Commercial Space Operations Noise and Sonic Boom Measurements (2020)

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Commercial Space Operations Noise and Sonic Boom Measurements 9 2 Database of Existing Data A systematic review of existing publications was performed to identify, evaluate, and compile research relevant to full-scale propulsion noise and sonic boom measurements of commercial space operations. As shown in Figure 4, the datasets identified in the literature survey spanned from the historic Apollo era to the present SLS development. This compilation of publications establishes the principal resources that can contribute to community noise model development and validation. The types of sources included books, journal articles, dissertations, conference proceedings, and government technical documents. Figure 4. Full-scale propulsion noise and sonic boom measurements included in the literature review. The existing research is categorized into the six categories summarized in Table 1. The first five categories are associated with propulsion noise from full-scale static and launch measurements, organized in reverse chronological order. The sixth and final category contains publications associated with sonic boom measurements. An introduction to each category is provided in the following sections, including a brief description of the measurements and data, summary of events, concise evaluation of data quality, and list of associated key publications. The quality of the existing data is evaluated relative to the objectives of the current research effort as informed by the documentation criteria defined in the community noise measurement protocol. A dataset’s usefulness depends on whether it includes well-documented, high-quality acoustic, trajectory,

Commercial Space Operations Noise and Sonic Boom Measurements 10 and weather data, which are the three necessary components for future community noise model development and validation efforts. The following lists describe the desired elements to be contained in a high-quality dataset for each type of data. Acoustic  Description of instrumentation for every microphone, pre-amplifier, and recording channel;  Test location data describing the physical arrangement of the microphones and recorders (including height and orientation);  Relevant metrics for propulsion noise (e.g. OASPL time-history, Sound Exposure Level (SEL), and Lmax) and sonic boom (e.g. pressure time-history, SEL, Steven’s Mark VII Perceived Level (PL), and Indoor Sonic Boom Annoyance Predictor (ISBAP));  One-third Octave (OTO) band time histories (for propulsion noise). Trajectory  Event details describing the vehicle and mission;  Vehicle location: time, latitude, longitude, and altitude; recorded at a rate of ≤ 1 sample/second;  Flight dynamics: velocity, acceleration, jerk, attitude (i.e. roll, pitch, yaw), flight path azimuth, flight path heading, weight, thrust, drag, and engine vectoring; and  Engine exhaust conditions: velocity relative to nozzle, nozzle exit pressure, temperature. Weather  Description of instrumentation and location for every weather station;  Temperature, humidity, ambient pressure, and wind velocity (speed and direction) recorded near the site of the event at a minimum of one sample per second; and  Weather balloon data from the nearest radiosonde to the launch/test site that captures the temperature and wind speed profile. Missing or limited data components decrease the value of the dataset in facilitating future community noise model development and validation efforts. A qualitative classification system is used to describe the quality level of each category using the following rankings:  “High” refers to a dataset that contains most if not all the elements described above and is useful in most model development or validation scenarios,  “Moderate” refers to a dataset that contains enough elements to still be useful in some model development or validation scenarios,  “Low” refers to a dataset that contains at least one element but is not useful in most model development or validation scenarios, and  “None” refers to a dataset that does not contain any of the above elements. As shown in Table 1, none of the existing datasets include high-quality data in all of the three components. The result of this literature review confirms the importance of the current measurement campaign.

