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#2980
by
Warren Platts
on 23 Sep, 2013 22:05
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Does anyone know what the temperature of the water was prior to a water dump?? Do they heat it up to sterilize it?
I know the pressure in the storage tank was ~31 psi, and that the exit velocity was 50 ft/sec (15.24 m/s). This seemingly indicates that the (Ostwald) solubility coefficient for dissolved air was only ~0.02, which for that pressure indicates a temperature pretty close to boiling!
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#2981
by
Warren Platts
on 25 Sep, 2013 21:15
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OK, I did a little more research. It turns out the ISS wastewater is heated up to 120 C. If the wastewater were heated up to 200 F by the time it was ejected, the solubility coefficient would be 0.0135, yielding a theoretical exit velocity of 9.25 m/s, which compares well with the observed 9.45 m/s.
Meanwhile, the Shuttle wastewater tank was pressurized by N2, but there is no mention of heating, so presumably it's kept at about room temperature. Thus, the Ostwald solubility coefficient would be about 0.017, yielding a theoretical exit velocity of 15.25 m/s which also agrees very well with the observed velocity.
The formula used is
1/2 v
2 = λ * P
0 / ρ
0 * (ln(P
0/P
out) - 1 + P
out/P
0)
http://www-personal.umich.edu/~youxue/publications/Zhang2000JVGR.pdf
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#2982
by
mjp25
on 27 Sep, 2013 01:52
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I know that with the relatively spacious quarters of the Space Shuttle compared to Soyuz it wasn't necessary, but was the shuttle capable of a fast rendezvous like Soyuz and Progress now use? As I understand it, the reason it has only been used recently was due to the ability of the booster to loft Soyuz into a precise orbit and ISS's ability to precisely control its orbit. So was the shuttle capable of this precision?
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#2983
by
psloss
on 27 Sep, 2013 10:47
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#2984
by
Specifically-Impulsive
on 27 Sep, 2013 23:08
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Meanwhile, the Shuttle wastewater tank was pressurized by N2, but there is no mention of heating, so presumably it's kept at about room temperature. Thus, the Ostwald solubility coefficient would be about 0.017, yielding a theoretical exit velocity of 15.25 m/s which also agrees very well with the observed velocity.
http://www-personal.umich.edu/~youxue/publications/Zhang2000JVGR.pdf
The shuttle water tanks were in the lower equipment bay, in the pressurized crew module. To a first approximation, they were the same temperature as the middeck, so room temperature is a good bet. No heaters on the tanks.
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#2985
by
Jim
on 28 Sep, 2013 11:29
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The shuttle water tanks were in the lower equipment bay, in the pressurized crew module. To a first approximation, they were the same temperature as the middeck, so room temperature is a good bet. No heaters on the tanks.
There were heaters in the nozzles.
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#2986
by
Warren Platts
on 29 Sep, 2013 11:54
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Do you know if they were at 120 C like the ISS nozzles?
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#2987
by
DaveS
on 02 Oct, 2013 11:27
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Does anyone know the spacing between the Ku band DEA and the lower-most starboard PLBD bulkhead latch roller? Also, does anyone have the dimensions of the actual DEA and the white deployment structure the entire Ku band DA sits on?
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#2988
by
Specifically-Impulsive
on 03 Oct, 2013 00:02
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Do you know if they were at 120 C like the ISS nozzles?
IIRC, there weren't thermostats on the nozzle heaters, they reached a steady state temp based on the water flow rate. After flow was terminated the temperature was allowed to rise and bake out the nozzles for a while, then power was removed from the heaters.
The lines between the tanks, nozzles, FES, etc, had thermostatically controlled heaters on them.
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#2989
by
DaveS
on 03 Oct, 2013 20:21
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Q on the payload bay doors: How thick are the ribs/longerons/intercostals of the PLBD framework? I have looked just about everywhere but have come up with nothing on the subject.
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#2990
by
Poseidonious
on 04 Oct, 2013 09:47
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Sorry in advance for my bad English. I would like to ask if there is a specific point through which space shuttles in orbit choose for their re entry in the atmosphere.
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#2991
by
Jim
on 04 Oct, 2013 11:25
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Sorry in advance for my bad English. I would like to ask if there is a specific point through which space shuttles in orbit choose for their re entry in the atmosphere.
