By Topic

Aerospace, IEEE Transactions on

Issue 2 • Date April 1964

Filter Results

Displaying Results 1 - 25 of 132
  • [Front cover]

    Page(s): c1
    Save to Project icon | Request Permissions | PDF file iconPDF (991 KB)  
    Freely Available from IEEE
  • IEEE Professional Technical Group on Aerospace

    Page(s): c2
    Save to Project icon | Request Permissions | PDF file iconPDF (102 KB)  
    Freely Available from IEEE
  • IEEE Transactions on Aerospace - Table of contents

    Page(s): 57
    Save to Project icon | Request Permissions | PDF file iconPDF (33 KB)  
    Freely Available from IEEE
  • From the Editor . . .

    Page(s): 58
    Save to Project icon | Request Permissions | PDF file iconPDF (91 KB)  
    Freely Available from IEEE
  • Professional Technical Group on Aerospace

    Page(s): 59 - 60
    Save to Project icon | Request Permissions | PDF file iconPDF (416 KB)  
    Freely Available from IEEE
  • International Conference & Exhibit on Aerospace Electro-Technology

    Page(s): 61 - 63
    Save to Project icon | Request Permissions | PDF file iconPDF (2781 KB)  
    Freely Available from IEEE
  • Index to the technical papers

    Page(s): 64 - 67
    Save to Project icon | Request Permissions | PDF file iconPDF (624 KB)  
    Freely Available from IEEE
  • A 30 x 5 Microelectronic Commutator

    Page(s): 68 - 73
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (1857 KB)  

    A 30 x 5 microelectronic commutator was designed and constructed for multiplexing sensor signals into an IRIG telemetry format. Logic control and selection are provided by 23 Texas Instruments solid circuits, signal transmission is via diode gates, and power conversion is internal. Dissipation is 1 watt, weight less than 6 ounces, and dimensions are 3 x 2 x 0.9 cubic inches. A complete series of tests was completed for application to the launch and orbit environments of space vehicles. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • Hybrid-Coupled VHF Transistor Power Amplifier

    Page(s): 74 - 78
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (1467 KB)  

    35 w of power was produced at 132 mc using four transistor amplifier modules in the final stage, combined by a hybrid network. The use of the hybrid system permits summing of signals with a high degree of isolation between the amplifier modules. This permits operation of the amplifier modules to their full power capacity without requiring a match of device characteristics or equal power-sharing capabilities. Isolation is also realized with respect to load mis-tuning and greater reliability is achieved. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • An S-Band, Multi-Channel, Phase-Coherent Transponder for the Goddard Range and Range Rate Tracking System

    Page(s): 79 - 86
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (2781 KB)  

    This paper describes an S-band, multi-channel transponder which is utilized in the Goddard Range and Range Rate Tracking System for extremely accurate orbital or trajectory tracking of spacecraft from near-earth to lunar distances. A short general description of the system operation and capabilities will be presented. A detailed definition of the physical and electrical configuration of the transponder plus a discussion of the operating characteristics and design problems will follow. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • Emergency UHF Radio for Gemini Astronauts

    Page(s): 87 - 90
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (1425 KB)  

    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. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • In this issue - Technically

    Page(s): 91 - 95
    Save to Project icon | Request Permissions | PDF file iconPDF (2790 KB)  
    Freely Available from IEEE
  • Minuteman Digital-Data Transmission System Tests

    Page(s): 96 - 102
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (1834 KB)  

    The high operational reliability required of the communications network for the MINUTEMAN launch-control system made it imperative that extensive testing be performed at various levels of development, prior to installation. Meeting this requirement rests on two types of reliability achievement: one comprises the familiar equipment reliability considerations; the other, emphasized in this paper, relates to the reliable generation, transmission, and demodulation (in the presence of interference) of the digital data signals used for command and status functions. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • A Multi-Command Decoder for Satellite Applications

    Page(s): 103 - 109
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (3276 KB)  

    This decoder accepts eight tone frequencies, from which it will produce twenty-one separate outputs. It meets all NASA requirements for address-execute command equipment.' The design and construction of the decoder will be discussed. Several circuit innovations will be described, including a solid state address switch with a slow release feature, a noise immune tone filter, and a novel d-c actuated memory element. Construction features include shock and vibration isolation for sustained operation in a highly adverse environment. Finally, the decoder is light and compact. Together with its companion receiver, the total weight is 2-1/ 2 pounds and the overall size is 43 cubic inches. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • Design and Development Concepts for Very Long Range Spacecraft Command System

    Page(s): 110 - 115
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (2717 KB)  

    During the period from May of 1960 to date a series of flight command subsystems have been designed, developed, built and flown for deep space interplanetary probes.* These subsystems, each consisting of approximately three thousand parts, have achieved a measured mean time to failure in excess of fifty thousand hours. It is felt the techniques used in achieving this high level of reliability are of significance to any persons engaged in the field of Aerospace Technology. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • Satellite Based System for Locating Drifting Sensor Platforms

    Page(s): 116 - 124
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (1463 KB)  

    The problems associated with determining the position of unmanned drifting buoys and constant pressure balloons from a medium. altitude satellite in a near-polar orbit are discussed. A system employing range-only measurements is described, and the errors in the computed position of the sensor platforn as a result of errors in range measurement, uncertainties in knowledge of the satellite ephemeris and the altitude and velocity of the balloon are analyzed. The oceanographic and meteorological operational requirements of this system are briefly discussed and the design implications of these requirements described. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • Control Electronics System for the University of Wisconsin OAO Experiment