Commercial Space Operations Noise and Sonic Boom Measurements 11 Table 1. Summary of Existing Data Data Quality Category Acoustic Trajectory Weather Description Solid Rocket Motor Tests at ATK High - Moderate Horizontal static tests conducted at ATK’s Promontory, Utah facility between 2008 and 2016 NASA Constellation Program Moderate - Low Near and far-field measurements of a Shuttle RSRM booster, two launches, and 10” diameter motor 1990’s Rocket Launches at VAFB and KSC High None None Launches of Delta, Peacekeeper, Scout, Taurus, and Titan launch vehicles at VAFB and KSC in the 1990’s Apollo Era (Pre-1972) Government Documents Low None None Historical references from the beginning of the U.S. space program until the early 1970’s Other Propulsion Noise Measurement Documents Low - High None None Other rocket propulsion studies from JAXA, U.S. universities, and NASA Ames Research Center Sonic Boom Low - High Low Low Sonic boom measurements during launch and re-entry of launch vehicles including three Apollo missions and a Titan IV launch KSC = Kennedy Space Center, VAFB = Vandenberg Air Force Base

Commercial Space Operations Noise and Sonic Boom Measurements 12 Solid Rocket Motor Tests at ATK Blue Ridge Research and Consulting, LLC & Brigham Young University Date: 2008-2016 The BRRC and BYU teams performed acoustic measurements of horizontal static tests conducted at ATK’s Promontory, Utah facility between 2008 and 2016. The tests between 2010 and 2012 were conducted under three phases of a NASA SBIR program. High-fidelity acoustic measurement instrumentation was deployed adjacent to the test facility along arrays parallel to the shear layer in addition to radial arrays. The tests focused on full-scale solid rocket motors with a range of thrusts from 151,000 lbs to 3.6 million lbs, with two smaller motors with thrust parameters unknown. Measurements were made as close as 8 nozzle diameters from the shear layer and as far away as 2.9 km. The resulting acoustic data are of high quality and are relevant to source characterization associated with source power and directivity as well as far-field noise characteristics. Acoustic Data: High Trajectory Data: N/A Weather Data: Moderate Events  QM-2 for NASA SLS, June 2016, ATK’s T-97 test facility, Promontory, UT  QM-1 for NASA SLS, March 2015, ATK’s T-97 Test facility, Promontory, UT  GEM-60, 6 September 2012, ATK’s T-6 test facility, Promontory, UT  Kinetic Energy Interceptor (KEI) Stage 2 motor, 26 January 2011, ATK, Promontory, UT  ORION 50 XLG, 24 June 2010, ATK’s T-6 test facility, Promontory, UT  GEM-60, 19 February 2009, ATK’s T-6 test facility, Promontory, UT  5-inch CP nozzle, 22 August 2008, ATK’s small motor test facility, Promontory, UT  GEM-60, 24 June 2008, ATK’s T-6 test facility, Promontory, UT Publications  B. O. Reichman, B. M. Harker, T. B. Neilsen, K. L. Gee, and W.-S. Ohm, “Acoustic measurements in the far field during QM-2 solid rocket motor static firing,” Proc. Mtgs. Acoust. Vol. 29, accepted, 2018.  B. O. Reichman, B. M. Harker, T. A. Stout, E. B. Whiting, K. L. Gee, and T. B. Neilsen, “Acoustical measurements during a static firing of the Space Launch System solid rocket motor,” Proc. Mtgs. Acoust. Vol. 25, 045006, 2017.  K. L. Gee, E. B. Whiting, T. B. Neilsen, M. M. James, and A. R. Salton, “Development of a Near-field Intensity Measurement Capability for Static Rocket Firings,” Trans. JSASS Aerospace Tech. Japan Vol. 14, No. ists30, pp. Po_2_9-Po_2_15, 2016.  T. B. Neilsen, K. L. Gee and M. M. James, “Analysis of the Effects of Finite Impedance Ground and Atmospheric Turbulence on Launch Vehicle Noise Measurements”, Trans. JSASS Aerospace Tech. Japan, Vol. 14, No. ists30, pp. Po_2_1-Po_2_7, 2016.  M. M. James, A. R. Salton, K. L. Gee, and T. B. Neilsen, “Comparative Analysis of NASA SP-8072’s Core Length with Full-Scale Rocket Data”, Trans. JSASS Aerospace Tech. Japan Vol. 14, No. ists30, pp. Po_2_17-Po_2_24, 2016.  M. M. James, A. R. Salton, K. L. Gee, and T. B. Neilsen, “Comparative Analysis of NASA SP-8072’s Core Length with Full-Scale Rocket Data”, 2015-o-2-08, 2015.  K. L. Gee, E. B. Whiting, T. B. Neilsen, M. M. James, and A. R. Salton, “Development of a Near-field Intensity Measurement Capability for Static Rocket Firings”, 2015-o-2-12, 2015.  T. B. Neilsen, K. L. Gee and M. M. James, “Analysis of the Effects of Finite Impedance Ground and Atmospheric Turbulence on Launch Vehicle Noise Measurements”, 2015-o-2-11, 2015.

