BAASS Self-Assessment of UAP Analysis Capabilities, November 2010

Summary Report on BAASS UAP Analysis Capabilities November 23, 2010 Summary Report on BAASSUAP Analysis Capabilities November 23, 2010 TABLE OF CONTENTS pg. LIST OF FIGURES ........................................................................................................................ 4 LIST OF TABLES .......................................................................................................................... 9 1. EXECUTIVE SUMMARY ...................................................................................................... 10 2. INTRODUCTION.................................................................................................................... 13 2.1 HISTORICAL EVENTS AND STUDIES ....................................................................... 13 2.2 BAASS' TWELVE TECHNOLOGY FOCUS AREAS .................................................. 14 2.3 BAASS PERSONNEL, SOFTWARE, EQUIPMENT AND DATA WAREHOUSE ................................................................................................................. 15 2.3.1 BAASS Personnel .................................................................................................... 15 2.3.2 ANSYS Multiphysics FEA ...................................................................................... 16 2.3.3 Equipment ................................................................................................................ 16 2.3.4 Data Warehouse ....................................................................................................... 19 3. TYPES OF UAPS OBSERVED .............................................................................................. 21 4. ANALYTICAL AND NUMERICAL SOLUTIONS FOR UAP INVESTIGATIONS ........... 25 4.1 "TIC TAC" INCIDENT .................................................................................................... 25 4.1.1 Analytical Solutions ofVelocities and Accelerations Associated with "Tic Tac" Performance ............................................................................................ 32 4.1 .2 Summary ofAnalytical Velocity and Acceleration Solutions ................................. 32 4.1.3 Numerical Analysis ofCompressible Flow ............................................................. 39 4.1.4 Summary and Conclusions of Compressible Numerical Analyses .......................... 46 4.1.5 Numerical Analysis of Incompressible Flow ofa UAP Entering Water ................. 47 4.1.6 Numerical Analysis of Incompressible Flow ofa UAP Entering Water Results ...................................................................................................................... 48 4.1. 7 Summary and Conclusions ofNumerical Analysis ofIncompressible Flow of a UAP Entering Water Results ............................................................................ 58 4.2 ANALYSES OF SPHERICAL UAPS .............................................................................. 58 4.2.1 Acoustical Analysis ofa Spherical USO ................................................................. 58 4.2.2 ANSYS Multiphysics Electromagnetic Capabilities ............................................... 82 4.2.3 Radar Cross Section Analysis ofa Spherical UFO .................................................. 83 5. SUMMARY AND CONCLUSION......................................................................................... 98 6. REFERENCES ....................................................................................................................... I00 SYMBOLS AND ACRONYMS ................................................................................................ 102 ATTACHMENT 1-ANSYS INPUT FILES ............................................................................. 105 Summary Report on BAASS UAP Analysis Capabilities Page 2 November 23, 2010 USO ANSYS Multiphysics Acoustics Input File Example .................................................... 105 ATTACHMENT II - "TIC TAC" CFD CONTOUR PLOTS FOR PRESSURE, ATTACHMENT III - RIGHT CIRCULAR CYLINDER CFD CONTOUR PLOTS UAP ANSYS Multiphysics RCS Input File Example ............................................................ 112 TEMPERATURE AND MACH NUMBER............................................................................... 116 FOR PRESSURE, TEMPERATURE AND MACH NUMBER ................................................ 128 Summary Report on BAASS UAP Analysis Capabilities Page 3 November 23, 2010 LIST OF FIGURES pg. Figure 1. The UFO Pattern: A Condensed Statement ofRepeated Observations ........................ 21 Figure 2. Lockheed Martin Skunk Works SR-71 Black Bird ....................................................... 22 Figure 3. Lockheed F-117 Nighthawk Stealth Fighter ................................................................. 22 Figure 4. Northrop Grumman B-2 Spirit Stealth Bomber ............................................................ 23 Figure 5. Boeing Phantom Works B-2 Stealth X-45A UAV ........................................................ 23 Figure 6. Three Dimensional Rendering ofa Cylindrical or "Tic Tac" UAP .............................. 24 Figure 7. Three Dimensional Rendering ofa Metallic Spherical UAP ........................................ 24 Figure 8. Location of the AAV during the F/AI 8 Intercept ......................................................... 26 Figure 9. FLIR in 'White Hot' Mode ............................................................................................ 30 Figure 10. FLIR in "Black I-lot" mode .......................................................................................... 30 Figure 11. Tic Tac Parametric Velocities for Selected Times of Event Duration in ft/sec ......................................................................................................................... 35 Figure 12. Tic Tac Parametric Velocities for Selected Times of Event Duration Figure 14. Tic Tac Parametric Accelerations for Selected Times ofEvent Duration Figure 15. Tic Tac Pressure at I /6 Scale, Air Temperature 223K and 700 mph Figure 16. Tic Tac Temperature at 1 /6 Scale, Air Temperature 223K and 700 mph Figure 17. Tic Tac Mach Number at 1/6 Scale, Air Temperature 223K and 700 mph Figure 18. Tic Tac Pressure at 1/6 Scale, Air Temperature 223K and 1500 mph Figure 19. Tic Tac Temperature at 1/6 Scale, Air Temperature 223K and 1500 mph Figure 20. Tic Tac Mach Number at 1/6 Scale, Air Temperature 223K and 1500 mph Figure 21. Cylinder Temperature at 1/6 Scale, Air Temperature 223K and 700 mph Figure 22. Cylinder Mach Number at 1/6 Scale, Air Temperature 223K and 700 mph Figure 23. Cylinder Pressure at 1/6 Scale, Air Temperature 223K and 1500 mph Figure 24. Cylinder Temperature at 1/6 Scale, Air Temperature 223K and 1500 mph Figure 25. Cylinder Mach Number at 1/6 Scale, Air Temperature 223K and 1500 mph in mph ......................................................................................................................... 36 Figure 13. Tic Tac Parametric Accelerations for Selected Times ofEvent Duration in ft/sec2 ...................................................................................................................... 37 in g .............................................................................................................................. 