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Orbit insertion
From Wikipedia, the free encyclopedia
Orbit insertion is a maneuver performed by an inter-planetary spacecraft designed to allow the spacecraft to be captured into orbit around a planet or other body such as a moon. The spacecraft approaches the planet at a speed greater than the escape velocity of the planet. The spacecraft must reduce its speed to below the planet's escape velocity. This is usually accomplished through a rocket firing (orbit insertion burn). The reduction in speed allows the spacecraft to settle into orbit around the planet. Aerobraking can also be used to slow the spacecraft, assuming the planet in question has an atmosphere.
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