Control system and method with multiple linked inputs

Abstract

Methods and systems for linking input control signals, such as control signals used to control aspects of aircraft operation. In one embodiment, the method includes receiving first and second force signals corresponding to first and second forces applied to first and second controllers. The method can further include directing first and second position signals to the first and second controllers to move the first and second controllers to approximately the same positions. Each force signal is transmitted along a signal path, and the signal paths can be linked at a point where the signals on each path correspond to a quantity other that a position of a controller. The signal paths can be linked such that only one of the forces must exceed a threshold value for both controllers to be moved, and if one of the forces is outside a selected limit range, that force can be at least partially discounted.

We claim:  
     
         1 . A computer-implemented method for linking input control signals, comprising: 
 receiving a first force signal corresponding directly to a first force applied to a first controller;    receiving a second force signal corresponding directly to a second force applied to the second controller;    linking the first force signal and the second force signal;    after linking the first and second force signals, directing a first position demand signal to a first servo motor to move the first controller to a first controller position, and directing a second position demand signal to a second controller to move the second controller to a second servo motor position, the first controller having a first neutral position, the first controller position being displaced from the first neutral position by a first distance, the second controller having a second neutral position, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance; and    directing a control signal to a controlled device based on at least one of the first and second force signals.    
     
     
         2 . The method of  claim 1  wherein linking the first and second signal paths includes linking the first and second signal paths at a point where a first signal on the first signal path corresponds linearly to the first force and a second signal on the second signal path corresponds linearly to the second force.  
     
     
         3 . The method of  claim 1 , wherein directing the control signal includes directing the control signal to an actuator operatively coupled to an aircraft flight control surface.  
     
     
         4 . The method of  claim 1 , further comprising combining a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force, and wherein directing a control signal includes directing a control signal based on a combination of the first value and the second value.  
     
     
         5 . The method of  claim 1 , further comprising summing a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force, and wherein directing a control signal includes directing a control signal based on a sum of the first and second values.  
     
     
         6 . The method of  claim 1 , further comprising combining a first value corresponding to the first force and a second value corresponding to the second force by: 
 determining a difference between the first value and the second value; and    subtracting half the difference from the first value and multiplying the resultant by two.    
     
     
         7 . The method of  claim 1 , further comprising combining a first value corresponding to the first force and a second value corresponding to the second force by: 
 determining a difference between the first value and the second value; and    adding half the difference to the second value and multiplying the resultant by two.    
     
     
         8 . The method of  claim 1 , further comprising: 
 determining whether at least one of the first force and the second force is outside a selected limit range; and    if the at least one force is outside the selected limit range, directing the control signal with the at least one force at least partially discounted.    
     
     
         9 . The method of  claim 1 , further comprising directing the control signal to a controllable device of an aircraft.  
     
     
         10 . The method of  claim 1 , further comprising directing the control signal to an actuator operatively coupled to at least one of an aircraft pitch control surface, an aircraft yaw control surface and an aircraft roll control surface.  
     
     
         11 . The method of  claim 1  wherein the first controller includes a control stick operatively coupled to a transducer and a motor, further wherein receiving the first force signal includes receiving the first force signal from the transducer, and wherein directing the first position signal includes directing the first position signal to the motor.  
     
     
         12 . A computer-implemented method for linking input control signals, comprising: 
 receiving a first force signal corresponding to a first force applied to a first controller,    receiving a second force signal corresponding to a second force applied to a second controller;    directing a first position demand signal to the first controller to move the first controller to a first controller position, the first controller having a first neutral position, the first controller position being displaced from the first neutral position by a first distance, the first force signal and the first position demand signal being transmitted along a first signal path;    directing a second position signal to the second controller to move the second controller to a second controller position, the second controller having a second neutral position, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance, the second force signal and the second position demand signal being transmitted along a second signal path;    directing a control signal to a controlled device based on at least one of the first and second force signals; and    linking the first and second signal paths at a point where signals on the first and second signal paths correspond to a quantity other than a position of a controller.    
     
