Specific angular momentum

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In celestial mechanics, the specific relative angular momentum (often denoted or ) of a body is the angular momentum of that body divided by its mass. [1] In the case of two orbiting bodies it is the vector product of their relative position and relative linear momentum, divided by the mass of the body in question.


Specific relative angular momentum plays a pivotal role in the analysis of the two-body problem, as it remains constant for a given orbit under ideal conditions. "Specific" in this context indicates angular momentum per unit mass. The SI unit for specific relative angular momentum is square meter per second.


The specific relative angular momentum is defined as the cross product of the relative position vector and the relative velocity vector .

where is the angular momentum vector, defined as .

The vector is always perpendicular to the instantaneous osculating orbital plane, which coincides with the instantaneous perturbed orbit. It is not necessarily be perpendicular to the average orbital plane over time.

Proof of constancy in the two body case

Distance vector
{\displaystyle \mathbf {r} }
, velocity vector
{\displaystyle \mathbf {v} }
, true anomaly
{\displaystyle \theta }
and flight path angle
{\displaystyle \phi }
{\displaystyle m_{2}}
in orbit around
{\displaystyle m_{1}}
. The most important measures of the ellipse are also depicted (among which, note that the true anomaly
{\displaystyle \theta }
is labeled as
{\displaystyle \nu }
). FlightPathAngle.svg
Distance vector , velocity vector , true anomaly and flight path angle of in orbit around . The most important measures of the ellipse are also depicted (among which, note that the true anomaly is labeled as ).

Under certain conditions, it can be proven that the specific angular momentum is constant. The conditions for this proof include:


The proof starts with the two body equation of motion, derived from Newton's law of universal gravitation:


The cross product of the position vector with the equation of motion is:

Because the second term vanishes:

It can also be derived that:

Combining these two equations gives:

Since the time derivative is equal to zero, the quantity is constant. Using the velocity vector in place of the rate of change of position, and for the specific angular momentum:

is constant.

This is different from the normal construction of momentum, , because it does not include the mass of the object in question.

Kepler's laws of planetary motion

Kepler's laws of planetary motion can be proved almost directly with the above relationships.

First law

The proof starts again with the equation of the two-body problem. This time one multiplies it (cross product) with the specific relative angular momentum

The left hand side is equal to the derivative because the angular momentum is constant.

After some steps (which includes using the vector triple product and defining the scalar to be the radial velocity, as opposed to the norm of the vector ) the right hand side becomes:

Setting these two expression equal and integrating over time leads to (with the constant of integration )

Now this equation is multiplied (dot product) with and rearranged

Finally one gets the orbit equation [1]

which is the equation of a conic section in polar coordinates with semi-latus rectum and eccentricity .

Second law

The second law follows instantly from the second of the three equations to calculate the absolute value of the specific relative angular momentum. [1]

If one connects this form of the equation with the relationship for the area of a sector with an infinitesimal small angle (triangle with one very small side), the equation

Third law

Kepler's third is a direct consequence of the second law. Integrating over one revolution gives the orbital period [1]

for the area of an ellipse. Replacing the semi-minor axis with and the specific relative angular momentum with one gets

There is thus a relationship between the semi-major axis and the orbital period of a satellite that can be reduced to a constant of the central body.

See also

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    1. 1 2 3 4 Vallado, David A. (2001). Fundamentals of astrodynamics and applications (2nd ed.). Dordrecht: Kluwer Academic Publishers. pp. 20–30. ISBN   0-7923-6903-3.