초록 ▼

A pedal operated apparatus controls an aircraft rudder during flight using a mechanical linkage and controls a nose wheel power steering system while the aircraft is on the ground. The apparatus includes a pair of foot pedals operatively connected to the rudder and also connected to the power steeri

A pedal operated apparatus controls an aircraft rudder during flight using a mechanical linkage and controls a nose wheel power steering system while the aircraft is on the ground. The apparatus includes a pair of foot pedals operatively connected to the rudder and also connected to the power steering system. Springs are operatively connected to the pedals only when the aircraft is on the ground to center the nose wheel after a turn. The springs are operatively disconnected when the aircraft is in flight.

대표청구항 ▼

1. An apparatus for operating an aircraft nose wheel steering mechanism including: right and left pedals having a neutral position and being operatively interconnected so that forward displacement of one pedal results in rearward displacement of the other,a steering assembly connected between the pe

1. An apparatus for operating an aircraft nose wheel steering mechanism including: right and left pedals having a neutral position and being operatively interconnected so that forward displacement of one pedal results in rearward displacement of the other,a steering assembly connected between the pedals and a nose wheel and operable to turn the nose wheel either right or left from a centered position in response to forward displacement of either the right or left pedal, respectively,a biasing assembly operatively connected to the pedals and urging the pedals to their neutral position, said neutral position corresponding to the centered position of the nose wheel, whereby when a forwardly displaced pedal is released, the biasing assembly returns the pedals to their neutral position and causes the nose wheel to return to its centered position, and wherein said biasing assembly is only operable to urge the pedals to the neutral position when the aircraft is on the ground, wherein the biasing assembly includes first and second springs, each spring being connected to a respective pedal so that the springs resist forward displacement of their respective pedal, and wherein each spring exerts a spring force resisting pedal movement until the spring is completely compressed and, after the spring is completely compressed, the compressed spring no longer exerts further spring force resisting pedal movement. 2. The apparatus as defined in claim 1 wherein the steering assembly includes a transducer for sensing a direction and amount of pedal displacement. 3. An apparatus for operating an aircraft nose wheel steering mechanism including: right and left pedals having a neutral position and being operatively interconnected so that forward displacement of one pedal results in rearward displacement of the other,a steering assembly connected between the pedals and a nose wheel and operable to turn the nose wheel either right or left from a centered position in response to forward displacement of either the right or left pedal, respectively,a biasing assembly operatively connected to the pedals and urging the pedals to their neutral position, said neutral position corresponding to the centered position of the nose wheel, whereby when a forwardly displaced pedal is released, the biasing assembly returns the pedals to their neutral position and causes the nose wheel to return to its centered position, and wherein said biasing assembly is only operable to urge the pedals to the neutral position when the aircraft is on the ground, wherein the biasing assembly includes first and second springs, each spring being connected to a respective pedal so that the springs resist forward displacement of their respective pedal, and wherein the springs cooperate to exert a first biasing force on the pedals in a first region of pedal movement adjacent a neutral position, and cooperate to exert a second biasing force on the pedals in a second region of pedal movement remote from said neutral position and distinct from said first region, wherein said first biasing force is greater than said second biasing force. 4. The apparatus as defined in claim 3, wherein the first biasing force is generally twice the second biasing force. 5. The apparatus as defined in claim 4, further comprising: a sensor for determining that the aircraft is on the ground;a lever; and,a lever locking and unlocking assembly;wherein the lever is placed in a locked condition by the locking and unlocking assembly in response to a signal from the sensor indicating that the aircraft is on the ground, and wherein the lever is otherwise in an unlocked condition. 6. The apparatus as defined in claim 5, wherein the biasing assembly is secured to the lever. 7. An apparatus for steering an aircraft, including: right and left pedals having a neutral position and being operatively interconnected so that forward displacement of one pedal results in rearward displacement of the other,a steering assembly connected between the pedals and a nose wheel and a rudder and operable to turn the nose wheel and/or the rudder either right or left from a centered position in response to forward displacement of either the right or left pedal, respectively,a biasing assembly having springs with first ends operatively connected to the pedals and being operable to urge the pedals toward their neutral position, said neutral position corresponding to the centered position of the nose wheel and rudder;a lever to which second ends of the springs of the biasing assembly are attached; and,a lever locking and unlocking assembly;wherein the lever is placed in a locked condition by the locking and unlocking assembly when the aircraft is determined to be on the ground so as to enable steering of the nose wheel against biasing forces of the biasing assembly, and wherein the lever is placed in an unlocked condition by the lever locking and unlocking assembly and thereby disabling the biasing assembly when the aircraft is determined to be airborne so as to permit steering of the aircraft via the rudder without working against the biasing forces of the biasing assembly;and wherein, when the aircraft is on the ground and a forwardly displaced pedal is released, the biasing assembly returns the pedals to their neutral position and the steering assembly causes the nose wheel to return to its centered position. 