First trajectory correction manoeuvre on Mars Orbiter successfully done by ISRO

The first flight Correction Man-oeuvre of India's maiden heavenly body mission to Mars was on Wednesday dispensed with success by Isro scientists on the satellite, that is presently traveling some a pair of.9 million kilometer removed from Earth.

"The initial flight Correction Man oeuvre (TCM) of satellite was dispensed with success at 06:30 hrs (IST) by firing the twenty two Newton Thrusters for a length of forty.5 seconds. The satellite is traveling at a distance of regarding twenty nine hundred thousand (2.9 million) kilometer removed from Earth," ISRO aforementioned during a statement.

The TCMs fine tune the flight of the satellite to stay it traveling within the meant track towards the superior planet.

Today's correction was dispensed by the pc on board the satellite, since the quantity of your time needed for the signal to travel and come back was regarding twenty seconds, as mum was already traveling regarding some a pair of.9 million kilometer away, ISRO said.

"MOM team is gaining active expertise in handling the communication delay because it keeps increasing step by step," it said.

The satellite had quarantined of the Earth’s orbit on December one. The Indian Space Research Organization (Isro) has planned four TCMs throughout its journey to Mars. The man-oeuvres area unit required to stay the satellite on the specified path. it's additionally essential for maintaining the specified speed.

"The eight thrusters on board are going to be laid-off exactly to steer the mum to Mars throughout the flight Manoeuvrings Correction (TMC). Our navigation team has currently got an exact understanding of the precise flight of mum supported the vary and speed information non-heritable over the many days since the Trans-Mars Injection (TMI). now's the time to eliminate the minor deviations within the flight," Isro aforementioned.

Mangalyaan is on its 680-million-km voyage to Mars. If it makes it, Asian nation can be a part of a pick club comprising the America, Russia and Europe. Once within the Mars orbit, the orbiter’s 5 payloads can then begin performing arts experiments for following six months.

Source: http://www.isro.org/

Cartosat - 2B

Cartosat-2B                                                                                             Launch Date : 12.07.2010

CARTOSAT - 2B is the seventeenth satellite in the Indian Remote Sensing Satellite series (IRS). CARTOSAT-2B carries a Panchromatic camera (PAN) similar to those of its predecessors - CARTOSAT-2 and 2A. It is capable of imaging a swath (geographical strip) of 9.6 km with a resolution of better than 1 metre. The scene specific spot imagery sent by CARTOSAT-2B's PAN will be useful for cartographic and a host of other applications. The highly agile CARTOSAT-2B is steerable up to ± 26^o along as well as across track to obtain stereoscopic imagery and achieve a four to five day revisit capability.

Mission	Remote Sensing
Weight	694 kg (Mass at lift off)
Onboard Orbit	930 Watts
Stabilization	3 – axis body stabilised based on inputs from star sensors and gyros using Reaction wheels, Magnetic Torquers and Hydrazine Thrusters
Payloads	Panchromatic Camera
Launch date	July 12, 2010
Launch site	SHAR Centre Sriharikota India
Launch vehicle	PSLV- C15
Orbit	630 kms, Polar Sun Synchronous
Inclination	97.71º

For More : http://www.isro.org/satellites/cartosat-2b.aspx

Oceansat - 2

 Oceansat - 2                                                                      Launch Date : 23.09.2009

Oceansat-2 satellite mainframe systems derive their heritage from previous IRS missions and launched by PSLV-C14 from Satish Dhawan Space Centre, Sriharikota on Sept. 23, 2009. It carries three payloads:

• Ocean Colour Monitor (OCM)
• Ku-band Pencil Beam scatterometer (SCAT) developed by ISRO
• Radio Occultation Sounder for Atmosphere (ROSA) developed by the Italian Space Agency.

Oceansat-2 is envisaged to provide continuity of operational services of Oceansat-1(IRS-P4) with enhanced application potential.

