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Journal articles on the topic 'Launch Vehicle Noise'

Author: Grafiati

Published: 6 September 2023

Last updated: 31 July 2025

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1

Moats, Levi T., Matthew G. Yancey, Grant W. Hart, and 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, no. 3_supplement (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

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Gee, Kent L., Logan T. Mathews, Bradley McLaughlin, Mark C. Anderson, Daniel Edgington-Mitchell, and Grant W. Hart. "Rocket noise: What does it mean for Australian spaceports?" Journal of the Acoustical Society of America 154, no. 4_supplement (2023): A346. http://dx.doi.org/10.1121/10.0023749.

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As the global space industry expands, rockets are being launched from an increasing number of spaceports, including in Australia. As launch cadence increases to meet demand for space access and as vehicle optimization for weight and cost reduction becomes more pressing, noise has the potential to create harmful impacts—from vehicle vibroacoustic loading to expanded environmental footprint. Using data from recently measured launches, this presentation reviews rocket noise generation and propagation fundamentals and discusses some of these impacts. As small- and medium-payload orbital rocket lau

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Kellison, Makayle S., Noah L. Pulsipher, Levi T. Moats, et al. "Comparing acoustical measurements from Falcon 9 launches." Journal of the Acoustical Society of America 154, no. 4_supplement (2023): A347. http://dx.doi.org/10.1121/10.0023755.

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The Falcon 9 rocket has successfully launched nearly 300 orbital missions, providing the opportunity to study noise radiation and propagation variability. Acoustical measurements of several Falcon 9 launches have been made on and near Vandenberg Space Force Base, ranging 0.5 to 14 km from the launch pad. This paper’s purpose is to compare collocated measurements from different Falcon 9 launches to begin to understand data variability as a function of launch and environmental conditions. One far-field location, at a distance of 8.4 km, has been measured across all launches, whereas several othe

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4

James, Michael M., and Alexandria R. Salton. "Modeling community noise impacts from launch vehicle propulsion noise." Journal of the Acoustical Society of America 142, no. 4 (2017): 2490. http://dx.doi.org/10.1121/1.5014090.

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Moats, Levi T., Noah Pulsipher, Kent L. Gee, Grant W. Hart, Megan R. McCullah-Boozer, and Lucas K. Hall. "Variation of Falcon 9 noise in the mid-field." Journal of the Acoustical Society of America 155, no. 3_Supplement (2024): A62. http://dx.doi.org/10.1121/10.0026805.

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The rapid launch cadence of SpaceX’s Falcon 9 rocket provides the opportunity to study the relative consistency of noise radiation. Acoustical measurements of several Falcon 9 launches have been made on and near Vandenberg Space Force Base within 1 km of the launch pad. This paper compares collocated mid-field measurements from different Falcon 9 missions to begin to understand data variability as a function of launch and environmental conditions. One location 395 m from the pad has been measured over 5 times. This comparative analysis includes time-varying levels, spectra, and waveform statis

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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, no. 6 (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 numbe

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Pulsipher, Noah, Levi T. Moats, Kent L. Gee, Grant W. Hart, Megan R. McCullah-Boozer, and Lucas K. Hall. "Variation of Falcon 9 noise at far-field recording sites." Journal of the Acoustical Society of America 155, no. 3_Supplement (2024): A62. http://dx.doi.org/10.1121/10.0026804.

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The rapid launch cadence of SpaceX’s Falcon 9 rocket provides the opportunity to study the relative consistency of far-field noise propagation. Acoustical measurements of several Falcon 9 launches have been made on and near Vandenberg Space Force Base at a far-field location 8.4–14 km from the pad. This paper compares collocated measurements from different Falcon 9 missions to begin to understand data variability as a function of launch and environmental conditions at far-field locations. The 8.4 km location has been measured over 10 times, whereas other locations span subsets of launches. Thi

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8

Cunningham, Carson F., Kent L. Gee, Grant W. Hart, et al. "Initial findings from Space Launch System liftoff measurements." Journal of the Acoustical Society of America 153, no. 3_supplement (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 fro

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Cazacu, Mihai, Tiberiu Axinte, and Elena Curca. "The Importance of an Unmanned Surface Vehicle: A Point of View." International Journal of Advanced Multidisciplinary Research and Studies 4, no. 2 (2024): 1545–48. http://dx.doi.org/10.62225/2583049x.2024.4.2.2730.

