| Development of the C-17 Fan Thrust Reverser Container, CNU-688/E |
OCT 2006 |
55 pages |
| Authors:
Mark W. Boals; Susan J. Evans; AIR FORCE PACKAGING TECHNOLOGY AND ENGINEERING FACILITY WRIGHT-PATTERSON AFB OH
|
 | The Air Force Packaging Technology and Engineering Facility (AFPTEF) was tasked with the design of a new shipping and storage container for the C-17 Fan Thrust Reverser (FTR) in March of 2004. The new container is designed to replace the wood crate and wood frame assembly presently used. The current containers lack of mechanical protection, environmental protection, handling issues, and left and right container requirements prompted AFPTEF's design of a ... |
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| Details on an AFRL Field Reversed Configuration Plasma Device |
JUN 2005 |
10 pages |
| Authors:
David Kirtley; Daniel L. Brown; Alec D. Gallimore; James Haas; MICHIGAN UNIV ANN ARBOR
|
| A field reversed configuration (FRC) plasma device is being developed at AFRL Edwards. This geometry concept is based off of the coaxial slow source FRC fusion reactor concept developed at the University of Washington by Vlases, et al. A scaling energy model, COTS FEA, and a proof-of-concept experiment have been completed. In addition a complete suite of magnetic diagnostics as well as photometric/optical and internal plasma measurements have been constructed. ... |
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| Application of Active Core Exhaust Control to Elliminate the Core Thrust Reverser on Heavy Lift Aircraft |
JUN 2001 |
8 pages |
| Authors:
Clarence F. Chenault; John D. Dorris; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIRECTORATE
|
| Pulsed jet blowing for mixing enhancement in a hot jet is examined using numerical simulation. Numerical simulations have been completed for a sub-scale turbojet engine a full scale ground demonstration case and a High-Bypass Ratio Engine (HBRE). These simulations have shown that pulsed jet blowing can significantly reduce jet plume potential core lengths at static and forward flight conditions. The numerical scheme utilizes large timestep implicit integration for efficiency and ... |
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| Hull Supported Steering and Reversing Steering and Reversing Gear for Large Waterjets. |
07 JAN 1997 |
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| Authors:
Charles M. Dai; DEPARTMENT OF THE NAVY WASHINGTON DC
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 | A waterjet propulsion system for a vessel permits stationary mounting of the pump within the vessel hull, and further allows minimizing the size and weight of the pump casing by providing a pivotably moveable, hull mounted and supported steering and reversing sleeve mechanism positioned to receive the waterjet flow from a waterjet nozzle and to redirect at least a portion of that flow for steering and production of reverse thrust. ... |
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| Marine Propeller. |
07 NOV 1995 |
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| Authors:
Robert M. Williams; Ernest O. Rogers; Maurice M. Sevik; DEPARTMENT OF THE NAVY WASHINGTON DC
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| A marine propeller using the circulation control principle of blowing tangentially over a Coanda surface at the trailing edge of each blade to develop high blade lift (thrust). Each blade has internal chambers and two blowing slots so that blowing is controllable for forward and for reverse thrust without reversing rotational direction of the propeller. This propeller is capable of generating much greater thrust and ship speed at lower RPM ... |
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| A Total Approach to Controlling ESD. |
MAY 1991 |
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| Authors:
S. L. Law; S. Mucha; S. Banks
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| A High Density Interconnect Process for VHSIC Signal Processing. |
MAY 1991 |
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| Authors:
W. M. Marcinkiewicz; J. F. Hale; C. C. Schuckert
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| Ultrasonic and Eddy Current Inspection. |
1991 |
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| Authors:
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| Single-Point Threading with Today's Tooling Options. |
JAN 1990 |
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| Authors:
B. R. Teets