     
         13 . The method of  claim 12  wherein linking the first and second signal paths includes linking the first and second signal paths at a point where a first signal on the first signal path corresponds linearly to the first force and a second signal on the second signal path corresponds linearly to the second force.  
     
     
         14 . The method of  claim 12 , wherein directing the control signal includes directing the control signal to an actuator operatively coupled to an aircraft flight control surface.  
     
     
         15 . The method of  claim 12 , further comprising combining a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force, and wherein directing a control signal includes directing a control signal based on a combination of the first value and the second value.  
     
     
         16 . The method of  claim 12 , further comprising summing a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force, and wherein directing a control signal includes directing a control signal based on a sum of the first and second values.  
     
     
         17 . The method of  claim 12 , further comprising combining a first value corresponding to the first force and a second value corresponding to the second force by: 
 determining a difference between the first value and the second value; and    subtracting half the difference from the first value and multiplying the resultant by two.    
     
     
         18 . The method of  claim 12 , further comprising combining a first value corresponding to the first force and a second value corresponding to the second force by: 
 determining a difference between the first value and the second value; and    adding half the difference to the second value and multiplying the resultant by two.    
     
     
         19 . The method of  claim 12 , further comprising: 
 determining whether at least one of the first force and the second force is outside a selected limit range; and    if the at least one force is outside the selected limit range, directing the control signal with the at least one force at least partially discounted.    
     
     
         20 . The method of  claim 12 , further comprising directing the control signal to a controllable device of an aircraft.  
     
     
         21 . The method of  claim 12 , further comprising directing the control signal to an actuator operatively coupled to at least one of an aircraft pitch control surface, an aircraft yaw control surface and an aircraft roll control surface.  
     
     
         22 . The method of  claim 12  wherein the first controller includes a control stick operatively coupled to a transducer and a motor, further wherein receiving the first force signal includes receiving the first force signal from the transducer, and wherein directing the first position demand signal includes directing the first position demand signal to the motor.  
     
     
         23 . A computer-implemented method for linking input control signals, comprising: 
 receiving a first force signal corresponding to a first force applied to a first controller;    receiving a second force signal corresponding to a second force applied to a second controller;    if the first force signal meets or exceeds a threshold value, directing a first position demand signal to the first controller to move the first controller to a first controller position, and directing a second position demand signal to the second controller to move the second controller to a second controller position independent of whether or not the second force signal meets or exceeds the threshold value, the first controller having a first neutral position, the first controller position being displaced from the first neutral position by a first distance, the second controller having a second neutral position, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance; and    directing a control signal based on at least one of the first and second force signals.    
     
     
         24 . The method of  claim 23 , wherein directing the control signal includes directing the control signal to an actuator operatively coupled to an aircraft flight control surface.  
     
     
         25 . The method of  claim 23 , further comprising combining a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force, and wherein directing a control signal includes directing a control signal based on a combination of the first value and the second value.  
     
     
         26 . The method of  claim 23 , further comprising summing a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force, and wherein directing a control signal includes directing a control signal based on a sum of the first and second values.  
     
     
         27 . The method of  claim 23 , further comprising combining a first value corresponding to the first force and a second value corresponding to the second force by: 
 determining a difference between the first value and the second value; and    subtracting half the difference from the first value and multiplying the resultant by two.    
     
     
         28 . The method of  claim 23 , further comprising combining a first value corresponding to the first force and a second value corresponding to the second force by: 
 determining a difference between the first value and the second value; and    adding half the difference to the second value and multiplying the resultant by two.    
     
     
         29 . The method of  claim 23 , further comprising: 
 determining whether at least one of the first force and the second force is outside a selected limit range; and    if the at least one force is outside the selected limit range, directing the control signal with the at least one force at least partially discounted.    
     