38 with Mixed Inlet and Supersonic Outlet ..................................................................... 41 with Mixed Inlet and Supersonic Outlet ..................................................................... 41 with Mixed Inlet and Supersonic Outlet.. ................................................................... 42 with Supersonic Inlet and Supersonic Outlet.. ............................................................ 42 with Supersonic Inlet and Supersonic Outlet .............................................................. 43 with Supersonic Inlet and Supersonic Outlet.. ............................................................ 43 with Mixed lnlet and Supersonic Outlet ..................................................................... 44 with Mixed lnlet and Supersonic Outlet ..................................................................... 44 with Supersonic Inlet and Supersonic Outlet.. ............................................................ 45 with Supersonic lnlet and Supersonic Outlet.. ............................................................ 45 with Supersonic Inlet and Supersonic Outlet.. ............................................................ 46 Figure 26. Solid Three Dimensional Geometry ofDisc and Water. ............................................. 50 Figure 27. Solid Three Dimensional Geometry Mesh ofDisc and Water .................................... 51 Figure 28. Solid Three Dimensional Geometry Mesh ofUAP Disc ............................................ 52 Summary Report on BAASS UAP Analysis Capabilities Page4 November 23, 2010 Figure 29. User Generated Cut Analysis Plane ............................................................................ 53 Figure 30. Animated Result, Fluid 2 Volume Fraction................................................................ 54 Figure 31. Total Pressure Around UAP ....................................................................................... 55 Figure 32. Water Surface Effects From Solid Impact.. ................................................................ 56 Figure 33. Water Surface Effects From Solid Impact (Side View) .............................................. 57 Figure 34. Mesh Plot for 1,000 Hz with 25 Elements per Wavelength in Water ......................... 61 Figure 35. Mesh Plot for 1,000 Hz with 50 Elements per Wavelength in Water ......................... 62 Figure 36. Contour Plot ofReal Component ofPressure (Pa) for t ,000 Hz with 50 Elements per Wavelength in Water ............................................................... 63 Figure 37. Contour Plot ofReal Component ofPressure (Pa) for 1,000 Hz Figure 38. Contour Plot of Imaginary Component ofPressure (Pa) for 1,000 Hz Figure 39. Contour Plot of the Magnitude ofPressure (Pa) for 1,000 Hz Figure 40. Steady State Real Component of Pressure (Pa) as a Function of Radial Figure 41 . Steady State Imaginary Component of Pressure (Pa) as a Function with 50 Elements per Wavelength in Water ............................................................... 64 with 25 Elements per Wavelength in Water ............................................................... 65 with 25 Elements per Wavelength in Water ............................................................... 66 Distance (m) Plot for 1,000 Hz with 25 Elements per Wavelength in Water. ............ 67 of Radial Distance (m) Plot for 1,000 Hz with 25 Elements per Wavelength in Water ....................................................................................................................... 68 Figure 42. Steady State Magnitude ofPressure (Pa) as a Function ofRadial Figure 43. Contour Plot ofReal Component ofPressure (Pa) for 5,000 Hz Figure 44. Contour Plot of Imaginary Component ofPressure (Pa) for 5,000 Hz Figure 45. Contour Plot of the Magnitude ofPressure (Pa) for 5,000 Hz Figure 46. Steady State Real Component of Pressure (Pa) as a Function Distance (m) Plot for 1,000 Hz with 25 Elements per Wavelength in Water. ............ 69 with 25 Elements per Wavelength in Water ............................................................... 70 with 25 Elements per Wavelength in Water ............................................................... 71 with 25 Elements per Wavelength in Water ............................................................... 72 of Radial Distance (m) Plot for 5,000 Hz with 25 Elements per Wavelength in Water....................................................................................................................... 73 Figure 47. Steady State Imaginary Component ofPressure (Pa) as a Function of Radial Distance (m) Plot for 5,000 Hz with 25 Elements per Wavelength in Water ....................................................................................................................... 74 Figure 48. Steady State Magnitude of Pressure (Pa) as a Function ofRadial Distance (m) Plot for 5,000 Hz with 25 Elements per Wavelength in Water. ............ 75 Figure 49. Contour Plot ofReal Component ofPressure (Pa) for 10,000 Hz Figure 50. Contour Plot ofImaginary Component of Pressure (Pa) for 10,000 Hz Figure 51. Contour Plot ofthe Magnitude ofPressure (Pa) for I 0,000 Hz Figure 52. Steady State Real Component of Pressure (Pa) as a Function with 25 Elements per Wavelength in Water ............................................................... 76 with 25 Elements per Wavelength in Water ............................................................... 77 with 25 Elements per Wavelength in Water ............................................................... 78 ofRadial Distance (m) Plot for 10,000 Hz with 25 Elements per Wavelength in Water....................................................................................................................... 79 Summary Report on BAASS UAP Analysis Capabilities Page 5 November 23, 2010 Figure 53. Steady State Imaginary Component ofPressure (Pa) as a Function ofRadial Distance (m) Plot for 10,000 Hz with 25 Elements per Wavelength in Water....................................................................................................................... 80 Figure 54. Steady State Magnitude ofPressure (Pa) as a Function ofRadial Distance (m) Plot for 10,000 Hz with 25 Elements per Wavelength in Water ................................ 81 Figure 55. Factors that Determine the Energy Returned by a Target... ........................................ 83 Figure 56. Effect of Distance from the radar to the Target on the· Power Density ....................... 84 Figure 57. Reduction in the Strength ofTarget Echoes with Range ............................................ 87 Figure 58. Geometry, Description and Maximum RCS .............................................................. 88 Figure 59. Radar Cross Section Comparison ............................................................................... 89 Figure 60. Mesh of½ Symmetry UFO Sphere with 25 Elements per Wavelength ..................... 90 Figure 61. Mesh of ½ Symmetry UFO Sphere with 50 Elements per Wavelength ..................... 91 Figure 62. Normalized radar Cross Section Plot for a ½ Symmetry IO m Metallic Sphere with a 1 m Dielectric Coating in Decibels for 300 MHz and 25 Elements per Wavelength ........................................................................................... 