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In the world there are various types of unmanned vehicles: Unmanned ground vehicle, unmanned aerial vehicle, unmanned surface vehicle and unmanned underwater vehicle. The objective of this paper, however, is to present the importance of an unmanned surface vehicle (USV) in the Black Sea. The safe operations of all USVs are carried out by experienced and qualified operators. These operators can control a USV from a ship or from land. An USV is equipped with various devices (eg. video camera, long range antennae or autopilot box) depending on the mission it has to carry out at sea. These boats a

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Roper, Jack. "Absolute Zero." Industrial Vehicle Technology International 28, no. 4 (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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Veerabathini, Surender, Sudhakara Reddy Penubolu, and Ramana Reddy Penubolu. "RCS Modeling and Validation of Full Scale Launch Vehicle for its Real Time Dynamic Trajectory." Defence Science Journal 73, no. 5 (2023): 505–11. http://dx.doi.org/10.14429/dsj.73.18193.

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Radar Cross Section (RCS) plays a significant role in detecting and tracking the space-based objects such as launch vehicles, missiles, aircrafts etc. In space applications, Radar systems are used to track and provide real-time trajectory information of the satellite launch vehicles after the lift off from the launch pad for range safety purpose. RCS is a critical key parameter that determines tracking performance of the Radar and it is highly dependent on both Radar operating parameters and the target characteristics. For space-based applications, a good quantity of RCS is required for quick

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12

Durrant, J. T., Kaylee Nyborg, Mark C. Anderson, Kent L. Gee, Grant W. Hart, and Lucas K. Hall. "Challenges in measuring and quantifying sonic booms from Falcon-9 booster landings." Journal of the Acoustical Society of America 154, no. 4_supplement (2023): A148. http://dx.doi.org/10.1121/10.0023079.

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Sonic booms from Falcon-9 booster landings contribute to the overall noise of the vehicle, but obtaining high-fidelity acoustical measurements and robust metric calculations of each sonic boom pose several challenges. This paper discusses three such challenges: sonic boom metric variability from differences in vehicle trajectory and meteorology, poor low-frequency response of low-sensitivity microphones, and contamination of the sonic boom by the landing burn noise. To quantify the variability between measurements, boom metrics are compared across four separate launches from Vandenberg Space F

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Yancey, Matthew G., Levi T. Moats, Mylan R. Cook, et al. "Acoustic overview of the Delta-IV Heavy NROL-91 launch." Journal of the Acoustical Society of America 153, no. 3_supplement (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

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Henderson, Benjamin K., Steven A. Lane, Joel Gussy, Steve Griffin, and Kevin M. Farinholt. "Development of an acoustic actuator for launch vehicle noise reduction." Journal of the Acoustical Society of America 111, no. 1 (2002): 174–79. http://dx.doi.org/10.1121/1.1420383.

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15

Cook, Mylan R., Kent L. Gee, Carson F. Cunningham, and 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, no. 3_supplement (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-correla

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Mathews, Logan T., Kent L. Gee, and Grant W. Hart. "Characterization of Falcon 9 launch vehicle noise from far-field measurements." Journal of the Acoustical Society of America 150, no. 1 (2021): 620–33. http://dx.doi.org/10.1121/10.0005658.

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17

Kemp, Jonathan D., and Robert L. Clark. "Noise reduction in a launch vehicle fairing using actively tuned loudspeakers." Journal of the Acoustical Society of America 108, no. 5 (2000): 2478. http://dx.doi.org/10.1121/1.4743141.

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18

Salton, Alexandria R., Michael M. James, Matthew F. Calton, et al. "Launch vehicle acoustic measurements for community noise model development and validation." Journal of the Acoustical Society of America 144, no. 3 (2018): 1673. http://dx.doi.org/10.1121/1.5067452.

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Kemp, Jonathan D., and Robert L. Clark. "Noise reduction in a launch vehicle fairing using actively tuned loudspeakers." Journal of the Acoustical Society of America 113, no. 4 (2003): 1986–94. http://dx.doi.org/10.1121/1.1558371.

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20

Escartí-Guillem, Mara S., Luis M. García-Raffi, and Sergio Hoyas. "URANS Analysis of a Launch Vehicle Aero-Acoustic Environment." Applied Sciences 12, no. 7 (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 correlatio

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21

Gee, Kent L. "The roar of the rocket: A hot topics discussion." Journal of the Acoustical Society of America 152, no. 4 (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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22

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, no. 3_supplement (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 i

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Lubert, Caroline P., Kent L. Gee, and 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, no. 4 (2021): A176. http://dx.doi.org/10.1121/10.0008037.

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24

Kang, Jun, Zhi Xiong, Rong Wang, and Ling Zhang. "Multi-Layer Fault-Tolerant Robust Filter for Integrated Navigation in Launch Inertial Coordinate System." Aerospace 9, no. 6 (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 measure

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Bae, Wonki, and Junhong Park. "Optimization of Pyroshock Test Conditions for Aerospace Components to Enhance Repeatability by Genetic Algorithms." Aerospace 11, no. 9 (2024): 700. http://dx.doi.org/10.3390/aerospace11090700.

