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Standard

SURFACE TEXTURE

1963-06-01
HISTORICAL
J448_196306
This SAE Standard is concerned with the geometrical irregularities of surfaces of solid materials. It establishes definite classifications for various degrees of roughness and waviness and for several varieties of lay. It also provides a set of symbols for use on drawings, and in specifications, reports, and the like. The ranges for roughness and waviness are divided into a number of steps, and the general types of lay are established by type characteristics. This standard does not define what degrees of surface roughness and waviness or what type of lay are suitable for any specific purpose. It does not specify the means by which any degree of such irregularities may be obtained or produced. Neither is it concerned with the other surface qualities such as luster, appearance, color, corrosion resistance, wear resistance, hardness, microstructure, and absorption characteristics any of which may be governing considerations in specific applications.
Standard

GENERAL REQUIREMENTS FOR APPLICATION OF VAPOR CYCLE REFRIGERATION SYSTEMS FOR AIRCRAFT

1963-05-01
HISTORICAL
ARP731
Recommendations of this ARP refer specifically to the application of closed cycle vapor cycle refrigeration systems as a source of cooling in an aircraft air conditioning system. General recommendations for an air conditioning system which may include a vapor cycle system as a cooling source are included in ARP 85, Air Conditioning Equipment, General Requirements for Subsonic Airplanes, ARP 292, Air Conditioning, Helicopters, General Requirements For, and AIR 806, Air Conditioning Design Information for Cargo and High Density Passenger Transport Airplanes, and are not included herein.
Standard

AUTOMATIC PILOTS (Turbine Powered Subsonic Aircraft)

1963-02-01
HISTORICAL
AS440
This Aerospace Standard covers Automatic Pilots intended for use on aircraft to automatically operate the primary and trim aerodynamic controls to maintain stable flight and/or to provide maneuvering about any of the three axes through servo control. Automatic control functions essential for primary or augmented flight control are excluded.
Technical Paper

Operational Experiences Of Jet Transports

1963-01-01
630445
Operational experiences of jet transports as determined from NASA VGH records collected during routine airline operations are discussed. The information presented relates to the flight loads, airspeed operating practices, and landing contact conditions. The load sources considered are gusts, maneuver, autopilot, and landing impact. The discussion of airspeeds covers the normal operating speeds, speeds in rough air, and overspeeds. Implications of the data as regards supersonic transport operations are indicated.
Technical Paper

Development of an Advanced Design Cryogenic Space Power System

1963-01-01
630444
The design and development of an advanced cryogenic space power system is described. Heat addition to the turbine cycle is derived from heat energy dissipated from the turbine powered components. Thus the environmental control system is integrated with the power supply, the Cryhocycle principle. This power supply is capable of long duration space missions and is targeted for 300 hr of continuous operation. Design features allow a low 300 F peak cycle temperature with a low 1.50 lb/shp/hr specific propellant consumption.
Technical Paper

Data Acquisition and Statistical Analysis Using Analog Computer Techniques

1963-01-01
630472
Paper is concerned with continuous data analysis using analog computer techniques. The author discusses briefly some of the possible techniques available. There are many variations or, and ramifications to, the circuits discussed. The type of analysis, the author points out, is an integral and important part of the design of any experiment.
Technical Paper

Low Pressure Timed Injection and Control System for the Otto Cycle Engine

1963-01-01
630468
The present use of the carburetor to supply fuel to the Otto cycle engine has placed it in a difficult competitive position with the diesel engine, which has successfully operated with a fuel injection system. The purpose of this study was to consider the feasibility of utilizing a low pressure injection system for the Otto cycle engine. The proposed design is discussed in detail. As the author points out, this system will allow design changes in the engine that would be impossible if the carburetor were retained, and thus considerable improvement in performance and efficiency can be realized for the Otto cycle engine.
Technical Paper

Portable Power from Nonportable Energy Sources

1963-01-01
630470
To meet future world energy demands, the engineer’s task will be to develop, through research, means of supplying new sources of energy. Though nuclear processes and solar energy will provide future energy, they are not readily adaptable to portable power systems due to inherent shortcomings. Energy can be supplied to portable power systems by energy storage systems using chemical, mechanical, or electrical forms, or it may be supplied through energy-in-transit systems. Technical discussion of various systems is presented. To develop suitable energy storage systems, thought must be given to problems of construction, operation, maintenance, and economics. Research is necessary to determine which chemical fuels are most adaptable for internal combustion engines.
Technical Paper

