Author Topic: PSLV-XL C50 - CMS-01 (ex GSAT-12R) - SLP - December 17, 2020 (10:11 UTC)  (Read 27986 times)

Offline input~2

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Launch of GSAT-12R to replace GSAT-12 at 83įE planned NET March.
« Last Edit: 12/11/2020 09:30 pm by input~2 »

Offline TheVarun

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Re: PSLV - GSAT 12R - NET March 31, 2020
« Reply #1 on: 02/29/2020 02:06 pm »
 Whoa, this launch came out of the blue!  Not mentioned on any mission list. Nice surprise.

Offline zubenelgenubi

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Re: PSLV-XL - GSAT 12R - NET March 31, 2020
« Reply #2 on: 03/02/2020 04:21 am »
2020 High Level Schedule
<snip>
> Advanced communication satellites - Gisat1 and Gsat-12R
<snip>
Source : https://m.timesofindia.com/india/isros-2020-target-sun-mission-gaganyaan-test-flight-mini-pslv-test-and-10-sat-launches/amp_articleshow/72931226.cms
Dated December 23, 2019; corrected quote content
***

GSat 12

Mass: 1410 kg, built on the I-1K bus; launched into a sub-GTO by a PSLV-XL

If this replacement is also built on the I-1K bus, and of similar mass, then it would most likely also be launched using the same LV model.
***

Launch NET March 31 could likely make this the launch immediately following GISAT-1.

The FLP is presumably occupied by preparations for the SSLV D1 launch in April.  So this launch, if it is before SSLV D1, would have to be from the SLP.
***

Do we have a source for the NET March 31 launch date?
« Last Edit: 03/02/2020 04:46 pm by zubenelgenubi »
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Offline input~2

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Re: PSLV - GSAT 12R - NET March 31, 2020
« Reply #3 on: 03/02/2020 06:58 am »
Do we have a source for the NET March 31 launch date?
Source is LEOP earth stations network

Offline K210

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Re: PSLV - GSAT 12R - NET March 31, 2020
« Reply #4 on: 03/19/2020 01:27 pm »
According to regional media PSLV C50 launch campaign is running in parallel to C49 and F10. Given the NET March 31st date by OP it is highly probable this is the vehicle that will carry GSAT-12R since payloads for C49 are already well known. 

Source (In Telugu): https://m.dailyhunt.in/news/india/telugu/eenadu-epaper-eena/shaarlo+raaket+anusandhaana+panula+nilipiveta-newsid-171311694

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Re: PSLV-XL C50 - GSAT 12R - SLP - 2020-H2
« Reply #5 on: 06/27/2020 04:27 am »
Cross-post:
https://www.eenadu.net/districts/latestnews/Nellore/9/120071838
Quote from: Google translate
Polar Satellite Launch Vehicle C49 (PSLV) [and] C50 carriers are ready for launch.
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Offline zubenelgenubi

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Re: PSLV-XL C50 - GSAT 12R - SLP - late August 2020
« Reply #6 on: 07/27/2020 05:53 pm »
Cross-post; apparently this will be the Indian "return to flight":
According to local media report, ISRO is aiming to launch PSLV C50 in last week of August from Second launch Pad depending upon COVID-19 situation.
[Article Language Telugu]
https://www.prabhanews.com/2020/07/corona-effect-isro/
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Offline zubenelgenubi

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Re: PSLV-XL C50 - GSAT 12R - SLP - NET year end 2020
« Reply #7 on: 09/07/2020 04:29 pm »
Cross-post re: PSLV C49 and C50:
Quote
Officials told TNIE that at least two launched would happen by this year end.
source: https://www.newindianexpress.com/nation/2020/aug/26/isro-rocket-launch-station-at-sriharikota-resumes-work-partially-2188285.html
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Offline K210

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Re: PSLV-XL C50 - GSAT 12R - SLP - NET year end, 2020
« Reply #8 on: 09/09/2020 09:28 am »
Launch delayed to March 2021:

Quote
Efforts are being made to complete the PSLV C49 experiment by December this year. In addition, the PSLV C50 and the GSLV F10, which was postponed to the last minute on March 5 this year, is scheduled to be completed by the end of March 2021. 