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Electronic components assembled in satellites should be able to withstand the vibration, noise, and impact loads generated by space vehicles during launch. To simulate the impact loading in a laboratory environment, a pyroshock test simulates an impact load resulting from explosions during the stage and pairing separation of launch vehicles, which imposes significant stress on the components, potentially leading to failures and damage. To ensure component reliability before the flight model (FM) stage, where components are mounted on the actual launch vehicle and sent into orbit, a pyroshock t

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Ignatius, Jopaul K., S. Sankaran, R. Ashok Kumar, T. N. V. Satyanarayana, and Satyanarayanan R. Chakravarthy. "Suppression of Jet Noise by Staged Water Injection during Launch Vehicle Lift-Off." International Journal of Aeroacoustics 7, no. 3-4 (2008): 223–41. http://dx.doi.org/10.1260/1475-472x.7.3.223.

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Guo, Rong, Hao Chen, and 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, no. 2 (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 th

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Tran Duc Anh, Tran Huu Phuong, and Vu Anh Hien. "Synthesis of synchronous filter for target tracking system of the self-guided infrared flying vehicle." Journal of Military Science and Technology, FEE (December 6, 2024): 79–84. https://doi.org/10.54939/1859-1043.j.mst.fee.2024.79-84.

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This article deals with research in the field of noise-based signal processing for target tracking systems of the self-guided infrared flying vehicle. The article conducts theoretical analysis, builds block diagrams, structural diagrams and describes the operating principle of the synchronous filter in low and high input frequency, and proposes a mathematical model of this filter. The simulation results, carried out in Matlab/Simulink and Atium environments, are the basis for designing the synchronous filter electrical circuit of the correction circuit board attached to the launch mechanism of

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Phillips, James E. "Planes, rockets, trains, and buildings—A career that included them all, and more." Journal of the Acoustical Society of America 156, no. 4_Supplement (2024): A41. https://doi.org/10.1121/10.0035034.

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James Phillips started his career conducting aircraft cabin acoustics measurements in the laboratory and in-flight at McDonnell Douglas while completing his Master of Science in Acoustics degree from the Pennsylvania State University in 1989. From there, he worked briefly at the Jet Propulsion Laboratory before moving on to the Aerospace Corporation where he analyzed launch vehicle and payload acoustic, vibration, and shock environments for the then United States Air Force Space and Missile Systems Center. After that, he changed his career path to work for an acoustical consulting firm where h

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Stoica, Adrian-Mihail, Costin Ene, and 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 express

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Kellison, Makayle S., Kent L. Gee, Carson F. Cunningham, Mark C. Anderson, Grant W. Hart, and Whitney L. Coyle. "Ongoing analysis of far-field acoustical measurements during the Artemis-I launch." Journal of the Acoustical Society of America 154, no. 4_supplement (2023): A346. http://dx.doi.org/10.1121/10.0023750.

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As the global space industry expands, impacts from super heavy-lift launch vehicle noise on payloads, communities, and natural habitats are better understood with improved source models. To support model development, this paper discusses ongoing analyses of far-field acoustical measurements made during the NASA Space Launch System (SLS) Artemis-I mission. Fifteen acoustical measurement stations were deployed prior to the launch, including ten autonomous stations within Kennedy Space Center and five manned stations off-Center, up to 50 km from the pad. This paper presents a brief summary of dat

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Priyadarshini, Sushree, Mohapatra Kumar Gourab, Utpal Mandal, and Angshuman Roy. "A Comparative Study on various Flight Termination System Technologies." Defence Science Journal 73, no. 3 (2023): 351–61. http://dx.doi.org/10.14429/dsj.73.18334.

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In a test range, a Flight Termination System (FTS) plays a prominent role in protecting range and flight personnel along with surrounding area population in case the flight vehicle is out of its trajectory range and possesses a threat to surrounding. An efficient FTS should posses high Signal to Noise Ratio, link robustness to ensure reliable communication between ground transmitting and onboard receiving systems and should be immune to interference. This article presents a detailed report on the requirement and features of FTS & technologies used in it. Techniques such as tone based, code

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Xing, Chenglong, Guigao Le, and 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, no. 1 (2022): 1173–94. http://dx.doi.org/10.1080/19942060.2022.2072953.

