| Tactical Conflict Detection and Resolution in a 3-D Airspace |
APR 2001 |
17 pages |
| Authors:
Gilles Dowek; Cesar Munoz; Alfons Geser; INSTITUTE FOR COMPUTER APPLICATIONS IN SCIENCE AND ENGINEERING HAMPTON VA
|
 | This paper presents an algorithm for detection and resolution of air traffic conflicts in a 3- dimensional (3-D) airspace for two aircraft, namely ownship and intruder. A conflict is a projected incursion of the intruder aircraft within the protected zone of the ownship. A solution is a single maneuver, to be performed by the ownship, that effectively keeps the required minimum separation without cooperation of the intruder aircraft. The input ... |
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| Fuzzy Control for Autonomous Ground Vehicles |
2000 |
15 pages |
| Authors:
Jeffrey S. Wit; Carl D. Crane III; David G. Armstrong Ii; WINTEC INC PANAMA CITY FL
|
| The Center for Intelligent Machines and Robotics (CIMAR) at the University of Florida has worked in the area of autonomous ground vehicles (AGVs) for several years under the sponsorship of the Air Force Research Laboratory at Tyndall Air Force Base, Florida. The objective of the work is to develop technological capabilities that can be applied to a variety of Air Force needs and application areas. Recently, one of these capabilities ... |
|
| The 55-MPH Highway Speed Limit Revisited: A Case-Control Study |
09 SEP 1998 |
62 pages |
| Authors:
Grover K. Yamane; AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH
|
| Motor vehicle accidents are a significant public health problem in the US. Several host, agent, and environmental factors influence the risk of crash death. Over the past several years, maximum highway speed limits have been raised in several states. Most studies have concluded that the increased limits have increased motor vehicles deaths. In this study, a case-control design was used to estimate the strength of association ... |
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| Flight Test Evaluation of a Differential Global Positioning System Sensor in Runway Performance Testing |
04 AUG 1998 |
|
| Authors:
Kenneth Paul Germann; MISSISSIPPI STATE UNIV MISSISSIPPI STATE
|
 | This study discusses the use of a carrier phase differential global positioning system (DGPS) receiver set in basic takeoff and landing performance flight testing. A technique for using DGPS receivers as theodolites in takeoff and landing performance tests is developed. Both position and velocity data are available from a DGPS receiver. As a result distances can be calculated by differencing the position coordinates or by ... |
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| Tire Test Correlation: Radial Versus Bias-Ply Tires |
MAR 96 |
32 pages |
| Authors:
Rich Anderson; GALAXY SCIENTIFIC CORP EGG HARBOR TOWNSHIP NJ
|
| The temperature performance of a radial tire was correlated with a bias ply tire of identical size under controlled laboratory dynamometer conditions. The general effects of increases in load and ground speed on the temperature profiles of each tire were compared. The results indicated that the bias ply tire used during the tests was more adversely affected by increases in load and speed than the radial tire. However, to further ... |
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| Measuring Mass and Speed at the National Training Center |
OCT 94 |
29 pages |
| Authors:
Dwight J. Goehring; Robert H. Sulzen; ARMY RESEARCH INST FOR THE BEHAVIORAL AND SOCIAL SCIENCES ALEXANDRIA VA
|
| In this report, a method is proposed and tested for measuring the massing of ground forces in force-on-force simulated combat. The relationship of the mass as well as the speed of an attacking force to attrition-based performance is explored. The researchers used archival data generated at the National Training Center, Fort Irwin, California. Successful attacking task forces were found to have had greater massing and to have closed with the ... |
|
| ATLAS 60' Fording Study |
03 MAR 1992 |
561 pages |
| Authors:
CATERPILLAR INC PEORIA IL DEFENSE PRODUCTS DEPT
|
| The All-Terrain, Articulated Lift System (ATLAS) is the next generation of rough-terrain, shooting boom, fork-lift trucks. ATLAS operational requirements call for a dash speed of 50 mph, 60 inches of seawater fording capability for Logistics-Over-the-Shore (LOTS) operations, 10,000 lbs lift capacity at 4 feet and 4,000 lbs lift capacity at 21.5 feet and enhanced operator controls. For ATLAS to reach the procurement phase, production and operating costs must be managed ... |
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| KRMS (K-Band Radiometric Mapping System) SSM/I Validation March 1988 Quick Look Report |
JAN 89 |
|
| Authors:
L. D. Farmer; Duane T. Eppler; Bruce Heydlauff; D. Olsen; NAVAL OCEAN RESEARCH AND DEVELOPMENT ACTIVITY STENNIS SPACE CENTER MS
|
| The primary objective of this mission was to provide high-re solution passive microwave imagery in support of the NASA SSM/I sea ice algorithm verification program. Four flights were flown, originating from Eielson AFB, Fairbanks, Alaska, over the Chukchi Sea, the Beaufort Sea, and the Bering Sea. The Ka-band Radiometric Mapping System (KRMS) was flown from 6 to 14 March 1988. Data were collected on each of four days during this ... |
