The open-loop design reference trajectory data used to analyze the capability of the SLV-3 to perform its role for the Lunar Orbiter (LO) mission are presented. This information is required by the various design groups for computation of aerodynamic heating and of structural, dynamic, and aerodynamic loads. The principal trajectory design data presented include: mission profile and SLV-3 mission requirements; launch vehicle description; aerodynamics, propulsion, weights, and environmental data; Trajectory design constraints; and exchange coefficients.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite