Attitude Determination and Control

The scientific mission of this satellite is to raise orbit using solar sails. For maximum orbit rise in minimum time, the solar sail has to be oriented in particular configurations depending on the position of satellite in orbit and position of Sun with respect to satellite. In the sunlit region the satellite should rotate from 0 to 90 degrees as it moves from north pole to south pole. In the eclipse region, satellite will be oriented such that sail will always tangential to orbit so that the air drag can be minimized.

To achieve these orientations, the passive control used in Swayam will be futile. Hence an efficient active control along with accurate attitude determination/estimation techniques will govern the success rate of the mission. The pointing accuracy of 10 degrees is required for the mission which is fulfilled by the actuators, magnetorquers and a reaction wheel, and sensors, sun sensors, magnetometers and gyroscopes.

Team Lead

Dnyanada Joshi (Final Year, Information Technology )

Email-ID: acs.csat@coep.ac.in

Team Members

Tanmay Khare (Final Year,  Mechanical Engineering)

Himabindu Boddupalli (Final Year, Computer Engineering)

Aditya Barve (Final Year, Computer Engineering)

Mihir Paranjape (Third Year, Mechanical Engineering)

Varad Ghodake (Third Year, Computer Engineering)

Aditya Neralkar (Third Year, Information Technology)

Asawari Joshi (Second Year, Instrumentation and Control)

Rahul Patil (Second Year, Mechanical Engineering)