Lecture

Departure from a Planet: Trajectories and Velocities

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Description

This lecture delves into the departure from a planet, focusing on trajectories and velocities in space mission design and operations. The instructor explains hyperbolic trajectories, vis-viva equations for elliptical and hyperbolic velocities, and the concept of sphere of influence. Key topics include hyperbola basics, total energy per unit mass, and the influence of various parameters on spacecraft trajectories.

In MOOC

Space Mission Design and Operations

Space exploration is a very exciting subject. Consider the achievements of Sputnik 1, Yuri Gagarin's first flight in space, the Apollo missions to the Moon, followed by the Shuttle program, the Hubble Space Telescope launch and maintenance on orbit, and finally the assembly and exploitation of the International Space Station. These were challenging undertakings involving space agencies and industrial teams of several nations, and private companies as well. Space telescopes are in service, and several compon

Official source

Ontological neighbourhood

Astronomy

Astrodynamics: Topics in astrodynamics

Related concepts (32)

Hyperbolic trajectory

In astrodynamics or celestial mechanics, a hyperbolic trajectory or hyperbolic orbit is the trajectory of any object around a central body with more than enough speed to escape the central object's gravitational pull. The name derives from the fact that according to Newtonian theory such an orbit has the shape of a hyperbola. In more technical terms this can be expressed by the condition that the orbital eccentricity is greater than one.

Elliptic orbit

In astrodynamics or celestial mechanics, an elliptic orbit or elliptical orbit is a Kepler orbit with an eccentricity of less than 1; this includes the special case of a circular orbit, with eccentricity equal to 0. In a stricter sense, it is a Kepler orbit with the eccentricity greater than 0 and less than 1 (thus excluding the circular orbit). In a wider sense, it is a Kepler orbit with negative energy. This includes the radial elliptic orbit, with eccentricity equal to 1.

Vis-viva equation

In astrodynamics, the vis-viva equation, also referred to as orbital-energy-invariance law or Burgas formula, is one of the equations that model the motion of orbiting bodies. It is the direct result of the principle of conservation of mechanical energy which applies when the only force acting on an object is its own weight which is the gravitational force determined by the product of the mass of the object and the strength of the surrounding gravitational field.

Parabolic trajectory

In astrodynamics or celestial mechanics a parabolic trajectory is a Kepler orbit with the eccentricity equal to 1 and is an unbound orbit that is exactly on the border between elliptical and hyperbolic. When moving away from the source it is called an escape orbit, otherwise a capture orbit. It is also sometimes referred to as a C3 = 0 orbit (see Characteristic energy). Under standard assumptions a body traveling along an escape orbit will coast along a parabolic trajectory to infinity, with velocity relative to the central body tending to zero, and therefore will never return.

Escape velocity

In celestial mechanics, escape velocity or escape speed is the minimum speed needed for a free, non-propelled object to escape from the gravitational influence of a primary body, thus reaching an infinite distance from it. It is typically stated as an ideal speed, ignoring atmospheric friction. Although the term "escape velocity" is common, it is more accurately described as a speed than a velocity because it is independent of direction.

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