A guidance algorithm for launch to equatorial orbit

摘要

The physical model chosen for this study is a two-stage launch vehicle. Both stages have liquid propellant motors with uncontrollable thrust magnitudes. However, the thrust direction is controllable, i.e. thrust vector control is possible. The first stage separates once its fuel has been consumed, and at this time the second stage motor ignites. The launch vehicle is designed to insert a 10 kg research satellite into a near circular LEO at the height of 200 km.