Abstract
A non linear attitude control law has been synthesised for the early reentry trajectory of a space plane, in the transition domain corresponding to low dynamic pressure, where it is necessary to pass from full thruster control to full aerodynamic control The principle of this attitude control law is based on the “task oriented control” technique. It consists in first selecting an objective or task. In second, a decoupled dynamic is chosen for the evolution of the real value of that objective toward its desired value. From this desired dynamic, it is then computed the corresponding momentum to apply to the space vehicle. This desired momentum is finally obtained by a proper combination of aerodynamic control deflections and thruster ignition This new attitude control law has been applied to Hermes space plane and checked from the point of view of respect of output versus time templates for canonical inputs in the transition domain. This check has been done in nominal conditions but also with aerodynamic modelling errors and turbulence. In addition, simulations of the whole early reentry, including first bank maneuver, has been lead in order to evaluate thruster consumption and aerodynamic control activity
Published Version
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