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.
Aerodynamic Performance Analysis Slv-3/Agena/Lunar Orbiter
1966
123 pages
Report
No indication
English
Spacecraft Trajectories & Flight Mechanics , Manned Spacecraft , Launch vehicles , Ascent trajectories , Mission profiles , Military requirements , Design , Aerodynamics , Liquid propellant rocket engines , Weight , Simulation , Computer programming , Flight control systems , Earth models , Atmosphere models , Aerodynamic heating , Aerodynamic loading , Staging , Errors , Scattering , Agena , Atlas , Lunar orbiter