DOI: 10.5937/jaes0-28127
This is an open access article distributed under the CC BY 4.0
Volume 18 article 749 pages: 705 - 712
The problem of launching a rocket into the Earth’s orbit has already been solved using the regularization method in
previous studies. But the regularization method remains relevant for application to solving integral equations of the
first kind, which determine the components of speed and acceleration. The problem of optimal control of propellant
consumption during the insertion of a rocket into a circle orbit of the Earth is solved using regularized solutions of
integral equations of the first kind which are solutions of corresponding Euler equations on discrete-time net. The
influence of the regularization parameter and some additional parameters on precision of discredited problem is investigated.
Calculations are carried out for existing chemical rocket engine and promising plasmic one. Considered
algorithm is summed up easily to problem of suborbital flights by setting desired coordinate system and modifying
motion equations. Conclusions were drawn about the required speed for the lowest fuel consumption, as well as
about the problem for a single-stage rocket. Thus, the development of a plasma rocket engine with an exhaust velocity
is more than ten times higher than that of a chemical one.
This research was supported by the Ministry of science
and high education of the Russian Federation in the
frame of the basic part of government-supported researches
(project No 9.9074.2017/БЧ).
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