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NEILSEN, Tracianne B., Kent L. GEE, and 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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Himelblau, Harry, and Allan Piersol. "Evaluation of a Procedure for the Analysis of Nonstationary Vibroacoustic Data." Journal of the IEST 32, no. 2 (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

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Tauhid Ahmad, Noor Hidayah, Nurliza Salim, Adhwa Amir Tan, Syahrim Azhan Ibrahim, and Maszlan Ismail. "High-Intensity Acoustic Chamber System Spectrum Profiling for Satellite Launching Environment." Applied Mechanics and Materials 793 (September 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 15

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Gee, Kent L., Grant W. Hart, and Caroline P. Lubert. "A brief rocket noise introduction for the interested ASA meeting attendee." Journal of the Acoustical Society of America 153, no. 3_supplement (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

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Srinivasan, R., B. Lakshmi, and Tessy Thomas. "An Architecture for On board Frequency Domain Analysis of Launch Vehicle Vibration Signals." Defence Science Journal 73, no. 1 (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 veh

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Chocat, Rudy, Loïc Brevault, Mathieu Balesdent, and 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 hi

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Hu, Mengya, and Yi Jiang. "Research on the High Speed of Piston Pumps Based on Rapid Erecting of Launch Vehicles." Applied Sciences 13, no. 12 (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,

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Simplício, Pedro, Paul Acquatella, and Samir Bennani. "Design and Analysis of a Launcher Flight Control System Based on Incremental Nonlinear Dynamic Inversion." Aerospace 12, no. 4 (2025): 296. https://doi.org/10.3390/aerospace12040296.

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This paper investigates the application of Incremental Nonlinear Dynamic Inversion (INDI) for launch vehicle flight control, addressing the limited exploration of nonlinear control architectures and their potential benefits in the context of the current “New Space” era. In this context, this study aims to bridge the gap between the launcher’s traditional linear control practice and nonlinear methods, focusing on INDI, which offers the potential to enhance limits of performance while reducing mission preparation (“missionisation”) efforts. INDI control commands incremental inputs by exploiting

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Weissman, Karen, Mark McNelis, and William Pordan. "Implementation of Acoustic Blankets in Energy Analysis Methods with Application to the Atlas Payload Fairing." Journal of the IEST 37, no. 4 (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 absorp

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NAJI, Naji Anees Muqdad, and Adrian STOICA. "Design of a robust controller for the VEGA TVC using the L1-Adaptive Control." INCAS BULLETIN 15, no. 4 (2023): 175–85. http://dx.doi.org/10.13111/2066-8201.2023.15.4.15.

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The purpose of this study is to Design of a robust controller for the VEGA TVC using the L1-Adaptive Control. The performance of the system with an L1 adaptive controller has been compared with that of a classical controller. The L1 adaptive controller optimization is an efficient as well as an effective approach for the design of a robust controller. The L1 adaptive controller ensures the robustness of the system against uncertainties, noise, and disturbances[10]. In a launch vehicle parameters like mass, thrust, and aerodynamic properties are time-varying. Due to the time-varying nature of t

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Batelaan, Richard, Mark C. Anderson, J. T. Durrant, Kent L. Gee, and Grant W. Hart. "Overall sound power levels from four launch vehicles." Journal of the Acoustical Society of America 153, no. 3_supplement (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,

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COYLE, Whitney, and Kent GEE. "An application of aircraft noise metrics to the Artemis-I launch." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 270, no. 5 (2024): 6304–11. http://dx.doi.org/10.3397/in_2024_3712.

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In aerospace and acoustical research, there has been significant focus on understanding the negative effects of noise from jet aircraft and flyover vehicles. However, there has been relatively little investigation into the specific noise impacts of launch vehicles. Despite a considerable rise in the number of launches from various spaceports globally in the past decade, there appears to be poor understanding of the potential harm these increasing launches could pose to nearby communities, including both humans and wildlife. This paper aims to apply established noise metrics such as overall sou

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Tousignant, Todd, Geon-Seok Kim, David Trumpy, et al. "A Case Study Comparing Active Vs. Passive Enablers for Vehicle Interior Noise Reduction." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 266, no. 2 (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

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Griffin, Steven, Steven A. Lane, and Anthony Lazzaro. "Active Vibroacoustic Device for Noise Reduction in Launch Vehicles." Journal of Spacecraft and Rockets 45, no. 6 (2008): 1282–92. http://dx.doi.org/10.2514/1.36787.

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Bernfeld, David, Christophe Mietlicki, and 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, no. 3 (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 whic

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Plotkin, Kenneth J. "A model for the prediction of community noise from launch vehicles." Journal of the Acoustical Society of America 127, no. 3 (2010): 1773. http://dx.doi.org/10.1121/1.3383858.

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Mathews, Logan T., Kent L. Gee, and Grant W. Hart. "Analysis of overall noise levels from space vehicle launches." Journal of the Acoustical Society of America 148, no. 4 (2020): 2704. http://dx.doi.org/10.1121/1.5147494.

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