AN OPTIMUM INTERCEPTION LAW WITH BOUNDED CONTROL IN PRESENCE OF NOISE
- 1 February 1967
- report
- Published by Defense Technical Information Center (DTIC)
Abstract
The subject of this report is the derivation of optimum control rule for guidance of a space vehicle which seeks to reach a moving target. The available thrust vector is assumed to be bounded in magnitude and any on-board measurements to be contaminated by random noise. The performance measure is chosen to be the expectation of terminal miss distance. The optimum control rule is shown to be a function of the sign of the expected value of line-of-sight angular rotation with respect to an inertial coordinate system and, consequently, measurement of this angular rate (e.g., by means of an angle tracking system) is sufficient to implement the optimum control rule. The optimum controller is very simple and more suited to space application than the conventional method of proportional navigation commonly used in missile systems operating in lower altitudes due to the desirability of using reaction jets in space vehicles.Keywords
This publication has 0 references indexed in Scilit: