Gotowe bibliografie tematyczne / Launch Vehicle Noise

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Gotowa bibliografia na temat „Launch Vehicle Noise”

Autor: Grafiati

Data publikacji: 6 września 2023

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Artykuły w czasopismach na temat "Launch Vehicle Noise"

Moats, Levi T., Matthew G. Yancey, Grant W. Hart i Kent L. Gee. "Assessing azimuthal asymmetry in the noise radiation from a three-core launch vehicle during liftoff". Journal of the Acoustical Society of America 153, nr 3_supplement (1.03.2023): A42. http://dx.doi.org/10.1121/10.0018089.

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Creating accurate rocket noise models is important for assessing impacts on humans, the environment, and payloads. The United Launch Alliance Delta IV Heavy launch vehicle is unique because of the separation of the three cores and their associated RS-68A nozzles. This makes it a good candidate for determining how the asymmetry of nozzle configuration affects noise radiation, which can affect noise models. The NROL-82 and NROL-91 missions both launched from Vandenberg Spaceforce Base using Delta IV Heavy Vehicles. For both of these launches, acoustic data were recorded between ∼0.9 and ∼5.2 km from the vehicle at different azimuths to determine the extent of azimuthal asymmetry in noise radiation. Maximum overall sound pressure level, spectra, and overall power level were determined for each launch. Methods for comparing the datasets and results will be discussed.

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James, Michael M., i Alexandria R. Salton. "Modeling community noise impacts from launch vehicle propulsion noise". Journal of the Acoustical Society of America 142, nr 4 (październik 2017): 2490. http://dx.doi.org/10.1121/1.5014090.

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Krishna, Ajay. "A Review on Vibro-Acoustic Analysis of a Launch Vehicle Structure". International Journal for Research in Applied Science and Engineering Technology 10, nr 6 (30.06.2022): 4154–57. http://dx.doi.org/10.22214/ijraset.2022.44873.

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Abstract: Space vehicles are subjected to significant dynamic pressure loads when their rocket propulsion systems are in use during flying missions. During the aerodynamic and launch phases, launch vehicles, payloads, and their parts are subjected to extremely high random acoustic loads. The noise from the engine exhaust gas, aerodynamic boundary layer noise, transonic buffering, structure-borne vibration, engine thrust fluctuation, etc. is the source of these loads, which also result in a secondary acoustic load. When the vehicle is lifting off and traveling at a speed greater than Mach number, acoustic stresses to the spacecraft and payload are very harsh and significant. This loading causes the structure to vibrate randomly, which could be dangerous for some vehicle parts, avionics, propulsion systems, and payloads like satellites. This paper discusses the vibration of the structure subjected to acoustic excitation on a diffuse acoustic field and the software used for the analysis.

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Cunningham, Carson F., Kent L. Gee, Grant W. Hart, Mark C. Anderson, Michael Bassett, Logan T. Mathews, Jeffrey T. Durrant i in. "Initial findings from Space Launch System liftoff measurements". Journal of the Acoustical Society of America 153, nr 3_supplement (1.03.2023): A71. http://dx.doi.org/10.1121/10.0018198.

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This presentation documents initial findings from far-field noise measurements at NASA’s Kennedy Space Center during liftoff of the Space Launch System’s Artemis I mission, which occurred on November 16, 2022. The vehicle— the most powerful ever successfully launched into orbit—consists of four liquid-fueled RS-25 engines and two five-segment, solid-fuel rocket boosters (SRBs). Because this was the first launch, the noise radiation characteristics of this vehicle were previously unknown. Overall sound pressure levels, waveform characteristics, and spectra are described at distances ranging from 1.5 to 8.4 km. The levels due to the SRBs’ ignition overpressure are particularly intense in the direction of the flame trench exit. The post-liftoff maximum one-third octave spectrum has a peak at 20 Hz, and maximum overall levels are greater than described in a pre-launch environmental assessment. These and other findings presently submitted to JASA Express Letters further understanding of super heavy-lift rocket acoustics.

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Roper, Jack. "Absolute Zero". Industrial Vehicle Technology International 28, nr 4 (listopad 2020): 26–32. http://dx.doi.org/10.12968/s1471-115x(23)70342-5.

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ONE ALL-ELECTRIC MACHINE IS A STEP TOWARDS LOW NOISE AND ZERO EMISSIONS, BUT IF IT'S SURROUNDED BY DIESEL SUPPORT VEHICLES THE JOB IS ONLY PART DONE. WITH THE LAUNCH OF ITS NEW EXCAVATOR WACKER NEUSON COMPLETES A VEHICLE TEAM THAT CAN DELIVER A FULLY ELECTRIC WORK ZONE

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Henderson, Benjamin K., Steven A. Lane, Joel Gussy, Steve Griffin i Kevin M. Farinholt. "Development of an acoustic actuator for launch vehicle noise reduction". Journal of the Acoustical Society of America 111, nr 1 (styczeń 2002): 174–79. http://dx.doi.org/10.1121/1.1420383.

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Yancey, Matthew G., Levi T. Moats, Mylan R. Cook, Lucas K. Hall, Mark C. Anderson, Grant W. Hart i Kent L. Gee. "Acoustic overview of the Delta-IV Heavy NROL-91 launch". Journal of the Acoustical Society of America 153, nr 3_supplement (1.03.2023): A42. http://dx.doi.org/10.1121/10.0018088.

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As commercial space launches continue to become more common, there is increasing interest in the subject of noise. The United Launch Alliance Delta IV Heavy is particularly interesting because of its three-core design with three widely separated engines. Measurements made by Brigham Young University at the NROL-91 launch on September 24, 2022, feature several microphones placed in an arc surrounding the launch facilities of the NROL-91 launch, ranging in distance from 670 m to 1.8 km. In addition, two long-range measurement locations (13.4 and 19.5 km) were included for propagation comparisons with an earlier Delta IV Heavy launch measurement (NROL-82). This presentation focuses on a description of the measurement made and several results, including spectra, directivity, and the sound power level calculated for the launch vehicle, as well as comparisons with the NROL-82 data.

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Mathews, Logan T., Kent L. Gee i Grant W. Hart. "Characterization of Falcon 9 launch vehicle noise from far-field measurements". Journal of the Acoustical Society of America 150, nr 1 (lipiec 2021): 620–33. http://dx.doi.org/10.1121/10.0005658.

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Kemp, Jonathan D., i Robert L. Clark. "Noise reduction in a launch vehicle fairing using actively tuned loudspeakers". Journal of the Acoustical Society of America 108, nr 5 (listopad 2000): 2478. http://dx.doi.org/10.1121/1.4743141.

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Salton, Alexandria R., Michael M. James, Matthew F. Calton, Kent L. Gee, Reese D. Rasband, Daniel J. Novakovich i Brent O. Reichman. "Launch vehicle acoustic measurements for community noise model development and validation". Journal of the Acoustical Society of America 144, nr 3 (wrzesień 2018): 1673. http://dx.doi.org/10.1121/1.5067452.

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Rozprawy doktorskie na temat "Launch Vehicle Noise"

Karthikeyan, N. "On the Contribution of the Launch Platform towards Acoustic Environment of a Launch Vehicle at Lift-off". Thesis, 2017. http://etd.iisc.ac.in/handle/2005/4313.

