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#320
by
isro-watch
on 08 Dec, 2014 04:06
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Expected Launch Date: 18-Dec-2014
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#321
by
vyoma
on 08 Dec, 2014 04:33
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http://www.thehindu.com/todays-paper/tp-national/tp-tamilnadu/women-power-the-most-powerful-rocket/article6669203.eceThe digital auto pilot (DAP), the software that controls the rocket, was designed by V.R. Lalithambika and her team. D.S. Sheela is the group director; V. Brinda is the head of the Control Design Division; and Manju Unnikrishnan and Rani designed the onboard software and its integration.
The simulation of the flight of LVM3 requires special software. S. Anitha, A. Sreelatha and Jayachithara are among the seniors who worked on the software.
B. Valsa is an expert in software engineering and deputy director responsible for the system reliability of the VSSC. “She and her team, comprising 200 engineers and other technical staff, are responsible for the quality and reliability of the systems as well as testing,” says Mr. Somanath.
Structural designer A.P. Beena, along with her young colleague Geethu Abraham and others, designed the Crew Module Atmospheric Re-entry Experiment (CARE) structure for this mission. “Beena has designed the propellant tanks of the L110 stage of LVM3,” Mr. Somanath notes.
Rachel SKD, a veteran in structural design, has earlier designed many structures of the PSLV and the GSLV. For LVM3, she and her colleagues have designed the most critical structures, very complex in design.
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#322
by
input~2
on 08 Dec, 2014 08:55
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Expected Launch Date: 18-Dec-2014
Seems to be confirmed by NOTAM announcing closure of airways East of Chennai (MMV VOR) from December 18, 0330UTC
A2212/14 - CLOSURE/ALTN ROUTINGS: I) P574 NOT AVBL BTN MMV VOR AND DUBTA ALTN RTE: MMV VOR-DCT-ADKIT-POINT Z 0854N08626E-DCT-DUBTA-P574 (BIDIRECTIONAL) II) P761 NOT AVBL BTN MMV VOR AND IDASO ALTN RTE: MMV VOR - TR319/139DEG-53NM-TTP VOR-DCT- POINT A 142225N0800303E-DCT- GURAS-DCT-IDASO(BIDIRECTIONAL) III) P762 NOT AVBL BTN BIKEN AND DUGOS ALTN RTE: BIKEN-DCT-POINT Z 0854N08626E-DCT -DUGOS-P762 (BIRECTIONAL) IV) W20 NOT AVBL BTN MMV VOR AND BODEL ALTN RTE: MMV VOR- TR319/139DEG-53NM-TTP VOR- TR357/177DEG-81NM- BODEL (BIDIRECTIONAL) V) A465 NOT AVBL BTN MMV VOR AND DOKET ALTN RTE: MMV VOR-TR319/139DEG-53NM-TTP VOR- DCT- POINT A 142225N0800303E-DCT-DOKET (BIDIRECTIONAL) VI) ATS RTE N563,B466,Q10,Q11,V003,V004,V006,V008,V009 AND V011 NOT AVBL. GND - UNL) END PART 1 OF 2, 0330-0730, 18 DEC 03:30 2014 UNTIL 31 DEC 07:30 2014. CREATED: 03 DEC 16:49 2014
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#323
by
abhishek
on 09 Dec, 2014 05:05
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GSLV Mark-III launch on Dec. 18 Indian Space Research Organisation’s heaviest and upgraded rocket -Geosynchronous Satellite Launch Vehicle (GSLV – Mark III) will lift off from the second launch pad at Satish Dhawan Space Centre SHAR, Sriharikota on December 18.
On Monday, a high level meeting was held and all activities done so far were cleared.
“The launch will happen on December 18. Anytime between 9 a.m. and 12 p.m. We will announce the exact time closer to the launch,” S. Somanath, project director, GSLV Mark III, said.
