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Artykuły w czasopismach na temat „Launch Vehicle Noise”

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Data publikacji: 6 września 2023

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1

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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2

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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4

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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5

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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6

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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7

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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8

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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9

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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10

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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11

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 113, nr 4 (kwiecień 2003): 1986–94. http://dx.doi.org/10.1121/1.1558371.

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12

Cook, Mylan R., Kent L. Gee, Carson F. Cunningham i Grant W. Hart. "Vector acoustic intensity analysis of noise from the Delta IV Heavy launch vehicle during liftoff". Journal of the Acoustical Society of America 153, nr 3_supplement (1.03.2023): A42. http://dx.doi.org/10.1121/10.0018087.

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The noise sources within a turbulent rocket plume are not well understood, let alone the radiation from multiple rocket nozzles. Even less is known about the noise sources during launch vehicle liftoff. This paper seeks to simultaneously address these noise source analysis challenges using data collected during the NROL-82 Delta IV Heavy (DIVH) launch from Vandenberg Space Force Base. The three-core DIVH’s liftoff noise was measured by a ground-based four-microphone array at a distance of 330 m. Hart et al. [Proc. Mtgs. Acoust. 45, 040003 (2022)] previously used this array with a cross-correlation technique to identify the overall noise source radiation locus as it switched from the flame trench exit to about 55 m downstream of the nozzle exit plane. Here, vector intensity is used to localize the frequency-dependent noise source axial distribution using a variant of the phase and amplitude gradient estimator method for acoustic intensity [Thomas et al., J. Acoust. Soc. Am. 137, 3366–3376 (2015)]. The results help clarify a complex noise source generation process that is both time and frequency-dependent and involves both free and impinging jet noise phenomena.

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13

Escartí-Guillem, Mara S., Luis M. García-Raffi i Sergio Hoyas. "URANS Analysis of a Launch Vehicle Aero-Acoustic Environment". Applied Sciences 12, nr 7 (25.03.2022): 3356. http://dx.doi.org/10.3390/app12073356.

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Predicting and mitigating acoustic levels become critical because of the harsh acoustic environment during space vehicle lift-off. This paper aimed to study the aero-acoustic environment during a rocket lift-off. The sound propagation within a launch event was studied using dedicated computational fluid dynamics (CFD). The resolution of all the phenomena that occur is unfeasible. We discuss the turbulence simplification and propose a feasible simulation through an unsteady Reynolds-averaged Navier–Stokes (URANS) model. The results were validated with experimental data showing a good correlation near the fairing surface and an improvable accuracy in the far field. To assess noise generation, the main shock waves were identified, and the evolution of the generated sound pressure was assessed. Moreover, vertical directivity was revealed by data analysis of the pressure field surrounding the fairing.

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14

Gee, Kent L. "The roar of the rocket: A hot topics discussion". Journal of the Acoustical Society of America 152, nr 4 (październik 2022): A189. http://dx.doi.org/10.1121/10.0015981.

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An increasing number of companies and countries are building and launching space vehicles of different sizes and configurations for diverse purposes. The goal of this Hot Topics presentation is two-fold: first, to introduce a wide-ranging audience of Acoustical Society of America members to principles of rocket noise radiation, propagation, and reception; second, to discuss needs and challenges related to future launch vehicle acoustics research. If attendees leave both mildly entertained and better informed, the presentation will have been a success.

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15

Lubert, Caroline P., Kent L. Gee i Seiji Tsutsumi. "Insights into heated, supersonic jet noise gained from writing a review article on launch vehicle noise". Journal of the Acoustical Society of America 150, nr 4 (październik 2021): A176. http://dx.doi.org/10.1121/10.0008037.

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16

Tinney, Charles. "The effect of nozzle contour on the vibroacoustic loads that form from high area ratio rocket nozzles during sea level launch". Journal of the Acoustical Society of America 153, nr 3_supplement (1.03.2023): A42. http://dx.doi.org/10.1121/10.0018085.