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| The world has been using threads since the days of Archimedes (278-212 BC) when he cut spiral grooves on a cylinder, lowered it in water, rotated it, and the water rose. Today's modern CNC (computer numerical control) machine tools and advanced carbide tool designs offer new possibilities for better application of historic technology. (Copyright 1990 Modern Machine Shop). |
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| Aerodynamics of Combat Aircraft Controls and of Ground Effects: Conference Proceedings of the Symposium of the Fluid Dynamics Panel Held in Madrid, Spain on 2-5 October 1989 |
OCT 89 |
|
| Authors:
ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRAN CE)
|
| This symposium provides an updated review of the aerodynamic design of controls for combat aircraft. The scope included the aerodynamic design of controls for takeoff and landing conditions, for manoeuvring at subsonic, transonic and supersonic speeds, for high angles of attack and yaw, and for departure prevention and post-stall manoeuvring. Also, part of the symposium was concerned with novel control devices. Regarding ground effects, computational and experimental methods were reviewed, ... |
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| Ground Surveillance Radars for the 1990s. |
NOV 1988 |
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| Authors:
R. Pengelley
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| STOL Handling Qualities Criteria for Precision Landings |
NOV 86 |
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| Authors:
Roger H. Hoh; David G. Mitchell; SYSTEMS TECHNOLOGY INC HAWTHORNE CA
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| This report documents an effort to expand on flying qualities design criteria for precision (STOL) landings. The primary emphasis is on non-powered lift, fighter-type aircraft using frontside control technique for longitudinal flight path control. The major thrust of this effort is, therefore, to be able to increase sortie generation due to bomb-damaged runways. Handling qualities criteria for STOL approaches and landings are developed. The proposed criteria have two elements: (1) ... |
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| Thrust Reverser/Exhaust Nozzle Assembly for a Gas Turbine Engine. |
27 MAY 1986 |
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| Authors:
Edward B. Thayer; DEPARTMENT OF THE AIR FORCE WASHINGTON DC
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| This patent discloses an improved thrust reverser/exhaust nozzle assembly which has a plurality of blocker devices located in the divergent section of the exhaust nozzle and a plurality of deflector devices located in the convergent section of the nozzle. The blocker and deflector devices are linked together such that they move simultaneously and maintain a substantially constant engine between forward and reverse thrust conditions. |
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| Multivariable Output Control Law Design for the STOL (Short Takeoff and Landing) F-15 in Landing Configuration |
DEC 85 |
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| Authors:
Bruce H. Acker; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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| Using the MULTI computer aided design and simulation program, multivariable, output feedback digital control laws are designed for the F-15 STOL aircraft in the landing configuration. The STOL F-15 landing configuration includes canards and reversible thrust in addition to conventional F-15 control surfaces. The additional controls allow decoupling of the output variables in the longitudinal plane. Longitudinal aircraft dynamics, derived from data provided by the prime contractor, McDonnell-Douglas, are presented ... |
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| Test Techniques for Jet Effects on Fighter Aircraft, |
FEB 1984 |
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| Authors:
E. A. Price Jr.; W. L. Peters; CALSPAN FIELD SERVICES INC ARNOLD AFS TN AEDC DIV
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| A description of efforts to improve test techniques for jet effects on fighter-type aircraft at the Arnold Engineering Development Center (AEDC) is given. Work in defining levels of aerodynamic interference on aircraft afterbodies from three types of model support systems, a prediction technique for hot jet effects on afterbody drag, and a hot versus cold jet experiment on target-type thrust reverses is summarized. Support system interference from a strut, sting, ... |
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| Supermaneuverability, |
1984 |
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| Authors:
