ATS 1 (Applications Technology Satellite) was designed and launched for the purpose of
(1) testing new concepts in spacecraft design, propulsion, and stabilization, (2)
collecting high-quality cloudcover pictures and relaying processed meteorological data via
an earth-synchronous satellite, (3) providing in situ measurements of the aerospace
environment, and (4) testing improved communication systems. The spin-stabilized
spacecraft was cylindrically shaped and measured 135 cm long and 142 cm in diameter. The
primary structural members were a honeycombed equipment shelf and thrust tube. Support
rods extended radially outward from the thrust tube. Solar panels were affixed to the
support rods and formed the outer walls of the spacecraft. Equipment components and
payload were mounted in the annular space between the thrust tube and solar panels. In
addition to solar panels, the spacecraft was equipped with two rechargeable nickel-cadmium
batteries to provide electrical power. Eight 150 cm-long VHF experiment whip antennas were
mounted around the aft end of the spacecraft, while eight telemetry and command antennas
were placed on the forward end. Spacecraft guidance and orbital corrections were
accomplished by 2.3 kg hydrogen peroxide and hydrazine thrusters, which were activated by
ground command. The satellite was initially placed at 151.16 deg W longitude over the
Pacific Ocean in a geosynchronous orbit. In general, most of the experiments were
successful. Data coverage was nominal until about 1970, after which limited real-time data
acquisition was carried out by NOAA until the May 1974 launch of SMS 1. Limited ATS 1 data
acquisition was begun by NASA at about that time for ATS 1 - ATS 6
correlative studies. The spacecraft has served as a communications satellite for a number
of state, federal, and public organizations up to the present. It is planned to continue
operations at its final longitude of 164 deg E until September 1983 and then move the
spacecraft out of the geostationary orbit.
ATS 3 (Applications Technology Satellite) was one of a series of spacecraft designed to
demonstrate the utility and feasibility of a variety of technological and scientific
activities that could be carried out by an earth-synchronous spacecraft. Of the 11
experiments on board, 8 were technological engineering experiments concerned with
navigation, communications, and spacecraft operation and equipment. Two of the remaining
experiments were photographic imaging experiments that could produce near real-time
daylight pictures of the earth-atmosphere system. The remaining experiment was an
ionospheric beacon. The spin-stabilized spacecraft was cylindrically shaped and measured
180 cm in length and 142 cm in diameter. The primary structural members were a honeycombed
equipment shelf and thrust tube. Support rods extended radially outward from the thrust
tube and were affixed to solar panels which formed the outer walls of the spacecraft.
Equipment components and payload were mounted in the annular space between the thrust tube
and solar panels. In addition to solar panels, the spacecraft was equipped with two
rechargeable nickel-cadmium batteries to provide electrical power. Eight 150-cm VHF
experiment whip antennae were mounted around the aft end of the spacecraft, while eight
telemetry and command whip antennae were placed on the forward end. Spacecraft guidance
and orbital corrections were accomplished by 2.3 kg hydrogen peroxide and hydrazine
thrusters, which were activated by ground command. Initially placed at 48 deg W longitude
over the Atlantic Ocean in a geosynchronous orbit, the satellite position later varied
between 45 and 95 deg W longitude in support of meteorological operations. In general, the
various experiments have been successful.
The proposed ATS C2 spacecraft was the back-up from ATS 1. The flight only reached the
proposal stage and was never approved.