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| Optical and Event-Duration Variables Affecting Self-Motion Perception |
NOV 85 |
|
| Authors:
Dean H. Owen; OHIO STATE UNIV RESEARCH FOUNDATION COLUMBUS
|
| This paper includes four experiment sections. The first pair of experiments investigated the usefulness of optical flow acceleration in detecting descent. When sink rate and ground speed are constant, optical flow accelerates. Holding fractional loss in altitude constant throughout a descent event also holds flow rate invariant, eliminating flow acceleration as a potential source of information. Detection of descent was accomplished easily without flow acceleration, and it was found that ... |
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| Airspeed and Wind Shear Measurements with an Airborne CO2 Continuous Wave Laser |
JUL 1983 |
|
| Authors:
A. A. Woodfield; J. M. Vaughan; ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (ENGLAND)
|
| The Laser True Airspeed System (LATAS) developed by the Royal Aircraft Establishment and Royal Signals and Radar Establishment and installed on the RAE HS 125 research aircraft is described. It has proved exceptionally reliable and rugged. Examples of results are presented including a climb to 43000 ft; flight through a severe thunderstorm wind shear (microburst); pressure error measurements; and signals observed in cloud, heavy rain and from solid objects such ... |
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| Mobility and Transportability Assessment of a Generic High Mobility Multipurpose Wheeled Vehicle (HMMWV) |
FEB 1983 |
|
| Authors:
Wayne E. Ferguson; Lawrence E. Martin; Joseph M. Rouse; Edward T. Kusterer; ARMY MATERIEL SYSTEMS ANALYSIS ACTIVITY ABERDEEN PROVING GROUND MD
|
| The performance of the HMMWV is analyzed and compared to the vehicles which it will replace. A generic HMMWV is postulated. The vehicles are assessed for off-road and on-road performance in Europe and the Mid-East. The performance criteria are: Speed profiles, percentages of total terrain area in which the vehicles were immobilized, factors using immobilization, factors limiting speed, vehicle acceleration, speed on slopes and stability during turns on side slopes. ... |
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| Simulation Study of Traffic-Sensor Noise Effects on Utilization of Traffic Situation Display for Self-Spacing Task |
FEB 1983 |
|
| Authors:
David H. Williams; Gene C. Moen; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CENTER
|
| A simulation study was undertaken to determine the effect of traffic- sensor noise on the ability of a pilot to perform an in-trail spacing task. The tests were conducted in a fixed-base cockpit simulator configured as a current- generation transport aircraft, with an electronic traffic display provided in the weather-radarscope location. The true positions of the traffic were perturbed in both relative range and azimuth by random errors to simulate ... |
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| Factors Affecting in-Trail Following Using CDTI (Cockpit Display of Traffic Information), |
JAN 1983 |
|
| Authors:
James R. Kelly; David H. Williams; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CENTER
|
| A joint NASA-FAA program is being conducted to explore the potential benefits and liabilities of Cockpit Display of Traffic Information (CDTI) for a broad range of applications. As part of this effort, piloted simulations have been conducted to determine the effect of various display parameters and separation criteria on terminal area in-trail following using CDTI. Both a conventional air carrier configuration, wherein the traffic data is presented on a centrally ... |
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| Development of Curves for Estimating Aircraft Arresting Hook Loads |
JUL 1982 |
|
| Authors:
Lyle W. Jones; AIR FORCE FLIGHT TEST CENTER EDWARDS AFB CA
|
| This Technical Information Memorandum was written to provide AFFTC engineers with a reliable, accurate method for predicting maximum aircraft arresting hook loads based on a knowledge of aircraft weight and groundspeed at the moment of cable engagement. Possible causes of excessive data dispersion are discussed and guidelines for minimizing dispersion are provided. Families of curves relating hook load and groundspeed which fit BAK-12ER and BAK-13 arresting system test data are ... |
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| A Digital Simulation Program Describing the Motion of an Aircraft Undergoing Engine Failure During Its Takeoff Ground Roll |
SEP 1981 |
|
| Authors:
Michael J. Miedlar; AERONAUTICAL SYSTEMS DIV WRIGHT-PATTERSON AFB OH
|
| This report presents a non-interactive 'MIMIC' program developed to generate the time history of an aircraft undergoing an engine failure during its ground roll. The program calculates the forces and moments acting on the aircraft, and uses MIMIC's implicit integration routine to track its motion. The equations and assumptions used are presented and discussed. This report also lists the program and delineates its functions. (Author) |
