Developing a Multi-Objective Guidance Scenario for the Entry to the Earth’s Atmosphere

A. R. Alemi Naeeni; J. Roshanian

Volume 6, Issue 4 , January 2014, , Pages 53-62

Abstract
  In this paper, a multi-objective guidance scenario has been developed which could be used to improve the accuracy of sub-orbital modules at the entry to the earth’s atmosphere. Developed algorithm could be used for the trajectory shaping and adjusting of the trajectory relative to the desired position. ...  Read More

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

Closed-Loop Guidance with Final Velocity Constraint Using Time-Varying Weighting Coefficient for Shaping of Commanded Acceleration

S. H. Jalali-Naini

Volume 2, Issue 3 , December 2009, , Pages 1-12

Abstract
  In this paper, a closed-loop optimal guidance with final position and velocity constraints is obtained by applying time-varying weighting coefficient in the performance index in order to shape the commanded acceleration. The control system is assumed to be linear, time-varying, and of arbitrary order ...  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