SRMSAT - 2
SRMSAT - 2 is the second mission of Team SRMSAT. SRMSAT - 2 is a progressive conceptual student small satellite mission and a step forward in deep space exploration, pushing horizons of robust small satellites to regimes beyond earth. The mission is directed towards the design of a small orbiter spacecraft to orbit and study moon in a Low Lunar Orbit (LLO). The primary objective of the SRMSAT - 2 is to attain a stable lunar orbit achieved by low energy transfer exploiting Weak Stability Boundary theory. As a part of the science mission, a Microwave Radiometer is selected as the primary payload to study the lunar regolith and a Radiation Dosimeter is chosen as the secondary payload to characterize the radiation environment along the trajectory. A Narrow Angle Camera is chosen as outreach payload. Other options like Hyperspectral/Multispectral Imager and Infrared Spectrometer were also considered, but the final decision regarding the selection of payload is subject to outcomes of the design review.
The mission assumes launch vehicle support till the GTO and starts going through a series of phasing orbits to reach the WSB region to move from the Sun-Earth Manifold to the Moon-Earth Manifold, which are traced using Poincare maps with an approach from initial conditions. The apogee of the final phasing orbit is close to 1.5 Million Kilometers, and that point has some of the most critical and precise maneuvers to be executed.
SRMSAT – 2 is a cube-shaped spacecraft with the following key features
|Dimensions||500mm × 502mm × 600mm (cube)|
|Payload||Microwave Radiometer, Radiation Dosimeter, Narrow Angle Camera, possibly Hyperspectral Imager (Final decision pending)|
|Propulsion||Bipropellant Primary Propulsion System, Monopropellant Reaction Control System|
|Tracking||S-Band two-way Doppler ranging|
|Attitude control||RCS and Reaction Wheels (3-axis stabilized)|
|Structure||Aluminium 6061-T6 alloy with honeycomb sandwich panels|
|Antenna||20dBi Parabolic Reflector, S-band Omnidirectional|
|Power||One body mounted and two deployed solar panels generating 142W at End of Life; 234 Wh battery.|
|Power transmitted||7 dBW typical, 15 dBW in special cases|
|Uplink||2110 to 2120 MHz1, 100 kbps|
|Downlink||2200 to 2290 MHz1, 4 kbps|
The objectives of the project are:
Indian Space Research Organization’s launch support along with
IDSN support for Telemetry, Tracking and Command is aspired and elementary
to the mission. For the mission operations, support with respect to
Space Link Extension (SLE) is established for interfacing Flight Dynamics facility,
Data processing center and Mission Operation Centre established at SRM University
with ISTRAC and IDSN stations is planned and proposal has been sent to ISRO.
A primary data center (SRM Lunar Science Data Center) will be established to collaborate with DSN and University tracking station with capabilities to support handling of downlinked science data and, maintaining and regulating data archives will be established. It will be responsible for interfacing with the scientific community and students of SRM University in providing acquired science data.