| Advanced Technology Tactical Transport (ATTT) |
84 |
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| Authors:
SRS TECHNOLOGIES ARLINGTON VA WASHINGTON OPERATIONS
|
 | The results of the (Advanced Technology Tactical Transport) Proof of Concept test program indicate that the design mission is do-able. The tandem wing configuration exhibited conventional performance and handling qualities except for the destabilizing influence of power in the (Short Takeoff/Landing) environment. Furthermore, the design and most of the validating data are in place. If this mission, or one of similar range and STOL capabilities is valid, the next step ... |
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| Enhancement and Verification of the Navy CASEE (Comprehensive Aircraft Support Effectiveness Evaluation) Model (Calendar Year 1983 Task) |
12 DEC 1983 |
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| Authors:
INFORMATION SPECTRUM INC ARLINGTON VA
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| In order to respond to evolving fleet requirements and procedures in operating systems and maintenance reporting systems, the Navy Comprehensive Aircraft Support Effectiveness and Evaluation (CASEE) Model required periodic updating and restructuring. The CASEE enhancements described in this report resulted from basic needs within the CASEE users community to have CASEE reflect the changing criteria that are instrumental in analyzing fleet operating and maintenance policies. Enhancements were selected and implemented ... |
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| Development of Advanced Circulation Control Wing High Lift Airfoils |
DEC 1983 |
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| Authors:
R. J. Englar; Gregory C. Huson; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT
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| Recent experimental and flight test programs have developed and confirmed the high lift capability of the Circulation Control Wing (CCW) concept. These CCW airfoils employ tangential blowing of engine bleed air over circular or near circular trailing edges, and are capable of usable lift coefficients triple those of simple mechanical flaps. Earlier versions of these blown airfoils made use of relatively complex leading and trailing edge devices which would have ... |
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| Human Factors Affecting Pilot Performance in Vertical and Translational Instrument Flight |
DEC 1983 |
92 pages |
| Authors:
J. S. Tatro; L. Corl; S. N. Roscoe; NEW MEXICO STATE UNIV LAS CRUCES BEHAVIORAL ENGINEERING LAB
|
 | As part of an overall research program to develop both forward- looking and downward-looking tactical situation displays for all-weather instrument flight in VTOLs, an integrated horizontal situation display was developed for both vertical and translational flight. This report covers the development and initial experimentation of the downward-looking display and control system. The effects of eight factors on pilot performance as a function of those eight factors were derived for each ... |
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| Investigation of Parameters Influencing the Deflection of a Thick Wall Jet by a Thin Wall Jet Coflowing over a Rounded Corner |
DEC 1983 |
54 pages |
| Authors:
G. G. Huson; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT
|
| Recent investigations proved the compatibility of the Circulation Control and the Upper Surface Blowing Concepts. This static investigation is a follow-up to determine what combinations of geometric and pneumatic variables produce an effective deflection of a thick wall jet by a thin wall jet exhausting over a rounded corner. Static pressure distributions over the corner indicate that maximum deflections of the thick wall jet occur when a high average suction ... |
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| Aircraft Having Variable Incidence Forward-Swept Wing. |
15 NOV 1983 |
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| Authors:
M. H. Shirk; DEPARTMENT OF THE AIR FORCE WASHINGTON DC
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| An aircraft having a fuselage and a pair of forward-swept wings includes a wing carry through extending transversely through the fuselage joining the wings together to form a unitary wing structure, two hinge assemblies, each located adjacent a different one of the wings for rotatably mounting the wing structure to the fuselage and located forwardly of the wing carry through and on a spanwise axis intersecting the aerodynamic centers of ... |
