Weight Analysis of Two-Stage-To-Orbit Reusable Launch Vehicles for Military Applications

@inproceedings{Caldwell2005WeightAO,
  title={Weight Analysis of Two-Stage-To-Orbit Reusable Launch Vehicles for Military Applications},
  author={Richard A. Caldwell},
  year={2005}
}
Abstract : In response to Department of Defense (DoD) requirements for responsive and low-cost space access, this design study provides an objective empty weight analysis of potential reusable launch vehicle (RLV) configurations. Each two-stage-to-orbit (TSTO) RLV has a fixed payload requirement of 20,000 lbf to low Earth orbit. The propulsion systems considered in this study include pure rocket, pure turbine, rocket-based-combined-cycle (RBCC), and turbine-based-combined-cycle (TBCC). The… CONTINUE READING

Citations

Publications citing this paper.

References

Publications referenced by this paper.
SHOWING 1-10 OF 41 REFERENCES

Aerospace Engineer, Aerospace Propulsion Division (AFRL/PRAT), Wright-Patterson AFB OH. Personal Correspondence, Phone: 937255-0632, Email: dean.eklund@wpafb.af.mil

  • Eklund, R Dean
  • 2004
VIEW 7 EXCERPTS
HIGHLY INFLUENTIAL

Critical Issues in TBCC Modeling

  • Marshall, W Andre, Ashwani K. Gupta, Mark J. Lewis, Thomas Lavelle
  • AIAA 2004-3827,
  • 2004

NASA's X-43A Hyper-X Reaches Mach 10 in Flight Test

  • Dornheim, A Michael
  • Aviation Week & Space Technology, http://www.aviationnow.com/avnow/,
  • 2004
VIEW 1 EXCERPT

Performance Study of Two-Stage-To-Orbit Reusable Launch Vehicle Propulsion Alternatives

  • Brock, A Marc
  • MS Thesis, AFIT/GSS/ENY/04-M02. Graduate School of Engineering and Management,
  • 2004
VIEW 2 EXCERPTS