Session
Technical Session VI: Subsystems I
Abstract
The principle objective of the Clementine spacecraft was to test the most advanced lightweight imaging sensors and component technologies for the next generation of Department of Defense spacecraft. As a secondary mission, Clementine was to obtain scientific data from a two month lunar mapping mission and a fly-by of the near-Earth asteroid 1620 Geographos. To meet these objectives the Attitude Determination and Control System (ADCS) was responsible for maintaining attitude knowledge and control in Earth and Lunar orbit, during the fly-by of Geographos, and during all the orbit transfers. This paper will present a description of the ADCS architecture, identify hardware selected, and show how the hardware and software was tested. ADCS hardware consisted of all new lightweight spacecraft components including two three-axis attitude determination Star Tracker Cameras, an Interferometric Fiber Optic Gyro Inertial Measurement Unit, a Ring Laser Gyro Inertial Measurement Unit, and a set of four Reaction Wheels, with a total system weight of less than 13 kg.
The Clementine Attitude Determination and Control System
The principle objective of the Clementine spacecraft was to test the most advanced lightweight imaging sensors and component technologies for the next generation of Department of Defense spacecraft. As a secondary mission, Clementine was to obtain scientific data from a two month lunar mapping mission and a fly-by of the near-Earth asteroid 1620 Geographos. To meet these objectives the Attitude Determination and Control System (ADCS) was responsible for maintaining attitude knowledge and control in Earth and Lunar orbit, during the fly-by of Geographos, and during all the orbit transfers. This paper will present a description of the ADCS architecture, identify hardware selected, and show how the hardware and software was tested. ADCS hardware consisted of all new lightweight spacecraft components including two three-axis attitude determination Star Tracker Cameras, an Interferometric Fiber Optic Gyro Inertial Measurement Unit, a Ring Laser Gyro Inertial Measurement Unit, and a set of four Reaction Wheels, with a total system weight of less than 13 kg.