93 Figure 63. Normalized radar Cross Section Plot for a½ Symmetry 10 m Metallic Sphere with a 1 m Dielectric Coating in Decibels for 300 MHz and Figure 64. Electric Filed Contour in V/m for a½ Symmetry 10 m Metallic Sphere 50 Elements per Wavelength ...................................................................................... 95 with a I m Dielectric Coating in Decibels for 300 MHz and 25 Elements per Wavelength ........................................................................................................... 96 Figure 65. Tic Tac Pressure at 1/6 Scale, Air Temperature 223K and 100 mph Figure 66. Tic Tac Temperature at 1/6 Scale, Air Temperature 223K and 100 mph Figure 67. Tic Tac Mach Number at 1/6 Scale, Air Temperature 223K and 100 mph Figure 68. Tic Tac Pressure at 1/6 Scale, Air Temperature 223K and 200 mph Figure 69. Tic Tac Temperature at 1/6 Scale, Air Temperature 223K and 200 mph Figure 70. Tic Tac Mach Number at 1/6 Scale, Air Temperature 223K and 200 mph Figure 71. Tic Tac Pressure at 1/6 Scale, Air Temperature 223K and 300 mph Figure 72. Tic Tac Temperature at 1/6 Scale, Air Temperature 223K and 300 mph Figure 73. Tic Tac Mach Number at 1/6 Scale, Air Temperature 223K and 300 mph Figure 74. Tic Tac Pressure at 1/6 Scale, Air Temperature 223K and 400 mph Figure 75. Tic Tac Temperature at 1/6 Scale, Air Temperature 223K and 400 mph Figure 76. Tic Tac Mach Number at 1/6 Scale, Air Temperature 223K and 400 mph with Subsonic Inlet and Subsonic Outlet.. ................................................................ 116 with Subsonic Inlet and Subsonic Outlet .................................................................. 116 with Subsonic Inlet and Subsonic Outlet.. ................................................................ 11 7 with Subsonic Inlet and Subsonic Outlet.. ................................................................ 117 with Subsonic Inlet and Subsonic Outlet .................................................................. 11 8 with Subsonic Inlet and Subsonic Outlet.................................................................. 118 with Subsonic Inlet and Subsonic Outlet.. ................................................................ 119 with Subsonic Inlet and Subsonic Outlet .................................................................. 119 with Subsonic Inlet and Subsonic Outlet.. ................................................................ 120 with Mixed Inlet and Subsonic Outlet ...................................................................... 120 with Mixed Inlet and Subsonic Outlet ...................................................................... 121 with Mixed Inlet and Subsonic Outlet ...................................................................... 121 .. Summary Report on BAASS UAP Analysis Capabilities Page 6 November 23, 2010 Figure 77. Tic Tac Pressure at 1/6 Scale, Air Temperature 223K and 500 mph with Mixed Inlet and Subsonic Outlet ...................................................................... 122 Figure 78. Tic Tac Temperature at 1/6 Scale, Air Temperature 223K and 500 mph Figure 79. Tic Tac Mach Number at 1/6 Scale, Air Temperature 223K and 500 mph Figure 80. Tic Tac Pressure at 1/6 Scale, Air Temperature 223K and 900 mph Figure 81 . Tic Tac Temperature at 1/6 Scale, Air Temperature 223K and 900 mph Figure 82. Tic Tac Mach Number at 1/6 Scale, Air Temperature 223K and 900 mph Figure 83. Tic Tac Pressure at 1/6 Scale, Air Temperature 223K and 1100 mph Figure 84. Tic Tac Temperature at 1/6 Scale, Air Temperature 223K and 1100 mph Figure 85. Tic Tac Mach Number at 1/6 Scale, Air Temperature 223K and 1100 mph Figure 86. Tic Tac Pressure at 1/6 Scale, Air Temperature 223K and 1300 mph Figure 87. Tic Tac Temperature at 1/6 Scale, Air Temperature 223K and 1300 mph Figure 88. Tic Tac Mach Number at 1/6 Scale, Air Temperature 223K and 1300 mph Figure 89. Cylinder Pressure at 1/6 Scale, Air Temperature 223K and 100 mph Figure 90. Cylinder Temperature at 1/6 Scale, Air Temperature 223K and 100 mph Figure 91. Cylinder Mach Number at 1/6 Scale, Air Temperature 223K and 100 mph Figure 92. Cylinder Pressure at 1/6 Scale, Air Temperature 223K and 200 mph Figure 93. Cylinder Temperature at 1/6 Scale, Air Temperature 223K and 200 mph Figure 94. Cylinder Mach Number at 1/6 Scale, Air Temperature 223K and 200 mph Figure 95. Cyljnder Pressure at 1/6 Scale, Arr Temperature 223K and 300 mph Figure 96. Cylinder Temperature at 1/6 Scale, Air Temperature 223K and 300 mph Figure 97. Cylinder Mach Number at 1/6 Scale, Air Temperature 223K and 300 mph Figure 98. Cylinder Pressure at 1/6 Scale, Air Temperature 223K and 400 mph Figure 99. Cylinder Temperature at 1/6 Scale, Air Temperature 223K and 400 mph with Mixed Inlet and Subsonic Outlet ...................................................................... 122 with Mixed Inlet and Subsonic Outlet ...................................................................... 123 with Supersonic Inlet and Supersonic Outlet.. .......................................................... 123 with Supersonic Inlet and Supersonic Outlet ............................................................ 124 with Supersonic Inlet and Supersonic Outlet ............................................................ 124 with Supersonic Inlet and Supersonic Outlet.. .......................................................... 125 with Supersonjc Inlet and Supersonic Outlet ............................................................ 125 with Supersonic Inlet and Supersonic Outlet.. .......................................................... 126 with Supersonic Inlet and Supersonic Outlet.. .......................................................... 126 with Supersonic Inlet and Supersonic Outlet.. .......................................................... 127 with Supersonic Inlet and Supersonic Outlet.. .......................................................... 127 with Subsonic Inlet and Subsonic Outlet.. ................................................................ 128 with Subsonic Inlet and Subsonic Outlet.. ................................................................ 128 with Subsonic Inlet and Subsonic Outlet.. ................................................................ 129 with Subsonic Inlet and Subsonic Outlet.. ................................................................ 129 with Subsonic Inlet and Subsonic Outlet.. ................................................................ 130 with Subsonic Inlet and Subsonic Outlet.. ................................................................ 130 with Subsonic Inlet and Subsonic Outlet.. ................................................................ 131 with Subsonic Inlet and Subsonic Outlet.. ................................................................ 131 with Subsonic Inlet and Subsonic Outlet.. ................................................................ 132 with Subsonic Inlet and Subsonic Outlet.. ................................................................ 132 with Subsonic Inlet and Subsonjc Outlet.. ................................................................ 133 Summary Report on BAASS UAP Analysis Capabilities Page 7 November 23, 2010 Figure 100. Cylinder Mach Number at 1/6 Scale, Air Temperature 223K and 400 mph with Subsonic Inlet and Subsonic Outlet.. ............................................................. 