|M.Sc Student||Tsalik Ronny|
|Subject||Inscribed Angle Guidance Law|
|Department||Department of Aerospace Engineering||Supervisor||Professor Tal Shima|
|Full Thesis text|
A three-point trajectory shaping guidance concept against stationary targets is presented in this thesis, based upon the principle of constant inscribed angles in a circle. This new guidance concept enables imposing a required impact angle by traversing specific circular paths. The guidance concept is implemented using a simple controller, obtained from linearization around the required nominal circular trajectory. Implementation of the guidance law requires information of the inscribed angle only. Several application concepts for the measurement of the inscribed angle are discussed. Linear and non-linear dynamic models are compared through simulation, and results are shown for various scenarios of applied desired impact angles. The proposed law can be viewed as generalization of the line-of-sight guidance concept. The guidance concept is investigated also against moving targets, the governing equations of motion are developed. It is shown that for moving targets the desired inscribed angle is not based only on the impact angle, but also on the lead-angle. For the particular case where the inscribed angle is equal to the lead angle the guidance concept yields similar trajectories as parallel navigation.