Aerospace Systems Future Small Spacecraft

Artist's rendering of an early warning Space-Based System Satellite. The satellite is one of five GEO satellites for the space-based infrared system. It will have a high-speed scanning sensor and complementary advanced resolution staring sensor. Launch of the first satellite is expected in 2002 (Courtesy of Lockheed Martin).
Trend in reducing spacecraft mass (courtesy of JPL).
The TRW-built "Lewis" Lightsat is part of NASA’s Small Spacecraft Technology Initiative (SSTI). It offers advanced capabilities and will furnish data for a wide range of users. The spacecraft weight is 385.6 kg and will be launched by LMLV-1 to a 523 km, Sun-synchronous orbit (courtesy of TRW Space and Electronics Group).
Artists’ renderings of the Space Test Experiment Platform (STEP) and the MightySat II spacecraft. The STEP spacecraft is 60 ´ 36 in. (stowed) and weighs 870 lb. Its design is configured to allow the use of two different altitude control schemes required by the on-board experiments. It will be launched on Pegasus XL to an operational orbit of 600 km circular. The MightySat II spacecraft is 20 ´ 24 ´ 30 in. and weighs 275 lb. (including 125 lb. payload). It will carry experimental payloads such as space-debris sensors, advanced structures, and battery technologies, and place them in low-Earth orbit. First flight planned for 1999 (courtesy of TRW Space and Electronics Group, U.S. Air Force Phillips Laboratory, and Spectrum Astro, Inc.).
BITSY - One kg satellite built by AeroAstro for the U.S. Air Force.
Artist’s rendering of Deep Space-1 (DS-1) spacecraft scheduled for launch in July 1998 to fly by Asteroid McAuliffe and Comet Kohoutek-Ikemura. The spacecraft wet launch mass is 480 kg, has a solar electric ion propulsion system, multi-functional structure, miniature integrated camera and spectrometer (courtesy of JPL and Spectrum Astro, Inc.).
Artist’s rendering of Deep Space-2 (DS-2) Mars microprobes to be mounted on Mars 98 Lander cruise ring for single-stage Mars entry, descent and landing. The mass of each penetrator is 1.5 kg, and the penetration depth is 0.5 to 2.0 m (courtesy of JPL).
Artist’s rendering of two optical interferometer systems, each consisting of three spacecraft constellation, for a candidate Deep Space-3 (DS-3) mission. The two collector spacecraft are 100m - 1 km apart (1 mas to 100 mas). The center spacecraft combines the light from the two collectors in order to detect fringes and perform the science measurements (courtesy of JPL).
Artist’s rendition of an Earth observation nanosat (courtesy of The Aerospace Corp.).


For additional information about the Center contact:
Professor Ahmed K. Noor
Director, Center for Advanced Engineering Environments
aknoor@odu.edu

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