| ENGINEERING DESIGN HANDBOOK. CARRIAGES AND MOUNTS SERIES, TRAVERSING MECHANISMS. |
JUN 1967 |
43 pages |
| Authors:
ARMY MATERIEL COMMAND ALEXANDRIA VA
|
 | The various types of mechanism are discussed, along with their operating characteristics and pertinent design data. Contents is devoted exclusively to traversing mechanisms except where limited descriptions of other elements of carriages and mounts are necessary to clarify the discussions. |
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| ADVANCED TECHNIQUES FOR ANALYZING AND IMPROVING GRAVITY GRADIENT SATELLITE POINTING ACCURACIES AT HIGH ORBITAL ALTITUDES. VOLUME I. ANALYSIS. |
JUN 1967 |
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| Authors:
J. L. Palmer; H. S. Blackiston; R. L. Farrenkopf; TRW SYSTEMS GROUP REDONDO BEACH CA
|
 | This study is directed toward the investigation of the problems, and possible solutions, associated with high pointing accuracies for gravity gradient systems at high orbital altitudes. Two major areas of investigation are considered. In the area of system response, consideration is given to determining the configuration parameters and design techniques which provide the greatest tolerance to disturbance torques. In the area of disturbances, the parameters and design techniques which minimize ... |
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| ADVANCED TECHNIQUES FOR ANALYZING AND IMPROVING GRAVITY GRADIENT SATELLITE POINTING ACCURACIES AT HIGH ORBITAL ALTITUDES. VOLUME II. APPENDICES. |
JUN 1967 |
|
| Authors:
J. L. Palmer; H. S. Blackiston; R. L. Farrenkopf; TRW SYSTEMS GROUP REDONDO BEACH CA
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| APPLICATION OF MAGNETIC TORQUING FOR DESATURATION OF CONTROL MOMENT GYROS IN SPACE VEHICLE CONTROL. |
JUN 1967 |
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| Authors:
Leonard R. Hart; Harold W. Alatalo; Jack Braumiller; WESTINGHOUSE DEFENSE AND ELECTRONIC SYSTEMS CENTER BALTIMORE MD AEROSPACE DIV
|
| A group of control moment gyros can be used to control the attitude of a space vehicle by exchanging momentum with the rest of the spacecraft. However, externally caused disturbance torques acting on the vehicle would saturate the momentum capability of the gyros if no auxiliary torquing methods were provided to unload the stored momentum. This function can be performed by a set of three current-carrying coils which interact with ... |
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| BASIS OF INERTIAL NAVIGATION, |
04 MAY 1967 |
|
| Authors:
A. A. Yakushenkov; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH
|
| The work expounds the bases of the theory of inertial systems designed for naval navigation, the principle of action of their component elements and questions of long-term development of inertial navigation for the naval fleet. As the basis of the book there are the somewhat expanded and consideration is given to the kinematics of systems of inertial navigation, oriented in certain coordinate systems, which are of interest for the naval ... |
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| MODEL TESTS OF A STEPPED PLANING BOAT WITH AN ADJUSTABLE STERN STABILIZER. |
MAY 1967 |
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| Authors:
Eugene P. Clement; NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER WASHINGTON D C HYDROMECHANICS LAB
|
| A stepped hull is being developed which has an adjustable planing stabilizer at the stern for balance, stability, and control of trim. At high speed, this craft planes on a small area forward of the step (which is located approximately at midlength), with the stern supported by the adjustable stabilizer. Since the afterbody wetted area is eliminated at high speed, the frictional resistance, and accordingly the total drag also are ... |
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| FEASIBILITY STUDY OF FLUID FLYWHEEL TECHNIQUES TO PROVIDE NUTATION DAMPING OF LARGE SPINNING SPACE VEHICLES. |
MAY 1967 |
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| Authors:
Gerard J. Caggiano; GENERAL ELECTRIC CO JOHNSON CITY NY LIGHT MILITARY ELECTRONICS DEPT
