Nearly circular transfer trajectories for descending satellites /

Simplified expressions describing the transfer from a satellite orbit to the point of atmospheric entry are derived. The expressions are limited to altitude changes that are small compared with the earth's radius, and velocity changes that are small compared with satellite velocity. They are further restricted to motion about a spherical, nonrotating earth. The transfer trajectory resulting from the application of thrust in any direction at any point in an elliptic orbit is considered. Expressions for errors in distance (miss distance) and entry angle due to an initial misalinement and magnitude error of the deflecting thrust are presented. The guidance and accuracy requirements to establish a circular orbit, and orbit corrections are also discussed.Includes bibliographical references (p. 15).Simplified expressions describing the transfer from a satellite orbit to the point of atmospheric entry are derived. The expressions are limited to altitude changes that are small compared with the earth's radius, and velocity changes that are small compared with satellite velocity. They are further restricted to motion about a spherical, nonrotating earth. The transfer trajectory resulting from the application of thrust in any direction at any point in an elliptic orbit is considered. Expressions for errors in distance (miss distance) and entry angle due to an initial misalinement and magnitude error of the deflecting thrust are presented. The guidance and accuracy requirements to establish a circular orbit, and orbit corrections are also discussed.Mode of access: Internet