Do you mean the same point in space (a location) on every mission? Or the same parameters (orbital height etc)?
The shuttle has deorbited from many different orbits (different altitudes, inclinations, etc) to three different landing sites (Kennedy Space Center, Edwards AFB, and White Sands) with different payload weights, so the where the shuttle starts to re enter varies. However, no matter what the orbital height is at deorbit burn, the shuttle will coast awhile until it reaches 400,000 feet, which is the entry interface (the start of re entry)
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#2992
by
Poseidonious
on 06 Oct, 2013 03:29
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Is there a way to calculate from which location above Earth will be initiated a re entry procedure in order for a shuttle to land in South Mexico? And while the re entry is in progress above which parts of our planet will the shuttle fly?
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#2993
by
Jim
on 06 Oct, 2013 14:17
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Is there a way to calculate from which location above Earth will be initiated a re entry procedure in order for a shuttle to land in South Mexico? And while the re entry is in progress above which parts of our planet will the shuttle fly?
1. It would be between the locations for the initiations for Florida and California landings ;-)
2. It would be similar to the orbital path but with some maneuvering.
This is outside the capability of a layman to figure out. One might be able to use some simulator games such as Orbiter and Space Shuttle Simulator to get an idea.
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#2994
by
Poseidonious
on 06 Oct, 2013 18:01
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I read somewhere that to get to Canaveral a shuttle in orbit must abandon orbit and fall in the atmosphere when it is above the Indian Ocean.
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#2995
by
DaveS
on 06 Oct, 2013 19:23
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I read somewhere that to get to Canaveral a shuttle in orbit must abandon orbit and fall in the atmosphere when it is above the Indian Ocean.
It depends on the actual orbit. For example, the de-orbit burn for STS-107 occurred over Australia. The goal is always the same: put the Entry Interface position approximately 4400 nautical miles from the landing site which in this case was KSC. If I remember correctly, the entry angle targeted was 1.5°. EI always occurred over the Pacific, never the Indian Ocean.
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#2996
by
Ronpur50
on 07 Oct, 2013 06:09
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I have been trying to search for information on a proposal made by an aerospace company in the late 80's or early 90's for a lunar architecture that was flown to orbit on the shuttles and then launched to the moon. I first read of it in Aviation Week and actually wrote the company and received a wonderful book detailing their plans. I can not even remember the company (possibly Lockheed?) and I have searched everywhere for the book. Any ideas on whose program it was and if there is any info around on it?
Edit: Never mind, found it...I was thinking of Early Lunar Access from General Dynamics.
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#2997
by
Poseidonious
on 07 Oct, 2013 19:13
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I read somewhere that to get to Canaveral a shuttle in orbit must abandon orbit and fall in the atmosphere when it is above the Indian Ocean.
It depends on the actual orbit. For example, the de-orbit burn for STS-107 occurred over Australia. The goal is always the same: put the Entry Interface position approximately 4400 nautical miles from the landing site which in this case was KSC. If I remember correctly, the entry angle targeted was 1.5°. EI always occurred over the Pacific, never the Indian Ocean.
I calculated that if a shuttle wants to land on Yacatan it has to proceed to de-orbit burn over Mauretania in Africa. If it is correct how much time will it take to reach Mexico?
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#2998
by
DaveS
on 07 Oct, 2013 20:03
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I read somewhere that to get to Canaveral a shuttle in orbit must abandon orbit and fall in the atmosphere when it is above the Indian Ocean.
It depends on the actual orbit. For example, the de-orbit burn for STS-107 occurred over Australia. The goal is always the same: put the Entry Interface position approximately 4400 nautical miles from the landing site which in this case was KSC. If I remember correctly, the entry angle targeted was 1.5°. EI always occurred over the Pacific, never the Indian Ocean.
I calculated that if a shuttle wants to land on Yacatan it has to proceed to de-orbit burn over Mauretania in Africa. If it is correct how much time will it take to reach Mexico?
Time from de-orbit burn to wheelstop is approximately 1 hour. It's slightly longer if it was a HST service mission due to the higher orbital altitude.
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#2999
by
TJL
on 13 Oct, 2013 15:40
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I know that the Spacelab (LM 1) module is on dispaly at the Udvar Hazy Centre in Virginia alongside Space Shuttle Discovery.
Where is the Spacelab LM 2 module stored?
Thank you.