Astronomy:Explorer 15

Explorer 15

Explorer 15 (EPE-C)
Mission type	Space physics
Operator	NASA
Harvard designation	1962 βλ1
COSPAR ID	1962-059A
SATCAT no.	445
Spacecraft properties
Bus	EPE Bus
Launch mass	44.4 kg (98 lb)
Start of mission
Launch date	27 October 1962, 23:17 (1962-10-27UTC23:17) UTC
Rocket	Delta A
Launch site	Cape Canaveral Air Force Station LC-17B
End of mission
Decay date	19 December 1978 (1978-12-20)
Orbital parameters
Reference system	Geocentric
Regime	Highly Elliptical
Eccentricity	0.56183
Perigee altitude	300 km (190 mi)
Apogee altitude	17,438 km (10,835 mi)
Inclination	18°
Period	311.4 minutes
Epoch	27 October 1962
Instruments
Instruments Electron and Proton Solid-State Detectors Directional and Omnidirectional Energetic Protons and Electrons Angular Distribution Proton-Electron Scintillation Detector Fluxgate Magnetometers
Explorers

Explorer 15, also called EPE-C, was an United States satellite launched as part of the Explorers program. Explorer 15 was launched on October 27, at Cape Canaveral Air Force Station , Florida, United States , with a Delta rocket.

Mission

Explorer 15 was a spin-stabilized, solar cell-powered spacecraft instrumented to study the artificial radiation belt produced by the Starfish high-altitude nuclear burst of July 1962. The backup payload for Explorer 14 was modified and used for Explorer 15. The instrumentation included three sets of particle detectors to study both electrons and protons, and a two-axis fluxgate magnetometer to determine magnetic aspect. A 16-channel PFM/PM time-division multiplexed telemeter was used. The time required to sample the 16 channels (one frame period) was 0.323 s. Half of the channels were used to convey eight-level digital information, and the others were used for analog information. During ground processing of the telemetered data, the analog information was digitized with an accuracy of 1/100th of full scale.

One analog channel was subcommutated in a pattern 16 frames long and was used to telemeter spacecraft temperatures, power system voltages, electric currents, etc. A digital solar aspect sensor measured the spin period and phase, digitized to 0.041 s, and the angle between the spin axis and the sun direction to about 3° intervals. During launch the spacecraft failed to despin. The spin rate ranged from 72.9 to 73.2 rpm during the life of the spacecraft. The spin axis pointed at right ascension 80.97° and declination 20.9°.