Lifting entry vehicle mass reduction through integrated thermostructural/trajectory design
Author:
Affiliation:
1. NASA Langley Research Center, Hampton, Virginia
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/3.8591
Reference13 articles.
1. Technology and Operational Considerations for Low-Heat-Rate Entry Trajectories
2. Impact of Far-Aft Center of Gravity for a Single-Stage-to-Orbit Vehicle
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1. Inviscid/Boundary-Layer Aeroheating Approach for Integrated Vehicle Design;55th AIAA Aerospace Sciences Meeting;2017-01-05
2. Aeroheating Design Issues for Reusable Launch Vehicles -- A Perspective;34th AIAA Fluid Dynamics Conference and Exhibit;2004-06-19
3. Multidisciplinary Design Optimization of the Shape and Trajectory of a Reentry Vehicle.;TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES;2002
4. Optimizing hypersonic sharp body concepts from a thermal protection system perspective;8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference;1998-04-27
5. Optimization of the rocket-powered ascent of hotol;Acta Astronautica;1989-01
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