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1967-02-01
Standard
ARP924
This recommended practice cover the requirements for the types of glass to be utilized in the fabrication of cover glasses and lighting wedges used in aerospace instruments. It defines the maximum extent of physical defects and recommend standard methods of inspection and evaluation. Definitions of terminology used in this document are covered in Appendix A.
1967-02-01
Technical Paper
670458
Derwyn M. Severy, Harrison M. Brink, Jack D. Baird
Engineering evaluations of the collision performance for the Liberty Mutual Safety Car and the 1966 Chevrolet sedan were made, consisting of two 30 mph rear-end and two 40 mph intersection collision experiments. Methodology provided comparative analysis of functional characteristics for five types of seats, each studied for different exposure conditions. Five conditions of restraint were included for four sizes of occupants; the anthropometric dummies, their restraints, seats, and crashing cars all carried appropriate transducers. Seven high G-tolerant, high-speed cameras, carried by the crashing cars provided close-up continuous monitoring of these quarter-second collision sequences, supported by many more tower and ground level special photographic units arranged about the collision scene. Data from photographic, electronic and related instrumentation are presented using photographic and graphical techniques designed to facilitate comprehension.
1967-02-01
Technical Paper
670854
John F. Foster, John H. Litchfield
Experimental results obtained with a continuous culture system for the cultivation of Hydrogenomonas eutropha for waste management in a life-support system indicate that a reliable and stable system can be designed under the present state-of-the-art. The present system provides for control of hydrogen, oxygen, carbon dioxide, pH, cell density, temperature, urea, and ammonia during growth. The culture system design is adaptable to operation in a zero-gravity field, and should be adaptable to integration with proposed water electrolysis and product recovery systems for waste management in an overall life support system.
1967-02-01
Technical Paper
670984
R. Trebosc
Discussed are the followed components of the Concorde's air conditioning system: dual pressure reduction/shutoff valve, mass flow control valve, primary heat exchanger bypass temperature control loop, cold air unit, temperature control valve, water extractor, and water extractor actuator controller. Functional and mechanical descriptions are given for each. The system is basically a bootstrap air cycle in which fuel and ram air cooling are provided in the intercooler loop.
1967-02-01
Technical Paper
670982
B. B. Turner
The Environmental Control System of the SST must keep the passengers safe and comfortable under all operating conditions. This requires not only an excellent system design, but a system that can be maintained and operated by typical airline personnel under all airline conditions of time and place. The airlines are working toward these objectives with the airframe manufacturer through SST specialist teams composed of engineering personnel from the airlines purchasing the 2707 or the Concorde. This paper discusses the objectives and considerations of the Environmental Control System specialist team in working toward minimizing the airlines problems on the SST.
1967-01-31
Standard
AS439
This standard covers stall warning instruments to provide positive warning to the pilot of an impending stall. Stall, as defined for the purpose of this standard, is the minimum steady flight speed at which the airplane is controllable.
1966-08-15
Standard
ARP842A
This recommended practice sets forth the design objectives for handling qualities applicable to transport aircraft operating in the subsonic, transonic and supersonic speed range. These objectives are not necessarily applicable to rotor or VTOL aircraft.
1966-08-01
Standard
AIR818A
This Aerospace Information Report, (AIR) is intended to provide the sponsors of Aerospace Standards, (AS), with standard wording, formatting, and minimum environment and design requirements for use in the preparation of their document. The individual shall use only those parts of this AIR which apply to their particular document. The individual sponsor may expand the standard wording, especially under Sections 4, 5, and 6 as required. The paragraphs of this AIR shall be used verbatim wherever possible. Unless otherwise directed by SAE, cross referenced documents shall be called out by specific revision letter, e.g. "shall be in accordance with AS XXXXB." In addition, all non-SAE documents called out shall include the document title when initially identified. However, every effort shall be made to keep cross-referencing to an absolute minimum.
1966-08-01
Standard
ARP699C
This Recommended Practice is intended to outline the design, installation, testing, and field maintenance criteria for a high temperature metal pneumatic duct system, for use as a guide in the aircraft industry. These recommendations are to be considered as currently applicable and necessarily subject to revision from time to time, as a result of the rapid development of the industry.