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| Proceedings of the Conference on Flight Mechanics and System Design Lessons from Operational Experience Held at Athens, Greece on 10-13 May 1983 |
OCT 1983 |
|
| Authors:
ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRANCE)
|
| The following Compilation report deals with: Investigation, Reporting and Analysis of US Army Aircraft Accidents; The use of Flight Recorders in the Investigation of Aircraft Mishaps; The Civil Aircraft Airworthiness Data Recording Programme; Two Decades of Air Carrier Jet Operation; Incident Reporting - Its Role in Aviation Safety and the Acquisition of Human Error Data; Flight Parameters Recording for Safety Monitoring and Investigation; Rotorcraft Icing Technology - An Update; Worldwide ... |
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| Hardware-in-the-Loop Simulation Techniques Used in the Development of the Sea Harrier Avionic System, |
OCT 1983 |
|
| Authors:
M. Mansell; W. J. Quinn; C. J. Smith; BRITISH AEROSPACE AIRCRAFT GROUP BROUGH (UNITED KINGDOM) KINGSTON-BROUGH DIV
|
| Simulation using airborne hardware in the loop during the development of avionic systems is now a well established technique used by airframe and weapon system contractors. However, each new weapon system produces a different set of problems that usually requires a change of technique in order to satisfy test requirements for the system. This paper gives a brief overview of the Sea Harrier avionic system and describes the techniques used ... |
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| A Pilot/Vehicle Model Analysis of the Effects of Motion Cues on Harrier Control Tasks |
SEP 1983 |
|
| Authors:
S. Baron; BOLT BERANEK AND NEWMAN INC CAMBRIDGE MA
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| In this study, the results of an analytical investigation of pilot control of a simulated AV-8B (Harrier) aircraft are presented. The analysis was performed using a well-established pilot-vehicle model, namely, the Optimal Control Model. The effects on closed-loop performance of aircraft configuration (SAS-ON or SAS-OFF) and flight condition (hover or cruise) and of simulator motion cueing condition (fixed-base, moving platform or g-seat) were all analyzed. In addition, the interaction between ... |
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| Use of Helicopters to Develop Operational Concepts for V/STOL (Vertical and Short Takeoff and Landing) Aircraft in Naval Missions |
AUG 1983 |
|
| Authors:
P. S. Montana; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT
|
| Vertical and short takeoff and landing (V/STOL) aircraft promise new operational capabilities for the Navy. In the past, new vehicle types have been slow in gaining acceptance because of the difficulty in visualizing how these new vehicles should be employed. Once built, experience gained with the vehicle evolved into an operational concept exploiting its best qualities. Now, competition for fiscal resources has reached a level from which it may be ... |
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| Tentative STOL (Short-Takeoff-and-Landing) Flying Qualities Criteria for MIL Standard and Handbook |
JUN 1983 |
|
| Authors:
Roger H. Hoh; David G. Mitchell; SYSTEMS TECHNOLOGY INC HAWTHORNE CA
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| A move is underway in the military services to expand the scope of the military flying qualities specification, MIL-F-8785C to include STOL flying qualities. This report is the result of review, analysis and unification of existing STOL flying qualities data in a form facilitating inclusion into the new MIL Standard and Handbook, particularly in the area where STOL aircraft differ from CTOL aircraft. The report recommends proposed requirements where sufficient ... |
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| YC-15 EBF (Externally-Blown Flap) STOL (Short Takeoff and Landing) Airplane Fuselage and Interior Noise Environment |
MAY 1983 |
|
| Authors:
Vincent R. Miller; AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH