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An accurate assessment of the vibro-acoustic loads that form during startup of large area ratio rocket nozzles is important for sea-level launch vehicle design and certification. These loads are driven principally by various flow and shock patterns that form inside the nozzle, which are unique to the nozzle contour. This presentation will review a number of laboratory-scale measurements of different nozzle contours and configurations reported by Baars and Tinney, Exp. Fluids, (2013), Donald et al. AIAA Journal (2014), Canchero etal. AIAA Journal (2016), and Rojo et al. AIAA Journal (2016) as it relates to launch platforms of current interest. In particular are the various sources of noise pertaining to transonic resonance, broadband shock associated noise, and the end-effects-regime (EER). The latter of these is unique to the thrust-optimized parabolic contour nozzle as is used on the current Space Launch System vehicle. This EER event occurs when the annular flow structure is in a partial restricted-shock separated (RSS) flow state and is categorized by an onset of relatively low frequency energy driven by intermittent buffeting between RSS flow and partial free shock separated flow at the nozzle lip.

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17

Ignatius, Jopaul K., S. Sankaran, R. Ashok Kumar, T. N. V. Satyanarayana i Satyanarayanan R. Chakravarthy. "Suppression of Jet Noise by Staged Water Injection during Launch Vehicle Lift-Off". International Journal of Aeroacoustics 7, nr 3-4 (wrzesień 2008): 223–41. http://dx.doi.org/10.1260/1475-472x.7.3.223.

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18

Kang, Jun, Zhi Xiong, Rong Wang i Ling Zhang. "Multi-Layer Fault-Tolerant Robust Filter for Integrated Navigation in Launch Inertial Coordinate System". Aerospace 9, nr 6 (24.05.2022): 282. http://dx.doi.org/10.3390/aerospace9060282.

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As to an aerospace vehicle, the flight span is large and the flight environment is complex. More than that, the existing navigation algorithms cannot meet the needs to provide accurate navigation parameters for aerospace vehicles, which results in the decline of navigation accuracy. This paper proposes a multi-layer, fault-tolerant robust filtering algorithm of aerospace vehicle in the launch inertial coordinate system to address this problem. Firstly, the launch inertial coordinate system is used as the reference coordinate system for navigation calculation, and the state equation and measurement equation of the navigation system are established in this coordinate system to improve the modeling accuracy of the navigation system. On this basis, a multi-layer, fault-tolerant robust filtering algorithm is designed to estimate and compensate the unknown input in the state equation in real time and adjust the noise variance matrix in the measurement equation adaptively. Simulation results show that the errors about the integrated navigation system output parameters are reduced, through this algorithm, which improves the attitude, velocity and position estimation accuracy of the integrated navigation system. In addition, the algorithm enhances the fault tolerance and robustness of the filtering algorithm.

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19

Guo, Rong, Hao Chen i Meng-Jia Wang. "Modeling and active control of power-split hybrid electric vehicle launch vibration". Journal of Low Frequency Noise, Vibration and Active Control 38, nr 2 (14.12.2018): 592–607. http://dx.doi.org/10.1177/1461348418817888.

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One of the key challenges with the development of hybrid electric vehicles is the noise, vibration, and harsh behavior, specifically the uncomfortable ride experience during launch. This paper focuses on the driveline vibration caused by the quick response of the traction motor in the launch condition of hybrid electric vehicles. A torsional vibration differential equation for frequency analysis, including a Ravigneaux planetary gear set, a reducer, a differential, half shafts, and wheels, is thus built. Based on the equation, many components of the power-split system are simplified to make the controller design easy. Finally, wave superposition control strategy has been proposed to suppress the vibration, in which the concept is delaying part of the input to superimpose with the original input to eliminate the output wave. In order to optimize the control effect, parameters of the controller are chosen according to the system response. The simulation outcomes demonstrate that wave superposition control strategy is effective in attenuating the vibration generated by hybrid electric vehicles during launch conditions.

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20

Stoica, Adrian-Mihail, Costin Ene i Istvan-Barna Jakab. "A discrete-time Kalman filtering method for launch vehicle under parametric modelling uncertainty". MATEC Web of Conferences 304 (2019): 07008. http://dx.doi.org/10.1051/matecconf/201930407008.

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The paper presents a Kalman filtering problem for discrete–time linear systems with parametric uncertainties. A stochastic model with multiplicative noise both in the state and in the output equations is used to represent the system with uncertain parameters. The solution of the filtering problem is a Kalman type filter which gain is determined by solving the H2 optimization problem for the resulting system obtained by coupling the filter with the stochastic system. It is proved that the optimal gain of the filter may be computed by solving a trace minimization problem with constraints expressed in terms of a system of matrix inequalities. The proposed filtering approach is illustrated by a case study aiming to estimate the states of the pitch dynamics of a space launch vehicle in its center of mass.

