Author Topic: 3 Ares I design papers - Operations/System Integration/J2-X  (Read 4100 times)

Offline CuddlyRocket

Building Operations Efficiencies into NASA’s Ares I Crew Launch Vehicle Design

http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20070002791_2007001540.pdf

System Integration Processes for NASA Ares I Crew Launch Vehicle

http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20070002810_2007001617.pdf

Development of the J-2X Engine for the Ares I Crew Launch Vehicle and the Ares V Cargo Launch Vehicle: Building on the Apollo Program for Lunar Return Missions

http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20070002803_2007001610.pdf

(This is the same paper as in the equivalent Ares V thread.)

Offline JonSBerndt

  • Aerospace Engineer
  • Full Member
  • ***
  • Posts: 399
  • Westminster, CO
    • JSBSim Open Source Flight Dynamics Software Library
  • Liked: 4
  • Likes Given: 61
Anyone seen a publicly accessible paper on the 5 segment SRB? (thrust vs. time trace, specifically?)

Jon

Offline RedSky

  • Veteran
  • Full Member
  • ****
  • Posts: 511
  • Liked: 109
  • Likes Given: 2
That J2X paper was really interesting, and gives you an appreciation for the hurtles to overcome with the EDS.  The 95-day loiter in orbit time is a real problem to overcome.  Do they have batteries to run the thing and keep it healthy over that length of time?  Maybe it will need some small solar panels to unfold (Soyuz style)... which would be jettisonned just prior to TLI burn.  Also the issues of restarting the engine after three months... assuming everything else is healthy.  I can easily see lots of unfortunate opportunities for LOM without the crew ever having left the ground.  :(

Offline Jim

  • Night Gator
  • Senior Member
  • *****
  • Posts: 37440
  • Cape Canaveral Spaceport
  • Liked: 21450
  • Likes Given: 428
Quote
RedSky - 11/2/2007  11:28 AM

That J2X paper was really interesting, and gives you an appreciation for the hurtles to overcome with the EDS.  The 95-day loiter in orbit time is a real problem to overcome.  Do they have batteries to run the thing and keep it healthy over that length of time?  Maybe it will need some small solar panels to unfold (Soyuz style)... which would be jettisonned just prior to TLI burn.  Also the issues of restarting the engine after three months... assuming everything else is healthy.  I can easily see lots of unfortunate opportunities for LOM without the crew ever having left the ground.  :(

Fuel Cells.  There is a lot of H2 and O2 onboard.  However the 95 day loiter has been reduced.  To around 15 days I believe

Offline Generic Username

  • Elite Veteran
  • Full Member
  • ****
  • Posts: 962
    • Aerospace Projects Review
  • Liked: 30
  • Likes Given: 0
Quote
JonSBerndt - 11/2/2007  6:33 AM

Anyone seen a publicly accessible paper on the 5 segment SRB? (thrust vs. time trace, specifically?)

I believe that's exactly the sort of thing that's not to be made publicly available.
"US Spacecraft Projects" and "US Launch Vehicle Projects"
aerospaceprojectsreview.com

Offline JonSBerndt

  • Aerospace Engineer
  • Full Member
  • ***
  • Posts: 399
  • Westminster, CO
    • JSBSim Open Source Flight Dynamics Software Library
  • Liked: 4
  • Likes Given: 61
Quote
Generic Username - 11/2/2007  12:07 PM

Quote
JonSBerndt - 11/2/2007  6:33 AM

Anyone seen a publicly accessible paper on the 5 segment SRB? (thrust vs. time trace, specifically?)

I believe that's exactly the sort of thing that's not to be made publicly available.

You might think so at first, but the thrust/time trace of the current STS SRB is printed in the CAIB report, and is also available in the Challenger documents. I'm not sure what kind of sensitivity there is for the 5 seg SRB, or why there would be. The max thrust is known, Isp, propellant type, burn duration, etc. It would not surprise me if there is a NASA document, AIAA paper, AvWeek article, etc. publicly available that has that information in it.

Jon

Offline Jim

  • Night Gator
  • Senior Member
  • *****
  • Posts: 37440
  • Cape Canaveral Spaceport
  • Liked: 21450
  • Likes Given: 428
Those were back before ITAR really raised its ugly head

Offline Generic Username

  • Elite Veteran
  • Full Member
  • ****
  • Posts: 962
    • Aerospace Projects Review
  • Liked: 30
  • Likes Given: 0
Quote
JonSBerndt - 11/2/2007  11:30 AM
I'm not sure what kind of sensitivity there is for the 5 seg SRB, or why there would be. The max thrust is known, Isp, propellant type, burn duration, etc. It would not surprise me if there is a NASA document, AIAA paper, AvWeek article, etc. publicly available that has that information in it.

I don't do any publishing (my work is boring). But those around me who *do* have to scrub their charts and graphs and non-dimensionalize them. Why? Shrug. The basic rule is that general physics is permitted but actual engineering is not. In other words, we can show you how to build a rocket, just not *this* rocket.
"US Spacecraft Projects" and "US Launch Vehicle Projects"
aerospaceprojectsreview.com

Offline JonSBerndt

  • Aerospace Engineer
  • Full Member
  • ***
  • Posts: 399
  • Westminster, CO
    • JSBSim Open Source Flight Dynamics Software Library
  • Liked: 4
  • Likes Given: 61
Quote
Generic Username - 11/2/2007  1:16 PM
I don't do any publishing (my work is boring). But those around me who *do* have to scrub their charts and graphs and non-dimensionalize them. Why? Shrug. The basic rule is that general physics is permitted but actual engineering is not. In other words, we can show you how to build a rocket, just not *this* rocket.

It's not a big deal, anyhow. It was for educational purposes.

Jon

Tags:
 

Advertisement NovaTech
Advertisement Northrop Grumman
Advertisement
Advertisement Margaritaville Beach Resort South Padre Island
Advertisement Brady Kenniston
Advertisement NextSpaceflight
Advertisement Nathan Barker Photography
1