Both FSMG and VDSMG are designed while not considering the dynamic characteristics of missile autopilot; thus, the precision of guidance is not necessarily guaranteed when there is dynamic delay of autopilot.
Not considering the dynamic delay of the missile autopilot, we perform simulation comparison between the designed FSMG, VDSMG, and the augmented proportional navigation guidance law  [[??].sub.m] = -6[??][??] + 0.5[z.sub.1] (of APNG for short), where [z.sub.1] is the total disturbance estimated according to the observer of (21).
As shown in Table 1, APNG is completely invalid, while both FSMG and VDSMG have small miss distances in any of the two cases, with basically the same flight time.
Considering that the missile autopilot has first-order delay, we perform a simulation comparison between FSMG, VDSMG, and FNTSMG, where the time constant of missile autopilot is [tau] = 0.5.
As shown in Table 2, VDSMG is invalid, while both FSMG and FNTSMG have small miss distances.
When not considering the dynamic delay of missile autopilot, two guidance laws are designed, namely, FSMG and VDSMG.
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