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| Terrain Microroughness and the Dynamic Response of Vehicles |
JUN 1981 |
|
| Authors:
Richard A. Weiss; ARMY ENGINEER WATERWAYS EXPERIMENT STATION VICKSBURG MS
|
| The design of vehicles with particular operating characteristics on rough terrain requires accurate descriptors of terrain roughness. At present a one parameter description of surface roughness is available that uses the standard deviation of a detrended elevation profile. In order to introduce the frequency content of the terrain into the roughness description, a three parameter model of the surface roughness power spectrum is developed whose parameters are determined from the ... |
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| Calibration of the R/V ATHENA Speed Sensor |
APR 1981 |
|
| Authors:
Shelton M. Gay; James A. Heffner; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD SHIP PERFORMANCE DEPT
|
| The Kenyon knotmeter on the R/V ATHENA was calibrated at sea. The calibration method is based on use of the ship's LORAN-C and CC-2 computer to provide a measure of ship speed relative-to-ground. However, the calibration procedure also accounts for ocean current speed and direction. Thus the technique results in an accurate measure of ship speed relative-to-water upon which the knotmeter calibration can be based. Calibration data indicate that the ... |
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| Groundspeed/Airspeed Differences as a Wind Shear Indicator and Flight Evaluation of a DME-Derived System to Determine Groundspeed. |
FEB 1981 |
|
| Authors:
David M. Lawrence; FEDERAL AVIATION ADMINISTRATION TECHNICAL CENTER ATLANTIC CITY NJ
|
| The use of groundspeed in conjunction with airspeed as a wind shear indicator is discussed. It is shown that a satisfactory indication of headwind can be obtained using indicated airspeed and a low-cost groundspeed measurement device. This report describes the flight test and evaluation of a distance measuring equipment (DME) range-rate derived system for measuring airplane groundspeed. The system consists of a specially developed airborne unit operating in conjunction with ... |
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| An Output Diagnosis Program for the NATO Reference Mobility Model. |
DEC 1980 |
|
| Authors:
Peter M. Brady Jr; STEVENS INST OF TECH HOBOKEN NJ DAVIDSON LAB
|
| The NATO Reference Mobility Model (NRMM) produces a prediction of the speed at which a vehicle can traverse an area (terrain unit). The program described here uses selected values calculated in the NRMM to determine the factor which is the limiter for a vehicle and terrain unit. In the case of a NO-GO prediction, the reason for the NO-GO is deduced. Detailed and summary diagnostic tables are produced together with ... |
|
| Angle Sensing System. |
18 MAR 1980 |
|
| Authors:
Bernard L. Lewis; DEPARTMENT OF THE NAVY WASHINGTON DC
|
| A system for measuring, in conjunction with a GCA radar, the crab angle of an aircraft which is making its landing approach above a runway. A loop antenna mounted on the craft transmit an audio-frequency electromagnetic wave to two sets of crossed receiving loops, each set mounted at one side of the runway. A line joining the centers of the loops makes a 45 deg angle with the plane of ... |
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| A Means of Specifying a Standard Reference Wet Surface for Military Aircraft, |
OCT 1979 |
|
| Authors:
R. W. Sugg; DEFENCE RESEARCH INFORMATION CENTRE ORPINGTON (ENGLAND)
|
| Aircraft specifications which quote stop distances under dry conditions can be misleading since it is the wet case which gives the longer stop distance and may define the length of an operational runway. Trials have shown however, that the wet stop distance can be between 10% and over 100% longer than the dry distance depending on factors such as water depth and surface type. To try and overcome this problem, ... |
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| An Investigation into Measuring Runway Surface Texture by the Grease Patch and Outflow Meter Methods, |
OCT 1979 |
|
| Authors:
R. W. Sugg; DEFENCE RESEARCH INFORMATION CENTRE ORPINGTON (ENGLAND)
|
| A measurement of 'surface texture' is used by some organizations as a means of specifying runway friction for stop distance calculations and certification purposes in spite of the conclusion by the American Society for Testing and Materials that it should be discontinued. This investigation confirms the ASTM conclusions by demonstrating the poor relationship between 'surface texture' and aircraft stop distance also between it and friction measured by two ground vehicles. ... |
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| Terrain Contour Matching (TERCOM): Sensitivity to Heading and Ground-Speed Errors. |
MAY 1978 |
|
| Authors:
Mark W. Cannon Jr; AEROSPACE MEDICAL RESEARCH LAB WRIGHT-PATTERSON AFB OHIO
|
