During the docked phase to the Columbus Free Flyer Laboratory (CFFL), the Hermes Space Vehicle (HSV) is required to perform the attitude control of the composite (HSV + CFFL) vehicle, keeping its longitudianl axis orientated towards the Sun. Because of its duration and of the profile of perturbating torques associated with the required pointing mode, this phase impacts widely on the propellant budget of the HSV and on the number of activations to be delivered by its front thrusters. A method to define realistic objectives is introduced as a guide for the design studies of the Hermes attitude control. The optimal propellant consumption during docked phase is calculated, taking into account the actual Hermes propulsive architecture. An activations strategy maximizing the duration of attitude free drift during two consecutive commutations, and allowing the propellant consumption to be maintained not far from the optimum is described. Simulation results are given for verification purpose. The proposed activations strategy is possibly an interesting basis for future development of spacecraft control laws.
Objective Propellant Consumption and Thrusters Activations for the Attitude Control of the Hermes-Columbus Composite
1991
6 pages
Report
No indication
English
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