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#400 by vineethgk on 17 Dec, 2014 05:45
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Does anyone have a good image of CARE before encapsulation? The only ones currently in this thread are one with a clearly erroneous aspect ratio and one with a logo crudely photoshopped onto it.
The first is one taken in clean room from ISRO's web page for the mission.
EDIT: Attaching a second one that has been taken from the Indian Human Spaceflight Program thread
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#401 by vyoma on 17 Dec, 2014 07:38
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http://isro.org/gslv-mkiii-x/mkiii-x-updates.aspxQuote
Dec 17, 2014
N2O4 propellant filling operation of Second Stage - L110 is completed by 17:15 hrs (IST)
N2O4 propellant filling operation of Second Stage - L110 has commenced at 15:30 hrs (IST) and under progress
UH25 propellant filling operation of Second Stage - L110 is completed by 13:00 hrs (IST)
UH25 propellant filling operation of Second Stage - L110 is under progress
24 and a half hour countdown for the mission has commenced at 09:00 hrs (IST) on Dec 17, 2014
Dec 16, 2014
24 and a half hour countdown for the mission will commence at 09:00 hrs (IST) on Dec 17, 2014
Mission Readiness Review (MRR) and Launch Authorisation Board (LAB) met on Dec 16, 2014 to review progress of prelaunch activities and cleared launch for Dec 18, 2014 at 09:30 hrs (IST)QuoteLive Telecast by Doordarshan and Webcast of the Launch will be available on Dec 18, 2014 from 09:00 hrs (IST) onwards
http://webcast.isro.gov.in/ (alternate links available at the bottom of the page)
http://webcast.gov.in/live/
https://www.youtube.com/user/DoordarshanNational -
#402 by vyoma on 17 Dec, 2014 11:12
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#403 by antriksh on 17 Dec, 2014 11:47
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#404 by antriksh on 17 Dec, 2014 11:50
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No Silica tiles. Side and apex cover Thermal protection is based on medium density ablative (MDA) tiles, forward area uses carbon phenolic composite.
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#405 by abhishek on 17 Dec, 2014 12:06
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From the Brochure ...No where the term GSLV MK3 is mentioned,It appears that LVM3 is the official name.
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#406 by chota on 17 Dec, 2014 12:16
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From the Brochure ...No where the term GSLV MK3 is mentioned,It appears that LVM3 is the official name.
The original name is/was GSLVM3. LVM3 is a shortened notation for simplification -
#407 by abhishek on 17 Dec, 2014 12:23
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Doordarshan Broadcast Link
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#408 by abhishek on 17 Dec, 2014 12:26
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Vehicle Integration
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#409 by vineethgk on 17 Dec, 2014 12:32
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From the Brochure ...No where the term GSLV MK3 is mentioned,It appears that LVM3 is the official name.
The original name is/was GSLVM3. LVM3 is a shortened notation for simplification
The first page of the brochure refers to the project as 'GSLV Mk-III project'. I do remember that for some time they used to write as 'gsLVM3' in their models/brochures (with 'gs' in small letters and 'LVM3' in caps), possibly to de-emphasize its primary orbital role and transition to a more neutral name. Still I personally would have preferred a Sanskrit name like the way DRDO's missiles are named.
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#410 by Ohsin on 17 Dec, 2014 12:51
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Whats the use of first stage SITVC when the stage has flex nozzles ? redundancy?
But is it SITVC for sure? Brochure says "S200 FNC oil tank" (Flex nozzle control?). -
#411 by antriksh on 17 Dec, 2014 12:55
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Whats the use of first stage SITVC when the stage has flex nozzles ? redundancy?
But is it SITVC for sure? Brochure says "S200 FNC oil tank" (Flex nozzle control?).
yeah, got it wrong. its oil tank for nozzle actuation system.
100 N RCS thruster is a new development? -
#412 by Chris Bergin on 17 Dec, 2014 13:39
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Moved for live coverage.
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#413 by kanaka on 17 Dec, 2014 14:43
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From the Brochure ...No where the term GSLV MK3 is mentioned,It appears that LVM3 is the official name.
The weight of CREW Module is 3.6 Ton. But GSLV MK III is intended to be tested for 4 or more tonnes. How the weight parameter will be achieved if we have to launch satellite weighing more than 4 tonnes? -
#414 by chota on 17 Dec, 2014 15:02
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From the Brochure ...No where the term GSLV MK3 is mentioned,It appears that LVM3 is the official name.
The weight of CREW Module is 3.6 Ton. But GSLV MK III is intended to be tested for 4 or more tonnes. How the weight parameter will be achieved if we have to launch satellite weighing more than 4 tonnes?
Since its the first flight, there will be margins. The GTO payload is stretchable to 5.5 tons with semi cryo booster which is a future option.
The current configuration is designed to keep max flight acceleration to less than 4g and qmax to less than 40kpa. Increasing the L110 to L130 and making cryo stage with double burn option can increase the payload to 4.3 tons.
