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India's Polar Satellite Launch Vehicle, PSLV-C16 will launch RESOURCESAT-2, YOUTHSAT and X-SAT satellites. RESOURCESAT-2 built by ISRO - the primary satellite is an advanced remote sensing satellite weighing 1206 kg for facilitating the study and management of natural resources. YOUTHSAT weighing 92 kg is a joint Indo-Russian satellite for stellar and atmospheric studies. X-SAT weighing 106 kg is a microsatellite for imaging applications built by Nanyang Technological University (NTU), Singapore.
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Launch date:|{colsp=3}
Launch time:| 04:42 UTC | 12:42 a.m. EDT | 10:12 a.m. IST
Launch site:|{colsp=3}
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There's calendar event created for this launch.
Payload:
Launch Vehicle:
Launch Preparations:
Links:
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Wednesday, April 20, 2011
Launch time:| 04:42 UTC | 12:42 a.m. EDT | 10:12 a.m. IST
Launch site:|{colsp=3}
Satish Dhawan Space Center, Sriharikota, India
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[highlight]L[eventtimer]2011-4-20 4:42;%c%%ddd%/%hh%:%mm%:%ss%[/eventtimer][/highlight]
There's calendar event created for this launch.
Payload:
RESOURCESAT-2:
YOUTHSAT:
XSAT:
Parameter/Satellite|
Orbit:|
Altitude at injection:|
Inclination:|
Period:|
Orbits/Day:|
Local Time of Equator crossing:|
Repetivity:|
Lift-off Mass:|
Dimensions:| |
Attitude and Orbit Control:|
Power:|
Lifespan:|
RESOURCESAT-2 is the eighteenth Remote Sensing satellite built by ISRO. RESOURCESAT-2 is a follow on mission to RESOURCESAT-I, launched in 2003. RESOURCESAT-2 is intended to continue the remote sensing data services to global users provided by RESOURCESAT-I that has far outlived its designed mission life. Also, it provides data with enhanced multispectral and spatial coverage as well.
RESOURCESAT-2 carries three cameras which are similar to those of RESOURCESAT-I. They are: a high resolution Linear Imaging Self Scanner (LISS-4) operating in three spectral bands in the Visible and Near Infrared Region (VNIR) with 5.8 m spatial resolution and steerable up to ± 26 deg across track to achieve a five day revisit capability; a medium resolution LISS-3 operating in three-spectral bands in VNIR and one in Short Wave Infrared (SWIR) band with 23.5 metre spatial resolution; and a coarse resolution Advanced Wide Field Sensor (AWiFS) operating in three spectral bands in VNIR and one band in SWIR with 56 metre spatial resolution.
Important changes in RESOURCESAT-2 compared to RESOURCESAT-1 are: Enhancement of LISS-4 multispectral swath from 23 km to 70 km and improved Radiometric accuracy from 7 bits to 10 bits for LISS-3 and LISS-4 and 10 bits to 12 bits for AWIFS. Besides, suitable changes, including miniaturisation in payload electronics, have been made in RESOURCESAT-2.
RESOURCESAT-2 also carries an additional payload known as AIS (Automatic Identification System) from COMDEV, Canada as an experimental payload for ship surveillance in VHF band to derive position, speed and other information about ships.
RESOURCESAT-2 carries two Solid State Recorders with a capacity of 200 Giga Bytes each to store the images taken by its cameras which can be read out later to ground stations.
RESOURCESAT-2 carries three cameras which are similar to those of RESOURCESAT-I. They are: a high resolution Linear Imaging Self Scanner (LISS-4) operating in three spectral bands in the Visible and Near Infrared Region (VNIR) with 5.8 m spatial resolution and steerable up to ± 26 deg across track to achieve a five day revisit capability; a medium resolution LISS-3 operating in three-spectral bands in VNIR and one in Short Wave Infrared (SWIR) band with 23.5 metre spatial resolution; and a coarse resolution Advanced Wide Field Sensor (AWiFS) operating in three spectral bands in VNIR and one band in SWIR with 56 metre spatial resolution.
