Computational Assessment of Afterburning Cessation Mechanisms in Fuel-Rich Rocket Exhaust Plumes

Calhoon, William H.

doi:10.2514/2.5715

Cited by 12 publications

(23 citation statements)

References 19 publications

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“…Afterburning is poorly understood and when operating significantly affects the "final" emission into the surrounding air. The blend of compounds leaving an afterburning rocket engine is not identical to the blend that eventually mixes into the atmosphere [Calhoon, 2001]. However, because afterburning typically completes in the lower stratosphere, we need not consider it further, greatly simplifying the task of estimating emissions.…”

Section: Emission Indices and Stratospheric Burdenmentioning

confidence: 99%

Radiative forcing caused by rocket engine emissions

Ross

Sheaffer

2014

Earth's Future

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Space transportation plays an important and growing role in Earth's economic system. Rockets uniquely emit gases and particles directly into the middle and upper atmosphere where exhaust from hundreds of launches accumulates, changing atmospheric radiation patterns. The instantaneous radiative forcing (RF) caused by major rocket engine emissions CO 2 , H 2 O, black carbon (BC), and Al 2 O 3 (alumina) is estimated. Rocket CO 2 and H 2 O emissions do not produce significant RF. BC and alumina emissions, under some scenarios, have the potential to produce significant RF. Absorption of solar flux by BC is likely the main RF source from rocket launches. In a new finding, alumina particles, previously thought to cool the Earth by scattering solar flux back to space, absorb outgoing terrestrial longwave radiation, resulting in net positive RF. With the caveat that BC and alumina microphysics are poorly constrained, we find that the present-day RF from rocket launches equals 16 ± 8 mW m −2 . The relative contributions from BC, alumina, and H 2 O are 70%, 28%, and 2%. respectively. The pace of rocket launches is predicted to grow and space transport RF could become comparable to global aviation RF in coming decades. Improved understanding of rocket emission RF requires more sophisticated modeling and improved data describing particle microphysics.

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Section: Emission Indices and Stratospheric Burdenmentioning

confidence: 99%

Radiative forcing caused by rocket engine emissions

Ross

Sheaffer

2014

Earth's Future

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“…This assessment will provide guidance for further investigation and for the enhancement of engineering level models. This work is a continuation of a previous study 4 that investigated mechanisms influencing the afterburning shutdown characteristics of rocket exhaust plumes.…”

mentioning

confidence: 89%

“…The simulations considered in this study were carried out for'a generic axisymmetric amine booster described in detail by Calhoon 4 . The exhaust nozzle was assumed to have an area ratio of 10 and protrude aft of the booster base.…”

Section: Rocket Plume Simulationsmentioning

confidence: 99%

“…The flame extinction phenomenon investigated by Calhoon 4 is a result of the interaction of turbulence and chemistry at small spatial scales. The model used by Calhoon 4 to account for this phenomenon was an elementary one applicable to high speed compressible flows.…”

mentioning

confidence: 99%

“…The model used by Calhoon 4 to account for this phenomenon was an elementary one applicable to high speed compressible flows. Other models do exist to more generally account for turbulence-chemistry interactions that are applicable to compressible flows.…”

mentioning

confidence: 99%

See 2 more Smart Citations

Assessment of Turbulence-Chemistry Interactions in Missile Exhaust Plume Signature Analysis

Calhoon

Kenzakowski

2003

Journal of Spacecraft and Rockets

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Real‐Time Plume Velocity Measurement of Solid Propellant Rocket Motors Using TDLAS Technique

Song

Zhao²,

et al. 2021

Propellants Explo Pyrotec

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Accurate measurement of plume velocity plays an important role in investigation of rocket motors, and the plume velocity is an indicator of energy level of solid propellants. A method based on laser Doppler effect using tunable diode laser absorption spectroscopy (TDLAS) is employed in this study. The absorption spectrum of water vapor feature at 1391.7 nm is utilized to measure the plume velocity. Three solid propellants, double‐base (DB), composite modified double‐base (CMDB), and nitrate ester plasticized polyether (NEPE) i. e., are burned in a motor with an internal diameter of 50 mm and their plume velocities are measured with scanned‐WMS‐2f technique. Afterburning reactions in the plume are numerically simulated. The simulations can provide insight into the nuances in measured TDLAS results and give confidence in the result. The results show that TDLAS is a good method to measure plume velocity. The relative standard deviation of the measurements is less than 4 %. The difference between the measured velocity and the simulated one is less than 8.25 %. Additionally, it is found that NEPE has the largest plume velocity, and the velocity of DB is the lowest. Uncertainties of velocity measurement using TDLAS are analyzed. Measurement uncertainty comes from velocity non‐uniformity in the direction perpendicular to the plume direction. Furthermore, it can be found that it is better to put the measurement position close to the nozzle exit to reduce measurement errors.

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Computational Assessment of Afterburning Cessation Mechanisms in Fuel-Rich Rocket Exhaust Plumes

Cited by 12 publications

References 19 publications

Radiative forcing caused by rocket engine emissions

Radiative forcing caused by rocket engine emissions

Assessment of Turbulence-Chemistry Interactions in Missile Exhaust Plume Signature Analysis

Real‐Time Plume Velocity Measurement of Solid Propellant Rocket Motors Using TDLAS Technique

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