Yaw damping system and method for aircraft
An alternative system for damping the dutch roll mode in an aircraft is provided using roll control surfaces. Classical yaw dampers for the dutch roll mode utilize the yaw control surfaces such as a rudder to dampen the dutch roll mode oscillations. An alternative damper is described that utilizes roll control surfaces such as spoilers or ailerons to dampen the dutch roll mode.
1. A method for damping the dutch roll mode in an aircraft having a roll control surface, comprising the steps of:
measuring at least one parameter of the motion of the aircraft;
applying a washout filter to the at least one parameter of motion to remove low frequency signals from the measured parameter of motion of the aircraft;
calculating a damping signal that is proportional to the at least one parameter of the motion of the aircraft as modified by the washout filter; and
actuating the roll control surface in proportion to the damping signal
wherein the step of applying a washout filter to the at least one parameter of motion further comprises the step of selecting a natural frequency for the washout filter that is higher than the natural frequency of the spiral mode of the aircraft and lower than the natural frequency of the dutch roll mode of the aircraft.
2. The method of claim 1 wherein the at least one parameter of motion of the aircraft is selected from the group consisting of a body axis yaw rate, a lateral acceleration and a roll rate.
3. The method of claim 1 wherein the step of calculating a damping signal further comprises the steps of calculating a sideslip rate estimate utilizing a measured body axis yaw rate, a measured lateral acceleration of the aircraft and a measured airspeed of the aircraft and assuming that an angle of attack of the aircraft is zero.
4. The method of claim 3 wherein the step of calculating a damping signal further comprises the step of calculating a sideslip estimate utilizing the measured lateral acceleration of the aircraft and assuming that a rudder deflection of the aircraft is zero.
5. The method of claim 4 wherein the step of calculating a damping signal further comprises the steps of calculating a derivative function of the at least one parameter of motion; multiplying the derivative function by a proportional gain; and adding the result to the damping signal.
6. The method of claim 5 wherein the step of calculating a damping signal further comprises the steps of calculating an integral function of the at least one parameter of motion; multiplying the integral function by a proportional gain; and adding the result to the damping signal.
7. The method of claim 4 wherein the step of calculating a damping signal further comprises the step of calculating the difference between a pilot command signal for the roll control surface and the combination of the sideslip rate estimate and the sideslip estimate.
8. The method of claim 1 further comprising the initial step of:
monitoring the condition of the aircraft until detection of a disabled, jammed or otherwise defective yaw control surface condition.
9. A method for damping the dutch roll mode of an aircraft comprising the steps of:
measuring at least one parameter of motion of an aircraft;
applying a washout filter to the at least one parameter of motion;
estimating the sideslip rate of the aircraft based on the at least one parameter of motion;
calculating a damping signal that is proportional to the estimated sideslip rate of the aircraft; and
actuating a roll control surface of the aircraft in proportion to the damping signal
wherein the step of applying a washout filter to the at least one parameter of motion further comprises the step of selecting a natural frequency for the washout filter that is higher than the natural frequency of the spiral mode of the aircraft and lower than the natural frequency of the dutch roll mode of the aircraft.
10. The method of claim 9 wherein the at least one parameter of motion of the aircraft is selected from the group consisting of a yaw rate, a lateral acceleration and a roll rate.
11. The method of claim 10 wherein the at least one parameter of motion of the aircraft is a body axis yaw rate of the aircraft.
12. The method of claim 9 wherein the step of estimating the sideslip rate of the aircraft further comprises the steps of:
assuming that the angle of attack of the aircraft is zero;
calculating an estimated sideslip rate that is proportional to a measured body axis yaw rate, a measured lateral acceleration of the aircraft and a measured airspeed of the aircraft.
13. The method of claim 12 wherein the step of calculating a damping signal further comprises the steps of calculating a derivative function of the sideslip rate;
multiplying the derivative function by a proportional gain; and adding the result to the damping signal.
14. The method of claim 13 wherein the step of calculating a damping signal further comprises the steps of calculating an integral function of the sideslip rate;
multiplying the integral function by a proportional gain; and adding the result to the damping signal.
15. The method of claim 12 wherein the step of calculating the damping signal further comprises the steps of:
Assuming a rudder deflection of the aircraft is zero;
Calculating an estimated sideslip utilizing the measured lateral acceleration of the aircraft; and
Combining the estimated sideslip and the estimated sideslip rate using a complementary filter.
16. The method of claim 12 wherein the step of calculating a damping signal further comprises the steps of:
calculating a difference between the estimated sideslip rate and a pilot command signal for the roll control surface; and
calculating a damping signal that is proportional to the calculated difference.
17. The method of claim 9 further comprising the initial steps of:
monitoring the condition of the aircraft to detect a disabled, jammed or otherwise defective yaw control surface condition;
activating the remaining steps of the method upon detection of said condition.
18. A method for damping the dutch roll mode of an aircraft having a roll control surface, comprising the steps of:
measuring at least one parameter of motion of the aircraft;
applying a washout filter to the at least one parameter of motion to remove low frequency signals from the measured parameter of motion of the aircraft;
calculating a damping signal that is proportional to the at least one parameter of motion of the aircraft;
applying a feedback signal to the damping signal that is proportional to a measured bank angle of the aircraft or to an integrated roll rate of the aircraft; and
actuating the roll control surface in proportion to the damping signal;
wherein the step of applying a washout filter to the at least one parameter of motion further comprises the step of selecting a natural frequency for the washout filter that is higher than the natural frequency of the spiral mode of the aircraft and lower than the natural frequency of the dutch roll mode of the aircraft.