Commercial Space Operations Noise and Sonic Boom Measurements 13  M. M. James, A. R. Salton, K. L. Gee, T. B. Neilsen, S. A. McInerny, “Full-scale Rocket Motor Acoustic Tests and Comparisons with Empirical Source Models”, POMA, 2014.  B. Y. Christensen, “Investigation of a New Method of Estimating Acoustic Intensity and Its Application to Rocket Noise”, BYU Masters Thesis, 2014.  M. M. James, A. R. Salton, K. L. Gee, and T. B. Neilsen, “Intensity-Based Approach to Characterize Near-Field Acoustic Environments of Space Flight Vehicles”, POMA, 2013.  J. H. Giraud, “Experimental Analysis of Energy-Based Acoustic Arrays for Measurement of Rocket Noise Fields”, BYU Masters Thesis, 2013.  M. M. James, A. R. Salton, K. L. Gee, “Full-scale Rocket Motor Acoustic Tests and Comparisons with Models: Revisiting the Empirical Curves Part 1”, ASA Kansas City, 2012.  M. M. James, A. R. Salton, K. L. Gee, “Full-scale Rocket Motor Acoustic Tests and Comparisons with Models: Updates and comparisons with SP-8072 Part 2”, ASA Kansas City, 2012.  M. M. James and K. L. Gee, “Advanced acoustic measurement system for rocket noise source characterization”, InterNoise NYC, 2012.  M. M. James, A. R. Salton, K. A. Bradley, K. L. Gee, S. A. McInerny, “Measurements, Modeling, and Verifications of 8072”, NASA SBIR Phase II Contract NNX11CC16C, 2012.  M. M. James, A. R. Salton, K. L. Gee, T. B. Neilsen, S. A. McInerny and R. J. Kenny, “Modification of directivity curves for a rocket noise model”, POMA 3aNS3, 2012.  K. L. Gee, “Energy-Based Measurements of Rocket Noise”, NASA Phase II Meeting, 2012.  S. A. Harper, “Statistical Analysis of Noise from Solid Rocket Motors”, n/a, 2012.  R. T. Taylor, K. L. Gee, J. H. Giraud, S. D. Sommerfeldt, J. D. Blotter, and C. P. Wiederhold, “On the use of prepolarized microphone systems in rocket noise measurements,“ Proc. Mtgs. Acoust. 14, 040005 (2012).  S. A. McInerny, “Kick Off Discussion”, Phase II Meeting, 2012.  M. M. James, K. L. Gee, “Energy-Based Acoustic Measurement System for Rocket Noise”, ASA San Diego, 2011.  M. M. James, K. L. Gee, “Energy-Based Acoustic Measurement System for Rocket Noise”, NASA Contract NNX11CC16C, 2011.  J. H. Giraud, K. L. Gee, S. D. Sommerfeldt, J. D. Blotter, T. Taylor, “Low-frequency calibration of a multidimensional acoustic intensity probe for application to rocket noise”, ASA San Diego, 2011.  S. A. Harper, K. L. Gee, J. H. Giraud, M. B. Muhlestein, “Statistical analysis of noise from solid rocket motors”, ASA San Diego, 2011.  T. Taylor, K. L. Gee, J. H. Giraud, S. D. Sommerfeldt, J. D. Blotter, C. P. Wiederhold, “On the use of prepolarized microphones in rocket noise measurements”, ASA San Diego, 2011.  T. Taylor, “Microphone System Response in High Amplitude Noise Environments”, BYU Senior Thesis, 2011.  J. H. Giraud and K. L. Gee, “Directivity indices for rocket noise modeling: measurement considerations”, ASA Baltimore, 2010.  M. B. Muhlestein, K. L. Gee, T. B. Neilsen, D. C. Thomas, “Prediction of nonlinear propagation of noise from a solid rocket motor”, POMA Vol. 18, 040006, 2013.  M. B. Muhlestein, D. C. Thomas, and K. L. Gee, “Time-domain effects of rigid sphere scattering on measurement of transient plane waves”, J. Acoust. Soc. Am. Vol. 136 No. 1 , 2014.  J. H. Giraud, K. L. Gee, and J. E. Ellsworth, “Acoustic temperature measurement in a rocket noise field”, J. Acoust. Soc. Am. Vol. 127 No. 5, 2010.

