A COMPARATIVE INVESTIGATION OF A GROUND AND AIR LAUNCH OF LEO-BOUND SMALL SATELLITES

摘要

Small satellites have shown that it is possible to execute missions very effectively and rapidly at low cost. Although, there is currently an oversupply of launch capacity in the world, there is no dedicated launch vehicle for the nano/micro class satellites except some Russian vehicles and piggy-back secondary payload launches. This study is based on the work conducted by a team of 27 Mechanical and Aerospace Engineering students from Carleton University in Ottawa, Canada. The Air launched Earth observing Ground Information System (AEGIS) preliminary design indicated that a three stage solid motor launcher configuration air launched from a CF-18 can insert a 13 kg payload into orbit. Building on the AEGIS teamwork, this paper applies alternate analysis methods to the mission's launch segment. This study comparatively investigates a ground and air launch for low-Earth orbit-bound small satellites. The performance investigation revealed that an air launch is favourable up to nearly 400 km in altitude at a given inclination. Logistically, an air launch benefits from a strategic launch location but is characterized with added complexity. Ultimately, the launcher could be designed for both air and ground launch with a modular and flexible design approach but the ground version could be considered first.