Use of a large microphone array to identify noise sources during a rocket engine test firing and a rocket launch

2013 ◽  
Vol 134 (5) ◽  
pp. 4056-4056 ◽  
Author(s):  
Jayanta Panda ◽  
Robert N. Mosher ◽  
Barry J. Porter
Keyword(s):  
Microphone Array ◽  
Rocket Engine ◽  
Engine Test ◽  
Noise Sources ◽  
Rocket Launch ◽  
Test Firing

scholarly journals Cold flow testing of laboratory-scale hybrid rocket engine test apparatus.

2021 ◽  
Author(s):  
Shivanand R. Patil
Keyword(s):  
Rocket Engine ◽  
Low Frequency ◽  
System Stability ◽  
Engine Test ◽  
Test Apparatus ◽  
Hybrid Rocket ◽  
Cold Flow ◽  
Hybrid Rocket Engine ◽  
Hot Test ◽  
Test Firing

A cold-flow experimental investigation is performed on the Ryerson University lab-scale hybrid rocket engine test apparatus, in order to gain a further understanding of transient phenomena affecting the engine’s hot test firing results to date. The hot test firing data was characterized primarily by noticeable thrust oscillation magnitudes at low frequency being measured by the test stand’s thrust-measuring load cell, relative to somewhat lower magnitude low-frequency pressure oscillations being measured by a head-end pressure transducer. The present investigation allows for the evaluation of the fluid-structure interaction behaviour of the rocket engine’s combustion chamber and upstream oxidizer feed-line/injection apparatus (along with the surrounding test stand structure). Pressurized air at a moderate temperature acts as the working fluid (rather than hot gas arising from combustion), passing through the internal flow system, and exiting at the engine’s exhaust nozzle. Cold flow tests are conducted at three different flow-regulating orifice-plate conditions upstream of the head-end injector: 1) unchoked, 2) marginally choked and, 3) choked, in order to potentially observe any trends in that regard, as tied to feed-system stability/instability. The cold flow test results, from the experimental time-dependent measurement of pressure, thrust and axial acceleration, in turn undergo FFT analyses to help identify any frequency-dependent trends in regard to transient behaviour. Hammer tests are conducted to further establish the relevant lower frequency natural modes of structural vibration of the test apparatus with the engine in position The potential applicability of Karabeyoglu’s well-known thermal lag-combustion-gasdynamic predictive model (for estimating a characteristic frequency), which captures to some degree the intrinsic low frequency combustion-based instability behaviour of hybrid rocket engines, is considered for the present test engine setup. There are some promising comparisons in terms of relevant frequencies of mechanisms in the 20 Hz range, mechanisms that might be coupling to produce a noticeably augmented oscillation condition (as was observed in the hot firing thrust measurements).

scholarly journals Cold flow testing of laboratory-scale hybrid rocket engine test apparatus.

2021 ◽  
Author(s):  
Shivanand R. Patil
Keyword(s):  
Rocket Engine ◽  
Low Frequency ◽  
System Stability ◽  
Engine Test ◽  
Test Apparatus ◽  
Hybrid Rocket ◽  
Cold Flow ◽  
Hybrid Rocket Engine ◽  
Hot Test ◽  
Test Firing

A cold-flow experimental investigation is performed on the Ryerson University lab-scale hybrid rocket engine test apparatus, in order to gain a further understanding of transient phenomena affecting the engine’s hot test firing results to date. The hot test firing data was characterized primarily by noticeable thrust oscillation magnitudes at low frequency being measured by the test stand’s thrust-measuring load cell, relative to somewhat lower magnitude low-frequency pressure oscillations being measured by a head-end pressure transducer. The present investigation allows for the evaluation of the fluid-structure interaction behaviour of the rocket engine’s combustion chamber and upstream oxidizer feed-line/injection apparatus (along with the surrounding test stand structure). Pressurized air at a moderate temperature acts as the working fluid (rather than hot gas arising from combustion), passing through the internal flow system, and exiting at the engine’s exhaust nozzle. Cold flow tests are conducted at three different flow-regulating orifice-plate conditions upstream of the head-end injector: 1) unchoked, 2) marginally choked and, 3) choked, in order to potentially observe any trends in that regard, as tied to feed-system stability/instability. The cold flow test results, from the experimental time-dependent measurement of pressure, thrust and axial acceleration, in turn undergo FFT analyses to help identify any frequency-dependent trends in regard to transient behaviour. Hammer tests are conducted to further establish the relevant lower frequency natural modes of structural vibration of the test apparatus with the engine in position The potential applicability of Karabeyoglu’s well-known thermal lag-combustion-gasdynamic predictive model (for estimating a characteristic frequency), which captures to some degree the intrinsic low frequency combustion-based instability behaviour of hybrid rocket engines, is considered for the present test engine setup. There are some promising comparisons in terms of relevant frequencies of mechanisms in the 20 Hz range, mechanisms that might be coupling to produce a noticeably augmented oscillation condition (as was observed in the hot firing thrust measurements).