http://www.thehindu.com/sci-tech/science/gslv-markiii-launch-on-dec-18/article6674261.ece
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#324
by
antriksh
on 09 Dec, 2014 06:07
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from past: Effective thermal shield made up of silica tiles and cc material -SRE-1 before and after reentry
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#325
by
vyoma
on 09 Dec, 2014 11:18
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Captions:
gslv-mkiii-x-1.jpg: The two S200 Strap-ons during the integration of the vehicle
gslv-mkiii-x-2.jpg: L110 Liquid Core Stage being prepared at Stage Preparation Facility
gslv-mkiii-x-3.jpg: The partially integrated vehicle with S200 Strap-ons and L110 Core Stage outside the Vehicle Assembly Building
gslv-mkiii-x-4.jpg: The passive C25 Cryogenic Upper Stage being hoisted at Vehicle Assembly Building
gslv-mkiii-x-5.jpg: Integration of the passive C25 Cryogenic Upper Stage with L110 liquid Core Stage in Progress at Vehicle Assembly Building
gslv-mkiii-x-6.jpg: CARE at clean room before its launch
Source:
http://isro.org/gslv-mkiii-x/Imagegallery/launchvehicle.aspx
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#326
by
vineethgk
on 09 Dec, 2014 11:57
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I wish ISRO settles on a single name for the rocket. Either GSLV Mk-III or GSLV-III or LVM3. Right now, it says LVM3 in the cryo stage mockup, but GSLV-Mk-III elsewhere.
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#327
by
antriksh
on 09 Dec, 2014 13:15
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Lets hope they have installed inflight video telemetry system
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#328
by
vyoma
on 10 Dec, 2014 02:05
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http://timesofindia.indiatimes.com/home/science/Isro-to-test-GSLV-Mk-III-crew-module-on-December-18/articleshow/45444522.cms... Geo-Synchronous Satellite Launch Vehicle (GSLV-MIII) on December 18 between 9am and 12pm from Sriharikota.
Somanath said that 325 seconds after the lift off, the crew module — made of aluminium alloy and with a lift-off mass of 3,735kg — will separate from the rocket at an altitude of 126km. Three different types of parachutes tested at facilities in Chandigarh and at Sriharikota by dropping them from a helicopter will be deployed during the descent. About 1,280 seconds after the launch the module will splashdown in the Bay of Bengal at a point 600km from Port Blair. It will be recovered by the Indian Coast Guard.
Somanath said that the module has an ablative thermal protection system because during re-entry into the atmosphere, it will experience heat around 1,600 degrees C.
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#329
by
abhishek
on 10 Dec, 2014 18:21
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The 3.7-tonne crew module being tested next week will be the same size, shape and weight as the capsule that is being developed to accommodate up to three astronauts. It will be equipped with the heat-protecting tiles and parachute system of the manned version.
While a capsule in orbit around Earth will re-enter with a velocity of over 28,000 km per hour, next week’s test will see the GSLV Mark III leave the crew module at a height of about 125 km with a velocity of around 19,000 km per hour. The crew module carries sensors that will make measurements of over 200 parameters during the flight, including the temperature, pressure and stress experienced at various points in the structure.
After separation from the GSLV Mark III, six liquid-propellant thrusters on the crew module will be used to correct any perturbations that occur during separation and bring the capsule down at the correct angle for re-entry into the atmosphere.
Once re-entry starts at a height of about 80 km, the thrusters will cease to operate. As the crew module streaks through the atmosphere, the air around it heats up and the spacecraft slows down.
The crew module carries two independent sets of parachutes, both of which are simultaneously deployed. First, the 2.5-metre diameter pilot parachutes come out, followed by the 6.5-metre drogue parachutes, which cut the capsule’s velocity down to 180 km per hour.Then the main parachutes are deployed at a height of about 5 km. These parachutes, each 31 metres in diameter, are the largest ever made in the country and were developed by the Aerial Delivery Research & Development Establishment, an Agra-based national defence laboratory.
On splashdown, the main parachutes will be immediately detached from the crew module and a beacon giving its position activated. A fluorescent green dye will also be emitted to aid in locating the spacecraft.
In the coming test, the crew module could experience decelerations of up to 13 g, said Mr. Nair. But, in a mission with humans onboard, the capsule’s thrusters would continue to operate till parachute deployment began, adjusting the spacecraft's orientation and trajectory, and keeping deceleration levels to less than 4 g. (One g being equivalent to the tug of Earth's gravity.
http://www.thehindu.com/sci-tech/science/unmanned-crew-module-to-be-tested/article6679866.ece
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#330
by
Danderman
on 10 Dec, 2014 18:34
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In the coming test, the crew module could experience decelerations of up to 13 g, said Mr. Nair. But, in a mission with humans onboard, the capsule’s thrusters would continue to operate till parachute deployment began, adjusting the spacecraft's orientation and trajectory, and keeping deceleration levels to less than 4 g. (One g being equivalent to the tug of Earth's gravity.
