Experimental/Small satellite

Jugnu:

Launch Date-12.10.2011

The Nano satellite Jugnu weighing 3 kg is designed and developed by Indian Institute of Technology, Kanpur under the guidance of ISRO. The satellite is intended:

·         To prove the indigenously developed camera system for imaging the Earth in the near infrared region and test image processing algorithms.

·         Evaluate GPS receiver for its use in satellite navigation.

·         Test indigenously developed MEMS based Inertial Measurement Unit (IMU) in space.

               

SRMSat

Launch Date-12.10.2011

The Nano satellite SRMSat weighing 10.9 kg is developed by the students and faculty of SRM University attempts to address the problem of Global warming and pollution levels in the atmosphere by monitoring Carbon dioxide (CO2) and water vapour (H2O). The satellite uses a grating Spectrometer, which will observe absorption spectrum over a range of 900nm -1700nm infrared range.

YOUTHSAT YOUTHSAT is a joint Indo-Russian stellar and atmospheric satellite mission with the participation of students from Universities at graduate, post graduate and research scholar level. With a lift-off mass of 92 kg, Youthsat is a mini satellite and the second in the Indian Mini Satellite (IMS) series. Youthsat mission intends to investigate the relationship between solar variability and thermosphere-Ionosphere changes. The satellite carries three payloads, of which two are Indian and one Russian. Together, they form a unique and comprehensive package of experiments for the investigation of the composition, energetics and dynamics of earth's upper atmosphere. The Indian payloads are: RaBIT (Radio Beacon for Ionospheric Tomography)- For mapping Total Electron Content (TEC) of the Ionosphere. LiVHySI (Limb Viewing Hyper Spectral Imager) - To perform airglow measurements of the Earth's upper atmosphere (80- 600 km) in 450-950 nm. The Russian payload SOLRAD - To study temporal and spectral parameters of solar flare X and gamma ray fluxes as well as charge particles in the earth polar cap regions.

Lift-off Mass 92 kg Orbit Period 101.35 min Dimension 1020 (Pitch) x 604 (Roll) x 1340 (Yaw) mm3 Attitude and Orbit Control 3-axis body stabilised using Sun and Star Sensors, Miniature Magnetometer, Miniature Gyros, Micro Reaction Wheels and Magnetic Torquers Power Solar Array generating 230 W, one 10.5 AH Li-ion battery Mechanisms Paraffin Actuator based Solar Panel Hold Down and Release Mechanism Launch date April 20, 2011 Launch site SHAR Centre Sriharikota India Launch vehicle PSLV- C16 Orbit Circular Polar Sun Synchronous Orbit altitude at injection 822 km + 20 km (3 Sigma) Orbit Inclination 98.731 º + 0.2 º Mission life 2 years

STUDSAT Launch Date-12-07-2010 Student Satellite (STUDSAT) is the first pico-satellite developed in the country by a consortium of seven engineering colleges from Karnataka and Andhra Pradesh. STUDSAT weighing less than 1 kg, has the primary objective of promoting space technology in educational institutions and encourage research and development in miniaturized satellites, establishing a communication link between the satellite and ground station, capturing the image of earth with a resolution of 90 meters and transmitting the payload and telemetry data to the earth station. Mission Experimental / Small Satellite Weight Less than 1 kg Altitude 630 km Orbit Polar Sun Synchronous

ANUSAT Launch Date-20-04-2009 ANUSAT (Anna University Satellite) is the first satellite built by an Indian University under the over all guidance of ISRO and will demonstrate the technologies related to message store and forward operations.

Altitude 550 km Inclination 41 deg Orbit Period 90 minutes Mass 40 kg

SRE-1

Launch Date-10-01-2007

Space Capsule Recovery Experiment (SRE – 1) is a 550 kg capsule intended to demonstrate the technology of an orbiting platform for performing experiments in micro gravity conditions. After completion of the experiments, the capsule was de-orbited and recovered. SRE – 1 mission provided a valuable experience in fields like navigation, guidance and control during the re-entry phase, hypersonic aero thermodynamic, development of reusable thermal protection system (TPS), recovery through deceleration and flotation, besides acquisition of basic technology for reusable launch vehicles.

SRE – 1 carries two experiments, an Isothermal Heating Furnace (IHF) and a Bio-mimeic experiment. SRE was launched into a 635 km polar SSO in January 2007 as a co-passenger with CARTOSAT -2 and stayed in orbit for 10 days during which its payloads performed the operations they are intended to. The SRE capsule was de-boosted and recovered successfully back on earth on 22nd January 2007. 

RS-1

First satellite successfully launched by the indigenous launch vehicle SLV

Mission Experimental Weight 35 kg Onboard power 16 Watts Communication VHF band Stabilization Spin stabilized Payload Launch vehicle monitoring instruments Launch date July 18,1980 Launch site SHAR Centre, Sriharikota, India Launch vehicle SLV-3 Orbit 305 x 919 km Inclination 44.7 deg. Mission life 1.2 years Orbital life 20 months

RTP

Mission Experimental Weight 35 kg onboard power 3 Watts Communication VHF band Stabilization Spin stabilized (spin axis controlled) Payload Launch vehicle monitoring instruments Launch date August 10,1979 Launch site SHAR Centre, Sriharikota, India Launch vehicle SLV-3 Orbit Not achieved

APPLE

APPLE was used for nearly two years to carry out extensive experiments on time, frequency and code division multiple access systems, radio networking computer inter connect, random access and pockets witching experiments. Mission Experimental geostationary communication Weight 670 kg Onboard Power 210 Watts Communication VHF and C-band Stabilization Three axis stabilized (biased momentum) with Momentum Wheels, Torquers &  Hydrazine based Reaction control system Payload C - band transponders (Two) Launch Date June19,1981 Launch Site Kourou (CSG), French Guyana Launch Vehicle Ariane -1(V-3) Orbit Geosynchronous (102 deg. E  longitude, over Indonesia) Inclination Near zero Mission life Two years

ARYABHATTA

The First Indigenously built Indian Satellites Mission Scientific/ Experimental Weight 360 kg On board power 46 Watts Communication VHF band Stabilization Spinstabilize Payload X-ray Astronomy Aeronomy & Solar Physics Launch date April 19,1975 Launch site Volgograd Launch Station (presently in Russia) Launch vehicle C-1 Intercosmos Orbit 563 x 619 km Inclination 50.7 deg Mission life 6 months(nominal), Spacecraft mainframe active till March,1981 Orbital Life Nearly seventeen years (Re-entered on February 10,1992)