     
         30 . The method of  claim 23 , further comprising directing the control signal to a controllable device of an aircraft.  
     
     
         31 . The method of  claim 23 , further comprising directing the control signal to an actuator operatively coupled to at least one of an aircraft pitch control surface, an aircraft yaw control surface and an aircraft roll control surface.  
     
     
         32 . The method of  claim 23  wherein the first controller includes a control stick operatively coupled to a transducer and a motor, further wherein receiving the first force signal includes receiving the first force signal from the transducer, and wherein directing the first position demand signal includes directing the first position demand signal to the motor.  
     
     
         33 . The method of  claim 23 , further comprising determining at least one of the first force and the second force exceeds a selected limit value.  
     
     
         34 . The method of  claim 23 , further comprising temporally varying a degree to which the at least one force signal contributes to the control signal.  
     
     
         35 . The method of  claim 23  wherein receiving the first force signal includes receiving the first force signal from a transducer operatively coupled to a movable aircraft control stick.  
     
     
         36 . A computer-implemented method for linking signals from a first aircraft controller having a first neutral position and a second aircraft controller having a second neutral position, the method comprising: 
 receiving a first force signal corresponding to a first force applied to the first aircraft controller;    receiving a second force signal corresponding to a second force applied to a second aircraft controller;    if the first force signal meets or exceeds a threshold value, directing a first position demand signal to the first aircraft controller to move the first aircraft controller to a first controller position and directing a second position demand signal to the second aircraft controller to move the second aircraft controller to a second controller position independent of whether or not the second force signal exceeds the threshold value, the first controller position being displaced from the first neutral position by a first distance, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance; and    directing a control signal operatively coupled to a flight control surface based on at least one of the first and second force signals.    
     
     
         37 . The method of  claim 36 , further comprising combining a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force, and wherein directing a control signal includes directing a control signal based on a combination of the first value and the second value.  
     
     
         38 . The method of  claim 36 , further comprising summing a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force, and wherein directing a control signal includes directing a control signal based on a sum of the first and second values.  
     
     
         39 . The method of  claim 36 , further comprising combining a first value corresponding to the first force and a second value corresponding to the second force by: 
 determining a difference between the first value and the second value; and    subtracting half the difference from the first value and multiplying the resultant by two.    
     
     
         40 . The method of  claim 36 , further comprising combining a first value corresponding to the first force and a second value corresponding to the second force by: 
 determining a difference between the first value and the second value; and    adding half the difference to the second value and multiplying the resultant by two.    
     
     
         41 . The method of  claim 36 , further comprising determining whether at least one of the first force and the second force is outside a selected limit range.  
     
     
         42 . The method of  claim 36 , further comprising: 
 determining whether at least one of the first force and the second force is outside a selected limit range; and    if the at least one force is outside the selected limit range, directing the control signal on the basis of an at least partially discounted value of the at least one force.    
     
     
         43 . The method of  claim 36 , further comprising directing the control signal to an actuator operatively coupled to at least one of an aircraft pitch control surface, an aircraft yaw control surface and an aircraft roll control surface.  
     
     
         44 . The method of  claim 36  wherein the first controller includes a control stick operatively coupled to a transducer and a motor, further wherein receiving the first force signal includes receiving the first force signal from the transducer, and wherein directing the first motion signal includes directing the first motion signal to the motor.  
     
     
         45 . A computer-implemented method for linking input control signals, comprising: 
 receiving a first force signal corresponding to a first force applied to a first controller;    receiving a second force signal corresponding to a second force applied to a second controller,    if the first force signal is within a selected limit range, directing a first control signal corresponding to a combination of the first and second force signals; and    if the first force signal is outside the selected limit range, directing a second control signal that at least partially discounts the first force signal.    
     