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21

Xing, Chenglong, Guigao Le i Hanyu Deng. "Numerical study on jet noise suppression with water injection during one-nozzle launch vehicle lift-off". Engineering Applications of Computational Fluid Mechanics 16, nr 1 (19.05.2022): 1173–94. http://dx.doi.org/10.1080/19942060.2022.2072953.

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22

NEILSEN, Tracianne B., Kent L. GEE i Michael M. JAMES. "Analysis of the Effects of Finite Impedance Ground and Atmospheric Turbulence on Launch Vehicle Noise Measurements". TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 14, ists30 (2016): Po_2_1—Po_2_7. http://dx.doi.org/10.2322/tastj.14.po_2_1.

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23

Himelblau, Harry, i Allan Piersol. "Evaluation of a Procedure for the Analysis of Nonstationary Vibroacoustic Data". Journal of the IEST 32, nr 2 (1.03.1989): 35–42. http://dx.doi.org/10.17764/jiet.1.32.2.f751r7g1321863v5.

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Much of the structural vibration and aeroacoustic noise of aerospace vehicles is nonstationary random. Methodology for nonstationary data analysis exists, but the procedure requires measurements from repeated flights, which is often impractical. An alternative parametric procedure can be applied to individual records under the assumption that the data have a specific type of nonstationarity. A type of parametric model, called the product model, and a special case, called the locally stationary model, are described and applied to space vehicle launch data. A nonstationary procedure is presented and evaluated using launch vibration data measured at a Shuttle Orbiter/payload interface. The procedure permits a longer sampling duration to be used for spectral analysis as compared with the traditional short-duration method, significantly reducing random errors. In this evaluation, only modest differences were observed between the two types of "raw" spectra. However, when random errors were taken into account (large for the traditional method and small for the nonstationary procedure), the short-duration spectra exceeded those for the nonstationary procedure by a significant amount. Thus unnecessarily high vibration spectra can be avoided using the nonstationary procedure.

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24

Gee, Kent L., Grant W. Hart i Caroline P. Lubert. "A brief rocket noise introduction for the interested ASA meeting attendee". Journal of the Acoustical Society of America 153, nr 3_supplement (1.03.2023): A41. http://dx.doi.org/10.1121/10.0018082.

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It can be difficult for ASA meeting attendees to find an entry point into topical special sessions; they may be interested in learning about a field outside their own but are unfamiliar with terminology, physical processes, and the challenges that motivate different research studies. For the topic of rocket noise, this presentation is intended to help attendees from different ASA technical areas feel more prepared to understand the significance and details of the other talks in this session. But because there is far more to discuss than can be addressed in a single presentation, attendees are also referred to a recent review article on launch vehicle acoustics [C. P. Lubert et al., J. Acoust. Soc. Am. 151, 752-791 (2022)].

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25

Tauhid Ahmad, Noor Hidayah, Nurliza Salim, Adhwa Amir Tan, Syahrim Azhan Ibrahim i Maszlan Ismail. "High-Intensity Acoustic Chamber System Spectrum Profiling for Satellite Launching Environment". Applied Mechanics and Materials 793 (wrzesień 2015): 605–9. http://dx.doi.org/10.4028/www.scientific.net/amm.793.605.

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Assembly, Integration and Test Centre at National Space Agency (ANGKASA) consist of Reverberation Acoustic Test Facility (RATF). The test facility are used to generate very high sound pressure levels for satellite testing, space vehicle components including flight hardware. This reverberant type of chamber is capable to simulate acoustic field of rocket launch. This paper is discussed on the requisite of high-intensity acoustic testing. The characteristic of chamber and the noise generating capabilities for high-intensity acoustic testing are described. The maximum requirement of chamber at 155dB spectrum profiling result is discussed in this paper.

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26

Srinivasan, R., B. Lakshmi i Tessy Thomas. "An Architecture for On board Frequency Domain Analysis of Launch Vehicle Vibration Signals". Defence Science Journal 73, nr 1 (13.03.2023): 3–10. http://dx.doi.org/10.14429/dsj.73.17690.

