Method and apparatus for limiting position servo authority

Claim 2

For use in a closed loop position servo system having input control signal S I , feedback signal S p , a signal S C indicative of a comparison between S I and S p , and an electromechanical actuator driven by an energizing signal S E , apparatus for limiting the authority of said actuator and having S C as input and providing S E as output, said apparatus comprising (i) first circuit means for providing a first component of S E wherein said first component is limited to a first predetermined constant value, (ii) second circuit means for providing a second component of S E wherein said second component is permitted to increase with time at least up to a second predetermined constant value, and (iii) third circuit means for combining said first and second components of S E .

Claim 3

Apparatus as defined in claim 1 including fourth circuit means for limiting S E to an absolute maximum predetermined constant value.

Claim 4

Apparatus as defined in claim 2 wherein said second circuit means comprises a closed loop circuit means for generating a signal S INT including (a) combinatorial means receiving a signal proportional to S INT and a second signal which is a function of S C , (b) comparator means receiving the combinatorial means output, and (c) integrator means receiving the comparator means output and providing S INT therefrom.

Claim 5

Apparatus for positioning an aircraft control surface in closed loop servo fashion in accordance with an input control signal S I comprising: electromechanical actuator means for moving said aircraft control surface; position feedback means for providing a feedback signal S p indicative of the position of said control surface; means for supplying a signal S C indicative of a comparison between S I and S p ; and actuator authority limiting means for converting S C into an actuator energizing signal such that for a predetermined step in S I occurring at a time t 0 , (i) the torque output TQ of said actuator cannot exceed, for time less than (t 0 + ΔT) where ΔT is a predetermined time interval, a predetermined value TQ 1 , and (ii) for time greater than (t 0 + ΔT), TQ can exceed TQ 1 .

Claim 6

Apparatus for positioning an aircraft control surface in closed loop servo fashion in accordance with an input control signal S I comprising: electromechanical actuator means for moving said aircraft control surface; position feedback means for providing a feedback signal S p indicative of the position of said control surface; means for supplying a signal S C indicative of a comparison between S I and S p ; and actuator authority limiting means for converting S C into an actuator energizing signal such that for a predetermined step in S I occurring at a time t 0 , (i) the torque output TQ of said actuator cannot exceed, for time less than (t 0 + ΔT) where ΔT is a predetermined time interval, a predetermined value TQ 1 , and (ii) for time greater than (t 0 + ΔT), TQ can exceed TQ 1 .

Claim 7

Apparatus as defined in claim 4 wherein said actuator authority limiting means further includes means for limiting TQ to an absolute maximum value of TQ 2 , where TQ 2 > TQ 1 .

Claim 8

In a position servo system of the type including electromechanical actuator means driven by an energizing signal S E , and means for developing from input and feedback signals a signal S C indicative of a comparison therebetween, improved circuit means receiving S C and providing S E therefrom comprising means for preventing the amplitude of S E from exceeding a limit which, in response to a predetermined input signal, varies in accordance with a predetermined function of time.

Claim 9

In a position servo system of the type including electromechanical actuator means driven by an energizing signal S E , and means for developing from input and feedback signals a signal S C indicative of a comparison therebetween, improved circuit means receiving S C and providing S E therefrom comprising means for preventing the amplitude of S E from exceeding a limit which, in response to a predetermined input signal, varies in accordance with a predetermined function of time.

Claim 10

Apparatus as defined in claim 6 wherein said limit increases, at least up to a predetermined maximum, in accordance with said predetermined function of time.

Claim 11

In a position servo system having electromechanical actuator means driven by an energizing signal S E , the method of limiting torque output of the electromechanical actuator comprising initially preventing S E from exceeding a first predetermined constant maximum and thereafter preventing S E from exceeding a maximum which increases with time from said first constant maximum to a second predetermined constant maximum.

Claim 12

In a position servo system having electromechanical actuator means driven by an energizing signal S E , the method of limiting torque output of the electromechanical actuator comprising initially preventing S E from exceeding a first predetermined constant maximum and thereafter preventing S E from exceeding a maximum which increases with time from said first constant maximum to a second predetermined constant maximum.

Claim 13

In an aircraft wherein a control surface is positioned by an actuator in accordance with a command, the method of limiting control surface position comprising initially preventing the actuator torque delivered to said control surface from exceeding a first predetermined constant maximum and thereafter preventing the actuator torque delivered from exceeding a maximum which increases with time from said first maximum at least up to a second predetermined constant maximum.

Claim 14

In an aircraft wherein a control surface is positioned by an actuator in accordance with a command, the method of limiting control surface position comprising initially preventing the actuator torque delivered to said control surface from exceeding a first predetermined constant maximum and thereafter preventing the actuator torque delivered from exceeding a maximum which increases with time from said first maximum at least up to a second predetermined constant maximum.

Claim 15

In a servo system of the type including electromechanical actuator means for delivering torque to an aircraft control surface in response to an actuator means energizing signal S E , and means for developing from input and feedback signals a signal S C indicative of a comparison therebetween, improved circuit means receiving S C and providing S E therefrom comprising means for initially preventing the actuator torque delivered to said control surface from exceeding a first predetermined constant maximum and thereafter preventing the actuator torque delivered from exceeding a maximum which increases with time from said first maximum at least up to a second predetermined constant maximum.

Claim 16

In a servo system of the type including electromechanical actuator means for delivering torque to an aircraft control surface in response to an actuator means energizing signal S E , and means for developing from input and feedback signals a signal S C indicative of a comparison therebetween, improved circuit means receiving S C and providing S E therefrom comprising means for initially preventing the actuator torque delivered to said control surface from exceeding a first predetermined constant maximum and thereafter preventing the actuator torque delivered from exceeding a maximum which increases with time from said first maximum at least up to a second predetermined constant maximum.