A minimum fuel minimum range error controller for a surface-to-surface missile

Author

Yun-Ching Tsuei

Date of Award

12-1983

Degree Type

Dissertation

Degree Name

Doctor of Philosophy

Major

Engineering Science

Major Professor

John M. Bailey

Committee Members

William T. Snyder, John N. Snider, Joseph M. Googe, Richard J. Jendrucko

Abstract

The purpose of this investigation was to conduct a sensitivity analysis of a surface to surface optimally controlled guided missile and compare it with one controlled by a conventionally guided missile. In particular, the problem was to find how much the performance of this missile was adversely affected if some of the parameters did not adhere to those utilized in the optimal simulation and how well the conventional scheme compared.

Two methods were employed in measuring the performance of "cost" of the missile. First a cost function was selected which was a function of the summation of all the deviations from an optimal trajectory and the amount of side thrust that was used by the steering rocket. Secondly, selected states at rocket burnout of the optimal trajectory were compared with those of the nominal trajectory to determine the magnitude of error as the missile began its ballistic path back to earth.

The method for determining the optimal trajectory and all the experimental data was obtained by mathematically simulating the missile on a digital computer. The aerodynamic equations of the missile and other parameters affecting its flight were obtained from a previous study of a typical surface-to-surface guided missile. I Its range was approximately 30 miles and it had a powered flight lasting for 5.12 seconds.

The parameters that were varied in the sensitivity analysis were:

1 . drag or axial force coefficient, C_A;

2. lift or normal force coefficient, C_N; 3. length from the tail to the center of mass;

4. length from center of mass to center of pressure, X;

5. thrust misalignment.

The exact procedure was to vary the above parameters one at a time by plus or minus 5% and then simulate the missile flight on the computer under several different winds. At the completion of each flight, the data for the cost function and selected states was analyzed to determine the effect of the perturbation.

In conclusion, it was found that the missile attitude was the parameter having the most significant effect on the missile's performance. The conventional scheme had a much smaller miss distance but in some cases (thrust misalignment) used more fuel.

Recommended Citation

Tsuei, Yun-Ching, "A minimum fuel minimum range error controller for a surface-to-surface missile. " PhD diss., University of Tennessee, 1983.
https://trace.tennessee.edu/utk_graddiss/13150