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The dynamic properties of the airborne structures plays a crucial role in the stability of the vehicle during flight. Modal and spectral behaviour of the structures are simulated and analysed. Ground tests are carried out with environmental conditions close to the flight conditions, with some assumptions. Subsequently, based on the flight telemetered data, the on-board mission algorithm and the auto-pilot filter coefficients are fine tuned. An attempt is made in this paper to design a novel architecture for analysing the modal and spectral random vibration signals on-board the flight vehicle and to identify the dominant frequencies. Based on the analysed results, the mission mode algorithm and the filter coefficients can be fine tuned on-board for better effectiveness in control and providing more stability. Three types of windows viz. Hann, Hamming and Blackman-Harris are configured with a generalised equation using FIR filter structure. The overlapping of the input signal data for better inclusiveness of the real-time data is implemented with BRAM. The domain conversion of the data from time domain to frequency domain is carried out with FFT using Radix-2 BF architecture. The FFT output data are processed for calculating the power spectral density. The dominant frequency is identified using the array search method and Goldschmidt algorithm is utilised for the averaging of the PSDs for better precision. The proposed architecture is synthesised, implemented and tested with both Synthetic and doppler signal of 300 Hz spot frequency padded with Gaussian white noise. The results are highly satisfactory in identifying the spot frequency and generating the PSD array.

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Chocat, Rudy, Loïc Brevault, Mathieu Balesdent i Sébastien Defoort. "Modified Covariance Matrix Adaptation – Evolution Strategy algorithm for constrained optimization under uncertainty, application to rocket design". International Journal for Simulation and Multidisciplinary Design Optimization 6 (2015): A1. http://dx.doi.org/10.1051/smdo/2015001.

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The design of complex systems often induces a constrained optimization problem under uncertainty. An adaptation of CMA-ES(λ, μ) optimization algorithm is proposed in order to efficiently handle the constraints in the presence of noise. The update mechanisms of the parametrized distribution used to generate the candidate solutions are modified. The constraint handling method allows to reduce the semi-principal axes of the probable research ellipsoid in the directions violating the constraints. The proposed approach is compared to existing approaches on three analytic optimization problems to highlight the efficiency and the robustness of the algorithm. The proposed method is used to design a two stage solid propulsion launch vehicle.

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Hu, Mengya, i Yi Jiang. "Research on the High Speed of Piston Pumps Based on Rapid Erecting of Launch Vehicles". Applied Sciences 13, nr 12 (15.06.2023): 7178. http://dx.doi.org/10.3390/app13127178.

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Rapid erection is a key technology for modern warfare in vehicle weapon launch systems. It is challenging to attain rapidity with the hydraulic erecting system because of the intensified cavitation in the piston chamber at high speeds, which reduces volumetric efficiency and increases flow pulsation in the typical high-pressure axial piston pump. In this paper, an improved scheme for the cylinder window area overflow surface was proposed to solve this problem. Based on the full cavitation model and the compressible model, a numerical model of the internal flow in the piston pump was developed, and the effect of rotational speeds on the flow and cavitation characteristics of the pump was analysed. The results show that after the improvement, the maximum flow of the pump is increased from 1.765 kg/s to 2.295 kg/s, an increase of 30.028%, and the maximum speed corresponding to the volumetric efficiency of more than 90% is increased from 1500 rpm to 2100 rpm. At high speeds, the improved block can effectively suppress the cavitation and backflow in the piston chamber, improve the volumetric efficiency of the piston pump and reduce the flow pulsation, which is conducive to reducing the vibration and noise of the pump body.

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Weissman, Karen, Mark McNelis i William Pordan. "Implementation of Acoustic Blankets in Energy Analysis Methods with Application to the Atlas Payload Fairing". Journal of the IEST 37, nr 4 (1.07.1994): 32–39. http://dx.doi.org/10.17764/jiet.2.37.4.a5k692w88170707q.

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Energy analysis methods are commonly used to predict the vibroacoustic response of a spacecraft inside a launch vehicle payload fairing during liftoff. The payload fairing wall is often lined with acoustic blankets which can be difficult to model. This paper shows the development of a practical working method for accurately representing acoustic blankets in a VAPEPS statistical energy analysis model. A clear scaling relationship between the acoustic absorption coefficient and the blanket thickness is established. The scaling procedure is demonstrated using two sets of data for different absorption materials. The absorption data are implemented in VAPEPS by converting them to frequency-dependent damping loss factors. A post-processing procedure is derived to account for the increase in transmission loss due to the addition of the blanket layer. The entire process is used to predict the noise reduction in a VAPEPS model of the Atlas 14-ft-diameter payload fairing. Comparisons to ground-test and flight data for the blanketed fairing are presented to validate the procedure.

