The Orbital Recovery Problem

Résumé du livre

An analysis technique has been developed which makes possible a rapid, accurate solution of the orbital return problem in terms of the determination of recall opportunities and the lateral-range requirements associated with these opportunities for the recovery of spacecraft. The methods of application of the analysis technique through an analytical-computer solution, a computer-graphical solution, and a slide-rule solution are discussed. The technique of analysis may be applied to the problem of return from any orbit inclination to any point or number of points on earth. In addition, the technique allows consideration of return from circular or elliptical orbits with any period. Although the analytical-computer solution may be costly in terms of machine time, the computer-graphical solution is shown to be practical method of obtaining rapid, economical results for a large number of constraints without adding any appreciable inaccuracy to the solution. Examples of the application of the computer-graphical solution are presented for return from circular orbits having periods of 1.5 and 10 hours and from an elliptical orbit with a period of 2 hours and apogee and perigee distances of 5165 and 3600 nautical miles, respectively. The computer-graphical technique of solution developed in part I of this report is used to select recovery sites for the wide spectrum of constraints presented separately in part II.