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#1360
by
Jim
on 04 Oct, 2010 16:34
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Is there anybody knows how long it takes to traslate the payload from the changeout room to payload bay?
Minutes
um, just curious, how do you figure minutes? If you're talking installing into the orbiter from the PCR, quite a bit more than minutes
Not installation but the actual translation (and not the final few inches).
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#1361
by
padrat
on 04 Oct, 2010 16:44
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Gotcha, that's what I figured you meant.
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#1362
by
DaveS
on 04 Oct, 2010 17:12
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The bodyflap positioning during entry is a function of mach number. The bodyflap position is used primarily to keep the elevons within a given range of operation and prevent "saturation".
THat's what I thought about it, but does it aid in the AoA maintenance? The reason for these questions is some disagreement between me and another developer of the SpaceShuttleUltra project.
I have always thought that the bodyflap assisted in AoA maintenance as the elevons are not strong enough to maintain it on their own.
It would be great if you guys could help us settle this issue once and for all.
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#1363
by
David413
on 04 Oct, 2010 21:44
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I've got a complete listing of the various inputs to the entry DAP that includes the specifics for each individual input (body flap, pitch jets, etc.). I'll check it again, but as near as I can tell, the elevons are sufficient for AoA control, provided the body flap is periodically adjusted to ensure the elevons have full authority. The body flap is fixed until mach 16 during entry, that much I remember.
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#1364
by
DaveS
on 04 Oct, 2010 22:26
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I've got a complete listing of the various inputs to the entry DAP that includes the specifics for each individual input (body flap, pitch jets, etc.). I'll check it again, but as near as I can tell, the elevons are sufficient for AoA control, provided the body flap is periodically adjusted to ensure the elevons have full authority. The body flap is fixed until mach 16 during entry, that much I remember.
Thanks. BTW, what kind of aerosurface data do you use in the Shuttle Fleet? We actually had strengthen the elevons to be able to maintain the 40° AoA which has lead to the orbiter being far to responsive to RHC control inputs. Maybe you would like to help us with this so we get it right?
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#1365
by
NASAaddict
on 08 Oct, 2010 06:33
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Hey guys, I was wondering if anybody could tell me what all these feed lines, pipes, etc. are on the SSME, and a brief description please? Listed below are 3 different angles from an SSME used on the previous mission.
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#1366
by
MP99
on 08 Oct, 2010 12:23
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Looking at images 2010-1918 & -1920, the SSME looks to be cantilievered from the nozzle. That came as a surprise to me.
Why is it handled like this?
I would have guessed it would be handled more like image 2009-6813.
Thanks, Martin
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#1367
by
zeke01
on 08 Oct, 2010 12:40
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Why is it handled like this?
How else would you get these engines installed in the shuttle aft compartment? It's a very tight fit, I understand.
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#1368
by
Jim
on 08 Oct, 2010 12:52
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Looking at images 2010-1918 & -1920, the SSME looks to be cantilievered from the nozzle. That came as a surprise to me.
Why is it handled like this?
I would have guessed it would be handled more like image 2009-6813.
Thanks, Martin
Most engines are installed by handling the nozzle. It is no big deal since the nozzle transmits the thrust through the combustion chamber into the gimbal.
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#1369
by
MP99
on 08 Oct, 2010 20:55
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Many thanks to both of you.
cheers, Martin
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#1370
by
Longhorn John
on 09 Oct, 2010 02:04
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#1371
by
NASAaddict
on 09 Oct, 2010 16:25
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Yes, I joined a few days ago. I will check those links.
Thanks,
Frank
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#1372
by
NASAaddict
on 10 Oct, 2010 00:25
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The twin Solid Rocket Boosters have a decibel level of 180 (right? wrong?). Can someone tell me how that is calculated please?
Air pressure and/or temperature +.....?
Thanks,
Frank
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#1373
by
Jim
on 10 Oct, 2010 01:18
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The twin Solid Rocket Boosters have a decibel level of 180 (right? wrong?). Can someone tell me how that is calculated please?
measured
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#1374
by
NASAaddict
on 10 Oct, 2010 02:12
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Ok... How is the 180 db level of the SRB's thrust measured?
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#1375
by
kch
on 10 Oct, 2010 03:34
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#1376
by
MP99
on 10 Oct, 2010 20:54
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My questions would be "180dB at what distance"?
I don't see how this could be "180dB at 1M", because 1M from the acoustic centre would be within the motor's plume and possibly within the nozzle itself, ie very much "near field", the acoustic equivalent of
http://en.wikipedia.org/wiki/Near_and_far_field.
Perhaps loudness is measured in the far field, then an "equivalent loudness at a notional 1M" is calcuated as 180dB?
cheers, Martin
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#1377
by
NASAaddict
on 11 Oct, 2010 06:25
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I was reading posts in this section I believe Friday or Saturday and someone recommended 2 rocket propulsion/engine books to someone else, but I don't remember the name of the 2nd book. The first book was Rocket Propulsion Elements by George P. Sutton. The other book had 3 authors.
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#1378
by
Danny Dot
on 17 Oct, 2010 07:59
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I've got a complete listing of the various inputs to the entry DAP that includes the specifics for each individual input (body flap, pitch jets, etc.). I'll check it again, but as near as I can tell, the elevons are sufficient for AoA control, provided the body flap is periodically adjusted to ensure the elevons have full authority. The body flap is fixed until mach 16 during entry, that much I remember.
IIRC the body flap is strictly a trim device and only drives to put the elevons back on schedule. And that schedule is a function of center of gravity location.
On STS-1 the estimated pitch moment was so far off the body flap almost saturated. The error was do to the strong shock wave brakes oxygen molecules into two single atoms. This changes the nature of the gas (air) enough to cause the error.
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#1379
by
Fequalsma
on 19 Oct, 2010 03:01
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Does anyone have close-up photos of the payload bay door strongback
and torque tube attachment points and hardware? If so, would you
please post them?
Thanks!
F=ma
