R. Y. Chiang

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P (d=dt)w gives 3u = 4((d 2 =dt 2) + (d=dt) + 1)y as the corresponding controller. The significance of the results of this section is that if the measurements are noise-free, then there is no harm, in fact, it can be helpful, to differentiate the measurements and achieve better disturbance attenuation. VI. CONCLUSION We proved an alternative and easily(More)
The recently developed nonlinear ser-vomechanism theory is applied to the attitude control of large maneuvering spacecraft subject to sinusoidal disturbances and parametric uncertainties. Simulation shows signticant advantages of our attitude controller over the controller resulting from the feedback linearization approach. Future spacecraft present(More)
q'his paper presents a systematic method to design roljust colitrollem from experimental data so as to ensure that the cont,rollcr is robust with J espect to all plants which cannot be discounted based on the data (to within a specified statistical confidence). l'hc present paper extends previous multi variable results to the structured uncertainty case and(More)
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