Author Topic: Soyuz-2.1b/Fregat-M - EgyptSat-A - Baikonur - (16:47 UTC) February 21, 2019  (Read 14628 times)

Offline Alter Sachse

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From twitter

twitter.com/roscosmos/status/1098653021481984001

Launch photo.
This is not a current photo.
Wrong fairing.

Offline ZachF

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RIA Novosti confirms the story :

https://ria.ru/20190221/1551211378.html

Problem with 3rd stage. Fregat compensates it. Mission success in the end.

Luckily for the Soyuz this payload was pretty undersized.
artist, so take opinions expressed above with a well-rendered grain of salt...
https://www.instagram.com/artzf/

Online russianhalo117

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RIA Novosti confirms the story :

https://ria.ru/20190221/1551211378.html

Problem with 3rd stage. Fregat compensates it. Mission success in the end.

Luckily for the Soyuz this payload was pretty undersized.
SSO. Fregat-M was purely for insertion into Direct SSO.
Destiny described here: http://russianspaceweb.com/egyptsat-a.html
Sat short name is ES-2A. Sat is slightly heavier than previous ES-2

Offline jcm

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RIA Novosti confirms the story :

https://ria.ru/20190221/1551211378.html

Problem with 3rd stage. Fregat compensates it. Mission success in the end.

Luckily for the Soyuz this payload was pretty undersized.
SSO. Fregat-M was purely for insertion into Direct SSO.
Destiny described here: http://russianspaceweb.com/egyptsat-a.html
Sat short name is ES-2A. Sat is slightly heavier than previous ES-2

So, two Fregat burns? First to raise transfer orbit perigee (even for nominal case, and this time extended...
would be nice to know the originally planned Blok-I perigee, can probably model it given the Arctic impact point)
and second to circularize. Plus a third burn for Fregat deorbit.
Also, at one point it was suggested there would be secondary payloads, but it looks like that's definitely not the case?
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Jonathan McDowell
http://planet4589.org

Offline max_schmurz

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RIA Novosti confirms the story :

https://ria.ru/20190221/1551211378.html

Problem with 3rd stage. Fregat compensates it. Mission success in the end.

Luckily for the Soyuz this payload was pretty undersized.
SSO. Fregat-M was purely for insertion into Direct SSO.
Destiny described here: http://russianspaceweb.com/egyptsat-a.html
Sat short name is ES-2A. Sat is slightly heavier than previous ES-2

So, two Fregat burns? First to raise transfer orbit perigee (even for nominal case, and this time extended...
would be nice to know the originally planned Blok-I perigee, can probably model it given the Arctic impact point)
and second to circularize. Plus a third burn for Fregat deorbit.
Also, at one point it was suggested there would be secondary payloads, but it looks like that's definitely not the case?
Too risky to send any secondary payloads on almost 'rotten' rocket

Offline zandr

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https://www.laspace.ru/press/news/launches/20190221_Fregat_73th_launch/
Google translate:
Quote
...The separation of the spacecraft from the upper stage took place normally at 21:04 Moscow time after two inclusions of the marching propulsion system in strict accordance with the flight sequence. The Egyptsat-A spacecraft is launched into the target orbit…

Offline zandr

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https://ria.ru/20190223/1551277960.html
Google translate:
Quote
MOSCOW, Feb 23 - RIA News. The cause of the emergency situation when the Egyptian satellite Egyptsat-A was launched, which led to the premature shutdown of the third stage engine of the Soyuz-2.1b launch vehicle, was the human factor, due to incorrectly tuned sensors in the rocket, the fuel was prematurely out of power, the source told the rocket - space industry.
Quote
"It was a human factor. Experts mistakenly set up the sensors before launching at the cosmodrome. As a result, an oxidizer ended prematurely in flight at the third stage of the rocket, and the engine shut down before the scheduled time," said the agency interlocutor.

Offline Nicolas PILLET

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So, two Fregat burns? First to raise transfer orbit perigee (even for nominal case, and this time extended...
would be nice to know the originally planned Blok-I perigee, can probably model it given the Arctic impact point)
and second to circularize. Plus a third burn for Fregat deorbit.

Block I was not intended to reach orbit. It flew as scheduled on suborbital trajectory. First Fregat burn was to insert in orbit, and second burn was to raise perigee.
Nicolas PILLET
Kosmonavtika : The French site on Russian Space

Offline jcm

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So, two Fregat burns? First to raise transfer orbit perigee (even for nominal case, and this time extended...
would be nice to know the originally planned Blok-I perigee, can probably model it given the Arctic impact point)
and second to circularize. Plus a third burn for Fregat deorbit.

Block I was not intended to reach orbit. It flew as scheduled on suborbital trajectory. First Fregat burn was to insert in orbit, and second burn was to raise perigee.

Yes, I realize that of coruse. From an orbital mechanics point of view though,  suborbital objects still have an orbital perigee value even if it never reaching it.
To match the intended impact zone between Svalbard and Greenland, an orbit of about
-1300 x 200 km seems to fit. A 30 m/s underspeed would give the reported 60 km shortfall in perigee to -1360 x 200 km, suggesting an impact of stage 3 only mildly downrange from the target, on the NE coast of Greenland
around 80N.

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Jonathan McDowell
http://planet4589.org

Offline zandr

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https://ria.ru/20190225/1551317322.html
Google translate:
Quote
MOSCOW, February 25 - RIA News. The premature shutdown of the third-stage Soyuz-2.1b rocket when the Egyptian satellite EgyptSat-A was launched on February 21 was due to the fact that an oxidizer was not added to the Baikonur cosmodrome, the source in the rocket and space industry told Monday.
“Before starting, the oxidizer filling level sensors were set up incorrectly. As a result, less oxidizer was loaded into the third-stage tank of the Soyuz-2.1b rocket. Accordingly, the oxidizer ended prematurely and the engine turned off before the allotted time ...”

Online russianhalo117

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https://ria.ru/20190225/1551317322.html
Google translate:
Quote
MOSCOW, February 25 - RIA News. The premature shutdown of the third-stage Soyuz-2.1b rocket when the Egyptian satellite EgyptSat-A was launched on February 21 was due to the fact that an oxidizer was not added to the Baikonur cosmodrome, the source in the rocket and space industry told Monday.
“Before starting, the oxidizer filling level sensors were set up incorrectly. As a result, less oxidizer was loaded into the third-stage tank of the Soyuz-2.1b rocket. Accordingly, the oxidizer ended prematurely and the engine turned off before the allotted time ...”
So TsENKI is at fault then.

Offline asmi

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-1300 x 200 km seems to fit. A 30 m/s underspeed would give the reported 60 km shortfall in perigee to -1360 x 200 km, suggesting an impact of stage 3 only mildly downrange from the target, on the NE coast of Greenland
around 80N.
Since Block I's acceleration at the end of the burn is about 3g, 30 m/s shortfall would imply shutting down about 1 second earlier than it should've.

Online russianhalo117

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Launcher serial numbers found so far:
February 21 (16:47) - EgyptSat-A - Soyuz-2.1b/Fregat-M (76031216/??)

Fregat-M serial number anyone??

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