gyros, 4 primary Sun sensors, 2 secondary Sun sensors, and an
Earth sensor. Power was supplied by 9792 Si solar cells contained
in the two solar panels, giving a total array area of 2.3 square
meters and producing 200 W. Two 1200 Watt-hr AgZnO batteries
rated at 26.5 V with a capacity for 9 hours of operation provided
power to each of the separate communication/TV camera chains.
Two 1000 Watt-hr AgZnO batteries stored power for spacecraft
operations. 


Communications were through the quasiomnidirectional low-gain
antenna and the parabolic high-gain antenna. Transmitters aboard
the spacecraft included a 60 W TV channel F at 959.52 MHz, a 60
W TV channel P at 960.05 MHz, and a 3 W transponder channel
8 at 960.58 MHz. The telecommunications equipment converted
the composite video signal from the camera transmitters into an
RF signal for subsequent transmission through the spacecraft high-
gain antenna. Sufficient video bandwidth was provided to allow for
rapid framing sequences of both narrow- and wide-angle television
pictures. 


Ranger 6 was launched into an Earth parking orbit and injected on
a lunar trajectory by a second Agena burn. The midcourse
trajectory correction was accomplished early in the flight by
ground control. On February 2, 1964, 65.5 hours after launch,
Ranger 6 impacted the Moon on the eastern edge of Mare
Tranquillitatis (Sea of Tranquility). The orientation of the spacecraft
to the surface during descent was correct, but no video signal was
received and no camera data obtained. A review board determined
the most likely cause of failure was due to an arc-over in the TV
power system when it inadvertently turned on for 67 seconds
approximately 2 minutes after launch during the period of
booster-engine separation.