133 Figure 101 . Cylinder Pressure at 1/6 Scale, Air Temperature 223K and 500 mph Figure 102. Cylinder Temperature at 1/6 Scale, Air Temperature 223K and 500 mph Figure 103. Cylinder Mach Number at 1/6 Scale, Air Temperature 223K and 500 mph Figure 104. Cylinder Pressure at 1/6 Scale, Air Temperature 223K and 700 mph Figure 105. Cylinder Pressure at 1 /6 Scale, Air Temperature 223K and 900 mph Figure l 06. Cylinder Temperature at 1/6 Scale, Air Temperature 223K and 900 mph Figure 107. Cylinder Mach Number at 1/6 Scale, Air Temperature 223K and 900 mph Figure l 08. Cylinder Pressure at l/6 Scale, Air Temperature 223K and 1100 mph Figure 109. Cylinder Temperature at 1/6 Scale, Air Temperature 223K and 1100 mph Figure 110. Cylinder Mach Number at 1/6 Scale, Air Temperature 223K and 1100 mph Figure 111. Cylinder Pressure at 1 /6 Scale, Air Temperature 223K and 1300 mph Figure 112. Cylinder Temperature at 1 /6 Scale, Air Temperature 223K and 1300 mph Figure 113. Cylinder Mach Number at 1/6 Scale, Air Temperature 223K and 1300 mph with Mixed Inlet and Subsonic Outlet.. ................................................................. 134 with Mixed Inlet and Subsonic Outlet ................................................................... 134 with Mixed Inlet and Subsonic Outlet ................................................................... 135 with Mixed Inlet and Supersonic Outlet.. .............................................................. 135 with Supersonic Inlet and Supersonic Outlet.. ....................................................... 136 with Supersonic Inlet and Supersonic Outlet.. ....................................................... 136 with Supersonic Inlet and Supersonic Outlet.. ....................................................... 137 with Supersonic Inlet and Supersonic Outlet......................................................... 137 with Supersonic Inlet and Supersonic Outlet ......................................................... 138 with Supersonic Inlet and Supersonic Outlet. ........................................................ 138 with Supersonic Inlet and Supersonic Outlet.. ....................................................... 139 with Supersonic Inlet and Supersonic Outlet.. ....................................................... 139 with Supersonic Inlet and Supersonic Outlet.. ....................................................... 140 Summary Report on BAASS UAP Analysis Capabilities Page 8 November 23,2010 LIST OFTABLES pg. Table 1. Mach Regimes ................................................................................................................ 32 Table 4. Normalized radar Cross Section for a 10 m Metallic Sphere with a 1 m Table 5. Normalized radar Cross Section for a 10 m Metallic Sphere withal m Table 2. Velocities and Accelerations ofTic Tac for Parametric Time Durations ofEvent.. ...... 34 Table 3. Properties ofWater Used for ANSYS Hannonic Analyses ........................................... 60 Dielectric Coating in Decibels for 300 MHz and 25 Elements per Wavelength ............ 92 Dielectric Coating in Decibels for 300 MHz and 50 Elements per Wavelength ............ 94 Summary Report on BAASS UAP Analysis Capabilities Page 9 November 23, 2010 1. EXECUTIVE SUMMARY The purpose of this r,eport is to summarize the field data collection, in-house databases and computational capabilities that currently reside at Bigelow Aerospace Advanced Space Studies (BAASS) for the study of advanced aerospace technology. Between 2008 and 20 IO BAASS was contracted by the Defense Warning Office of the Defense Intelligence Agency (DIA) to create, staff, and equip a new organization in order to examine and analyze the threat to national security associated with advanced aerospace technology. By selecting and modeling a few sentinel cases of encounters with advanced aerospace technology, this report demonstrates the in-house data collection, data storage and analysis resources built by BAASS under DIA contract HHM402-08-C-0072. Throughout the millennia individuals have observed and reported unexplained phenomena in the sky. Some ofthese reports included bright and flashing lights, objects streaking across the sky or silently hovering, and multiple colored and flashing structures morphing into one. Cylindrical, cigar, spherical, lenticular, triangular and ellipsoid shaped structures have been reported hovering and/or accelerating at rapid rates from a stationary position. Some of these abrupt, high speed maneuvers have been harder to explain with conventional physics, considering the inherently poor aerodynamic properties of many ofthese objects. It should be stressed many, but not all, of these sightings may be explained by natural phenomena, or by unacknowledged aerospace technology. Several official government studies were conducted from the late 1940s until around 1970, but many of these studies were superficial and lacking in rigor. Since 1970, because of an absence of research funding, the study of Unidentified Aerial Phenomena (UAP) has been characterized by cursory analysis and amateur, unscientific data collection. Pilots, both civilian and military, have reported seeing unusual objects in the air, some of which have been independently confirmed by radar. During the 1960s and 1970s a series of incidents was reported along the so called Northern Tier of the United States where silent hovering objects were observed over military facilities housing nuclear weapons. One report in March 1967 involving the simultaneous disabling of multiple missiles for a period of time, while a UAP allegedly hovered nearby, stimulated considerable public interest when information of the event began to emerge. The 1967 incident, if true, as well as other Northern Tier incidents, arguably had national security implications. Over the years, there have also been numerous reports of Unidentified Submerged Objects (USO), in all bodies of water. Some USO and UAP reportedly exhibited superior performance capabilities in velocity and acceleration underwater in the absence of detectable turbulence or cavitation signatures. While comparing our state of the art military equipment with these capabilities a reasonable individual may conclude there are national security implications. Bigelow Aerospace Advanced Space Studies, LLC (BAASS) is a research organization focused on the identification, evaluation, and acquisition of novel and emerging future technologies worldwide as they specifically relate to air and space craft. Cutting edge research areas include propulsion systems, space applications of nanosensors, piezoelectric and nanowire fabrics, human performance, plasma stealth technologies, and directed high energy weapons. BAASS Summary Report on BAASS UAP Analysis Capabilities Page 10 November 23, 2010 was contracted to the Defense Intelligence Agency (DIA) in 2008 to investigate and analyze the possibility of a credible threat posed by UAPs. To accomplish this mission, BAASS over the past two years has focused on developing three separate resources, each unique to the study of UAP: 1) to obtain the most comprehensive suite of portable field sensors and personnel available, 2) to build the most all-inclusive database of UAP performance capabilities and behavior in the world and 3) to acquire world class computational methodology for analysis of UAP data. This report touches on all aspects of these resources, but concentrates on the in-house computational capabilities. BAASS acquired the ANSYS Multiphysics Finite Element Analysis (FEA) program, for "a first of a kind" engineering and physics in-house resource devoted