منابع مشابه
Spacecraft Attitude Tracking Control
The problem of reorienting a spacecraft in to acquire a moving target is investigated. The spacecraft is modeled as a rigid body with N axisymmetric wheels controlled by axial torques, and the kinematics are represented by Modified Rodriques Parameters. The trajectory, denoted the reference trajectory, is one generated by a virtual spacecraft that is identical to the actual spacecraft. The open...
متن کاملPassive Attitude Control for Spacecraft
The stability of spacecraft attitude is studied with considering sinusoidal disturbance. A passive attitude controller without angular velocity measurement for spacecraft described by quaternion is designed. The passive controller has no information related to system parameters. So it has robustness to model error and uncertainty of model parameters. The stability of spacecraft attitude control...
متن کاملThe Distributed Spacecraft Attitude Control System Simulator: Development, Progress, Plans
Virginia Tech has developed a testbed comprised of two independent spherical air-bearing platforms for formation flying attitude control simulation, the Distributed Spacecraft Attitude Control System Simulator (DSACSS). The DSACSS provides the flexibility to experimentally implement many types of control techniques. Novel individual platform control options include nonlinear compensation of an ...
متن کاملTurner and Hall Adaptive Spacecraft Attitude Control ADAPTIVE SPACECRAFT ATTITUDE CONTROL USING NEURAL NETWORKS
Neural networks offer a unique approach to controlling a dynamically changing system. By updating synaptic weights of an interconnected, algebraic framework, desired system objectives can be reached despite an unknown operating environment. This research implements a neural network for controlling the attitude of a satellite with unknown system disturbances. The training and updating of the con...
متن کاملNonlinear H ∞ for Spacecraft Attitude Control
This paper presents a nonlinear H∞ state feedback attitude control design method for spacecraft large angle maneuvers, which is subject to moment-of-inertia (MOI) uncertainty. Moreover, the operation of attitude maneuver is affected by external disturbances. The attitude control design thus employs a nonlinear H∞ method to achieve stability and robustness so that both MOI uncertainty and extern...
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ژورنال
عنوان ژورنال: The International Journal of Multiphysics
سال: 2007
ISSN: 1750-9548
DOI: 10.1260/175095407781421586