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A launch vehicle experiences intense acoustic loading in the initial phase of its lift-off due to the noise generated by the rocket exhaust. This affects the launch vehicle structure in addition to sensitive payloads and may result in their failure. The launch vehicle structure has to be specially stiffened to withstand such loading which adversely affects its payload capabilities. Therefore, the mitigation of the lift-off acoustic environment of the launch vehicle is of utmost importance. At lift-off, the components of launch environment such as the launch platform and jet blast deflector contribute to the intense acoustic loads experienced by the launch vehicle by either reflecting the noise generated by the rocket jet exhaust or by creating additional sources of noise. Though the effect of jet blast deflector shape on the acoustic loading has been extensively investigated, contributions from other launch structures such as the launch platform are often ignored. The present work attempts to characterize the acoustic behaviour of the launch platform by simulating a scaled down launch vehicle environment at lift-off, inside an anechoic chamber. The lift-off scenario was simulated by allowing jets from single and twin jet launch vehicle models to impinge on flat plates with and without cut-outs, at varying lift-off distances. The results from the acoustic measurements carried out in the near and far-field of the launch vehicle models show that the presence of the cut-outs have significant effect on the near-field acoustics of the launch vehicle at low lift-off distances(L/De). The acoustic field in the vicinity of the launch vehicle is found to be considerably lower than that obtained when jets impinged on solid flat plates without cut-outs. The influence of the cut-outs, diminishes at higher L/De, when a large fraction of the jet, in addition to flowing through the cut-outs, impinges on the launch platform. The study also explores a new concept of including perforations in the launch platform as a means to attenuate the its contribution to the acoustic levels experienced by the launch vehicle. The inclusion of perforations in the launch platform, decreased the surface area of the launch platform available for jet impingement at higher L/De, thereby reducing the acoustic levels experienced by the launch vehicle at these lift-off distances. The perforated launch platform is found to be effective even with the presence of jet blast deflector, all the way up to 16 nozzle diameters after lift-off. Flow visualizations using schlieren technique indicate that the effectiveness of the perforations stem from the fact that they reduce the strength of the flow features such as wall jets and fountain flow - that are characteristic of jet impingement. The thesis brings out the significant contribution to the lift-off noise from a typical launch platform and the role of flow features like the wall jets and the fountain flow towards noise generation. It is shown that an attenuation of about 4-5 dB can be achieved at L/De>8 by perforating the platform. An optimal design of the launch platform incorporating the perforations can considerably reduce the acoustic loading of the launch vehicle thereby increasing its payload capabilities and ensuring its safety.

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Streszczenia konferencji na temat "Launch Vehicle Noise"

Griffin, Steven F., Steven A. Lane i Donald J. Leo. "Power Consumption for Active Acoustic Control of Launch Vehicle Payload Fairings". W ASME 2000 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/imece2000-1693.

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Abstract Vibroacoustics during space vehicle launch has been blamed for as many as 60% of first day satellite failures. At the Air Force Research Laboratory in Albuquerque NM USA, modeling and analysis was performed to determine the feasibility of monolithic piezoceramic actuators and active acoustic control to reduce noise transmission during launch of the OSP launch vehicle with a hypothetical composite fairing. Voltage, power and energy were studied as a function of transmission reduction. The conclusion reached for the case explored in depth was that off-the-shelf monolithic piezoceramic actuators did not have sufficient control authority to reduce noise transmission at realistic sound levels.

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Sescu, Adrian, Eric Collins, Robert E. Harris i Edward A. Luke. "Assessing Acoustic Source Forcing Tools for Launch Vehicle Jet Noise Prediction". W 21st AIAA/CEAS Aeroacoustics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-2381.

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Hersh, A., B. Walker, J. Celano, H. Osman i C. Mitchell. "Control of very low frequency noise in launch vehicle payload fairings". W 6th Aeroacoustics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-1919.

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Kandula, Max. "Some Perspectives on Jet Noise with Relevance to Launch Vehicle Acoustics". W 28th AIAA/CEAS Aeroacoustics 2022 Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2022. http://dx.doi.org/10.2514/6.2022-3026.

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KENNEDY, W., P. VAN LAAK, H. SCARTON i L. MYRABO. "Simulation of acoustic noise generated by an airbreathing, beam-powered launch vehicle". W 24th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-2971.

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Kennedy, W. C. "Simulation of Acoustic Noise Generated by an Airbreathing, Beam-Powered Launch Vehicle". W BEAMED ENERGY PROPULSION: Third International Symposium on Beamed Energy Propulsion. AIP, 2005. http://dx.doi.org/10.1063/1.1925147.

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Gely, D., G. Elias, C. Bresson, H. Foulon, S. Radulovic i Ph Roux. "Reduction of supersonic jet noise - Application to the Ariane 5 launch vehicle". W 6th Aeroacoustics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-2026.

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Frampton, Kenneth D. "Decentralized Vibration Control in a Launch Vehicle Payload Fairing". W ASME 2002 International Mechanical Engineering Congress and Exposition. ASMEDC, 2002. http://dx.doi.org/10.1115/imece2002-33352.

