Vertical ascent to geosynchronous orbit with constrained thrust angle

A discussion is presented about the overall payload ratio of a solid-rocket-booster-assisted laser propulsion system for geosynchronous-Earth-orbit payload launch with thrust-angle constraint. A trajectory shaping method is used for constructing the vertical ascent trajectory in the equatorial plane. There is a thrust angle under which the payload ratio (ratio of final mass to initial mass) is to be maximized. This maximum payload can be obtained only when the ground station can provide the required peak laser power Now, if the peak laser power is limited to a lower level, the payload ratio that can be obtained will also be lower. When the peak laser power that can be provided is too low, the thrust-to-weight ratio will he less than one at the initial phase of the launch. To keep the performance of the launching system, we include in the model a strap-on solid rocket booster to compensate the system for thrust loss. It is found that the penalty can be reduced significantly.