Control linkage

Abstract

Systems and methods for implementing control linkages that may be employed to produce synchronous motion in two adjacent controlled devices controlled by a common input. In one example implementation, a semi-rigid modified constant velocity (CV) joint control linkage may be provided that is laterally self-stabilizing. The modified constant velocity CV joint control linkage may include an input push rod assembly that is self-aligning, deflectable and of an adjustable length. The CV joint may be configured with a central cage that is allowed to skew to allow for alignment of the controlled devices.

1 . A control assembly for controlling two adjacent controllable devices, comprising:
 a first rotational joint comprising two first yoke uprights with a first yoke axle disposed therebetween and a first hinge axle oriented at a right angle to said first yoke axle, said first yoke axle being configured for coupling at a right angle to a first one of said controllable devices;   a second rotational joint comprising two second yoke uprights with a second yoke axle disposed therebetween and a second hinge axle oriented at a right angle to said second yoke axle, said second yoke axle being configured for coupling at a right angle to a second one of said controllable devices;   a cross-connection coupled between said first and second hinge axles of said first and second rotational joints, wherein said cross connection comprises a third hinge axle between said first and second hinge axles so that said control assembly produces synchronous motion in said first and second controllable devices in response to a single input control motion received at said third hinge axle of said cross connection, and so that said cross-connection is adjustable to produce differential motion between said first and second controllable devices; and   a self-aligning input push rod assembly having a first end coupled to said cross connection at said third hinge axle of said cross connection between said first and second hinge axles, and a second end configured for coupling to receive said control motion provided by a control input device;   wherein said first rotational joint is configured to rotate only in a single plane relative to said cross connection; and wherein said second rotational joint is configured to rotate in multiple planes relative to said cross connection.   
   
   
       2 . The control assembly of  claim 1 , wherein said first and second rotational joints each comprise a universal joint yoke assembly. 
   
   
       3 . The control assembly of  claim 1 , further comprising a push rod deflection mechanism configured to laterally deflect said input push rod assembly. 
   
   
       4 . The control assembly of  claim 3 , wherein said first and second rotational joints each comprise a universal joint yoke assembly. 
   
   
       5 . The control assembly of  claim 1 , wherein said first rotational joint is configured for coupling to a first one of said controllable devices that is a control surface of an aircraft; and wherein said second rotational joint is configured for coupling to a second one of said controllable devices that is a control surface of an aircraft. 
   
   
       6 . The control assembly of  claim 5 , wherein said adjacent controllable devices comprise dual adjacent elevator surfaces of a T-tail aircraft. 
   
   
       7 . The control assembly of  claim 1 , wherein said first yoke axle is configured for coupling at a right angle to a hinge line of said first one of said controllable devices; wherein said second yoke axle is configured for coupling at a right angle to a hinge line of said second one of said controllable devices; and wherein said hinge line of said first one of said controllable devices is skewed relative to said hinge line of said second one of said controllable devices. 
   
   
       8 . A control linkage mechanism for producing synchronous motion in two adjacent elevator surfaces of a T-tail aircraft, comprising:
 a first universal joint yoke assembly configured for coupling to control a first one of said adjacent elevator surfaces of a T-tail aircraft that is rotatably attached to a horizontal stabilizer of a tail assembly of said aircraft;   a second universal joint yoke assembly configured for coupling to control a second one of said adjacent elevator surfaces of a T-tail aircraft that is rotatably attached to a horizontal stabilizer of said tail assembly of said aircraft;   a central cage coupled between said first universal joint yoke assembly and said second universal joint yoke assembly; and   an input push rod assembly having a first end coupled to said central cage and a self aligning second end configured for coupling to a control input device;   wherein said first universal joint yoke assembly is configured to rotate only in a single plane relative to said central cage; and wherein said second universal joint yoke assembly is configured to rotate in multiple planes relative to said central cage.   
   
   
       9 . The control linkage mechanism of  claim 8 , further comprising a push rod deflection mechanism configured to laterally deflect said input push rod assembly. 
   
   
       10 . The control linkage mechanism of  claim 9 , wherein said push rod deflection mechanism comprises a lockable eccentric cam assembly, said lockable eccentric cam assembly being configured to deflect said input push rod assembly laterally about a rod deflection pivot point. 
   
   
       11 . The control linkage mechanism of  claim 8 , wherein said self aligning second end comprises a self-aligning rod end bearing. 
   
   
       12 . The control linkage mechanism of  claim 8 , wherein said first universal joint assembly comprises two first yoke uprights with a first yoke axle disposed therebetween and a first hinge axle oriented at a right angle to said first yoke axle; wherein said second universal joint yoke assembly comprises two second yoke uprights with a second yoke axle disposed therebetween and a second hinge axle oriented at a right angle to said second yoke axle; wherein said central cage is coupled between said first hinge axle of said first universal joint yoke assembly and said second hinge axle of said second universal joint yoke assembly; and wherein said first universal joint yoke assembly is configured to rotate about said first hinge axle only in a single plane relative to said central cage; and wherein said second universal joint yoke assembly is configured to rotate about said second hinge axle in multiple planes relative to said central cage. 
   
