Abstract
A guided flight vehicle using the principle of proportional navigation has a target tracker to measure the line-of-sight angle rate. The tracker dynamics have the uncertainties caused by the gain variation in tracking loop, the imperfect tracker stabilization and the tracker acceleration sensitivity.
In the guidance system including these uncertainties, the target tracker measurement noise such as white glint noise and white fading noise is apt to aggravate the system performance.
Applying Adjoint Method to this guidance system, we obtain a new performance index, which can be used to evaluate the uncertainties from the standpoint of system performance. In addition, the relation between the index and the system performance is presented.
