DESIGN, ANALYSIS, AND TESTING OF AN AEROBRAKE TEST MODEL

A one-tenth-scale test model of a spherical sandwich aerobrake propose d for a lunar transfer vehicle was developed. The objective of this pa per is to demonstrate the structural integrity of this aerobrake test model. Membrane stress analysis and the idea of equal stress/strength ratio of the skin material were used in the design. The test model had an outer radius of 4.45 ft (1.36 m), a base diameter of 5 ft (1.5 m), and a total wall thickness of 0.9 in (23 mm). The sandwich shell wall was made out of glass/polyester resin skin and polyvinyl foam core. A n air-pressure test was conducted. The measured displacements and stra ins agreed well with the finite element analysis results. The aerobrak e model survived 160% of the design pressure with no structural failur e.