1966-08-01
Standard
J576B_196608
This SAE Recommended Practice provides test methods and requirements to evaluate the suitability of plastic materials intended for optical applications in motor vehicles. The tests are intended to determine physical and optical characteristics of the material only. Performance expectations of finished assemblies, including plastic components, are to be based on tests for lighting devices, as specified in SAE Standards and Recommended Practices for motor vehicle lighting equipment. Field experience has shown that plastic materials meeting the requirements of this document and molded in accordance with good molding practices will produce durable lighting devices.
1966-07-01
Standard
AS916
This SAE Aerospace Standard (AS) defines the overall requirements applicable to oxygen flow indicating devices intended to operate in conjunction with an oxygen regulator and mask system. Flow indicators covered by this document are for use with pressure demand, diluter-demand and continuous flow oxygen systems.
1966-06-01
Standard
J954_196606
This SAE Recommended Practice is intended to provide uniform tolerances for dimensions of urethane materials used for motor vehicle seating. Table 1 describes these tolerances as related to slab and molded applications.
1966-06-01
Standard
AS428
This standard establishes the essential minimum safe performance standards for exhaust gas temperature instruments primarily for use with turbine powered, subsonic aircraft, the operation of which may subject the instruments to the environmental conditions specified in paragraph 3.3 et seq. The exhaust gas temperature instruments covered by this standard are of the electrical servonull balance type, actuated by varying emf output of one or more parallel connected Chromel-Alumel thermocouples.
1966-05-01
Standard
J953_196605
The scope of this SAE Recommended Practice is to establish uniform test procedures for passenger cars, to determine whether the system is defined as a defroster or defogger, and to establish minimum performance requirements for each system. A defroster for purposes of this practice is a system which will remove moisture and/or frost from the interior surface of the backlight at -18 °C. A defogger is a system which will remove moisture and/or fog from the interior surface of the backlight at 4 °C. The test procedure is intended to simulate actual conditions by utilizing either a cold room with an appropriate device to introduce air flow over the backlight or a sufficiently large wind tunnel with ambient temperature control. The test procedure and the minimum performance requirements are based on currently available engineering data.
1966-04-01
Standard
AIR512
This document covers the general recommendations for cabin lighting in order to provide satisfactory illumination for, but not limited to: a. Boarding and deplaning b. Movement about the cabin c. Reading d. Use of lavatories e. Use of work areas f. Exiting under emergency conditions g. Using stowage compartments, coat rooms, and closets h. Using interior stairways and elevators (lifts)
1966-02-01
Technical Paper
660797
Bernard C. Hilton
British medical and road safety research teams have revealed the need for improvement in vehicle seating designs to eliminate serious injuries and deaths arising from car occupant movement and ejection during impact. The paper describes the main requirements of safety seating and the result of three years development work in Britain to produce effective seats and mountings of low cost, capable of being fitted into conventional vehicles and of coping with forward loads of over 30 G. It is estimated that the adoption of such seats would increase the vehicle cost by less than 2%.
1966-02-01
Technical Paper
660207
Arthur E. Miller
The importance of oxygen in our environment is briefly reviewed, and a number of potential future developments which might result in radically different oxygen storage and distribution systems in aircraft are described and discussed.
1966-02-01
Technical Paper
660154
J. B. Beltz, A. K. Watt, J. H. Diener, W. A. Weidman, R. J. Schultz, J. R. Doidge, D. P. Marquis
This five part paper discusses in detail the development of a car -- a new breed -- The Toronado. The desire to create a better automobile, one from which both driver and passenger would receive maximum benefit, prompted the original concept. The exploratory design study, undertaken by many Oldsmobile departments, was unfettered by commitment to traditional arrangement. This led to the development of a vehicle employing front wheel drive with all the power components designed into a single unit forward of the passenger compartment. Among the advantages of the unitized powerplant approach are maximum passenger space, a nearly vibration-free ride, and exceptional directional stability.