     
         46 . The method of  claim 45 , further comprising if the first force signal meets or exceeds a threshold value, directing a first position demand signal to the first controller to move the first controller to a first controller position, and directing a second position demand signal to the second controller to move the second controller to a second controller position independent of whether or not the second force signal meets or exceeds the threshold value, the first controller having a first neutral position, the first controller position being displaced from the first neutral position by a first distance, the second controller having a second neutral position, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance.  
     
     
         47 . The method of  claim 45  wherein the first and second force signals indicate forces in at least approximately the same direction, and wherein directing the second control signal includes basing the second control signal on a constant value for the first force signal.  
     
     
         48 . The method of  claim 45  wherein directing the first and second control signals includes directing the control signals to an actuator operatively coupled to an aircraft flight control surface.  
     
     
         49 . The method of  claim 45 , further comprising combining a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force, and wherein directing the first control signal includes directing a control signal based on a combination of the first and second values.  
     
     
         50 . The method of  claim 45 , further comprising summing a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force.  
     
     
         51 . The method of  claim 45 , further comprising combining a first value corresponding to the first force and a second value corresponding to the second force by: 
 determining a difference between the first value and the second value; and    subtracting half the difference from the first value and multiplying the resultant by two.    
     
     
         52 . The method of  claim 45 , further comprising combining a first value corresponding to the first force and a second value corresponding to the second force by: 
 determining a difference between the first value and the second value; and    adding half the difference to the second value and multiplying the resultant by two.    
     
     
         53 . The method of  claim 45 , further comprising directing the first control signal to a controllable device of an aircraft.  
     
     
         54 . The method of  claim 45 , further comprising directing the first control signal to an actuator operatively coupled to at least one of an aircraft pitch control surface, an aircraft yaw control surface and an aircraft roll control surface.  
     
     
         55 . The method of  claim 45  wherein receiving the first force signal includes receiving the first force signal from a transducer operatively coupled to a movable aircraft control stick.  
     
     
         56 . The method of  claim 45  wherein the first controller includes a control stick operatively coupled to a transducer and a motor, further wherein receiving the first force signal includes receiving the first force signal from the transducer, and wherein directing the first and second control signals includes directing first and second position signals to the motor to move the first controller to corresponding first and second positions.  
     
     
         57 . A computer-implemented method for linking signals from a first aircraft controller having a first neutral position and a second aircraft controller having a second neutral position, the method comprising: 
 receiving a first force signal corresponding to a first force applied to the first aircraft controller;    receiving a second force signal corresponding to a second force applied to the second aircraft controller,    if the first force signal is within a selected limit range, directing a first control signal to control a state of a flight control surface, the first control signal corresponding to a combination of the first and second force signals; and    if the first force signal is outside the selected limit range, directing a second control signal to control a state of a flight control surface, the second control signal at least partially discounting the first force signal.    
     
     
         58 . The method of  claim 57 , further comprising: 
 if the first force signal meets or exceeds a threshold value, directing a first position demand signal to the first controller to move the first controller to a first controller position independent of whether or not the second force signal meets or exceeds the threshold value; and    directing a second position demand signal to the second controller to move the second controller to a second controller position, the first controller having a first neutral position, the first controller position being displaced from the first neutral position by a first distance, the second controller having a second neutral position, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance.    
     
     
         59 . The method of  claim 57 , further comprising combining a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force, and wherein directing the first control signal includes directing a control signal based on a combination of the first and second values.  
     
     
         60 . The method of  claim 57 , further comprising summing a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force, and wherein directing the first control signal includes directing a control signal based on a sum of the first and second values.  
     
     
         61 . The method of  claim 57 , further comprising combining a first value corresponding to the first force and a second value corresponding to the second force by: 
 determining a difference between the first value and the second value; and    subtracting half the difference from the first value and multiplying the resultant by two.    
     
     
         62 . The method of  claim 57 , further comprising combining a first value corresponding to the first force and a second value corresponding to the second force by: 
 determining a difference between the first value and the second value; and    adding half the difference to the second value and multiplying the resultant by two.    
     
