Bhat, M Seetharama and Shrivastava, K (1987) An Optimal g-Guidance Scheme for Satellite Launch Vehicles. In: Journal of Guidance, Control, and Dynamics, 10 (1). pp. 53-60.
j_guidence_10-1_87.pdf - Published Version
Restricted to Registered users only
Download (653Kb) | Request a copy
A closed-loop steering logic based on an optimal (2-guidance is developed here. The guidance system drives the satellite launch vehicle along a two- or three- dimensional trajectory for placing the payload into a specified circular orbit. The modified g-guidance algorithm makes use of the optimal required velocity vector, which minimizes the total impulse needed for an equivalent two-impluse transfer from the present state to the final orbit. The required velocity vector is defined as velocity of the vehicle on the hypothetical transfer orbit immediately after the application of the first impulse. For this optimal transfer orbit, a simple and elegant expression for the Q-matrix is derived. A working principle for the guidance algorithm in terms of the major and minor cycles, and also for the generation of the steering command, is outlined.
|Item Type:||Journal Article|
|Additional Information:||copy right of this article belongs to American Institute of Aeronautics and Astronautics.|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||19 Jan 2010 09:49|
|Last Modified:||19 Jul 2011 10:28|
Actions (login required)