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| The purpose of this effort was to investigate the exterior fuselage and interior noise of the USAF/McDonnell-Douglas YC-15 Advanced Medium-Range Short-Takeoff- and Landing Transport airplane. This aircraft employs an under- the-wing, externally-blown-flap powered lift system designed to create augmented lift, which creates an intense acoustic environment. The blowing of the flap produces higher noise levels at lower frequencies than does the jet alone, increasing the acoustic environment of the fuselage ... |
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| Increasing Future Fighter Weapon System Performance by Integrating Basing, Support, and Air Vehicle Requirements |
APR 1983 |
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| Authors:
M. B. Berman; C. L. Batten; RAND CORP SANTA MONICA CA
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| This report argues that the Air Force should consider alternative basing and support characteristics before completing concept formulation for the Advanced Technical Fighter. In so doing, the Air Force could integrate these characteristics using a methodology described in this Note. This methodology aims at identifying the best match between specific air vehicle characteristics and such basing and support improvements as dispersed and/or rearward basing, short-take-off-and-landing and rough-field-landing capabilities, increased combat ... |
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| Short Takeoff Performance Using a Gravity Assist Ski Jump |
MAR 1983 |
34 pages |
| Authors:
Roger J. Furey; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT
|
| A modified or gravity assist ski jump is developed, through an application of the calculus of variations, to provide for the shortest takeoff roll for a thrust vector control type vertical or short takeoff and landing (V/ STOL) aircraft that will maintain a better-than-minimum required rate of climb. As a means of comparison between the resulting modified and a conventional ski jump, the equations of motion are programmed to model ... |
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| Investigation of a Pneumatic Thrust Deflector Based on Circulation Control Technology |
FEB 1983 |
|
| Authors:
Michael J. Harris; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT
|
| An investigation was conducted to validate the potential of a pneumatic thrust deflector based on circulation control technology. This thrust deflector concists of a small blown curved surface mounted adjacent to a two- dimensional nozzle. In the configuration evaluated, a 3.5-in. (8.9-cu) -diameter blown surface was used to deflect the exhaust of a 660-lb (2.94-kN) thrust turbojet. Thrust deflection through 65 deg was achieved at reduced thrust levels. This performance ... |
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| V/STOL Fountain Force Coefficient |
JAN 1983 |
|
| Authors:
L. W. Glaze; D. R. Bristow; D. R. Kotansky; MCDONNELL AIRCRAFT CO ST LOUIS MO
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| The McDonnell Aircraft Company (MCAIR) V/STOL force and moment methodology was applied to a two-jet, a three-jet and four-jet V/STOL aircraft in hover in ground effect to determine the fraction (Lambda) of the impinging fountain momentum flux transferred to the airframe as a fountain impingement force. The use of potential flow panel methods was verified for the calculation of suckdown forces on V/STOL aircraft in hover, provided the jet entrainment ... |
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| Human Factors Affecting Pilot Performance in Vertical and Translational Instrument Flight |
DEC 1982 |
34 pages |
| Authors:
Stanley N. Roscoe; Louis Corl; NEW MEXICO STATE UNIV LAS CRUCES BEHAVIORAL ENGINEERING LAB
|
| A conceptual analysis and review of human factors problems in piloting VTOL aircraft including helicopters is presented. VTOL mission and flight requirements are contrasted with those of CTOLs. Deficiencies in present VTOL flight instrumentation are summarized. An experimental approach that is based on established display principles and emphasizes dynamically predictive skeletal,perspective, vertical and horizontal situation displays is presented. |
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| On the Prediction of the Lateral/Directional Characteristics of Distributed Jet STOL Configurations |
DEC 1982 |
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| Authors:
Richard E. Kuhn; KUHN (RICHARD E) NEWPORT NEWS VA