Source (In Telugu): https://www.sakshi.com/telugu-news/andhra-pradesh/isro-launches-pslv-c49-december-shar-1313902

Offline input~2

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Offline input~2

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Offline K210

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Re: PSLV-XL C50 - GSAT 12R - SLP - December 2020
« Reply #11 on: 10/07/2020 10:01 am »
C50 Launch vehicle as of June 2020

Offline zubenelgenubi

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Re: PSLV-XL C50 - CMS-01 - SLP - December 2020
« Reply #12 on: 11/07/2020 02:43 pm »
Cross-post:
Next launch is PSLV C50 with "CMS 01" followed by first SSLV with "EOS 02" and GSLV F10 with "EOS 03".

End of webcast.
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Offline Steven Pietrobon

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Re: PSLV-XL C50 - CMS-01 - SLP - December 2020
« Reply #13 on: 11/08/2020 01:12 am »
Hopefully I heard right that this is now called CMS 01. It took me a couple of goes to understand EOS 02 and EOS 03 for the other missions.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

Offline zubenelgenubi

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Re: PSLV-XL C50 - CMS-01 - SLP - December 2020
« Reply #14 on: 11/08/2020 03:11 am »
Hopefully I heard right that this is now called CMS 01. It took me a couple of goes to understand EOS 02 and EOS 03 for the other missions.

I went back and listened to the post launch speech as well.  Same conclusion as you.
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Offline otter

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Re: PSLV-XL C50 - CMS-01 - SLP - December 2020
« Reply #15 on: 11/08/2020 05:29 am »
https://www.indiatvnews.com/amp/science/isro-communication-satellites-generic-name-pslv-c49-eos-01-launch-663162

/.../ Chairman of Indian Space Research Organisation (ISRO), K. Sivan, said the next rocket to fly will be PSLV-C50 with CMS-01 satellite.

The acronym CMS stands for Communication Satellite and the 01 tagged to it is the serial number.

As per plans, ISRO will launch the GSAT-12R satellite using the PSLV-C50.

Offline Skyrocket

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Re: PSLV-XL C50 - CMS-01 - SLP - December 2020
« Reply #16 on: 11/08/2020 09:09 am »
It seems, that ISRO is replacing the real satellite names with generic designations. I will continue to use the real names (as long as they are known) and add the generic EOS or CMS designations as secondary designations (similar to the USA designations for US military satellites).

Offline otter

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Re: PSLV-XL C50 - CMS-01 - SLP - December 2020
« Reply #17 on: 11/13/2020 04:34 am »
A4302/20 NOTAMN

Q) WMFC/QRDCA/IV/BO /W /000/999/0955N09522E039
A) WMFC B) 2012060930 C) 2101041330 D) DLY 0930-1330
E) TEMPO DNG AREA ESTABLISHED DUE TO THE LAUNCHING OF PSLV-C50 ROCKET FM INDIA
WI: 0935N 09450E-1030N 09505E- 1015N 09555E-0920N 09540E (DNG ZONE 6)
RMK: 1. NO FLT IS PERMITTED OVER THE DNG ZONE. 2. ATS RTE P628 IS AFFECTED WITHIN KUALA LUMPUR FIR AND A PORTION BTN WPT MAPSO AND IGREX IS NOT AVBL DUE TO DNG ZONE 6.
F) SFC G) UNL

Offline otter

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A2878/20 NOTAMN
Q) VOMF/QWMLW/IV/NBO/W/000/999/
A) VOMF PART 1 OF 3 B) 2012070930 C) 2101041330 D) 0930-1330
E) PSLV-C50 ROCKET LAUNCH FM SHAR RANGE, SRIHARIKOTA WILL TAKE PLACE AS PER FLW DETAILS. THE LAUNCH WILL BE ON ANY ONE OF THE DAY DRG THIS PERIOD. ACTUAL DATE OF LAUNCH WILL BE INTIMATED 24HRS IN ADVANCE THROUGH A SEPERATE NOTAM.
/../
   
