In addition, the spacecraft was designed to provide data on the effects of the space environment on the operation of capacitor penetration detectors and solar cell power supplies.

The spacecraft mass, neglecting the fourth stage vehicle hardware and motor, was 133.8 kg (295 lb).

Prior to liftoff, all detectors were functioning properly; however, on the first interrogation made shortly after fourth stage burnout, it was found that the CdS cells were saturated with light.

Apparently the aluminized PET film covers were damaged during launch, preventing data acquisition.

[4] The purpose of the experiment was to determine whether the space radiation environment had any adverse effects on the operation of the capacitor as a meteoroid-penetration detector.

Observations in the laboratory indicated that energetic electrons in space might collect in the dielectric and produce false penetration counts.

The instrumentation consisted essentially of two capacitors made up of a thin film polymer dielectric (bilaminate 3.8-micron thick, half-hard, type 302), which served as one electrode.

A copper layer, about 0.65-micron thick, was vacuum-deposited on the outer surface of the dielectric, thus permitting it to serve as the second electrode.

The foam support, in turn, was seated in a laminated fiberglass tray that served as the mounting fixture.

[5] The mass distribution of meteoroids in space was determined by an impact-detection system consisting of 24 triangular 0.13-cm-thick 6061 aluminium alloy sounding boards.