     
         63 . The method of  claim 57 , further comprising normalizing the first force signal by applying a correction factor to the first force signal if the first force signal corresponds to a selected force direction.  
     
     
         64 . The method of  claim 57 , further comprising directing the first control signal to an actuator operatively coupled to at least one of an aircraft pitch control surface, an aircraft yaw control surface and an aircraft roll control surface.  
     
     
         65 . The method of  claim 57  wherein receiving the first force signal includes receiving the first force signal from a transducer operatively coupled to a movable aircraft control stick.  
     
     
         66 . The method of  claim 57  wherein the first controller includes a control stick operatively coupled to a transducer and a motor, further wherein receiving the first force signal includes receiving the first force signal from the transducer, and wherein the method further comprises directing a motion signal to the motor to move the first controller to a selected position.  
     
     
         67 . A computer-implemented method for linking signals from a first aircraft controller having a first neutral position and a second aircraft controller having a second neutral position, the method comprising: 
 receiving a first force signal corresponding to a first force applied to the first aircraft controller;    if the first force signal exceeds a threshold value, directing a first position demand signal to the first aircraft controller to move the first aircraft controller to a first controller position and directing a second position demand signal to a second controller to move the second aircraft controller to a second controller position, the first controller position being displaced from the first neutral position by a first distance, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance;    receiving a second force signal corresponding to a second force applied to the second aircraft controller;    if the first force signal is within a selected limit rage, directing a first control signal to control a state of a flight control surface, the first control signal corresponding to a combination of the first and second force signals and being independent of whether or not the second force signal exceeds the threshold value; and    if the first force signal is outside the selected limit range, directing a second control signal to control the state of the flight control surface, the second control signal at least partially discounting the first force signal.    
     
     
         68 . The method of  claim 67 , further comprising combining a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force, and wherein directing a control signal includes directing a control signal based on a combination of the first value and the second value.  
     
     
         69 . The method of  claim 67 , further comprising combining a first value corresponding to the first force and a second value corresponding to the second force by: 
 determining a difference between the first value and the second value; and    subtracting half the difference from the first value and multiplying the resultant by two.    
     
     
         70 . The method of  claim 67 , further comprising directing the control signal to an actuator operatively coupled to at least one of an aircraft pitch control surface, an aircraft yaw control surface and an aircraft roll control surface.  
     
     
         71 . The method of  claim 67  wherein the first and second force signals indicate forces in at least approximately opposite directions, and wherein at least partially discounting at least one of the first and second force signals includes setting the at least one force signal to a constant value.  
     
     
         72 . The method of  claim 67  wherein at least partially discounting at least one of the first and second force signals includes at least partially discounting both the first and second force signals.  
     
     
         73 . A computer-readable medium the contents of which cause a computer to perform a method for linking signals from a first aircraft controller having a first neutral position and a second aircraft controller having a second neutral position, the method comprising: 
 receiving a first force signal corresponding to a first force applied to the first aircraft controller;    if the first force signal exceeds a threshold value, directing a first position demand signal to the first aircraft controller to move the first aircraft controller to a first controller position and directing a second position demand signal to a second aircraft controller to move the second aircraft controller to a second controller position independent of whether or not the second force signal exceeds the threshold value, the first controller position being displaced from the first neutral position by a first distance, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance;    receiving a second force signal corresponding to a second force applied to the second aircraft controller; and    directing a control signal operatively coupled to a flight control surface based on at least one of the first and second force signals.    
     
     
         74 . The computer-readable medium of  claim 73  wherein the method further comprises combining a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force, and wherein directing a control signal includes directing a control signal based on a combination of the first value and the second value.  
     
     
         75 . The computer-readable medium of  claim 73  wherein the method further comprises combining a first value corresponding to the first force and a second value corresponding to the second force by: 
 determining a difference between the first value and the second value; and  
 subtracting half the difference from the first value and multiplying the resultant by two.  
 
