Optimization of the trajectory of the spacecraft insertion into the system of heliocentric orbits

The possibility of the spacecraft insertion into the system of operational heliocentric orbits has been analyzed. It has been proposed to use a system of several operational heliocentric orbits. On each orbit, the spacecraft makes one or more revolutions around the Sun. These orbits are characterize...

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Bibliographic Details
Published in:Cosmic research 2017-05, Vol.55 (3), p.214-223
Main Authors: Konstantinov, M. S., Thein, Min
Format: Article
Language:English
Subjects:
Astronomy
Astrophysics and Astroparticles
Astrophysics and Cosmology
Electric propulsion
Inclination
Orbit insertion
Orbits
Physics
Physics and Astronomy
Polar environments
Polar regions
Solar orbits
Space Exploration and Astronautics
Space Sciences (including Extraterrestrial Physics
Spacecraft
Spacecraft propulsion
Trajectory optimization
Transportation
Transportation systems
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Summary:The possibility of the spacecraft insertion into the system of operational heliocentric orbits has been analyzed. It has been proposed to use a system of several operational heliocentric orbits. On each orbit, the spacecraft makes one or more revolutions around the Sun. These orbits are characterized by a relatively small perihelion radius and relatively high inclination, which allows one to investigate the polar regions of the Sun. The transition of the spacecraft from one orbit to another has been performed using an unpowered gravity assist maneuver near Venus and does not require the cruise propulsion operation. Each maneuver transfers the spacecraft into the sequence of operational heliocentric orbits. We have analyzed several systems of operational heliocentric orbits into which the spacecraft can be inserted by means of the considered transportation system with electric propulsion (EP). The mass of the spacecraft delivered to these systems of operational orbits has been estimated.
ISSN:0010-9525
1608-3075
DOI:10.1134/S0010952517020034