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This study analyzes the design of a two-stage reusable satellite launch vehicle. This launcher was designed to orbit payloads of up to 500 kg to low orbits (LEO). Two RISCRAM™ jet engines (Rocket Ignited Supersonic Combustion Ramjet) power the first stage that is fully reusable. They aspirate atmospheric air and allows speeds of up to Mach 6, below 30 km, and Mach 15 above 40 km of altitude. The second stage is powered by a solid rocket motor that carries the payload at the orbital speed of Mach 24. In this work are presented details of the concept of the vehicle and an economic feasibility analysis of system operation. Launch cost estimative are made and compared to the values of the current satellite launchers that are not reusable. The conclusion of the article is that the proposed system would be able to reduce by an order of magnitude the cost of placing the kilogram of payload in low orbit.

This paper relates to the wind tunnel balance design that aims to meet the need for reliable but more affordable equipment that could accurately perform Aerodynamic measurements and act on three axes, being a Multitasking device, adaptable for prototypes of aircrafts, automobiles, buildings, sports products design, etc., through digital control that will measure the drag, lift and the aerodynamic pitch moment. The main task is stimulating creativity, to solve real problems and reduce technology dependence. The composite tubes used in the fixation of the "Sting-Compound" were chosen to avoid inaccurate measurements and have high flexural strength, even with a small cross section. That's feature is justified because the terminal velocity of wind tunnel is 50 m/s (97 knots), enabling to search many different model sizes and subsonic Reynolds speed regime.