TY - GEN
T1 - Method for determining nozzle throat erosion history in hybrid rockets
AU - Kamps, Landon
AU - Saito, Yuji
AU - Kawabata, Ryosuke
AU - Takahashi, Yusuke
AU - Nagata, Harunori
N1 - Publisher Copyright:
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
Copyright:
Copyright 2020 Elsevier B.V., All rights reserved.
PY - 2016
Y1 - 2016
N2 - The authors introduce a new reconstruction technique titled Nozzle Throat Reconstruction Technique or NTRT to estimate nozzle throat erosion history and oxidizerto-fuel mass ratio history in hybrid rockets. Nine five-second static firing tests were carried out on a 2kN-class Cascaded Multistage Impinging-jet type hybrid rocket motor under varying oxidizer flowrates to evaluate the accuracy of NTRT results. Nozzle throat erosion histories calculated by NTRT agreed well with measured values for initial and final nozzle throat radius, and successfully reconstructed the case where no measureable amount of nozzle throat erosion occurred. For equivalence ratios 0.6-1.4, the relationship between nozzle throat erosion rate and equivalence ratio determined by NTRT displays a trend consistent with chemical kinetic limited heterogeneous combustion theory, as well as predictions made by previous researchers. A numerical simulation was carried out to investigate the applicability of an alternative computational technique which uses a nozzle exit pressure measurement as input data, and revealed that pressure in vicinity of the static pressure port is likely to deviate from centerline pressure by up to 0.1 [MPa] or 30%.
AB - The authors introduce a new reconstruction technique titled Nozzle Throat Reconstruction Technique or NTRT to estimate nozzle throat erosion history and oxidizerto-fuel mass ratio history in hybrid rockets. Nine five-second static firing tests were carried out on a 2kN-class Cascaded Multistage Impinging-jet type hybrid rocket motor under varying oxidizer flowrates to evaluate the accuracy of NTRT results. Nozzle throat erosion histories calculated by NTRT agreed well with measured values for initial and final nozzle throat radius, and successfully reconstructed the case where no measureable amount of nozzle throat erosion occurred. For equivalence ratios 0.6-1.4, the relationship between nozzle throat erosion rate and equivalence ratio determined by NTRT displays a trend consistent with chemical kinetic limited heterogeneous combustion theory, as well as predictions made by previous researchers. A numerical simulation was carried out to investigate the applicability of an alternative computational technique which uses a nozzle exit pressure measurement as input data, and revealed that pressure in vicinity of the static pressure port is likely to deviate from centerline pressure by up to 0.1 [MPa] or 30%.
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U2 - 10.2514/6.2016-4747
DO - 10.2514/6.2016-4747
M3 - Conference contribution
AN - SCOPUS:85088408863
SN - 9781624104060
T3 - 52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016
BT - 52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016
Y2 - 25 July 2016 through 27 July 2016
ER -