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Relates the delta-v (Δv) to the exhaust velocity and the initial and final mass of a rocket.

The change in velocity required to perform a maneuver, such as changing orbits or achieving escape velocity.

A measure of how much an orbit deviates from being circular; ranges from 0 (circular) to 1 (parabolic trajectory).

The point in an orbit closest to the central body.

Three laws describing the motion of planets around the sun: orbits are ellipses (1st), equal areas in equal times (2nd), and a relation between the orbital period and semi-major axis (3rd).

A technique where a spacecraft gains or loses orbital energy by passing close to a planet or moon.

Five positions in an orbital configuration where a small object affected only by gravity can maintain a stable position relative to two larger objects (e.g., the Earth and the Moon).

A circular orbit around Earth with an orbital period that matches Earth's rotation on its axis, resulting in a stationary position over the equator.

A phenomenon where a spacecraft's use of propulsion is more effective when traveling at high speeds, typically at periapsis in a highly elliptical orbit.

Points where an orbit crosses a reference plane, with the ascending node being where the object moves northward through the plane, and the descending node where it moves southward.

The angle between the orbital plane of an object and the reference plane (usually the equatorial plane of the body being orbited).

A two-impulse, energy-efficient orbital maneuver to transfer between two coplanar orbits using an elliptical transfer orbit.

The minimum velocity needed for an object to break free from the gravitational pull of a celestial body, without further propulsion.

The point in an orbit farthest from the central body.