Preliminary analysis of hybrid rockets for launching nanosats into LEO

Abstract

This work determines the preliminary mass distribution of hybrid rockets using 98% H2O2 and solid paraffin mixed with aluminum as propellants. An iterative process is used tocalculate the rocket performance characteristics and to determine the inert mass fractionfrom given initial conditions. It is considered a mission to place a 20 kg payload into a 300 km circular equatorial orbit by air launched and ground launched hybrid rockets usingthree stages. The results indicate total initial masses of about 7800 kg for a groundlaunched hybrid rocket and 4700 kg for an air launched hybrid rocket

Preliminary Study of Launch and Orbit of a CubeSat Using a Modified VSB-30 Launcher Vehicle

“…Values over the maximum can be reached using top-level materials and technologies during the development of the motors. In addition, achieving the third liquid stage propellant ratio is feasible in accordance with the data presented in Costa and Vieira (2010), retrieved from Isakowitz et al (1999), which presents motors such as the Chinese YF-40 (ζ = 0.93), the Russian 11D49 (ζ = 0.93), the American RS27A (ζ = 0.93) and the Soviet RD-171 (ζ = 0.92).…”

An optimized hybrid rocket motor for the SARA platform reentry system

“…Hence, we considered a 20 addition of the optimized engine candidate mass arguing that the mass of the subsystems (catalytic bead for and other components for the ignition system, plumbing, valves etc) is proportional to the mass of the system. This gure is twice as much of that proposed by Costa and Vieira (2010) on account of the lack of reliable data of the components of the propulsive system. All the tanks and combustion chamber would be made of aluminum reinforced with carbon ber.…”