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| A method for estimating the lateral/directional stability characteristics of jet flap STOL transport configurations at high power-on lift coefficients is presented. In addition to inducing a large stabilizing sidewash at the vertical tail powered lift reduces the directional instability contribution of the wing/body, increases the wing body side force and tends to reduce (depending on the amount of geometric dihedral incorporated) the high level of effective dihedral normally associated with ... |
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| V/STOL (Vertical/Short Takeoff and Landing) Low Speed and Transition Equivalent Systems Analysis |
DEC 1982 |
|
| Authors:
Carl G. Carpenter; John Hodgkinson; MCDONNELL AIRCRAFT CO ST LOUIS MO
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| A fixed base manned V/STOL handling qualities simulation was performed to investigate 1) classification criteria of attitude and rate command systems in hover and low-speed flight; 2) control system blending schemes for transition from approach dynamics to hover dynamics and vice versa, and 3) the amount of control usage. Pilot ratings and comments showed that a time response criterion discriminated well between attitude and rate systems; blending schemes for transition ... |
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| Soft Landing Gear. |
16 NOV 1982 |
|
| Authors:
Louis T. Kramer; Franklin H. Butler; Anthony V. Camino; DEPARTMENT OF THE AIR FORCE WASHINGTON DC
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| This report describes a bogie type landing gear especially suitable for providing soft landing capabilities for short take-off and landing (STOL) aircraft wherein fore and aft wheels are mounted on opposite ends of a vertical shock strut. In one embodiment, a torque link pivotally connects the aft end of the bogie to the shock strut such that, under normal landing conditions, the front wheel will touch down first thereby reducing ... |
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| A Preliminary Assessment of Helicopter/VSTOL Handling Qualities Specifications |
04 NOV 1982 |
|
| Authors:
K. Goldstein; NAVAL AIR DEVELOPMENT CENTER WARMINSTER PA AIRCRAFT AND CREW SYSTEMS TECHNOLOGY DIRECTORATE
|
| The flying quality characteristics of four state-of-the-art rotary wing aircraft have been compared to the present day helicopter and VSTOL flying qualities criteria. Hover control power and dynamic stability characteristics were analyzed for the longitudinal, lateral and directional axes. For forward flight, static and dynamic stability characteristics were analyzed for the longitudinal and lateral-directional axes. Results in terms of the applicability/utility of the MIL-H-8501A criteria are presented for each of ... |
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| A Flight Test Evaluation and Analytical Study of the Ball-Bartoe Jetwing Propulsive Lift Concept without Ejector |
01 OCT 1982 |
141 pages |
| Authors:
Ralph d. Kimberlin; Uwe P. Solies; Atin K. Sinha; TENNESSEE UNIV SPACE INST TULLAHOMA
|
| This report covers the results of a two part research effort on the Ball-Bartoe Jetwing propulsive lift concept. This effort was conducted by the University of Tennessee Space Institute, Tullahoma, Tennessee for the Advanced Aircraft Development and Systems Objectives Office (AIR-03PA) of Naval Air Systems Command under contract Number N00019-81-C-0506. The first part of the effort, which is covered in Part I of this report, was a follow on to ... |
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| An Analysis of the Flow Turning Characteristics of Upper-Surface Blowing Devices for STOL Aircraft |
OCT 1982 |
47 pages |
| Authors:
K. T. Yen; BLM APPLIED MECHANICS ASSOCIATES LARAMIE WY
|
| Experimental data from wind-tunnel tests on the static flow turning performance or upper-surface blown (USB) flaps have been assembled, analyzed, and correlated in the present study. Formulas for calculating the flow turning angle and flow turning efficiency have derived for rectangular nozzles with radius flaps. In the formula for the flow turning angle, the variables are the flap angle, the aspect ratio of the nozzle, the ratio of the flap ... |
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| Technical Evaluation Report on the AGARD Fluid Dynamics Panel Symposium on Fluid Dynamics of Jets with Applications to V/STOL |
JUL 1982 |
|
| Authors:
B. M. Spee; ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRANCE)
|
