An iterative method for finding the transient response of an automatically controlled missile having non-linear stiffness.
iterativemethodf00grah.pdf (6.488Mb)Abstract
An equation of missile motion in the pitching plane was found,
assuming a non-linearity in aerodynamic stiffness in the form of a
cubic term. An iterative method for approximating the angle-ofattack
response to a step displacement of elevator angle was
formulated. The results of applications of this method were
compared with computer solutions; convergence of the approximations was demonstrated. A simple feedback control system was designed, and the iterative
method was extended to the case of a control system step input.
The method was thought to have limited practical value because
of the labor required in using it.
Description
This thesis document was issued under the authority of another institution, not NPS. At the time it was written, a copy was added to the NPS Library Collection for reasons not now known. It has been included in the digital archive for its historical value to NPS. Not believed to be a CIVINS (Civilian Institutions) title.
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