2006-2007 - Kennedy Space Center Technology Transfer Office

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Predicting the Acoustic Environment Induced by the Launch of theAres I VehicleDecision/DataModels andAnalysisThe exhaust plumes of launch vehicles impose severe heating rates, pressures, andvibroacoustic loads on ground support equipment (GSE) on the Mobile Launcher (ML),as well as on the vehicle itself. The vibroacoustic environment must be predicted beforethe criteria for the acceptance and qualification testing of GSE components and theirinstallations can be determined.Near-field launch noise levels are traditionally computed as described in NASA SP-8072, “AcousticLoads Generated by the Propulsion System,” published in 1971. Figure 1 illustrates the method fordetermining the noise load on the vehicle. The rocket exhaust plume is a distribution of acousticsources, each of which propagates to a point on the vehicle. The report contains empirical models fordetermining the strength and distribution of the noise and includes simple factors for various types ofdeflectors (Figure 1).Since SP-8072 was published, there has been considerable research in jet and rocket noise modelingand sound propagation. For example, the overall sound power model in SP-8072 was based on asimple acoustic efficiency factor and is not consistent with Lighthill’s well-established jet noise theory.Consistent rocket noise models, more recent research on source distributions and characteristics,and a much better understanding of the shielding of noise by parts of the launcher itself are nowavailable.Figure 1. Noise modeling sketch from NASA SP-8072 shows the predominantangle of maximum noise generation.46 Spaceport Structures and Materials
The sketch in Figure 2 shows alauncher deck and general location ofthe receivers along the launch tower.Figure 3 shows the vehicle rising pastthe tower. Various propagation pathsare indicated, including those in areaswhere the launcher deck providesshielding.This project updates launch noisemodeling in the following ways:• It provides the overall soundpower emission of the rocketwith the Lighthill-consistentmethod developed bySutherland.• It updates distributions ofnoise along the plume with theempirical work of Sutherland,McInerny, et al., and bythe recent theoretical andlaboratory work of Harper-Bourne and others.• It computes the shieldingof propagation paths by thelauncher deck via Maekawa’sthin screen diffraction model.• It uses the modern groundimpedance model of Chien andSoroka to address how groundreflection affects propagation,and it uses current ANSI/ISOstandards to determine theeffects of absorption by air.Key accomplishments werereviewing SP-8072 methodology andidentifying components requiringupdate, generalizing the methodologyfor off-vehicle locations (in particular,locations on the launch tower), andidentifying current technology to beused in updating predictions.Figure 2. Noise modeling is shown for a mobile launcher with a rocket on the pad.Figure 3. Noise contours and spectrum shown for a mobile launcher with avehicle rising past the tower.Contact: Dr. Bruce T. Vu , NASA-KSC, (321) 867-2376Participating Organization: Wyle Laboratories (Dr. Kenneth J. Plotkin)KSC Technology Development and Application 2006-200747
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ForewordSuccessful technology devel
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ContentsSpaceport Structures and Ma
Page 9 and 10: Contents (continued)Process and Hum
Page 11 and 12: IntroductionJohn F. Kennedy Space C
Page 13 and 14: Constellation SystemsSurfaceSystems
Page 15 and 16: Spaceport Structures and MaterialsK
Page 17 and 18: 20181614∆ E1210Modified Sensor Be
Page 19 and 20: Initial results of the EDEM model o
Page 21 and 22: Contacts: Dr. Carlos I. Calle ,NASA
Page 23 and 24: Close examination of the corrosions
Page 25 and 26: Adhesion at Failure (psi)2500200015
Page 27 and 28: Figure 1. After 500 hours of salt f
Page 29 and 30: Contacts: Dr. Paul E. Hintze , NASA
Page 31 and 32: Figure 2. Repairs to various types
Page 33 and 34: on top of the cuvette contains the
Page 35 and 36: Figure 2. A corrugated NiTi sheet e
Page 37 and 38: The PLTD can be used to (1) calibra
Page 39 and 40: SEM images of neat MWNT fibers: (a)
Page 41 and 42: Contacts: Trent M. Smith
Page 43 and 44: Figure 1. An isometric cutaway view
Page 45 and 46: Figure 2. Quartz sand flowing in th
Page 47 and 48: Figure 2. Top images show how the e
Page 49 and 50: Sand volume fraction contour at t =
Page 51 and 52: Integrated LWRD/RVC engineering bre
Page 53 and 54: Mean relative percentage change in
Page 55 and 56: We compared the model’s predictio
Page 57 and 58: Figure 2. Three-dimensional simulat
Page 59: Figure 3. Camera calibration model.
Page 63: Figure 2. Signal generator (right)
Page 66 and 67: Hail Size Distribution MappingA 3-D
Page 68 and 69: Launch Pad 39 Hail Monitor Array Sy
Page 70 and 71: Autonomous Flight Safety System - P
Page 72 and 73: The Photogrammetry CubeSpaceport/Ra
Page 74 and 75: Bird Vision SystemThe Bird Vision s
Page 76 and 77: Automating Range Surveillance Throu
Page 78 and 79: Next-Generation Telemetry Workstati
Page 80 and 81: GPS Metric Tracking UnitAs Global P
Page 82 and 83: Space-Based RangeSpace-Based Range
Page 85 and 86: Fluid System TechnologiesKSC Techno
Page 87 and 88: 0.900.850.80Discharge Coefficient,
Page 89 and 90: Composite seals for performance eva
Page 91 and 92: 140000120000100000Signal80000600004
Page 93 and 94: Contacts: Dr. Barry J. Meneghelli ,
Page 95 and 96: 60555045Comparative k-value (mW/m-K
Page 97 and 98: a compatible spacecraft model where
Page 99 and 100: In an ongoing effort for improvemen
Page 101: Low-gravity probe prototype test.th
Page 104 and 105: Countermeasure for Radiation Protec
Page 106 and 107: Focused Metabolite Profiling for Di
Page 109 and 110: Process and Human FactorsEngineerin
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DON uses game technology to enable
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Type of mobile crane that impacted
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SALT proof-of-concept communication
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SSLM CAD model.Our design offers th
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Variables that can be integrated by
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Exploration Supply Chain Simulation
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Nanosensors for Evaluating Hazardou
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Sixty-four-Channel Inline Cable Tes
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Wireless Inclinometer Calibration S
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Generating Safety-Critical PLC Code
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Spacecraft Electrostatic Radiation
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Ion Beam Propulsion StudySpacecraft
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RT-MATRIX: Measuring Total Organic
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Appendix AKSC High-Priority Technol
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Risk Assessment ToolMission Data Fe
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Appendix BInnovative Partnership Pr
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system for the Government, using th
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tracking objects after launch, and
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2006-2007 - Kennedy Space Center Technology Transfer Office

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