| This report presents an evaluation of the papers presented during the AGARD Fluid Dynamics Panel Symposium on Fluid Dynamics of Jets with Applications to V/STOL held 2-5 November in Lisbon, Portugal. General observations on progress in the understanding of the flow phenomena associated with jets are followed by more specific comments related to the five topical sessions of the meeting: Jet Interactions with Neighboring Surfaces, Jet Structure and Development; Windtunnel ... |
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| On the Structure of an Underexpanded Rectangular Jet |
JUL 1982 |
|
| Authors:
A. Krothapalli; Y. Hsia; D. Baganoff; K. Karamcheti; STANFORD UNIV CA JOINT INST OF AERONAUTICS AND ACOUSTICS
|
| An experimental investigation was carried out on an underexpanded jet of air issuing from a converging rectangular nozzle of moderate aspect ratio. Schlieren pictures of the flow field along with hot-wire measurements in the jet were obtained at different pressure ratios. At the pressure ratio corresponding to the maximum screeching sound, Schlieren photographs show a very strong organized cylindrical wave pattern on either side of the jet, with their respective ... |
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| An Engineering Method for Estimating the Aerodynamic Characteristics of Circulation Control Wings (CCW) |
01 JUN 1982 |
|
| Authors:
Campbell Henderson; NAVAL AIR DEVELOPMENT CENTER WARMINSTER PA AIRCRAFT AND CREW SYSTEMS TECHNOLOGY DIRECTORATE
|
| An engineering method for predicting the aerodynamic characteristics of Circulation Control Wings is presented. The method has been developed from correlations of the available DTNSRDC data base in accordance with theoretical developments of circulation control by slot blowing and modified jet flap theory for finite span effects. (Author) |
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| A Set of Flight Dynamic Equations for Aircraft Simulation |
JUN 1982 |
|
| Authors:
P. H. Hall; AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA)
|
| The six degrees of freedom dynamic equations of aircraft motion are documented for use in aircraft simulations at ARL. Earth axes are chosen for the integration of the force equations, and body axes for the integration of the moment equations. The use of quaternions to calculate aircraft attitude and associated direction cosines is described. A brief description of an atmospheric data subroutine for use in aircraft simulation is also included. ... |
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| The AV-8B Decision |
JUN 1982 |
|
| Authors:
Joel L. Goza; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| This thesis is a case study of the debate over the decision of the United States Government to procure the McDonnell Douglas AV-8B Advanced Harrier V/STOL jet aircraft for the U.S. Marine Corps. It includes a history of the development of the AV-8A Harrier, the development of the Marine Corps' concept of employment of V/STOL aircraft, and the development of the AV-8B. The study centers around the actions taken by ... |
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| Proceedings: Ejector Workshop for Aerospace Applications |
JUN 1982 |
1050 pages |
| Authors:
Richard P. Braden; K. S. Nagaraja; H. J. P. von Ohain; DAYTON UNIV OH RESEARCH INST
|
| These are the Proceedings of the Ejector Workshop for Aerospace Applications, which was conducted 2-5 August 1981 at the Bergamo Conference Center, Dayton, Ohio. The Workshop was hosted by the Air Force Office of Scientific Research and the Flight Dynamics and Aeropropulsion Laboratories of the Air Force Wright Aeronautical Laboratories. |
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| An Assessment of Factors Affecting Prediction of Near-Field Development of a Subsonic VSTOL Jet in Cross-Flow |
JUN 1982 |
|
| Authors:
A. J. Baker; J. A. Orzechowski; COMPUTATIONAL MECHANICS CONSULTANTS INC KNOXVILLE TN
|
| A three-dimensional parabolic Navier-Stokes numerical solution algorithm has been analyzed for prediction of the nearfield flow development of a VSTOL jet in subsonic crossflow. The essential aspects of algorithm definition, with regards to initial and boundary condition specifications, has been summarized. A momentum conserving pressure gradient computation has been developed to complete the problem definition and facilitate problem initialization. A sequence of overlapping interaction solutions has been evaluated for prediction ... |
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| Some Applications of Ejector Technology to STOL and V/STOL Aircraft Projects, |