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| The purpose of this study was to examine the feasibility of using fluid flywheels for nutation damping of large manned spinning space vehicles. A model space vehicle was selected, and a flywheel loop and pump analysis was conducted to define the best loop configuration and fluid-pump combination. Operational feasibility, weight and power requirements of the final system were determined by both analysis and analog simulation. It was concluded that a ... |
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| ROCKET CONTROL, |
20 APR 1967 |
|
| Authors:
v. p. petrov; A. A. Sochivko; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
|
| The book outlines the physical principles of rocket weapon control. Basic information from jet propulsion theory is given, and the most common rocket guidance systems described in the non-Soviet press are considered. |
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| ANTITANK ROCKET MISSILES, |
13 APR 1967 |
93 pages |
| Authors:
B. I. Evdokimov; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
|
| The pamphlet gives a popular treatment of the problems of design and combat application of antitank guided missiles (ATGM) (IITYPC). It relates the reasons that prompted the development of these missiles and the classification of ATGM's according to the most important criteria. After an acquaintance with the general concept of an ATGM, a more detailed account is given of the basic principles of designing the individual components of the ATGM ... |
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| STATIC WIND TUNNEL TESTS OF THE M823 RESEARCH STORE WITH FIXED AND FREE-SPINNING TAILS, |
05 APR 1967 |
|
| Authors:
Frank J. Regan; Mary E. Falusi; John E. Holmes; NAVAL ORDNANCE LAB WHITE OAK MD
|
| The M823 configuration is an instrumented free fall store used in bomb stability research programs. The report presents the results of the static wind tunnel tests of the basic forebody to which have been attached various stabilizers. These stabilizers include fixed and free-spinning cruciform tails and free-spinning monoplane tails. (Author) |
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| SERVO DAMPING OF A GRAVITY-GRADIENT STABILIZED SATELLITE. |
APR 1967 |
|
| Authors:
Gerard L. Commerford; James S. Whittier; AEROSPACE CORP EL SEGUNDO CA LABS DIV
|
| A system using gimballed optical sensors with servo controlled torques has been conceived as a possible mechanism for damping the librations of a gravity-gradient stabilized satellite. Analyses of the linearized equations of motion have established the servo gains required for stability, the type of motion to be expected, and the damping within all portions of the stable zones. A double compound pendulum has been constructed which qualitatively demonstrates the operation ... |
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| STABILIZATION SYSTEM ANALYSIS AND PERFORMANCE OF THE GEOS-A GRAVITY-GRADIENT SATELLITE (EXPLORER XXIX). |
MAR 1967 |
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| Authors:
V. L. Pisacane; P. P. Pardoe; B. J. Hook; JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB
|
| The paper discusses the stabilization system analysis and orbital performance of the GEOS-A gravity-gradient satellite which was launched into orbit on 6 November 1965. The analysis is performed with the aid of a rather general digital simulation of the non-linear differential equations of motion. It includes the effects of gravity-gradient forces, orbital eccentricity, eddy current dampers, residual magnetic dipoles, solar radiation pressure, and thermal distortion of the spacecraft's stabilization boom. ... |
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| A NEW APPLICATION OF THE PERFECTLY STIRRED REACTOR (P.S.R.) THEORY TO DESIGN OF COMBUSTION CHAMBERS. |
MAR 1967 |
|
| Authors:
Robert H. Essenhigh; PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF FUEL SCIENCE
|
| The chief requirement for combustion chamber design is a guarantee of ignition. This guarantee, it was suggested by Bragg 15 years ago, can best be met by formation of a Perfectly Stirred Reactor (P.S.R.) section at the burner location of a combustion chamber. This proposition is now proved formally in this report by considering representation of a plane or plug-flow flame by a sequence of P.S.R.'s. It is then shown ... |
