The maneuvers of interest are doublets ranging in magnitude and centered

around a trim condition. Therefore, the assumption of linearity is reasonable since the

maneuvers are about trim. For the approximation, the rates which are considered are

roll and yaw rate because they are of most interest for maneuvers such as doublets.

The accelerometers were considered but the data was very noisy, therefore, not

allowing for accurate approximations to be made.

 The simulated and measured values of roll rate and yaw rate are shown in

Figure 5-12.

 200 200
 150i 150
 100 100
 50 50
 0 0
 4 -50 \- -50
 -100 -100
 150 150
 -200 -------------------- 200--------------------
 0 05 1 15 22 25 0 05 1 1 5 2 25
 Time(sec) Time(sec)
Figure 5-12: Simulated (- ) and Actual (-) Roll Rate(left) and Yaw Rate(right)
Responses to Morphing Doublet


 The simulated responses show good correlation with the actual data. The model is

thus considered a reasonable representation of the aircraft dynamics as it is excited by

the doublet. The existence of such a model is important for future design of autopilot

controllers but it is also valuable for interpreting the morphing.

 When using the ARX simulation in Matlab, a linear approximation could not be

made on the maneuvers which were not centered around trim. Therefore, not only are

maneuvers around trim desired for a linear approximation, but they are also necessary

in order for the simulation to be done.

 The model which will be used was chosen because it produced the closest match

to the maneuver as compared to four other doublets. The maneuvers compared were

from the same data set, but the one that was chosen resulted in a closer match due to