Developing a New Explicit Guidance Method for the Trajectory Correction of Sub-Orbital Modules

A. R. Alemi Naeeni; J. Roshanian

Volume 6, Issue 3 , October 2013, , Pages 15-26

Abstract
  This paper presents an explicit guidance method which could be used in the problems of orbit correction for sub-orbital modules. This method is based on solving the Lambert problem. Two efficient methods of solving the Lambert problem are introduced and compared. Using of the selected method a guidance ...  Read More

Flight Path Angle Steering with Lambert Guidance Reference

R Zardashti; M Bagherian

Volume 2, Issue 2 , July 2009, , Pages 75-79

Abstract
  In this paper a new guidance technique for ballistic missiles and launch vehicles is proposed. Generally the Lambert guidance is used to generate missile nominal (correlated) parameters through powered flight to put it in a ballistic flight path. Because of uncertainties and undesired factors, the nominal ...  Read More