Rudder and brake pedal assembly

Patent metadata

Field	Value
Publication number	US-11396362-B2
Application number	US-201916672164-A
Country	US
Kind code	B2
Filing date	Nov 1, 2019
Priority date	Nov 1, 2019
Publication date	Jul 26, 2022
Grant date	Jul 26, 2022

Abstract

An airplane rudder and brake pedal assembly includes a rudder arm assembly having one rudder arm with first upper and lower arm portions, and another rudder arm with second upper and lower arm portions. The rudder arm assembly is assembled to a beam at an intersection of the first upper and lower arm portions, and an intersection of the second upper and lower arm portions. The first and second rudder arms are configured to rotate about the beam at the intersection. The rotation of the first and second rudder arms is configured to adjust control surfaces that control a yaw axis of the airplane. A brake pedal is attached to the first and second lower arm portions. Rotation of the brake pedal brakes the airplane. A rotary sensor is assembled to the brake pedal and the lower arm portion, and configured to determine an extent of the brake pedal rotation.

First claim

What is claimed is:

1. 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 brake pedal attached to an end of at least one of the first and second lower arm portions at an attachment point, wherein rotation of the brake pedal at the attachment point operates the wheel brakes of the airplane; and
a rotary sensor assembled to both the brake pedal and the lower arm portion at the attachment point, the rotary sensor configured to determine an extent of the brake pedal rotation; and
wherein the rotary sensor is an on-axis rotary sensor comprising:
a sensor with an input gear and an idler gear fixed to the lower arm portion at the attachment point;
an internal sector gear fixed to the brake pedal, the idler gear disposed between and engaging the input gear, on a first side, and engaging the internal sector gear on a second side opposite the first side, such that rotation of the brake pedal causes the internal sector gear to travel a distance along the idler gear and the input gear, the distance being proportional to the extent of the brake pedal rotation.

2. 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 brake pedal attached to an end of at least one of the first and second lower arm portions at an attachment point, wherein rotation of the brake pedal at the attachment point operates the wheel brakes of the airplane; and
a rotary sensor assembled to both the brake pedal and the lower arm portion at the attachment point, the rotary sensor configured to determine an extent of the brake pedal rotation;
wherein the brake pedal is biased to a normal position by one or more springs attached to the brake pedal, and further comprising a third spring coupled to the rotary sensor, the third spring configured to bias the brake pedal to the normal position in the event of a failure of the one or more springs.

3. 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 brake pedal attached to an end of at least one of the first and second lower arm portions at an attachment point, wherein rotation of the brake pedal at the attachment point operates the wheel brakes of the airplane;
a rotary sensor assembled to both the brake pedal and the lower arm portion at the attachment point, the rotary sensor configured to determine an extent of the brake pedal rotation; and
a trim mechanism operated by a motor, the trim mechanism configured to control a neutral position of the rudder arm assembly, thereby controlling the control surfaces used to trim the airplane.

4. The rudder and brake pedal assembly of claim 3 , wherein the trim mechanism comprises a first worm screw configured to rotate synchronously to drive a first worm wheel, wherein movement of the first worm wheel adjusts the control surfaces used to trim the airplane.

5. The rudder and brake pedal assembly of claim 4 , wherein the trim mechanism comprises a second redundant worm screw parallel to the first worm screw and a second redundant worm wheel parallel to the first worm wheel, wherein movement of the second worm wheel adjusts the control surfaces used to trim the airplane.

6. The rudder and brake pedal assembly of claim 3 , further comprising a centering mechanism configured to return the first and second rudder arms and attached brake pedals to a neutral position determined by the trim mechanism.

7. The rudder and brake pedal assembly of claim 6 , wherein the centering mechanism comprises either one or more springs which bias the first and second rudder arms and attached brake pedals to the neutral position, or a motor configured to bias the first and second rudder arms and attached brake pedals to the neutral position.

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 brake pedal attached to an end of at least one of the first and second lower arm portions at an attachment point, wherein rotation of the brake pedal at the attachment point operates the wheel brakes of the airplane; and
a rotary sensor assembled to both the brake pedal and the lower arm portion at the attachment point, the rotary sensor configured to determine an extent of the brake pedal rotation;
wherein a brake pedal assembly includes the brake pedal, and a brake sensor with a sensor cord and connector such that by connecting or disconnecting the sensor cord and connector, the entire brake pedal assembly can be attached to or removed from the lower arm portion.

9. 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 th

Assignees

• Voiles Jeffrey T
• Stachniak Darryl S
• Romana Roy
• Woodward Inc

Inventors

• Voiles Jeffrey T
• Stachniak Darryl S
• Romana Roy

Classifications

• G05G13/00

  Manually-actuated control mechanisms provided with two or more controlling members and also two or more controlled members (interlocking G05G5/08) · CPC title

• G05G9/02

  the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only · CPC title

• B64C13/503

  Fly-by-Wire · CPC title

• B64C13/50

  using electrical energy · CPC title

• B64C13/08

  Trimming zero positions · CPC title