Abstract
In a previous paper, the authors addressed the problem of augmenting gravity assist by using planetary atmospheric maneuvering such that the heliocentric velocity of the spacecraft after flyby was maximized. The optimization was carried out by using Pontryagin's maximum principle. The results showed that the heating rate was high during maneuvering of the spacecraft through the atmosphere. Therefore in the present paper, a heating rate constraint is imposed on the atmospheric trajectory for aerogravity assist (AGA). A comparison of AGA for Venus and Mars is given that shows the overall superiority of using Mars over Venus. The results also show that AGA with heat constraint gives slightly lower heliocentric velocity than AGA without heat constraint, particularly when the drag polar based on the Newtonian theory for the hypersonic regime is used in numerical calculations. This study concludes that AGA is possible with moderate planetocentric velocity.
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