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An exposed four element array of 12.8 m diameter elements mounted on a common pedestal is the recommended ground antenna configuration in support of the 2 GHz bandwidth Ku-band downlink from tdr satellites. The array provides three channel phase monopulse tracking capability with only listening feeds in each element. The array is as cost effective as a single aperture antenna and offers significant advantages in tracking and reliability.
Digital techniques are discussed for application to the servo and control systems of large antennas. The tracking loop for an antenna at a STADAN tracking site is illustrated. The augmentation mode is also considered.
A matched pair of VHF (220-260 MHz) conical spiral antennas for use in a rocket-tracking interferometer array was designed and tested. While gain, bandwidth, impedance, and pattern measurements met specifications, the phase match between antennas at low elevations was not equal to the design goal.
The layout of a technology base is reported from which a mechanically gimballed, directional antenna can be developed to support a manned space station proposed for the late 1970's. The effort includes the concept definition for the antenna assembly, an evaluation of available technology, the design of critical subassemblies and the design of critical subassembly tests.
Discussion of the present state of the art of low-noise antennas, and speculation about some future achievements that can be anticipated in the light of present trends. Attention is focused on major means of generating side lobes and techniques that may be used to obtain improved side lobe performance. Antennas with no side lobes are also considered.
Antenna could be used in any application where increased ultrahigh frequency beamwidth is desired. Possible applications include aircraft, communication links, ground omniranges, and satellites. It is also possible that antenna could be adapted for use in television transmission and receiving.
Series of plots must be made of antenna pattern on polar-coordinate sheet depicting vertical planes. Separate sheets are plotted depicting antenna patterns in vertical plane at azimuth positions. After all polar plots are drawn, they are labeled according to their azimuthal positions. Transparencies are then stiffened with regular wire, cardboard, or molded plastic.
An attempt was made to determine the cause of antenna tracking interruptions during Apollo 14 and Apollo 15 missions prior to powered descent, and after ascent from the lunar surface but before rendezvous. Probable causes examined include: (1) amplitude modulation on the uplink radio frequency carrier, (2) noise capacitively or inductively coupled into the track error line, and (3) hardware problems resulting in tracking loop instabilities. It was determined that amplitude modulation caused the antenna oscillations. The corrective procedures taken are given.
A phase control coupling circuit for use with a phased array antenna is described. The coupling circuit includes a combining circuit which is coupled to a transmission line, a frequency multiplier circuit which is coupled to the combining circuit, and a recombining circuit which is coupled between the frequency multiplier circuit and phased array antenna elements. In a doubler embodiment, the frequency multiplier circuit comprises frequency doublers and the combining and recombining circuits comprise four-port hybrid power dividers. In a generalized embodiment, the multiplier circuit comprises frequency multiplier elements which multiply to the Nth power, the combining circuit comprises four-part hybrid power dividers, and the recombinding circuit comprises summing circuits.
An antenna capable of deriving several beams about a single boresight axis including a focusing means, such as a parabolic reflector or a lens is described. Plural arrays, each including plural radially aligned antenna elements extending from the boresight axis, are located in proximity to a focal point for the focusing means. The elements of the plural arrays are independently excited as each of the arrays is independently rotated about the boresignt axis.
Recent activities at JPL directed toward the development of large furlable spacecraft antennas using conical main reflectors are described. Development of two basic antenna configurations conceived at JPL and utilizing conical main reflectors was pursued. A 4.3-m (14-ft)-diameter model based on the two-reflection conical-Gregorian concept and a 1.8-m (6-ft)-diameter model based on the four-reflection Quadreflex concept have been made and RF-tested. RF gain measurements for the 4.3-m (14-ft)-diameter conical-Gregorian model were 48.83 db at X-band (8.448 GHz) and 37.82 db at S-band (2.297 GHz). These gains correspond to efficiencies of 53.6 and 57.5%, respectively. RF gain measurements for the 1.8-m (6-ft)-diameter Quadreflex model were 47.59 db at Ku-band (16.33 GHz) and 41.30 db at X-band (8.448 GHz), corresponding to efficiencies of 58.6 and 51.5%, respectively.
A lightweight small high gain antenna which is capable of being packaged in a collapsed form and automatically expanded when in use is described. The antenna includes a cylindrical housing having a rod with a piston adjacent to one end extending through it. Attached to the outer end of the rod in a normally collapsed state is a helical wire coil. When the gas producing means is activated the piston and rod are shifted outwardly to expand the wire coil. A latch is provided for holding the helical coil in the expanded position.
The research performed and the data obtained on candidate space shuttle antenna window and heat shield materials are presented. The measurement technique employs a free-space focused beam microwave bridge for obtaining RF transmission data, and a device which rotates a sample holder which is heated on one side by natural gas-air flames. The surface temperature of each sample is monitored by IR pyrometry; embedded and rear surface thermocouples are also used in obtaining temperature data. The surface of the sample undergoing test is subjected to approximately the same temperature/time profile that occurs at a proposed antenna position on the space shuttle as it re-enters. The samples are cycled through ten of these temperature profiles to determine the recycling effects. Very little change was noted in the materials due to the recycling.
Based upon a boundary-value formulation, a new approximate expression is derived for the total axial current on an infinite antenna immersed in an unbounded, cold, collisional magnetoplasma with a dc magnetic field oriented parallel to the antenna. Numerical results are presented for the current distributions over plasma parameters corresponding to each of the eight regions of the Clemmow-Mullaly-Allis diagram and for different values of the collision frequency.
The electrical properties of the lunar surface in the area of the Apollo 17 landing site were recently studied by the use of electromagnetic sounding techniques. The Apollo 17 Surface Electrical Properties Experiment was different from most other electromagnetic investigations of the lunar surface in that both the transmitting and receiving equipment was located directly on the lunar surface. The use of such inplace measurements of the electrical properties of the lunar surface is significant in that the exact structure and density of the soil contributes largely to the total electrical model of the moon. This paper will be concerned with a discussion of the transmitter antenna design problems for the Surface Electrical Properties Experiment as well as what is indicated by the returned lunar data about the transmitter antenna performance during the Apollo 17 mission.
The corrugated horn is discussed as is a valuable tool for use in microwave pattern ranges. It has the properties of concentrated energy in the main beam, low backlobes, high efficiency, almost monotonic amplitude, and phase radiation patterns which make the corrugated horn useful for a source antenna in a pattern range and also as a possible standard antenna for calibration purposes.
The microwave radiation hazards associated with the use of large antennas become increasingly more dangerous to personnel as the transmitters go to ever higher powers. The near-field area is of the greatest concern. It has spill over from subreflector and reflections from nearby objects. Centimeter waves meeting in phase will reinforce each other and create hot spots of microwave energy. This has been measured in front of and around several 26-meter antennas. Hot spots have been found and are going to be the determining factor in delineating safe areas for personnel to work. Better techniques and instruments to measure these fields are needed for the evaluation of hazard areas.
This is a survey paper wherein phased array antenna systems, now operating on spacecraft, are reviewed so as to reveal their basic techniques of beam formation, steering, and receive/transmit (transponder) functions. Laboratory developmental antennas, designed for ultimate spacecraft flight qualification, are assessed in terms of the needs of communications, earth resources instrumentation, and area surveillance.