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


Personal Author(s) : KALENSHER, B E


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/149918.pdf


Report Date : 12 Apr 1957


Pagination or Media Count : 42


Abstract : The equations of motion of a rocket are derived by applying the fundamental definition of the derivative to Newton's 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.


Descriptors :   *EQUATIONS OF MOTION , *GUIDED MISSILE TRAJECTORIES , EARTH ORBITS , MATHEMATICAL ANALYSIS , SATELLITE ATTITUDE


Subject Categories : Guided Missile Traj, Accuracy and Ballistics


Distribution Statement : APPROVED FOR PUBLIC RELEASE