| A simulation of the TERCOM navigation system is presented and the effects of a number of error sources are studied. Two error sources are course heading and ground-speed variation. A third source is the fact that the radar altimeter samples the terrain at geographical coordinates lying between coordinates that specify the locations of terrain altitudes stored in the on-board computer. The latter is shown to be an insignificant error with ... |
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| Piloted Flight Simulation Study of Low-Level Wind Shear Phase 3. All-Weather Landing Systems, Engineering Services Support Project, Task 2. |
MAR 1978 |
|
| Authors:
W. B. Gartner; D. M. Condra; W. H. Foy; W. O. Nice; C. E. Wischmeyer; SRI INTERNATIONAL MENLO PARK CA AVIATION SYSTEMS LAB
|
| This task is concered with development and test by piloted flight simulation of airborne techniques designed to aid the pilot to detect and cope with low-level wind shear. This report documents the Phase 3 tests on a DC-10 aircraft simulator, involving a set of wind profiles significantly expanded over those used previously and an especially large group (26) of subject pilots in the major test. The operational situation simulated was ... |
|
| APL Arctic SEV Subsystem Development Program. |
JUN 1977 |
|
| Authors:
T. Thompson; L. L. Warnke; JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB
|
| APL conducted a study to define the navigation, terrain surveillance, and communications subsystem requirements in developing a large, high-speed, long-range Arctic-based Surface Effect Vehicle (SEV). During 1970-1974, APL participated in a program to develop the technology required to use the SEV's potential as a high performance platform for Arctic operations. APL's task was to provide the obstacle-avoidance, navigation, and communications concepts and the design information for future Arctic SEV applications. ... |
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| The Overland Gully, Ramp and Step Response of the AALC JEFF (A) ACV, Model Experiments. |
JUN 1977 |
|
| Authors:
Lawrence O. Murray; David D. Moran; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD SHIP PERFORMANCE DEPT
|
| A series of experiments was performed to evaluate the overland behavior of the Amphibious Assault Landing Craft Program Air Cushion Vehicle designated as the JEFF(A). The experiments consisted of free passages of the craft over a series of gullies, ramps, and steps and allowing the vehicle to pitch and heave. The resultant pitch and heave response functions are presented graphically. (Author) |
|
| Overland Dynamics of the Amphibious Assault Landing Craft JEFF (B) One-Sixth Scale Model. |
MAY 1977 |
|
| Authors:
David D. Moran; Richard F. Messale; Lawrence O. Murray; Joseph J. Ricci; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD SHIP PERFORMANCE DEPT
|
| The dynamic response of the AALC 1/6 scale JEFF (B) model for craft passage over gullies or ground plane indentations is presented for a series of gully lengths. The experimental results are compared with responses predicted by a static mathematical model of the JEFF (B) vertical plane response. (Author) |
|
| Electronically Agile Radar (EAR) Interface Investigations. |
APR 1977 |
|
| Authors:
Martin Thornburg; Memphis Hixon; Everett W. Scovel; Don Hutchison; Waller Newby; BOEING WICHITA CO KS
|
| A flight test interface for the Electronically Agile Radar (EAR) in a model B-52G strategic weapon system test bed is defined. Space provisions were developed considering flight test requirements and, for the nose radome area only, the requirements of B-52 defensive subsystems. The Ear and instrumentation require added B-52 environmental control system capability. An analysis of radome characteristics indicates beam deflection compensation requirements are reasonably continuous and change little with ... |
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| The Effects of Wind Shear on Automatic Landing. |
APR 1977 |
|
| Authors:
Robert P. Denaro; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OHIO
|
| Automatic approaches and landings are simulated on a hybrid computer in constant winds, linear wind shear, logarithmic wind shear and knife-edge wind shear to determine the effects of wind shear on automatic landing. The aircraft is modeled by the longitudinal equations of a large jet transport with a typical autoland system. Results identified large differences in performance in the three types of shear, with large touchdown dispersions in moderate logarithmic ... |
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| Piloted Flight Simulator Study of Low-Level Wind Shear, Phase 2. |
MAR 1977 |
|
| Authors:
W. B. Gartner; D. W. Ellis; W. H. Foy; M. G. Keenan; A. C. McTee; SRI INTERNATIONAL MENLO PARK CALIF
|
| Task 2 of the All-Weather Landing Systems project is concerned with piloted flight simulation tests of various techniques designed to aid the pilot to detect and cope with low-level wind shear on approach and landing. This report documents the tests of Phase 2, a comparative evaluation of the most promising panel-displayed techniques from the Phase 1 study. The operational situation of a DC-10 aircraft landing in Category I visibility with ... |
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| F-4 Rain Tire Performance Flight Tests. Appendix B. |
MAR 1974 |
|
| Authors:
