The FALCON I Launch Vehicle
- Paper number
IAC-06-B5.5.01
- Author
Mr. Hans Koenigsmann, Space Exploration Technologies, United States
- Coauthor
Mrs. Gwynne Shotwell, Space Exploration Technologies, United States
- Year
2006
- Abstract
Falcon I is the first in a family of launch vehicles designed by Space Exploration Technologies to facilitate low cost access to space. Falcon I is a mostly reusable, two stage, liquid oxygen and kerosene powered launch vehicle. The vehicle is designed above all for high reliability, followed by low cost and a benign flight environment for the payload. A standard Falcon I can carry over 700 lbs to sun-synchronous orbit and 1200 lbs due east to 100 NM. The costs, which nominally assume no advantage for recovery, are $5.9M for a standard Falcon I. Launch sites include facilities on the Kwajalein atoll in the Marshall Islands and SLC 3W at Vandenberg Air Force Base. This paper will describe the path to first flight with a focus on the effort to reduce the launch campaign duration, including the countdown. Results from the maiden flight will also be addressed.
- Abstract document
- Manuscript document
IAC-06-B5.5.01.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.