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#415 by inventodoc on 17 Dec, 2014 15:21
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Now here's something smart. Look at the servicing/integration structure and see how they keep the opening narrow by having the rocket exist sideways, as opposed to the wide door approach with TITAN and DELTA IV HEAVY. There's some practical thinking.
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#416 by Lars-J on 17 Dec, 2014 15:56
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I'm looking forward to the launch!
I have two questions about the LV, though, after seeing the latest schematic from the PDF:
1. Why do they leave the intertank area open on the upper stage of this LV? Or is this just for the inert test upper stage that isn't loaded with (semi) cryogenics? Has there ever been a launch vehicle that has had an enclosed interstage but exposed intertank section?
2. It looks like the the main load bearing for the SRBs is at the top, connected to the interstage. So since the core stage is not lot at launch, the interstage is pulling along the entire filled core stage?
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#417 by chota on 17 Dec, 2014 17:00
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2. It looks like the the main load bearing for the SRBs is at the top, connected to the interstage. So since the core stage is not lot at launch, the interstage is pulling along the entire filled core stage?
There are 2 joints between S200 and L110 stages, the top joint and the bottom joint.
Top joint helps in transferring the thrust from S200 SRB to the core vehicle
Bottom joint takes care of lateral, tensile and compressive loads -
#418 by AJA on 17 Dec, 2014 17:23
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FINALLY! A brochure! \m/ I'll take advantage of it not being launch-day yet, to interrupt the updates with ...
A few questions:
1. That plot of differential thrust on page 2 is interesting.
a) They've gone right up to (and possibly even past) the limit of what they can accept (between 20-30 seconds). Wonder if that's a real concern on this test. If you watch the PM's visit to SHAR, where he was meeting the scientists with their posters, one of them was also impressing how well the boosters were performing, and how they were well within the allowed asymmetries.
b) I also notice that there's a kink in the nominal curve too. i.e. some level of differential thrust is EXPECTED - and not even in a symmetric sense. They except a particular booster to have more thrust than another - even in their models? (see t~=120s) Why?
c) What are "paired/sim sorted propellants"
2. In the validation of base-heating/aerothermal design box:
a) they mention that they expect reverse flow at ~85 seconds. Huh? The rocket sure as hell doesn't start FALLING... even if 85 seconds was around staging (it's not). The L-110 ignition is also much later than 85 seconds. So what is this reverse flow they're talking about?
b) What's "nozzle closure performance" ?
3. Is the collet separation mechanism standard issue on other LVs (both ISRO and non-ISRO)?QuoteIndependent Telecommand system for each stage
Methinks that's a direct fallout from the shroud-gate, and that wire-tunnel deformation and loss of communication between the computer and the lower stagesQuoteThe LOX and LH2 tank are filled with Liquid Nitrogen (LN2) and Gaseous Nitrogen (GN2) respectively
Clever
. LN2 would weigh around as much as LO2 of the same volume (assuming they have similar liquid state densities)... and they can chill GN2 until it probably weighs as much as LH2, albeit without turning liquid, and nightmarish.
4. I notice that the launch azimuth is a 120 degrees. This probably had a lot to do with bringing CARE down near extant Naval facilities in Port-Blair, for expedited transfer back to the peninsula, as well as sticking to the no-fly zones. But, given the high trajectory, could they not have gotten a bit more "free" energy - translated into height... if they'd flown at the optimum azimuth? (i.e. at 90- ~13 = 77 degrees- as measured clockwise from North, where ~13 is the latitude of the launch pad?) Would that have entailed overflying some of our coastal areas? At first glance it seems like we'd be able to splash-down near WB... or even in the Chandipur test range, if they went higher, rather than longer.
5. (They changed the acronym from GNC to NGC <aargh>). What are "mini resins" that they're referring to when they talk about navigational aids for CARE?
Finally, to nitpick.. why are there no secondary sounding-rocket-type high atmosphere science payloads? Securely mounted to the inside wall of the PLF, without posing a major threat to the heat-shield.Now here's something smart. Look at the servicing/integration structure and see how they keep the opening narrow by having the rocket exist sideways, as opposed to the wide door approach with TITAN and DELTA IV HEAVY. There's some practical thinking.
Isn't there a drawback too? You'd have to wait for a booster to get into place before you began integration. (Assuming that each door was either an entry and/or exit door only, and that there wouldn't be enough manoeuvring room - horizontally.. inside the VAB). And what about moving the crane, and or equipment, if they needed to be changed out? Making the doors slide a bit more doesn't add a lot more in terms of cost does it? -
#419 by chota on 17 Dec, 2014 17:36
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I'm looking forward to the launch!
I have two questions about the LV, though, after seeing the latest schematic from the PDF:
1. Why do they leave the intertank area open on the upper stage of this LV? Or is this just for the inert test upper stage that isn't loaded with (semi) cryogenics? Has there ever been a launch vehicle that has had an enclosed interstage but exposed intertank section?
GSLV-MK2 has a similar setup. Weight reduction?
. LN2 would weigh around as much as LO2 of the same volume (assuming they have similar liquid state densities)... and they can chill GN2 until it probably weighs as much as LH2, albeit without turning liquid, and nightmarish.