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So much hard work by so many people to achieve this fantastic milestone. Thank you to everyone who contributes to and supports NSF on any platform.

It’s the amazing support that provides the income for NSF to do all that it does.

Long may it continue!
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https://twitter.com/nasaspaceflight/status/1773436766160073162

Quote
Thanks to everyone for their support in getting our youtube channel to one million subs.

Nothing at NSF would have been possible without our amazing team - past and present - involved, and a superb space flight community that supports what we all do!

Too many names to mention and words to say, so we just hit the mics at the end of the DIV-H stream to say thank you! Clipped here:
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T-0 for tomorrow is 17:37 UTC

My bold:
NGA Rocket Launching notice.
Quote from: NGA
191855Z MAR 24
NAVAREA IV 333/24(GEN).
NORTH ATLANTIC.
FLORIDA.
1. HAZARDOUS OPERATIONS, ROCKET LAUNCHING
   281740Z TO 282251Z MAR, ALTERNATE
   291737Z TO 292251Z MAR AND 011725Z TO 012251Z
   APR IN AREAS BOUND BY:
   A. 28-34.73N 080-34.39W, 28-37.00N 080-20.00W,
      28-34.00N 079-44.00W, 28-30.00N 079-45.00W,
      28-28.00N 080-20.00W, 28-28.88N 080-32.26W,
      28-30.00N 080-32.80W, 28-33.65N 080-34.05W.
   B. 28-31.00N 073-23.00W, 28-22.00N 070-35.00W,
      27-51.00N 070-38.00W, 27-58.00N 073-22.00W.
   C. 22-05.00N 042-25.00W, 22-29.00N 042-17.00W,
      20-36.00N 036-57.00W, 20-22.00N 037-03.00W.
2. CANCEL THIS MSG 012351Z APR 24.

Quote from: Tory Bruno tweet
[Launch window] 4 hrs from original open.

March 29 launch window is probably 17:37 to 21:37 UTC = 1:37 to 5:37 pm EDT.
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Other Launchers (Korean, Brazilian etc.) / Re: Brazilian VLM-1
« Last post by Rik ISS-fan on Today at 06:35 pm »
DLR has started integration of the S50 thrust vector assembly onto the S50 motor for the second static firing test.
https://www.instagram.com/moraba_dlr/reel/C38UrrRikoU/
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"Why I shouldn't have used the word Nasa in my website name" is too long.
<snip>


Two observations:

1. That title is not too long actually
2. That title is perfect

I'll let myself out now.
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I envision one of the uses of rotating stations is to provide the living quarters for the zero-G workforce.
Living at one G and working at zero-G should prevent most of the problems encountered with the human body. So an easy way to transfer at shift change would be beneficial.
Many mining sites in northern Canada use buses for this.  The mine site is not a good place to live, and not very pretty.  So the living quarters are a few km away on a pleasant lake.  There are always many pick-up trucks around for individual errands. Once the mine site is build, traffic goes way down, except for the haul roads.
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Quote from: ULA tweet
The launch of a ULA #DeltaIVHeavy carrying the #NROL70 mission for the @NatReconOfc was scrubbed due to an issue with the gaseous nitrogen pipeline which provides pneumatic pressure to the launch vehicle systems. The team initiated operations to secure the vehicle.
<Charlie Brown Uuuugh! here>
I thought all the GN2 supply and distribution issues were taken care of last year!
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https://twitter.com/torybruno/status/1773431882052440168

Quote
We exceeded the limit for winds and had to call a hold with a 4 min recycle

During the hold, a Cape GN2 pipeline ground pump failed causing a scrub

See you tomorrow
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Advanced Concepts / Re: Spinlaunch on the Moon
« Last post by lamontagne on Today at 06:28 pm »

Second, aluminium might not be the best choice since it has quite a coefficient of expansion and has lifetime fatigue issues (the arms will be rotating quite fast, with a wobble when the payload has departed). On that note, I expect you'll have some really DEEP anchoring. How are tensegrity towers for this kind of application? You could make the tower a tripod, pentapod shape or whatever because you just need to clear the arm (failure modes notwithstanding).

For the last mile problem catching, you could probably use some kind of electrostatically charged net. Payload has a positive charge, and so does the net except near the middle.
-Good point.  I'll go for carbon fiber matrix for the few first ones then, and after that switch to locally produced steel.

-Should have paid more attention during my dynamics classes :-)  It's really an energy transfer and damping problem at that point.

-I really need to do my homework and circularize the orbit.  Instead of waving my hands around and talking of cold gas thrusters.

-A cool thing is that once the design is working, it can be increased to much larger payloads with almost the same physical footprint.  Just need a bigger motor, beefier arm, stronger mast and deeper foundations.
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Quote from: OTV Booster link=topic=58288.msg2581416#msg2581416
There were earlier posts about small engine tests at MacGregor, but I've seen no details. Maybe RCS, maybe lunar landing engines. SX really prefers rolling their own but if they need a gas thruster right now to get through the current tests, plumbing shouldn't be all that much of a problem.
would anyone care to school me about gasses and pumps etc.?

my idea is:
- pump propellant gasses out of ullage into a pressurized tanks (COPV if I understand correctly), early in the flight
- later mix them and burn them in one central hot-pot. store the resulting hot gas in another COPV
- use that gas for RCS

or variously:
- use tiny rocket motors for each RCS, fed from the propellant COPVs
- forget the ridiculous ignition idea, just choose one propellant, pump ullage into a high pressure COPV early in the launch, use that high pressure gas post-boost for RCS. This addresses the perhaps non-existent issues of ullage-gas-less-reliable-and-or-not-ideal-in-free-fall

One system I have seen mentioned around here.
Pump liquid prop into higher pressure COPV.
Let warm and gasify, may have external heat applied.
Use higher pressure COPV gas in thrusters with electric igniter.

I believe JohnL sketched something similar.
John described it, I sketched what he described, at https://forum.nasaspaceflight.com/index.php?topic=46574.msg2076920#msg2076920
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