Automatic flight control system having unified graphic mistrim indicator

Claim 2

An improved automatic flight control system having unified graphic mistrim indicator comprising: a flight control computer for monitoring the position and status of a plurality of control surface servos; a single mistrim indicator, for simultaneously displaying the pitch, roll and yaw mistrim conditions of the aircraft; a plurality of connectors, coupling the mistrim indicator and the flight control computer; and, said mistrim indicator including a fixed reference frame with a movable reference bar disposed completely within the reference frame when said aircraft is in a proper trimmed configuration and movable outside the reference frame when the aircraft is in any combination of a pitch, roll or yaw mistrim condition.

Claim 3

A flight control system comprising: a rudder servo, for controlling position of an aircraft rudder, in response to a rudder position signal; an aileron servo, for controlling the position of an aircraft aileron, in response to an aileron position signal; an elevator servo, for controlling the position of an aircraft elevator, in response to an elevator position signal; a flight control computer coupled with said rudder servo, said aileron servo, and said elevator servo for generating rudder position signals, aileron position signals, and elevator position signals, which are representative of the position of a rudder, an aileron, and an elevator respectively; a mistrim indicator, coupled with said flight control computer, for receiving said rudder position signals, aileron position signal, and elevator position signal; said indicator including a fixed reference marker representative of an aircraft in proper trim and a movable marker, having a central point therein; and, said movable marker representative of the current trim condition of the aircraft and responding to said rudder position signal, aileron position signal, and said elevator position signal, so that, said movable marker is simultaneously caused to move horizontally in response to changes in said rudder position signal, rotate about said central point in response to changes in said aileron position signal, and move vertically in response to said elevator position signal.

Claim 4

A flight control system comprising: a rudder servo, for controlling position of an aircraft rudder, in response to a rudder position signal; an aileron servo, for controlling the position of an aircraft aileron, in response to an aileron position signal; an elevator servo, for controlling the position of an aircraft elevator, in response to an elevator position signal; a flight control computer coupled with said rudder servo, said aileron servo, and said elevator servo for generating rudder position signals, aileron position signals, and elevator position signals, which are representative of the position of a rudder, an aileron, and an elevator respectively; a mistrim indicator, coupled with said flight control computer, for receiving said rudder position signals, aileron position signal, and elevator position signal; said indicator including a fixed reference marker representative of an aircraft in proper trim and a movable marker, having a central point therein; and, said movable marker representative of the current trim condition of the aircraft and responding to said rudder position signal, aileron position signal, and said elevator position signal, so that, said movable marker is simultaneously caused to move horizontally in response to changes in said rudder position signal, rotate about said central point in response to changes in said aileron position signal, and move vertically in response to said elevator position signal.

Claim 5

A flight control system of claim 2, wherein said fixed reference marker is a rectangular frame.

Claim 6

A flight control system of claim 3, wherein said movable marker is a rectangular bar, capable of being positioned inside said rectangular frame.

Claim 7

A flight control system of claim 2, wherein said fixed reference marker is an outline of two intersecting, perpendicular lines.

Claim 8

A flight control system of claim 5, wherein said movable marker is a rectangular cross.

Claim 9

A flight control system of claim 2, wherein said fixed reference marker is representative of a shape of a fixed wing aircraft.

Claim 10

A flight control system of claim 7, wherein said movable marker is a representation of a shape of a fixed wing aircraft.

Claim 11

A flight control system of claim 2, wherein said fixed reference marker is a polygon.

Claim 12

A flight control system of claim 9, wherein said movable marker is a second polygon capable of being positioned inside the first polygon.

Claim 13

A flight control system of claim 2, wherein said fixed reference marker is elliptical in shape.

Claim 14

A flight control system of claim 11, wherein said movable marker is elliptical in shape.

Claim 15

A flight control system comprising: a rudder servo, for controlling position of an aircraft rudder, in response to a rudder position signal; an aileron servo, for controlling the position of an aircraft aileron, in response to an aileron position signal; an elevator servo, for controlling the position of an aircraft elevator, in response to an elevator position signal; a flight control computer coupled with said rudder servo, said aileron servo, and said elevator servo for generating rudder position signals, aileron position signals, and elevator position signals, which are representative of the position of a rudder, an aileron, and an elevator respectively; a mistrim indicator directly coupled with said flight control computer, for receiving said rudder position signals, aileron position signal, and elevator position signal; said indicator including a fixed reference marker representative of an aircraft in proper trim and a movable marker, having a central point therein; and, said movable marker representative of the current trim condition of the aircraft and responding to said rudder position signal, aileron position signal, and said elevator position signal, so that, said movable marker is simultaneously caused to move horizontally in response to changes in said rudder position signal, rotate about said central point in response to changes in said aileron position signal, and move vertically in response to said elevator position signal.

Claim 16

A flight control system comprising: a rudder servo, for controlling position of an aircraft rudder, in response to a rudder position signal; an aileron servo, for controlling the position of an aircraft aileron, in response to an aileron position signal; an elevator servo, for controlling the position of an aircraft elevator, in response to an elevator position signal; a flight control computer coupled with said rudder servo, said aileron servo, and said elevator servo for generating rudder position signals, aileron position signals, and elevator position signals, which are representative of the position of a rudder, an aileron, and an elevator respectively; a mistrim indicator directly coupled with said flight control computer, for receiving said rudder position signals, aileron position signal, and elevator position signal; said indicator including a fixed reference marker representative of an aircraft in proper trim and a movable marker, having a central point therein; and, said movable marker representative of the current trim condition of the aircraft and responding to said rudder position signal, aileron position signal, and said elevator position signal, so that, said movable marker is simultaneously caused to move horizontally in response to changes in said rudder position signal, rotate about said central point in response to changes in said aileron position signal, and move vertically in response to said elevator position signal.

Claim 17

A flight control system of claim 13, wherein said mistrim indicator comprises a video display.

Claim 18

A flight control system of claim 14, wherein said video display is a cathode ray tube.

Claim 19

A flight control system of claim 14, wherein said video display is a liquid crystal display.

Claim 20

A flight control system of claim 14, wherein said fixed reference marker is a polygon.

Claim 21

A flight control system of claim 17, wherein said movable marker is a polygon.

Claim 22

A flight control system of claim 14, wherein said fixed reference marker is an ellipse.

Claim 23

A flight control system of claim 19, wherein said movable marker is an ellipse.