Commercial Space Operations Noise and Sonic Boom Measurements 14 NASA Constellation Program Various Date: 2007-2008 Various full-scale measurement campaigns were conducted in support of the prior NASA Constellation program. The Constellation tests included multiple near- and far-field measurements of a four-segment Space Shuttle Reusable Solid Rocket Motor (RSRM), two vehicle launches, and study of the noise from a 10-in. diameter motor similar to the Orion Crew Vehicle launch abort motor. The launch abort motor data are most useful for determining near-field characteristics, whereas the RSRM data help determine important level, spectral, and directivity information and transition of nonlinear propagation effects from the near to the far fields. The directivity data are critical to community noise prediction modeling. The two launch datasets, on ALV-XI and Ares I-X, are less relevant to the community noise problem, but are useful for determining levels and spectra on the vehicle and launch tower, i.e., near-source characteristics including the effects of pad impingement. Acoustic Data: Moderate Trajectory Data: N/A Weather Data: Low Events  Ares I-X, 28 October 2009, NASA Kennedy Space Center LC-39B  ATK Launch Vehicle (ALV-X1), 22 August 2008, Mid-Atlantic Regional Spaceport Pad 01B  Orion Crew Vehicle 10“ Launch Abort Motor Tests, NASA Ames Facility, CA  RSRM: Technical Evaluation Motor 13 (TEM-13), 2007, ATK, Promontory, UT  RSRM: Flight Verification Motor 2 (FVM-2), 2008, ATK, Promontory, UT  RSRM: Flight Simulation Motor 15 (FSM-15), 2008, ATK, Promontory, UT Publications  W. C. Horne, N. J. Burnside, J. Panda, and C. Brodell, “Measurements of unsteady pressure fluctuations in the near-field of a solid rocket motor plume,“ Int. J. Aeroacoust. Vol. 15, 554-569, 2016.  X. Gao and J. D. Houston, “Acoustics Research of Propulsion Systems”, NASA TR- 20140011603, 2014.  K. L. Gee, R. J. Kenny, T. B. Neilsen, T. W. Jerome, C. M. Hobbs and M. M. James, “Spectral and statistical analysis of noise from reusable solid rocket motors”, POMA Vol. 18, 040002, 2013.  K. L. Gee, R. J. Kenny, T. W. Jerome, T. B. Neilsen, C. M. Hobbs, M. M. James, “Analysis of noise from reusable solid rocket motor (RSRM) firings”, ASA Kansas City, 2012.  J. Haynes, R. J. Kenny, “Modifications to the NASA SP-8072 Distributed Source Method II for Ares I Lift-Off Environmental Predictrions”, AIAA 2009-3160, 2009.  R. J. Kenny, C. M. Hobbs, K. Plotkin, and D. Pilkey, “Measurement and Characterization of Space Shuttle Solid Rocket Motor Plume Acoustics,” AIAA 2009-3161, 2009.  J. D. Houston, D. Counter, R. J. Kenny, and J. Murphy, “ATK Launch Vehicle (ALV-X1) Liftoff Acoustic Environments: Prediction vs. Measurement”, NASA TR- 20090023538, 2009.