Larry K. McCallon; AIR FORCE FLIGHT TEST CENTER EDWARDS AFB CA
|
|
| F-4 Rain Tire Performance Flight Test. |
MAR 1974 |
|
| Authors:
Larry K. McCallon; AIR FORCE FLIGHT TEST CENTER EDWARDS AFB CA
|
| This report presents the results of the F-4 Rain Tire flight test program. A total of 155 test landings were made by an unslatted F-4E on both a dry and wet concrete runway. These tests were done primarily to (1) compare the performance of the Hytrol Mark III antiskid system to the production F-4 antiskid system, the Hytrol Mark II, (2) evaluate the wet runway stopping performance of four new ... |
|
| Flight Test Report of AN/ASN-114 Inertial Navigation System. |
DEC 1973 |
|
| Authors:
Raymond F. Clark; ARMY ELECTRONICS COMMAND FORT MONMOUTH NJ
|
| The AN/ASN-114 Inertial Navigation Set (INS) is a sensor for aircraft positions, velocity, attitude, and heading information. The system develops navigational data from self-contained, inertial sensors, consisting of a vertical accelerometer, two horizontal accelerometers and two two-axis displacement gyroscopes. The sensing elements are mounted in a four gimbal, gyro stabilized inertial platform. The set provides pitch, roll, and heading in both analog (synchro) and digital form. In addition, the following ... |
|
| Take-Off Velocities, |
28 NOV 1973 |
|
| Authors:
M. Rozenblat; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
|
| In the last 10-15 years the aeronautical engineering characteristics of cargo aircraft have changed considerably. There has been a sharp increase in the ranges of possible flight velocities and flying weights and flight safety requirements have been raised. However, the method of using aerodynamic corrections to the velocity indicator retained a number of tolerances which were valid earlier. Under modern conditions these tolerances lead to considerable errors in information on ... |
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| Flight Plan Position Extrapolation in an Automated Oceanic Air Traffic Control System. |
MAY 1973 |
|
| Authors:
Frank V. Giallanza; Charles P. Giallanza; James C. Brown; META SYSTEMS INC SANTA CLARA CALIF
|
| A method was developed to extrapolate the position of an aircraft along its flight plan route based on information contained in a stored flight plan and current meteorological data. The method assumes great circle flying. (Author) |
|
| Equivalent Route Winds for Helicopter Air Routes at Heights of 5,000, 10,000, and 18,000 Feet. Volume I, |
APR 1973 |
|
| Authors:
D. G. Brown; R. J. Cooper; R. D. Spragg; BOEING VERTOL CO PHILADELPHIA PA
|
| Equivalent headwinds or equivalent winds are computed using Sawyer's method for approximately 4400 strategic world air routes contained in Volumes I and 2. The seasonal mean equivalent wind and its standard deviation and the annual 50-, 75-, and 85- percent reliability equivalent winds are tabulated. Route winds are computed for the 5000-, 10,000-, and 18,000 foot levels. An IBM 360/65 program was used to compute the equivalent winds. Input data ... |
|
| Equivalent Route Winds for Helicopter Air Routes at Heights of 5,000, 10,000, and 18,000 Feet. Volume II, |
APR 1973 |
|
| Authors:
D. G. Brown; R. J. Cooper; R. D. Spragg; BOEING VERTOL CO PHILADELPHIA PA
|
| Equivalent headwinds or equivalent winds are computed using Sawyer's method for approximately 4400 strategic world air routes contained in Volumes I and II. The seasonal mean equivalent wind and its standard deviation and the annual 50-, 75-, and 85- percent reliability equivalent winds are tabulated. Route winds are computed for the 5000-, 10,000-, and 18,000 foot levels. (Author Modified Abstract) |
|
| Arresting Gear Tests for Elevated Short Take-Off and Landing Ports (STOL). |
NOV 1972 |
|
| Authors:
Anthony Zagarella; Daniel Spalluto; NAVAL AIR TEST FACILITY LAKEHURST N J
|
| Tests were performed at the Naval Air Test Facility with an S-2A Aircraft utilizing the M44B-2C arresting gear to determine the degree of angular and the maximum off-center engagements that still allowed the aircraft to remain on the 300 ft. wide by 2000 ft. long surface of a STOLport. (Author) |
|
| Ultraviolet Laser Recording Techniques for Side Looking Radar Applications. |
AUG 1972 |
|
| Authors:
Arthur L. Morganstern; William R. Limburg; W. T. Kelly; RESALAB INC DALLAS TEX LIGHT ELECTRONICS DIV
|
| This report describes the analytical and experimental work done to investigate the advantages, design tradeoffs, and potential problems associated with the use of ultraviolet and near-ultraviolet lasers in very high resolution and very wide bandwidth precision raster type laser beam recorders (LBR's) for side-looking radar and other reconnaissance sensor applications. Recommended designs are presented for each of the major subsystems of the recorder, including the traveling-wave light modulator design, and ... |
|
| Multiwheel Landing Gear - Soils Interaction and Flotation Criteria - Phase III. Part II. |
JAN 1972 |
|
| Authors:
David C. Kraft; Henry Luming; J. Richard Hoppenjans; Fred Bogner; DAYTON UNIV OH RESEARCH INST
|