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Batelaan, Richard, Mark C. Anderson, J. T. Durrant, Kent L. Gee i Grant W. Hart. "Overall sound power levels from four launch vehicles". Journal of the Acoustical Society of America 153, nr 3_supplement (1.03.2023): A72. http://dx.doi.org/10.1121/10.0018202.

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To better understand the radiated sound from launch vehicles, this paper describes an effort to quantify the overall sound power level (OAPWL) from different launches. The classic NASA SP-8072 report (K. Eldred, 1971) contains data showing OAPWL as a function of mechanical power but little has been published on actual OAPWL since. This paper uses noise data from four different vehicles launched from Vandenberg Space Force Base to examine the relationship between OAPWL and measurement distance from the launch pad. Because OAPWL values calculated from measurements lessen with increased distance, an empirical correction based on nozzle diameter is described. [Work supported in part by NSF.]

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Tousignant, Todd, Geon-Seok Kim, David Trumpy, Adam Walt, Matthew Wickman, Dan McCain i Levi Magnuson. "A Case Study Comparing Active Vs. Passive Enablers for Vehicle Interior Noise Reduction". INTER-NOISE and NOISE-CON Congress and Conference Proceedings 266, nr 2 (25.05.2023): 718–27. http://dx.doi.org/10.3397/nc_2023_01_1044.

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The implementation of enablers on a luxury sport utility vehicle is used to illustrate the development process for reduction of road noise. The vehicle in this case study was launched into production with two tuned mass dampers for reduction of low frequency road noise content which was amplified by frame modes. Additionally, resonators were integrated into the wheels (rims) to address the dominant cavity resonance frequencies. The results of this successful production implementation are illustrated herein. An RNC (road noise cancellation) system was integrated into the case vehicle to assess its performance relative to the passive enablers listed above. This production representative (embedded software solution) RNC system utilized the vehicle's existing audio system for creation of active noise to cancel noise content which was predicted using accelerometers mounted to the vehicle chassis. A comparison of in-vehicle noise indicated a significant reduction at low frequencies (at all seating locations) when utilizing the active noise control solution. These noise improvements are coupled with a vehicle mass reduction of greater than 4 kg, when compared to the passive enabler solution.

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Galas', M. I., i A. A. Romanyuta. "Multipurpose nose fairing for space launch vehicles". Kosmìčna nauka ì tehnologìâ 5, nr 2-3 (30.03.1999): 60–65. http://dx.doi.org/10.15407/knit1999.02.060.

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Griffin, Steven, Steven A. Lane i Anthony Lazzaro. "Active Vibroacoustic Device for Noise Reduction in Launch Vehicles". Journal of Spacecraft and Rockets 45, nr 6 (listopad 2008): 1282–92. http://dx.doi.org/10.2514/1.36787.

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Bernfeld, David, Christophe Mietlicki i Fanny Mietlicki. "Hydre: a noise radar to automatically track down excessively noisy vehicles in real traffic conditions". INTER-NOISE and NOISE-CON Congress and Conference Proceedings 265, nr 3 (1.02.2023): 4959–66. http://dx.doi.org/10.3397/in_2022_0718.

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The developments made by Bruitparif since 2016 around sound source localization technologies applicable to the field of environmental noise resulted in the launch on the market of a patented combined acoustic and imaging sensor called "Medusa". An article of law was voted in France at the end of 2019 in order to enable the experimentation of noise radars in order to punish drivers causing significant noise nuisances by their behavior. The evaluation process includes track trials, roadsite tests and a final phase with fines. We will describe this national experimentation and the context in which it takes place. We will then detail the prototype called "Hydre" that we have developed for this purpose, and will present case results showing how it solves the major difficulties of the legal measurement of the pass-by noise of vehicles in real traffic conditions.

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35

Plotkin, Kenneth J. "A model for the prediction of community noise from launch vehicles." Journal of the Acoustical Society of America 127, nr 3 (marzec 2010): 1773. http://dx.doi.org/10.1121/1.3383858.

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Mathews, Logan T., Kent L. Gee i Grant W. Hart. "Analysis of overall noise levels from space vehicle launches". Journal of the Acoustical Society of America 148, nr 4 (październik 2020): 2704. http://dx.doi.org/10.1121/1.5147494.

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Lubert, Caroline P., Kent L. Gee i Seiji Tsutsumi. "Supersonic jet noise from launch vehicles: 50 years since NASA SP-8072". Journal of the Acoustical Society of America 151, nr 2 (luty 2022): 752–91. http://dx.doi.org/10.1121/10.0009160.

