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This paper presents a methodology for the concurrent first-stage preliminarydesign and ascent trajectory optimization, with application to a Vega-derivedLight Launch Vehicle. The reuse as first stage of an existing upper-stage(Zefiro 40) requires a propellant grain geometry redesign, in order to accountfor the mutated operating conditions. An optimization code based on theparallel running of several Differential Evolution algorithms is used to findthe optimal internal pressure law during Z40 operation, together with theoptimal thrust direction and other relevant flight parameters of the entireascent trajectory. Payload injected into a target orbit is maximized, whilerespecting multiple design constraints, either involving the alone solid rocketmotor or dependent on the actual flight trajectory. Numerical results for SSOinjection are presented.

Integrated Optimization of Ascent Trajectory and SRM Design of Multistage Launch Vehicles