Direct side force control device

Claim 5

In an airplane which includes a rudder and opposite-wing-mounted split-type speed brakes, control means operable to perform a flat turn comprising: a. electronic means interconnecting the control means for said rudder with the control means for said speed brakes, said speed brake control means being operable to actuate said speed brakes so that said speed brakes open and close differentially for yaw-producing moments, b. a manually controlled switch operable to actuate said electronic interconnecting means from an inoperable to an operable condition, c. a pilot''s turn controller connected to said electronic interconnecting means, d. and side force control means in said interconnecting means responsive to said turn controller when said interconnecting means is operable to differentially operate said speed brakes in one yaw-producing direction and to deflect said rudder in the opposite yaw-producing direction, e. whereby the lateral side force on said airplane from said rudder deflection combined with an initial yawing motion started by said speed brakes differential operation can produce a wings-level flat turn of said airplane.

Claim 6

In an airplane which includes a rudder and opposite-wing-mounted split-type speed brakes, control means operable to perform a flat turn comprising: a. electronic means interconnecting the control means for said rudder with the control means for said speed brakes, said speed brake control means being operable to actuate said speed brakes so that said speed brakes open and close differentially for yaw-producing moments, b. a manually controlled switch operable to actuate said electronic interconnecting means from an inoperable to an operable condition, c. a pilot''s turn controller connected to said electronic interconnecting means, d. and side force control means in said interconnecting means responsive to said turn controller when said interconnecting means is operable to differentially operate said speed brakes in one yaw-producing direction and to deflect said rudder in the opposite yaw-producing direction, e. whereby the lateral side force on said airplane from said rudder deflection combined with an initial yawing motion started by said speed brakes differential operation can produce a wings-level flat turn of said airplane.

Claim 7

Apparatus in accordance with claim 3 wherein said split-type speed brakes comprise a pair of split-flap type brakes conforming to the trailing edge of each of the left and right wing portions of said airplane when said speed brakes are closed.

Claim 8

Apparatus in accordance with claim 3 wherein said differential actuation of said speed brakes includes opening of the speed brakes on only one side of said airplane if the other side speed brakes are initially closed.

Claim 9

Apparatus in accordance with claim 3 wherein said side force control means comprises a. a speed brake position comparator, b. left and right speed brake control actuators having their inputs connected respectively to said position comparator, c. left and right speed brake position transducers having their outputs respectively connected back to said position comparator, and d. means connecting the output of said position comparator to the control means for said rudder.

Claim 10

Apparatus in accordance with claim 6 wherein said rudder control means includes a sideslip angle sensor and a yaw damper.

Claim 11

Apparatus in accordance with claim 6 wherein said speed brake position comparator includes amplifier means for rEgulating rudder movement to an amount responsive to speed brake position to cancel the yaw moment produced by the initial differential movement of said speed brakes, thus leaving an unbalanced lateral side force on said airplane due to rudder deflection which produces a flight path direction change accompanying the initial yaw, whereby said wings-level flat turn is accomplished.