Aerodynamic force and moment equations are developed for 6-DOF missile simulations of both the ascent phase of flight and a tumbling re-entry. The missile coordinate frame (M frame) and a frame parallel to the M frame were used for formulating the aerodynamic equations. The missile configuration chosen as an example is a cylinder with fixed fins and a nose cone. The equations include both the static aerodynamic coefficients and the aerodynamic damping derivatives. The inclusion of aerodynamic damping is essential for simulating a tumbling re-entry. Appended information provides insight into aerodynamic damping.
Missile Aerodynamics for Ascent and Re-entry
2012-11-01
Report
No indication
English
Missile Aerodynamics for Ascent and Re-entry
NTIS | 2012
|SLUB | 1988
|NTRS | 1988
|NTIS | 1990