Loading...

A near optimal midcourse guidance law based on spherical gravity

Deihoul, A. R ; Sharif University of Technology | 2003

126 Viewed
  1. Type of Document: Article
  2. Publisher: Sharif University of Technology , 2003
  3. Abstract:
  4. In [1], an optimal midcourse guidance law for close distances, where the difference of gravity for interceptor and ballistic missile is negligible, was introduced. There, a closed form solution, based on an optimization problem, was found, with very good performance for close distances but degraded performance in real problems with unequal gravity for missile and interceptor. In this paper, the difference of gravity is taken into account by considering a spherical gravity model. A new equation to express the relative motion between missile and interceptor is used to derive a "Near Optimal Guidance Law". The results found using the new derivation are similar to those in [1] but it provides a guidance law with matrix coefficients. Next, the performance of the guidance law is improved using Kepler's algorithm. This modified approach results in an almost perfect intercept, even for large distances between missile and interceptor. © Sharif University of Technology, October 2003
  5. Keywords:
  6. Gravity ; Trajectory prediction ; Missile
  7. Source: Scientia Iranica ; Volume 10, Issue 4 , 2003 , Pages 436-442 ; 10263098 (ISSN)
  8. URL: http://scientiairanica.sharif.edu/article_2608.html