To intercept an orbiting target by another satellite implies, that the two vehicles must arrive simultaneously to the same point in space. In the following a calculation procedure is presented for solving this coincidence problem. To facilitate the calculation of the unknown semi major axis of the interceptor's orbit, Lambert's Equation is rewritten in form of a power series which can be evaluated by a convenient differential correction technique instead of the usual trial and error method. (Author)
Satellite Interception
1960
2 pages
Report
Keine Angabe
Englisch
Midcourse guidance problem in satellite interception -- 1
Engineering Index Backfile | 1960
|Satellite proximate interception vector guidance based on differential games
British Library Online Contents | 2018
|