Thesis - Leigh Moody.pdf - Bad Request - Cranfield University

Chapter 7 / Missile Trajectory Optimisation
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Changes in the controls are limited between optimisation cycles to make the
optimisation process more robust. These controls are then converted into
guidance demands for fire control, launcher steering and in-flight
manoeuvring. Validation of the optimiser can be undertaken once the noise
characteristics associated with the boundary conditions provided by the state
observers are known. This work will:
• Consider each contribution to the cost function in turn and compare the
trajectory produced by the optimiser, wherever possible with analytic
results, and with the baseline results presented in this document.
• Quantify any increase in target capture region compared with conventional
guidance alternatives.
• Investigate the convergence rate from the initial trajectory and review other
alternatives such as keeping the controls at zero and pointing the launcher at
the predicted intercept point.
• Assess convergence rates as a function of processor load to determine if online
optimisation is feasible with current processors.
• Systematically add cost function elements and dynamic constraints to
determine if in combination they prevent the optimiser from converging to a
sensible solution. If so, can the cost weights be re-balanced, or be made
trajectory dependent, to avoid the conflicts.
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