Guidance Strategy for Solid Propelled Launchers

Satellite launcher pointing for orbit injection with uncontrolled solid-propellant last stage

“…The energy and angular momentum equations that hold for the suborbital trajectory are applied for the time t i [3]:…”

“…If results Dt a t i < t tip + t cent (fault: insu©cient time in the increasing altitude sector), then E i is recalculated for the decreasing altitude sector [3]: E i = 2π−E i . Then, Dt a t i is recalculated as in Eq.…”