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Luna Ye-8-LS

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Ye-8 Lunar Lander Ye-8 robot lunar soil return spacecraft.

AKA: Ye-8-LS. Status: Operational 1971. First Launch: 1971-09-28. Last Launch: 1974-05-29. Number: 2 . Gross mass: 5,820 kg (12,830 lb).

Photo Gallery

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Luna Ye-8LS Credit: Manufacturer Image

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• Luna 19 - . Payload: Ye-8-LS s/n 202. Mass: 5,810 kg (12,800 lb). Nation: Russia. Agency: MOM. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft Bus: Luna Ye-8. Spacecraft: Luna Ye-8-LS. USAF Sat Cat: 5488 . COSPAR: 1971-082A. Apogee: 140 km (80 mi). Perigee: 140 km (80 mi). Inclination: 40.60 deg. Period: 121.75 min.

  Heavy lunar Orbiter; conducted lunar surface mapping. Luna 19 entered an intermediate earth parking orbit and was then put on a translunar trajectory by the Proton Block D stage. It entered lunar orbit on October 3, 1971. Luna 19 extended the systematic study of lunar gravitational fields and location of mascons (mass concentrations). It also studied the lunar radiation environment, the gamma-active lunar surface, and the solar wind. Photographic coverage via a television system was also obtained. Parameters are for lunar orbit.

• Luna 22 - . Payload: Ye-8-LS s/n 206. Mass: 5,835 kg (12,863 lb). Nation: Russia. Agency: MOM. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft Bus: Luna Ye-8. Spacecraft: Luna Ye-8-LS. Decay Date: 1975-12-31 . USAF Sat Cat: 7315 . COSPAR: 1974-037A. Apogee: 220 km (130 mi). Perigee: 220 km (130 mi). Inclination: 19.60 deg. Period: 130.00 min.

  Heavy lunar orbiter. Scientific investigation of the moon and circumlunar space from the orbit of an artificial satellite of the Moon, which was begun by the Luna 19 automatic station. The spacecraft carried imaging cameras and also had the objectives of studying the Moon's magnetic field, surface gamma ray emissions and composition of lunar surface rocks, and the gravitational field, as well as micrometeoroids and cosmic rays. Luna 22 braked into a circular lunar orbit on 2 June 1974. The spacecraft made many orbit adjustments over its 18 month lifetime in order to optimise the operation of various experiments, lowering the perilune to as low as 25 km. Manoeuvring fuel was exhausted on 2 September and the mission was ended in early November. Parameters are for lunar orbit.