to providing a scientifically sound mathematical analysis and modeling of UAP behavior. Thus BAASS has acquired significant computational capability to convert field data into mathematical models and three dimensional simulations. This report provides theory, analytical and numerical solutions for selected UAP and USO incidents through engineering and physics analyses. In particular, we examine a sentinel incident - the "Tic Tac" event - where Fl A-18 aircraft from a United States Carrier Strike Group were vectored to a nearby unidentified contact in November 2004. The white object observed by four F/A-18F aircrew was described as 40 feet in length and shaped and colored like a "Tic Tac" candy. Many analyses of UAP may use analytical or closed form solutions to solve the equations that describe the physics of an event. Where analytical solutions do not exist or the geometry is too complex, ANSYS multiphysics provides a powerful computational platform to solve large problems numerically, while combining and solving many different physical equations. Compressible fluid flow analyses were performed to visualize the steady state pressure, temperature and Mach number contours around two craft shapes. An incompressible fluid flow problem around a solid disc shaped object descending through the air into a body of liquid was investigated to observe the disturbance produced on the surface of the water. A successful analysis of a USO was conducted using a full harmonic acoustics simulation; and computed values showed good agreement with the expected theoretical solutions. An analysis of a spherical UAP radar cross section (RCS) was conducted using a full harmonic electromagnetic simulation. Various other shapes of UAP and USOs may be evaluated by applying boundary conditions and transient physics equations to obtain a better understanding of the capabilities of these objects. BAASS employees and contractors comprise scientists, engineers, analysts, intelligence and investigative professionals with a wide range of technical capabilities and backgrounds. Many of the professional staff members are considered national and international experts in their respective fields. BAASS' personnel have experience in performing work for government agencies such as the Department of Energy and Department of Defense. A broad mandate to research and develop future technology platforms pertaining to advanced propulsion, advanced non- aerodynamic lift capabilities, future material science breakthroughs including nanofabrication, novel power generation and signature reduction technologies, human interaction and effects of advanced technologies including field and radiation biological effects exists in Summary Report on BAASS UAP Analysis Capabilities Page 11 November 23, 20 I 0 BAASS' work scope. BAASS' vision is to identify and acquire disruptive or discontinuous technologies that will fonn the basis of aerospace and defense applications through the year 2050, as well as those that pose potential threats to national security. The company goal is to become a major entity in the research and development of future aerospace propulsion systems, controls, detection and tracking systems, stealth and directed energy uses by employing the best and brightest engineers and scientists available. The previous mentioned capabilities place BAASS in a strong position to provide technical results in both classified and unclassified endeavors. Summary Report on BAASS UAP Analysis Capabilities Page 12 November 23, 2010 _ 2. INTRODUCTION 2.1 lliSTORICAL EVENTS AND STUDIES Disc, triangle, cigar and bell- shaped flying objects have been reported and documented on a global basis for millennia. The sighting by l1843(a)(2) Ion June 24, 1947 in the state of Washington garnered unprecedented global media attention and began the modern UFO era. While flying near Mt. Rainier, he observed a chain of nine unusual objects flying from north to 1843(a)(2) _sou.th.! !reported that "two or three of them would dip or change course slightly, just 1843(a)(2) ;~:~~;~~~~:~~;.~:~~~:v~r~::~~ l~~le 1 l~or:~~~~~~:~!~t~~t:d~~ ~I~~~-~ s~~i::~7,~~~ described them at the time their flight was like speed boats on rough water or similar to the tail of a Chinese kite that l once saw blowing in the wind. As l put it to newsmen in Pendleton, Oregon, they flew like a saucer would if you skipped it across the water." 1843(a)(2) Thus the moniker "flying saucer" was born. The terms "flying saucer" and " · used commonly and interchangeably in the media to describe what are now known as UFOs (Unidentified Flying Object). Many sightings of UFOs were reported by commercial and military pilots during the late 1940s and a flying saucer allegedly crashed outside of Roswell, New Mexico, in early July 1947. Shortly thereafter, a series of sightings of "green fireballs" began. These reports were almost exclusively over the state of New Mexico. Increasing significantly in number by December 1948, these sightings typically occurred over sensitive government installations, most notably the ~~~~:.,;i..l,lol.ll,l,...lol.lil£/.dia National Laboratories. An investigation was initiated by meteor expert After personally witnessing a green fireball four to five degrees above the - on- zo-n- on_ a__o_n__z.....ontal trajectory on December 12, 19481 !concluded the fireballs were 1~~~(~)(2) structured, that is, not atmospheric phenomena. InitiaHy they were thought to be of Russian origin. In April 1950, Project Twinkle was created to be a network of stations with the purpose of observing, studying, and collecting data on the fireball phenomena. This project did little to solve the mystery, and was disbanded later that year. Large numbers of UFO sightings continued in the late 1940s and as a result, some unease about the nature of the objects began to escalate in military circles, notably in the Air Force. For example, in September 1947, Air Force l1843(a)(2) lissued a memorandum stating 'The reported operating characteristics such as extreme rates ofclimb, maneuverability (particularly in roU), and motion which must be considered evasive when sighted or contacted by friendly aircraft and radar, lend belief to the y some of the objects are controlled either manually, automatically or remotely. 11 1843(a)(?L recommended a detailed study of the UFO phenomenon. Based on increasing concern o p rt ofthe military, the U.S. government initiated official studies ofUFOs. Project Sign was the first official U.S. government study of UFOs performed by the United States Air Force in early 1948 and concluded in early 1949. Project Sign officials argued UFOs were likely of extraterrestrial origin, and most of the project's personnel came to favor the extraterrestrial hypothesis. This hypothesis was rejected by the senior Air Force personnel. Project Sign eventually came to no oflicial conclusion about UFOs with the final report staling the existence of flying saucers could neither be confirmed nor denied. Project Sign was concluded and restarted as Project Grudge in February 1949. Summary Report on BAASS UAP Analysis Capabi lities Page 13 November 23, 2010 Project Grudge attempted to give each and every case a solution or an identifier tag. Grudge existed in various form and name until project completion in March 1952. The final Project Grudge report stated 22% of cases were categorized as unidentified, 69% identified, and 9% contained insufficient infonnation to categorize. In March 1952 Project Blue Book replaced Grudge and remained headquartered at the Air Technical Intelligence Center at Wright-Patterson Air Force Base in Ohio. Over the next seventeen years, Project Blue Book recorded approximately 15,000 UFO incidents, and Blue Book reported 701 of these incidents as "unidentifie " • • • • • in 1952 prompted the CIA to convene a scientific panel, 1843(a)(2) m January 1953 to examine recent UFO data. It is wt e y state among mo ·O organizations that the I1843(a)(2) Iadvocated a campaign to "debunk" UFOs. Beginning on November l, 1966, the Air Force Office of Scientific Research awarded $313 000 to a research team at the University of Colorado 1843(a)(2) >-----........ ..---...... .---..........--....-"'" study the scientific implications of UFOs. The stu y was un erta en on t e matena mis e y Project Blue Book. The 1843(a)(2) final (and controversial) conclusion stated "we have recommended agams e moun mg o a ma·or effort for continuing UFO study for scientific reasons." 1843(a)(2) announced Blue Book would be closed due to the fact further funding "cannot be justified either on the grounds of national security or in the interest of science." The last publicly taken report for project Blue Book operations was December 17, 1969, but officially it closed on January 30, 1970. Since the end of Blue Book numerous organizations have taken on the role of UFO/UAP investigations. Few ofthese groups have been professionally organized, trained, or equipped to properly investigate the phenomena. In contrast, one purpose of this report is to show BAASS is on the route to being the leading force in complete investigation and scientific analysis of the phenomena. 2.2 BAASS' TWELVE TECHNOLOGY FOCUS AREAS BAASS is a research organization focused on the identification, evaluation, and acquisition of novel and emerging future technologies worldwide as they specifically relate to air and space craft. Cutting edge research areas include propulsion systems, space applications of nanosensors, piezoelectric and nanowire fabrics, human perfonnance, plasma stealth technologies, and directed high energy technologies. Research and development necessary for the procurement of the technology required for advanced space and weapons systems is conducted through use of computational Multiphysics FEA programs, development of computer code, experimentation, material science testing and manufacturing of prototypes in BAASS/Bigelow Aerospace in-house and in collaborating facilities and laboratories. Research areas of interest include Computational Fluid Dynamics, Heat Transfer, Nuclear Engineering, Electromagnetics and Radio Frequencies, Theoretical and Computational Physics, Biological Sciences and Chemistry. Summary Report on BAASS UAP Analysis Capabilities Page 14 November 23, 2010 Research performed through theoretical and computational applications, as well as modeling of components of non-conventional propulsion systems is under way to provide for future development of vehicles capable of operating in the atmosphere, under water and in space. BAASS research intends to provide innovative approaches and concepts for aircraft, propulsion, and flight technologies demonstrating significant advances in performance and capabilities beyond those in operation today. BAASS' twelve key technology areas concentrate on how breakthrough technologies will provide for the development of advanced spacecraft concepts and weapon technologies through the year 2050 and beyond. The twelve areas are: l. Lift 2. Propulsion 3. Control 4. Power Generation 5. Spatial Temporal Translation 6. Materials 7. Configuration, Structure 8. Signature Reduction 9. Human Interface I0. Human Effects 11. Armament 12. Other Peripheral Areas 2.3 BAASS PERSONNEL, SOFTWARE, EQUIPMENT AND DATA WAREHOUSE Although the majority of this report is devoted to demonstrating BAASS' capabilities in mathematical modeling of various UAP performance parameters, the next section provides a short summary of some ofthe BAASS personnel, portable data collection sensors, as well as the current BAASS in-house database architecture. 2.3.1 BAASS Personnel BAASS employees and contractors comprise scientists, engineers, analysts, intelligence and investigative professionals from diverse backgrounds. A majority of BAASS personnel have performed work for government agencies such as the Department of Energy and Department of Defense. Research and development necessary for the procurement of the technology required for advanced space and weapons systems is conducted by numerical computational analysts through use of computational multiphysics FEA programs. Application and scientific programmers are involved in development of computer code that drives data mining and scientific applications used to evaluate historical and present UAP cases. Professionals in all areas conduct experimentation, material science testing and manufacturing of prototypes in both in-house facilities and collaborating facilities and laboratories. Areas of concentration include Summary Report on BAASS UAP Analysis Capabilities Page 15 November 23, 2010 Computational Fluid Dynamics (CFO), Heat Transfer, Nuclear Engineering, Electromagnetics and Radio Frequencies (RF), Theoretical and Computational Physics, Biological Sciences and Chemistry. 2.3.2 ANSYS Multiphysics FEA The ANSYS Workbench platform is a powerful multi-domain simulation environment that harnesses the core physics from ANSYS, enables their interoperability, and provides common tools for interfacing with CAD, repairing geometry, creating meshes and post-processing results. To our knowledge, this powerful computational capability has not been previously utilized in the 64 year history of UFO study. It is hypothesized that through this more broad ranging analysis, additional theoretical constructs can be generated regarding UAP and USO behavior. These in tum can provide the scaffolding for advanced engineering concepts. 2.3.3 Equipment 2.3.3.1 Field Investigative Equipment BAASS has amassed a considerable amount of field investigative equipment. The inventory includes a variety of iimaging devices, along with Global Positioning Systems (OPS) and range finding items. Of note are the following: 2.3.3.1.1 Canon 50 MK II Digital SLR Cameras Two Canon 5D MK 11, 21.1 Megapixel, Digital SLR cameras were selected based on their capability for low light photography when combined with the Canon EF 300 mm ultrasonic, and the Canon EF 24-105 mm ultrasonic lenses. The 21.1 Megapixel size allows for RAW images suitable for scientific examination and analysis. 2.3.3.1.2 Sony A350 Digital SLR camera The Sony A350 is a 14.2 Megapixel, digital SLR camera, with a Sony N 50-300 mm, a Sony N 50-70 mm lens, and a Sony Macro 2.8/50 mm lens. The a350 while a high quality camera, is compact and portable. It also allows for close-up and one-to-one photography. 2.3.3.1.3 Sony High Definition Video Cameras Three Sony High Definition Video (HOV) 1080i, High Definition Video cameras, with low light capability were chosen for video capture in various field conditions. 2.3.3.1.4 Sony Handicam, Digital Video Cameras Four Sony Handicam, digital video cameras with 80 GB hard drive storage capacity. These cameras are compact and portable, and using the HOD allow for up to 4 hours of continuous video recording with no tapes or other external media. They can also capture still images. Summary Report on BAASS UAP Analysis Capabilities Page 16 November 23, 2010 2.3.3.1.5 ATT PVS-7, Night Vision Devices Seven A TT PVS-7, Nmght Vision Devices - military quality, state-of-the-art night vision devices. 