Full NOTAM text - https://pastebin.pl/view/fbb601a5

Offline lucas071200

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« Last Edit: 11/29/2020 07:42 am by lucas071200 »

Offline zubenelgenubi

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A2878/20 NOTAMN
Daily launch windows, December 7 to January 4, 0930-1330 UTC.
***

NET 14th According to this article https://www.eenadu.net/apmukyamshalu/mainnews/ap-main/2501/120142957
Reason : hurricanes
One tropical cyclone = hurricane: Very Severe Cyclonic Storm Nivar blew ashore from the Bay of Bengal on November 25/26 UTC (correct dates?).  Is there another tropical cyclone brewing in the Bay?  I checked Wikipedia (I know, I know) before posting and found no mention of such.

Article paraphrase, via Google translation: The LV transfer to the pad was to occur on December 2.
Quote
However, the Sharjah Meteorological Department said there would be a series of hurricanes till the 8th.

edit by input~2: Sharjah is a mistranslation for SHAR
« Last Edit: 12/02/2020 12:13 pm by input~2 »
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Offline zubenelgenubi

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Cross-post:
Guys is the launch of GSAT12-R set for 14th December ?
There is a possibility it might be delayed to later this month or early next month due to unfavourable weather.
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Offline input~2

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A4553/20 NOTAMN Q) WMFC/QRDCA/IV/BO /W /000/999/0955N09522E039 A) WMFC B) 2012070930 C) 2101041330 D) 0930-1330 E) TEMPO DNG ZONE 6 ESTABLISHED WI THE FLW COORD DUE TO THE LAUNCHING OF PSLV-C50 ROCKET FROM INDIA: 0935N 09450E-1030N 09505E- 1015N 09555E-0920N 09540E. NO FLT IS PERMITTED OVER AND NEAR THE DNG ZONE. ATS RTE P628 IS AFFECTED WI KUALA LUMPUR FIR AND A PORTION BTN WPT MAPSO AND IGREX IS NOT AVAILABLE. REF NOTAM VOMF A2878/20. RMK: ACTUAL DATE OF LAUNCH WILL BE INTIMATED 24HRS IN ADVANCE THROUGH NOTAM PUBLICATION BY VOMF. F) SFC                             G) UNL

Offline otter

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Postponed to the December 17 due to the possibility of storms and rains

https://www.eenadu.net/nationalinternational/newsarticle/general/0702/120150404

Offline otter

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A2971/20 NOTAMN
Q) VOMF/QWMLW/IV/BO/W/000/999/
A) VOMF PART 1 OF 4 B) 2012170930 C) 2101041330 D) 0930-1330
E) PSLV-C50 ROCKET LAUNCH FM SHAR RANGE, SRIHARIKOTA WILL TAKE PLACE AS PER FLW DETAILS. THE LAUNCH WILL BE ON ANY ONE OF THE DAY DRG THIS PERIOD. ACTUAL DATE OF LAUNCH WILL BE INTIMATED 24HR IN ADV THROUGH A SEPERATE NOTAM.
LAUNCH PAD COORD: 134312N 0801348E NO FLT IS PERMITTED OVER THE DNG ZONE. DNG ZONE -1: IS A CIRCLE OF 10NM AROUND THE LAUNCHER. DNG ZONE -2: IS AN AREA ENCLOSED BY THE FLW COORD: I. 1330N 08030E II. 1350N 08035E III.1335N 08135E IV. 1315N 08130E DNG ZONE 3: IS AN AREA ENCLOSED BY THE FLW COORD: I. 1300N 08210E II. 1330N 08215E III.1305N 08405E IV. 1235N 08400E
END PART 1 OF 4

