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The styles of war progress with the development of science. To attack the
enemy by launching ballistic missiles must come true in the future. To
defense the threat of ballistic missiles is a very important work in many
advanced countries. Some topics about the terminal guidance problems of
high altitude anti-ballistic-missile missile are studied in this thesis,
from the references to the theater-high-altitude-area-defense (THAAD)
project of U.S. Army.
The imaginary target, which the intercept missile must impact, is with
the advantage of velocity (about twice of the velocity of the missile).
Also with the limitation of the structure of the missile and the flight
environment, the missile can only output thrust with fixed amplitude and
perpendicular to the axis of the missile. The divert thrust is used to
change the flight trajectory of the missile. A kind of proportional
navigation guidance law based on the uniform concept of zero-effort-miss
(ZEM) is proposed, and it is used to compute the acceleration command
according to the attitude of the missile. Also, the guidance law can
estimate the initial conditions the midcourse guidance must achieve.
To decide the firing of impulse thrust and torque, a new firing logic
based on the prediction of ZEM is proposed, too. The divert control system
and the attitude control system are integrated and the performance is
demonstrated by numerical simulation.
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