Important changes in RESOURCESAT-2 compared to RESOURCESAT-1 are: Enhancement of LISS-4 multispectral swath from 23 km to 70 km and improved Radiometric accuracy from 7 bits to 10 bits for LISS-3 and LISS-4 and 10 bits to 12 bits for AWIFS. Besides, suitable changes, including miniaturisation in payload electronics, have been made in RESOURCESAT-2.
RESOURCESAT-2 also carries an additional payload known as AIS (Automatic Identification System) from COMDEV, Canada as an experimental payload for ship surveillance in VHF band to derive position, speed and other information about ships.
RESOURCESAT-2 carries two Solid State Recorders with a capacity of 200 Giga Bytes each to store the images taken by its cameras which can be read out later to ground stations.
YOUTHSAT:
A joint Indo-Russian satellite for stellar and atmospheric studies with the participation of students from Universities at graduate and post graduate level. With a lift-off mass of 92 kg, Youthsat intends to investigate the relationship between solar variability and thermosphere-ionosphere changes.
The micro satellite bus is planned and designed to carry different kinds of payloads like earth imaging, atmospheric applications, weather monitoring, stellar observations, scientific experiments etc. It will carry 3 payloads, one designed by Russian students and two by Indian students.
Those payloads include SolRad, Solar Radiation, is the name of equipment being developed by Moscow state university. The experimental equipment SolRad is intended for registration of hard X-ray radiation within the energy ranges of 10-100 keV, measurements of gamma- radiation within the energy ranges 0.02-5.0 MeV and charged particles: electrons with energy of 0.3-3.0 MeV and protons with energy of 3-100 MeV.
The payloads provided by ISRO are RaBIT (Radio beacon for Ionospheric Tomography) which will be meant for two-dimensional mapping of ionospheric structures- both top and bottom side along the satellite path. And, Limb Viewing Hyper Spectral Imager (Visible) for the altitude profile of neutral and ionized species of the upper atmosphere. Not much information is available on the Indian institutes workingn on these payloads.
The micro satellite bus is planned and designed to carry different kinds of payloads like earth imaging, atmospheric applications, weather monitoring, stellar observations, scientific experiments etc. It will carry 3 payloads, one designed by Russian students and two by Indian students.
Those payloads include SolRad, Solar Radiation, is the name of equipment being developed by Moscow state university. The experimental equipment SolRad is intended for registration of hard X-ray radiation within the energy ranges of 10-100 keV, measurements of gamma- radiation within the energy ranges 0.02-5.0 MeV and charged particles: electrons with energy of 0.3-3.0 MeV and protons with energy of 3-100 MeV.
The payloads provided by ISRO are RaBIT (Radio beacon for Ionospheric Tomography) which will be meant for two-dimensional mapping of ionospheric structures- both top and bottom side along the satellite path. And, Limb Viewing Hyper Spectral Imager (Visible) for the altitude profile of neutral and ionized species of the upper atmosphere. Not much information is available on the Indian institutes workingn on these payloads.
XSAT:
The third payload of PSLV-C16 is Singapore's first satellite. Weighting 106 kg at lift-off, X-SAT is a Mini Satellite with a multispectral camera IRIS as its primary payload.
This is a developmental project undertaken by CREST (Centre For Research in Satellite Technologies) with partners such as CRISP (Centre for Remote Imaging, Sensing and Processing, NUS), and overseas collaborators.
X-SAT mission mainly intends to demonstrate technomogies related to satellite based remote sensing and onboard image processing.
This is a developmental project undertaken by CREST (Centre For Research in Satellite Technologies) with partners such as CRISP (Centre for Remote Imaging, Sensing and Processing, NUS), and overseas collaborators.
X-SAT mission mainly intends to demonstrate technomogies related to satellite based remote sensing and onboard image processing.
RESOURCESAT-2
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YOUTHSAT
Orbit:|
- Circular Polar Sun Synchronous
- Circular Polar Sun Synchronous
Altitude at injection:|
- 822 ± 20 km (3 Sigma)
- 822 ± 20 km (3 Sigma)
Inclination:|
- 98.731 ± 0.2°
- 98.731 ± 0.2°
Period:|
- 101.35 min
- 101.35 min
Orbits/Day:|
- 14
- 14
Local Time of Equator crossing:|
- 10:30 a.m.
