No description available.

A method is developed to estimate the projection of a higher dimensional (three or more) controllable set onto a lower dimensional (usually one or two) space. This method requires that an n-dimensional dynamical system subject to a scalar control be transformed into two lower dimensional subsystems by choosing a proper transformation matrix. It is shown that such a transformation can always be determined for an n-dimensional linear I/O system. For some nonlinear dynamical system problems such as an aircraft missile avoidance problem, a proper transformation matrix still can be determined. From the transformed system, both an overestimate and an underestimate for an actual projected controllable set in the state space of interest can be provided by using the method presented in this dissertation. With these information, the actual projected controllable set can be estimated. Two linear I/O systems subject to a scalar control and an aircraft missile avoidance problem are used to illustrate the method.

No description available.

No description available.

Impact point dispersion of a direct fire rocket can be drastically reduced with a ring of appropriately sized lateral pulse jets coupled to a trajectory tracking flight control system. The system is shown to work well against uncertainty in the form of initial off-axis angular velocity perturbations as well as atmospheric winds. For an example case examined, dispersion was reduced by a factor of one hundred. Dispersion reduction and mean miss distance are strong functions of the number of individual pulse jets, the pulse jet impulse, and the trajectory tracking window size. Proper selection of these parameters for a particular rocket and launcher combination is required to achieve optimum dispersion reduction to the pulse jet control mechanism. For the lateral pulse jet control mechanism that falls into the category of an impulse control mechanism, the trajectory tracking flight control law provides better reduction in dispersion and mean miss distance than the proportional navigation guidance law especially when small number of individual pulse jets is used. Estimation of body frame components of angular velocity and angular acceleration of a rigid body projectile undergoing general three-dimensional motion using linear acceleration measurements is considered. The results are comparable to those obtained from a conventional Inertial Measurement Unit (IMU) that composes of accelerometers and gyroscopes. From the study of the effect of sensor errors to the measurement and the control performance, the sensitivity of the angular rate estimation to the sensor noise is a strong function of the constellation of these three accelerometers. When more than three point measurements are used, the most effective method to fuse data is with one cluster that contains all sensors. In the conventional IMU, the dispersion and miss distance are less sensitive to the errors from accelerometers than to the gyroscopes. The estimation of angular rates plays essential roles in the performance of the control system in the reduction of dispersion and miss distance. The use of many accelerometers does not guarantee to reduce the sensitivity to errors. The selection of constellation among accelerometers in the data fusion process must be carefully taken into account. / Graduation date: 2002

Thesis (M.S.)--West Virginia University, 2009. / Title from document title page. Document formatted into pages; contains xii, 113 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 76-77).

No description available.

No description available.

No description available.

No description available.