W. B. Herbst; MESSERSCHMITT-BOELKOW-BLOHM G M B H MUNICH (GERMANY F R)
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| Supermaneuverability is defined as the capability of a fighter aircraft to execute tactical maneuvers with controlled side slipping and at angles of attack beyond maximum lift. This paper deals particularly with post stall maneuverability at zero side slipping since this element of supermaneuverability is relatively unknown. The analysis is based on optimum control calculation of simplified maneuver elements and on extensive manned and computerized close air combat simulation. This analysis ... |
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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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| Thrust Deflector and Force Augmentor. |
16 AUG 1983 |
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| Authors:
James H. Nichols Jr.; Roger J. Furey; Robert J. Englar; David G. Lee; DEPARTMENT OF THE NAVY WASHINGTON DC
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| A non-moving fluids thrust deflector and force augmentor is disclosed for aerodynamic and hydrodynamic vehicles and devices. When the deflector is utilized in an aerodynamic application and in conjunction with a thrust producer and a plenum, upon pressure initiation within the plenum, a jet sheet issues and remains attached to a specially designed wing having a rounded trailing edge by balancing reduced static pressure with centrifugal force, and thus provides ... |
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| Fluidics: Basic Components and Applications |
AUG 1983 |
24 pages |
| Authors:
James W. Joyce; HARRY DIAMOND LABS ADELPHI MD
|
| Since its discovery at Harry Diamond Lab. in 1959, fluidics has gradually been developed into a viable technology. This report describes fluidic components and systems now in use or ready for use in many applications. The fluidic technology provides sensing, computing, and controlling functions with fluid power through interaction of fluid streams. Since fluidics can perform these functions without mechanical moving parts that will wear out, it has the advantages ... |
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| Reattachment of a Three-Dimensional, Incompressible Jet to an Adjacent Axisymmetric Inclined Surface |
MAR 1983 |
44 pages |
| Authors:
E. E. Niemi Jr; LOWELL UNIV RESEARCH FOUNDATION MA
|
| A study was made of the fluid mechanics of a thrust reverser jet reattaching to an aircraft nozzle afterbody. The problem basically involves the Coanda effect flow of a three-dimensional, incompressible jet to an adjacent axisymmetric, inclined surface. The equations were derived in integral form and programmed for numerical solution for the case of an exhaust flow with no opposing free stream flow. Test data are reported for a scale ... |
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| COANDA Control of a Thick Wall-Jet in the Static Case |
NOV 1982 |
10 pages |
| Authors:
G. G. Hudson; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER ANNAPOLIS MD
|
| The thrust from a turbofan engine top-mounted on a circulation control (CC) wing was recently found to vector downward (and in some cases more than 90 degrees downward, producing thrust reversal) when the CC Coanda jet is activated. Experimental research was undertaken to provide a basis for understanding this phenomenon, for projecting its practical limits, and for exploiting its benefits. Within the range of parameters investigated, thrust- turning performance tended ... |
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| Minimum Time Turns Constrained to the Vertical Plane |
DEC 1981 |
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| Authors:
Christopher S. Finnerty; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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| The objective of this study is to find the throttle controls and trajectories which yield the minimum turning times for a high performance aircraft with thrust reversal capability. The aircraft remains in the vertical plane allowing only pull-up and split-s maneuvers. A second-order parameter optimization method coupled with the suboptimal control approach is used to solve the minimum time-to-turn problem. The results of the study found that trajectories restricted to ... |
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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 ... |
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| Experimental Development of an Advanced Circulation Control Wing System for Navy STOL Aircraft |
MAY 1981 |
19 pages |
| Authors:
