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Accession Number:
AD0149918
Title:
EQUATIONS OF MOTION OF A MISSILE AND SATELLITE FOR AN OBLATE-SPHEROIDAL ROTATING EARTH
Corporate Author:
JET PROPULSION LAB PASADENA CA
Report Date:
1957-04-12
Abstract:
The equations of motion of a rocket are derived by applying the fundamental definition of the derivative to Newtons second law of motion. Three independent cases are considered notion of the missile Center of mass, rotation of the missile about a transverse axis through the center of mass, and rotation of the missile about the longitudinal axis. The second case describes the motion in pitch or yaw, and the third case describes the rotation spin or roll of the missile due to a ring of small lets placed around its circumference. The equations of motion of the center of mass ate then modified to describe the motion of a satellite moving around the earth in a nearly circular orbit. Finally, a method is developed for computing the approximate impact point of the missile by algebraic means.
Supplementary Note:
Rept. on Proj. ORDCIT. DOI: 10.21236/AD0149918
Pages:
0042
Distribution Statement:
Approved for public release; distribution is unlimited.
Contract Number:
DA-04-495-ORD-18
File Size:
1.26MB