| The design and utilization of military aircraft in forward area situations has required a continual investigation of those factors which define the aircraft flotation performance and operations capability on semi- and unprepared soil runways. This report summarizes these efforts conducted under Phase III - Part II of a continuing research program in landing gear/soil interaction. Phase III - Part II consisted primarily of a comprehensive investigation of the flotation variable ... |
|
| A Synthesis of Design Data Relating to Existing and Near-Future Air-Cushion Vehicles. |
MAR 1971 |
|
| Authors:
Basil V. Nakonechny; DAVID TAYLOR MODEL BASIN WASHINGTON DC
|
|
| SONOBUOY LOCATION. |
SEP 1970 |
|
| Authors:
Thomas Penn French Jr; NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF
|
| In airborne anti-submarine warfare operations there is a critical requirement for maintaining an accurate relative plot of the sonobuoys with respect to the aircraft. This study proposed a method for locating sonobuoys in a pattern using aircraft-to-buoy slant range information. The method did not use triangulation procedures and attempted to minimize the restrictions placed on the aircraft. The study showed the feasibility of the proposed methodology and the approximate errors ... |
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| FEATURES OF THE PROCESS OF OPTIMIZATION OF HIGH SPEED SOARING FLIGHT, |
30 JAN 1969 |
|
| Authors:
E. P. Vachasov; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH
|
| A characteristic of the conditions for optimality of high-speed soaring flight is that, regardless of the nature of the change in the meteorological conditions along the route, the form of their recording remains the same. The optimum procedure at each stage is determined by the characteristics of the external conditions of the present and future and is independent of the past. This makes it possible in all studies of high-speed ... |
|
| VTOL AND STOL SIMULATION STUDY. |
APR 1968 |
54 pages |
| Authors:
Robert C. Conway; NATIONAL AVIATION FACILITIES EXPERIMENTAL CENTER ATLANTIC CITY N J
|
| A simulation study to determine the effect on air traffic control when both Vertical and Short Takeoff and Landing aircraft are introduced into a terminal air traffic control environment was conducted. The simulation was conducted using the Model B Dynamic Air Traffic Control Simulator. Several approach conditions, various glide slope angles, and separation criteria were investigated to determine the effect on a terminal environment. It was concluded that Vertical and ... |
|
| EVALUATION OF THE BAK-11/F AIRCRAFT ARRESTING BARRIER ENGAGING DEVICE. |
JAN 1968 |
|
| Authors:
Raymond E. Ramirez; AIR FORCE FLIGHT TEST CENTER EDWARDS AFB CA
|
| A total of 38 aircraft engagements of the T-33, F-100, F-101, and B-47 aircraft were made during the test program. A timing integration slope ratio of 1.75 in the EMERGENCY mode and 2.25 in the OPERATIONAL mode was determined the most adequate to allow a successful aircraft engagement. A LEAD ADJUST setting of 6.0 was found to be the most adequate for EMERGENCY mode engagements of the aircraft main landing ... |
|
| ENGINEERING TEST (DESERT) OF TRUCK, FORKLIFT, MULTIPURPOSE, 4,000-POUND CAPACITY, UL-42 (SANDPIPER). |
NOV 1966 |
|
| Authors:
Lef W. Kenyon; YUMA PROVING GROUND AZ
|
| An engineering test of Truck, Forklift, Multipurpose, 4000-Pound Capacity, UL-42 (Sandpiper) was conducted at Yuma Proving Ground, Yuma, Arizona, from 12 July to 28 October 1966. The purpose of the test was to determine the ability of the test item to operate in, and withstand the rigors of, low altitude desert climate and terrain conditions and to collect data on the safety aspects of the test vehicle. Drawbar pull and ... |
|
| TE-28 ARRESTING GEAR/AIRCRAFT CALIBRATION. |
07 OCT 1966 |
|
| Authors:
N. Cocco; NAVAL AIR TEST FACILITY LAKEHURST NJ SHIP INSTALLATIONS
|
| A calibration test program was conducted to determine the performance of the TE-28 arresting gear when using the following aircraft: 16,000-pound A-4, 22,000-pound F-8, 33,000-pound F-4, and 50,000- and 70,000-pound A-3. Comparison of test results of this calibration program with the data obtained during similar tests with aircraft arrested by the M-44B arresting gear yielded the following information on limiting engaging speeds: A-3 aircraft (both lightweight and heavyweight) test results ... |
|
| TWO DIMENSIONAL SPECTRAL ANALYSIS, |
JUL 1966 |
|
| Authors:
Louis J. Cote; PURDUE UNIV LAFAYETTE IND DEPT OF STATISTICS
|
| The author presents a theoretical sketch of two dimensional stationary processes with some possible uses of their spectra. Then details are given of the statistical estimation of two dimensional spectra. Measurement errors are discussed and formulas used in computation are summarized. The major part of the work was sponsored by the Land Locomation Laboratory of the Army Tank-Automotive Center, Warren, Michigan and appears in (AD-438 405). The measured spectra were ... |
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| FEASIBILITY OF TECHNIQUES FOR A DOPPLER OPTICAL NAVIGATOR. |
SEP 1964 |
|
| Authors:
W. J. Hannan; L. J. Nicastro; T. E. Penn; J. VOLLMER; RADIO CORP OF AMERICA CAMDEN N J
|
