Author Topic: Testing upper stage propulsive entry survivability  (Read 5701 times)

Offline Kaputnik

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Thinking about how SpaceX approached the issue of first stage recovery testing, is there any merit in doing the same with the second stage? That is, use margin on an operational launch, using existing hardware, to see how far through entry the vehicle can get.

Using the numbers of Ed Kyle's site, I get a delta V of about 11,000m/s for the second stage.
If there were no payload at all (hypothetical scenario), I estimate you would have around 5,300m/s to deorbit and slow the entry. That's quite a lot, but is it enough?

We know what combination of speed/altitude the first stage can survive, but I lack the knowledge to translate that information into the relevant conditions for the upper stage.

Secondly, does it seem likely that the second stage might be more robust than the first, from an entry standpoint?

So my main question is... does the forum think that there is anything to be learned from attempting partial propulsive entry testing? And are there any particularly small payloads manifested that would be potential opportunities (like CASIOPE was).
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Offline Lar

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Re: Testing upper stage propulsive entry survivability
« Reply #1 on: 02/20/2017 04:28 PM »
I think the theory is the numbers miss by so much that there's no merit in trying to actually recover. But you may be on to something in that there may be things that can be learned by higher speed reentries even if the stage isn't recovered. But what? What does SpaceX need to know that it hasn't gotten from S1 reentry and the low density heat shield work NASA already did?

If we can spot something?
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Online envy887

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Re: Testing upper stage propulsive entry survivability
« Reply #2 on: 02/20/2017 05:30 PM »
It would be interesting to see if (or how long) the vac nozzle can survive hypersonic entry aero loads. Even after launching a very light LEO payload and propulsive deceleration it will still be travelling somewhere around Mach 10 at entry interface.

Offline Kaputnik

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Re: Testing upper stage propulsive entry survivability
« Reply #3 on: 02/20/2017 05:46 PM »
Where I would see the value in this experiment is in determining the survival point of the stage. Start the entry burn just before you think the stage is about to be lost, and make a long, throttled back burn to see how long the stage can survive. There is still a lot to be learned in hypersonic retropropulsion.
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Offline whitelancer64

Re: Testing upper stage propulsive entry survivability
« Reply #4 on: 02/20/2017 05:54 PM »
Recovering the second stage with retropropulsion isn't going to work, too much fuel is needed. Just stick a heat shield (perhaps expandable) on the nose.
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Offline R7

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Re: Testing upper stage propulsive entry survivability
« Reply #5 on: 02/20/2017 07:17 PM »
S2 with proper heat shield doesn't even have to do atmospheric entry burn S1 does.
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Offline S.Paulissen

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Re: Testing upper stage propulsive entry survivability
« Reply #6 on: 02/22/2017 04:10 AM »
S2 with proper heat shield doesn't even have to do atmospheric entry burn S1 does.

Is there evidence for this assertion?  How much would the shield mass?  Is that factored into sim?  What are peak breaking gees?  Just curious.
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Offline R7

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Re: Testing upper stage propulsive entry survivability
« Reply #7 on: 02/22/2017 08:31 AM »
1. Is there evidence for this assertion? Is that factored into sim?
2. How much would the shield mass?
3. What are peak breaking gees?

1. Rational reasoning. Reusable S2 has to cope with heat and stresses while decelerating from orbital speed. Heat shield is given, more on this below, so whatever thermal environment the S1 couldn't cope without powered breaking was, S2 can do it. S2 is more stubby which adds to structural strength. And it has to be aerodynamically stable during reentry. Didn't early F9 S1 reentry attempts fail mainly because there were no means to control the attitude, no RCS no fins, so it didn't stabilize and kept tumbling until aerodynamic forces broke it?

2. There are calculations in other threads estimating Dragon heatshield weighing little over 200kg. Area is known and PICA-X density is known, it's very light stuff. Then there's of course some additional support structure but it's still a total of how many hundreds of kgs, not tons. Relying on that mass to decelerate from orbital speed to terminal velocity vs. hypersonic retropropulsion isn't much of a contest.

3. Hard to say for sure because need to know things like S2 ballistic coefficient, drag coefficient and whether it uses any lift or does purely ballistic reentry. BC would likely to be smaller than any returning SCs so far. IIRC low BC means greater deceleration in upper atmosphere but lower peak deceleration because velocity when entering the quickly thickening lower atmosphere is smaller. Read about this in some paper analysing ICBM RV trajectories, fun!  ;)

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Online dorkmo

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Re: Testing upper stage propulsive entry survivability
« Reply #8 on: 02/23/2017 01:10 AM »
would the center of gravity be a problem?

Online envy887

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Re: Testing upper stage propulsive entry survivability
« Reply #9 on: 02/23/2017 03:27 AM »
S2 will have a ballistic coefficient similar to Apollo unless it does a lifting entry, in which case the heat shield needs to extend down one side but the BC can be 4 or 5 times less.

With chines, a full length shield, and an engine flap it could enter like ITS, with a very high alpha, lots of lift, and quite low ballistic coefficient.