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The vibro-acoustic environment inside a launch vehicle payload fairing is extremely violent resulting in excessive development costs for satellites and other payloads. The development of smart structures and active noise and vibration control technologies promised to revolutionize the design, construction and, most importantly, the acoustic environment within these fairings. However, the early promise of these technologies has not been realized in such large-scale systems primarily because of the excessive complexity, cost and weight associated with centralized control systems. Now, recent developments in MEMS sensors and actuators, along with networked embedded processor technology, have opened new research avenues in decentralized controls based on networked embedded systems. This work describes the development and comparison of decentralized control systems that utilize this new control paradigm. The controllers are hosted on numerous nodes, possessing limited computational capability, sensors and actuators. Each of these nodes is also capable of communicating with other nodes via a wired or wireless network. The constraints associated with networked embedded systems control that the control systems be relatively simple computationally, scalable and robust to failures. Simulations were conducted that demonstrate the ability of such a control architecture to attenuate specific structural modes.

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Motlagh, Amin M., Mohammad H. Elahinia, Mohammad Abuhaiba i Walter W. Olson. "Application of Smart Materials for Noise and Vibration of Hydraulic Systems". W ASME 2007 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/detc2007-34317.

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As market demands vehicles with higher performance, lower fuel consumption, and less emission, hybrid vehicles receive increasing attention. Hybrid technologies have been developed for both passenger and heavy-duty vehicles. Hydraulic hybrid is a technology that is specifically suitable for heavy SUVs and trucks. Despite beneficial aspects of hydraulic systems in reducing the fuel consumption and increasing the launch acceleration for these vehicles, hydraulic vibration and noise is barrier in commercializing this technology. Many studies have been performed on noise and vibration problems of hydraulic systems and many solutions have been proposed. This paper, after introducing the hydraulic hybrid vehicle technology and conventional hydraulic systems in vehicles, reviews the state of the art of the solutions developed for hydraulic noise and vibration. The focus is on the sources of hydraulic noise and vibration. Different approaches for reducing the noise and vibration in hydraulic systems have been reviewed with an emphasis on the application of smart materials. These existing solutions are examined and evaluated for mitigating noise and vibration in hydraulic hybrid vehicles.

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Wang, Hui, Yuanyuan Liu i Zheng-Dong Ma. "Sub-Frame Design for a Hydraulic Hybrid Vehicle System". W ASME 2005 International Mechanical Engineering Congress and Exposition. ASMEDC, 2005. http://dx.doi.org/10.1115/imece2005-81557.

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Hybrid vehicles are gaining increasing popularity in recent years, and there are three major types of hybrid systems, hybrid hydraulic, hybrid electric, and hybrid fuel cell. The hydraulic system offers great advantages for vehicles operating in stop-and-go conditions because the reversible hydraulic pump/motor can capture large amounts of energy when the brakes are applied, and this energy is released through the hydraulic pump/motor to propel the vehicle. The key component in this new system is a HLA (Hydraulic Launch Assist) unit, which employs an advanced hydraulic hybrid power train system. Technical challenges with hydraulic hybrids include packaging and noise issues. HLA is an over 600 lbs system, and to fit it into a traditional designed vehicle, as well as to fit possibly multiple candidate platforms, the design of a sub-frame that can mount the HLA to the vehicles is a critical task. Because HLA system development is an on-going work, different structural problems emerge during this process. Therefore, an efficient design system is necessary to address the problems in the up-front design stage. Function-Oriented Material Design (FOMD) with special topology optimization techniques, such as multi-domain multi-step topology optimization, is a tool suitable for this task. The theoretical background is described and sub-frame design process is summarized in this paper. The effectiveness of the design system is demonstrated through design examples. The design method and procedure proposed in this paper is applicable to other vehicle structural design problems, which will reduce the design cycle and achieve the required functionalities in an efficient way.

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Raporty organizacyjne na temat "Launch Vehicle Noise"

Howard, Carl Q., i Colin Hansen. Investigation of Passive Control Devices for Potential Application to a Launch Vehicle Structure to Reduce the Interior Noise Levels During Launch. Fort Belvoir, VA: Defense Technical Information Center, maj 2006. http://dx.doi.org/10.21236/ada473434.

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