| The objective of this program was to determine the feasibility of novel laser techniques for Doppler optical navigation. The ultimate performance goal is the measurement of ground speed of a satellite, traveling at a velocity of 10,000 meters per second at an altitude of 300 miles, with an accuracy of 5 meters per second. Either of two approaches can be used to instrument a Doppler optical navigator--the continuous-wave approach or ... |
|
| DOPPLER OPTICAL NAVIGATOR. |
19 DEC 1963 |
|
| Authors:
W. J. Hannan; L. J. Nicastro; G. Clubine; T. E. Penn; RADIO CORP OF AMERICA CAMDEN N J DEFENSE ELECTRONIC PRODUCTS
|
| The objective of this program is to determine the feasibility of novel laser techniques for Doppler optical navigation. The performance goal is the measurement of ground speed with 5 m/sec accuracy at a maximum altitude of 300 mi. Analysis and experimental results indicate that amplitude modulation can be used to improve the coherence of the return signal. At optical frequencies the ground is a diffuse reflector whereas at a subcarrier ... |
|
| STATISTICAL STUDIES OF STABLE GROUND ROUGHNESS, |
NOV 1963 |
|
| Authors:
Frank Kozin; Louis J. Cote; ARMY TANK-AUTOMOTIVE CENTER WARREN MICH
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| A method of estimating statistical characteristics of stable ground roughness for use in offroad land locomotion is developed. Computer programs for obtaining these estimates from survey data were prepared. Several estimated power spectral densities obtained from survey data taken at military installations are presented. Pertinent features of these estimated power spectral densities are interpretable in terms of visual features of plotted ground profiles. The estimated power spectral densities may be ... |
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| ADDITIONAL RESULTS ON THE STATISTICAL ANALYSIS OF A LINEAR VEHICLE USING MEASURED GROUND POWER SPECTRAL DENSITY |
NOV 1963 |
32 pages |
| Authors:
John L. Bogdanoff; Frank Kozin; ARMY TANK-AUTOMOTIVE CENTER WARREN MI
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| An extension is presented of previous results relating the parameters of an idealized two-dimensional linear vehicle to stable ground roughness as described by power spectral densities. Optimal vehicle parameters are obtained relative to a ride roughness criterion for ground contours described by power spectral densities estimated from real ground survey data. It is found that the ride is not sensitive to changes in the wheel base length parameter when is ... |
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| HUMAN TRACKING ABILITY FOR MAXIMUM TERRAIN FOLLOWING (PROJECT DIRECT). |
31 AUG 1963 |
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| Authors:
W. J. Ruby; R. A. Monty; CORNELL AERONAUTICAL LAB INC BUFFALO N Y
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| The present experiment examined two command signals: the aircraft flight vector angle, and the elevator deflection angle. Each of these two command signals were computed for three aircraft speeds, 0.6M, 0.75M, and 0.9M over two terrains, Southern Pennsylvania and Rocky Mountain. A group of twelve subjects was randomly assigned to each command signal for the experiment. Each subject flew each combination of aircraft speed and terrain (6 combinations) on each ... |
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| STUDIES TO DETERMINE OPTIMUM LUNETTE LOAD FOR THE LANCE LIGHTWEIGHT LAUNCHER, |
25 JUL 1963 |
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| Authors:
D. E. Cristensen; R. I. Strickland; ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING LAB REDSTONE ARSENAL AL GRO UND EQUIPMENT/MATERIALS DIRECTORATE
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| This report presents studies to determine an optimum static lunette load for the LANCE lightweight launcher. Included are studies pertaining to prime mover and launcher dynamics, grade ability, braking loads, stopping distance, and human factors of manhandling the launcher. (Author) |
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| JANAIR. JOINT ARMY-NAVY AIRCRAFT INSTRUMENTATION RESEARCH. CONTACT ANALOG SIMULATOR EVALUATIONS. HOVERING AND AIR TAXI MANEUVERS, |
JUL 1963 |
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| Authors:
Joseph A. Sgro; BELL HELICOPTER CO FORT WORTH TEX
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| This study represents the second in a series of evaluations of the JANAIR vertical display. Four basic configurations (basic grid plane, basic grid plane with ground position indicator, basic grid plane with pathway, basic grid plane with pathway plus tarstrips) which could be incorporated into a vertical display are evaluated. Four subjects (Ss) were required to perform three basic flight maneuvers. These maneuvers were presented at various assigned flight conditions ... |
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| INVESTIGATION OF ACTIVE DOPPLER VELOCITY SENSOR. |
JUN 1963 |
1 pages |
| Authors:
RAYTHEON CO BEDFORD MASS
