The Molniya (Russian: Молния, IPA: [ˈmolnʲɪjə] (listen), "Lightning") series satellites are military and communications satellites launched by the Soviet Union from 1965 to 2004. These satellites use highly eccentric elliptical orbits known as Molniya orbits, which have a long dwell time over high latitudes. They are suited for communications purposes in polar regions, in the same way that geostationary satellites used for equatorial regions.
|Country of origin||Russia|
|Applications||communications and surveillance|
|Design life||1.5 to 5 years|
|Launch mass||1,600 kilograms (3,500 lb)|
|Dimensions||4.4m tall, 1.4m base diameter |
|Power||6 solar panels + batteries |
|First launch||Molniya 1-1, 23 April, 1965 |
|Last launch||Molniya 1-93, 18 February, 2004 |
In the early 1960s, when Europe and America was establishing geostationary communication satellites, the Russians found these orbits unsuitable. They were limited in the amount of rocket power available and it is extremely energy intensive to both launch a satellite to 40,000 km, and change its inclination to be over the equator, especially when launched from Russia. Additionally geostationary satellites give poor coverage in polar regions, which consists of a large portion of Russian territory. As a result, OKB-1 sought a less energy-consuming orbit. Studies found that this could be achieved using a large elliptical orbit, with an apogee over Russian territory. The satellite's name, "quick as lightning", is in reference to the speed with which is passes through the perigee.
The Molniya program was authorized on October 30 1961 and design was handled by OKB-1. They were based on the KAUR-2 satellite bus, with design finishing in 1963. The first launch took place on June 4, 1964 and ended in failure when the 8K78 booster core stage lost thrust 287 seconds into launch due to a jammed servo motor. The next attempt was on August 22 and reached orbit successfully, but the parabolic communications antennas did not properly deploy due to a design flaw in the release mechanism. Publicly referred to as Kosmos 41, it nonetheless operated for nine months. The first operational satellite, Molniya 1-1, was successfully launched on April 23, 1965.
The early Molniya-1 satellites were designed for television, telegraph and telephone across Russa, but they were also fitted with cameras used for weather monitoring, and possibly for assessing clear areas for Zenit spy satellites. The system was operational by 1967, with the construction of the Orbita groundstations.
By the 1970s, the Molniya 1 series (and the upgrade Molniya 1T) was mostly used for military communications, with civilian communications moving to Molniya 2.
In total 94 Molniya 1 series satellites were launched, with the last going up in 2004.
The first Molniya 2 satellites were tested from 1971 with the first operational satellite launching in 1974 from Plesetsk. The used the same satellite bus and basic design as later model Molniya 1 satellites, but with an expanded number of users under the military's Unified System of Satellite Communications (YeSSS) program. Development was difficult because the final satellite bus was unpressurized, changing their selection of radios.
Only seventeen Molniya 2 series satellite were launched, as they were soon superseded by the Molniya 3.
Originally called the Molniya-2M, their development began in 1972, with launches from 1974. They were also based on the KAUR-2 bus, launching solely from Plesetsk. Earlier models were used for civilian communications in a similar orbit, but different purpose, to the military-only Molniya-1 satellites. From 1980s they were used by the military, and by the 1990s they were operated in the same manner as the Molniya 1 satellites.
A total of 53 Molniya 3 series satellites were launched, with the last one going up in 2003.
A typical Molniya series satellite, has:
- Semi-major axis: 26,600 km
- Eccentricity: 0.74
- Inclination: 63.4°
- Argument of perigee: 270°
- Period: 718 minutes
In general, the oblateness of the Earth perturbs the argument of perigee ( ), so that even if the apogee started near the north pole, it would gradually move unless constantly corrected with station-keeping thruster burns. Keeping the dwell point over Russia, and useful for communications necessitated without excessive fuel use meant that the satellites needed an inclination of 63.4°, for which these perturbations are zero.
To maximise the dwell time the eccentricity, the differences in altitudes of the apogee and perigee, had to be large.
However, the perigee needed to be far enough above the atmosphere to avoid drag, and the orbital period needed to be approximately half a sidereal day. These two factors constrained the eccentricity to become approximately 0.737.
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