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David Lammers ASTE 527 Concept 13 December 2011

Powered Re-entry Vehicle. David Lammers ASTE 527 Concept 13 December 2011. Why and What is Powered Re-entry ?. Take advantage of on orbit refueling ΔV burn to decrease re-entry velocity Light weight Lower heat of re-entry = no heavy heat shield tiles

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David Lammers ASTE 527 Concept 13 December 2011

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  1. Powered Re-entry Vehicle David Lammers ASTE 527 Concept 13 December 2011

  2. Why and What is Powered Re-entry? • Take advantage of on orbit refueling • ΔV burn to decrease re-entry velocity • Light weight • Lower heat of re-entry = no heavy heat shield tiles • Easier on passengers (lower decelerations) • Easier on vehicle = reusability • Unlimited cross range capability • Land anywhere on the Earth you desire

  3. Fuel Depot Game changing technology to utilize future on-orbit fuel depots

  4. Powered Re-entry Vehicle • Small vehicle • Lightweight • Decreases up and down propellant requirement • Designed for a small crew only • 3-6 astronauts • Horizontal landing • May incorporate air breathing/turboprop propulsion for in-atmosphere range extension

  5. PRV • Must be delivered to space • Ex. X-37 • X-37 architecture • Build on sub-orbital platform • Space Ship 2, Lynx, Super Mod, etc. • Low weight materials • Carbon composites • Less (or no)TPS

  6. Case Study: X-37 • Phased design • Designed for a 3.1 km/s ΔV and 270 days in orbit • launch weight of ~ 5000 kg • Upgraded X-37C design announced 2011 • 165-180% scale of X-37B • Carry up to 6 astronauts in modified cargo bay Reported Cost ($ in millions) • 1999: NASA 109, USAF 16, Boeing 67 • 2002: Boeing awarded additional 310 under SLI • Total of $500 million

  7. Case Study: Space Ship Two • Suborbital (~110km) • Max velocity ~ Mach 3 (SS1) • Increase drag through “feathering” • Highly stable • Low skin temperature • Allows use of light weight carbon composites without heat shield

  8. Velocity Profile of Shuttle

  9. Propellant Requirement • Uses Ideal Rocket Equation which neglects all forces other than thrust 5000kg burnout mass 1200kg burnout mass

  10. Size Comparisons of X-37 and Shuttle • Shuttle loaded mass 381,600 kg (estimate) • 81,600 kg dry mass • X-37B loaded mass 4,990 kg • 2,600 kg dry mass (estimate)

  11. Reusability is Key • Low mechanical stress and low heat buildup on vehicle should lead to a highly reusable system • Need to keep turnaround costs down • Est. $450 million per shuttle launch • Ideally the craft could be reused quickly with almost zero cycle cost

  12. Multiple PRV’s • Economies of scale • More customers • Nations • Private industry • Individuals Credit: Buzz Aldrin

  13. Future Work • Feasibility • Would a system like this really work • Simulation comparing reentry velocity, drag, delta V, aerothermal simulation, etc. • Figure out maximum velocity that the “feathering” technique could be employed • Initial thought it needs to be done at the apex of a trajectory, thus a very low (almost zero) velocity

  14. References http://www.af.mil/information/factsheets/factsheet.asp?fsID=16639 http://www.protechcomposites.com/pages/High-Temp-Panels.html http://blogs.voanews.com/science-world/files/2011/09/iss.jpg http://scienceblogs.com/startswithabang/upload/2009/05/could_an_asteroid_have_wiped_o/impact3.jpg http://spacesolarpower.info/wp-content/uploads/2011/10/fotovoltaico_spaziale.jpg http://up-ship.com/blog/?p=639 http://buzzaldrin.com/space-vision/rocket_science/multi-crew-modules/ http://www.nasa.gov/centers/kennedy/about/information/shuttle_faq.html blogs.airspacemag.com/.../10/x37-still-aloft/ http://www.boeing.com/defense-space/space/hsfe_shuttle/facts.html

  15. Powered Re-entry Vehicle

  16. BACKUP SLIDES

  17. Reentry, as it is Now Shuttle • Mach 25 at 120 km • TPS = 8574 kg (30,000 tiles) • Includes all types of tiles FRSI, LRSI (FIB), HRSI, and RCC FRSI < 371 C FIB < 649 C HRSI < 1260 C RCC > 1260 C

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