Repetivity:|
- 24 days
Lift-off Mass:|
- 1206 kg
- 92 kg
Dimensions:| |
- 1020 (pitch) x 604 (roll) x 1340 (yaw) mm
Attitude and Orbit Control:|
- 3-axis body stabilised using Reaction Wheels
- Magnetic Torquers
- Hydrazine Thrusters
- 3-axis body stabilised using Sun and Star Sensor
- Miniature Magnetometer
- Miniature Gyros
- Micro Reaction Wheels
- Magnetic Torquers
Power:|
- Solar Array 1250 W (EOL)
- 2 x 24 Ah Ni-Cd baterries
- Solar Array 230 W
- 10.5 Ah Li-Ion battery
Lifespan:|
- 5 years
- 2 years
Launch Vehicle:
PSLV-C16 is the eithteenth flight of ISRO's Polar Satellite Launch Vehicle, PSLV. In this flight, the standard version of PSLV with six solid strap-on motors is used.
PSLV was initially designed for launching 900 kg Indian Remote Sensing Satellites into a 900 km polar SSO. Since the first launch in 1993, PSLV has been successively improved to attain its present sapability.
The major changes made in PSLV since its first launch include changes in strap-on motors ignition sequence, increase in the propelland loading of the first stage and strap-on solid propellant motors as well as the second and fourth stage liquid propellant motors, improvement in the performance of the third stage motor by optimising motor case and enhanced propellant loading and employing a carbon composite payload adapter.
The PSLV has four stages using solid and liquid propulsion systems alternately. The first stage is one of the largest solid-fuel rocket boosters in the world and carries 138 tonnes of Hydroxyl-terminated polybutadiene (HTPB) bound propellant with a diameter of 2.8 m. The motor case is made of maraging steel. The booster develops a maximum thrust of about 4,430 kN. Six strap-on motors, four of which are ignited on the ground, augment the first stage thrust. Each of these solid propellant strap-on motors carries nine tonnes of HTPB propellant and produces 677 kN thrust. Pitch and yaw control of the PSLV during the thrust phase of the solid motor is achieved by injection of an aqueous solution of strontium perchlorate in the nozzle to constitute Secondary Injection Thrust Vector Control System (SITVC). The injection is stored in two cylindrical aluminum tanks strapped to the solid rocket motor and pressurized with nitrogen. There are two additional small liquid engine control power plants in the first stage, the Roll Control Thrusters (RCT), fixed radially opposite one on each side, between the triplet set of strap-on boosters. RCT is used for roll control during the first stage and the SITVC in two strap-on motors is for roll control augmentation.
The second stage employs the Vikas engine and carries 41.5 tonnes (40 tonnes till C-5 mission) of liquid propellant – Unsymmetrical Di-Methyl Hydrazine (UDMH) as fuel and Nitrogen tetroxide (N2O4) as oxidizer. It generates a maximum thrust of 800 kN (724 till C-5 mission). Pitch & yaw control is obtained by hydraulically gimbaled engine (±4°) and two hot gas reaction control for roll.
The third stage uses 7 tonnes of HTPB-based solid propellant and produces a maximum thrust of 324 kN. It has a Kevlar-polyamide fiber case and a submerged nozzle equipped with a flex-bearing-seal gimbaled nozzle (±2°) thrust-vector engine for pitch & yaw control. For roll control it uses the RCS (Reaction Control System) of fourth stage.
The fourth and the terminal stage of PSLV has a twin engine configuration using liquid propellant. With a propellant loading of 2 tonnes (Mono-Methyl Hydrazine as fuel + Mixed Oxides of Nitrogen as oxidiser), each of these engines generates a maximum thrust of 7.4 kN. Engine is gimbaled (±3°) for pitch, yaw & roll control and for control during the coast phase uses on-off RCS. PSLV-C4 used a new lightweight carbon composite payload adapter to enable a greater GTO payload capability.
PSLV is designed and developed at Vikram Sarabhai Space Centre (VSSC), Thiruvananthapuram, Kerala. The inertial systems are developed by ISRO Inertial Systems Unit (IISU) at Thiruvananthapuram. The liquid propulsion stages for the second and fourth stages of PSLV as well as the reaction control systems are developed by the Liquid Propulsion Systems Centre (LPSC), also at Thiruvananthapuram. The solid propellant motors are processed by Satish Dhawan Space Centre SHAR, which also carries out launch operations.
