Random positioning machine (RPM) as a ground based microgravity simulating platform was designed, fabricated and validated. Experiments using biological samples proved that the achieved microgravity levels (10-3g) significantly influenced many biological parameters and the results were also compared with data from spaceflight studies. The developed RPM can be effectively utilized for the ground based optimization of spaceflight experiments. (currently under patent filing: KG Sreejalekshmi and Srujana Juratagi)

InspireSat-1 was successfully launched on board the PSLV C52 mission on February 14, 2022 and is being successfully operated by the students of IIST from the IIST ground station with support from the INSPIRE partners including LASP, USA and NCU, Taiwan, and NTU, Singapore. The spacecraft had an expected mission life of 6 months, however it has continued to work for more than one year till date [07-03-2023] collecting valuable scientific data.

Pslv-In-orbitaL Obc and Thermals (PILOT), is a payload designed for the fourth (and final) stage of PSLV with the aim to achieve thermal model validation and flight qualifications for the in-house developed On-board computer, which is expected to fly in multiple upcoming missions developed at SSPACE. The payload carries a number of temperature sensors which are used to collect valuable thermal data for thermal model validation of various subsystems in LEO. The PILOT payload has a volume of ~1U, and a mass of less than 1kg. The bus is designed to work on less than 0.5W power.

With the goal of in-situ radiation dosimetry, SSPACE (Small-spacecraft Systems and PAyload CEntre), IIST Thiruvananthapuram, India, is developing a constellation of 3U CubeSats with AHAN as the first in this series expected to be launched by 3rd quarter of 2023. The CubeSat is about 2kg in mass with a nominal power consumption of about 3 Watts. The CubeSat houses a Geiger-Muller Counter for radiation dosimetry, which serves as the payload. The satellite is developed with all in-house subsystems which will also serve the purpose of flight validation of the subsystems.

The invention is a closed loop MEMS Accelerometer implemented using suspended gate field effect transistors (SGFET) and the method of fabricating this sensor. This closed loop accelerometer (Closed loop in plane movable SGFET-CLIP-SGFET) has an in-plane movable suspended gate FETs in the differential amplifier configuration. In the closed loop operation, the CMOS-MEMS SGFET differential amplifier’s output voltage is used, through a closed loop controller and a high voltage charge pump to drive an actuator which brings the gate back to its resting position.