Tundra orbit

Groundtrack of QZSS orbit

A Tundra orbit (Russian: Тундра) is a highly elliptical geosynchronous orbit with a high inclination (usually near 63.4°) and an orbital period of one sidereal day (about 4 minutes less than a solar day). A satellite placed in this orbit spends most of its time over a chosen area of the Earth—a phenomenon known as apogee dwell. The ground track of a satellite in a tundra orbit is a closed figure eight.

These orbits are conceptually similar to Molniya orbits, which have the same inclination but half the period (about 12 hours). The only current known users of Tundra orbits are Sirius Satellite Radio and the EKS satellite. The EKS satellite is part of a Russian early warning constellation for missile launches,^[1] while Sirius operates a constellation of three satellites used for satellite radio.^[2] The RAAN and mean anomaly of each satellite is offset by 120 degrees so that when one satellite moves out of position, another has passed perigee and is ready to take over.

Tundra and Molniya orbits are used to provide high latitude users with higher elevation angles than a geostationary orbit. Neither the Tundra nor Molniya orbits are geostationary because that is possible only over the equator, so both orbits are elliptical to reduce the time that the satellite is away from its service area. An argument of perigee of 270 degrees places apogee at the northernmost point of the orbit. An argument of perigee of 90° would likewise serve the high southern latitudes. An argument of perigee of 0° or 180° would cause the satellite to dwell over the equator, but there would be little point to this as this could be better done with a conventional geostationary orbit.

The Tundra and Molniya orbits use a $sin -1 \sqrt 4/5 \approx 63.4°$ inclination to null the secular perturbation of the argument of perigee caused by the Earth's equatorial bulge. With any inclination other than 63.4 degrees or its supplement, 116.6 degrees, the argument of perigee would change steadily over time so that apogee would occur either before or after the highest latitude is reached.

References

Gravitational orbits

Types

General	Box Capture Circular Elliptical / Highly elliptical Escape Graveyard Hyperbolic trajectory Inclined / Non-inclined Osculating Parabolic trajectory Parking Synchronous semi sub Transfer orbit

Geocentric	Geosynchronous Geostationary Sun-synchronous Low Earth Medium Earth High Earth Molniya Near-equatorial Orbit of the Moon Polar Tundra

About other points	Areosynchronous Areostationary Halo Lissajous Lunar Heliocentric Heliosynchronous

Parameters

Shape Size	$e$ Eccentricity $a$ Semi-major axis $b$ Semi-minor axis $Q$ , $q$ Apsides

Orientation	$i$ Inclination $Ω$ Longitude of the ascending node $ω$ Argument of periapsis $ϖ$ Longitude of the periapsis

Position	$M$ Mean anomaly $ν$ True anomaly $E$ Eccentric anomaly $L$ Mean longitude $l$ True longitude

Variation	$T$ Orbital period $n$ Mean motion $v$ Orbital speed $t 0$ Epoch

Maneuvers

Orbital mechanics

List of orbits

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