Derivation of Kane's equations of motion and the formulation of an initial-value problem for the Polaris A3 missile

Technical Report · Sat Mar 01 00:00:00 EST 1986

OSTI ID:5809718

Etter, J R

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
• Resource Relation: Other Information: Portions of this document are illegible in microfiche products. Original copy available until stock is exhausted
• Country of Publication: United States
• Language: English

Related Subjects

45 MILITARY TECHNOLOGY, WEAPONRY, AND NATIONAL DEFENSE
MISSILES
EQUATIONS OF MOTION
DYNAMICS
THRUSTERS
DIFFERENTIAL EQUATIONS
EQUATIONS
MECHANICS
PARTIAL DIFFERENTIAL EQUATIONS
450202* - Explosions & Explosives- Nuclear- Weaponry- (-1989)