JUN 1982 |
|
| Authors:
D. B. Garland; DE HAVILLAND AIRCRAFT OF CANADA LTD DOWNSVIEW (ONTARIO)
|
| A discussion of some elements of ejector technology, as developed at DHC (DeHavilland Aircraft Co.), is presented. Three operational areas are considered, i.e. (a) Static or hovering condition; (b) Low forward speed (STOL regime); (c) High subsonic cruise. Subsequently, three project study aircraft are introduced to illustrate the application of ejectors in their respective operational areas. These aircraft are: (a) An advanced turbo fan powered STOL transport; (b) A STOVL ... |
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| Reliability and Maintainability Improvement Program for the AV-8A/TAV-8A Harrier Head-Up Display Set, Development of the Signal Data Converter, CV-3600/ AVQ-30(V). Volume III |
28 MAY 1982 |
|
| Authors:
M. D. Carmichael; SMITHS INDUSTRIES AEROSPACE AND DEFENSE SYSTEMS INC CLEARWATER FL CLEARWATER DIV
|
| The circuitry driving the head-up display in the AV-8A aircraft, called the Waveform Generator, was revised and updated to improve reliability. The new unit, called the Signal Data Converter, provides greater capability, built-in test features, phosphor protection circuits, reduced size and weight, and greater adaptability to changed input or output requirements. (Author) |
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| High Pressure Bleed for STOL and STO-VL Performance - A Conceptual Examination |
MAY 1982 |
|
| Authors:
Richard E. Kuhn; KUHN (RICHARD E) NEWPORT NEWS VA
|
| The engines in modern combat aircraft are sized by combat maneuverability considerations. These aircraft therefore have much more thrust available than is needed at normal takeoff and landing speeds. Only the Harrier, which can vector the thrust of the centrally-mounted engine through the center of gravity can use its excess thrust to reduce the takeoff and landing distance (to zero at low operating weights). The engines on the others are ... |
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| Experimental Investigation of Thrust Augmenting Ejectors Using Vane Excited Primary Jets |
MAR 1982 |
|
| Authors:
Thomas Robert McClellan; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| An experimental investigation has been conducted to evaluate the entrainment characteristics of a thrust augmenting ejector, with a small, oscillating airfoil inserted in the potential core of the primary jet. Velocity distributions were measured across the width of the jet, at downstream distances of 20 and 40 nozzle widths, with the jet exhausting into still air and with the jet exhausting into an instrumented ejector shroud for the following range ... |
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| Development of a Low-Order Model of an X-Wing Aircraft by System Identification |
FEB 1982 |
|
| Authors:
James H. Vincent; John W. Bunnell; SYSTEMS CONTROL INC (VT) PALO ALTO CA
|
| The original purpose of this contract was to prepare a flight test plan for the proposed X-wing demonstrator using system identification to extract useful math models from the flight test data. Since the original statement of work was submitted, however, the scope of this study changed. An X-wing program decision has been reached not to carry the Lockheed X-wing configuration to flight test. Therefore, this task was modified to provide ... |
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| Viscous Flowfields Induced by Three-Dimensional Lift Jets in Ground Effect |
30 JAN 1982 |
|
| Authors:
W. W. Bower; MCDONNELL DOUGLAS RESEARCH LABS ST LOUIS MO
|
| The turbulent flowfields associated with single and multiple jets impinging on a ground plane are relevant to the aerodynamics of VTOL aircraft in ground effect. These flowfields are computed using the Reynolds equations and a two-equation turbulence model to describe an isolated jet and two interacting jets with fountain formation. Coordinate transformations are employed to apply the boundary conditions for the governing equations in the far field, and a third-order-accurate ... |
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| OV-10A Nose Gear Fork Damage Tolerance Analysis |
JAN 1982 |
|
| Authors:
Kenneth F. Barnes; James L. Haines; SAN ANTONIO AIR LOGISTICS CENTER KELLY AFB TX
|
