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Finding the minimum time maneuver corresponds to solving the problem ((mathcal {P}_{S})).
This example deals with a minimum time maneuver of a coupled attitude-trajectory dynamic system.
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Their research, both experimental and numerical, has covered weave, wobble, chatter, simulators, vehicle modelling, tire modelling, handling, and minimum lap time maneuvering.
Simulation results for minimum time control of a two-axis gimbal system and for rapid maneuvering of a TDRS single-access antenna, wherein it is desired to limit the excitation of the satellite body to which the antenna is attached, are presented to illustrate the concepts.
Its approach stems from the fact that the minimum time to destination can be attained when the thruster(s) of the vehicle always operates at maximum thrust levels during the maneuver.
The minimum time to collision, defined as the remaining gap between the passing vehicle and the oncoming vehicle at the end of the passing process, expresses a measure of the risk involved in the passing maneuver.
Minimum time aggregation scheduling.
The last term J3 in Eq. 3c is a minimum time term multiplied by a scaling factor w T. By changing the scaling factor w T ∈ [0, 1] it is possible to produce faster maneuvers by relying on larger longitudinal and/or lateral accelerations and jerks.
In this section, we address the minimum time-energy pull-up maneuver problem for airborne launch vehicles with a focus on the numerical solution method.
The minimum-time orbital phasing maneuver for a spacecraft with an electric thruster is studied.
Eigenaxis rotation is generally regarded as a near-minimum time strategy for rapid attitude maneuver due to its constitution of the shortest angular path between two orientations.
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