The 102-cm Far Infrared Telescope was one of the most sensitive and versatile balloon-borne instruments ever used for observations in the far-infrared region of the spectrum (40 ~ 250 µm), producing high resolution maps of large sky areas including molecular clouds, dark cloud complexes, planets, asteroids, and leading to the discovery of many new IR sources. At left can be seen a picture of it during preparations for a flight (click to enlarge).
The gondola was designed and constructed by the Solar Satellite Engineering Group, of the Harvard College Observatory while the University of Arizona contributed the primary and secondary mirrors and the infrared detectors. The core of the instrument was a Cassegrain telescope composed by a spherical primary mirror measuring 102 cm of diameter, constructed of Tenzalloy (an aluminum alloy) along with a 18-cm secondary mirror, made of Pyrex, and figured to match the primary mirror. The Cassegrain focus occured behind the primary mirror where the infrared beam was reflected by a dichroic beam splitter that passed visible light. A second beam splitter directed half the optical light onto an N-slit mask at a second focal plane. Light passing through the mask was focused onto a photomultiplier tube. The secondary mirror was mounted by means of a central bolt to a solenoid-driven chopper mechanism further mounted on a commandable-focus drive, which made the mirror to oscillate in the azimuthal direction. The whole secondary system was supported by four sheet-metal spiders to the external support ring and then through conventional tubular trusses to the central telescope ring.
The telescope was mounted in a rectangular aluminum-frame gondola 5.1 m high and 3.4 X 2.9 m wide. Heavy structural elements were used throughout the central portion of the gondola to maintain the integrity of the telescope tube, the elevation and azimuth axes, and the payload electronics. The instrument was stabilized and pointed by means of positional servo controls on the elevation and azimuth axes. The entire gondola moved in azimuth, but the telescope motion in the elevation direction was with respect to the gondola frame. The driving element for each axis was a DC torque motor mounted directly on the axis without gearing. In elevation, the reaction mass was the main frame of the suspended gondola. Reaction forces for the azimuth position control were provided by a large reaction wheel mounted on the gondola center line below the telescope. Also to control the reaction-wheel speed and to isolate the gondola from balloon rotations the system used a "momentum dump" device. The main power for the payload was supplied by silver zinc batteries pack. The entire system weighted approximately 1814 kg.
Positioning the telescope optical line of sight was accomplished in two modes: first, an acquisition mode, determined with respect to the horizontal component of the earth's magnetic field in azimuth and with respect to the local vertical in elevation; and second, an inertial mode, determined by a two-axis gyroscope system mounted on the telescope tube, that gave stability in inertial space. For the acquisition mode, a null magnetometer was mounted on a table and servo-driven in azimuth so as to remain fixed to local magnetic north. The N-slit photometer, was used also for fine-position determination of the telescope. As Stars transited across the three branches of the N mask, this information was telemetered to the ground, indicating with high precision the elevation and azimuth of the optical object with respect to the star field during scanning activities.
For postflight pointing verification a 35-mm-sequence camera was mounted on the telescope, with a field of view of about 15º. It took images of stars and recorded a projected reticle pattern, along with data indicating frame number, time, and status of the payload. It could be commanded from the ground, or automatically triggered during scanning. In the event of failure of one or more major systems in the primary operation of the telescope pointing, -something that occured in the first flights- a simple backup control system was available to be activated by tone commands. This system served two functions: automatic stow and crude pointing control of the telescope in azimuth and elevation.
The infrared detection system used on the focal plane of the instrument in the firsts flights consisted of four gallium-doped germanium bolometers, cooled to 1.8 degrees Kelvin in a liquid helium dewar vented to ambient atmospheric pressure. The cooled optics, consisted of a sandwich of 0.86 mm crystalline quartz and 1 mm calcium flouride. During the entire duration of the program another five instruments have been flown at the focal plane of the telescope, broadening the scope of research and increasing the amount of institutions that benefited of the use of the platform. These included a Single-beam, four-color infrared photometer developed by the University of Palermo, Italy, a Ge:Ga photoconductor broadband photometer developed by the Smithsonian Institution and the Naval Research Laboratory, a Scanning Fabry-Perot Interferometer developed by the Service d'Aeronomie, C.N.R.S., France, FIRS-1 a Far-infrared Michelson interferometer developed by the Smithsonian Astrophysical Observatory and a far-infrared a Fabry-Perot interferometer and grating spectrometer developed by the University College London, England.
Althought no serious incidents occured during the two decades that the program lasted at some point the gondola, associated electronics and wiring started to be too unreliable in later stages. Funds were requested from NASA for a complete refurbishment of the instrument, but the upgraded never materialized and rather than risk a failure, after nineteen flights the program was terminated in 1989 and the platform was put in storage. In 1996 the Smithsonian Astrophysical Observatory transfered the gondola to the National Air and Space Museum in Washington, D.C. where several components of it are in display. As inheritance, the innovative design of the gondola was taken by three different scientific groups whom further developed the concept in brand new instruments for astronomical and astrophysical research.
Balloon launched on: 7/8/1982 at 00:23 utc
Launch site: Columbia Scientific Balloon Facility, Palestine, Texas, US
Balloon launched by: National Scientific Balloon Facility (NSBF)
Balloon manufacturer/size/composition: Zero Pressure Balloon Raven 195.387 m3 (17.78 Microns - X-124) / N15SI-7/10/10T-6.90
Balloon serial number: R6.90-2-101
Flight identification number: 1294P
End of flight (L for landing time, W for last contact, otherwise termination time): 7/8/1982 at 8:35 utc
Balloon flight duration (F: time at float only, otherwise total flight time in d:days / h:hours or m:minutes - ): F 8 h 50 m
Landing site: 10 miles NNE of Lampasas, Texas, US
Payload weight: 2438 Kgs.
This was the seventeenth flight of the program. In the previous months before the flight, several modifications were made to the payload: microprocessor monitoring and control of the telescope and supporting systems, replacement of electronic circuits and connectors, redesign and rebuilding of the momentum dump system, upgrading of the ground support equipment, and the addition of two new broadband photometers with significant increase in sensitivity.
At the focal plane of the instrument was located the broadband photometer developed by the Smithsonian Institution and the Naval Research Laboratory. It consisted of a four-element broadband far-infrared (40-120 µm) detector system using Ge:Ga photoconductors. The four detectors were arranged in a linear array, with three of them subtending an angle of 1.5 arcmin in elevation and 1.0 arcmin in azimuth. The fourth detector was 30 arcsec square. Reflecting optics were used and the detectors were mounted in spherical cavities. The filters consisted of calcium fluoride and quartz with a polyethylene window. The filters had antireflection coatings and diamond dust on one side. The detectors and filters were mounted in a Model HD-3 helium dewar.
The balloon was launched succesfully but a leak appeared in the balloon during ascent and the altitude of the balloon never exceeded 72,000 ft., considerably below the planned altitude of 95,000 ft. After approximately six hours the flight was automatically terminated at 65,000 ft. Although the photometer sensitivities were considerably reduced by the higher pressure, the scientific team proceeded to observe anyway, primarily to calibrate the two new photometers. Not only was the calibration of both photometers achieved with observations of Mars, but the scientists were able to observe two star-formation regions: the supernova-molecular cloud interface region W28, and the HII region G347.2+0.2.
If you consider that this website is interesting or useful, you can help to keep it running with just the equivalent of the price of a cup of coffee. Click on the button on the right for more information.