Kepler's Laws of Planetary Motion consist of the law of ellipses, the law of equal areas, and the law of periods. The law of harmonic motion is not a part of Kepler's Laws.

According to Kepler's first law, the path of a planet's orbit around the Sun is an ellipse, with the Sun at one of the foci of the ellipse.

This relationship is known as Kepler's third law, which states that the square of the orbital period of a planet is proportional to the cube of the semi-major axis of its orbit.

At the perigee, the spacecraft is closest to the central body and therefore has the highest velocity in its orbit.

The specific orbital energy of a spacecraft in a circular orbit is negative because the spacecraft is bound to the central body by gravitational attraction.

The Hohmann transfer maneuver is a two-impulse maneuver used to transfer a spacecraft from one circular orbit to another.

A geostationary orbit is a circular orbit around Earth with an altitude of approximately 35,786 kilometers, which allows a satellite to remain fixed over a specific point on Earth's surface.

Elliptical transfer orbits are often used for interplanetary travel because they require less energy than Hohmann transfer maneuvers.

The stability of an orbit is primarily determined by the mass of the central body.

The angle between the orbital plane of a satellite and the equatorial plane of the Earth is called inclination.

The angle between the ascending node of an orbit and the vernal equinox is called the right ascension of the ascending node.

The angle between the perigee of an orbit and the ascending node is called the argument of perigee.

The angle between the current position of a spacecraft in its orbit and the perigee is called the true anomaly.

The angle between the perigee of an orbit and the true anomaly is called the eccentric anomaly.