Commercial Space Operations Noise and Sonic Boom Measurements 15 1990’s Rocket Launches at VAFB and KSC Various Date: 1990’s This grouping is based on the work of Dr. Sally Anne McInerny, who helped the launch vehicle community transition to more physically relevant analyses based on the time series and spectral data. The measurements, made at Vandenberg Air Force Base, CA, and Kennedy Space Center, FL, during launches of the Delta, Peacekeeper, Scout, Taurus, and Titan launch vehicles, were made using digital audio tape recorders attached to the AC-output of sound level meters with ½” microphones. Data were recorded at stations 0.36 to 13.2 km from the launch pad, with the purpose of characterizing the far-field levels, spectral content, and time domain characteristics during the maximum sound exposure portion of the launch. The acoustic data are of high quality and can be used to characterize rocket noise. However, with limited trajectory and weather data, the usefulness of these reports for model validation efforts is reduced. Acoustic Data: High Trajectory Data: None Weather Data: None Events  Various Delta launches, 1990’s, Vandenberg Air Force Base and Kennedy Space Center  Various Peacekeeper launches, 1990’s, Vandenberg Air Force Base and Kennedy Space Center  Various Scout launches, 1990’s, Vandenberg Air Force Base SLC-5  Various Taurus launches, 1990’s, Vandenberg Air Force Base  Various Titan IV launches, mid-1970’s and 1990’s, Vandenberg Air Force Base Publications  S. A. McInerny, “Perspective on Launch Noise—Measurement, Prediction, and Characterization,” Acoustical Society of America Meeting, Baltimore, MD, 2010.  S. A. McInerny, “Nonlinearities in Rocket and Missile Noise: Implications for Propagation and Instrumentation”, Space and Missiles Defense Conference, 2005.  S. A. McInerny and S. M. Olcmen, “High-intensity rocket noise: Nonlinear propagation, atmospheric absorption, and characterization”, J. Acoust. Soc. Am., Vol. 117, No. 2, 2004.  S. A. McInerny, G. Lu, and S. Olcmen, “Rocket and Jet Mixing Noise, Background and Prediction Procedures”, University of Mississippi Contract UM 03-08-013, 2004.  S. A. McInerny, J. K. Francine, B. S. Stewart, and P. H. Thorson, “The influence of low-frequency instrumentation response on rocket noise metrics,” J. Acoust. Soc. Am., Vol. 102, No. 5, 1997.  S. A. McInerny, “Launch Vehicle Acoustics, Part 1: Overall Levels and Spectral Characteristics & Part 2: Statistics of the Time Domain Data”, Journal of Aircraft Vol. 33, No. 3, 1996.  S. A. McInerny, “Rocket Noise - A Review”, AIAA-90-3981, 1990.  S. A. McInerny, “Peacekeeper Launch Sound Levels at 1000, 2000, and 4000 Feet from the Pad”, ATR-93(3566)- 1, 1993.  S. A. McInerny, “Delta Launch Sound Levels at 1500, 2000, and 3000 Feet from the Pad”, ATR-93(3566)-2, 1993.  S. A. McInerny, “Scout Launch Sound Levels at 1000, 2000, 3000, and 4000 Feet from the Pad”, ATR-93(3566)- 3, 1993.  T. T. Do and N. R. Keegan, “Delta II Launch Sound Levels at Varying Distance from the Launch Pad”, TOR- 96(2108)-2, 1996.  E. E. Yang, “Analysis of Saturn V Launch Acoustic Data”, Cal State University Dissertation.

Commercial Space Operations Noise and Sonic Boom Measurements 16 Apollo Era (Pre-1972) Measurement Documents Various Date: 1950’s-1972 This category of documents comprises historical references from the beginning of the U.S. space program until the early 1970’s. These references contain overall levels and octave-band levels and include both static firings and launch measurements. The early rocket noise measurement data culminated in the development of the acoustic-loading codes contained in NASA SP-8072 (Eldred, 1971). The non- dimensional empirically driven quantities documented in NASA SP-8072 currently serve as the basis for rocket propulsion noise source definitions used in environmental noise analysis. The Saturn launch data, while of low fidelity, may have