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The word "technician" embraces a broad spectrum of skilled workers. This paper is concerned with a few specialized groups who are defined in detail for further study. The examination includes their background and training, the organization for administration and supervision of their work, where they come from, and what their opportunities presently seem to be. The paper describes certain factors which determine how many technicians may be utilized effectively and the experienced trends of one organization. It concludes with a short discussion of the use of the title "engineer" and the problem of technician job stability.

The airline industry, continuing its support for the development and implementation of the ATC radar beacon system, now strongly endorses the use of automatic altitude reporting. In discussing the pitfalls which have delayed implementation of the basic ATC radar beacon system, this paper calls attention to the need for automatic altitude reporting in the ATC system, and the need to provide it quickly. In describing the need for automatic altitude information for both en route and terminal ATC, the choice of an altitude-interrogation mode, the 100-foot-altitude reporting increment, and the flexible code structure being proposed which is intended to cover all significant altitude strata to provide both coarse-grain and fine-grain information as required, are discussed. The paper also describes both early and recent actions by the airline industry in the field of secondary radar.

The electronic power converter, controlled by the equipment described in this paper, consists of two units rated 10,000 kw installed and operating at the Edgar Thomson Works of the Carnegie-Illinois Steel Corporation. The power converters connect a 60-cycle 69-kv system and a 25-cycle 44-kv system with a permissible power transfer of 20,000 kw in either direction between the systems. Transfer of power by rectification and inversion and the design of the electronic power converter are discussed in companion papers.1,2 The switchgear and control devices are discussed in this paper and for convenience and clarity, the discussion is divided into three main headings: ``Switching,'' ``Control,'' and ``Protection.''

The air traffic control problem consists of operational, technical, and political elements. This paper, however, is confined to the technical (equipment) aspects of the problem. The equipment subsystem consists of five essential elements. These are: Type I?means whereby pilots of aircraft may know their positions and means whereby they may be able to conduct their aircraft over any arbitrarily chosen routes from terminal to terminal; Type II?means whereby a central decision-making entity may be able to know the position of all aircraft within its jurisdiction; Type III?means where-by the decision-making entity can determine instantly safe, nonconflicting flight procedures for all aircraft within its purview; Type IV?means whereby instantaneous safe-flight instructions may be transmitted unambiguously to all aircrafts concerned; Type V?means whereby action may be coordinated among the several central flightinstruction, decision-making entities. The paper lists the significant actions which have affected the air traffic control equipment subsystem. It gives the history of the various units which form the present equipment subsystem and forecasts the equipment that may constitute the future traffic control subsystem.

This paper reviews the problems of skid design for electronic equipment shelters, lists and evaluates possible skid system types, and suggests an approach for future designs.

Advancements in technology have led to increased demand for avionics in airborne applications. Although aeronautical system suppliers have implemented improved procedures and design approaches which are generally effective, challenges continue to exist. This paper explores several areas where overall aeronautical system design might be improved by proper emphasis on avionic subsystem design. The topics selected include standardization, weight impact, environmental control, maintainability, and avionic equipment growth. Comparisons are made in terms of ultimate cost to the aeronautical system user.

Failure analysis experience gained in support of several major spacecraft programs has shown the vast majority of electronic part failures encountered to be the result of relatively straightforward quality defects and misuse. Within the framework of this experience, it is estimated that the number of part failures resulting from these simple causes is at least 100 percent greater than that due to more subtle time/environment dependent failure mechanisms. Therefore, even first-order failure analysis without resort to sophisticated facilities and techniques can provide substantial information regarding the cause of equipment malfunction. It is the intent of this paper to briefly discuss the role of part failure analysis in support of system development, indicate the relative proportion of part failures due to various major causes, and present several examples of failure analysis results.

The prime purpose of this paper is to describe the advances in Zener diode transient suppressors for ground vehicle and aircraft application. The evolution of the transient suppressor development for the U.S. Army is presented with emphasis on space, weight, and cost considerations. Improvements including an electronic thermal switch and a "battle override" switch are also described. A futuristic transient suppressor of modular design developed for use as an integral part of the equipment being protected is functionally described.

From a small beginning only a few decades ago, the electronics industry has grown to a place of first importance in our national economy. Electrical engineering education has not only adapted to reflect this growth but continually altered its approach in order to provide leadership for further expansion of the field. In this paper the process of educating engineers for careers in industrial electronics is discussed, with emphasis upon the kinds of educational experiences engineering students should now have in order that they may be prepared to cope with the many challenges the industry will face in the future.

