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These proceedings were developed to enhance information exchange and improve understanding and control of wildlife hazards to aircraft. The 38 papers contained herein represent a wide range of views on how to control wildlife, par...
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These proceedings were developed to enhance information exchange and improve understanding and control of wildlife hazards to aircraft. The 38 papers contained herein represent a wide range of views on how to control wildlife, particularly birds, which create safety hazards. Information is provided on wildlife hazards in both the United States and internationally. The Proceedings includes papers on bird strike statistics, airworthiness of aircraft and engines, identification and tracking of birds, wildlife control techniques, landscaping and airport site selection considerations, compatible land use, solid waste site bird hazards, and case studies in wildlife control. (Author)
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In air to air engagements with mobile threat helicopters, the possession of a round of ammunition which could depart from a normal flight trajectory to engage a maneuvering enemy target would be of great value. Maneuvering project...
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In air to air engagements with mobile threat helicopters, the possession of a round of ammunition which could depart from a normal flight trajectory to engage a maneuvering enemy target would be of great value. Maneuvering projectiles launched from an automatic cannon would have the added benefit of putting a number of rounds on target in a short time. The FC&SCWSL has initiated the development of such a projectile. In the sections that follow results of analytical investigation of the explosive thruster concept, which is only one of several maneuvering techniques, are described. (Author)
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An experimental program was conducted to evaluate a landing gear concept that redistributes the impact energy of an autorotational landing. This landing gear concept redistributes the impact energy by providing an interconnection ...
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An experimental program was conducted to evaluate a landing gear concept that redistributes the impact energy of an autorotational landing. This landing gear concept redistributes the impact energy by providing an interconnection between the front and rear landing gears. Through the interconnection, as the rear landing gear moves from the flight position toward the full compressed position under landing impact, the front gear is impelled to move from the flight position toward the fully extended position. When these motions have been accomplished, the skids remain on the ground surface throughout the landing, greatly reducing the pitching moments. The landing gear was drop tested to demonstrate the effects of sink rate, gross weight, center-of-gravity (CG) location, touchdown attitude (both pitch and yaw), ground resonance, system damping, and spring rate. The testing included drop velocities up to 19.5 feet per second and simulated forward and lateral speed landings. For purpose of design and development, the OH-6A helicopter was used as the baseline aircraft, and the landing gear was designed to require minimum modification to the OH-6A. The results of the testing showed that the interconnected landing gear reduces the nosedown pitching velocities and angles during autororation landings. A cost analysis indicated that incorporation of the interconnected landing gear in new production aircraft would result in a return on investment greater than 2:1.
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摘要 :
The objective of this AGARDograph, assembled by the Guidance and Control Panel of AGARD, is to bring together the benefits in use of major test facilities and techniques in evaluating aircraft guidance and control functions, compo...
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The objective of this AGARDograph, assembled by the Guidance and Control Panel of AGARD, is to bring together the benefits in use of major test facilities and techniques in evaluating aircraft guidance and control functions, components and systems. The emphasis will be on specific examples of user oriented test programs rather than descriptions of the facilities. The AGARDograph is organized into five parts. Part I deals with control handling and active control testing; Part II covers tests on flight path control; Part III focuses on navigation system testing; Part IV embarks on combat guidance and control evaluation and Part V gives some insight in testing of flight-crucial digital systems in guidance and control.
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A computational study was performed for a doubly-swept rotor blade tip todetermine its benefit for high-speed impulsive (HSI) and blade-vortex interaction (BVI) noise. This design consists of aft and forward sweep. For the HSI-noi...
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A computational study was performed for a doubly-swept rotor blade tip todetermine its benefit for high-speed impulsive (HSI) and blade-vortex interaction (BVI) noise. This design consists of aft and forward sweep. For the HSI-noise computations, unsteady Euler calculations were performed for several variations to a rotor blade geometry. A doubly-swept planform was predicted to increase the delocalizing Mach number to 0.94 (representative of a 200+ kt helicopter). For the BVI-noise problem, it had been hypothesized that the doubly-swept blade tip, by producing a leading-edge vortex, would reduce the tip-vortex effect on BVI noise. A procedure was used in which the tip vortex velocity profile computed by a Navier-Stokes solver was used to compute the inflow associated with BVI. This inflow was used by a Euler solver to compute the unsteady pressures for an acoustic analysis. The results of this study were inconclusive due to the difficulty in accurately predicting the viscous tip vortex downstream of the blade. Also, for the condition studied, no leading-edge vortex formed at the tip.
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摘要 :
This volume contains measured steady and alternating forward and aft controls loads tabulated by flight and event number. This same data is shown plotted versus true airspeed and can be found in Volumes 6 and 7.