PSLV was initially designed for launching 900 kg Indian Remote Sensing Satellites into a 900 km polar SSO. Since the first launch in 1993, PSLV has been successively improved to attain its present sapability.
The major changes made in PSLV since its first launch include changes in strap-on motors ignition sequence, increase in the propelland loading of the first stage and strap-on solid propellant motors as well as the second and fourth stage liquid propellant motors, improvement in the performance of the third stage motor by optimising motor case and enhanced propellant loading and employing a carbon composite payload adapter.
The PSLV has four stages using solid and liquid propulsion systems alternately. The first stage is one of the largest solid-fuel rocket boosters in the world and carries 138 tonnes of Hydroxyl-terminated polybutadiene (HTPB) bound propellant with a diameter of 2.8 m. The motor case is made of maraging steel. The booster develops a maximum thrust of about 4,430 kN. Six strap-on motors, four of which are ignited on the ground, augment the first stage thrust. Each of these solid propellant strap-on motors carries nine tonnes of HTPB propellant and produces 677 kN thrust. Pitch and yaw control of the PSLV during the thrust phase of the solid motor is achieved by injection of an aqueous solution of strontium perchlorate in the nozzle to constitute Secondary Injection Thrust Vector Control System (SITVC). The injection is stored in two cylindrical aluminum tanks strapped to the solid rocket motor and pressurized with nitrogen. There are two additional small liquid engine control power plants in the first stage, the Roll Control Thrusters (RCT), fixed radially opposite one on each side, between the triplet set of strap-on boosters. RCT is used for roll control during the first stage and the SITVC in two strap-on motors is for roll control augmentation.
The second stage employs the Vikas engine and carries 41.5 tonnes (40 tonnes till C-5 mission) of liquid propellant – Unsymmetrical Di-Methyl Hydrazine (UDMH) as fuel and Nitrogen tetroxide (N2O4) as oxidizer. It generates a maximum thrust of 800 kN (724 till C-5 mission). Pitch & yaw control is obtained by hydraulically gimbaled engine (±4°) and two hot gas reaction control for roll.
The third stage uses 7 tonnes of HTPB-based solid propellant and produces a maximum thrust of 324 kN. It has a Kevlar-polyamide fiber case and a submerged nozzle equipped with a flex-bearing-seal gimbaled nozzle (±2°) thrust-vector engine for pitch & yaw control. For roll control it uses the RCS (Reaction Control System) of fourth stage.
The fourth and the terminal stage of PSLV has a twin engine configuration using liquid propellant. With a propellant loading of 2 tonnes (Mono-Methyl Hydrazine as fuel + Mixed Oxides of Nitrogen as oxidiser), each of these engines generates a maximum thrust of 7.4 kN. Engine is gimbaled (±3°) for pitch, yaw & roll control and for control during the coast phase uses on-off RCS. PSLV-C4 used a new lightweight carbon composite payload adapter to enable a greater GTO payload capability.
PSLV is designed and developed at Vikram Sarabhai Space Centre (VSSC), Thiruvananthapuram, Kerala. The inertial systems are developed by ISRO Inertial Systems Unit (IISU) at Thiruvananthapuram. The liquid propulsion stages for the second and fourth stages of PSLV as well as the reaction control systems are developed by the Liquid Propulsion Systems Centre (LPSC), also at Thiruvananthapuram. The solid propellant motors are processed by Satish Dhawan Space Centre SHAR, which also carries out launch operations.
Launch Preparations:
Links:
- ISRO:
PSLV-C16 Launch Kit (PDF)- Press Releases:
- RIA Novosti: 2011-04-18: India starts countdown for launch of 3 satellites
- Hindusian Times: 2011-04-18: Countdown for PSLV-C16 mission on
- The Hindu: 2011-04-18: All set for PSLV-C16 launch on Wednesday
- Wikipedia: [ame=http://en.wikipedia.org/wiki/Polar_Satellite_Launch_Vehicle]Polar Satellite Launch Vehicle[/ame]
