Ranger 5
Ranger 5
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| Mission type | Lunar impactor |
|---|---|
| Operator | NASA |
| Harvard designation | 1962 Beta Eta 1 |
| COSPAR ID | 1962-055A |
| SATCAT no. | 439 |
| Mission duration | 64 hours |
| Spacecraft properties | |
| Manufacturer | Jet Propulsion Laboratory |
| Launch mass | 342.5 kilograms (755 lb) |
| Power | 135 W |
| Start of mission | |
| Launch date | October 18, 1962, 16:59:00 UTC |
| Rocket | Atlas LV-3 Agena-B |
| Launch site | Cape Canaveral LC-12 |
| Orbital parameters | |
| Reference system | Heliocentric |
| Eccentricity | 0.056 |
| Perihelion | 0,9839 AU |
| Apohelion | 1,163 AU |
| Inclination | 0.44° |
| Period | 370.22 days |
| Lunar flyby (failed impact) | |
| Closest approach | October 21, 1962 |
| Distance | 725 kilometers (450 mi) |
Ranger 5 was a spacecraft of the Ranger program designed to transmit pictures of the lunar surface to Earth stations during a period of 10 minutes of flight prior to impacting on the Moon, to rough-land a seismometer capsule on the Moon, to collect gamma-ray data in flight, to study radar reflectivity of the lunar surface, and to continue testing of the Ranger program for development of lunar and interplanetary spacecraft. Due to an unknown malfunction, the spacecraft ran out of power and ceased operation. It passed within 725 km of the Moon.
Ranger 5 was a Block II Ranger spacecraft similar to Ranger 3 and Ranger 4. The basic vehicle was 3.1 m high and consisted of a lunar capsule covered with a balsawood impact-limiter, 65 cm in diameter, a mono-propellant mid-course motor, a retrorocket with a thrust of 5080 lbf (23 kN), and a gold and chrome plated hexagonal base 1.5 m in diameter. A large high-gain dish antenna was attached to the base. Two wing-like solar panels (5.2 m across) were attached to the base and deployed early in the flight. Power was generated by 8680 solar cells contained in the solar panels which charged an 11.5 kg 1 kWh capacity AgZn launching and backup battery. Spacecraft control was provided by a solid-state digital computer and sequencer and an earth-controlled command system. Attitude control was provided by six Sun and one Earth sensor, gyroscopes, and pitch and roll cold nitrogen gas jets. The telemetry system aboard the spacecraft consisted of two 960 MHz transmitters, one at 3 W power output and the other at 50 mW power output, the high-gain antenna, and an omnidirectional antenna. White paint, gold and chrome plating, and a silvered plastic sheet encasing the retrorocket furnished thermal control.
The experimental apparatus included: (1) a vidicon television camera, which employed a scan mechanism that yielded one complete frame in 10 s; (2) a gamma-ray spectrometer in a 300 mm sphere mounted on a 1.8 m boom; (3) a radar altimeter; and (4) a seismometer to be rough-landed on the lunar surface. The seismometer was encased in the lunar capsule along with an amplifier, a 50 mW transmitter, voltage control, a turnstile antenna, and six silver-cadmium batteries capable of operating the lunar capsule transmitter for 30 days, all designed to land on the Moon at 130 to 160 km/h (80 to 100 mph). The instrument package floated in a layer of freon within the balsawood sphere. The radar altimeter would be used for reflectivity studies, but was also designed to initiate capsule separation and ignite the retro-rocket.
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