J. H. Nichols Jr.; R. J. Englar; M. J. Harris; G. G. Huson; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT
|
| An advanced high lift system is being developed which combines a Circulation Control Wing (CCW) with Upper Surface Blowing (USB) to produce significant lift for STOL operations by Navy aircraft. The concept uses circulation control to pneumatically deflect USB engine thrust and thus augment aerodynamic wind lift produced by the outboard CCW. Two series of wind tunnel investigations have confirmed significant thrust turning to angles near 160 deg, suggesting the ... |
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| Investigation of the Circulation Control Wing/Upper Surface Blowing High-Lift System on a Low Aspect Ratio Semispan Model |
MAY 1981 |
|
| Authors:
Michael J. Harris; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT
|
| The results from one in a series of investigations undertaken to develop the Circulation Control Wing/Upper Surface Blowing (CCW/USB) high-lift concept are presented. Included are: isolation of propulsion jet turning, effects of tip devices, and thrust reversing. As evaluated, the concept employs a modified supercritical wing with a 3.6-percent chord circular trailing edge and tangential blowing from a thin, full-span slot over this trailing edge. In addition, turbofans are mounted ... |
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| Time-Constrained Maximum-Energy Turns. |
DEC 1980 |
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| Authors:
Steven Petersen; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
|
| The object of this study is to find the trajectories which a high performance aircraft would employ to maximize the change in specific energy during a prescribed turn. These values of the change in specific energy are compared to the changes in specific energy which result from a minimum time turn. A suboptimal control approach, which uses both gradient and second-order techniques, is employed to find the maximum specific energy ... |
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| Minimum Time Turns with Thrust Reversal. |
DEC 1979 |
|
| Authors:
Thomas L. Johnson; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
|
| The object of this study is to find the optimal trajectories and corresponding minimum turning times for a high performance aircraft with and without thrust reversal to perform a prescribed turn, and then to compare those trajectories and times to evaluate the benefit of thrust reversal. Optimal control theory is applied to solve the minimum time to turn optimal control problem, using a suboptimal control problem approach and a second-order ... |
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| An Application of Optimal Control Theory to the FFG-7 Gas Turbine Propulsion System. |
JUN 1979 |
|
| Authors:
Richard A. Kalyn; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| An optimal integral control design program was applied to a linearized state variable model of the FFG-7 ship class gas turbine and Controllable Reversible Pitch (CRP) propeller main propulsion system. Various combinations of output parameters were investigated in an attempt to produce a feasible control design. Only one acceptable design was achieved which did not violate any physical constraints. (Author) |
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| Ahead and Backing Open Water Characteristics of Model Propeller 4716-Nozzle System, |
JUN 1979 |
|
| Authors:
James G. Peck; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD SHIP PERFORMANCE DEPT
|
| Model Propeller 4716-nozzle system was characterized in open water, ahead and backing. Model propeller 4716 was also characterized, ahead and backing, without the nozzle. The propeller-nozzle system and propeller performance data are presented in this report. The results indicate that under heavily loaded conditions, especially in backing, the propeller-nozzle system is more efficient than the propeller alone at the same loading. (Author) |
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| New Concepts in Ship Directional Control, |
14 MAY 1979 |
|
| Authors:
Herman E. Sheets; Tadeusz Kowalski; RHODE ISLAND UNIV KINGSTON DEPT OF OCEAN ENGINEERING
|
| A new propulsion system for ships has been discussed in Sheets (1978). This propulsion system provides a source of pressurized water between the pump and the turbine of the hydraulic transmission and generates a water jet leaving the transmission turbine. The water jet leaving the transmission turbine can be vectored by means of discharge vanes so that it is possible to greatly improve the directional controllability of ships. Several configurations ... |
