1 / 23

Introduction to Hypersonic Propulsion Systems

Dr. Andrew Ketsdever Assistant Professor Department of Mechanical and Aerospace Engineering University of Colorado at Colorado Springs aketsdever@eas.uccs.edu http:// eas.uccs.edu/aketsdever. Introduction to Hypersonic Propulsion Systems. Technology Requirements. Propulsion System Factors.

tiva
Download Presentation

Introduction to Hypersonic Propulsion Systems

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. Dr. Andrew Ketsdever Assistant Professor Department of Mechanical and Aerospace Engineering University of Colorado at Colorado Springs aketsdever@eas.uccs.edu http://eas.uccs.edu/aketsdever Introduction to Hypersonic Propulsion Systems

  2. Technology Requirements

  3. Propulsion System Factors • Efficiency • Weight • Complexity • Variability • Longevity and cost of components • Fuels (density, rheology, stowability, handling, combustion characteristics, cost) • Materials • Mission requirements (trajectory, cost, etc.)

  4. Selection Process

  5. Performance • Specific impulse • Thrust • Inert mass fraction • All three must be optimized in order to achieve desired outcome

  6. Performance

  7. Temperature Small Space Booster Thrust Chambers NASP Boost Glide Vehicles • Solid • Staged • Combustion Cruise Missiles Satellite Propulsion Booster Liquid Rocket Engine Nozzles Time, sec Materials

  8. Fuels

  9. Problems • Most launch vehicles are rockets, which suffer from low specific impulse compared with air-breathing systems (5000 sec. for turbojets vs. 500 sec. for rockets) • This degrades overall performance and increases weight (a good reason to investigate hybrid systems for future launch vehicles!)

  10. Problems • The need to carry so much fuel makes overall weight a crucial design factor • The structure of the vehicle is made as light as possible to compensate • Boosters are not strong, rigid bodies. While they are fairly strong longitudinally, they are very weak laterally • Most rockets cannot fly at significant angles of attack through the atmosphere or they would fall apart! • A rocket carrying satellites usually starts vertically, but must end in a horizontal orbit trajectory • How can you control trajectories??? • How do you keep from falling apart???

  11. Pratt & Whitney J58 Turbo-ramjet cycle 35,000-lb thrust class, 9-stage compressor, SFC 2.17 1/hr

  12. SUBSONIC TURBINE ENGINE HIGH ALTITUDE SUPERSONIC TURBINE ENGINE RAMJET, AIR-AUGMENTED ROCKET LOW ALTITUDE SUPERSONIC TURBINE ENGINE HYPERSONIC RAMJET Flight Regimes 200 150 ALTITUDE, KFT 100 50 0 0 1 2 3 4 5 6 7 FLIGHT MACH NUMBER

  13. Propulsion Options Combined cycle Propulsion • “Low speed” cycle + scramjet • Rocket Based Combined Cycle (RBCC): Mach 0--25 air-breathing +rocket + scramjet + rocket • Turbine Based Combined Cycle (TBCC): Mach 0--4, 5 turbine + scramjet • Scramjet • Supersonic combustion ramjet • Hydrocarbon (Mach 3-8) • Hydrogen (Mach 3-15)

  14. Scramjet Vehicle and Propulsion system are totally integrated No Moving Parts Necessary Mach 4 and higher Body Fuel Cowl Combustor Forebody (Compression) Nozzle Shock Wave Isolator Inlet

  15. NASA X-34 Scramjet Program "On 16 November, 2004, NASA's unmanned Hyper-X (X-43A) aircraft reached Mach 9.6 (~7,000mph). The X-43A was boosted to an altitude of 33,223 meters (109,000 feet) by a Pegasus rocket launched from beneath a B52-B jet aircraft. The revolutionary 'scramjet' aircraft then burned its engine for around 10 seconds during its flight over the Pacific Ocean."

  16. Turbine Based Combined Cycle (TBCC) • Accelerator Turbine (Mach 0—4.3) is combined with a duel-mode scramjet engine (Mach 4—8) • Transition from turbine power to ramjet is performed at Mach 4 Over-Under configuration Accelerator Turbines Turbine-engine inlets • Cocooning hot turbine engines will be a technical challenge • Tail rockets would likely be added if vehicle is the first stage of launch system

  17. Rocket Based Combined Cycle (RBCC) Rocket-Based Combined Cycle promises a propulsion system that can achieve good performance from M = 0--25 Body Strut & Rockets Cowl Combustor Forebody (Compression) Nozzle Shock Wave Inlet & Door Isolator Vehicle and Propulsion system are totally integrated

  18. RBCC Modes of Operation Air-Augmented Ejector Mode Mach = 0—3 AIR Ramjet Mode M = 3—6 AIR M <1 GREEN ARROWS: FUEL INJECTION AIR M >1 Scramjet Mode M = 6—10 Inlet Closed Rocket Mode M > 10 Each mode is sub-optimized in its operating range

  19. RBCC-TBCC

  20. 3 2 Detonation wave moves Detonation is initiated through fuel-air mixture 4 Resulting high pressure gas 1 fills detonation chamber Fuel is mixed with air 5 Detonation wave exits engine Air drawn in by reduced pressure Pulsed Detonation Engines • Pulse Detonation Engine • Operating Concept Typical: 40 cycles/sec

  21. Re-Entry

  22. Re-Entry: Meteors

More Related