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In this chapter, the aerothermodynamic phenomena of blunt body entry vehicles are discussed.
Laminar and turbulent heating rates play an important role in the design of Mars entry vehicles.
Two different entry vehicles are presented here: the Inflatable Reentry and Descent Demonstrator (IRDT), and Huygens.
An accurate determination of the catalytic property of thermal protection materials is crucial to design reusable atmospheric entry vehicles.
Implicit ablation and thermal response software was developed to analyse and size charring ablative thermal protection systems for entry vehicles.
The robust tracking control problem for Mars entry vehicles subject to parameter perturbations, external disturbances and initial state errors during the entry phase is investigated in this paper.
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When three or more beacon measurements are employed, the states of entry vehicle become observable.
Aerothermodynamic environment predictions play an important role in the heatshield design of Mars entry vehicle.
In this paper, a new adaptive cubature Kalman filter is proposed for state trajectory estimation of a hypersonic entry vehicle.
In this paper, the drag-based trajectory tracking guidance problem is investigated for Mars entry vehicle subject to uncertainties.
With the development of aerospace industry, the guidance system of an entry vehicle becomes more robust, reliable and autonomous.
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