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| ESTABLISHMENT OF INFRARED SPECTRA OF NITRATION PRODUCTS OF DIPHENYLAMINE. |
MAR 1967 |
|
| Authors:
Harry Levitsky; George Norwitz; FRANKFORD ARSENAL PHILADELPHIA PA QUALITY ASSURANCE DIRECTORATE
|
| The infrared spectra of the 19 nitration products of diphenylamine were established. It was necessary to synthesize 11 of these compounds. A comparison was made of the spectra obtained and assignments were made to the principle bands. (Author) |
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| THE UTILIZATION OF GROUND OBSERVATIONS FOR ATTITUDE CONTROL OF AN ORBITING VEHICLE. |
MAR 1967 |
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| Authors:
James D. Wilger; Robert G. Clodfelter; TECHNOLOGY INC DAYTON OH
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| A laboratory test program was conducted to determine the feasibility of a ground-controlled remote maneuvering unit (RMU) performing as a maneuverable satellite. A gyro-stabilized nitrogen-powered RMU mounted in a five-degree-of-freedom simulator and equipped with a television camera was employed in this exercise. Experiments were conducted to determine whether a ground controller can position and maintain the vehicle in a desired orientation with respect to the earth when his only information ... |
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| STABLE EQUILIBRIUM ORIENTATION OF A SPACECRAFT WHICH CONTAINS A MOMENTUM WHEEL. |
20 FEB 1967 |
|
| Authors:
J. U. Beusch; MASSACHUSETTS INST OF TECH LEXINGTON LINCOLN LAB
|
| The orientation of a spacecraft when it is in a stable equilibrium state is studied. The spacecraft contains a single momentum wheel which stores angular momentum. The axis of the wheel is not necessarily parallel to a principal axis of the spacecraft. For an arbitrary but fixed speed of the wheel relative to the spacecraft body, it is shown that there may be one, two, or three stable equilibrium points. ... |
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| DEVICE FOR AUTOMATIC BALANCING OF HYDRAULIC JIB CRANE, |
FEB 1967 |
|
| Authors:
L. D. Fabachnikov; Yu. K. Bugoslavskii; INSTITUTE OF MODERN LANGUAGES INC WASHINGTON D C
|
| A device for automatic equilibration of the hydraulic jib crane consisting of mobile counterbalance, subject to the change of load, run by power hydrocylinder connected with cylinder-transducers, placed on the operating devices that determine load and retaining moments. To raise safety measures of the crane's operation, a distributing slide-valve is installed in the artery connecting transducers with power hydrocylinder of counterbalance. This distributing slide-valve guarantees the feedback control of counterbalance ... |
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| FLUIDIC YAW DAMPER SYSTEM. |
FEB 1967 |
|
| Authors:
Orrin E. Ostlund; William G. Beduhn; HONEYWELL INC MINNEAPOLIS MN AERONAUTICAL DIV
|
| A fluidic yaw damper system, operating from jet engine bleed air, was designed, fabricated, and flight tested in an F101B aircraft. The purpose of the program was to demonstrate the capability of a fluid system to provide stability augmentation of a high-performance aircraft comparable to that provided by conventional electronic dampers. Major accomplishments involved: (1) Matching a vortex rate sensor with an eight-stage proportional fluid amplifier to obtain the desired ... |
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| INVESTIGATION OF CREW ESCAPE CONCEPTS FOR VTOL AND LOW-ALTITUDE DASH VEHICLES |
FEB 1967 |
|
| Authors:
John O. Bull; Edward L. Serocki; Jakob Schor; Larry J. Nolan; Bernie C. Mackey; BOEING CO RENTON WA
|
| This report covers the results of a study to define crew escape requirements and criteria for selection, evaluation, and design of crew escape systems for VTOL and low-altitude dash vehicles. Escape concept performance, survival, pressurization, restraint, crew comfort and efficiency, and development and qualification testing requirements are defined. Representative open ejection seat, encapsulated ejection seat, cockpit pod, and separable nose capsule escape concepts and vehicle configurations are defined. Escape concept ... |
