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Orbital inclination change is a orbital maneuver aimed at changing inclination of orbiting body's orbit. These maneuvers can are also known as an orbital plane change as the plane of the orbit is tipped. This maneuver requires a change in the orbital velocity vector (delta v) at the orbital nodes (i.e. the point where the initial and desired orbits intersect, the line of orbital nodes is defined by the intersection of the two orbital planes). An orbital maneuver is a change from one orbit to another, accomplished by applying thrust. ...
Inclination is one of the six orbital parameters describing the shape and orientation of a celestial orbit and is the angular distance of the orbital plane from the plane of the reference (usually planets equator or the ecliptic), stated in degrees. ...
In physics, an orbit is the path that an object makes, around another object, whilst under the influence of a source of centripetal force, such as gravity. ...
In general physics, delta-v is simply the change in velocity. ...
Orbital nodes are points where an orbit crosses a plane of reference (e. ...
Maximum efficiency of inclination change is achieved at apoapsis, (or apogee), where orbital velocity  is the lowest. In general, inclination changes require the most delta v to perform, and most mission planners try to avoid them whenever possible to conserve fuel. This can sometimes be achieved by launching a spacecraft directly into the desired inclination, or as close to it as possible so as to minimize the inclination change required. This article is about several astronomical terms (apogee & perigee, aphelion & perihelion, generic equivalents based on apsis, and related but rarer terms. ...
This article is about several astronomical terms (apogee & perigee, aphelion & perihelion, generic equivalents based on apsis, and related but rarer terms. ...
An important sublty of performing an inclination change is that Keplerian orbital inclination is defined by the angle between ecliptic North and the vector normal to the orbit plane, (i.e. the angular momentum vector. This means that inclination is always positive and is entangled with other orbital elements primarily the argument of periapsis which is in turn connected to the longitude of the ascending node. This can result in two very different orbits with precisely the same inclination. Inclination is one of the six orbital parameters describing the shape and orientation of a celestial orbit and is the angular distance of the orbital plane from the plane of the reference (usually planets equator or the ecliptic), stated in degrees. ...
The plane of the ecliptic is well seen in this picture from the 1994 lunar prospecting Clementine spacecraft. ...
In physics the angular momentum of an object with respect to a reference point is a measure for the extent to which, and the direction in which, the object rotates about the reference point. ...
The elements of an orbit are the parameters needed to specify that orbit uniquely, given a model of two ideal masses obeying the Newtonian laws of motion and the inverse-square law of gravitational attraction. ...
In an orbit, the argument of periapsis () is the angle between the ascending node (the point where the orbiting body passes from the southern to the northern hemisphere) and the periapsis (the point of closest approach to the central body). ...
The Longitude of the ascending node () is one of the orbital elements used to specify the orbit of an object in space. ...
Inclination is one of the six orbital parameters describing the shape and orientation of a celestial orbit and is the angular distance of the orbital plane from the plane of the reference (usually planets equator or the ecliptic), stated in degrees. ...
For the most efficient example mentioned above, targeting an inclination at apoapsis also changes the argument of periapsis. However, targeting in this manner limits the mission designer to changing the plane only along the line of apsis. This article is about several astronomical terms (apogee & perigee, aphelion & perihelion, generic equivalents based on apsis, and related but rarer terms. ...
In an orbit, the argument of periapsis () is the angle between the ascending node (the point where the orbiting body passes from the southern to the northern hemisphere) and the periapsis (the point of closest approach to the central body). ...
Another view of Keplerian orbital elements. ...
Calculation In a pure inclination change, only the inclination of the orbit is changed while all other orbital characteristics (radius, shape.. etc) remains the same as before. Delta-v ( ) required for a pure inclination change ( ) can be calculated as follows: General In general physics delta-v is simply the change in velocity. ...
 where: - is orbiting body's velocity at orbital position where maneuver takes place.
For more complicated manuvers which may involve a combination of change in inclination and orbital radius, the amount of delta v is the vector difference between the velocity vectors of the initial orbit and the desired orbit at the transfer point.
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