Abstract
Thedynamicsassociated with thejettisoning ofa strap-onboosterfrom theparentlaunch vehicle isinvestigated. The present analysis accounts for experimental aerodynamics of separation utilizing a two-step method that employs a wind tunnel in a problem-solving mode. The e rst step consists of collecting wind-tunnel test results at a large number of points in the multidimensional space of independent variables. A suitable approach for surface e tting to the data leads to empirical models of the aerodynamic behavior, which are used in numerical simulations to design the appropriate separation system. The suitability of this design is examined, as a second step, through extensivesimulationsusingthewindtunnelasahardwaresubroutinetogenerateaerodynamicforcesandmoments. Two strap-on booster cone gurations are used for illustration.
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