Offline corneliussulla

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Re: Testing upper stage propulsive entry survivability
« Reply #10 on: 02/23/2017 10:00 AM »
The ITS is effectively a 2nd stage re entry vehicle. A similar type vehicle could be built for launch on falcon I would think. In a world where ITS refuelling exists refuelling a notional falcon 2nd stage for deorbit would be a minor affair I would think. ITS tankers could be parked in orbit to enable a great number of falcon 2nd stages to return to earth for each ITS tanker launch. If ITS tanker will be available in next 6 years this would seem the most logical way forward rather than trying to make the existing 2nd stage survivable

Re: Testing upper stage propulsive entry survivability
« Reply #11 on: 02/23/2017 09:52 PM »
Seems like a good thread to re-post this old 2011 animation showing S2 re-entry, landing. But would it be able to land back at the cape? Would it have to orbit first?


Online speedevil

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Re: Testing upper stage propulsive entry survivability
« Reply #12 on: 02/24/2017 02:15 AM »
Seems like a good thread to re-post this old 2011 animation showing S2 re-entry, landing. But would it be able to land back at the cape? Would it have to orbit first?
Second engine cutoff is around 600 seconds into flight, at ~8km/s. Neglecting stuff, that's probably over 1/3*8*600 = 1500km or so downrange.
In order to get back to the takeoff site without orbiting, you're going to need to do something wacky - as you are at this point in orbit. Something like a quite substantial burn to intersect the atmosphere, use the atmosphere to kill most of the velocity, burn back up ballistically to the takeoff site, entry trim burns perhaps, and then entry and landing burns like F9 S1.

This is going to need a _lot_ more delta-v than waiting around a day, perhaps with a trim manoever to adjust phasing and going straight in for a landing without the intervening~1500km ballistic hop needing several kilometers/s worth of fuel.
Unless of course you add high performance wings.
(which would be insane)

Offline Lars-J

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Re: Testing upper stage propulsive entry survivability
« Reply #13 on: 02/24/2017 05:41 PM »
Seems like a good thread to re-post this old 2011 animation showing S2 re-entry, landing. But would it be able to land back at the cape? Would it have to orbit first?

Short answer: A reusable 2nd stage could only make it back to the launch site after one orbit. (it might have to wait more orbits, perhaps as long as a day)

Offline mvpel

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Re: Testing upper stage propulsive entry survivability
« Reply #14 on: 02/24/2017 09:37 PM »
I can certainly see why they've tabled this for the time being - they're already recovering 90% of the engines and 70% of the cost of the launch vehicle, and bringing down that last engine and its tankage is clearly a very tricky proposition.
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Offline Jcc

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Re: Testing upper stage propulsive entry survivability
« Reply #15 on: 02/26/2017 01:24 PM »
I can certainly see why they've tabled this for the time being - they're already recovering 90% of the engines and 70% of the cost of the launch vehicle, and bringing down that last engine and its tankage is clearly a very tricky proposition.

They have clearly determined that there is no way to make it work for Falcon, but it is already an integral feature for ITS. It works (hopefully) with ITS by scaling to 10x more thrust in the first stage and over 20x more thrust in the 2nd stage/payload, on orbit refueling, all composite structure, low bulk density for the nearly empty returning vehicle, etc.  you could call these non-trivial changes.

Offline deruch

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Re: Testing upper stage propulsive entry survivability
« Reply #16 on: 03/08/2017 09:35 PM »
I can certainly see why they've tabled this for the time being - they're already recovering 90% of the engines and 70% of the cost of the launch vehicle, and bringing down that last engine and its tankage is clearly a very tricky proposition.
1 MVac costs more than all 9 of the SL Merlins put together. 
« Last Edit: 03/08/2017 09:35 PM by deruch »
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Offline S.Paulissen

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Re: Testing upper stage propulsive entry survivability
« Reply #17 on: 03/09/2017 04:06 AM »
I can certainly see why they've tabled this for the time being - they're already recovering 90% of the engines and 70% of the cost of the launch vehicle, and bringing down that last engine and its tankage is clearly a very tricky proposition.
1 MVac costs more than all 9 of the SL Merlins put together.

Perhaps your reputation alone can attest to this, but I would like to see this claim substantiated with some evidence. 
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Offline Danderman

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Re: Testing upper stage propulsive entry survivability
« Reply #18 on: 03/09/2017 04:24 AM »
I vaguely remember a Gary Hudson concept where the upper stage would return engine first, with the engine firing during re-entry. Apparently, this would be sufficient for the stage to survive the re-entry heating.

Offline JamesH65

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Re: Testing upper stage propulsive entry survivability
« Reply #19 on: 03/09/2017 10:10 AM »
I can certainly see why they've tabled this for the time being - they're already recovering 90% of the engines and 70% of the cost of the launch vehicle, and bringing down that last engine and its tankage is clearly a very tricky proposition.
1 MVac costs more than all 9 of the SL Merlins put together.

Perhaps your reputation alone can attest to this, but I would like to see this claim substantiated with some evidence.

Indeed - I've not seen any claims or data on this before.

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