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| Space Probes. |
19 JAN 1967 |
|
| Authors:
FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH
|
| Launched within the framework of the International Geophysical Year, the first artificial satellites provided a source of general information regarding the characteristics and physical processes of the upper atmosphere. More ambitious probes aimed at the distant environment of the Earth, Moon, and outer space were made possible by the first automatic interplanetary stations. This new stage in space investigation provided scientists with an opportunity to verify the hypotheses and ideas ... |
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| A STUDY OF HEAVY EQUIPMENT AERIAL DELIVERY AND RETRIEVAL TECHNIQUES |
JAN 1967 |
402 pages |
| Authors:
Edward L. White; Carl E. Brown; Robert F. Sturgeon; Benjamin H. Lightfoot; LOCKHEED-GEORGIA CO MARIETTA ADVANCED CONCEPTS DEPT
|
| Analytical studies were conducted for the purpose of defining optimum systems for the aerial delivery of payloads in the 35,000 to 70,000-pound range and the aerial retrieval of payloads in the 3,000 to 10,000-pound range. A generalized approach was utilized in the analysis and evaluation of candidate systems for both functions. Included in the study was a definition of requirements for each operational phase, the development of criteria for concept ... |
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| A HEAD RESTRAINT DEVICE FOR VESTIBULAR STUDIES. |
JAN 1967 |
|
| Authors:
W. Carroll Hixson; Jorma I. Niven; Charles A. Lowery; NAVAL AEROSPACE MEDICAL INST PENSACOLA FLA
|
| A restraint system based on a vacuum bladder technique was constructed from standard, commercially available materials. It provides a degree of restraint comparable to that available with permanent, rigid head/torso molds individually fitted to each subject without the attendant costs in preparation time and money. (Author) |
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| DESIGN STUDY ROLL CONTROL OF SEA-SITTING AIRCRAFT. |
JAN 1967 |
|
| Authors:
L. E. Lundquist Jr; LOCKHEED-CALIFORNIA CO BURBANK
|
| The feasibility of roll axis stabilization of air-sea vehicles during extended periods of sea-sitting on open ocean surfaces has been investigated for significant wave heights up to twelve feet (Sea State 5). Vehicle configurations included a conventional seaplane hull and a vehicle of advanced design which utilizes a tandem spar-buoy flotation system. While previous studies and tests have shown the feasibility of fitting aircraft with vertical floats to improve sea-sitting ... |
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| V/STOL APPROACH AND LANDING SYSTEMS. |
1967 |
|
| Authors:
ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT PARIS (FRANCE)
|
| The report presents the results of a survey on the practicalities of providing approach and landing guidance for V/STOL aircraft in accordance with the recommendations of AGARD Report VLS '65. While specific equipments were examined, the findings are framed in terms of general system types and should be interpreted as such. It is recommended that development work on guidance systems should continue at its present level pending the availability of ... |
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| TECHNIQUES FOR SUPER-MODE OSCILLATION. |
31 DEC 1966 |
|
| Authors:
Russell Targ; D. E. Caddes; J. D. Foster; J. M. French; L. M. Osterink; SYLVANIA ELECTRONIC SYSTEMS-WEST MOUNTAIN VIEW CALIF ELECTRONIC DEFENSE LABS
|
| An evaluation was made of the FM stabilization system, making use of the odd harmonic FM beats to achieve absolute frequency stabilization of the FM carrier with respect to the center of the atomic gain profile. The system is able to provide stabilization of better that 1 part in 10 to the 8th power on a long-term basis with no net drift in the FM spectrum. The FM laser not ... |
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| ENGINEERING FLIGHT TEST OF THE UH-1B HELICOPTER EQUIPPED WITH THE MODEL 540 ROTOR SYSTEM. PHASE D. |
DEC 1966 |
|
| Authors:
Laurel G. Schroers; John R. Melton; Allan L. Darling; Eldon F. Sampson; ARMY AVIATION SYSTEMS TEST ACTIVITY EDWARDS AFB CA
