Space Research Institute, Malek Ashtar University of Technology
Aerospace Engineering, Malek-Ashtar University of Technology
Electrical Engineering, Islamic Azad University DamavandBranch
The purpose of this paper is to perform the feasibility and performance evaluation of the High-altitude launch technique using high altitude atmospheric Properties to near earth orbits. The current propulsion transportation system from Earth to space has been deemed by many to be expensive, unreliable, and an unnecessarily dangerous means of travel to space. It is suggested in this paper to analyze a different type of launch from a high altitude to the LEO orbit. Two altitudes serve as the initial launch conditions, 20 to 40 km that is evaluated according to thrust profile variations with respect to vehicle’s weight and under launch different angles. the trajectory equations used in the simulation code also take into consideration Spectral and Diffusive reflection model for near space conditions. The methodology is based on the previously mentioned model that calculates the forces affecting a flat plate as it gains altitude. To summarize the results and conclude, when comparing all cases, a higher altitude with a high T/W ratio and a low angle of attack is more desirable.