Transmission of a control force
AssigneeEADS Deutschland GmbH
InventorJost Seifert
Life of this patent
Estimating the term…
Abstract
A control force transmission arrangement for an aircraft is provided. A transmission device has a first and a second force transmission point, and a coupling unit disposed between them. The coupling unit has a first and a second side element and a connecting element. The first and the second side elements are each connected to the first force transmission point and to the connecting element. At least the first side element has an element for altering the length of the side element. The second force transmission point is provided on the connecting element and is adjustable at least between a first and a second position.
Claims10
A transmission device for transmission of a control force in a vehicle, comprising:
- a first force transmission point;
- a second force transmission point;
- and
- a coupling unit disposed between the first and the second force transmission points,
- wherein the coupling unit has a first side element, a second side element, and a connecting element,
- wherein the first and the second side elements are each rotatably connected at one end to the first force transmission point and are each connected at a respective other end to the connecting element at a respective first or second connection point,
- wherein the first and the second connection points are spaced apart from one another on the connecting element,
- wherein at least the first side element has an element configured to alter a length of the first side element between the first force transmission point and the first connection point, and
- wherein the second force transmission point is provided on the connecting element and is adjustable at least between a first and a second position, wherein the second force transmission point in the first position is disposed in the region of the first connection point and in the second position is disposed in the region of the second connection point.
An aircraft with a control system for actuating a control component;
- wherein the control system comprises:
- an input device configured for input of a control command;
- control force generating device;
- a transmission system configured for transmission of the control force;
- and
- at least one aeronautical control component,
- wherein the transmission system has at least one transmission device comprising
- a first force transmission point;
- a second force transmission point;
- and
- a coupling unit disposed between the first and the second force transmission points,
- wherein the coupling unit has a first side element, a second side element, and a connecting element,
- wherein the first and the second side elements are each rotatably connected at one end to the first force transmission point and are each connected at a respective other end to the connecting element at a respective first or second connection point, wherein the first and the second connection points are spaced apart from one another on the connecting element,
- wherein at least the first side element has an element configured to alter a length of the side element,
- wherein the second force transmission point is provided on the connecting element and is adjustable at least between a first and a second position, wherein the second force transmission point in the first position is disposed in the region of the first connection point and in the second position is disposed in the region of the second connection point, and
- wherein the aircraft has an at least partially fly-by-wire flight control.
Dependencies are inferred from the claim text.