An optimal Qguidance scheme for satellite launch vehicles
Abstract
A closedloop steering logic based on an optimal Qguidance is developed here. The guidance system drives the satellite launch vehicle along a two or threedimensional trajectory for placing the payload into a specified circular orbit. The modified Qguidance algorithm makes use of the optimal required velocity vector, which minimizes the total impulse needed for an equivalent twoimpulse 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 Qmatrix 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.
 Publication:

Journal of Guidance Control Dynamics
 Pub Date:
 February 1987
 DOI:
 10.2514/3.20180
 Bibcode:
 1987JGCD...10...53B
 Keywords:

 Launch Vehicles;
 Optimal Control;
 Spacecraft Guidance;
 Spacecraft Launching;
 Trajectory Optimization;
 Algorithms;
 Circular Orbits;
 Differential Equations;
 Transfer Orbits;
 Astrodynamics