   
       13 . A control assembly for producing synchronous motion in two adjacent controllable devices, comprising:
 a first means for rotatably coupling to a first one of said controllable devices;   a second means for rotatably coupling to a second one of said controllable devices; and   a connection means for rotatably coupling each of said first and second means together in laterally spaced relationship;   wherein said first means comprises a rigid means for rotating in a single plane relative to said connection means; and wherein said second means comprises a semi-rigid means for rotating in multiple planes relative to said connection means.   
   
   
       14 . The control assembly of  claim 13 , further comprising a self-aligning means for transmitting control motion from a control input device to said connection means. 
   
   
       15 . The control assembly of  claim 14 , wherein said self-aligning means for transmitting control motion comprises a push rod assembly; and wherein said control assembly further comprises a means for laterally deflecting said push rod assembly. 
   
   
       16 . The control assembly of  claim 13 , said first means for rotatably coupling to a first one of said adjacent controllable devices that is a control surface of an aircraft; and said second means for rotatably coupling to a second one of said adjacent controllable devices that is a control surface of an aircraft. 
   
   
       17 . The control assembly of  claim 16 , wherein said adjacent controllable devices comprise dual adjacent elevator surfaces of a T-tail aircraft; wherein said T-tail aircraft comprises a vertical stabilizer and a horizontal stabilizer supported by said vertical stabilizer; and wherein said dual adjacent elevator surfaces are each rotatably supported by said horizontal stabilizer. 
   
   
       18 . A method for inducing synchronous motion of two adjacent controllable devices, comprising:
 providing a first rotational joint comprising two first yoke uprights with a first yoke axle disposed therebetween and a first hinge axle oriented at a right angle to said first yoke axle, said first yoke axle being coupled at a right angle to a first one of said controllable devices;   providing a second rotational joint comprising two second yoke uprights with a second yoke axle disposed therebetween and a second hinge axle oriented at a right angle to said second yoke axle, said second yoke axle being coupled at a right angle to a second one of said controllable devices;   providing a cross-connection coupled between said first and second hinge axles of said first and second rotational joints, said cross connection comprising a third hinge axle between said first and second hinge axles and being adjustable to produce differential motion between said first and second controllable devices, said first rotational joint being configured to rotate only in a single plane relative to said cross connection and said second rotational joint being configured to rotate in multiple planes relative to said cross connection;   providing a self-aligning input push rod assembly having a first end coupled to said cross connection at said third hinge axle between said first and second hinge axles, and a second end configured for coupling to receive a single input control motion; and   inducing said synchronous motion in said first and second controllable devices in response to said single input control motion received at said third hinge axle of said cross connection;   wherein said synchronous motion is induced by providing control motion to said first controllable device through said first rotational joint, and providing control motion to said second controllable device to said second controllable device through said second rotational joint.   
   
   
       19 . The method of  claim 18 , wherein said first and second rotational joints each comprise a universal joint yoke assembly. 
   
   
       20 . The method of  claim 19 , wherein said first rotational joint comprises a rigid universal joint yoke assembly; and wherein said second rotational joint comprises a semi-rigid universal joint assembly. 
   
   
       21 . The method of  claim 18 , wherein said input push rod assembly comprises a push rod deflection mechanism configured to laterally deflect said input push rod assembly. 
   
   
       22 . The method of  claim 18 , wherein said two adjacent controllable devices comprise adjacent control surfaces of an aircraft. 
   
   
       23 . The method of  claim 18 , wherein said two adjacent controllable devices comprise dual elevator surfaces of a T-tail aircraft. 
   
   
       24 . A control linkage mechanism for producing synchronous motion in two adjacent elevator surfaces of a T-tail aircraft, comprising:
 a first universal joint yoke assembly configured for coupling to control a first one of said adjacent elevator surfaces of said T-tail aircraft;   a second universal joint yoke assembly configured for coupling to control a second one of said adjacent elevator surfaces of said T-tail aircraft;   a central cage coupled between said first universal joint yoke assembly and said second universal joint yoke assembly;   an input push rod assembly having a first end coupled to said central cage and a self aligning second end configured for coupling to a control input device; and   a push rod deflection mechanism configured to deflect said input push rod assembly;   wherein said push rod deflection mechanism comprises a lockable eccentric cam assembly, said lockable eccentric cam assembly being configured to deflect said push rod laterally about a rod deflection pivot point;   wherein said lockable eccentric cam assembly comprises an adjustable eccentric circular cam received within an elongated opening defined in said push rod.   
   