Full NOTAM text - https://pastebin.pl/view/raw/1ec00bf6

Offline Danderman

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A4553/20 NOTAMN Q) WMFC/QRDCA/IV/BO /W /000/999/0955N09522E039 A) WMFC B) 2012070930 C) 2101041330 D) 0930-1330 E) TEMPO DNG ZONE 6 ESTABLISHED WI THE FLW COORD DUE TO THE LAUNCHING OF PSLV-C50 ROCKET FROM INDIA: 0935N 09450E-1030N 09505E- 1015N 09555E-0920N 09540E. NO FLT IS PERMITTED OVER AND NEAR THE DNG ZONE. ATS RTE P628 IS AFFECTED WI KUALA LUMPUR FIR AND A PORTION BTN WPT MAPSO AND IGREX IS NOT AVAILABLE. REF NOTAM VOMF A2878/20. RMK: ACTUAL DATE OF LAUNCH WILL BE INTIMATED 24HRS IN ADVANCE THROUGH NOTAM PUBLICATION BY VOMF. F) SFC                             G) UNL

What will be the inclination of the initial orbit?

It looks like all 3 drop zones are somewhere around 13 degrees north, and drop zone 3ís map location on the graphic doesnít match up with the given coordinates.

The coordinates in the NOTAM imply that the lower stages are flying to a 13 degree inclination.
« Last Edit: 12/11/2020 03:05 am by Danderman »

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Offline TheVarun

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Brochure for the flight. No mention of the weight/mass of the satellite(?).  The first GSLVGSAT-12 was 1410 kg. Is this one identical in mass?( Wikipedia says yes, it is 1410kg)

https://www.isro.gov.in/pslv-c50-cms-01/pslv-c50-cms-01-brochure

Edit by mod
« Last Edit: 12/11/2020 09:23 pm by input~2 »

Offline A.K.

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Brochure for the flight. No mention of the weight/mass of the satellite(?).  The first GSLVGSAT-12 was 1410 kg. Is this one identical in mass?( Wikipedia says yes, it is 1410kg)

https://www.isro.gov.in/pslv-c50-cms-01/pslv-c50-cms-01-brochure

Edit by mod
Wikipedia doesn't say anything itself but cites ISRO sources.

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Assembled vehicle rolled out to launch pad.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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Official webcast:
bit.ly/SpaceLaunchCalendar ☆ bit.ly/SpaceEventCalendar

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Webcast has started, but the SNR is pretty low.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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Vehicle on the pad.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-35 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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Launch milestones.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-30 minutes. DD stream has unfortunately stopped.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

Offline K210

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So this mission is to sub-GTO after all. The mission brochure mentioned intended orbit as GTO which is now confirmed to be incorrect.

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Assembly photos.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-25 minutes. DD is back.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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Vehicle configuration.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-20 minutes. Spacecraft on internal battery.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-15 minutes. Authorisation for launch given.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-12 minutes. Launch sequence.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-10 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-9 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-8 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-7 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-6 minutes. CMS-01 mission.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-5 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-4 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-3 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-2 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T-1 minute. Weather is fine.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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Liftoff!
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T+1 minute. Ground lit strapons separated.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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Air lift strapons separated.

T+2 minutes. First stage separated.
« Last Edit: 12/17/2020 09:14 am by Steven Pietrobon »
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T+3 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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Fairing separation.

T+4 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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Second stage separation.

T+5 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T+6 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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Third stage cutoff.

T+7 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T+8 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T+9 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T+10 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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Third stage separation.

Fourth stage ignition.

T+11 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T+12 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T+13 minutes. Fourth stage performance nominal.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T+14 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T+15 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T+16 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T+17 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T+18 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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T+19 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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PS4 cutoff. Injection conditions achieved.

T+2 minutes.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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Separation!
« Last Edit: 12/17/2020 09:32 am by Steven Pietrobon »
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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Happy team.
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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ISRO Chairman announcing mission success. Saying this is a continuation of GSAT 12 mission!
« Last Edit: 12/17/2020 09:35 am by Steven Pietrobon »
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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Next mission is PSLV C51 with three satellites. Carrying private Earth observation mission called Anand? from Excel India?. Other satellites are from Spacefix India? called Saditsat? and the University Consortium Unitysat.

Solar panels have deployed.

Wishing everyone Merry Christmas and a Happy New Year.
« Last Edit: 12/17/2020 09:58 am by Steven Pietrobon »
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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End of webcast.

Congratulations to ISRO for the successful launch!
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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Congratulations to ISRO for the successful launch!

