Explosion at kennedy Space Center
Nemo Me Impune Lacessit
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I wonder if it's possible to insure payloads against disasters likeI wonder if it's possible to insure payloads against disasters like that? And if so, what the premium would be? that? And if so, what the premium would be?
Don't know very much at all about rocketery but, if a test involving the live firing of the rocket is required, would it not be prudent to carry out this test before the valuable satellite is placed on top?
Don't know very much at all about rocketery but, if a test involving the live firing of the rocket is required, would it not be prudent to carry out this test before the valuable satellite is placed on top?
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In the bad old days of rocketry it was not uncommon to source at least two copies of parts for each satellite/interplanetary probe in case of such a mishap. I am taking a wild guess that now it is not so common, given the incredible expense and complexity of such a high capacity modern communication satellite.
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Some good information on this lies in the "forum" of NASASpaceFlight.com discussing this very practice. Bottom line is that early mating of the payload and rocket is cheaper, given that the launch was scheduled for this weekend. Alas.....
Speaking of Saturn V's,here's an interesting article about a recent project to get re-acquainted with the Rocketdyne F-1 engine.
http://arstechnica.com/science/2013/...-back-to-life/
http://arstechnica.com/science/2013/...-back-to-life/
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However, as I understand it, the in-flight failure was due to acceleration forces, which would be going in the opposite direction to bouyancy. They've put extra effort into checking every single strut since then. and I presume the second stage has been test-fired (and, hence, previously fuelled), like the first.
It's possible it's a related problem, but, from what I've read, the failure seemed to start around the umbilical attachments, which would make them a prime candidate. If it disconnected and started spraying liquid oxygen around, that would have been bad news.
It's possible it's a related problem, but, from what I've read, the failure seemed to start around the umbilical attachments, which would make them a prime candidate. If it disconnected and started spraying liquid oxygen around, that would have been bad news.
I've seen videos of a car driving round a roundabout with a helium baloon inside. It looks *really* weird when the baloon is pressed toward the *inside* of the roundabout (i.e onto the driver)...
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There are three main explosive reports in the initial event 1) the initial tank rupture 2) a much larger report 3 seconds later, possibly from the RSO operating the self-destruct mechanism and 3) the report from the satellite stage toppling to the ground about 11 seconds after the first report.
-drl
-drl
Thanks TWT, for the Saturn V article. I just had good read through it. The stats and figures are monsterous! I feel the same awe as I got when I found the same sort of info on the V2 weapon. I remember struggling to absorb the key facts such as 500 hp (if memory serves) being needed just to drive the fuel pump for the main engine. 500 hp is a good amount of power for a decent road car at the start of the 21st century and they were using this much just to drive a fuel pump in the 1940s. Magic.
Speakingb of Saturn V's,here's an interesting article about a recent project to get re-acquainted with the Rocketdyne F-1 engine.
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SpaceX have been totally transparent with their launcher failures and are far and above any other organisation in this respect.
The previous helium tank failure was traced down to a 3 D 4" square area by interrogating strain gauge outputs and applying different filtration to the raw data to produce the result.
This showed that the support struts could have suffered oxygen intergranular corrosion.
This was proven when lab tests showed a number of the struts had a chemical imbalance that could lead to this type of weakening.
The support struts were then manufactured in house.
The previous helium tank failure was traced down to a 3 D 4" square area by interrogating strain gauge outputs and applying different filtration to the raw data to produce the result.
This showed that the support struts could have suffered oxygen intergranular corrosion.
This was proven when lab tests showed a number of the struts had a chemical imbalance that could lead to this type of weakening.
The support struts were then manufactured in house.
I remember struggling to absorb the key facts such as 500 hp (if memory serves) being needed just to drive the fuel pump for the main engine.