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Jia, Juhong, Debin Fu i Zepeng He. "Aerodynamic interactions of a Reusable Launch Vehicle model with different nose configurations". Acta Astronautica 177 (grudzień 2020): 58–65. http://dx.doi.org/10.1016/j.actaastro.2020.07.022.

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Escartí-Guillem, Mara S., Sergio Hoyas i Luis M. Garcia-Raffi. "Deflector shape impact on aero-acoustic noise generation and propagation". Journal of the Acoustical Society of America 152, nr 4 (październik 2022): A222. http://dx.doi.org/10.1121/10.0016076.

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The vibroacoustic loading generated during the launch of space vehicles can cause the failure of electronic and mechanical components. Therefore, the prediction and mitigation of these vibroacoustic levels are crucial to improve the reliability of launchers and payload comfort. Because a properly designed flame deflector has the power to significantly reduce the acoustic pressure level, the aeroacoustics characteristics of diverse types of flame deflectors must be understood. Three different deflector geometries have been analysed: a wedge-type deflector, which is currently used on the VEGA rocket launch pad, a 30-degree inclined deflector, since new studies highlight its noise reduction capacity, and a flat deflector, since the impact on a flat plate is the simplest case of reflection. The sound generation and propagation in the launch platform full domain for each case were studied using dedicated computational fluid dynamics in BSC MareNostrum. To assess noise generation, the main shock waves were identified, and the evolution of the generated sound pressure was assessed. Moreover, the sound pressure levels at the fairing surface have been studied. Further research is focused right now on the use of an efficient solver running on graphics processing units that is capable of computing large-scale turbulence.

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40

Lempert, D. B., V. I. Trushlyakov i V. E. Zarko. "Estimating the mass of a pyrotechnic mixture for burning the launch vehicle nose fairing". Combustion, Explosion, and Shock Waves 51, nr 5 (wrzesień 2015): 619–22. http://dx.doi.org/10.1134/s0010508215050147.

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Howard, Carl Q., Colin H. Hansen i Anthony Zander. "Vibro-acoustic noise control treatments for payload bays of launch vehicles: Discrete to fuzzy solutions". Applied Acoustics 66, nr 11 (listopad 2005): 1235–61. http://dx.doi.org/10.1016/j.apacoust.2005.04.009.

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Фролов, Виктор Петрович, Галина Ивановна Сокол i Владислав Юрьевич Котлов. "ВОЛНОВОЙ ПАРАМЕТР КАК КРИТЕРИЙ В ОСНОВЕ МЕТОДА ИССЛЕДОВАНИЯ АКУСТИЧЕСКИХ ИСТОЧНИКОВ ПРИ СТАРТЕ РАКЕТ". Aerospace technic and technology, nr 3 (27.06.2018): 4–12. http://dx.doi.org/10.32620/aktt.2018.3.01.

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The purpose of this work is to develop a method for determining the types of acoustic sources of radiation and their acoustic fields during the space rockets launch in the first seconds based on the wave parameter values. The main noise source during the space rocket launch is its propulsion system (PS). The cross-section of the nozzle is taken as the oscillation source. The theory of siren sound emission is based on the acoustic power calculation of a jet as a volume sound radiator or a radiator with a space velocity. In the model of a volumetric spherical radiator, the front of a spherical wave is a spherical surface, and the sound rays, according to the definition of the wave front, coincide with the radii of the sphere. As a result of the divergence of waves, the sound intensity decreases with distance from the source. The present work has a prospective character for clarifying the nature of the acoustic fields and for calculating the noise levels from the space rocket launch when designing the cosmodromes. In the requirements for the construction of such structures, the noise impact on the environment of infrasound radiation upon launching launch vehicles is identified. A method for determining the types of acoustic radiation sources during the space rocket launch and their acoustic fields has been developed. The method makes it possible to develop physical models of acoustic fields and apply known mathematical models to calculating their characteristics. The method is applicable for the study of acoustic emissions in the first seconds of the space rocket launch based on the determination of the wave parameter kR and allows us to provide valid data on the levels of sound pressure, intensity and acoustic power at specific points of airspace around the PS in the first seconds of the launch. The character of the acoustic wave radiation from a hole in a specific size gas flue has been studied. To calculate the acoustic characteristics, an algorithm and a program on Java programming language have been developed. Two models of acoustic field generation in the environment are described during the work of a rocket as a plane radiator and spherical waves, depending on the value of the wave parameter kR. A technique for calculating the noise of a remote control in the range for the first 1.5-4 seconds of the space rocket start time is developed

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Krishnan, Athira B., Prashanthan A. i Basil Sabu. "Design and Analysis of a Slanted Strapon Nose Cone (SSNC) of an Advanced Launch Vehicle". IOSR Journal of Mechanical and Civil Engineering 13, nr 05 (maj 2016): 137–41. http://dx.doi.org/10.9790/1684-130501137141.