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| Advanced Nozzle Technology. |
JUN 1978 |
|
| Authors:
Lawrence D. Wolfe; Arthur E. Fanning; AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OHIO
|
| This report contains a description of some of the exhaust concepts being developed as design options for use on the turbine engines which will power advanced fighter aircraft. Nozzle configurations which are not axisymmetric receive the major portion of the attention. Potential benefits of these types of nozzles are discussed and three general classes of nonaxisymmetric nozzles are described. Recent work in the areas of internal nozzle performance, cooling effectiveness, ... |
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| Deformable Plug for an Aircraft Engine Exhaust Nozzle. |
21 FEB 1978 |
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| Authors:
Richard M. Lowman Jr; DEPARTMENT OF THE AIR FORCE WASHINGTON D C
|
| A deformable plug for use within an aircraft engine exhaust nozzle system having thrust vectoring and thrust reversing capability, as well as the capability to vary the nozzle area thereby improving propulsion efficiency. This invention utilizes an exhaust nozzle passageway having a rectangular nozzle exit area with the aerodynamically shaped plug centrally located in the path of the engine exhaust gases. The portion of the plug extending aft of the ... |
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| Fluidics--Basic Components and Applications. |
OCT 1977 |
|
| Authors:
James W. Joyce; Richard N. Gottron; HARRY DIAMOND LABS ADELPHI MD
|
| Since its discovery at Harry Diamond Laboratories in 1959, fluidics has gradually been developed into a viable technology. This report provides a description of fluidic components and systems now in use or ready for use in many applications. The fluidic technology provides sensing, computing, and controlling functions with fluid power through the interactions of fluid streams. Sinc fluidics can perform these functions without mechanical moving parts that will wear out, ... |
|
| Simulation of a Controllable Reversible Pitch (C.R.P.) Propeller System. |
JUN 1977 |
|
| Authors:
Masaaki Kanazawa; NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF
|
| A computer model was developed to simulate a C.R.P. propeller system. A set of simultaneous differential equations was solved using CSMP III-the IBM simulation language. The computer model was verified against manufacturer's data. Power piston displacement, power piston velocity and chamber pressure were determined for a nominal supply pressure of 600 PSI and various loadings. Overall, the system model and data should prove useful for investigations of design variations. (Author) ... |
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| In-Flight Modulating Thrust Reverser. |
21 SEP 1976 |
|
| Authors:
Arthur McCardle Jr.; George H. Israel Jr.; Frank J. Trombetta; David F. Howard; DEPARTMENT OF THE AIR FORCE WASHINGTON D C
|
| The patent relates generally to the field of thrust reversers and, in particular, to a fully or substantially fully modulating-inflight thrust reverser to be added to the engine(s) of advanced fighter aircraft. |
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| Variable Jet Nozzle with Balanced Two-Dimensional Blocker Flap. |
14 APR 1976 |
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| Authors:
Sankaran Gowrinathan; DEPARTMENT OF THE NAVY WASHINGTON D C
|
| A variable area jet nozzle construction capable of blocking flow in favor of another nozzle in a vertical or short take-off aircraft utilizes a balanced two-dimensional flap that is pivotable about rollers and movable, along curved tracks cooperable with the rollers, to assume a plurality of nozzle area varying or blocking positions under the influence of linear hydraulic actuators. (Author) |
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| Shutting Down the Solid Fuel Rocket Engine, |
07 JAN 1976 |
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| Authors:
Todor Andreev; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
|
| Up to now there are two ways known for shutting down a solid rocket engine, or stopping the thrust; extinguishing the burning fuel, and neutralization of the thrust (reversing the thrust). These two methods can be applied separately or combined. |
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| FAA JT3D Quiet Nacelle Retrofit Feasibility Program. Volume III. Lower Goal Flight Testing, Economic Analyses and Summary. |
FEB 1974 |
|
| Authors:
J. E. Mayer; BOEING CO WICHITA KANS WICHITA DIV
|