1966-02-01
Technical Paper
660208
G. R. Whitnah, R. D. Mills
In recent years, vapor-cycle cooling systems have been used widely on airliners and are currently offered on some business aircraft. Several aircraft manufacturers are now studying the incorporation of vapor-cycle systems in their new business. In an independent research and development program, the Applied Science Division of Litton Systems, Inc. has developed a vapor-cycle air conditioning system designed to the requirements of this class of aircraft. Minimum power consumption consistent with reasonable weight and volume is considered extremely important. Compatibility with ventilation or pressurization systems is also an important design consideration. Test results are given for a range of operating speeds.
1966-02-01
Technical Paper
660209
L. B. Clay
A general discussion of the problems involved in introducing air conditioning in small executive aircraft. The discussion includes: (1) early studies and hardware for “add on” package units, (2) system selection studies for small pressurized turbine powered aircraft, (3) system design including structural changes required, (4) testing, development and service experience on the Beech King Air cooling system and (5) other applications and possible future development trends.
1966-02-01
Technical Paper
660451
Vaino J. Vehko, William E. Ruhland
To meet the demands of increasing payload size and weight, and to fill the large payload gap between the Saturn IB and Saturn V, a number of methods of uprating the Saturn IB have been studied by NASA and Chrysler Corp. of providing increased payload capability is discussed in this paper. Four 120 in. United Technology Center UA-1205 solid propellant motors, originally developed for the Air Force Titan III program, are clustered around the S-IB first stage of the Saturn IB launch vehicle. These four solid propellant motors provide the total thrust for liftoff of the vehicle, with S-IB stage ignition occurring just prior to burnout and separation of the solid propellant motors. The term “Zero Stage” is applied to this added stage.
1966-02-01
Technical Paper
660672
Gordon N. Davison
The large difference between the total numbers of manned and unmanned spacecraft and their respective missions is discussed. The environmental and functional requirements having different effects on the two spacecraft types are described. The materials characteristics involved in those requirements and the resulting typical configurations are reviewed. It is concluded that vibration and pressurized gas containment have the outstanding influence on spacecraft structural systems. It is noted that new structural factors of safety have not been derived on the basis of any rational consideration of the design conditions for stability or pressure critical structure.
1966-02-01
Technical Paper
660749
Wilhelm Bosch
A new laboratory technique is described which permits visual display and easy evaluation of the discharge characteristics of any given fuel injection pump at random nozzle back-pressure. In contrast to former fuel rate indication devices, the instrumentation is basically simple and lends itself to accurate calibration. Discussed are the basic underlying theory, the dimensional requirements for the measuring apparatus proper, and practical and theoretical applications of the new method on fuel injection systems. In conformance with the original dissertation, metric dimensions are used throughout.
1966-01-01
Magazine
1965-11-01
Standard
AIR847
The purpose of this information report is to provide minimum design criteria for oxygen equipment to be used on commercial transport aircraft which fly above 45,000 ft. To separate these requirements from those for spaceplanes, the maximum flight altitude for aircraft defined by this report is limited to the maximum altitude obtainable by aircraft using air-breathing engines.
1965-11-01
Standard
AIR910
The purpose of this report is to provide information on ozone and its control in high altitude aircraft environmental systems. Sources of this information are listed in the selected bibliography appearing at the end of this report, to which references are made throughout.
1965-10-20
Technical Paper
650958
ROGER P. DANIEL, L. M. PATRICK
1965-10-01
Standard
AS452A
The purpose of this standard is to establish optimum standards for crew demand and pressure-breathing oxygen mask assemblies for use by crew members in civil aircraft. This standard covers both general type and quick-donning type mask assemblies in the following classes: a. Class A, oronasal, demand b. Class B, oronasal, pressure-demand c. Class C, full face, demand d. Class D, full face, pressure-demand
1965-10-01
Standard
ARP881
This SAE Aerospace Recommended Practice (ARP) lists the lamps in Table 1 that are recommended for the type of service indicated. This list is not intended as a catalog and does not include many types that are now in use. This specification is not applicable to Solid State Lighting Lamp Assemblies (Based LED lamps). It does, however, reflect current practice.
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