   
       25 . The control linkage mechanism of  claim 24 , wherein said first universal joint yoke assembly is configured to rotate only in a single plane relative to said central cage; and wherein said second universal joint yoke assembly is configured to rotate in multiple planes relative to said central cage. 
   
   
       26 . A control linkage mechanism for producing synchronous motion in two adjacent elevator surfaces of a T-tail aircraft, comprising:
 a first universal joint yoke assembly configured for coupling to control a first one of said adjacent elevator surfaces of said T-tail aircraft;   a second universal joint yoke assembly configured for coupling to control a second one of said adjacent elevator surfaces of said T-tail aircraft;   a central cage coupled between said first universal joint yoke assembly and said second universal joint yoke assembly; and   an input push rod assembly having a first end coupled to said central cage and a self aligning second end configured for coupling to a control input device;   wherein said self aligning second end comprises a self-aligning rod end bearing.   
   
   
       27 . The control linkage mechanism of  claim 26 , wherein said first universal joint yoke assembly is configured to rotate in a single plane relative to said central cage; and
 wherein said second universal joint yoke assembly is configured to rotate in multiple planes relative to said central cage.   
   
   
       28 . A control assembly for controlling two adjacent controllable devices, comprising:
 a first rotational joint comprising two first yoke uprights with a first yoke axle disposed therebetween and a first hinge axle oriented at a right angle to said first yoke axle, said first yoke axle being configured for coupling at a right angle to a first one of said controllable devices;   a second rotational joint comprising two second yoke uprights with a second yoke axle disposed therebetween and a second hinge axle oriented at a right angle to said second yoke axle, said second yoke axle being configured for coupling at a right angle to a second one of said controllable devices;   a cross-connection coupled between said first and second hinge axles of said first and second rotational joints, wherein said cross connection comprises a third hinge axle between said first and second hinge axles so that said control assembly produces synchronous motion in said first and second controllable devices in response to a single input control motion received at said third hinge axle of said cross connection, and so that said cross-connection is adjustable to produce differential motion between said first and second controllable devices; and   a self-aligning input push rod assembly having a first end coupled to said cross connection at said third hinge axle of said cross connection between said first and second hinge axles, and a second end configured for coupling to receive said control motion provided by a control input device;   wherein said first hinge axle intersects said cross-connection at a first end of said cross connection, said first hinge axle being disposed at a right angle to said cross connection; and   wherein said second hinge axle intersects said cross-connection at a second end of said cross connection, said second hinge axle being disposed at a right angle to said cross connection.   
   
   
       29 . The control assembly of  claim 28 , wherein said first rotational joint is configured for coupling to a first one of said controllable devices that is a control surface of an aircraft; and wherein said second rotational joint is configured for coupling to a second one of said controllable devices that is a control surface of an aircraft. 
   
   
       30 . The control assembly of  claim 29 , wherein said adjacent controllable devices comprise dual adjacent elevator surfaces of a T-tail aircraft. 
   
   
       31 . A method for inducing synchronous motion of two adjacent controllable devices, comprising:
 providing a first rotational joint comprising two first yoke uprights with a first yoke axle disposed therebetween and a first hinge axle oriented at a right angle to said first yoke axle, said first yoke axle being coupled at a right angle to a first one of said controllable devices;   providing a second rotational joint comprising two second yoke uprights with a second yoke axle disposed therebetween and a second hinge axle oriented at a right angle to said second yoke axle, said second yoke axle being coupled at a right angle to a second one of said controllable devices;   providing a cross-connection coupled between said first and second hinge axles of said first and second rotational joints, said cross connection comprising a third hinge axle between said first and second hinge axles and being adjustable to produce differential motion between said first and second controllable devices;   providing a self-aligning input push rod assembly having a first end coupled to said cross connection at said third hinge axle between said first and second hinge axles, and a second end configured for coupling to receive a single input control motion; and   inducing said synchronous motion in said first and second controllable devices in response to said single input control motion received at said third hinge axle of said cross connection;   wherein said synchronous motion is induced by providing control motion to said first controllable device through said first rotational joint, and providing control motion to said second controllable device to said second controllable device through said second rotational joint;   wherein said first hinge axle intersects said cross-connection at a first end of said cross connection, said first hinge axle being disposed at a right angle to said cross connection; and   wherein said second hinge axle intersects said cross-connection at a second end of said cross connection, said second hinge axle being disposed at a right angle to said cross connection.   
   
   
       32 . The method of  claim 31 , wherein said two adjacent controllable devices comprise adjacent control surfaces of an aircraft. 
   
   
       33 . The method of  claim 31 , wherein said two adjacent controllable devices comprise dual elevator surfaces of a T-tail aircraft.