|
| The objectives of the test were to determine the airworthiness and to define the performance characteristics and flying qualities of the helicopter. Test Results, where appropriate, were compared with previous test results of the standard UH-1B. Tests were conducted at Edwards Air Force Base, California, and at remote test sites in California and Colorado from 19 May 1965 through 30 April 1966. Total aircraft flight time was 336.30 hours. Quantitative ... |
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| ON THE RELATIVE IMPORTANCE OF THE LOW SPEED CONTROL REQUIREMENT FOR V/STOL AIRCRAFT, |
DEC 1966 |
|
| Authors:
Stephen Goldberger; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE STATION TENN
|
| The closed loop dynamic response of a V/STOL airplane, pilot, and autostabilization system was studied with the purpose of demonstrating which airplane parameters are most important in determining the airplane's low speed flight characteristics. The influence of the stability augmentation system was found to be so great that the other parameters are small by comparison. The most important stability and control parameter in low speed, V/STOL aircraft flight, therefore, is ... |
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| THE ANALYSIS OF THE CONTROL OF ACTIVATED ANTI-ROLL TANKS. |
DEC 1966 |
|
| Authors:
William C. Webster; P. Dogan; ILLINOIS STATE NATURAL HISTORY SURVEY URBANA
|
| The application of activated, anti-roll tanks is considered in detail. Particular attention is paid to the configuration and the design of the control system to actuate the tank. In the first sections, the equations of motion of the ship, tank and pumps as well as the forces created by the seaway are derived. The methods of selecting the control are then discussed and the techniques of solving both the linearized ... |
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| CONTROL MOMENT GYROSCOPE GIMBAL ACTUATOR STUDY |
NOV 1966 |
239 pages |
| Authors:
L. Morine; T. O'Connor; J. Carnazza; H. Varner; D. Pool; BENDIX CORP TETERBORO NJ ECLIPSE-PIONEER DIV
|
| The purpose of this study is the determination of an optimal gimbal actuator for large double gimbal control moment gyros. The optimization study is divided into three distinct phases: torquers and transmissions, which together form the actuators, and controllers. The DC torquer and an epicyclic transmission are selected as optimal, on the basis of power, weight, size, reliability and performance. Pulse width modulation of a type designated as single channel ... |
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| SYNTHESIS OF A FLUIDIC FLIGHT CONTROL SYSTEM. |
NOV 1966 |
|
| Authors:
Lael B. Taplin; Kenneth W. Verge; Walter F. Datwyler; BENDIX RESEARCH LABS SOUTHFIELD MI
|
| A program was conducted to investigate the feasibility of synthesizing a fully-pneumatic fluidic flight control system for advanced vehicle applications. A pitch axis flight stabilization system was developed to determined feasibility and to indicate achievable performance. The system approach selected for investigation utilizes a novel pulsating vortex rate sensor, jet digital signal processing elements, and orifice-volume analog frequency shaping network, and a complete integrated rotary position servo. The position servo ... |
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| TECHNIQUES FOR SUPER-MODE OSCILLATION. |
30 SEP 1966 |
|
| Authors:
Russell Targ; J. M. French; ELECTRONIC DEFENSE LABS SYLVANIA ELECTRONIC SYSTEMS-WEST MOUNTAIN VIEW CALIF
|
| Construction of an automatic frequency control system for the absolute frequency stabilization of our 2-meter long, 50 mw FM laser was completed. The FM laser produces an error signal which increases as the laser frequency drifts with respect to the center of the Doppler-broadened fluorescence line. The electrical phase of the error signal changes by 180 degrees as the laser drifts from one side of line center to the other. ... |
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| THE BASES OF AUTOMATION AND TECHNICAL CYBERNETICS, |
23 SEP 1966 |
|
| Authors:
A. A. Krasovskii; G. S. Pospelov; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
|
