 Molniya orbit

For other uses, see Molniya (disambiguation).
Molniya orbit is a type of highly elliptical orbit with an inclination of 63.4 degrees, an argument of perigee of 90 degree and an orbital period of one half of a sidereal day. Molniya orbits are named after a series of Soviet/Russian Molniya (Russian: "Lightning") communications satellites which have been using this type of orbit since the mid 1960s.
A satellite in a highly eccentric orbit spends most of its time in the neighborhood of apogee which for a Molniya orbit is over the northern hemisphere, the subsatellite point at apogee having a latitude of 63.4 degrees North. As the apogee altitude is as high as 40000 km it will therefore, for a considerable period around apogee, have an excellent visibility from the Northern hemisphere, from Russia but also from northern Europe, Greenland and Canada.
To get a continuous high elevation coverage of the northern hemisphere at least three Molniya spacecraft are needed.
The reason why the inclination should have the value 63.4 deg is that then the argument of perigee is not perturbed by the J2 term of the gravitational field of the Earth but stays 90 deg.
Contents
Properties
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 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. In fact, in the period from apogee 3 hours to apogee +3 hours the subsatellite point of the spacecraft is north of latitude 55.5 deg N and the elevation of the spacecraft is over 10 deg from all points north of latitude 54.1 deg N and over 5 deg from all points north of latitude 49.2 deg N.
An additional advantage is that considerably less launch energy is needed to bring a spacecraft into a Molniya orbit than into a geostationary orbit. Disadvantages are that as opposed to a spacecraft in a geostationary orbit the ground station needs a steerable antenna to track the spacecraft and that the spacecraft will pass the Van Allen belt 4 times per day.
It is necessary to have at least three spacecraft if permanent high elevation coverage is needed for a large area like the whole of Russia where some parts are as far south as 45 deg N. If three spacecraft are used each spacecraft is active for periods of 8 hours per orbit centered at apogee as illustrated in figure 9. As the Earth rotates half a revolution in 12 hours every second apogee will serve one half of the northern hemisphere and every second the other half. If for example the apogee longitudes are 90 deg E and 90 deg W this means that every second apogee will serve Europe and Asia (see figures 3 to 5) and every second Northern America (see figures 6 to 8). The orbits of the three spacecraft should then have the same apogee longitudes (for example 90 deg W and 90 deg E) but pass the apogee with 8 hours shift, i.e. the right ascensions of the ascending nodes should be separated with 120 deg. When one spacecraft has reached the point corresponding to figure 5 (or figure 8) 4 hours after apogee passage the next spacecraft having 4 hours left to reach apogee and having a right ascension of ascending node 120 deg larger then the previous spacecraft has the visibility displayed in figure 3 (or figure 6) and the switchover can take place. Note that the two spacecraft at the time of switchover only are separated with about 1500 km and that the ground stations therefore 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 unless constantly corrected with "station keeping" thruster burns. To avoid this expenditure of fuel, the Molniya orbit uses an inclination of 63.4°, for which these perturbations are zero. That this is the case follows from equation (28) of the article Orbital perturbation analysis (spacecraft) as the factor
then is zero.
The reason why the orbital period shall be half a sidereal day is that the geometry relative to the ground stations should repeat every 24 hours keeping the longitudes for the apogees passages. In fact, the precise ideal orbital period resulting in a ground track repeating every 24 hours is not precisely half a sidereal day but rather half a "nodal day"! The J2 term of the gravitational field of the Earth causes secular perturbations of both the right ascension of the ascending node and the argument of perigee , the formulas giving the change per orbital revolution (in radians) being
which are equations (24) and (28) of the article Orbital perturbation analysis (spacecraft)
For a Molniya orbit the inclination is selected such that as given by the formula above is zero but as given by the other equation will be 0.0742 deg per orbit. The rotational period of the Earth relative the node, i.e. the "nodal day", will therefore be only 86129 seconds, 35 seconds less then the sidereal day which is 86164 seconds.
Uses
The primary use of the Molniya orbit was for the communications satellite series of the same name. After two launch failures in 1964, the first successful satellite to use this orbit was Molniya 101 launched on April 23, 1965. The early Molniya1 satellites were used for longrange military communications starting in 1968, but the satellites had a short lifespan and had to be constantly replaced. Its replacement, the Molniya2, 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 Molniya3 design. There is some confusion in the existing sources about the naming, with some sources suggesting that all of the satellites onorbit are of the Molniya3 type, but referred to as Molniya1 through 3 depending on their purpose.
The same orbits, with slight adjustments, were also used by some Soviet spy satellites, with the apogee point over the continental United States. Although geostationary orbits are useful for observing the continental United States, Soviet sensor technology sometimes required highcontrast observing angles which could only be achieved from higher latitudes. One such example is the USKS earlywarning satellite which watches for US missile launches, although improvements in these systems have since allowed them to move these to geostationary orbits.
See also
References
 Orbital Mechanics by Robert A. Braeunig
 Molniya1 spacecraft by Mark Wade of Encyclopedia Astronautica
External links
 JAVA applet animating the orbit of a satellite in an elliptic Kepler orbit around the Earth. For a Molniya orbit, set the semimajor axis to 26562 km and eccentricity to 0.74105.
 Real time satellite tracking for a typical Molniya satellite
 3D Molniya constellation viewer (Java applet)
 illustration of the communication geometry provided by satellites in 12hour Molniya orbits (video)
Categories: Celestial mechanics
 Orbits
 Astrodynamics
 Earth orbits
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