| A limited Damage Tolerance Analysis (DTA) of the OV-10A nose gear fork was performed to determine the fracture characteristics at a location on the underside of the fork in a machined fillet radius just aft of the jack point. The analysis included determination of a landing load history, finite element stress analysis, stress spectrum development, stress intensity solution, crack growth analysis, and residual strength calculations. (Author) |
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| Fluid Dynamics of Jets with Applications to V/STOL |
JAN 1982 |
|
| Authors:
ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRANCE)
|
| The Symposium on Fluid Dynamics of Jets with Applications to V/STOL was planned in response to current aeronautical developments which highlight the need for improvements in the understanding of jets and the fundamentals of mixing. The most important of these developments are vertical and short take-off and landing aircraft which employ thrust vectoring or lift augmentation. Sessions on Jet Interactions with Neighbouring Surfaces, Jet Structure and Development, Wind Tunnel Simulation, ... |
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| ALQ-164 POD/AV-8C Environmental Evaluation Flight Test |
11 DEC 1981 |
|
| Authors:
Lawrence J. Mertaugh; NAVAL AIR TEST CENTER PATUXENT RIVER MD
|
| This report provides the test results of a flight test program conducted to evaluate the environmental conditions to which the ALQ-164 pod is exposed when carried on the AV-8C aircraft. Descriptions are provided of the test program, test equipment, instrumentation, and methods of analysis. The test results include cooling-air mass flow and temeprature, vibration levels measured on the pod structure and on the isolator mounted equipment support structure, and pod ... |
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| XH-59A ABC Technology Demonstrator Altitude Expansion and Operational Tests |
DEC 1981 |
|
| Authors:
A. J. Ruddell; UNITED TECHNOLOGIES CORP STRATFORD CT SIKORSKY AIRCRAFT DIV
|
| this report presents the results of two flight test programs conducted with the XH-59A Advancing Blade Concept demonstrator aircraft. The first program, conducted in the auxiliary propulsion configuration, consisted of altitude and center-of-gravity envelope expansion testing. Test results verified the concept of developing lift primarily on the advancing rotor blades to dramatically improve lift and speed potential. The XH-59A achieved a maximum speed of 263 knots true airspeed and demonstrated ... |
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| Human Factors Affecting Pilot Performance in Vertical and Translational Instrument Flight |
DEC 1981 |
66 pages |
| Authors:
Stanley N. Roscoe; J. C. Hull; Paul M. Simon; Louis Corl; NEW MEXICO STATE UNIV LAS CRUCES BEHAVIORAL ENGINEERING LAB
|
| A conceptual analysis and review of human factors problems in piloting VTOL aircraft including helicopters is presented. VTOL mission and flight requirements are contrasted with those of CTOLs. Deficiencies in present VTOL flight instrumentation are detailed. The requirement that information regarding ground-referenced and airmass-referenced position in all six degrees of freedom be presented to the VTOL pilot and/or incorporated into positional control stabilization is stated. (Author) |
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| A Short Takeoff Performance Computer Program |
25 NOV 1981 |
|
| Authors:
David Bruce Kobus; NAVAL AIR DEVELOPMENT CENTER WARMINSTER PA AIRCRAFT AND CREW SYSTEMS TECHNOLOGY DIRECTORATE
|
| A short takeoff performance computer program has been developed by NAVAIRDEVCEN to be used for performance estimation and conceptual aircraft design. (Author) |
|
| XFV-12A Diagnostic and Development Program |
NOV 1981 |
|
| Authors:
P. M. Bevilaqua; C. P. Combs; ROCKWELL INTERNATIONAL COLUMBUS OH NORTH AMERICAN AIRCRAFT OPERATIONS
|
| The purpose of this report is to document the activity during the XFV-12A thrust augmenter development program conducted from May 1979 to June 1981. The diagnostic tests also indicated that a major source of performance deficiency could be attributed to feed duct/augmenter component interface problems rather than the basic augmenter configuratiion. The interface problems seriously affected both the isolated performance and flow quality of the primary augmenter nozzles resulting in ... |
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| Airborne Flight Test System (AFTS) |
26 OCT 1981 |
|
| Authors:
John A. Maynard; M. Ross; MCDONNELL DOUGLAS ASTRONAUTICS CO-ST LOUIS MO
|