| The book has three sectiins and contains a systematic account of the theory of elements of automatic devices, the theory of automatic control and the bases of technical cybernetics. A number of transmitters, amplifiers, controllers and regulating devices are discussed. The account of the theory of automatic adjustment includes the dynamics of linear, nonlinear and pulse systems of automatic control. The third section of the book - technical cybernetics - ... |
|
| PARACHUTE |
09 SEP 1966 |
4 pages |
| Authors:
E. F. Efremov; G. V. Petkus; K. S. Morozov; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSONAFB OH
|
| The object of the invention is a parachute with a canopy in the form of a circular belt. To increase its coefficient of lift and its stability, it is equipped with a small hemispherical canopy, the shroud lines of which go through an eye ring that is fastened to the central shroud line and the external rim is connected with the internal edge by four mutually perpendicular shroud lines. |
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| COMPILATION OF DATA ON CREW EMERGENCY ESCAPE SYSTEMS |
SEP 1966 |
356 pages |
| Authors:
John O. Bull; Edward L. Serocki; Howard L. McDowell; BOEING CO RENTON WA
|
| A comprehensive group of appropriate open ejection seats, encapsulated ejection seats, cockpit pod capsules, separable nose capsules, and subsystems are described. The descriptions provide information on items such as initiation, crew positioning and restraint, emergency pressurization and oxygen, seat-man separation, capsule separation, rocket motors, rocket catapults, stabilization, deceleration, recovery parachute, landing impact attenuation, flotation, location aids, and survival equipment or provisions. Information is also provided on escape system performance, tests, ... |
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| APPLICATION OF FLUIDICS TO AUTOMATIC FLIGHT CONTROL. |
SEP 1966 |
|
| Authors:
E. M. Dexter; S. D. Wills; C. V. DiCamillo; L. A. Kaufman; C. Van Dusen; BOWLES ENGINEERING CORP SILVER SPRING MD
|
| The report evaluates the feasibility and desirability of a fluidic Automatic Flight Control System. The study is carried out in four parts: (1) a description of the basic flight control system and fluidic components; (2) the definition and requirements for an automatic flight control; (3) a proposed fluidic system; and (4) an evaluation of the proposed system with a comparison with an existing Automatic Flight Control System. The Automatic Flight ... |
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| THE SUBCAVITATING HYDROFOIL (HYSTAD) PROGRAM. |
01 JUN 1966 |
|
| Authors:
GENERAL DYNAMICS/CONVAIR SAN DIEGO CALIF
|
| A series of four digital computer programs was used to facilitate the analysis of longitudinal mode stability of a given hydrofoil craft design. These programs have been modified for use on the BUSHIPS IBM 1620 Digital Computer. Craft physical data are converted into weight, center of gravity, and moment-of-inertia information; coefficients of the linearized equations of motion are generated; and finally the poles and zeroes of the open loop transfer ... |
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| THE SUBCAVITATING HYDROFOIL (HYSTAD) PROGRAM. |
01 JUN 1966 |
|
| Authors:
GENERAL DYNAMICS/CONVAIR SAN DIEGO CALIF
|
| The report summarizes the activities of a design definition phase (Phase I) of a program to design, fabricate and evaluate a set of HYSTAD-equipped, subcavitating, fully-submerged hydrofoils on the U. S. Navy's high speed hydrofoil research craft, FRESH-1. HYSTAD identifies a mechanical HYdrofoil STAbilization Device for providing stability to fully submerged hydrofoil systems in a highly reliable and nonelectronic manner. The results of analytical and design studies are presented along ... |
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| CONTROL OF SUPERSONIC AIRCRAFT, |
31 MAY 1966 |
|
| Authors:
F. I. Sklyanskii; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
|
