Solid-fuel regression rate behavior of vortex hybrid rocket engines

Journal of Propulsion and Power

Volumn 18, Issue 3, 2002, Pages 600-609

  Knuth, William H ^a,b   Chiaverini, Martin J ^a,b   Sauer, J Arthur ^a,b   Gramer, Daniel J ^a,b  

^a Orbital Technologies Corporation   (United States)

^b Space Center ^*  (United States)

Author keywords

[No Author keywords available]

Indexed keywords

HEAT TRANSFER; LIQUID PROPELLANTS; PIPE FLOW; REYNOLDS NUMBER; SOLID PROPELLANTS; TURBULENT FLOW; VORTEX FLOW;

VORTEX HYBRID ROCKET ENGINES;

ROCKET ENGINES;

EID: 0036575398     PISSN: 07484658     EISSN: None     Source Type: Journal    
DOI: 10.2514/2.5974     Document Type: Article

References (17)

1. Cost and performance payoffs inherent in increased fuel regression rates
2. Turbulent boundary layer combustion in the hybrid rocket
3. Fundamentals of hybrid boundary layer combustion
4. Heat transfer enhancement using tangential injection
5. Pyrolysis behavior of hybrid rocket solid fuels under rapid heating conditions
6. Regression rates of metalized hybrid fuel systems
7. Introductory considerations on hybrid rocket combustion
8. Size scale-up in hybrid rocket motors
9. Regression rate and heat transfer correlations for hybrid rocket combustion