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| A study program is directed toward the advance ment of the state-of-the-art of doppler naviga tion radar techniques to meet the high speed, high altitude requirements of an aerospace ve hicle. Flight testing of the manual spectral compression system is reported, with band-width compression ratios of the order of 10 to 1 being achieved. The preliminary development of the Computer and Control unit was completed, and fabrication of the flyable ... |
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| OPERATIONAL TEST AND EVALUATION OF AIR TRAFFIC CONTROL CENTRAL AN/GSN-11 |
JAN 1963 |
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| Authors:
AVCO CORP CINCINNATI OH ELECTRONICS AND ORDNANCE DIV
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| A METHOD OF EVALUATING RUNWAY FRICTION FOR THE PREDICTION OF ACTUAL TAKE-OFF RUNS, |
JAN 1963 |
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| Authors:
G. Ciampolini; ADVISORY GROUP FOR AERONAUTICAL RESEARCH AND DEVELOPMENT PARIS (FRANCE)
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| A method is described of obtaining practical values of the rolling coefficient of friction immediately before take-off. This procedure allows preliminary calculations to be made, using simple nomograms, of the actual ground-run distances for the atmospheric and ground conditions prevailing at the time. (Author) |
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| GROUND RUN PREDICTION, |
JAN 1963 |
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| Authors:
D. A. Rush; ADVISORY GROUP FOR AERONAUTICAL RESEARCH AND DEVELOPMENT PARIS (FRANCE)
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| The problem of monitoring aircraft performance during take-off ground run and indicating whether or not the take-off can be made safely is considered in relation to the take-off procedure commonly employed by the operators of transport aircraft. The argument is developed that a velocity/distance criterion is the correct choice for obtaining a true monitor of performance and that the ideal monitor should contain prediction in order to avoid delaying pilot ... |
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| WIND-SHEAR EFFECTS ON AIR SPEED, |
MAR 1962 |
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| Authors:
J. A. Browne; AIR WEATHER SERVICE SCOTT AFB IL
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| A change in airspeed will occur whenever an aircraft traverses from one wind condition to a different one in less time than the aircraft ground speed can adjust to the new wind component. Recommended flight procedures include allowances for these variations, and there is no danger of getting into difficulty as long as proper airspeed is maintained. Extreme conditions of wind shear encountered during a landing approach can be hazardous ... |
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| TESTS OF THE TYPE XMB-1 AIRCRAFT ARRESTING ENERGY ABSORBER. |
FEB 1960 |
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| Authors:
Robert B. Wysor; William J. Nissley Jr; ALL AMERICAN ENGINEERING CO WILMINGTON DEL
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| The results of full scale testing of the XMB-1 Runway Overrun Carrier System which incorporates the Air Force MA-1 aircraft engaging device and a hydraulically controlled, friction type, energy absorber are reported. Operation of the barrier system and a unique method of testing with captive jet aircraft are described. Performance limitations resulting from loads induced on high velocity engagements and energy absorber vibration are discussed. Actual and theoretical energy absorber ... |
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| Characteristics of Systems Feasible for Inertial Navigation of Submarines, |
AUG 1951 |
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| Authors:
Forrest E. Houston; John Hovorka; MASSACHUSETTS INST OF TECH CAMBRIDGE INSTRUMENTATION LAB
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| This report is the result of a study of possible submarine inertial navigation methods. Prior investigation has narrowed the field of inquiry to gravity-field navigation, and pointed to a system design based on a stable vertical element which is essentially an equivalent pendulum with eight-four-minute-period characteristics, a so-called Schuler-tuned system. The equivalent pendulum is represented by a controlled member which is oriented by accelerometer-monitored gyro units to indicate the vertical. ... |
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| EXPERIMENTAL DATA FORMING THE BASIS FOR THE BOMBING TABLES BT-100-A-1 BOMB, PRACTICE, 100-LB., M39, |
20 JUN 1938 |
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| Authors:
F. V. Reno; BALLISTIC RESEARCH LABS ABERDEEN PROVING GROUND MD
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| Range bombing was conducted for the Bomb, Practice, 100-lb., M39 from December 1, 1936 to April 29, 1937. A total of seventy ranges for nominal altitudes between 4000 feet and 15000 feet with true air speed varying between 119.6 miles per hour and 197.9 miles per hour, with the largest proportion of air speeds in the neighborhood of 160 miles per hour, was obtained. The results are summarized. (Author) |
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Reports by Keyword(s)
GROUND SPEED