| Contents: General information, equations of motion, definitions; Stability and controllability characteristics of aircraft, formation of forces on control levers of aircraft with non-power-assisted (boosterless) control systems; Change of characteristics of stability and controllability of aircraft at transonic and supersonic speeds of flight; Improvement of stability and controllability characteristics by methods of aerodynamic design and selection of shapes of supersonic aircraft; Power control formation of forces on aircraft control levers with ... |
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| STUDY OF APPLICATION OF RELIABILITY PREDICTION TECHNIQUES ON FLIGHT CONTROL COMPONENTS |
MAY 1966 |
148 pages |
| Authors:
J. B. Wertz; J. R. Goldgraben; M. E. Hassfurther; J. V. Baum; J. L. Easterday; BATTELLE MEMORIAL INST COLUMBUS OH
|
| A previous reliability research effort generated an analytical technique called the Moment method for predicting drift-type failures in components and systems. This technique is based on the Propagation of Variance formula, which combines data derived from the system, or system model, and formula, which combines data derived from the system, or system model, and parameter tolerance data, to formulate an estimate of the probability that the system will perform within ... |
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| Collection of Documents Pertinent to Development of Military Soil Stabilization Objectives and Requirements (1956-1959), |
MAY 1966 |
|
| Authors:
G. R. Kozan; J. D. Stouffer; ARMY ENGINEER WATERWAYS EXPERIMENT STATION VICKSBURG MISS
|
| The report consists of a collection of documents (Appendixes A-F) prepared during the period 1956 through 1959 which summarize the development of objectives and requirements pertinent to the military soil stabilization research activities. The collection includes memoranda, correspondence, and minutes of conferences which were concerned with the delineation of the broad project objectives in specific terms and measurable parameters to provide realistic guides for the development, evaluation, and design phases ... |
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| A CONTRIBUTION TO THE PROBLEM OF CONTROLLING THE IMAGE STEADINESS IN MOTION PICTURE CAMERAS. |
08 APR 1966 |
|
| Authors:
V. Hyrsl; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
|
| The article describes and evaluates the means for obtaining picture stability in various types of professional picture cameras, analyzes the sources of picture glittering, and considers the problem of certain arrangements in relation to imperfections of perforation opening. A simple practical method of controlling picture stability characterized by a so-called medium empirical value is described. |
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| SPACE VEHICLE ATTITUDE CONTROL WITH A MODIFIED VISCOUS LANCHESTER DAMPER. |
APR 1966 |
|
| Authors:
Harold D. Nuffer; NAVAL ORDNANCE TEST STATION CHINA LAKE CA
|
| Some applications of space probes or satellites require that the vehicle be spin stabilized about the principal axis of maximum moment of intertia. In this report, a passive precession damper for stabilization of a space vehicle is analyzed, and basic requirements for such a damper are discussed. Exact equations of motion for a modified viscous Lanchester damper are determined. Owing to the unwieldy nature of these equations, certain approximations are ... |
|
| TURBINE-DRIVEN NU-8F LIAISON TEST BED. |
APR 1966 |
|
| Authors:
BEECH AIRCRAFT CORP WICHITA KANS
|
| The development and flight test program of the NU-8F was conducted. A Beech Model U-8F was modified by the installation of two UACL PT6A-6 turbine engines in place of the reciprocating engines, and by replacing the stabilizer and rudder with a Beech Model A80 stabilizer and rudder. Ground and flight tests were conducted using FAA regulations as the standard of acceptability. The report contains a comparison of performance characteristics of ... |
|
| Report of Conferences on Dust Control, January 1966, |
APR 1966 |
|
| Authors:
W. L. McInnis; ARMY ENGINEER WATERWAYS EXPERIMENT STATION VICKSBURG MISS
|
| The first conference was held with industry representatives and the second conference was held with Consultants. Minutes of the two conferences are summarized. |
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| INITIAL DEVELOPMENT OF A NONLINEAR MECHANICAL MODEL FOR THE MOMENT RESPONSE OF FREE-SURFACE ROLL STABILIZATION TANKS. |