A Review of Commercial Air Transport From Its Beginning--Its Future and Problems

1963-01-01
630466
Milestones of domestic air transportation in the past 50 years are highlighted. Many early innovations were of European origin. Lindbergh’s flight accelerated the use of airplanes as a means of domestic transportation. The DC-3, prior to World War II, achieved a high degree of standardization and established a foundation for future airline growth. After World War II, converted military transports were primary means of conveyance. Phenomenal growth of air travel is due to increased speed, safety, and comfort brought about by use of four-engine planes, automatic pilot, cabin pressurization, and improvements in electronic guidance systems. Basic problems such as over-capacity, need for greater standardization, better ground facilities, and efficient servicing of local air traffic face the airlines today.
Technical Paper

Simulation Approach to Development of the XV-5A Lift-Fan V/STOL Aircraft

1963-01-01
630377
Design features of the XV-5A lift fan V/STOL airplane combine uniquely to give it the speed performance of a jet in conventional flight and the take-off and landing capability of a helicopter. The simulation program represents three main functions in the aircraft development cycle: mathematical models optimize the flight control system design; an actual control system replaces its mathematical counterpart; simulation enables the test pilot to become completely familiar with cockpit controls and handling. Flight simulation faithfully represents aircraft dynamics and presents a realistic visual display of position and motion of the aircraft with respect to the earth.
Technical Paper

Management Responsibility for Electromagnetic Compatibility

1963-01-01
630383
Modern weapon systems and large industrial complexes utilize large portions of the electromagnetic compatibility spectrum from the lowest power line frequency up through the microwave regions. These large complexes present the need of a definite management program to obtain intra-system functional compatibility and electromagnetic compatibility. Management needs policies, specifications, and procedures to obtain the functional integration that is necessary for the end requirement. It cannot be emphasized too strongly that electromagnetic compatibility is not a test program, and this paper will bring these points to light and will outline the management objectives and areas that should be followed.
Technical Paper

Calorimeters: Heat Rate Sensors for Space Vehicle Boosters

1963-01-01
630368
Methods of measuring radiation and convective heating on airborne vehicles are discussed. Different modes of heat transfer require special gages for determining transient and steady state heating rates. The slug or slope type calorimeter is used to measure both total and radiant heating. A unique conical purge method is used to insure filter cleanliness during flight duration and measuring period. Various types of heating rate gages are discussed outlining the capabilities of each and the factors influencing their accuracy. Experimental data indicates that convective and conductive heat losses from the sensors can be decreased significantly by incorporating special design features. Black body characteristics of the sensors are discussed in relation to the wave length and temperature of the emitting infrared source. Preflight and postflight calibration techniques are used to eliminate uncertainties.
Technical Paper

APPLICATION OF SELF-ADAPTIVE CONTROL TECHNIQUES TO THE FLEXIBLE SUPERSONIC TRANSPORT*

1963-01-01
630369
Two self-adaptive control techniques, the limit-cycle technique of Minneapolis-Honeywell and the model-reference technique of MIT, are applied in the design of flight control systems for a flexible supersonic transport. The primary objectives are to provide good airplane handling qualities and adequate damping of the structural bending modes. Only control of the longitudinal short-period response and symmetric bending modes is considered in detail. Though it is concluded that either self-adaptive technique can be applied successfully to the SST, there are problems with meeting handling qualities requirements and controlling the structural modes, and with operation of the adaptive systems in the presence of disturbances such as gusts. Further study is necessary.
Technical Paper

4300 F Thermocouples for Re-Entry Vehicle Applications Part II

1963-01-01
630360
This paper presents a discussion of the component evaluation and design development work performed in developing a 4300 F reentry vehicle nose cap temperature sensor. Material compatabilities, insulation resistance, and atmospheric pressure effects on bare wire calibration data are discussed in some detail. The final design is outlined and the application problems discussed. The probe utilizes: a sintered iridium high temperature sheath (4300 F) and platinum 20% rhodium as the low temperature sheath (3000 F); beryllia as insulation -- hard fired at 4300 F and compacted powder at 3000 F; tungsten versus tungsten 26% rhenium as the thermocouple pair.
Technical Paper

High Temperature Sensors for a Re-entry Research Vehicle

1963-01-01
630366
In the early fall, a re-entry research vehicle is scheduled to be flight tested to obtain aerothermodynamic and elastic environmental test data at various flight angles and speeds. This paper deals with the temperature portion of that vehicle. Specifically, it considers the analytical temperature profile at various portions of the vehicle, the history and stability testing of the thermocouples as well as their coatings, the manufacturing procedure for the sensors, and the problem areas encountered during their processing. The materials selected for the flight test are: molybdenum, columbium and platinum-20% rhodium sheaths, magnesium and beryllium oxide insulation, and tungsten-5% rhenium versus tungsten-26% rhenium and platinum versus platinum-10% rhodium thermoelements.
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