8. The apparatus as defined in claim 7, wherein the steering assembly includes a transducer for sensing a direction and amount of pedal displacement. 9. The apparatus as defined in claim 8, wherein the springs of the biasing assembly include first and second springs, each spring being operatively connected to a respective pedal so that the springs resist forward displacement of their respective pedal, wherein each spring exerts a spring force resisting pedal movement until the spring is completely compressed and, after the spring is completely compressed, the compressed spring no longer exerts further spring force resisting pedal movement. 10. The apparatus according to claim 9, wherein the springs cooperate to exert a first biasing force on the pedals in a first region of pedal movement adjacent a neutral position, and cooperate to exert a second biasing force on the pedals in a second region of pedal movement remote from said neutral position and distinct from said first region, wherein said first biasing force is greater than said second biasing force. 11. The apparatus as defined in claim 10, wherein the first biasing force is generally twice the second biasing force. 12. An apparatus for operating an aircraft rudder and nose wheel steering mechanism comprising: right and left pedals having a neutral position and being operatively interconnected so that forward displacement of one pedal results in rearward displacement of the other,a mechanical linkage operatively connecting the pedals to the rudder,a transducer for sensing pedal movement and providing an electrical signal that is used to actuate a drive assembly to turning the aircraft nose wheel in either direction from a centered position,a lever having a central pivot axis and having an unlocked condition wherein the lever is free to turn about its axis and a fixed condition wherein the lever is locked against turning movement,first and second springs, said first spring being operatively connected between a first end of said lever and the first pedal and said second spring being operatively connected between the second end of said lever and said second pedal so that when the lever is locked springs resist forward displacement of either pedal and when the lever is unlocked and freely turned without resistance from the springs, anda lever locking and unlocking assembly that is operable to unlock the lever when the aircraft is in flight and to lock the lever in its fixed position when the aircraft is on the ground. 13. The apparatus as defined in claim 12, wherein the lever has a tubular hub that defines a downwardly facing detent, and wherein the lever locking and unlocking assembly includes: a slide movable in a vertical path of travel between an upward position wherein it engages the detent to lock the lever and a downward retracted position spaced away from the detent so that the lever is unlocked,a spring urging the slide upward to the locking position, anda drive device for selectively forcing the slide downwardly against the force of the spring to the retracted unlocking position. 14. The apparatus as defined in claim 13, wherein the spring is a helical spring coaxial with the hub and the slide. 15. The apparatus as defined in claim 14, wherein the means for retracting the slide comprises: a rotor mounted coaxially with the hub,a rotary actuator adapted to turn the rotor in angular increments, anda conversion device for converting angular movement of the rotor to linear movement of the slide of the slide. 16. The apparatus as defined in claim 15, wherein the conversion device includes: a tubular spindle that supports the hub for pivotal movement thereon and that supports the slide, the spindle having a vertical guide formed in its tubular wall and the slide having radially extending guide elements extending through the tubular wall and engageable with the vertical guide,a support for means supporting the rotor for rotary movement within the spindle, the rotor having helical grooves formed therein and adapted to receive the guide elements of the slide,whereby angular movement of the rotor forces the guide elements downward against the force of the spring to disengage the slide from the detents in the hub and unlock the lever. 17. The apparatus as defined in claim 16, wherein the vertical guide includes a pair of opposed vertical slots extending through the tubular wall of the spindle. 18. The apparatus as defined in claim 17, wherein the guide elements in the slide comprise opposed pins extending radially inward through the slots in the spindle and into the helical grooves in the rotor. 19. The apparatus as defined in claim 3 further comprising: a lever; and,a lever locking and unlocking assembly for placing the lever in a locked condition when the aircraft is on the ground, and otherwise placing the lever in an unlocked condition, and further wherein the biasing assembly has springs with first ends operatively connected to the pedals and being operable to urge the pedals toward their neutral position, and second ends attached to the lever.