| The objective of the AFTS program was to demonstrate the operation of a full 1000 Mbps laser communications system transmitting from an aircraft to a ground station receiver. The system was designed around a spaceborne terminal requirements and included prototype operational components. The six years of contract activity included design of a spaceborne high data rate transmitter, adapting the space platform design to operate on a KC-135 aircraft, development and ... |
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| An Oxygen Enriched Air System for the AV-8A Harrier |
OCT 1981 |
|
| Authors:
Richard L. Routzahn; NAVAL AIR DEVELOPMENT CENTER WARMINSTER PA AIRCRAFT AND CREW SYSTEMS TECHNOLOGY DIRECTORATE
|
| Due to the high support costs, increase in aircraft down time and hazards associated with the utilization of liquid oxygen, development has been progressing with On-Board Oxygen Generation Systems (OBOGS) which have the capability of providing an aviator's breathing gas of sufficient quality and quantity. An Oxygen Enriched Air System (OEAS), employing the molecular sieve concept, has been subjected to environmental test and evaluation by the Naval Air Development Center. ... |
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| An Empirical Method For Estimating the Effect of Ground Proximity on the Jet-Induced Lift of V/STOL Aircraft Employing Rectangular Jets |
AUG 1981 |
|
| Authors:
J. A. Sansone; W. H. Foley; GENERAL DYNAMICS CORP FORT WORTH TX FORT WORTH DIV
|
| An empirical method has been developed to predict the propulsive- induced forces on a V/STOL aircraft hovering in proximity of the ground. This method is applicable to configurations employing two, three, or four rectangular exhausts. Planform contour, nozzle pressure ratio, and lift improvement devices are considered. Accuracies on the order of one percent of propulsive thrust are demonstrated. (Author) |
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| A Flight Test Evaluation of the Ball-Bartoe Jetwing Propulsive Lift Concept |
01 JUL 1981 |
189 pages |
| Authors:
Ralph d. Kimberlin; TENNESSEE UNIV SPACE INST TULLAHOMA
|
| The need for military aircraft that will operate from short unimproved airfields, and the decks of smaller aircraft carriers has increased in recent years due to a changing world situation and the shrinking of the dollar. Such aircraft need to be fuel efficient, quiet, maneuverable, have low infrared signature, and carry a large useful load. The Ball-Bartoe 'Jetwing' is a single engine upper surface blowing concept which offers the possibility ... |
|
| A Study of Wall Jets and Tangentially Blown Wings |
JUL 1981 |
177 pages |
| Authors:
N. D. Malmuth; W. D. Murphy; J. D. Cole; ROCKWELL INTERNATIONAL THOUSAND OAKS CA SCIENCE CENTER
|
| A study of transonic wall jets and tangentially blown wings has been performed by using asymptotic and computational methods. For the portion of the effort dealing with wall jets, both submerged and coflowing cases have been investigated. For the submerged configurations, the nature of the decay process for disturbances emanating from the jet exit has been examined. In this analysis, the Kutta condition on the nozzle rim can be satisfied ... |
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| A Numerical Three-Dimensional Turbulent Simulation of a Subsonic VSTOL Jet in Cross-Flow Using a Finite Element Algorithm |
JUN 1981 |
|
| Authors:
A. J. Baker; J. A. Orzechowski; P. D. Manhardt; COMPUTATIONAL MECHANICS CONSULTANTS INC KNOXVILLE TN
|
| The purpose of this study, the results of which are reported herein, was to formulate a mathematical model of the basic VSTOL jet, and to validate its appropriateness by performing a series of computational experiments on the discrete analog (numerical) approximation to the mathematical description. Since the VSTOL jet problem is essentially steady, turbulent and fully three- dimensional, the mathematical description must be quite comprehensive. The approach selected was to ... |
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| The Impact of Military Applications on Rotocraft ad V/STOL Aircraft Design |
JUN 1981 |
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| Authors:
ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRANCE)
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| Twenty-six papers were presented in the following sessions: (1) Operational Experience; (2) Present Status of Technology; (3) V/STOL Aircraft Trends; and (4) Military Mission Effectiveness. |
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V/STOL
