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Blue Origin thread.


Vanamonde

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ED made the observation that this could be the first US methalox rocket to go to orbit. It's debatable, but I suppose it can have that, as a treat.

Disregard

Edited by AckSed
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2 minutes ago, AckSed said:

ED made the observation that this could be the first US methalox rocket to go to orbit. It's debatable, but I suppose it can have that, as a treat.

Vulcan already did this.

Over a year ago.

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19 minutes ago, AckSed said:

Oops. Oh well, it can be the first US methalox engine to reach orbit...

*remembers Relativity*

Dammit!

Actually, we should remember Zhuque-2 from Landspace in June ‘23.

Yes, we are in a race y’all and don’t ya forgit it

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54 minutes ago, AckSed said:

Oops. Oh well, it can be the first US methalox engine to reach orbit...

*remembers Relativity*

Dammit!

I say leaving out 200 m/s for safety on an test launch count as orbital. Its obvious an fail if you try to launch something to orbit unless you had an kick stage who is an 3 or 4th stage anyway. 
But this leaves SS as the winner. Race is who put an usable payload into orbit. 

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22 minutes ago, magnemoe said:

I say leaving out 200 m/s for safety on an test launch count as orbital. Its obvious an fail if you try to launch something to orbit unless you had an kick stage who is an 3 or 4th stage anyway. 
But this leaves SS as the winner. Race is who put an usable payload into orbit. 

Agreed. I’m just reflecting on all the jeering about starship not making orbit.

If enough orbital energy is reached that if an orbit with the same energy could be entirely above the atmosphere or if there is enough propellant remaining to raise perigee above the atmosphere at apogee that is “orbital” in my book, or at minimum, “orbital capable”.  Especially if upper stage relight has been successful

Edited by darthgently
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3 hours ago, darthgently said:

As for the TWR,  they may have been throttled down.  That would make sense, but with only seven engines that TWR makes for a dramatic hypothetical engine out scenario

It matches my memory of the liftoff speed of a Saturn V (the only video I can easily find of the Saturn V right now are slow motion movies). I presumed they were doing it to go easy on the engines, since they had almost no payload.  Or maybe so that somebody here could rant about how they are lying about the actual thrust capacity and reliability (since they failed to relight for landing) of the BE-4 engines. But I don't see that rant. Odd.

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What we need is an LLM that is rigorously trained specifically to look for conversion errors in code.  It has one job.

 But probably better if vars in a computer language had a units type as well as data type inherent in its definition.  In fact you’d need this to truly do the paragraph above

Edited by darthgently
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7 minutes ago, darthgently said:

Great observation

 

The first director of ARPA-E, a new/renewable-energy think-tank, said, "Culture eats strategy for breakfast, lunch and dinner."

A workplace culture with a person or persons at the helm that listens to their engineers, has a clear objective and is able to make changes to its direction when needed, is a culture that gets the job done.

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40 minutes ago, Brotoro said:

It matches my memory of the liftoff speed of a Saturn V (the only video I can easily find of the Saturn V right now are slow motion movies). I presumed they were doing it to go easy on the engines, since they had almost no payload.  Or maybe so that somebody here could rant about how they are lying about the actual thrust capacity and reliability (since they failed to relight for landing) of the BE-4 engines. But I don't see that rant. Odd.

Think Saturn 5 was 1.1 TWR, this was on purpose as longer fuselages and more fuel is cheaper than more engines. Later on SRB become standard to kick the rocket up. 
For reusability  higher TWR has benefits, way more so if you want to do an boost back. 
Now engines might be run below max trust to increase reliability? 

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NG GS1 staged very low in the atmosphere and the landing barge was relatively close-by to land.

I think this is splitting the difference between Starship/Super Heavy's RTLS, 'near-SSTO with just enough booster to get out of the atmosphere' approach, and a F9 far-out landing barge. The closer the landing barge, the less time GS1 takes to reach port and be processed, improving cadence.

Other possibilities are that this was a test of booster re-entry, and they were making this as gentle as possible. 'Proper ' payloads might necessitate a further-out landing barge.

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26 minutes ago, Spaceception said:

And it looks like their next mission will be to the Moon with Mk 1, which is exciting. 

I hope the imperial/metric mess up is just an odd/funny coincidence, and not the actual reason. 

No more likes, but I agree

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