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Back at the ranch History
The helium tank issue brought back some very old memories re the Saturn first stage- I’m talking 1963-64. Working at Boeing at a facility which had some large steam- accumulators to run steam ejectors to simulate 100K altitudes for early ramjets ( BOMARC ) gave us a facility which allowed us to simulate some parts of the S-1C first stage oxygen tankage system using the accumulators as a large air supply to evaluate the LOX tank pressurization system. The GOX ( gaseous oxygen ) in the fight bird used some bleed oxygen from the turbo pumps to maintain some pressure in the LOX tank to prevent pump cavitation . It was mounted on the top of the dome and fed by a approx 4 inch diameter tube running up the outside of the tank. The concern was the effects of impingement on the top dome of relatively high velocity oxygen. So we built an upside down 1/8 section of the dome ( like a ski ramp-) mounted the distributor upside down in the correct relative location. The flight design distributor was like a large 3-4 foot diameter trash can with half of the cylinder made of ‘ regimesh ‘ - sort of a multilayer screen to break up the flow and then run it with air and monitor with tufts and some instruments the impingement and internal pressures, etc. Each test run was about 30 seconds on condition. But we had various photo and instrumentation and flow measurement problems which with running certain specific flow rates required so we made several test runs. About the 5th or 6th run ( 30 seconds each ) the distributor exploded ! Luckily We had some high speed cameras focused on the distributor .As the Engineer in charge I ordered 3 copies of the film to be made ASAP. Examination of some of the parts indicated a fatigue failure ( high pressure, high flow and supersonic noise can do a lot of things ). The test was on a friday. I called the designers in New orleans and told them I had destroyed the distributor- after convincing them I was NOT joking- they hopped a plane to be in Seattle by Monday .
Monday afternoon when I got the file, I was “ invited “ into the Seattle Program Directors office ( George Stoner ) to show the film and explain as best I could what happened. The film showed the beginning of a seam in the regimesh starting to unzip.[ NOTE- In normal flight the SIC stage runs for about 2 minutes and 40 seconds- our total test time on that unit was close to 3 minutes !! ]
Getting together with the designers- I suggested three changes - adopted- 1) an intermediate dome in the distributor with many many 1/4-3/8 holes, 2) the above ( below in flight attitude ) cylinder not of regimesh but many many 3/8 holes and 3) a change to holes in the supply tube from slots.
We fabricated such a design and ran and ran and ran it for three to four times the normal expected flight time with no problems other that some minor ‘ working” of fastener holes evidenced by smudges around the fasteners. As far as I know- that was the design that flew.
SideNote - we used 4 inch diameter SS tubing - special run of about 30 feet. Leftover tubing from the initial build was sold to a local junkyard as no problems were anticipated. I chased the tubing down, bought it back to fabricate the new tube design ( about 3 -4 feet used for the tests ) . The remainder tubing was again sold. Junkyard sold several 3 foot sections as local clam guns - ( seattlelites know what they are )
There are three main explosive reports in the initial event 1) the initial tank rupture 2) a much larger report 3 seconds later, possibly from the RSO operating the self-destruct mechanism and 3) the report from the satellite stage toppling to the ground about 11 seconds after the first report.
https://www.youtube.com/watch?v=maRTEzlSBLk
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The payload and second stage remained in place for seconds before toppling. Once it toppled, it fell to the ground where it created a blast and mushroom cloud of its own.
I'm not so sure that there wasn't an explosion. There are a couple of fragments that were ejected with considerable velocity from the original (frame 1) blast point. That was a diamond shaped blast - as you might expect from a relatively small container rupturing under pressure. Or perhaps it was just shaped from obstacles around it.
Last edited by .Scott; 7th Sep 2016 at 19:20. Reason: Removed text that was a likely misinterpretation of pre-incident news reports.
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not sure where you got that from?
both 1st and second stages were fully fueled with RP-1, only the stage 2 LOX tank was still being loaded, reports suggest it was at ~80% at the time of the fire/explosion)
both 1st and second stages were fully fueled with RP-1, only the stage 2 LOX tank was still being loaded, reports suggest it was at ~80% at the time of the fire/explosion)
only the stage 2 LOX tank was still being loaded, reports suggest it was at ~80% at the time of the fire/explosion)