Spacecraft Insertion into Jupiter Galilean Satellites Orbits by the Spatial Aerodynamic Maneuver

Aeronautical and Space-Rocket Engineering


Аuthors

Starinova O. L.*, Sharipova A. R.**

Samara National Research University named after Academician S.P. Korolev, Moskovskoe shosse, 34, Samara, Russia

*e-mail: starinova@ssau.ru
**e-mail: Sharipovaaliya2016@yandex.ru

Abstract

Being energy intensive, the interplanetary flights to Jupiter and its satellites require large propellant margin. The objective of the work consists in developing a technique for an aerodynamic maneuver application in the atmosphere of Jupiter to reduce the working fluid consumption for the maneuver of the spacecraft transition from an interplanetary trajectory to the orbits of the Jupiter Galilean satellites.
The change of both the orbital plane and the spacecraft orbit parameters is necessary for a spacecraft injecting into the Jupiter Galilean satellites orbits. The orbital plane rotation with the orbit aphelion point radius changing with minimum working body consumption without the cruise engine activation is may be accomplished due to the dense Jupiter atmosphere by the spatial aerodynamic maneuver.
The article considers the spacecraft motion in the atmosphere of Jupiter with a constant angle of attack, angle of slip and lift-to-drag ratio. The atmosphere of Jupiter was described by a mathematical model based on the results of the Galileo probe exploration. The structure of the Jupiter atmosphere was measured at altitudes from 1,03 · 106 m to 1,33 · 105 m below the level of 1,0 · 105 Pa during the Galileo probe atmospheric entry and descent.
The flight is being by a spacecraft with a low-thrust engine. The speed and elements are being determined on the heliocentric section of the flight. To enter one of the orbits of the Jupiter Galilean satellites (Io, Europa, Ganymede and Callisto), it is necessary to decelerate the spacecraft on the planet account atmosphere and change the inclination. On leaving the Jupiter atmosphere, the spacecraft performs maneuvers by the propulsion system to form a specified orbit.
The spatial aerodynamic maneuver was modeled from the atmospheric altitude of 4,5 · 105 m. The entrance angle to the atmosphere of each planet of destination and gliding angle were being selected for the spacecraft transition to each of the Jupiter Galilean satellites orbits. 
When modeling the spacecraft motion in the Jupiter atmosphere of, it is necessary to account for the overloads acting on the spacecraft. According to the computational results, the overload values are in the range from 1.7 to 3.05 units. By reference to the results, it is obvious that while the spatial aerodynamic maneuver performing, maximum overloads acting on the spacecraft do not reach critical values.
The authors performed modeling of the spatial aerodynamic maneuver with a view to entering orbits of each of the Jupiter Galilean satellites, as well as computation of the Io, Ganymede, Europa and Callisto satellites orbits forming. The graphs of velocity changing vs. altitude; the altitude changing vs. distance, velocity changing vs. time and angle of exit vs. time for each of the Galilean satellites were plotted by the results of modeling. The trajectories of the spacecraft entering the atmosphere of Jupiter during transition to the orbits of the Jupiter Galilean satellites are demonstrated as well.

Keywords:

spacecraft for Jupiter exploration, motion in the Jupiter atmosphere, spatial aerodynamic maneuver in the Jupiter atmosphere, motion equations of a spacecraft in the atmosphere of the planet, model of the Jupiter atmosphere

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