Optimized pitch and roll control apparatus for an aircraft
AssigneeThe Boeing Company
InventorsJOSEPH E. ELLIOTT, ANDREW SONES, JOHN STANDLEY
Life of this patent
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Abstract
An apparatus for controlling the pitch of an aircraft. The apparatus includes a horizontal control column extending from a control wheel horizontally towards a front wall of a cockpit. A pitch output link is connected to a downstream pitch control mechanism to transfer a force applied at the pitch output link to the downstream pitch control mechanism. A transfer assembly is connected to the horizontal control column and to the pitch output link. The transfer assembly translates a horizontal force applied to the horizontal control column to the pitch output link to provide the force applied to the downstream pitch control mechanism.
Claims20
An apparatus for control of aircraft pitch comprising:
- a horizontal control column extending from a control wheel horizontally towards a front wall of an aircraft cockpit;
- a pitch output link having a first pitch output link connection point and a second pitch output link connection point connected to a downstream pitch control mechanism, wherein the pitch output link is configured to transfer a force applied at the first pitch output link connection point to the downstream pitch control mechanism;
- and
- a transfer assembly connected to the horizontal control column and to the pitch output link at the first pitch output link connection point, wherein the transfer assembly configured to translate a horizontal force applied to the horizontal control column to the pitch output link.
An aircraft control console for controlling an aircraft comprising:
- a front instrument panel positioned to face a pilot when the aircraft control console is operating in an aircraft cockpit;
- and
- a pitch control apparatus including:
- a horizontal control column extending at a downward angle from a control wheel then horizontally towards a front wall of the aircraft cockpit;
- a pitch output link having a first pitch output link connection point and a second pitch output link connection point connected to a downstream pitch control mechanism, the pitch output link configured to transfer a force applied at the first pitch output link connection point to the downstream pitch control mechanism;
- and
- a transfer assembly connected to the horizontal control column and to the pitch output link at the first pitch output link connection point, the transfer assembly configured to translate a horizontal force applied to the horizontal control column to the pitch output link.
An pitch control apparatus in an aircraft comprising:
- a horizontal control column extending from a control wheel under an aircraft instrument panel and through a cockpit fore wall in a direction substantially parallel to an aircraft cockpit floor;
- a linkage system attached to at least one aircraft structure point and to the horizontal control column, the linkage system configured to support the horizontal control column and to enable fore and aft movement of the horizontal control column substantially along a plane substantially parallel to the aircraft cockpit floor;
- and
- a pitch output link connected to transfer a first force received via fore and aft movement of the horizontal control column to a second force applied to a downstream pitch control mechanism configured to alter a pitch angle of the aircraft in response to the second force.
Dependencies are inferred from the claim text.