CALCULATION OF THE INTEGRAL NOISE LEVEL AT A FIELD POINT OF A FREE SUPERSONIC JET OF A ROCKET ENGINE

Akustika ◽  
2020 ◽  
Vol 36 (36) ◽  
pp. 22-24
Author(s):  
Anatoly Kochergin ◽  
Valeeva Ksenia
Keyword(s):  
Acoustic Field ◽  
Noise Level ◽  
Rocket Engine ◽  
Supersonic Jet ◽  
Noise Sources ◽  
Field Point

The paper considers an acoustic field created by a supersonic jet (CES) of a rocket engine freely flowing into flooded space. The acoustic field was presented in the form of a diagram of noise isobars, from which it can be seen that the acoustic field is formed by two effective noise sources: the nearest one, lying at a distance of 5-10 calibers from the nozzle cut and the far one, lying at a distance of 15-30 calibers from the nozzle cut.

scholarly journals Design and Experimental Investigation on Gas Oxygen/Kerosene Ejector Rocket for RBCC Application

2018 ◽  
Vol 36 (3) ◽  
pp. 558-564
Author(s):  
Xianggeng Wei ◽  
Fei Qin ◽  
Lei Shi ◽  
Baoqing Zhang ◽  
Guoqiang He
Keyword(s):  
Working Conditions ◽  
Rocket Engine ◽  
Combined Cycle ◽  
Engine Test ◽  
The Core ◽  
Technical Requirements ◽  
Core Components ◽  
Design Requirements ◽  
Working Parameters ◽  
Firing Tests

The ejector rocket is one of the core components of the rocket based combined cycle propulsion system, and must be capable of variable working conditions. In order to meet technical requirements for RBCC application, the variable duty operating ejector rocket using the gas Oxygen/Kerosene was designed based on the gas pressurized propellant feed systems. Hot firing tests of four different working conditions had been completed. Experimental results show that the designed ejector rocket engine was stable and reliable, and the working parameters met the design requirements, and the working conditions were adjusted quickly. It lays a foundation for the study of the RBCC engine test and the engine technology of large adjustment ratio.

Noise sources localization in the RRJ-95 aircraft pressure cabin by spherical microphone array. Part 1. Cockpit

2020 ◽  
Vol 27 (2) ◽  
pp. 37-51
Author(s):  
Petr Moshkov ◽  
Dmitry Vasilenkov ◽  
Victor Rubanovskii ◽  
Alexey Stroganov
Keyword(s):  
Microphone Array ◽  
Noise Sources

Noise sources localization in the RRJ-95 aircraft pressure cabin by spherical microphone array. Part 2. Passenger cabin

2020 ◽  
Vol 27 (3) ◽  
pp. 60-72
Author(s):  
Petr Moshkov ◽  
Dmitry Vasilenkov ◽  
Victor Rubanovskii ◽  
Alexey Stroganov
Keyword(s):  
Microphone Array ◽  
Noise Sources ◽  
Passenger Cabin

Airframe noise measurements on JAXA Jet Flying Test Bed “Hisho” using a phased microphone array

2017 ◽  
Vol 16 (4-5) ◽  
pp. 255-273 ◽  
Author(s):  
Takehisa Takaishi ◽  
Hiroki Ura ◽  
Kenichiro Nagai ◽  
Yuzuru Yokokawa ◽  
Mitsuhiro Murayama ◽  
...  
Keyword(s):  
Microphone Array ◽  
Low Frequency ◽  
Landing Gear ◽  
Frequency Resolution ◽  
Test Bed ◽  
Noise Sources ◽  
Low Frequencies ◽  
Airframe Noise ◽  
Noise Measurements ◽  
Wooden Platform

In 2015, the Japan Aerospace Exploration Agency launched the Flight demonstration of QUiet technology to Reduce nOise from High-lift configurations project to verify by flight demonstration the feasibility of practical noise-reducing aircraft modification concepts. In order to serve as a baseline for comparison before modification, airframe noise sources of the JAXA Jet Flying Test Bed “Hisho” were measured with a 30 m diameter array of 195 microphones mounted on a wooden platform built temporary beside the runway of Noto Satoyama Airport in Japan. A classical Delay and Sum in the time domain beamforming algorithm was adapted for the present study, with weight factors introduced to improve the low-frequency resolution and autocorrelations eliminated to suppress wind noise at high frequencies. In the landing configuration at idle thrust, the main landing gear, nose landing gear, and side edges of the six extended flap panels were found to be the dominant “Hisho” airframe noise sources. Deconvolution by the DAMAS and CLEAN-SC algorithms provided clearer positions of these sound sources at low frequencies. Integration of acoustical maps agreed well with the sound pressure level measured by a microphone placed at the center of the microphone array and gave detailed information about the contribution of each noise source.

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