A question concerning Soyuz launches and a listing of event sequences from today's 'Live Coverage' of TMA-17...Regarding this portion: "L- 20 sec: Ignition of 1st, 2nd stage engines at intermediate thrust level" 1st and 2nd stage is referring to the four 'boosters' as 1st and the inner 'core' as 2nd stage, right? I see 'stages' named differently at different sites and am just clarifying terms used. ~Same as saying Stage 0 and Stage 1 as well? And the inner/centrally-located engine, which stays at ~'intermediate power' while boosters are lit (right?) becomes Stage Two (second Stage, per se) once the lateral boosters (and SAS 'abort things') are done/dropped and that inner engine *then* goes ~full-power, right?Basically correct? I searched around a bit and did not see anything specific on this, fwiw Alex
Reading the Soyuz LV Users Guide for Kourou, I noticed that the Fregat orbital transponder operates at 2860 Mhz, whereas the Ariane V transmits at 2200 MHz. Since I doubt that the existing Ariane V ground stations can adapt to 2860 Mhz, does this mean that Fregat's orbit determination system will be modified to transmit at 2200 Mhz? Such a change may have significant ramifications for the future, since it would allow European, commercial and Russian orbit determination systems to be unified.
Quote from: Danderman on 12/25/2009 06:32 pmReading the Soyuz LV Users Guide for Kourou, I noticed that the Fregat orbital transponder operates at 2860 Mhz, whereas the Ariane V transmits at 2200 MHz. Since I doubt that the existing Ariane V ground stations can adapt to 2860 Mhz, does this mean that Fregat's orbit determination system will be modified to transmit at 2200 Mhz? Such a change may have significant ramifications for the future, since it would allow European, commercial and Russian orbit determination systems to be unified.Ground stations are very adaptable. The same stations support Atlas, Delta II, Pegasus, Ariane, etc.
All of the western LVs listed above have transponders operating at 2200 Mhz, whereas Soyuz Fregat operates at 2860 Mhz, so I am not sure if the adaptation by a ground station is that trivial or even possible, compared to adapting the Fregat transponder. I'm not a radio guy, so I don't know which is the easiest approach.
The various launch vehicles use various methods to downlink data, analog, digital, PCM, etc. They are very adaptable.The same ground stations also receive spacecraft downlinks
Someone from among the thermal mode specialists came to the conclusionthat the hot jets of gas from the DPO nozzles would blow on the solar arraypanels. They reported to Feoktistov. Without giving it much thought, heproposed that they turn them on their support bracket 180 degrees about theiraxis, so as not to undertake a complex modification of the spacecraft and lookfor other sites to install the engines.
Why are they still flying the standard Soyuz TMA (20 and 21) after validating the new version, and once again (Soyuz TMA 22) after Soyuz TMA 02M?
Tri-module separation occurred at 6:57am. 16 sec after the separation command, software pitched the PAO instrumentation/propulsion module in the rear to a specific angle (-78.5 deg from reference axis) which, if the PAO would have remained connected to the SA/Descent Module, would have resulted in enough heating on the connecting truss to melt it, thus ensuring separation.
Found in ISS Status Report of 18th march :QuoteTri-module separation occurred at 6:57am. 16 sec after the separation command, software pitched the PAO instrumentation/propulsion module in the rear to a specific angle (-78.5 deg from reference axis) which, if the PAO would have remained connected to the SA/Descent Module, would have resulted in enough heating on the connecting truss to melt it, thus ensuring separation.Is it a new procedure, or an old one I did't know about ??
What was the complete official designation of "Soyouz TM"?
As a result of more stringent parameters of loading the engine using synthetic oil, engine 11D511PF should have greater margin of stability with respect to the HF oscillations.From the experience of many years of mass production of engines was detected sensitivity stability margin of the working process in the cells on the mode of the main stage to violations in the manufacture of centrifugal two-component jets (as a rule - to violations in the manufacture of tangential holes in the jets) (see also Engines 14D22, 14D21 ). For this reason, a series of chambers as a result of cold prolivok Water Samples of those who have hydraulic characteristics of the mixing head is in a range. Cameras are selected in such a way mixing heads used in the engine 11D511PF (RD-117PF).By 1996, production of engines for the rocket Soyuz at the Plant Frunze in Samara have decreased significantly, making it impossible to select engines, capable of working on a synthetic fuel.To continue the operation of the rocket Soyuz-U2 "it was necessary to either increase the level of manufacturing technology, or to conduct additional studies to clarify the nature of high-frequency vibrations and make appropriate modifications to the mixing head.
