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Even during the busiest times of my life I have endeavored to maintain some form of model building activity. This site has been created to help me chronicle my journey through a lifelong involvement in model aviation, which all began in Mayo, MD ... |
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Radio Measurements in Space
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May 1967 Electronics World
[Table of Contents]People old and young enjoy waxing nostalgic about and learning some of the history of early electronics. Electronics World was published from May 1959 through December 1971. As time permits, I will be glad to scan articles for you. All copyrights (if any) are hereby acknowledged. The next thing that happened was that I was reminded of how images such as the op-art tracing of antenna oscillation that are routinely generated today by sophisticated software, required huge amounts of setup time and trials to yield just a single useful and meaningful image using actual hardware. The third thing was, wow, 1967 was 45 years ago, and that was nine years after I was born. Ouch. Radio Measurements in SpaceBy Joseph H. Wujek, Jr.Scheduled for an early launch is a satellite to be used for radio astronomy purposes only. An array of space antennas having 750-foot elements will be used. 
 Scale model of the Radio Astronomy Explorer satellite, world's first satellite devoted exclusively to radio astronomy.  Fig. 1. Graph of noise from solar activity at 2.8 GHz showing the last complete eleven-year cycle. Right now solar activity is on upswing and new peak should occur around 1969.  Fig. 2. The STEM (Storable Tubular Extendable Member) principle.  Fig. 3. The principles of gravity gradient stabilization. The science of radio astronomy has also benefited from space r.f. measurements. It has been known for some time that stars, galaxies, and some planets emanate EM waves. The star nearest earth, our sun, exhibits increased flare, or sunspot activity, on a somewhat regular basis. In particular, the occurrence of these flares increases to a maximum every eleven years (Fig. 1). Radio communications in cer-tain frequency bands are severely affected during such in-creased solar activity. By studying the nature of the r.f. emanations of the sun and other stars, scientists are able to better understand the energy processes which occur in these bodies. The solar flares, which are believed to be reactions similar to those of a fusion or hydrogen bomb, release enormous amounts of energy. Swarms of charged particles and EM waves are discharged from these reactions. The earth is about 93 million miles or 8 light-minutes from the sun, yet some of these particles and waves find their way through the atmosphere and ultimately reach the earth. In an earlier article ("Radiation Measurements in Space", August 1966) we showed how energetic particles are detected and measured. Here we will discuss systems used to measure r.f. energy in space. Space Radiometry Instruments used to measure radiation in the EM spectrum are called "radiometers". Many different kinds of radiometers exist; the type used will depend on the portion of the spectrum to be measured. In this article we shall be concerned only with radio-frequency systems. Radiometers have been used in space experiments from the very beginnings of space exploration. These systems generally consist of an antenna, an amplifier, and a telemetry readout system. The amplifiers are usually of the frequency-selective variety so as to amplify and pass only those frequencies of interest, while all other frequencies are rejected. Some systems use several amplifiers and/or antennas which are shared by means of automatic switching controlled by a programmer subsystem. Ground commands may also be used to select a particular channel when the payload is traversing a given region of space. As in the case of ground-based systems, antenna design depends on the range of signal frequencies to be gathered. Space radiometers have been developed which have input sensitivities as low as 0.1 microvolt per meter. For some perspective, remember that in order to obtain a good-quality TV picture on most commercial receivers, a signal strength of 100 microvolts per meter is required with a signal-to-noise ratio of at least 30 dB. Space systems can yield higher sensitivities because they are far removed from high-level man-made signals and interference. These higher sensitivities cannot, in general, be verified experimentally in the laboratory due to the high level of surrounding interference. Radio Astronomy Explorer Satellites The first Radio Astronomy Explorer (RAE) satellite has been tentatively scheduled for launch this year. This will mark the first time a satellite has been designed and developed for radio astronomy purposes exclusively. Due to be another first in space