1 / 30

Thermal Engines for Launch Vehicle Configurations

Thermal Engines for Launch Vehicle Configurations. Agenda. What is propulsion Thermal engine basics LOX Augmented Thermal Engines Launch Vehicle Dynamics SSTO/MSTO. Propulsion. Propulsion is energy. Energy and momentum are related. more energy = more propulsion. Energy Sources.

jade-gamble
Download Presentation

Thermal Engines for Launch Vehicle Configurations

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. Thermal Engines for Launch Vehicle Configurations HYPERION ERAU

  2. Agenda • What is propulsion • Thermal engine basics • LOX Augmented Thermal Engines • Launch Vehicle Dynamics • SSTO/MSTO HYPERION ERAU

  3. Propulsion Propulsion is energy Energy and momentum are related more energy = more propulsion HYPERION ERAU

  4. Energy Sources HYPERION ERAU

  5. Thermal Engines • Produce heat to expand a propellant • Requires core materials to withstand high melting points (~2000-4000 K) such as Tungsten and Carbon • Propellant must have a high Cp and low atomic weight. Liquid Hydrogen is a primary candidate HYPERION ERAU

  6. Specific Impulse HYPERION ERAU

  7. Thrust HYPERION ERAU

  8. Nuclear Thermal Rocketry (NTR) • Heavily tested • Must use a combination • of W, LiH, Be • Radiation and spallation • Limited by material melting • point HYPERION ERAU

  9. Positron Thermal Rocket (PTR) • Identical to NTR • Uses positrons as a heat source • Concentric cylinder configuration • Requires only Tungsten, allowing higher core temp. and Isp HYPERION ERAU

  10. LOX Augmentation Increases thrust Decreases Isp HYPERION ERAU

  11. LOX Augmentation • - Based on NTR NERVA configuration • Assumes that PTR is scaled to NTR NERVA specs. • More advanced PBR could increase T/W by X7 HYPERION ERAU

  12. LOX Augmentation HYPERION ERAU

  13. LOX Augmentation HYPERION ERAU

  14. LOX Augmentation HYPERION ERAU

  15. LOX Augmentation HYPERION ERAU

  16. Launch Vehicle HYPERION ERAU

  17. Launch Vehicle Requirements HYPERION ERAU

  18. Single Stage to Orbit (SSTO) • Simple • Quick turnaround time • Short loiter time in orbit • Small payloads delivered HYPERION ERAU

  19. SSTO HYPERION ERAU

  20. SSTO HYPERION ERAU

  21. Multistage Rocketry (MSTO) • Assume all 1st stage engines are Saturn F-1’s Isp: 330 seconds T/W: 96 • Upper-stage chemical engines are SSME’s Isp; 450 seconds T/W: 73 HYPERION ERAU

  22. MSTO Assumptions HYPERION ERAU

  23. MSTO HYPERION ERAU

  24. MSTO HYPERION ERAU

  25. MSTO HYPERION ERAU

  26. MSTO HYPERION ERAU

  27. MSTO HYPERION ERAU

  28. Future Work • Validate Altitude equation • Consider using a PBR analysis • Use Mars transfer analysis for baseline PTR configuration • Use more precise computer model to demonstrate changes in D, alpha, gamma, etc… • Determine launch cost to include H2, O2, etc… HYPERION ERAU

  29. References • Blevins, J., Patton, B., Ryhs, N., Schmidt, G., Limitations of Nuclear Propulsion for Earth to Orbit, AIAA Paper 2001-3515 • Smith, D., Wulff, J., Pearce, C., Bingaman, J., Webb, J., Thermal Radiation Studies for an Electron Positron Annihilation Propulsion System, AIAA Paper 2005-3230 • Humble, R., Henry, G., Wiley, J., Space Propulsion Analysis and Design, McGraw Hills Co. Inc. 1995 • Smith, G., Kramer, K., Meyer, K., Thode, T., High Density Storage of Antimatter for Space Propulsion Application, AIAA Paper 2001-3230 • Borowski, S., Dudzinski, L., 2001 A Space Odyssey Revisited – The Feasibility of 24 Hour Commuter Flights to the Moon Using NTR Propulsion with LUNOX Afterburners, published with permission from NASA, AIAA Paper 97-2956 • Bulman, M., Messit, D., Niel, T., Borowski, S., High Area Ratio LOX-Augmented Nuclear Thermal Rocket (LANTR) Testing, AIAA Paper 2001-3369 HYPERION ERAU

  30. Questions/Comments • ????? HYPERION ERAU

More Related