Quote from: Nicolas PILLET on 05/11/2010 09:14 pmWhat was the complete official designation of "Soyouz TM"?11F732A51.
A Soyuz parachute question I have been asked and have no idea about: are the main and reserve/backup parachutes stored in one compartment (with one hatch opening) or two? I have done some searching but can't come up with a clear answer or diagram! The screenshot below from "Soyuz: A Universal Spacecraft" shows only one hatch, but it looks like there is another on the side.
On pictures like these, you can see clearly where is the main parachute compartiment (open) and where is the backup one (closed).http://www.kosmonavtika.com/vaisseaux/soyouz/visite/reels/30/30.html
Quote from: Suzy on 07/07/2012 03:28 amA Soyuz parachute question I have been asked and have no idea about: are the main and reserve/backup parachutes stored in one compartment (with one hatch opening) or two? I have done some searching but can't come up with a clear answer or diagram! The screenshot below from "Soyuz: A Universal Spacecraft" shows only one hatch, but it looks like there is another on the side. Main and backup parachutes are stored in two separate compartments. Each compartment has its own hatch. The left parachute is the main, the right one is the backup.
Quote from: Zero-G on 07/07/2012 12:15 pmQuote from: Suzy on 07/07/2012 03:28 amA Soyuz parachute question I have been asked and have no idea about: are the main and reserve/backup parachutes stored in one compartment (with one hatch opening) or two? I have done some searching but can't come up with a clear answer or diagram! The screenshot below from "Soyuz: A Universal Spacecraft" shows only one hatch, but it looks like there is another on the side. Main and backup parachutes are stored in two separate compartments. Each compartment has its own hatch. The left parachute is the main, the right one is the backup.The original question relates to this image (and plenty of others like it).http://scamme.org/info/soyuz-tma19/pict17.jpgThe main 'chute (and it's drogue and braking 'chute have obviously been deployed, and the cover of the backup 'chute is in place, so what is the apparent packed 'chute still in the parachute compartment?
What is the purpose and function of the blue stick with the handgrip on top, which is installed on the "Kazbek" seats in the Soyuz descent module? (see first two photos)There is one of these blue sticks on every seat, but they don't seem to be linked together. (see last photo I made of one of the Soyuz sims at TsPK)
PTT button
ZG, While youre asking, theres another crucial accessory control (rarely seen) to be aware of: The Manual Descent Controller. (If you know of it just ignore this)http://www.asc-csa.gc.ca/eng/vehicles/soyuz/descent.aspCredit: Originally posted by Chris Hadfield
I've just realized that EVERY Soyuz spaceships make a deorbit burn with Delta-V = 115,2m/s
Quote from: Nicolas PILLET on 03/04/2014 06:59 pmI've just realized that EVERY Soyuz spaceships make a deorbit burn with Delta-V = 115,2m/sSoyuz TMA-09M - 128 m/sSoyuz TMA-08M - 128 m/sSoyuz TMA-07M - 128 m/sSoyuz TMA-06M - 128 m/sSoyuz TMA-05M - 128 m/sSoyuz TMA-04M - 115 m/sSoyuz TMA-03M - 115 m/s
Anyone have diagrams of the TMA flight instrument panel? I'm curious on how much the real thing matches the movie Gravity.
Remind me if this question was answered already:Why do nearly all of the ISS Soyuz launches take place at night? I mean, compared to the Space Shuttle, the lighting conditions for all logged flights are the opposite; the Shuttle launched more during the day (99 as opposed to 36 night launches).
And now for something different:this is a short animation showing the nominal maneuver of the upper stage after separation of the Progress payload, as developed by the designers of the Soyuz rocket. The movement is generated by some sort of gas system.
Which is the pipe? Are those things wrapped in silver plastic telemetry antennas?