CURRENT bibliographies on aircraft instruments list a reference to an early article dated 1904–40 years ago. This paper, describing an altimeter, has been followed by thousands more indicating the interest and technical advancements in aircraft instruments. The needs of the aircraft industry have been met by the instrument manufacturers. Developments in instruments have paralleled the rapid developments in aircraft due to the close co-operation of measurement and aeronautical engineers. A typical aircraft instrument panel is shown in Figure 1.

This paper discusses the various configurations which rotary converter and inverter sets might assume as major functional units within larger systems. Included is the description of various generator types, as well as excitation and regulation systems. An analysis of typical specifications and performance capabilities, as relate primarily to 400 cps output sets, is presented. This general discussion should be useful in providing the reader insight into considerations important for proper application of these rotary units.

Simulation, or modeling, has become an indispensable tool in aerospace vehicle development, providing essential experimental information in support of analytical work on an economical and timely basis. Simulation techniques, properly implemented and applied, are equally useful for telemetry and instrumentation design and development. This paper describes a Data System Simulator facility designed and constructed to provide factual evidence of data system design approach validity prior to proposal preparation or commitment to hardware construction. Representative uses of the simulator and advantages of data system simulation are discussed.

This paper on the Courier satellite presents some of the background against which this experiment on an operational satellite communication system is being conducted. Details on the development, construction and testing of both the ground and orbiting segments of the system are outlined. Information on the results expected from the operational aspects of the experiment are also presented.

Careful and diligent failure analysis is necessary to obtain maximum benefit from life tests of electronic equipments. The importance of good failure analysis is often underrated in a test program, to the detriment of the program. This paper discusses the role and the significance of correct attitudes, advance indoctrination, thorough planning, skills, facilities, and effective supervision in adequately diagnosing each failure incident, in recording its details, and in preserving the lesson learned.

This paper discusses the increasing importance of the transfer of intelligence and data from the military user to the contractor and its effect upon the development of a system or product. The discussion considers significant events in a typical program from conception through operation and explores the advantages and disadvantages of existing methods for obtaining this feedback. Recommendations are made which would ensure improved use of this data on the system delivered to the military.

This paper describes a UHF Beacon/ Transceiver which will be part of the Gemini astronauts' survival kit. The all solid-state transmitter provides a minimum of 2 watts average power for 24 hours in the beacon mode and 1.2 watts of average power in the voice mode. The dynamic range of the double conversion superheterodyne receiver permits the radio to communicate with search aircraft at ranges from 50 feet to 25 miles.

The author has been involved with the technical aspects of failure analysis for the past three years. This paper presents a number of typical autopsy analyses which illustrate the techniques which have evolved and examples of electronic part failure causes. The experiences lead to the conclusion that most part failures are the results of defects in design and construction or are the products of human errors in testing. Reliability improvements may be achieved by recognizing these failure causes and adapting appropriate corrective action.

This paper deals with Lockheed Engineering Flight Test experience in the preparation of electromagnetic campatibility test plans on F-104G (MAP) and other later model F-104 aircraft. Literal interpretation of MIL-E-6051C as applied to test plan requirements for various types of electronic and electrical systems is covered. Specifically, the establishment of malfunction criteria for several types of systems including electronic, synchro-type, optical, radar, and pyro-technics are expanded upon. Problems in test plan development encountered for each individual system type are discussed, including how the most critical interference point in a particular system is determined; how a "malfunction" is determined; and how the test plan is prepared from the established information. Lockheed believes that the resulting interference test plans were some of the most comehensive ever written for a modern fighter aircraft. Many useful ideas for EMC test plan preparation may be drawn frcam the information presented.

The Long Island Section of the IRE has attempted to attack the problem of cooperation with the secondary schools in its region in two ways. The first is to supply technical support to the high-school science teacher by direct contact with the student in areas where rapid scientific advances have made specialist knowledge a requirement. The second is towards the provision of a lecture series specifically for the teachers themselves. This paper describes the approach and the results of the first two years of operation of the program.

