Examples of both “top-down” and “bottom-up” methods for predicting launch and ascent loads, as well as launch vehicle component sizing, are presented. These techniques are most applicable during the conceptual and preliminary design stages, early in the project life-cycle where a lack of fidelity of detail is more acceptable. These techniques are applied to estimate the mass of components from the Saturn V and Space Shuttle launch vehicles, and results are compared to actual values from the flown vehicles
Loads and Sizing for Launch Vehicle Conceptual and Preliminary Design
2024
32 pages
Report
Keine Angabe
Englisch
LAUNCH VEHICLE ATMOSPHERIC FLIGHT LOADS - Launch Vehicle Atmospheric Flight Loads
Online Contents | 2000
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