AEROELASTIC DIVERGENCE
Aeroelastic Divergence Characteristics of Unguided, Slender Body, Multi-Stage Launch Vehicles
The primary function of this computer program is the calculation of the divergence dynamic pressure and associated divergence modal characteristics of unguided, slender-body, multistage launch vehicles. . The program also includes an option for calculating a generalized static margin which approximates the degeneration in rigid-body static margin due to aeroelasticity effects. Evaluated equations are also programmed to allow for the exclusion of the effect of aerodynamic crossflow resulting from vehicle angular velocities if desired. Other physical and aerodynamic properties calculated include total mass, center of mass, moments of inertia in pitch about the reference station, total aerodynamic lift curve slope, static aerodynamic center of pressure, rigid body static margin, and short period frequency.
Program Size: 1,551 Statements
Computer Language: FORTRAN IV
Copyright (c) 1996 Pacific HiTech, Inc. and COSMIC 