This paper describes the organization of a Laboratory Electronics Course in the Department of Aircraft Electrical Engineering at the College of Aeronautics, Cranfield, England. The course caters to two standards of specialization and to students with a wide range of previous training. The minor specialization course concentrates solely on fundamentals and the basic concepts, while the major course is carried to the threshold of design procedures. The contents of both courses are limited by the student's previous training and the time available for practical work. The over-all standard of the major course is that of the M.Sc. degree of a British University. Four different ways of construction and presentation of experiments are described and the limitations of each are discussed. Finally, the laboratory layout, equipment, and scheme of work for both courses is described.

This paper is an outgrowth of an investigation to determine how avionic equipment reliability might be improved articularly in view of the experience gained on the ``Minuteman'' high reliability program. The latter program showed that missile electronics reliability could be improved over commercial equipments of similar complexity by several orders of magnitude by emphasis on highly reliable components. No attempt was made to resort to redundancy to obtain reliability with existing components. The basic premise in emphasizing best possible components was that over a period of time, proachhis approach was the only one that was economically feasible. The high cost of unreliability cannot be overstressed, and particularly in view of current cost trends, suggests that this philosophy also makes sense in commercial avionics.

The development of the function-ensemble-average concept of automatic image displacement determination permits a practical realization of terminal guidance for ballistic weapons systems. In this paper the fundamentals of this concept are developed both theoretically and experimentally. Illustrative examples are presented.

For several years, a very intensive program has existed within the connector industry to attempt to define and measure connector reliability. One of the stumbling blocks in the way of this necessary work has been the lack of actual field application data and the correlation of connector failures to such data. Over the eleven months stretching from January, 1962 through November, 1962, the Boeing Airplane Company received reports from major domestic and international carriers having to do with connector problems occurring in the 707 and the 720 Jet Aircraft. Amphenol's engineers, working with the Boeing Reliability people, have correlated report summaries to the extent that they have separated connector categories according to the specific environmental experiences which the connectors have undergone. This has resulted in the establishment of eight different environmental cycle applications, and the data is arranged so as to produce failure rates associated with each. Also, it is possible to compare various types of connectors as to their ability to withstand extreme environmental shocks reliably. The study involves some 173,707 and 720 Aircraft, which are approximately half the entire jet fleet. It involves 437,000 flight hours, 193,000 departures, and approximately 212,000 total connectors. Connector operating hours are in excess of 400,000,000. This paper is considered unique in that, to the best of the author's knowledge, no other such study has ever been attempted in respect to electrical connectors.

The flexibility of the flight director to include practically any all-weather mission is accomplished by the coupling of the basic navigation data to the central flight director computer with special signal-shaping circuits designed on a modular basis. This paper describes the nature of these mission-coupling devices and an extension of their use to improve the basic flight panel information.

This paper is devoted to the mathematical and philosophical development of control laws which form the foundation of a new approach to the control of aircraft in terrain-following and formation-flight modes of operation. The somewhat similar problems of terrain-following and formation flight are attacked thru the solution of the well known Euler-Poisson equation for an applicable definition of an optimal integral error criterion. The approach is compared to past and present methods of control law formulation to perform the tasks of terre. in-following and formation-flight.

This paper is concerned with the problem of obtaining nearly omnidirectional patterns in one plane of large conducting bodies having circular cross sections. To define the problem in terms of discrete sources, calculations were made for typical element patterns F(?') = 1, F(?') = 1 + cos ?', and F(?') = 1 + 1/2 cos ?'. Array circumferences Z? from 20? to 40? were considered for the number of sources S from S = Z/? to S = 1.5Z/?. Several prototype antennas were studied which partially overcome the practical problems of feeding large numbers of discrete sources.

To serve as a general introduction to the theoretical papers immediately following, the analytical techniques available for estimating the backscattering cross section of a metal target are reviewed. These are classified according to the dimension-to-wavelength ranges for which they are appropriate, and an attempt is made to interpret them in the light of the scattering processes involved. Some examples are discussed.

"Integral relay" is a relay concept in which all the aircraft in a control sector that are under the control of an Army flight operations center (FOC) are electronically capable of functioning as relays for communication with aircraft out of direct contact with the FOC. This paper deals with the effectiveness of integral relay operations based on the assumption of random spatial distribution of aircraft. It describes the development of a control sector line-of-sight (LOS) model and of a methodology for effectiveness analysis, and the application of the methodology to one numerical example. It is shown that the LOS conditions in the control sector may be represented by two LOS characteristics which are functions of both aircraft clearance and the terrain and FOC characteristics. Probabilities of direct and indirect (via relay) LOS between the FOC and randomly located aircraft are derived for operations without and with integral relay. The effectiveness, expressed as an increase in LOS probability, is a function of aircraft density and the above two LOS characteristics and is representative of the control sector as a whole. Numerical results are obtained by probability analysis and statistical sampling.