technology is the array of antennas, each of which is 750 feet in length. These antennas were first developed by The de Havilland Aircraft of Canada, Limited. In addition to functioning as antennas, the long tubular sections provide gravity gradient stabilization of the spacecraft. The principle by which these rods are fabricated is designated STEM, from the name Storable Tubular Extendable Member. STEM devices have been used successfully on such space missions as Gemini (16-foot antenna), the Canadian Topside satellite (60-foot antennas), and the TRAAC satellite (60-foot gravity stabilizing boom). br> The STEM device consists of a strip of thin material, usually stainless steel or beryllium-copper alloy, which has been preformed to a tubular configuration. The strip is then wound on a drum or compressed in telescope fashion into a canister. In the case of the longer element lengths, a drive motor rotates the drum to unfurl the STEM device (Fig. 2). The canister-version boom is expanded by removing the canister lid, resulting in a jack-in-the-box unfurling. An explosive bolt or squib is usually detonated by an electrical signal to shear a pin or latch and thus open the canister. While the principles of antennas are familiar to all of us, the notion of gravity gradient stabilization is perhaps not so familiar. The physics involved here is not too different from the tightrope walker who carries a long pole for balance. In the case of spacecraft stabilization, the small difference in gravity over the length of the rod produces a torque which tends to align the rod parallel to the gravitational field, as shown in Fig. 3. The addition of more long rods to the spacecraft produces more torque which yields a spacecraft attitude which is stable with respect to earth. Because of the great length and thin walls of STEM devices, several problems appear with their use. The vacuum of space is a cold void except when matter is present to be heated by the sun's radiations. As a result, that side of the STEM device which faces the sun is much warmer than the side which looks away from the sun. Due to contraction and expansion of materials with heating, the element tends to bend under these temperature conditions. Thus, the tip of such an element of 300-foot length, with 1/2-inch diameter and 0.002-inch walls, may deflect more than 100 feet. The deflection may be reduced by using thicker walls in the tubing, but if this is done, weight is also increased - which is a great disadvantage in a good many space applications. Testing of long STEM devices is also a problem since a low-gravity environment is required. This is particularly a problem for the longer elements. How does one create a low-gravity, high-vacuum, sun-simulating environment for testing? The mechanical forces which act during unfurling are quite complicated and testing is demanded. Engineers at NASA's Goddard Space Flight Center have provided at least a partial solution by using cameras and photographing the trace created by a small lamp attached to the tip of the antenna. Some very interesting light patterns are produced during such tests. One of these is illustrated in the lead photograph on page 46. The RAE will probably be assigned a three-stage improved Delta launch vehicle with an over-all length of 91 feet. The first stage Thor rocket develops 346,000 pounds of thrust. Recall that jet engines, as used in commercial transports today, typically develop 16,000 pounds of thrust. The second stage develops approximately 7000 pounds of thrust, with the third stage (which carries the spacecraft) producing about 2000 pounds thrust. It is anticipated that an orbital altitude of about 300 kilometers (186 miles) will be used. The RAE Mission The mission of the RAE satellite may be categorized by five scientific objectives. 1. To observe low-frequency radio storms on earth. These storms are believed to be interactions between particles emanating from the sun and earth's radiation belts. 2. To monitor large radio noise sources, such as the constellation Centaurus A. 3. To study Jupiter, which is the only planet other than the earth which is known to occasionally emit low-frequency noise bursts. 4. To obtain an EM map of our galaxy (the Milky Way) in the frequency range from 400 kHz to 10 MHz. 5. To gather data on low-frequency bursts of EM energy which emanate from the sun. This data should provide added insight into the nature of the sun's reactions. IIn order to achieve orbit and deploy the four 750-foot antennas, a sequence which will require about two weeks will be initiated by ground command from Goddard Space Flight Center, Greenbelt, Maryland. The data gathered by RAE satellites and their successors may provide space scientists with enough information to formulate new theories concerning the earth and its surroundings.
Posted February 16, 2012 |
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