2.3.3.1.6 Oasys Universal Thermal Monocular (UTM) This device is a ruggedizcd thermal imaging and designation system. It includes a digital magnetic, both still and video capture capability as well as a digital PC interface allowing for real-time review ofimages in the field. 2.3.3.1.7 Garmin Global Positioning Systems One Colorado 400t and two Oregon 400t, Global Positioning Systems, allowing for route mapping as well as waypoint storage in the field. 2.3.3.1.8 Leica Rangemaster 1200 Laser Range Finders These two range finders are accurate out to 1500 meters, extremely compact and user friendly. 2.3.3.1.9 Sony CyberShot Cameras Three Sony CyberShot I0.1 megapixel digital cameras - compact and portable for quick reaction to opportunities while actively investigating. These equipment items give BAASS considerable capability when investigating events in the field. In addition to the items listed above a wide range of other support type items are in the BAASS inventory. These include Toshiba laptop computers, digital voice recorders, digital Game Cameras, TR spot lights, power invertors, several pieces of older night vision equipment, and packaging and storage items for solid, liquids, and hazardous materials. In addition, BAASS obtained Technical Surveillance Countermeasures (TSCM) equipment in an effort to enhance the security of BAASS facilities. ln addition to the below listed TSCM equipment BAASS personnel are trained by Research Electronics International in Cookeville, TN; also the manufacturer of the equipment. • OSCOR 5000E, Omni-Spectral Correlator covering the radio frequency range from 50 kHz to 3 GHz • ORION Non-Linear Junction Detector • T ALAN Telephone Analyzer • CPM-700 Broadband Detector Summary Report on BAASS UAP Analysis Capabilities Page 17 November 23, 20 10 2.3.3.2 Scientific Equipment 2.3.3.2.1 Veho VMS-001 200X 1.3 Megapixel Digital USB Microscope This instrument is a very portable (4.4 x 1.3 inches) digital microscope which expands the capability of the field! investigators. The microscope allows detailed images to be taken and connects directly to a laptop. Illumination is via 4 built in white LED lights. 2.3.3.2.2 Celestron 44340 3.5" LCD Digital Microscope This instrument is a bench top digital microscope. The microscope has magnification capabilities of 40-400,X extending up to 1600X with digital zoom. Images can be uploaded to a PC or laptop via a USB connection. It could also be taken into the field if required. 2.3.3.2.3 Niton XL3t 900S GOLDD Analyzer This instrument is an X-ray fluorescence (XRF) analyzer. The device analyzes the emission of characteristic "secondary" (or fluorescent) X-rays from a material that has been excited by bombarding with high-energy X-rays. BAASS field teams deploy the Niton and conduct on-site elemental analysis. 2.3.3.2.4 Colibri TTC Handhcld Dose Rate Meter This instrument package allows for the detection and quantification of alpha, beta and gamma radiation in the field. The ability to accurately measure and quantify these three types of radiation adds another critical level ofcapability to the BAASS arsenal ofanalysis. 2.3.3.2.5 Hand held Spectrum Analyzer Pro Bundle 3 (NF-5030 and HF-60100) These are instruments designed to detect and measure a broad spectrum of electromagnetic (EMF) radiation and high frequency radio waves. The NF-5030 measures three dimensional magnetic fields from as low as background up to 20 Gauss. Combining the two instruments electric fields are measured from 0.1 V/m to 20 kV/m and frequencies from 1 Ilz to 9.4 Gllz. Summary Report on BAASS UAP Analysis Capabilities Page 18 November 23, 2010 2.3.3.6 Hardware for ANSYS Workbench Platform The research and work performed by BAASS ranges from technical design and prototyping, all the way up to advanced theoretical and computational studies of partial differential equations describing multiphysics problems. An expandable twelve core Hewlett Packard server with 48 GB of RAM and I TB of storage is used to perform parallel processing solutions for structural, fluid flow, heat transfer, high and low frequency electromagnetic problems along with coupled physics oftwo or more of those listed previously. 2.3.4 Data Warehouse BAASS developed a Data Warehouse to support research on UAP and related anomalies and titled it "Project CAPELLA". The BAASS Data Warehouse is revolutionary because it: 1) AAP Person incorporates a format ~a~_c!_on _the~ - JSix Layer Model for analyzing UAP, 2) ~· MP 58 •·· includes several new databases developed by BAA S, and 3) incl.udes databases developed by erson others which have never been collectively analyzed. The Data Warehouse currently consists of eleven separate databases and their associated supporting documentation in electronic format such as witness interviews, photographs, videos, recordings, sketches, analytical reports, etc. Each of the databases contains UAP sighting events relating lo the purpose of that particular database, although some of the reported cases do overlap. Four of the databases will continue to catalogue current and future sighting reports. Seven of the databases have been completed and fully integrated and populated with all pertinent information captured by the CAPELLA format. BAASS will continue to input historical data in the CAPELLA format and will expand the Data Warehouse with additional databases and unusual aerial phenomena information. The eleven databases currently included in the Data Warehouse are: I . NIOS Database 2. l 1843(a)(2) !Pilot Database 3. Sign/Grudge/Dlue Book Database 4. UFOCA T Database 5. MUFON Case Management System Database 6. Project Colares Database 7. Canadian Release Database 8. United Kingdom Release Database 9. BAASS Database 10. Utah Ranch Database 11. Post-Utah Ranch EITects Database Summary Report on BAASS UAP Analysis Capabilities Page 19 November 23, 20 I 0 The BAASS Data Warehouse is an electronic repository for historical, ongoing, and future UAP reporting and investigations. The Data Warehouse is designed to facilitate sophisticated analyses and data mining to improve our understanding ofthe extent, structure, and frequency of UAP, as well as their potential correlation to known physical, environmental, biological, or socio-political factors. 2.3.4.1 CAPELLA Format AAP Person 5, AAP The CAPELLA database format is based upon the "Six Layer Model for Ano alous Person 58 0 Phenomena" developed by !AAP Person 5 Iand .,..fA ....,...P_P_e_rs_...,n,...s..,.a ..... 1i.....-................................. ·~ _ ... --·_---_.. ....................1 1 This six layer model encapsulates all of the potential characteristics o UAP events that can e studied. The six layers are: 1. The Physical Layer - those physical characteristics associated with a UAP event 2. The Anti-Physical Layer - the patterns that conflict with those predicted in modem physics 3. The Psychological Layer - the psychological impacts to the witness(es) and the social conditions that surround them 4. The Physiological Layer - the effects perceived by humans 5. The Psychic Layer - the effects commonly found in parapsychology literature 6. The Cultural Layer - the primary and secondary effects upon society. Additionally, the CAPELLA format captures administrative details associated with the UAP event, such as witness information, location, date, time, duration, etc. 2.3.4.2 Data Warehouse Upgrade BAASS is undergoing a database upgrade project to further enhance data security and integrity, and increase processing power for greater analytical capability. The CAPELLA framework and methodologies will be preserved in the upgraded system. This upgrade will increase efficiency and effectiveness, and will allow databases to be analyzed individually or collectively. 