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#40
by
Raj2014
on 10 Jan, 2018 19:43
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Anyone have or know where I can find the latest images of the ESM? I have looked myself but the dates are very old. I want to compare to an image from a ESA video showing the Orion CM and ESM together and there is a dish attached to the back of the ESM.
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#41
by
brickmack
on 11 Jan, 2018 14:39
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#42
by
Raj2014
on 12 Jan, 2018 00:07
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#43
by
brickmack
on 12 Jan, 2018 16:45
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Looks like that video is just using the Orion CEV service module with ATV-style solar wings instead of the UltraFlex panels from CEV. Note the larger Orion Main Engine and the 4 pods jutting out from the sides for the auxiliary thrusters, among other issues. CEV did plan to use such a dish.
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#44
by
whitelancer64
on 23 Apr, 2018 21:19
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Do we have any reliable statement or estimate for the per-unit cost / cost per build of the Orion spacecraft?
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#45
by
theinternetftw
on 23 Apr, 2018 22:49
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Do we have any reliable statement or estimate for the per-unit cost / cost per build of the Orion spacecraft?
According to
this presentation from Edgar Zapata (page 10, pdf warning) it's $980M per-unit production costs if you build one a year, $654M if you build two a year, and $1,672M if you build less than one a year.
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#46
by
whitelancer64
on 23 Apr, 2018 23:29
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Do we have any reliable statement or estimate for the per-unit cost / cost per build of the Orion spacecraft?
According to this presentation from Edgar Zapata (page 10, pdf warning) it's $980M per-unit production costs if you build one a year, $654M if you build two a year, and $1,672M if you build less than one a year.
That's fantastic, thank you. Interesting to see the Dragon v2 and Starliner cost estimates there too
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#47
by
mobile1
on 24 Jun, 2018 13:52
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NASA built the Orion capsule. For what will it be used?
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#48
by
zhangmdev
on 24 Jun, 2018 14:06
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#49
by
Hog
on 25 Jun, 2018 16:18
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Orion also was on orbit during its December 2014 flight test (EFT-1) that lasted for about 4 hours 24 minutes.
It is planned to be used atop NASA's heavy lifter, the Space Launch System.
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#50
by
EnigmaSCADA
on 25 Jun, 2018 23:15
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<never mind, I don't want to spoil the ending for others>
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#51
by
whitelancer64
on 06 Dec, 2018 15:12
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How much hydrazine does the Orion carry for its thrusters?
I'm wondering about the Orion capsule itself, NOT in the service module.
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#52
by
whitelancer64
on 07 Dec, 2018 14:53
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Orion has 12 thrusters for use in-space and during reentry. From what I've read, it's dual-redundant with two separate fuel lines. However, none of the documentation says how large the fuel tanks within the Orion capsule are, or how much hydrazine Orion is actually carrying.
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#53
by
whitelancer64
on 10 Jul, 2019 22:15
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If going to the lunar surface is now once again an objective, Orion is underfueled and that capability will have to be made up by a larger lander or on-orbit fueling.
Not true. It has plenty of propellant to get into lunar orbit and back. If a lander is involved, then the lander should provide its own delta V. Apollo conop is not the only nor correct one.
How close of an orbit can Orion theoretically get? Like, what's the lowest circular orbit around the Moon it could achieve? While still having enough fuel to return to Earth, of course.
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#54
by
Proponent
on 10 Jul, 2019 22:29
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We had a discussion about this a while ago. I believe a number around 500 km was mentioned.
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#55
by
whitelancer64
on 10 Jul, 2019 23:12
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We had a discussion about this a while ago. I believe a number around 500 km was mentioned.
Wow, that's a bit lower than I thought was possible.
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#56
by
ncb1397
on 11 Jul, 2019 00:34
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We had a discussion about this a while ago. I believe a number around 500 km was mentioned.
Wow, that's a bit lower than I thought was possible.
Can't seem to achieve a circular 500 km orbit with only 650 m/s of dV. I think it is more like 2000 km or about 1 lunar radius in altitude. Going from 500 km to 100 km lunar orbit is only about 80 m/s. Orion's deficit is more than that (more like 250 m/s).
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#57
by
whitelancer64
on 11 Jul, 2019 15:44
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We had a discussion about this a while ago. I believe a number around 500 km was mentioned.
Wow, that's a bit lower than I thought was possible.
Can't seem to achieve a circular 500 km orbit with only 650 m/s of dV. I think it is more like 2000 km or about 1 lunar radius in altitude. Going from 500 km to 100 km lunar orbit is only about 80 m/s. Orion's deficit is more than that (more like 250 m/s).
That's still pretty close! I know that early on (years ago) they were looking at 10,000 km circular lunar orbits as the "reference" mission for Orion, so I'm impressed.