This paper is a report on a joint Bell-Bendix-Decca program to investigate the problems of flying a helicopter in remote areas under instrument flight conditions with presently available machines, the Decca navigator system, and other sensory equipment. The approach and transition phase to a remote landing spot under instrument conditions was of particular interest and present information displays were found to be unsuitable. During the development program a system was built, tested, and demonstrated that would allow complete instrument flight, including precise navigation along any desired flight path and ils type approaches to any desired landing spot in an area covered by the Decca navigation system. The program results clearly indicated that: 1) Flight in remote areas under zero-zero conditions is possible today. 2) The Decca navigation system is an excellent navigation, approach, and landing aid for helicopter instrument flight. 3) Unsatisfactory information displays are most responsible for the limited helicopter instrument flight operations possible today. Research programs to develop integrated displays must be continued.

The paper discusses in summary form the mechanization of the Integrated Helicopter Avionics System (IHAS) on a hybrid computer. A few of the many mathematical models which had to be established to provide a valid analysis of IHAS, and some of the results of this analysis are presented.

This paper describes the development of a failure reporting mechanism specifically tailored for evaluation and maintenance of electronic hardware systems. The mechanism centers around an incident reporting form designed to optimize the human factors attendant to operational reporting on complex, modularized, transistorized and computer oriented systems.

A survey has been made of real-time electronic analog computer (differential analyzer) installations. This survey was conducted (1) so that a directory of the installations could be compiled and (2) so that various data regarding the installations could be made available for analysis. The survey was conducted by a mail questionnaire. Information was obtained regarding size of installation, size of staff, weekly usage of the equipment, age of installation, and availability to outside organizations from 96 installations havig a total of 8,320 computer amplifiers. The results of the survey have been analyzed and are presented in this paper, together with the directory.

Manned spacecraft designed for long lifetime in space impose a unique requirement for inflight maintenance for all vehicle systems. The key factors in implementing onboard maintenance are accessibility to equipment, rapid fault detection and isolation, and modularized equipment packaging using a supply of interchangeable components. This paper discusses the general configuration of the Manned Orbital Research Laboratory (MORL) studied under contract NAS 1-3612, NASA Langley Research Center and also presents in digest form some conceptual maintenance, design and installation approaches.

Oceanographic instrumentation represents one of the most important problems shared by the ocean engineering and marine sciences communities. In comparison with other areas of technology-notably with the aerospace fields-the state-of-the-technology in oceanographic instrumentation is still relatively primitive. Continuation of this situation is intolerable as it produces unreliable data and is wasteful of time, ships, manpower, and money. This paper examines some of the current problems of oceanographic instrumentation as they affect both the collectors and users of data from the marine environment and as they are derived from present policies and procurement practices of the Government agencies which are the major buyers and users. Several recommendations are developed for new policies and action programs by the Federal Government to support the advancement of the state-of-the-technology and improvement in the quality of oceanographic instrumentation that will remove the present constraints to meaningful change in this area.

This paper is concerned with the evolution and evaluation of an integrated electronic display for V/STOL flight. Such design considerations as vehicle dynamics, handling qualities, and mission requirements are discussed. Data are presented on the performance improvements obtained with a representative display when compared with conventional instruments in two simulated tasks.

This paper presents the results of a study conducted to determine the use of a centralized thermoelectric cooling system to provide cooling for military avionic equipment. The system considered is a recirculatory system capable of cooling an avionic equipment compartment or a number of avionic equipment components from the centralized cooler. The results of the study indicate that the system is competitive on a weight basis with respect to contemporary subsonic avionic cooling systems in the range of from 2 to 4 kilowatts cooling capacity and that the system presents many attractive features for avionic equipment cooling.

The pending widespread use planned for PCM telemetry has caused some confusion in the area of PCM or digital standards. It is the purpose of this paper to discuss proposed PCM standards on a realistic basis and to show by example the organization of an integrated digital flight test system using these standards. Consideration is given to the variety of testing applications and ultimate usage of digital flight test data.

