are just count commands to the servo because the actual deflection caused by morphing

is difficult to quantify.

 40

 30
 -0


 o 10


 -10

 -20

 301
 0 05 1 15 2 25
 Time(sec)
 Figure 6-5: Doublet Command to Morphing Servo



 The responses to the morphing doublets are measured by the on-board data

acquisition system. The roll rate and yaw rate are presented in Figure 6-6.

 80 80

 60 60

 40 40


 S20 \ 20
 0 0


 -40 40

 60 60
 0 05 1 15 2 25 0 05 1 15 2 25
 Time(sec) Time(sec)
 Figure 6-6: Roll Rate(left) and Yaw Rate(right) in Response to Morphing Doublet



 The roll rate is clearly correlating well with the commanded doublet and demon-

strates the morphing is capable of commanding roll maneuvers. The yaw rate is

somewhat more difficult to understand. Notably, the aircraft builds up yaw rate approx-

imately 0.5 seconds after the onset of the doublet command. This flight characteristic

results from the single-sided nature of the morphing. Essentially, the wing that is

morphed loses lift but also increases drag. The loss of lift immediately causes rolling

and the increase of drag causes a slight delay in building up the yaw rate.