The ballistic design of interplanetary missions consists of a choice of control programs and associated trajectories that ensure the achievement of the objective while meeting a variety of constraints. The use of solar-sails spacecraft for interplanetary missions imposes additional restrictions on mission parameters. These include limitations on the flight duration, the minimum distance from the Sun, the maximum angular velocity of spacecraft’s rotation and many others. Obtaining an exact optimal solution to such complex problem is associated with significant theoretical and computational difficulties. In this paper, they describe a technique for designing interplanetary missions of a solar sail spacecraft, based on the use of locally optimal control laws. This method allows determining such a combination of these laws, which ensures all mission’s requirements. An example of the application of the described technique to the calculation of the research mission associated with the exit from the Solar system is given.
The mission’s design of solar sail spacecraft based on locally-optimal control laws
ICNPAA 2018 WORLD CONGRESS: 12th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences ; 2018 ; Yerevan, Armenia
AIP Conference Proceedings ; 2046 , 1
2018-12-04
8 pages
Conference paper
Electronic Resource
English
ENGINEERING NOTES - Heliocentric Solar Sail Orbit Transfers with Locally Optimal Control Laws
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