The present paper deals primarily with CAA contribution to the art of instrument landing systems and is confined to the localizer and glide-path portions of the system. It describes briefly the present standard 8-loop localizer used at most sites as well as some modifications made in the basic localizer concept in order to adapt it to locations where siting problems exist. It also describes the standard glide slope as well as a new type of glide slope for use at extremely poor locations.

The present manual system of air traffic control is described briefly to provide background material for the reader who is not familiar with existing practice. Then follows an outline of the plans for modernization of our national airways system as set forth in the Curtis Report. The body of this paper deals with the plans of Airways Modernization Board for applying computers to air traffic control in its five-year Phase II program.

Systems for classifying or categorizing areas of science and technology are required, not only for use in information retrieval operations, but also for methods used for R&D project selection and evaluation. This paper describes the background and development of one such system which was devised for information retrieval purposes. Either the system itself, or the methods by which it was devised, may be of use to others facing problems similar to those of the organization for which it was devised.

This paper is concerned with the problem of arraying Yagi disk or disk on rod surface wave structures having large interelement spacings. It is shown that symmetrical arrays having acceptable sidelobe levels (below 13 db) can be designed using simple array theory and the knowledge of a single-element pattern.

This paper reviews some of the earlier developments of civil avionic equipment design specifications, and describes how the U.S. Flag Air Carriers now arrive at procurement specifications, and how they determine their current operational needs. The responsibilities and activities of ATA, ARINC, AEEC, and RTCA are described and related to the development and coordination of such specifications.

The design, fabrication and testing of a 16 × 16 multiplier chip, will be described. The circuit contains 17,000 transistors and resistors on a 301 × 279-mil chip and does a multiplication in less than 350 ns.

With "faster, cheaper, better" pervading the requirements for present spacecraft designs, the Shuttle Small Payloads Project offers unique access to users of the Space Shuttle. "Payloads of Opportunity", such as Hitchhikers, combine for manned spaceflight customers the advantages of ground commanding and telemetry with quick turnaround and low-cost. This paper presents the capabilities of the Hitchhiker carrier systems. It also discusses typical ground integration and mission operations services available to Hitchhiker customers.

The various manufacturing activities nave receivea the primary emphasis curing efforts to improve productivity through automation. Inspection activities, especially electronic module inspection, have received only secondary emphasis. This has resulted in a trend which has developed where the cost of manufacturing an item is decreasing with the cost of inspection rising due to inflationary causes. This trend increases the ratio of the cost of inspection to the cost of manufacturing. Quality Assurance activities must recognize that the cost of inspection is becoming an increasingly significant percentage of unit cost and make a concerted effort to reverse this trend. This paper describes some of the problems we are faced with in Aerospace electronics manufacturing (small lot size, highly complex designs, reliability requirements, personnel requirements) and some of the areas in which we think an optical system may be developed to meet our needs.

This paper discusses the application of introspective testing techniques to in-flight checkout of a postulated manned space vehicle. The advantages of introspective testing techniques are shown through comparisons With other in-flight checkout methods. Finally, the principles of introspective testing as applied to checkout of typical radar and communication subsystems are described.

The B-1B has received a great deal of criticism since it was first fielded in 1985. Much of this criticism, deserved or not, was the result of perceived shortcomings in the avionics system-especially the Defensive Avionics System. These shortcomings were largely the result of software deficiencies, the B-1B is now entering a conventional mission upgrade, which will include replacing some of the computers and modifying some of the software. The challenge for the B-1B Conventional Weapons Team is to manage the risk inherent in this computer upgrade in order to prevent more criticism in the future. This will require a new approach to the way risk has been managed for the B-1B. This paper briefly describes the history of the B-1B's computer hardware and software, risk management techniques used previously on the B-1B program, lessons learned, and risk management plans for the conventional mission upgrade now under way for the B-1B. >

This paper considers the possibility of controlling an artificial upper extremity by a special-purpose computer, where the points that the extremity should reach are given in advance.

This paper discusses concepts for a multifunction avionics system based on the use of accurate synchronixed clocks at each terminal of the system. An experimental program to identify technological barriers and aid in their resolution will be dascribed. This experimental activity involves developent and utilization of a facility known as the Time Ordered Techniques Experimental System (TOTES).