some limited use in validating far-field modeling efforts. Acoustic Data: Low Trajectory Data: None Weather Data: None Events  Various Saturn V launches, Kennedy Space Center’s LC-39, FL  Various Saturn V S-IC (15) and S-II (30) firings, 1967-1970, Mississippi Test Facility, MS  Various Saturn IB launches (AS-201 and AS-202), 1966, Cape Canaveral Air Force Station, FL  Various Saturn I launches (SA-1 to SA-10), 1961-1965, Cape Kennedy Air Force Station, FL  Other various rocket motor/jet engine static tests/firings Publications  S. H. Guest and R. M. Slone, Jr., “Structural Damage Claims Resulting from Acoustic Environments Developed During Static Test Firing of Rocket Engines”, NASA MSFC, 1972.  K. M. Eldred, “Acoustic Loads Generated by the Propulsion System”, NASA SP-8072, 1971.  S. H. Guest and J. H. Jones, “Far-Field Acoustic Environmental Predictions for Launch of Saturn V and a Saturn V MLV Configuration”, NASA TN D-4117, 1967.  R.C. Potter and M.J. Crocker, “Acoustic Prediction Methods for Rocket Engines, Including the Effects of Clustered Engines and Deflected Exhaust Flow”, NASA CR-566, 1966.  D. A. Bond, “A Summary of Model and Full-Scale Acoustic Data for Prediction of Missile Liftoff Environments”, NOR-64-215, 1964.  S.H. Guest, “Acoustic Efficiency Trends for High Thrust Boosters”, NASA TN D-1999, 1964.  G.A. Wilhold, S.H. Guest, and J.H. Jones, “A Technique for Predicting Far-Field Acoustic Environments Due to a Moving Rocket Sound Source”, NASA TN D-1832, 1963.  W. H. Mayes and Philip M. Edge, “Noise measurements during captive and launch firings of a large rocket- powered vehicle”, NASA TN-1502, 1962.  P. A. Franken and the Staff of Bolt Beranek and Newman Inc., “Methods of Space Vehicle Noise Prediction”, WADC TR 58-343, Vol. II, 1960.  W. H. Mayes, “Some Near- and Far-Field Noise Measurements for Rocket Engines Operating at Different Nozzle Pressure Ratios”, J. Acoust. Soc. Am., Vol. 31, No. 7, 1959.  W. H. Mayes, W. E. Lanford, and H. H. Hubbard, “Near-Field and Far-Field Noise Surveys of Solid-Fuel Rocket Engines for a Range of Nozzle Exit Pressures”, NASA TN D-21, 1959.  J. N. Cole, H. E. Von Gierke, D. T. Kyrazis, K. M. Eldred, and A. J. Humphrey, “Noise Radiation from Fourteen Types of Rockets in the 1,000 to 130,000 Pounds Thrust Range”, WADC TR 57-354 AD130794, 1957.

Commercial Space Operations Noise and Sonic Boom Measurements 17 Other Propulsion Noise Measurement Documents Various Date: 1990’s - Present This category, as its name indicates, describes other rocket propulsion studies with high-quality data. At present, the category includes studies from the Japanese Aerospace Exploration Agency (JAXA), as well as work from U.S. universities and NASA Ames Research Center. Static (e.g., Fukuda, Tam) and launch data (e.g., Smith, Tsutsumi) are considered. The work of Panda (2013, 2014) and Ishii (2016) focuses on noise source identification around the launch pad, whereas Tam (2018) analyzes others’ static firings for characteristics related to large-scale and fine-scale turbulence. Sutherland (1993) and Smith (2013) both treat the overall prediction problem by examining the source sound power and directivity estimates using data related to Eldred (1971). Related to community noise validation, the papers in this category are largely useful for understanding the nature of the noise sources for undeflected and impinging plumes in realistic pad environments, and for establishing physicality of the models. Acoustic Data: Low-High Trajectory Data: None Weather Data: None Events  Falcon 9 launch, 22 May 2012, LC-40, Cape Canaveral Air Force Station.  NAL-735 Motor, December 2007, JAXA’s Noshiro Testing Center.  Orion Crew Vehicle 10” Launch Abort Motor Tests, NASA Ames Facility, CA.  Espilon launch, September 2013, Uchinoura Space Center.  Antares A-1 Launch, 21 April 2013, Mid-Atlantic Regional Spaceport Pad 01B.  