2.3.4.3 Statistical Analysis BAASS h u~OJ21$.1S::a....LimL:.1S:~ l, yet comprehensive statistical analyses for three of the databases: !i:-"TT':=c:-T~=~--,r,:1 Pilot Database, Pro·ect Si n/Grudge/Blue Book Database, and the U anc a ase. e analyses on th 1843(a)(2) and Blue Book databases are focused on identifying patterns of technical information om e case reports. The Utah Ranch analysis delves into patterns and aspects of when anomalous activity is reported in an attempt to identify potential times and improve the means of future detection methods. Summary Report on BA.ASS UAP Analysis Capabilities Page 20 November 23,2010 3. TYPES OF UAPS OBSERVED NASA aeronautical engineed 1843(a)(2) Imade important inroads into attempts to delineate some quantitative characteristics ofUFO perfonnance by close examination of, and derivation of numerical parame • . ligated sentinel UFO casesP843(a)(2) I ln addition, computer scientist AAP Person 5 has attem ted to compute estimates of optical power output derived from reports AAP Person 5 This report attempts to extend and broaden these preliminary studies using considerably enhanced computational power and mathematical modeling capabilities. Figure 1, taken froml1843(a)(2) !depicts illustrations of the various shapes associated with the UAP phenomena. THE UFO PATTERN A Cond«!Mcl Statement ofRepeated Obsemltions CONAGUUJIOMOF HIGNLY ll9(Al1NG SHAPES .IAUC'.M • IU#'SOINl,..,o,#oofWJ' 0 0 ......... ~, ~ ,~ , l>offltclS-.. u,,lkulo, S.UCt< OIOill< '"'°'''ommonl • OOU..HAT "'E:3 " ,,,.... • C'OMCMHA1(,,.., :A­o • MTUM (:): NOrf:(IJSll#w,-b.,,_r,p;a,lnlg#lllinwoitglow.(1}Dml>-dal-"<:olanlMineltra««OJtlsol.,,,-,y,(3}Glonldi,ors/tow,,._ol,o. Figure 1. The UFO Pattern: A Condensed Statement of Repeated Observations As an important component of these studies, BAASS understands a considerable number, possibly a majority, of UAP reports can be explained by simple misidentification of current advanced technology platforms. Some recent black triangle and even possibly some saucer and hat shaped UAP reports over the last several decades may have been explained by aircraft sightings of the Lockheed SR-71 Blackbird (Figure 2), Lockheed F-117 Nighthawk Stealth Fighter (Figure 3), Northrop Grumman B-2 Spirit Stealth Bomber (Figure 4) and Boeing Phantom Works Stealth X-45A Unmanned Arial Vehicles (UAV) (Figure 5). Nevertheless, a significant number of cylindrical and cigar shapes along with spherical, lenticular and ellipsoid Summary Report on BAASS UAP Analysis Capabilities Page 21 November 23, 2010 shaped UAPs which appear to hover and/or accelerate at rapid rates from a stationary position have been harder to explain considering the inherently poor aerodynamic properties of these objects. It is this latter subset of UAP reports that BAASS has focused on. Figure 2. Lockheed Martin Skunk Works SR-71 Black Bird Figure 3. Lockheed F-117 Nighthawk Stealth Fighter Summary Report on BAASS UAP Analysis Capabilities Page 22 November 23. 2010 Figure 4. Northrop Grumman B-2 Spirit Stealth Bomber Figure 5. Boeing Phantom Works B-2 Stealth X-45A UAV Summary Report on B/\ASS IJAP Analysis Capubilitic:s Pugc 21 November 23. 2010 Figure 6. Three Dimensional Rendering of a Cylindrical or "Tic Tac" UAP Figure 7. Three Dimensional Rendering of a Metallic Spherical UAP Summary Report on BA ASS UAP Analysi'> <'arabilities Page 24 November 23, 20I 0 4. ANALYTICAL AND NUMERICAL SOLUTIONS FOR UAP INVESTIGATIONS 4.1 "TIC TAC" INCIDENT The following summary is excerpted from the report of an investigation conducted by personnel assigned to DIA of an observation by elements of the Nimitz Carrier Strike Group of UAP off the coast of Mexico in November 2004. Note: The DIA personnel who wrote the report utilized the term Anomalous Aerial Vehicle (AAV) rather than the more common Unidentified Aerial Phenomenon (UAP) or Unidentified Flying Object (UFO). All three terms, AAV, UAP, and UFO are used at different times in this section and should be considered interchangeable. During the period of approximately I 0-16 November 2004, the Nimitz Carrier Strike Group (CSG) was operating off the western coast of the United States in preparation for their deployment to the Arabian Sea. The USS Princeton on several occasions detected multiple Anomalous Aerial Vehicles (AAVs) operating in and around the vicinity of the CSG. The AAVs would descend "very rapidly" from approximately 60,000 feet down to approximately 50 feet in a matter of seconds. They would then hover or stay stationary on the radar for a short time and depart at high velocities and tum rates. On 14 November after again detecting the AAV, the USS Princeton took the opportunity of having a flight oftwo FlA-18Fs returning from a training mission to further investigate the AAV. The USS Princeton took over control of the F/A-l 8s from the E-2C Airborne Early Warning aircraft and vectored in the f/A- l 8s for intercept leading to visual contact approximately one mile away from the AAV, which was reported to be "an elongated egg or a 'Tic Tac' shape with a discernable midline horizontal axis." It was "solid white, smooth, with no edges. It was "uniformly colored with no nacelles, pylons, or wings." It was approximately 46 feet in length. The F/A-18Fs radar could not obtain a 'lock' on the AAV; however it could be tracked while stationary and at slower speeds with the Forward Looking Infrared (FLIR). The AAV did take evasive actions upon intercept by the F/A-18 demonstrating an advanced acceleration (g), aerodynamic, and propulsion capability. The AAV did not take any offensive action against the CSG; however, given its ability to operate unchallenged in close vicinity to the CSG it demonstrated the potential to conduct undetected reconnaissance leaving the CSG with a limited ability to detect, track, and/or engage the/\/\V. According to l1843(a)(2) Ithe AAVs would descend from a very high altitude into the scan volume of the AN/SPY-1 at a high velocity. The top of the scan volume would put the AAVs at higher than 60,000 feet. The AAVs would descend "very rapidly" from approximately 60,000 feet down to approximately 50 feet in a matter of seconds. They would then hover for a short time and depart at high velocities and at tum rates demonstrating an advanced acceleration (g) capability. p843(a)(2) 7 added that based on his experience, which is 17 years as a Fire Control on Aegis cruisers, Che AA V exhibited ballistic missile Characteristics in reference to its appearance, velocity, and indications on the radar. Since the radar was in the mode to handle /\ir Intercept of conventional aircraft it never obtained an accurate track of the AAVs and was quickly "dropped" by the radar meaning it was eliminated by the computer to reduce the amount ofclutter on the radar, as any other false target is handled. If the radar were set up in a mode for Ballistic Missile tracking they likely would have had the capability to track the AAV. They were detected three separate times during the week operating off the western