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search.filters.applied.f.advisor: Braun, Robert D. × End date: 2016 × Start date: 2016 × Item Type: Publication × search.filters.applied.f.isOrgUnitOfPublicationTitle: Daniel Guggenheim School of Aerospace Engineering × search.filters.applied.f.isSeriesOfPublicationTitle: Master of Science in Aerospace Engineering × search.filters.applied.f.isSeriesOfPublicationTitle: Master's Projects ×

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Now showing 1 - 3 of 3
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Mechanical Design of a Cubesat Aeroshell for an Earth Demonstration of Single-Stage Drag Modulated Aerocapture

2016-08-01 , Woollard, Bryce A.

The following article documents the conceptual study of a smallsat entry vehicle to be implemented for demonstration of single-stage drag modulated aerocapture at Earth. The specific nature of the contents below focuses on the mechanical design and analysis of the aeroshell and drag device, as well as the mechanisms by which all parts are to be manufactured, assembled and actuated in order to perform the intended orbital maneuver. The results of this study show that accomplishing aerocapture with a cubesat entry vehicle appears to be feasible with a 2U payload and would require approximately 20 kg and 0.1 m3 of secondary payload mass and volume, respectively. First order stagnation point thermal protection sizing suggests that 4.2 cm of PICA would be required globally around the vehicle, although potential exists to optimize this value relative to geometric location. Static stability analysis indicates that the designed vehicle is nose-forward stable for a majority of the atmospheric interface with outstanding questions pertaining to atmospheric egress. Manufacturing costs for a full scale aeroshell would be approximately $15,000 and require roughly 2 months of lead time, dependent on presently available machine shop capabilities.

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Supersonic Vehicle Configuration Transitions to Enable Supersonic Retropropulsion during Mars Entry, Descent, and Landing

2016-02-29 , Blette, David J.

This paper investigates types of supersonic vehicle configuration transition events nec essary to initiation supersonic retropropulsion as part of human-class Mars entry, descent, and landing. This research assumes an entry vehicle with a 105 mT entry mass and an ellipsled aeroshell similar to the NASA EDL Design Reference Architecture 5.0. All entry architectures are assumed all-propulsive. Three transition architectures are considered: a pitch-around maneuver, an aeroshell front-exit, and an aeroshell hinged-exit. Propulsive subsystem thrust requirements are defined for the pitch-around maneuver. For transitions involving solid mass ejections, debris flight envelopes are determined and compared to a descent vehicle trajectory under a modified gravity turn. It is shown that far-field recon tact risks exist for the proposed architectures involving solid mass ejections and recontact mitigation schemes are required.

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Entry Characteristics of a Half-Ogive Aeroshell at Earth

2016-02-05 , Booher, Robert M.

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