| The Phase 1 quiet nacelle includes a two-ring acoustically treated inlet, hydraulically powered fan thrust reverser, 3/4 length acoustically treated fan ducts, and revised contour aft translating sleeve. The nacelle retains the standard Boeing 707 primary thrust reverser and tailpipe. An extensive ground test program, both model and full-scale was conducted to establish acoustic and propulsion performance and to confirm the adequacy of the design of the Phase 1 quiet ... |
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| FAA JT3D Quiet Nacelle Retrofit Feasibility Program, Volume IV. Compatibility Analysis and Design Study for DC-8 Aircraft. |
NOV 1973 |
|
| Authors:
BOEING CO WICHITA KANS WICHITA DIV
|
| Task 1 of this study consisted of a design study of the possible application of the Boeing JT3D quiet nacelle to the current DC-8 short duct and long duct domestic aircraft fleet as exemplified by the DC-8-61 and DC-8-63 aircraft. The Task 1 study identified many physical and functional problems associated with the use of the Boeing quiet nacelle on DC-8 aircraft. Of the configurations studied, two configurations for the ... |
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| FAA JT3D Quiet Nacelle Retrofit Feasibility Program. Volume 1-2. Lower Goal System and Compatibility Tests. |
SEP 1973 |
|
| Authors:
J. E. Mayer; BOEING CO WICHITA KANS WICHITA DIV
|
| The Phase 1 quiet nacelle for JT3D powered 707 aircraft includes a two-ring acoustically treated inlet, hydraulically powered fan thrust reverser, 3/4 length acoustically treated fan ducts, and revised contour aft translating sleeve. The nacelle retains the standard 707 primary thrust reverser and engine tailpipe. Full scale and model testing of the Phase 1 nacelle were accomplished to determine engine/nacelle performance and the adequacy of new or extensively revised systems. ... |
|
| Supersonic Transport Noise Reduction Technology Summary. Phase I. Summary of GE4/SST Acoustic Suppression Research. Volume 1. |
DEC 1972 |
786 pages |
| Authors:
J. F. Brausch; V. L. Doyle; GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP
|
| A development program for a commercial supersonic aircraft and engines was sponsored by the Federal Aviation Administration during a five-year period from 1966 through 1971. The unique propulsion system, an afterburning turbojet, required acoustic suppression techniques to reduce its noise levels to those federally regulated for subsonic aircraft. An acoustic suppression research program was conducted by the General Electric Company to develop technology applicable to prototype and commercial supersonic engines. ... |
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| Internal Aeronautical Manual. Volume II |
JUN 1970 |
|
| Authors:
ROCKWELL INTERNATIONAL COLUMBUS OH COLUMBUS DIV
|
| The Internal Aerodynamics Handbook has been developed in order to provide a convenient, accurate and reliable internal aerodynamics design manual which enables rapid determination of the internal airflow effects on airplane performance. It also enables the computation of internal airflow systems performance by developed theoretical and empirical methods. The scope of the design manual relates specifically to internal aerodynamics for the complete aircraft speed range up to and including Mach ... |
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| OPERATING CHARACTERISTICS OF GAS-TURBINE AIRCRAFT ENGINES, |
23 MAY 1969 |
|
| Authors:
A. L. Klyachkin; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
|
| The operating characteristics of aviation gas turbine engines are reviewed. The information covers thermodynamic control principles, throttling, altitude, speed, acceleration, startup, and special characteristics of turbojet, turboprop, and turbofan engines. A number of important problems are covered, which until recently were not included in textbooks for civil aviation institutes. These problems include specific characteristics of double shaft by-pass turbojet engines with a high by-pass ratio; the effect ... |
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| Method for Evaluating the Effectiveness and Weight of Aircraft Deceleration Devices. |
JUN 1968 |
|
| Authors:
Herbert Greiner; Jack H. Hilbig; ROHR CORP CHULA VISTA CA
|
| A program was established in order to develop a standard and expedient method for estimating the performance and weights of deceleration devices used to decrease the landing ground roll of an aircraft. The method of approach to the problem was to obtain all data available both from flight test and theory; and to compile a step-by-step procedure for determining the weight penalties and the force increments affecting aircraft landing performance. ... |
