Publication Date:
2011-08-24
Description:
The effect of continuous tangential thrust on the orbital motion and mass loss of a vehicle initially in a circular orbit is investigated analytically. It is shown that, for a thrust-to-weight ratio of greater than 0.16175, escape speed will eventually be reached along an unwinding spiral trajectory. For lower thrust-to-weight ratios, escape speed is never attained, and the flight path oscillates around a logarithmic spiral trajectory. Formulas are obtained for the approximate orbital motion and time of flight along each type of trajectory and for mass loss due to expenditure of rocket propellant.
Keywords:
ASTRODYNAMICS
Type:
Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 15; 6; p. 1503-1507.
Format:
text
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