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Extra-close oppositions of Mars happen every 15 to 17 years, when we pass between Mars and the Sun around the time of its perihelion (closest point to the Sun in orbit). The minimum distance between Earth and Mars has been declining over the years, and in 2003 the minimum distance was 55.76 million km, nearer than any such encounter in almost ...
The Mars time of noon is 12:00 which is in Earth time 12 hours and 20 minutes after midnight. For the Mars Pathfinder, Mars Exploration Rover (MER), Phoenix, and Mars Science Laboratory missions, the operations teams have worked on "Mars time", with a work schedule synchronized to the local time at the landing site on Mars, rather than the ...
Substituting the mass of Mars for M and the Martian sidereal day for T and solving for the semimajor axis yields a synchronous orbit radius of 20,428 km (12,693 mi) above the surface of the Mars equator. [3] [4] [5] Subtracting Mars's radius gives an orbital altitude of 17,032 km (10,583 mi). Two stable longitudes exist - 17.92°W and 167.83°E.
A synchronous orbit around Earth that is circular and lies in the equatorial plane is called a geostationary orbit. The more general case, when the orbit is inclined to Earth's equator or is non-circular is called a geosynchronous orbit. The corresponding terms for synchronous orbits around Mars are areostationary and areosynchronous orbits.
A mission could have a period of 365 days in a year, a few weeks each month, [6] a few weeks every 26 months (e.g. Mars launch periods), [7] or a short period time that won't be repeated. A launch window indicates the time frame on a given day within the launch period that the rocket can launch to reach its intended orbit.
Earth/Mars transfer time (days) Notes 1 1 2.135 2.23 146 Aldrin cycler 2 2 4.27 2.33 158 2 3 4.27 1.51 280 Aphelion inside semi-major axis of Mars orbit 3 4 6.405 1.89 189 3 5 6.405 1.45 274 Aphelion inside semi-major axis of Mars orbit 3 5 6.405 1.52 134 Aphelion inside semi-major axis of Mars orbit 4 5 8.54 1.82 88 4 6 8.54 1.53 157
The time of flight is related to other variables by Lambert's theorem, which states: The transfer time of a body moving between two points on a conic trajectory is a function only of the sum of the distances of the two points from the origin of the force, the linear distance between the points, and the semimajor axis of the conic. [2]
Sketch of a circumlunar free return trajectory (not to scale), plotted on the rotating reference frame rotating with the moon. (Moon's motion only shown for clarity) In orbital mechanics, a free-return trajectory is a trajectory of a spacecraft traveling away from a primary body (for example, the Earth) where gravity due to a secondary body (for example, the Moon) causes the spacecraft to ...
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