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This paper introduces an algorithm to perform optimal reorientation of aspacecraft during a high speed flyby mission that maximizes the time a certaintarget is kept within the field of view of scientific instruments. The methoddirectly handles the nonlinear dynamics of the spacecraft, sun exclusionconstraint, torque and momentum limits on the reaction wheels as well aspotential faults in these actuators. A sequential convex programming approachwas used to reformulate non-convex pointing objectives and other constraints interms of a series of novel convex cardinality minimization problems. Thesesubproblems were then efficiently solved even on limited hardware resourcesusing convex programming solvers implementing second-order conic constraints.The proposed method was applied to a scenario that involved maximizing thescience time for the upcoming Comet Interceptor flyby mission developed by theEuropean Space Agency. Extensive simulation results demonstrate the capabilityof the approach to generate viable trajectories even in the presence ofreaction wheel failures or prior dust particle impacts.

Optimal Science-time Reorientation Policy for the Comet Interceptor Flyby via Sequential Convex Programming