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Liftoff/Onboard camera video:


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 Good launch!   Still no mention of the exact weight of the CMS-01 anywhere that is readable/audible :). And no reasonably precise date for the SSLV-D1, which is very long awaited!  It was originally scheduled for the end of 2019.
« Last Edit: 12/17/2020 01:55 pm by TheVarun »

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Good launch!   Still no mention of the exact weight of the CMS-01 anywhere that is readable/audible :). And no reasonably precise date for the SSLV-D1, which is very long awaited!  It was originally scheduled for the end of 2019.

The story here on the front page gives the mass of CMS-01.

I still have not seen the orbital parameters of the GTO interim orbit. The launch azimuth was 102.9 degrees, which implies something around 12 degrees orbital inclination.
« Last Edit: 12/17/2020 02:54 pm by Danderman »

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2 objects have been cataloged:
2020-099A/47256 in 275 x 20881 km x 17.79į (Arg. of perigee: 178.73į)
2020-099B/47257 in 257 x 20656 km x 17.86į

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---
SMS ;-).

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What will be the delta-V from initial sub-GTO to GEO?
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What will be the delta-V from initial sub-GTO to GEO?

1980 m/s.

http://www.sworld.com.au/steven/space/orbit.zip

Delta-V calculator by Steven S. Pietrobon. 22 Jun 2019.
Enter negative perigee height to exit program.
Enter negative height for geosynchronous altitude.

Enter initial perigee height (km): 275
Enter initial apogee height (km): 20881
Enter required inclination change (deg): 17.79
Enter required perigee height (km): -1
Geosynchronous perigee = 35786.0 km
Enter required apogee height (km): -1
Geosynchronous apogee = 35786.0 km

Burn at   275.0 km: theta1 =  0.00 deg, dv1 =  359.1 m/s
Burn at 35786.0 km: theta2 = 17.79 deg, dv2 = 1622.1 m/s
dv = 1981.2 m/s

Burn at   275.0 km: theta1 =  0.19 deg, dv1 =  360.6 m/s
Burn at 35786.0 km: theta2 = 17.60 deg, dv2 = 1619.0 m/s
dv = 1979.7 m/s
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

Offline Danderman

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So PSLV flew at an azimuth of 102.9 degrees from the launch site, resulting in a 17 degree inclination orbit, since the launch site is at 13 degrees.

Why didnít PSLV fly due East at 90 degrees to enter into a 13 degree orbit? That would have allowed more payload.

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So PSLV flew at an azimuth of 102.9 degrees from the launch site, resulting in a 17 degree inclination orbit, since the launch site is at 13 degrees.

Why didnít PSLV fly due East at 90 degrees to enter into a 13 degree orbit? That would have allowed more payload.

I believe its to avoid flying over populated areas that are directly east of the launch site. Could also be due to ground station access along the flight path.

https://spaceflight101.com/gslv-gsat-6a/flight-profile/
« Last Edit: 12/18/2020 05:45 am by Steven Pietrobon »
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

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So PSLV flew at an azimuth of 102.9 degrees from the launch site, resulting in a 17 degree inclination orbit, since the launch site is at 13 degrees.

Why didnít PSLV fly due East at 90 degrees to enter into a 13 degree orbit? That would have allowed more payload.

I believe its to avoid flying over populated areas that are directly east of the launch site. Could also be due to ground station access along the flight path.

https://spaceflight101.com/gslv-gsat-6a/flight-profile/
« Last Edit: 12/20/2020 05:43 am by Danderman »

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So PSLV flew at an azimuth of 102.9 degrees from the launch site, resulting in a 17 degree inclination orbit, since the launch site is at 13 degrees.

Why didnít PSLV fly due East at 90 degrees to enter into a 13 degree orbit? That would have allowed more payload.

My theory:
If the PSLV started to the east, the upper stage would have to ignite twice.
One ignition to achieve a LEO, then a ballistic phase and then a second ignition over the equator.
For a proper GTO perigee/apogee must be above the equator. (incorrect at Ariane VA241)
The second ignition would then be out of sight of the Indian ground stations.
The launch to the southeast shortens the way to the equator.

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