I am translating the above to mean that a nominal descent would use thrusters to control the vehicle's attitude during re-entry by rotating around the vehicle c/g (to generate lift), whereas this test will use a ballistic return.
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#331
by
Danderman
on 10 Dec, 2014 18:37
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The 3.7-tonne crew module being tested next week will be the same size, shape and weight as the capsule that is being developed to accommodate up to three astronauts.
This is another data point indicating that the capsule is larger than Soyuz, although it is unclear whether the 3.7 ton mass is just the capsule, or if it includes peripheral equipment.
For reference, Soyuz has a mass of 3 tons for the descent module. The 3.7 ton mass implies a larger diameter, perhaps 2.5 meters - 3 meters.
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#332
by
antriksh
on 10 Dec, 2014 19:54
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In the coming test, the crew module could experience decelerations of up to 13 g, said Mr. Nair. But, in a mission with humans onboard, the capsule’s thrusters would continue to operate till parachute deployment began, adjusting the spacecraft's orientation and trajectory, and keeping deceleration levels to less than 4 g. (One g being equivalent to the tug of Earth's gravity.
I am translating the above to mean that a nominal descent would use thrusters to control the vehicle's attitude during re-entry by rotating around the vehicle c/g (to generate lift), whereas this test will use a ballistic return.
For this test, capsule's flight profile will be actively controlled till the point of reentry. From renetry onwards, the flight profile will be ballistic.
For manned capsule, flight profile up to the point of deployment of parachutes would be controlled by thrusters.
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#333
by
antriksh
on 10 Dec, 2014 19:57
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The 3.7-tonne crew module being tested next week will be the same size, shape and weight as the capsule that is being developed to accommodate up to three astronauts.
This is another data point indicating that the capsule is larger than Soyuz, although it is unclear whether the 3.7 ton mass is just the capsule, or if it includes peripheral equipment.
For reference, Soyuz has a mass of 3 tons for the descent module. The 3.7 ton mass implies a larger diameter, perhaps 2.5 meters - 3 meters.
Dia = 3.1 m, Ht = 2.6 m
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#334
by
vineethgk
on 11 Dec, 2014 04:03
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The 3.7-tonne crew module being tested next week will be the same size, shape and weight as the capsule that is being developed to accommodate up to three astronauts.
This is another data point indicating that the capsule is larger than Soyuz, although it is unclear whether the 3.7 ton mass is just the capsule, or if it includes peripheral equipment.
For reference, Soyuz has a mass of 3 tons for the descent module. The 3.7 ton mass implies a larger diameter, perhaps 2.5 meters - 3 meters.
Dia = 3.1 m, Ht = 2.6 m
Would love to know how the habitable volume of this capsule would compare to that of Soyuz and Shenzhou reentry modules, since this has a more conical rather than 'headlight' shape. Initially, when Shenzhou reentry capsule was found to be larger than Soyuz, there were some speculations that the Chinese were planning to accommodate 4 persons, though it did not happen. Since this capsule looks quite a bit larger than either of them, I wonder if it would be feasible (or even possible) to accommodate a crew of 4, albeit a bit cramped.
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#335
by
Ohsin
on 11 Dec, 2014 05:54
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Drum roll !!
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#336
by
vineethgk
on 11 Dec, 2014 06:11
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Drum roll !!
Great!
So 'LVM3' seems to be the name ISRO has settled to. Its written all over (S-200, L-110 and C-25)
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#337
by
chota
on 11 Dec, 2014 10:55
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#338
by
chota
on 11 Dec, 2014 12:13
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Tracks from Vehicle Assembly Building (VAB) to Second Launch Pad (SLP).
Solid Stage Assembly Building (SSAB) in the background
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#339
by
vineethgk
on 11 Dec, 2014 12:37
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Tracks from Vehicle Assembly Building (VAB) to Second Launch Pad (SLP).
Solid Stage Assembly Building (SSAB) in the background
Was just going to ask what was the building that I was seeing behind VAB. Thanks Chota!
Btw, what is that launch pedestral-like thing with rails which I see on the left bottom corner of the first image (kind of midway between SSAB and VAB)?
So 'LVM3' seems to be the name ISRO has settled to. Its written all over (S-200, L-110 and C-25)