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Durrant, J. T., Kent L. Gee, Mark C. Anderson, Logan T. Mathews i Grant W. Hart. "Analysis of sonic booms from Falcon 9 booster landings". Journal of the Acoustical Society of America 151, nr 4 (kwiecień 2022): A86. http://dx.doi.org/10.1121/10.0010743.

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One drawback to the ability to land boosters of orbital launch vehicles, such as the Falcon 9, is the associated reentry sonic boom. Because of the Falcon 9 booster shape and landing orientation, the observed waveform at the ground contains three shocks (a triple boom), rather than the two associated with a traditional N-wave. To assess the impact of these sonic booms, acoustic data from a Falcon-9 booster landing at Vandenberg Space Force Base are analyzed. The data were collected in Lompoc, CA, at locations 7-14 km away from the landing site. Waveform and spectral characteristics are examined and various metrics, including A-weighted Sound Exposure Levels (ASEL), are calculated. These metrics from the reentry sonic booms are compared with metrics calculated from the launch noise.

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45

Koshigoe, S., A. Teagle i C. H. Tsay. "A Rapidly Convergent Adaptive Controller Applied to Suppression of Random Noise Transmission". Journal of Vibration and Acoustics 120, nr 2 (1.04.1998): 449–54. http://dx.doi.org/10.1115/1.2893850.

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In this paper, an efficient rapid convergent control algorithm will be developed and will be compared with other adaptive control algorithms using a plate-cavity system. The plate-cavity system used for these numerical experiments is a test bed of noise suppression technology for expendable launch vehicles. It consists of a flexible plate backed by a rigid cavity. Piezoelectric (PZT) actuators are considered to be bonded on both sides of the plate symmetrically. The plate is bombarded with an amplified random noise signal, and the control system is used to suppress the noise inside the cavity generated by the outside sound source. Other control algorithms included for the comparisons are LMS Widrow’s finite impulse response (FIR) adaptive control algorithm [1], and a modified Godard’s algorithm [2]. Comparisons of the random noise attenuation capability, transient and convergence performance, and computational requirements of each algorithm will he made as the order of the controller and relevant convergence parameters are varied.

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46

Shuvalov, V. A., V. G. Tikhii, L. P. Potapovych, A. I. Priymak, N. I. Pismennyi i G. S. Kochubey. "Molecular contamination of spacecraft surfaces in thermostatic control and orbital injection of launch vehicle nose cone". Kosmìčna nauka ì tehnologìâ 13, nr 3 (30.05.2007): 3–11. http://dx.doi.org/10.15407/knit2007.03.003.

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Tahsini, Amir Mahdi, i Seyed Amir Hosseini. "Numerical Study of the Temperature History of Thermally Protected Blunt Nose during Flight". Applied Mechanics and Materials 598 (lipiec 2014): 294–97. http://dx.doi.org/10.4028/www.scientific.net/amm.598.294.

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In the present work, the surface temperature history of a metal shell of the blunt nose of supersonic launch vehicle which is covered by a thermal protection coating is numerically predicted and compared with experimental data. The full Navier-Stokes equations are used to estimate the aerodynamic heat flux during flight, coupled with the governing equations for the thermal protection system to study the erosion rate and temperature variations. The results show the importance of the properties of the coating on accuracy of the numerical predictions.

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48

Nöding, Michel, Martin Schuermann, Lothar Bertsch, Marc Koch, Martin Plohr, Robert Jaron i Jeffrey J. Berton. "Simulation of Landing and Take-Off Noise for Supersonic Transport Aircraft at a Conceptual Design Fidelity Level". Aerospace 9, nr 1 (23.12.2021): 9. http://dx.doi.org/10.3390/aerospace9010009.

