Reentry trajectories have been studied since the beginning of the space activity. In 1961 Yuri Gagarin performed a safe re-entry into the atmosphere from a Low Earth Orbit and soon after the Apollo missions began reentry from the Moon. There are two major issues in re-entry missions: the peak deceleration produced by the drag force and the peak heat flux produced by the conversion of the kinetic energy loss into thermal energy. The heat and deceleration peaks constraints are satisfied by trajectories that fly within a specified region called the entry corridor. In the case of ballistic reentry (negligible lift) the entry corridor can be determined by analytical formulae derived here that patch the Kepler solution (no drag) with the Allan-Egger formula (no gravity). To increase the entry corridor and control the trajectory to the desired landing point, a small aerodynamic efficiency is required. The three-dimensional equations for re-entry with lift are then analysed together with algorithms for correcting the point of impact.
Reentry Trajectories
Springer Aerospace Techn.
27.12.2024
47 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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