    Page(s): 125 - 134
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (2735 KB)  

    This control electronics system provides for remote control programming of variable optics of seven telescopic instruments which form a major payload for the first Orbiting Astronomical Observatory (OAO). Controlled variables include measurement channel gain, viewing angle, collimation, and spectral band. Features of the electronic system include: (1)Selective redundancy of command code bits, use of control modes of operation, and sequence of data readout format. (2) Conversion of the complete system design into qualified hardware consuming less than 8 watts average power. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • The AN/FPS-85 Satellite Tracking Phased Array Radar

    Page(s): 135 - 138
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (2941 KB)  

    The AN/FPS-85 radar system is part of the overall Space Detection and Tracking system of the Air Force. This radar is a phased array system incorporating many advanced techniques. It is completely computer controlled to take advantage of the inertialess scanning beams of the phased array. This paper will discuss techniques being used and show pictures of the installation and hardware. Features include: a. Long Range Detection Capability b. High Transmitted power c. Inertialess Electronic Beam Steering d. Multiple Receiving Beam Capability e. High Reliability f. Extreme Flexibility g. Determination of Target Trajectories and Orbits and Maintenance of Ephemerides on Large Numbers of Satellites. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • Radar System Design for Spacecraft Terminal Control

    Page(s): 139 - 144
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (1089 KB)  

    This paper discusses several radar design considerations for use in the terminal control of manned and unmanned space vehicles of the maneuverable type. The main body of the paper deals with specific areas of radar development resulting from recent work in developing a terminal control system. The radar system discussed uses a transponder on board the vehicle. The transponder receives and transmits PCM commands and flight data in addition to reference pulses for angle and range tracking. The technical areas discussed are reliability of self-acquisition, pulse code modulated (PCM) data transmission, semidigital ranging, and the accuracy of computed radar data. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • An Automatic Sensitivity Time Control System

    Page(s): 145 - 150
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (1545 KB)  

    A completely transistorized automatic sensitivity time control (ASTC) circuit was designed and developed to operate in conjunction with a side-looking airborne radar surveillance set. The ASTC technique is a closed loop system which automatically controls the radar receiver gain vs range function in accordance with the average signal return. The addition of ASTC substantially improved the imagery of a side-looking airborne radar recorded during low altitude flights. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • Post-Detection in the Navy Space Surveillance System

    Page(s): 151 - 159
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (1134 KB)  

    The Naval Space Surveillance System is a multistatic cw radar system using the principle of the radio interferometer. Satellites are located in space by measuring the direction cosines of the reflected radio energy and triangulating from two or more receiving sites. Since the direction cosines are determined by electronically measuring the electrical phase difference between pairs of antennas, it is important to maintain phase coherency between all phase carrying channels as well as minimizing all differential phase shifts throughout the post-detection circuits. Characteristics of post-detection filters and phase measuring circuits are discussed in the light of the undesirable incidental phase changes in the system and those caused by phase-rate (the latter being a function of the satellite's relative speed with respect to the surveillance fence). Sensitivity and system error is examined as the phase signals are traced through wide and narrow band post-detection filters. Some work on the affect of "phase jump" on the system is also considered as simple circuits are stimulated by a sudden change in phase. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • Spatial Coverage of Radar Reflectors

    Page(s): 160 - 165
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (3113 KB)  

    Passive reflectors may be employed to enhance the radar return of a space vehicle for some phases of tracking, as in orbital rendezvous. Contour charts prepared on a suitable base grid provide an objective means of evaluating the spatial coverage of different designs for this application. The superiority of a circular corner reflector over square or triangular designs is demonstrated by plotting their backscattering areas in this manner. Comparison can also be made of altogether different types of reflectors, as illustrated by a jack, which provides very poor return relative to the three types of corners. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • Improved Transistor Low Temperature Gain Characteristic by Driving Point Admittance Specification

    Page(s): 166 - 175
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (990 KB)  

    A technique is presented whereby the temperature gain stability of a cascade of high frequency transistor bandpass amplifiers may be improved by utilizing the intrinsic parameter variations of the transistors. Analysis and supporting empirical evidence is presented which indicates that the temperature coefficient of gain variation is dependent upon the magnitude and phase of the short circuit input driving point admittance Yie.It is shown that cascades of transistors specified in terms Of Yie yield nearly flat low temperature gain characteristics. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • Stored-Program PCM Telemetry Ground Stations ... A New Class of Data Processors

    Page(s): 176 - 186
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (2724 KB)  

    The character of time-multiplexed pulse-code-modulation telemetry data is reviewed here, and requirements for demultiplexing and processing are considered. Salient design features of a high-performance "ground station" are presented. Reasons are given for the use of specialized system elements for recognition of synchronization patterns, tagging of samples with source identifiers, distribution to diverse destinations, and preselection of significant data. With a stored-program PCM ground station playing a major role, total data-system performance is far superior to that which would be obtainable if key functions were assigned to general purpose computers. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.
  • Telemetry Data Reduction for Space Vehicles

    Page(s): 187 - 192
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (1777 KB)  

    Real-time automatic digital data reduction and evaluation have been used at Lockheed Missiles and Space Company for the last year and a half. The advantages of this method over analog-record methods are clearly demonstrated. The computer programming-software is described which controls the system. The operation of the data evaluation system is described and operational data is included. View full abstract»

    Full text access may be available. Click article title to sign in or learn about subscription options.

Aims & Scope

This Transactions ceased publication in 1965. The new retitled publication is IEEE Transactions on Aerospace and Electronic Systems.

Full Aims & Scope