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The German Aerospace Center has launched an internal project to assess the noise impact associated with supersonic transport aircraft during approach and departure. A dedicated simulation process is established to cover all relevant disciplines, i.e., aircraft and engine design, engine installation effects, flight simulation, and system noise prediction. The core of the simulation process is comprised of methods at the complexity and fidelity level of conceptual aircraft design, i.e., typical overall aircraft design methods and a semi-empirical approach for the noise modeling. Dedicated interfaces allow to process data from high fidelity simulation that will support or even replace initial low fidelity results in the long run. All of the results shown and discussed in this study are limited to the fidelity level of conceptual design. The application of the simulation process to the NASA 55t Supersonic Technology Concept Aeroplane, i.e., based on non-proprietary data for this vehicle, yields similar noise level predictions when compared to the published NASA results. This is used as an initial feasibility check of the new process and confirms the underlying methods and models. Such an initial verification of the process is understood as an essential step due to the lack of available noise data for supersonic transport aircraft in general. The advantageous effect of engine noise shielding on the resulting system noise is demonstrated based on predicted level time histories and certification noise levels. After this initial verification, the process is applied to evaluate a conceptual supersonic transport design based on a PhD thesis with two engines mounted under the wing, which is referred to as aircraft TWO. Full access to this vehicle’s design and performance data allows to investigate the influence of flight procedures on the resulting noise impact along approach and departure. These noise results are then assembled according to proposed Federal Aviation Agency regulations in their Notice of Proposed Rulemaking, e.g., speed limitations, for Supersonic transport noise certification and the regulations from Noise Chapters of the Annex 16 from the International Civil Aviation Organization in order to evaluate the resulting levels as a function of the flight procedure.

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Guo, An, Zhou Zhou, Xiaoping Zhu, Xin Zhao i Yuxin Ding. "Automatic Control and Model Verification for a Small Aileron-Less Hand-Launched Solar-Powered Unmanned Aerial Vehicle". Electronics 9, nr 2 (21.02.2020): 364. http://dx.doi.org/10.3390/electronics9020364.

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This paper describes a low-cost flight control system of a small aileron-less hand-launched solar-powered unmanned aerial vehicle (UAV). In order to improve the accuracy of the whole system model and quantify the influence of each subsystem, detailed modeling of UAV energy and a control system including a solar model, engine, energy storage, sensors, state estimation, control law, and actuator module are established in accordance with the experiment and component principles. A whole system numerical simulation combined with the 6 degree-of-freedom (DOF) simulation model is constructed based on the typical mission route, and the parameter precision sequence and energy balance are obtained. Then, a hardware-in-the-loop (HIL) experiment scheme based on the Stewart platform (SP) is proposed, and three modes of acceleration, angular velocity, and attitude are designed to verify the control system through the inner and boundary states of the flight envelope. The whole system scheme is verified by flight tests at different altitudes, and the aerodynamic force coefficient and sensor error are corrected by flight data. With the increase of altitude, the cruise power increases from 47 W to 78 W, the trajectory tracking precision increases from 23 m to 44 m, the sensor measurement noise increases, and the bias decreases.

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Mourouzidis, C., D. Del Gatto, S. Adamidis, C. Villena Munoz, C. Lawson, B. Martinez Corzo, P. Leyland i in. "Preliminary design of next generation Mach 1.6 supersonic business jets to investigate landing & take-off (LTO) noise and emissions – SENECA." Journal of Physics: Conference Series 2526, nr 1 (1.06.2023): 012011. http://dx.doi.org/10.1088/1742-6596/2526/1/012011.

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Abstract With the approach of next generation supersonic transport entry into service, new research activities were initiated to support updates on ICAO regulations and certification processes for supersonic transport vehicles. Within this context, the EU Horizon 2020 SENECA project has been launched to investigate the levels of noise and gaseous emissions in the vicinity of airports as well as the global climate impact of next generation supersonic civil aircraft. This paper introduces some of the preliminary outcomes of this investigation. It presents the preliminary design and performance analysis of a Mach 1.6 business jet, following an integrated aircraft-engine design approach. The preliminary design was performed accounting for the limitations posed by future environmental restrictions on respective subsonic vehicles. The market space and mission route definition exercise assumed only “over-sea” supersonic operations, while for “over-land”, only subsonic operations where allowed. Parametric studies on engine integrated design demonstrated modest core temperatures while cruising and the significant impact of engine installation on performance. At this first design iteration, assuming current state of the art technology, the Mach 1.6 business jet showed good potential to satisfy the predicted mission requirements while respecting the environmental constraints in terms of Landing & Take-Off (LTO) noise and emissions.

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