A Comprehensive Investigation of an Air versus Ground-Launch of LEO-Bound Small Satellites

Paper number

IAC-05-E2.2.05

Author

Mr. Michael Labib, Carleton University, Canada

Coauthor

Dr. Tarik Kaya, Carleton University, Canada

Year

2005

Abstract

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Small satellites have shown that it is possible to execute missions very effectively and rapidly at low cost.  Applications such as forest fire detection, urban planning, land use, crop monitoring, precision farming, environmental studies and geological mapping are only a few of the important science applications which can be performed by small satellites.  Although, there is currently an oversupply of launch capacity in the world, there is no dedicated launch vehicle for the small satellites except some Russian converted missiles and piggy-back secondary payload launches.  The launch cost is consistently a problem for the small satellite business and there is a strong demand for low cost launchers.  The need for small launchers is also stimulated by an unmet demand for low cost launchers by universities and small aerospace companies.  Many countries including the members of the European Space Agency (ESA), US, Israel, Russia, and Brazil are all developing low cost small launch vehicles, indicating a clear interest in this area.  
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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) team project developed a low-Earth orbit (LEO) system to capture thermal images of Canada to benefit the fields of agriculture, environmental studies and geology and determined the feasibility of developing a rapidly deployable Canadian air launch system using a CF-18 as the carrier aircraft.  The preliminary design indicated that the 40 kg cubic configuration satellite and the launcher cannot be integrated as a result of the dimensional and mass constraints imposed by the CF-18.  However, the team demonstrated that a three stage solid motor launch vehicle configuration would be capable of inserting a 13 kg payload into the target orbit.
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Building on the AEGIS teamwork, this paper applies alternate analysis methods to the launch segment of the mission.  This study comprehensively investigates an air versus ground-launch for LEO-bound small satellites.  Specifically, both quantitative and qualitative comparisons are examined.  The quantitative segment investigates critical comparison criteria such as trajectory, payload capability and flight time.  These considerations are largely substantiated by the Aerospace Trajectory Optimization Software developed at the Institute of Flight Mechanics and Control of the University of Stuttgart and partly financed by ESA in addition to in-house software.  The qualitative component details a wide range of aspects from the vehicle integration to launch of the two platforms.  These include vehicle components implications, aircraft selection considerations for the air-launch case, launch infrastructure and logistics as well as the associated reliability, complexity and cost.  Ultimately, this study identifies favourable air and ground-launch circumstances for given missions with consideration for a multitude of technical and logistical factors.

Abstract document

IAC-05-E2.2.05.pdf

Manuscript document

IAC-05-E2.2.05.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.