Space Capsule Recovery Experiment

Space Capsule Recovery Experiment

Infobox Spacecraft
Name = Space Capsule Recovery Experiment

Caption = The SRE-1 kept for public display at Thiruvananthapuram on April 29, 2007
Organization = ISRO
Major_Contractors =
Mission_Type = Orbiter
Satellite_Of = Earth
Orbital_Insertion_Date = January 10, 2007
Launch = January 10, 2007
Launch_Vehicle = PSLV C7
Decay =
Mission_Duration = 12 Days
Webpage = [ Space Capsule Recovery Experiment]
Mass = 550 kg
Power =
Orbital_elements =
Semimajor_Axis =
Eccentricity =
Inclination =
Orbital_Period =
Apoapsis =
Periapsis =
Orbits =
The Space Capsule Recovery Experiment (SCRE or more commonly SRE or SRE-1) is an Indian experimental spacecraft which was launched at 03:53 GMT on January 10, 2007 from Sriharikota by the Indian Space Research Organization (ISRO). The launch was conducted using the PSLV C7 rocket, along with three other satellites. It remained in orbit for 12 days before re-entering the Earth's atmosphere and splashing down into the Bay of Bengal at 04:16 GMT on January 22. [ [ PSLV to put recoverable satellite into orbit] , "The Hindu" December 22, 2006] [ [ The Hindu: PSLV-C7 launch a success] January 11, 2007] [ [ ISRO Ready For Launch Of Multi-Mission PSLV] January 05, 2007]


The SRE 1 was designed to demonstrate the capability to recover an orbiting space capsule, and the technology of an orbiting platform for performing experiments in microgravity conditions. It was also intended to test reusable Thermal Protection System, navigation, guidance and control, hypersonic aero-thermodynamics, management of communication blackout, deceleration and flotation system and recovery operations. [ [ China View: India's first space capsule returns to earth] January 22, 2007] [ [ ISRO Press Release] January 22, 2007] [ [ 46-minute splash into elite space club] The Telegraph January 22, 2007]


SRE-1 is a 555 kg capsule. It comprises aero-thermo structure, internal structure, Mission Management Unit, Altitude sensors and Inertial measurement unit, S-band transponder with unique belt array antenna embedded to ATS, power and electronics packages to support deceleration and flotation system. It also houses two microgravity payloads. It has a sphere-cone-flare configuration with a spherical nose of about 0.5 m radius, base diameter of 2 m and 1.6 m height. The parachute, pyro devices, avionics packages of triggering unit and sequencer, telemetry and tracking system and sensors for measurement of system performance parameters are placed inside the SRE capsule. Parachutes for SRE capsule were provided by ADRDE. [ [ "Aerial Delivery Research and Development Establishment, Agra, provided the parachutes"] ]

To withstand the heat of re-entry, the cone-shaped SRE has a heat shield composed of silica tiles over much of the surface, and an ablative nose cap of carbon-phenolic composite. ISRO is also working on technology to manufacture carbon-carbon composite heat shields, which, along with the silica tiles tested with the SRE, could find use in future reusable spacecraft such as ISRO's planned Reusable Launch Vehicle.


SRE 1 was traveling around the earth in a circular polar orbit at an altitude of 637 kilometers. In preparation for its reentry, SRE 1 was put into an elliptical orbit with a perigee of 485 kilometers and an apogee of 639 kilometers by issuing commands from the spacecraft control centre of ISTRAC at Bangalore on January 19, 2007. The critical de-boost operations were executed from SCC, Bangalore supported by a network of ground stations at Bangalore, Lucknow, Mauritius, Sriharikota, Biak in Indonesia, Saskatoon in Canada, Svalbard in Norway besides shipborne and airborne terminals.

On January 22, 2007, the re-orientation of SRE 1 capsule for de-boost operations commenced at 08:42 am IST. The de-boost started at 09:00 am with the firing of on-board rocket motors and the operations were completed at 09:10 am. At 09:17 am, SRE 1 capsule was reoriented for its re-entry into the dense atmosphere. The capsule made its re-entry at 09:37 am at an altitude of 100 kilometers with a velocity of 8 km/s (ca. 29,000 km/h). During its reentry, the capsule was protected from the intense heat by carbon phenolic ablative material and silica tiles on its outer surface.

By the time SRE 1 descended to an altitude of 5 km, aerodynamic braking had considerably reduced its velocity to 101 m/s (364 km/h). Pilot and drogue parachute deployments helped in further reducing its velocity to 47 m/s (169 km/h).

plashdown and recovery

The main parachute was deployed at about 2 km altitude and finally, SRE 1 splashed down in the Bay of Bengal with a velocity of 12 m/s (43 km/h) at 09:46 am IST (04:16 am GMT). The floatation system, which was immediately triggered, kept the capsule floating. Recovery operations were supported and carried out by the Indian Coast Guard and Indian Navy using ships, aircraft and helicopters.


During its stay in orbit, the following two experiments on board SRE 1 were successfully conducted under microgravity conditions.
* One of the experiments was related to the study of metal melting and crystallization under microgravity conditions. This experiment, jointly designed by the Indian Institute of Science, Bangalore and Vikram Sarabhai Space Centre, Thiruvananthapuram, was performed in an isothermal heating furnace.
* The second experiment, jointly designed by National Metallurgical Laboratory, Jamshedpur and ISRO Satellite Centre Bangalore, was intended to study the synthesis of nano-crystals under microgravity conditions.This was an experiment in designing biomaterials that better replicate natural biological products. The experimental results will be analyzed in due course by the principal scientific investigators of the two experiments.

ee also


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