System & method of filtering low order oscillation from non-rigid suspension systems
A system and method of guiding an aircraft is disclosed. The aircraft includes at least one non-rigidly attached sensor for providing a signal indicative of the angular rate of turn of the aircraft. The signal includes an oscillation component and an angular rate of turn component. A filter receives the signal from the sensor and attempts to remove the oscillation component found in the signal. A guidance system provides a commanded turn rate signal. A stability augmentation system receives the filtered angular rate of turn signal and the commanded turn rate signal and processes those signals to provide an actuator command signal. The actuator command signal can best be used to control an air vehicle activation device. The method involves receiving at least one signal indicative of an angular rate of turn of the aircraft from the sensor not rigidly suspended from an aircraft, wherein the signal includes an oscillation component and an angular rate of turn component. The signal is filtered to attenuate the oscillation component while a command a turn rate signal is received. Finally, the filtered signal and the commanded turn rate signal are processed to determine an actuator command signal.
1 . A method of guiding an aircraft comprising the acts of:
receiving at least one signal indicative of an angular rate of turn of said aircraft from at least one sensor non-rigidly suspended from an air wing, said at least one signal including an oscillation component and an angular rate of turn component;
filtering said at least one signal to attenuate said oscillation present in said at least one signal using at least one filter;
receiving at least one commanded turn rate signal; and
processing said at least one filtered signal and said at least one commanded turn rate signal to determine an actuator command signal.
2 . The method as claimed in claim 1 wherein a stability augmentation system (SAS) processes said at least one filtered signal and said at least one commanded turn rate signal to determine said actuator command signal.
3 . The method as claimed in claim 2 wherein said SAS includes a Proportional+Integral+Derivative (PID) controller.
4 . The method as claimed in claim 2 wherein said SAS includes an adaptive SAS.
5 . The method as claimed in claim 4 wherein said adaptive SAS includes a neural network.
6 . The method as claimed in claim 1 wherein said at least one filter includes at least one linear filter.
7 . The method as claimed in claim 6 wherein said act of filtering includes at least two first order filters in series.
8 . The method as claimed in claim 1 wherein said at least one filter is a non-linear filter.
9 . The method as claimed in claim 1 wherein said act of receiving said at least one signal indicative of said angular rate of turn of said aircraft includes receiving at least one signal from an attitude and heading reference system or an inertial measurement unit.
10 . The method as claimed in claim 1 wherein said act of receiving said at least one commanded turn rate signal includes receiving at least one signal from a global positioning system receiver.
11 . The method as claimed in claim 1 wherein said act of receiving said at least one commanded turn rate signal includes receiving at least one signal from a source remote from said aircraft.
12 . The method as claimed in claim 1 wherein said act of receiving said at least one commanded turn rate signal includes receiving at least one signal from an operator located proximate to said aircraft.
13 . A guidance system for an aircraft comprising:
at least one sensor non-rigidly suspended from an air wing, said at least one sensor providing at least one signal indicative of an angular rate of turn of said aircraft, said at least one signal including an oscillation component and an angular rate of turn component;
at least one filter, receiving said at least one signal indicative of an angular rate of turn of said aircraft, for filtering said at least one signal to attenuate said oscillation component present in said at least one signal;
a guidance system, for providing at least one commanded turn rate signal; and
a stability augmentation system, receiving said at least one filtered signal and said at least one commanded turn rate signal, for processing said at least one filtered signal and said at least one commanded turn rate signal to provide an actuator command signal.
14 . The system of claim 13 wherein said SAS includes a Proportional+Integral+Derivative (PID) controller.
15 . The system of claim 13 wherein said SAS includes an adaptive SAS.
16 . The system of claim 15 wherein said adaptive SAS includes a neural network.
17 . The system of claim 13 wherein said at least one filter includes at least one linear filter.
18 . The system of claim 13 wherein said at least one filter includes at least two linear filters in series.
19 . The system of claim 13 wherein said at least one filter includes at least one non-linear filter.
20 . The system of claim 13 wherein said attitude and heading reference system receives at least one signal from a global positioning system receiver.
21 . The system of claim 13 further including at least one actuator device, coupled to said guidance system processing unit and to an air wing adjustment device, for receiving said actuator command signal and in response to said actuator command signal, for moving said actuator device from a first position to a second position, said movement of said actuator device causing movement of said air wing adjustment device for effectuating a change in said air wing flight.
22 . A guidance system for an aircraft comprising:
at least one sensor, non-rigidly suspended from an air wing, said at least one sensor providing at least one signal indicative of an angular rate of turn of said aircraft, said at least one signal including an oscillation component and an angular rate of turn component;
at least one filter, receiving said at least one signal indicative of an angular rate of turn of said aircraft, for filtering said at least one signal to attenuate said oscillation component present in said at least one signal;
an attitude and heading reference system, for providing at least one commanded turn rate signal;
a guidance system processing unit including a stability augmentation system (SAS), receiving said at least one filtered angular rate of turn signal and said at least one commanded turn rate signal, for processing said at least one filtered signal and said at least one commanded turn rate signal to provide an actuator command signal; and
at least one actuator device, coupled to said guidance system processing unit and to an air wing adjustment device, for receiving said actuator command signal and in response to said actuator command signal, for moving said actuator device from a first position to a second position, said movement of said actuator device from said first to said second position causing movement of said air wing adjustment device for effectuating a change in said air wing flight.
23 . The guidance system of claim 22 wherein said air wing includes a parafoil and wherein said air wing adjustment device includes a plurality of parafoil lines.