Launch date Sept 23, 2009 Launch site SHAR, Sriharikota Launch vehicle PSLV - C14 Orbit Polar Sun Synchronous Altitude 720 km Inclination 98.28° Period 99.31 minutes Local time of Eq. crossing 12 noon ± 10 minutes Repetitivity cycle 2 days Payloads OCM, SCAT and ROSA Mass at lift off 960 kg Power 15 Sq.m Solar panels generating 1360W, Two 24 Ah Ni-Cd Batteries Mission Life 5 years

For More : http://www.isro.org/satellites/oceansat-2.aspx

RISAT - 2

RISAT - 2                                                                            Launch Date    20.04.2009

RISAT - 2

RISAT-2 is a Radar Imaging Satellite with all weather capability to take images of the earth. This Satellite will enhance ISRO's capability for Disaster Management applications.

Altitude	550 km
Inclination	41 deg
Orbit Period	90 minutes
Mass	300 kg

  For More : http://www.isro.org/satellites/RISAT-2.aspx

Technology Experiment Satellite (TES)

Technology Experiment Satellite (TES)                   Launch Date 22.10.2001

The Technology Experiment Satellite (TES), weighing 1108 kg, was launched on October 22,2001. TES is an experimental satellite to demonstrate and validate the technologies like attitude and orbit control system, high-torque reaction wheels, new reaction control system, light-weight spacecraft structure, solid state recorder, X-band phased array antenna, improved satellite positioning system, miniaturised TTC and power systems and, two-mirror-on-axis camera optics.

TES also carried a panchromatic camera for remote sensing experiments.

Launch date	22 October 2001
Launch site	SHAR Centre Sriharikota India
Launch vehicle	PSLV- C3
Orbit	572 kms Sun Synchronous
Payloads	PAN

Indian Remote Sensing Satellites System (IRS)

Indian Remote Sensing Satellites System (IRS)

The Indian Remote Sensing (IRS) satellite system is one of the largest constellations of remote sensing satellites in operation in the world today. The IRS programme commissioned with launch of IRS-1A in 1988 and presently includes Ten satellites that continue to provide imageries in variety of spatial resolutions from better than a metre ranging upto 500 metres.

1.	CARTOSAT-2B	Launched on July 12, 2010 by PSLV-C15
2.	OCEANSAT-2	Launched on Sept 23, 2009 by PSLV-C14
3.	RISAT-2	Launched on Apr 20, 2009 by PSLV-C12
4.	CARTOSAT-2A	Launched on Apr 28, 2008 by PSLV-C9
5.	IMS-1	Launched on Apr 28, 2008 by PSLV-C9
6.	CARTOSAT - 2	Launched on Jan 10, 2007 by PSLV-C7
7.	CARTOSAT-1	Launched on May 05, 2005 by PSLV-C6
8.	RESOURCESAT-1	Launched on Oct 17, 2003 by PSLV-C5
9.	TES	Launched on Oct 22, 2001 by PSLV-C3
10.	OCEANSAT-1	Launched on May 26, 1999 by PSLV-C2

For More : http://www.isro.org/scripts/currentprogrammein.aspx

INSAT - 4CR

INSAT - 4CR                                                    Launch Date 02.09.2007

INSAT - 4CR

INSAT–4CR spacecraft is configured with exclusive Ku band employing the I-2K Bus with a mass of 2130 Kg. It was injected into the orbit by GSLV-F04 rocket with enhanced Russian Cryogenic engine and co-located at 74^o East longitude along with INSAT–3C / Kalpana–1 / GSAT–3 (EDUSAT).

INSAT-4CR carries 12 high-power Ku-band transponders designed to provide Direct-to-home (DTH) television services, Video Picture Transmission (VPT) and Digital Satellite News Gathering (DSNG).