     
     
         76 . The computer-readable medium of  claim 73  wherein the method further comprises: 
 determining whether at least one of the first force and the second force is outside a selected limit range; and  
 if the at least one force is outside the selected limit range, directing the control signal on the basis of an at least partially discounted value for the at least one force signal.  
 
     
     
         77 . The computer-readable medium of  claim 73  wherein the method further comprises directing the control signal to an actuator operatively coupled to at least one of an aircraft pitch control surface, an aircraft yaw control surface and an aircraft roll control surface.  
     
     
         78 . The computer-readable medium of  claim 73  wherein the first controller includes a control stick operatively coupled to a transducer and a motor, further wherein receiving the first force signal includes receiving the first force signal from the transducer, and wherein directing the first motion signal includes directing the first motion signal to the motor.  
     
     
         79 . A computer-readable medium the contents of which cause a computer to perform a method for linking signals from a first aircraft controller having a first neutral position and a second aircraft controller having a second neutral position, the method comprising: 
 receiving a first force signal corresponding to a first force applied to the first aircraft controller;    receiving a second force signal corresponding to a second force applied to the second aircraft controller;    if the first force signal exceeds a threshold value, directing a first position demand signal to the first aircraft controller to move the first aircraft controller to a first controller position and directing a second position demand signal to a second controller to move the second aircraft controller to a second controller position, the first controller position being displaced from the first neutral position by a first distance, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance;    if the first force signal is within a selected limit range, directing a control signal to control a state of a flight control surface, the first control signal corresponding to a combination of the first and second force signals and being independent of whether or not the second force signal exceeds the threshold value; and    if the first force signal is outside the selected limit range, directing a second control signal to control the state of the flight control surface, the second control signal at least partially discounting the first force signal.    
     
     
         80 . The computer-readable medium of  claim 79 , wherein the method comprises: 
 if the first force signal meets or exceeds a threshold value, directing a first position demand signal to the first controller to move the first controller to a first controller position, and directing a second position demand signal to the second controller to move the second controller to a second controller position, the first controller having a first neutral position, the first controller position being displaced from the first neutral position by a first distance, the second controller having a second neutral position, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance; and    directing the first control signal independent of whether or not the second force signal meets or exceeds the threshold value.    
     
     
         81 . The computer-readable medium of  claim 79  wherein the first and second force signals indicate forces in at least approximately the same direction, and wherein at least partially discounting at least one of the first and second force signals includes selecting the at least one force to have a constant value.  
     
     
         82 . The computer-readable medium of  claim 79  wherein the first and second force signals indicate forces in at least approximately opposite directions, and wherein at least partially discounting at least one of the first and second force signals includes selecting the at least one force to have a constant value.  
     
     
         83 . The computer-readable medium of  claim 79  wherein at least partially discounting at least one of the first and second force signals includes at least partially discounting both the first and second force signals.  
     
     
         84 . The computer-readable medium of  claim 79 , wherein the method further comprises combining a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force, and wherein directing the first control signal includes directing a control signal based on a combination of the first and second values.  
     
     
         85 . The computer-readable medium of  claim 79 , wherein the method further comprises directing the first control signal to an actuator operatively coupled to at least one of an aircraft pitch control surface, an aircraft yaw control surface and an aircraft roll control surface.  
     
     
         86 . The computer-readable medium of  claim 79  wherein receiving the first force signal includes receiving the first force signal from a transducer operatively coupled to a movable aircraft control stick.  
     
     
         87 . The computer-readable medium of  claim 79  wherein the first controller includes a control stick operatively coupled to a transducer and a motor, further wherein receiving the first force signal includes receiving the first force signal from the transducer, and wherein the method further comprises directing a motion signal to the motor to move the first controller to a selected position.  
     