Other events include various static firings at ATK small motor and T-6 test facilities, static firings presented in SP-8072, and Saturn V launches at Kennedy Space Center LC-39. Publications  FAA, “Supplemental EA to the December 2014 EA for SpaceX Vertical Landing of the Falcon 9 Vehicle and Construction at Launch Complex 13 at Cape Canaveral Air Force Station”, 2017.  K. Fukuda, S. Tsutsumi, K. Fujii, K. Ui, T. Ishii, H. Oinuma, J. Kazawa, and K. Minesugi, “Acoustic Measurement and Prediction of Solid Rockets in Static Firing Tests”, AIAA 2009-3368, 2009.  W. O. Smith III, “An Empirical and Computational Investigation into the Acoustical Environment at the Launch of a Space Vehicle”, Auburn University Dissertation, 2013.  L. C. Sutherland, “Progress and Problems in Rocket Noise Prediction for Ground Facilities”, AIAA-93-4383, 1993.  C. K. W. Tam, W. C. Horne, N. J. Burnside, and J. Panda, “Spectral Analysis of the Acoustic Near Field of a Solid- Propellant Rocket,“ AIAA Journal, In press, 2018.  Y. Ishii, T. Ishii, J. Hald, H. Oinuma, S. Tsutumi, and K. Ui, “Application of Beamforming using deconvolution method to the development of the new launch pad of Epsilon,“ BeBec 2016-D13, 2016.  S. Tsutsumi, T. Ishii, Kyoichi, S. Tokudome, and K. Wada, “Assessing Prediction and Reduction Technique of Lift- off Acoustics Using Epsilon Flight Data,“ AIAA-2015-1007, 2015.  J. Panda, R. N. Mosher, and B. J. Porter, “Noise Source Identification During Rocket Engine Test Firings and a Rocket Launch,“ J. Spacecraft Rockets, Vol. 51, 1761-1772, 2014.  J. Panda, R. N. Mosher, and B. J. Porter, “Identification of Noise Sources During Rocket Engine Test Firings and a Rocket Launch Using a Microphone Phased-Array”, NASA/TM-2013-216625, 2013.

Commercial Space Operations Noise and Sonic Boom Measurements 18 Sonic Boom Various Date: 1971-1996 This category summarizes published reports on sonic boom measurements during launch and re-entry of space vehicles. Three Apollo missions are documented. The reports describing Apollo 15 and 16 show sonic boom recordings for ascent and descent at various locations along the flight track. The Apollo 17 report, however, puts emphasis on the ascent focus region. Maglieri (2011) provides a detailed summary of Space Shuttle sonic boom measurements, which include both ascent and a larger number of re-entry booms. Finally, Downing and Plotkin provide a comparison of measured and predicted sonic booms for Titan IV launches from Vandenberg Air Force Base. Recorded data fidelity varies from peak overpressure to time signatures. With limited trajectory and weather data, the usefulness of these reports for model validation efforts is reduced. Acoustic Data: Low-High Trajectory Data: Low Weather Data: Low Events  Titan IV launch, 12 May 1996, LC-4E Vandenberg Air Force Base, CA  Various Space Shuttle reentries (18), 1981-1990, Edwards Air Force Base, CA  Various Space Shuttle reentries (5), 1984-1985, Kennedy Space Center, FL  Various Space Shuttle launches (3), 1982-1984, Kennedy Space Center, FL  Apollo 17 – Saturn V, 7 December 1972, Kennedy Space Center’s LC-39A, FL  Apollo 16 – Saturn V, 16 April 1972, Kennedy Space Center’s LC-39A, FL  Apollo 15 – Saturn V, 26 July 1971, Kennedy Space Center’s LC-39A, FL Publications  D. J. Maglieri, H. R. Henderson, S. J. Massey, E. G. Stansbery, “A Compilation of Space Shuttle Sonic Boom Measurements”, NASA/CR-2011-217080, 2011.  J. M. Downing, K. J. Plotkin, “Validation of launch vehicle sonic boom predictions”, Third Joint Meeting of ASA and ASJ, 1996.  H. R. Henderson and D. A. Hilton, “Sonic-Boom Measurements in the Focus Region During the Ascent of Apollo 17”, NASA TN D-7806, 1974.  H. R. Henderson and D. A. Hilton, “Sonic-Boom Ground Pressure Measurements from the Launch and Re-entry of Apollo 16,“ NASA TN D-7606, 1974.  D. A. Hilton, H. R. Henderson, and R. McKinney, “Sonic-Boom Ground-Pressure Measurements from Apollo 15”, NASA TN D-6950, 1972.