A Molniya orbit (Russian: Молния, IPA: [ˈmolnʲɪjə] ( listen), "Lightning") is a type of satellite orbit. They are highly elliptical orbits with an inclination of 63.4 degrees, an argument of perigee of 270 degrees and an orbital period of approximately half a sidereal day. The name comes from a series of Soviet/Russian Molniya communications satellites which have been using this type of orbit since the mid-1960s.
The first use of the Molniya orbit was by the communications satellite series of the same name. After two launch failures in 1964, the first successful satellite to use this orbit, Molniya 1-01, launched on April 23, 1965. The early Molniya-1 satellites were primarily used for long-range military communications, but were also fitted with cameras used for weather monitoring and/or assessing clear areas for spy satellites. The original Molniya satellites had a lifespan of approximately 1.5 years, as their orbits were disrupted by perturbations, and they had to be constantly replaced.
Its successor, the Molniya-2, provided both military and civilian broadcasting, and was used to create the Orbita television network, spanning the Soviet Union. These were in turn replaced by the Molniya-3 design, followed by the Mayak and Meridian satellites in 1997 and 2002 respectively.
From 1971, the American Jumpseat and Trumpet satellites were launched into Molniya orbits, and possibly used to strategically intercept soviet communications from the Molniya satellites. Detailed information about both projects remains classified as of 2018.
This was followed by the American SDS constellation, which operates with a mix of Molniya and geostationary orbits. These satellites are used to relay imagery from lower flying satellites back to ground stations in the United States and have been active in some capacity since 1976. A single classified communication satellite launch in 1998 may be related to this constellation.
A Russian satellite constellation called Nord (and later, Tyulpan) was designed to support mobile communications at high latitudes, in a similar manner to the Iridium constellation, but it did not progress past the planning phase.
Much of the area of the former Soviet Union, and Russia in particular, is located at high latitudes. To broadcast to these latitudes from a geostationary orbit (above the Earth's equator) would require considerable power due to the low elevation angles. A satellite in a Molniya orbit is better suited to communications in these regions because it looks directly down on them during large portions of its orbit. With an apogee altitude as high as 40,000 km, and a sub-satellite point of 63.4 degrees north, it spends a considerable portion of its orbit with excellent visibility of the Northern Hemisphere, from the Russian Federation but also from Northern Europe, Greenland and Canada.
While Molniya orbits require considerably less launch energy than geostationary orbits (especially from Russia),, the ground station needs a steerable antenna to track the spacecraft, links must be switched between satellites, the range is varying, there is a greater need for station keeping, and the spacecraft will pass the Van Allen radiation belt four times per day.
A typical Molniya orbit, has:
- Semi-major axis: 26,600 km
- Eccentricity: 0.74
- Inclination: 63.4°
- Argument of perigee: 280°
- Period: 718 minutes
It is necessary to have a constellation of at least three spacecraft for permanent high elevation coverage of a large area, like the whole of Russia where some parts are as far south as 45° N. If three spacecraft are used, each spacecraft is active for periods of eight hours per orbit centered at apogee as illustrated in figure 9.
The Earth completes half a rotation in 12 hours, so the apogees of successive Molniya orbits will alternate between one half of the northern hemisphere and the other. For the original Molniya orbit, this places the apogees over Russia and Canada, but by changing the right ascension of the ascending node this could be varied. For example, if the apogee longitudes are 90° E and 90° W, the apogees will alternately serve Europe and Asia (see figures 3 to 5) and next Northern America (see figures 6 to 8).
The orbits of the three spacecraft should then have the same orbital paramters, but different right ascension of the ascending nodes, with their passes over the apogees (for example 90° W and 90° E) separated by 7.97 hours. Since each satellite has an operational period of 8 hours, when one spacecraft travels four hours after its apogee passage (see figure 5 or figure 8), the next satellite will enter it's operational period. The next satellite will have a view of the earth shown in figure 3 (or figure 6) and the switch-over can take place. Note that the two spacecraft at the time of switch-over are separated about 1500 km, so that the ground stations only have to move the antennas a few degrees to acquire the new spacecraft.
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, according to equation 1, unless constantly corrected with station-keeping thruster burns.
where is the gravitational constant, is the perturbing factor, and is the semi-latus rectum.
To avoid this expenditure of fuel, the Molniya orbit uses an inclination of 63.4°, for which these perturbations are zero. At this inclination the factor is zero, so there is no change in perigee over time.
Since the inclination of a Molniya orbit is set, this perturbation is degrees per orbit. To compensate, the orbital period is adjusted so that the longitude of the apogee changes enough to cancel out this effect.
The eccentricity of the orbit is based on the differences in altitudes of its apogee and perigee. To maximise the amount of time that the satellite spends over the apogee the eccentricity should be as high as possible.
However, the perigee needs to be high enough to keep the satellite above the atmosphere to avoid drag, and the orbital period needs to be approximately half a sidereal day. These two factors constrain the eccentricity, which becomes approximately 0.737.
To track satellites using Molniya orbits, scientists use the SDP4 simplified perturbations model, which calculates the location of a satellite based on orbital shape, drag, radiation, gravitation effects from the sun and moon, and earth resonance terms.
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