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| STUDY OF THE EFFECTIVENESS OF INFLIGHT-THRUST REVERSERS FOR AN AIRCRAFT PERFORMING A 180-DEGREE TURNING MANEUVER. |
JUN 1968 |
|
| Authors:
Donald W. Powell; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
|
| Modern control theory is used to find a control scheme to minimize certain flight parameters of an aircraft in a 180-degree turning maneuver. The specific technique is that of the conjugate gradient method. The aircraft is described by a set of nonlinear differential equations. Two problems, constant and near constant altitude, are considered. For each problem, the comparison is made of the flight parameters between aircraft with and without inflight-thrust ... |
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| LINEARIZED INVISCID-FLOW THEORY OF TWO-DIMENSIONAL THIN JET PENETRATION INTO A STREAM. |
FEB 1968 |
|
| Authors:
T. Strand; M. H. Y. Wei; AIR VEHICLE CORP LA JOLLA CALIF
|
| The potential flow of a stream that interacts with a two-dimensional thin jet of a different total head, being injected into the stream from an infinite plane surface at an arbitrary angle, is analyzed using natural coordinates. The velocity magnitudes along the interface and the nondimensional shape of the interface between the jet and the stream are obtained as functions of the injection angle and the ratio of the free ... |
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| SYSTEM 411L. AIRBORNE WARNING AND CONTROL SYSTEM. SYSTEM STUDY. VOLUME VII. SYSTEM SUBSTANTIATION - AIR VEHICLE SUBSYSTEMS. |
01 SEP 1967 |
|
| Authors:
DOUGLAS AIRCRAFT CO LONG BEACH CA AIRCRAFT DIV
|
| Contents: Air Vehicle Subsystem--Introduction, Secondary power (Secondary power subsystem selection, electrical power subsystem, hydraulic subsystem and auxiliary power unit), Airframe (Radome structural design, rotodome and support structural configuration, rotodome bearing and center mounting platform and structural analysis), Environmental Control (Environmental control subsystem selection, cabin air conditioning subsystem, avionic cooling subsystem and rotodome ice protection), Propulsion (Short duct pod, engine air inlet, thrust reversers, backup starting subsystem, engine noise, engine interface ... |
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| DETERMINATION OF THE EFFECTIVENESS OF OPTIMAL THRUST REVERSER USE FOR AN AIRCRAFT IN A PULL-UP MANEUVER. |
JUN 1967 |
|
| Authors:
Harold L. Daniel; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
|
| Pontryagin's Minimum Principle is applied to a two control optimization problem in which the effectiveness of a thrust reverser is evaluated for an aircraft in a pull-up maneuver. The aircraft is described by a set of nonlinear differential equations. A gradient technique is used to solve the resulting two point boundary value problem. Two performance criteria are used in determining the effectiveness of an optimal thrust reverser for an aircraft ... |
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| SUPERSONIC TRANSPORT DEVELOPMENT PROGRAM. PHASE III. BOEING MODEL 2707. AIRCRAFT ENGINE INSTALLATION SUBSYSTEM SPECIFICATION, |
31 DEC 1966 |
|
| Authors:
L. G. Dhoors; BOEING CO SEATTLE WA SUPERSONIC TRANSPORT DIV
|
| This specification defines the objectives, criteria, and configuration, and establishes the requirements for performance, design, test, and qualification for the Aircraft Engine Installation Subsystem (AEIS) for the prototype model supersonic transport airplane. Differences between the prototype and production airplanes are described. The subsystem provides the total propulsive power required by the airplane for accomplishing its intended functions. The subsystem also provides mechanical and pneumatic power for supporting airframe accessory, environmental ... |
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| REINFORCED GRAIN ADVANCED DEVELOPMENT PROGRAM. |
OCT 1966 |
|
| Authors:
ROCKETDYNE MCGREGOR TEX SOLID ROCKET DIV
|
| The program originally outlined the development of three designs of lightweight, upper-stage motors using wire as grain reinforcement. Eventually, one of the original three upper-stage designs was replaced by a testweight air-launched demonstration motor with extreme environmental requirements. One of the upper-stage designs included a supersonic split-line gimbaled nozzle. Static firing test results of the upper-stage motors showed the design approach yielded high mass fraction goals. However, fabrication experience proved ... |
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Reports by Keyword(s)
THRUST REVERSAL
