Vanguard (20in Cloud cover #1) |
USA |
Spacecraft n°: 24 |
USA satellite n°: 19 |
Launch data:
Designation | F00041 / 58F16 |
Launch date | 26 Sep 1958 - 15:38 UT |
Launch site | CC, LC18A |
Launch vehicle |
Vanguard SLV-3 |
Mission | Cloud cover satellite |
Perigee / Apogee | km |
Inclination | ° |
Period | min |
Launch Failure.
The second stage produced low thrust only, and not enough to provide the required velocity. The third stage fired, and the satellite made slightly less than one orbit of the Earth.
Spacecraft data:
Prime contractor | |
CustomerOperatorPlatform | |
Mass at launch | kg |
Dry Mass | kg |
Basic shape | Magnesium sphere |
Dimension | 50,8 cm dia |
Solar array | |
Stabilization | spin stabilized at 50 rpm |
DC power | |
Decay | 26 Sep 1958 |
Mission details:
Vanguard SLV-3 and Vanguard 2 were earth-orbiting satellites designed to
measure cloud-cover distribution over the daylight portion of its orbit. The
spacecraft was a magnesium sphere 50.8 cm in diameter. It contained two optical
telescopes with two photocells. The sphere was internally gold-plated and
externally covered with an aluminum deposit coated with silicon oxide of
sufficient thickness to provide thermal control for the instrumentation. Radio
communication was provided by a 1 W, 108.03 MHz telemetry transmitter and a 10
mW, 108 MHz beacon transmitter that sent a continuous signal for tracking
purposes. A command receiver was used to activate a tape recorder that relayed
telescope experiment data to the telemetry transmitter. Both transmitters
functioned normally for 19 days. The satellite was spin stabilized at 50 rpm,
but telemetry data were poor because of an unsatisfactory orientation of the
spin axis. The power supply for the instrumentation was provided by mercury
batteries.
Ref.: #7, #14, #102 - update: 2.07.05
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