Derivation of Kane's equations of motion and the formulation of an initial-value problem for the Polaris A3 missile
Kane's Equations of Motion for the Polaris A3 missile are derived, and an initial-value problem which can be used in a time simulation of the missile's flight is developed. A brief overview of Kane's method for dynamical analysis is included to assist readers who may not be familiar with the techniques employed. The model assumes rigid body dynamics, and accomodates the earth's geometry and gravity field, the aerodynamic forces, and the missile's thrust vector control.
- Research Organization:
- Sandia National Labs., Albuquerque, NM (USA)
- DOE Contract Number:
- AC04-76DP00789
- OSTI ID:
- 5809718
- Report Number(s):
- SAND-86-0403; ON: DE86009784
- Country of Publication:
- United States
- Language:
- English
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