When the Soyuz rocket is mated to the Volga upper stage, the connecting ring between them is called SZB "standard payload section" by RussianSpaceWeb:http://www.russianspaceweb.com/volga.htmlA similar item on Soyuz is called the "launch vehicle transfer compartment" when integrated with Progress or Soyuz spacecraft:http://inspaceforum.ru/en/post/roscosmos-transfer-compartment-was-docked-with-sc-soyuz-tma-19mAre the different terms for the same type of hardware simply a function of two different companies doing the processing (TsSKB vs RSC Energia) or are these adapter rings really that different?
Сборочно-защитный блок (СЗБ) предназначен для обеспечения защиты КА от воздействия внешней атмосферы и тепловых потоков и для сопряжения КА с РН. В состав СЗБ входят головной обтекатель (ГО) и переходной отсек (ПхО). Для запусков КА с помощью РН «Союз-2» в составе СЗБ планируется использование штатного ГО 11С529, массой 1050 кг и штатного ПхО массой 220 кг.Вместе с тем, в случае выведения КА с помощью РН «Союз-2» (этапа разработки «1б») в составе СЗБ может использоваться унифицированный ГО 14С74 массой 2100 кг и ПхО массой 350 кг.
борочно-защитный блок (СЗБ) в составе головного обтекателя (ГО) и переходного отсека, (ГО изготавливается по разделу II ФКПР-2015). Для выведения КА «Ресурс-П» № 2 используется сборочно-защитный блок 196КС, включающий головной обтекатель (ГО) 81КС диаметром 4,11м, c необходимой доработкой;
Quote Сборочно-защитный блок (СЗБ) предназначен для обеспечения защиты КА от воздействия внешней атмосферы и тепловых потоков и для сопряжения КА с РН. В состав СЗБ входят головной обтекатель (ГО) и переходной отсек (ПхО). Для запусков КА с помощью РН «Союз-2» в составе СЗБ планируется использование штатного ГО 11С529, массой 1050 кг и штатного ПхО массой 220 кг. Вместе с тем, в случае выведения КА с помощью РН «Союз-2» (этапа разработки «1б») в составе СЗБ может использоваться унифицированный ГО 14С74 массой 2100 кг и ПхО массой 350 кг.
Сборочно-защитный блок (СЗБ) предназначен для обеспечения защиты КА от воздействия внешней атмосферы и тепловых потоков и для сопряжения КА с РН. В состав СЗБ входят головной обтекатель (ГО) и переходной отсек (ПхО). Для запусков КА с помощью РН «Союз-2» в составе СЗБ планируется использование штатного ГО 11С529, массой 1050 кг и штатного ПхО массой 220 кг. Вместе с тем, в случае выведения КА с помощью РН «Союз-2» (этапа разработки «1б») в составе СЗБ может использоваться унифицированный ГО 14С74 массой 2100 кг и ПхО массой 350 кг.
The whole interstage (a/k/a transfer compartment) issue is new to me; apparently, the interstage is the responsibility of either the payload provider or the upper stage provider. So, RSC Energia seems to provide the transfer compartment for Progress and Soyuz, whereas Lavochkin handles the interstage for launches using Fregat, and TsSKB for launches using their payloads.It would be interesting to see the index numbers for the interstages, and also if there are any other providers besides those mentioned above.
Now to launch Resurs-P № 2 on a Soyuz, it was decided to use the larger 81КС fairing. As that launch did not require a Fregat, which would have come with a PKhO, RKTs-Progress supplied one instead. It was referred to as 196КС.
It is possible 196КС is a complete SZB too; it includes an 81КС GO.http://novosti-kosmonavtiki.ru/forum/messages/forum14/topic12755/message1316921/#message1316921I think 81КС is just the GO.
По Договору застраховано следующее имущество: Головной обтекатель 81 КС (ГО 48/134) и Переходный отсек 196КС (ПхО 48/134) для КА "Ресурс-П" №2. (далее по тексту ГО 48/134 и ПхО 48/134 -"Груз") .
Not the best thread for this, but I didn't want to necrobump. How can the baikonour range support launches by two different vehicle types on consecutive days?