     
         88 . A system for controlling an aircraft flight control surface, comprising: 
 a first aircraft controller having a first input device configured to receive a first operator's input command, the first input device being coupled to a first sensor to sense a force applied to the first input device, the first input device being coupled to a first motor to move the first input device from a first neutral position;    a second aircraft controller having a second input device configured to receive a second operator's input command, the second input device being coupled to a second sensor to sense a force applied to the second input device, the second input device being coupled to a second motor to move the second input device from a second neutral position; and    a computer-readable medium operatively coupled to the first and second aircraft controllers, the computer-readable medium being configured to: 
 receive a first force signal corresponding to a first force applied to the first aircraft controller;  
 if the first force signal exceeds a threshold value, direct a first position signal to the first motor to move the first input device to a first input device position and direct a second signal to a second motor to move the second input device to a second input device position, the first input device position being displaced from the first neutral position by a first distance, the second input device position being displaced from the second neutral position by a second distance at least approximately equal to the first distance;  
 receive a second force signal corresponding to a second force applied to the second aircraft controller; and  
 direct a control signal operatively coupled to a flight control surface, the control signal being based on at least one of the first and second force signals and being independent of whether or not the second force signal exceeds the threshold value.  
   
     
     
         89 . The system of  claim 88 , wherein the method further comprises combining a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force, and wherein directing a control signal includes directing a control signal based on a combination of the first value and the second value.  
     
     
         90 . The system of  claim 88 , wherein the method further comprises combining a first value corresponding to the first force and a second value corresponding to the second force by: 
 determining a difference between the first value and the second value; and    subtracting half the difference from the first value and multiplying the resultant by two.    
     
     
         91 . The system of  claim 88 , wherein the method further comprises determining whether a difference between the first force and the second force meets or exceeds a selected differential value.  
     
     
         92 . The system of  claim 88 , wherein the method further comprises: 
 determining whether at least one of the first and second forces is outside a selected limit range; and    if the at least one force is outside the selected limit range, directing the control signal on the basis of an at least partially discounted value for the at least one force signal.    
     
     
         93 . The method of  claim 88 , further comprising directing the control signal to an actuator operatively coupled to at least one of an aircraft pitch control surface, an aircraft yaw control surface and an aircraft roll control surface.  
     
     
         94 . The method of  claim 88  wherein the first controller includes a control stick operatively coupled to a transducer and a motor, further wherein receiving the first force signal includes receiving the first force signal from the transducer, and wherein directing the first motion signal includes directing the first motion signal to the motor.  
     
     
         95 . A system for controlling an aircraft flight control surface, comprising: 
 a first aircraft controller having a first input device configured to receive a first operator's input command, the first input device being coupled to a first sensor to sense a force applied to the first input device, the first input device being coupled to a first motor to move the first input device from a first neutral position;    a second aircraft controller having a second input device configured to receive a second operator's input command, the second input device being coupled to a second sensor to sense a force applied to the second input device, the second input device being coupled to a second motor to move the second input device from a second neutral position; and    a computer-readable medium operatively coupled to the first and second aircraft controllers, the computer-readable medium being configured to: 
 receive a first force signal corresponding to a first force applied to the first aircraft controller;  
 receive a second force signal corresponding to a second force applied to the second aircraft controller;  
 if the first force signal is within a selected limit range, direct a first control signal to control a state of the aircraft flight control surface, the first control signal corresponding to a combination of the first and second force signals; and  
 if the first force signal is outside the selected limit range, direct a second control signal to control a state of the aircraft flight control surface, the second control signal at least partially discounting the first force signal.  
   
     
     
         96 . The system of  claim 95 , wherein the computer-readable medium is configured to: 
 determine if the first force signal meets or exceeds a threshold value;    if the first force signal meets or exceeds a threshold value, direct a first position signal to the first controller to move the first controller to a first controller position, and direct a second position signal to the second controller to move the second controller to a second controller position, the first controller having a first neutral position, the first controller position being displaced from the first neutral position by a first distance, the second controller having a second neutral position, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance; and    direct the first control signal independent of whether or not the second force signal meets or exceeds the threshold value.