MAR 1966 |
|
| Authors:
John F. DALZELL; SOUTHWEST RESEARCH INST SAN ANTONIO TEX DEPT OF MECHANICAL SCIENCES
|
| The report outlines the development of a nonlinear mechanical model for the moments exerted on the ship by the fluid contained in the free-surface roll stabilization tank. Though it is not clear that the current model is the best that can be achieved, the correlation demonstrated in the report between the current mechanical model and experimental results is comparable with that obtained in the aerospace industry between experimental results for ... |
|
| A REVIEW OF RESEARCH ON THE INTERACTION OF A JET WITH AN EXTERNAL STREAM. |
MAR 1966 |
|
| Authors:
C. C. Lee; BROWN ENGINEERING CO INC HUNTSVILLE ALA RESEARCH LABS
|
| A descriptive review is made of recent studies on the interaction of a jet with an external stream. Experimental data and empirical equations for the jet center line were reported. The existence of a pair of vortices in the jet flow was indicated. Further study, in order to determine the strength and location of the vortices either by acquisition of more data or by the development of the theory, is ... |
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| STABILITY/CONTROL AUGMENTATION SYSTEM EVALUATION. |
FEB 1966 |
|
| Authors:
Marvin Easter; OHIO STATE UNIV COLUMBUS DEPT OF AVIATION
|
| A study was made to evaluate competency of pilots trained in aircraft having a stability augmentation system. This is to determine the necessity of issuing restricted certificates to private pilots if they are unable to pass the private flight check by manual operation of controls. This project was to train five students to required flight performance for a private pilot certificate in a Cherokee-140 equipped with the Mitchell AK-153 Stability ... |
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| THE QUESTION OF CALCULATING THERMAL COMPENSATION IN OSCILLATORY CIRCUITS AND STABILIZATION OF THE OSCILLATION PERIOD OF THE BALANCE WHEEL IN A NEW TYPE ESCAPEMENT REGULATOR WITH RESTRICTED MOVEMENT, |
FEB 1966 |
|
| Authors:
L. D. Vishnevskii; Z. M. Akselrod; ARMY FOREIGN SCIENCE AND TECHNOLOGY CENTER WASHINGTON D C
|
| A method is presented for selecting the values of capacitors to be used in the temperature-compensating circuits of temperature-stable oscillators. Parallel and series connected compensators are considered. Temperature compensation by variable capacitor is briefly discussed. A new type of escapement regulator, with restricted movement is described, and its dynamic characteristics are presented. In the new type escapement, the geared wheel moves one notch when the balance wheel, with one slot, ... |
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| AN EXPERIMENTAL PARAMETER STUDY OF THE FLUID FORCE AND MOMENT RESPONSE OF TWO TYPICAL SHIP ROLL STABILIZATION TANKS. |
FEB 1966 |
|
| Authors:
John F. DALZELL; SOUTHWEST RESEARCH INST SAN ANTONIO TEX DEPT OF MECHANICAL SCIENCES
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| In the course of a continuing study of the internal fluid dynamics of free-surface ship-roll stabilization tanks, a lack was noted of systematic experimental information combining the effects of tank distance from center of rotation, excitation amplitude and fluid depth for either the 'rectangular' type tank or the 'H' type. The purpose of the report is to present data obtained in an experimental study aimed at supplying a portion of ... |
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| ARTILLERY WEAPON DUST ALLEVIATION TESTS. |
FEB 1966 |
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| Authors:
J. L. Decell; ARMY ENGINEER WATERWAYS EXPERIMENT STATION VICKSBURG MISS
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| Tests were conducted at the Rock Island Arsenal and the Yuma Proving Ground to determine the effectiveness of medium-weight and lightweight ground covers when used as dust alleviators beneath the muzzle blast of an XM-102 artillery weapon. The ground covers proved to be adequate dust alleviators, and test results indicate that a minimum size cover of 75 by 75 ft should be used with the XM-102 weapon. The lightweight ground ... |
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