Flight control mechanical backup system
First Claim
1. A mechanical back-up control system for mechanically coupling an operator control apparatus with moveable elements adapted to control positioning of a control member upon failure of an electrical control system which under normal operating conditions controls positioning of the control member in response to the operator control apparatus, said mechanical back-up control system comprising:
- positioning apparatus which during normal operation of the electrical control system is responsive to control signals from the electrical control system to continuously maintain positioning of said moveable elements substantially in phase with said control member;
linkage which is positioned in response to positioning of said operator control apparatus and which is adapted to be coupled with said moveable elements; and
a coupler for coupling said linkage with said movable elements upon failure of the electrical control system, the coupler under normal operating conditions permitting movement of said linkage without transmitting said movement to said movable elements.
3 Assignments
0 Petitions
Accused Products
Abstract
A robust mechanical reversion system which provides the ability to fly and land in the absence of any fly-by-wire controls and which is transparent to the pilot during normal operation. The described invention provides a mechanism which includes redundant linear variable differential transmitters (LVDT) which generates a transmitted signal in proportion to the displacement of the control apparatus in the cockpit. The signal is fed to the flight control computer which determines the magnitude of the change represented by the signal and in turn, commands both the control surface servo actuators as well as an electrical mechanical servo actuator (EMA) located in close proximity to the flight compartment and coupled to the mechanical system to move in proportion to the change.
An Electromagnetic Actuator drives the disconnected mechanical system in synchronization with the position of the cockpit controls in the fly-by-wire mode for a given control surface each time the servo actuator(s) for the control surface are electrically commanded by the flight computer. This causes the mechanical system to remain in phase with the position of the control elements as if connected thereto. In the event of a failure of the fly-by-wire system the mechanical system is automatically coupled into the control system through locking actuators which release a coupling mechanism including a interlocking pin, locking cams, clutch or other engagement device and clamps or locks the pilots input to the mechanical control loop thus providing direct mechanical control to the surface actuators with very little transient effects.
75 Citations
25 Claims
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1. A mechanical back-up control system for mechanically coupling an operator control apparatus with moveable elements adapted to control positioning of a control member upon failure of an electrical control system which under normal operating conditions controls positioning of the control member in response to the operator control apparatus, said mechanical back-up control system comprising:
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positioning apparatus which during normal operation of the electrical control system is responsive to control signals from the electrical control system to continuously maintain positioning of said moveable elements substantially in phase with said control member; linkage which is positioned in response to positioning of said operator control apparatus and which is adapted to be coupled with said moveable elements; and a coupler for coupling said linkage with said movable elements upon failure of the electrical control system, the coupler under normal operating conditions permitting movement of said linkage without transmitting said movement to said movable elements. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12)
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13. A mechanical bypass control system for bypassing a flight computer control system responsive to operator control which drives at least one control surface comprising:
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a. means for positioning said control surface, adapted for changing position responsive to commands from said flight computer control system, b. mechanical linkage adapted for coupling operator control to said control surface, c. means for moving said mechanical linkage generally in phase with said positioning means in response to commands from said flight computer control system during normal operation thereof, and d. means for selectively engaging and disengaging said mechanical linkage with said control surface positioning means. - View Dependent Claims (14, 15, 16, 17, 18, 19, 20)
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21. A mechanical bypass control system having mechanical linkage for bypassing an electrical control system activated by cockpit controls which controls at least one moveable control surface comprising:
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a. at least one control surface actuator coupled to actuator control apparatus responsive to said electrical control system for positioning said control surface which control surface is adapted for changing position; b. at least one linkage actuator responsive to said electrical control system coupled to said mechanical linkage and adapted to move said mechanical linkage generally in phase with the position of said control surface during normal operation of the electrical control system; c. at least one locking apparatus for selectively engaging and disengaging said mechanical linkage with said cockpit controls; and d. at least one interlock apparatus for selectively coupling said mechanical linkage to said control surface actuator on failure of said electrical control system. - View Dependent Claims (22, 23, 24, 25)
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Specification