The dynamic equations of motion for a station-keeping satellite (such as a weather satellite) are where...

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The dynamic equations of motion for a station-keeping satellite (such as a weather satellite) are where x=2wj3w²x = 0, ÿ+2wx=u, x = radial perturbation, y = longitudinal position perturbation, engine thrust in the y-direction, as depicted in Fig. 7.95. If the orbit is synchronous with the earth's rotation, then = 2π/(3600 x 24) rad/sec. (a) Is the state x = [xxy y observable? (b) Choose x = [xxyy as the state vector and y as the measurement, and design a full-order observer with poles placed at S = -20, -3w, and -3w ± 3wj. Reference longitude Desired location on orbit The dynamic equations of motion for a station-keeping satellite (such as a weather satellite) are where x=2wj3w²x = 0, ÿ+2wx=u, x = radial perturbation, y = longitudinal position perturbation, engine thrust in the y-direction, as depicted in Fig. 7.95. If the orbit is synchronous with the earth's rotation, then = 2π/(3600 x 24) rad/sec. (a) Is the state x = [xxy y observable? (b) Choose x = [xxyy as the state vector and y as the measurement, and design a full-order observer with poles placed at S = -20, -3w, and -3w ± 3wj. Reference longitude Desired location on orbit

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a Observability Analysis Matrix Derivation The given system dynamics are 2 3x 0 y 2x u Combining these equations for y y 2x u Nowdefine the state vect... View the full answer