Patent ID: 11919623
Assignee: WOODWARD, INC.
Field: Transport (Mechanical engineering)
Classification: CPC B  G | IPC B

Claim 7:
8. A rudder and brake pedal assembly for an airplane, the assembly comprising:
a rudder arm assembly having a first rudder arm with a first upper arm portion coupled to a first lower arm portion, and having a second rudder arm with a second upper arm portion coupled to a second lower arm portion, the rudder arm assembly being assembled to a beam at an intersection of the first upper and lower arm portions, and at an intersection of the second upper and lower arm portions, the first and second rudder arms configured to rotate about the beam at the intersection, the rotation of the first and second rudder arms configured to adjust those control surfaces used to control a yaw axis of the airplane;
a bellcrank configured to rotate about a centering hub shaft, the bellcrank having a first end on a first side of the centering hub shaft, and a second end on a second side of the centering hub shaft opposite the first side, the first end being operatively coupled to the first upper arm portion and the second end being operatively coupled to the second upper arm portion, the bellcrank operating such that when the first rudder arm is rotated in a first direction, the second rudder arm is rotated to the same degree as the first rudder arm but in a second direction opposite the first direction, the bellcrank being further configured to maintain a fixed position during adjustment of the rudder arm assembly to adjust a position of a brake pedal attached to an end of at least one of the first and second lower arm portions;
a brake pedal assembly having a brake pedal and position sensor to sense a position of the brake pedal, wherein the brake pedal is attached to the first or second rudder arm;
a position-sensing mechanism for sensing a position of the first or second rudder arm;
a trim mechanism coupled to the first and second rudder arms, the trim mechanism configured to adjust those control surfaces used to trim the airplane;
a centering mechanism configured to return the first and second rudder arms to a neutral position;
wherein the brake pedal assembly, trim mechanism, centering mechanism, and position-sensing mechanism are integrated into a single device configured to be positioned below a cockpit instrument panel; and
wherein the bellcrank maintains a fixed position relative to the airplane during adjustment of the rudder arm assembly.