Abstract A study is performed to maximize aerodynamic performance of an atmospheric maneuvering vehicle, based on the starbody concept. A unique method of parameterizing these starbodies, which form a specific class of the generic “waverider” category of supersonic vehicle shapes is presented, with a focus on applicability to an atmospheric entry with both aerocapture and plane change. A simplified control system is also included in order to assess the effectiveness of such geometries in accomplishing desired mission objectives. A gradient based routine has been run to perform coupled vehicle shape and trajectory optimization. It is found that with high-performing aerodynamic designs on a reference mission to Mars, considerable lifting plane change is possible, on the order of 85 degrees, as well as successful capture into a low apoapsis orbit. General guidelines are also given that define the limitations of the aerodynamic plane change. It is shown that there is a direct tradeoff between incorporating increased plane change during the maneuver and other important design metrics such as maximum g-load and volumetric efficiency.
Concurrent Aerocapture with Orbital Plane Change Using Starbody Waveriders
2014
Aufsatz (Zeitschrift)
Englisch
Concurrent Aerocapture with Orbital Plane Change Using Starbody Waveriders
Springer Verlag | 2014
|Concurrent Aerocapture with Orbital Plane Change Using Starbody Waveriders
Online Contents | 2014
|British Library Conference Proceedings | 2012
|AIAA | 1994
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