Developed a one-tenth scale test model of a spherical sandwich aerobrake proposed for a lunar transfer vehicle. Membrane stress analysis and the idea of equal stress/strength ratio of the skin material were used in the design. The test model had outer radius 4.45 feet (1.36 m), base diameter 5 feet (1.5 m), and the total wall thickness 0.9 inches (23 mm). The model was also a sandwich shell, with skin made of glass/polyester resin and the core made of polyvinyl foam. The model was supported on a ring beam at 75 % span and air pressure tested. The vertical displacements, and hoop and meridional strains were measured as function of the pressure. The aerobrake model survived 160 % of the design pressure with no structural failure. Measured displacements and strains were compared with an axisymmetric finite-element analysis. The displacement data agreed very well with the analysis. Because the strains are functions of local values of radius, thickness, and elastic modulus, the agreement between the test and analysis data was not superior.
Design, fabrication, testing, and analysis of an LTV aerobrake test model
Entwurf, Herstellung, Prüfung und Analyse eines Luftbremsen-Testmodells für ein Mondfahrzeug
1994
10 Seiten, 14 Bilder, 14 Quellen
Aufsatz (Konferenz)
Englisch
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