the cavity including at least a first end and an opposed second end,
- a plurality of roller elements disposed within the cavity,
- a spring disposed within the cavity proximate the cavity first end, the spring configured to bias the roller elements toward the cavity second end, and
- a cover movably coupled to the main body and at least partially enclosing the cavity, the cover coupled to one or more of the roller elements and having an inner surface and an opposed outer surface, the inner surface facing the roller elements and the outer surface configured to engage the aircraft brake element.
An actuator assembly, comprising:
- a motor configured to supply a rotational drive force;
- an actuator coupled to receive the rotational drive force from the motor and configured, upon receipt thereof, to translate;
- and
- a cap assembly coupled to the actuator and configured to translate therewith, the cap assembly including:
- a main body having a first end and a second end, the main body first end coupled to the actuator, the main body second end having a cavity formed then the cavity including at least a first end and an opposed second end,
- a plurality of roller elements disposed within the cavity,
- a spring disposed within the cavity proximate the cavity first end, the spring configured to bias the roller elements toward the cavity second end, and
- a cover movably coupled to the main body and enclosing the cavity, the cover coupled to one or more of the roller elements and having an inner surface facing the roller elements and an opposed outer surface.
A cap assembly for selectively engaging an aircraft brake element, comprising:
- a main body having a first end and a second end, the main body first end adapted to couple to an actuator, the main body second end having a cavity formed therein, the cavity including at least a first end and an opposed second end;
- a plurality of roller elements disposed within the cavity,
- a spring disposed within the cavity proximate the cavity first end, the spring configured to bias the roller elements toward the cavity second end;
- and
- a cover movably coupled to the main body and enclosing the cavity, the cover coupled to one or more of the roller elements, and having an inner surface and an opposed outer surface, the inner surface facing the roller elements and the outer surface configured to engage the aircraft brake element.
Dependencies are inferred from the claim text.