 

Mission	Communication
Weight	2,130 kg (Mass at Lift – off)
Onboard power	3000 W
Communication Payload	12 Ku-band transponders employing 140 W Traveling Wave Tube Amplifiers (TWTA) Ku-band Beacon
Launch date	September 2, 2007
Launch site	SHAR, Sriharikota, India
Launch vehicle	GSLV-F04
Orbit	Geosynchronous (74° E)
Mission life	12 Years

 

INSAT - 4B

INSAT - 4B                                               Launch Date 12.03.2007

INSAT-4B

INSAT–4B Spacecraft is the second in the INSAT 4 series of spacecrafts and is configured with exclusive communication payloads to provide services in Ku and C frequency bands. This is co-located with INSAT–3A at 93.5 ^o E longitude.

Mission	Communication
Weight	3025 Kg (at Lift – off)
Onboard Power	5859 W
Stabilization	It uses 3 earth sensors, 2 digital sun sensors, 8 coarse analog sun sensors, 3 solar panel sun sensors and one sensor processing electronics. The wheels and wheel drive electronics were imported with indigenous wheel interface module to interface the wheel drive electronics and AOCE.
Propulsion	The propulsion system is employing 16 thrusters, 4 each located on east, west and AY sides and 2 each on north and south sides. There is one 440 N liquid apogee motor (using Mono Methyl Hydrazine (MMH) as fuel and oxides of Nitrogen ( MON3 as oxidizer) and three presurant tanks mounted on the LAM deck.
Payload	12 Ku band high power transponders covering Indian main land using 140W radiatively cooled TWTAs.
	12 C band high power transponders with extended coverage, covering southeast and northwest region apart from Indian main land using 63 W TWTAs
Launch date	March 12, 2007
Launch Site	French Guyana
Launch Vehicle	Ariane5
Orbit	Geostationary (93.5o E Longitude)
Mission Life	12 Years

INSAT - 4A

INSAT - 4A                                         Launch Date 22.12.2005

INSAT-4A

INSAT-4A, first in INSAT-4 Satellites series provides services in Ku and C-band frequency bands. The Ku transponders cover the Indian main land and C-Band transponders cover an extended area. It has a dozen Ku transponders and another dozen of C-band transponders. This spacecraft is placed at 83^o E along with INSAT-2E and INSAT-3B, by Ariane launch vehicle (ARIANE5-V169).

Spacecraft Mass	Lift off 3081 Kg Dry Mass 1386.55 Kg
Orbit	Geostationary ( 83o E)
Power	Solar Array to provide a power of 5922 W
Battery	Three 70 Ah Ni H2 Batteries for eclipse support of 4264 W
Life	12 Years
Launch date	December 22, 2005
Launch vehicle	ARIANE5-V169

EDUSAT

EDUSAT                                       Launch Date         20.09.2004

EDUSAT

GSAT-3, known as EDUSAT is meant for distant class room education from school level to higher education. This is the first dedicated "Educational Satellite" that provide the country with satellite based two way communication to class room for delivering educational materials.

This is a Geo-synchronous satellite developed on I-2K bus. GSAT-3 is co-located with METSAT(KALPANA-1) and INSAT-3C at 74o E longitude.

Mission	Education
Spacecraft Mass	1950.5 Kg mass (at Lift - off) 819.4 Kg (Dry mass)
Onboard power	Total four solar panel of size 2.54 M x 1.525 M generating 2040 W (EOL), two 24 AH NiCd batteries for eclipse support
Stabilization	3 axis body stabilised in orbit using sensors, momentum and reaction wheels, magnetic torquers and eight 10 N & 22N reaction control thrusters.
Propulsion	440 N Liquid Apogee Motor with MON - 3 and MMH for orbit raising
Payload	Six upper extended C - band transponders Five lower Ku band transponders with regional beam coverage One lower Ku band National beam transponder with Indian main land coverage Ku beacon 12 C band high power transponders with extended coverage, covering southeast and northwest region apart from Indian main land using 63 W LTWTAs
Launch date	September 20, 2004
Launch site	SHAR, Sriharikota, India
Launch vehicle	GSLV-F01
Orbit	Geostationary (74oE longitude)
Mission Life	7 Years (minimum)

For More : http://www.isro.org/satellites/edusat.aspx