Kepler's Laws Of Planetary Motion

Sir Mathematical Model of the empirical observations, which Newton then interpreted using Calculus and his new Physics .

KEPLER'S FIRST LAW

''The Orbit of a Planet about a Star is an Ellipse with the star at one Focus .''

There is no object at the other focus of a planet's orbit. The Semimajor Axis , ''a'', is half the major axis of the ellipse. In some sense it can be regarded as the average distance between the planet and its star, but it is not the time average in a strict sense, as more time is spent near Apocentre than near Pericentre .

KEPLER'S SECOND LAW

''A Line joining a planet and its star sweeps out equal Area s during equal intervals of Time
This is also known as the law of equal areas.

Suppose a planet takes 1 Day to travel from Point s ''A'' to ''B''. During this Time , an imaginary line, from the Sun '''to the planet, will sweep out a roughly Triangular Area . This same amount of area will be swept every day.

As a planet travels in its elliptical orbit, its Distance from the Sun will vary. As an equal area is swept during any period of time and since the distance from a planet to its orbiting star varies, one can conclude that in order for the area being swept to remain Constant , a planet must vary in Speed . The physical meaning of the law is that the planet moves faster when it is closer to the sun. This is because the sun's gravity accelerates the planet as it falls toward the sun, and decelerates it on the way back out.

KEPLER'S THIRD LAW

''The Square s of the Orbital Period s of planets are directly Proportional to the Cube s of the Semi-major Axis of the orbits.''
:

T^2 \propto a^3

T

= orbital period of planet
:

a

= semimajor axis of orbit

So the expression ''T''²''a''^–3 has the same value for all planets in the solar system as it has for Earth .

That value is (with T in seconds, a in meters)

3.00	imes 10^{-19} rac{s^{2}}{m^{3}}   \pm \ 0.7%\,

.

Thus, not only does the length of the orbit increase with distance, the Orbital Speed decreases, so that the increase of the sidereal period is more than proportional.

See the actual figures: Attributes Of Major Planets .

This law is also known as the harmonic law.

ACCURACY AND LIMITATIONS

As discussed below, Kepler's third law needs to be modified when the orbiting body's mass is not negligible compared to the mass of the body being orbited. However, the correction is fairly small in the case of the planets orbiting the Sun .

A more serious limitation of Kepler's laws is that they do not work well in a system consisting of more than two bodies. They were designed to give a description of the motion of the planets around the sun, which is satisfactory for most planets but a particularly bad approximation in the case of the Earth-Sun-Moon system. For calculations of the Moon 's orbit, Kepler's laws are far less accurate than the empirical method invented by Ptolemy more than a thousand years before.

Newton generalized Kepler's first law with the realization that an object moving at greater than escape velocity (e.g., some Comet s) would have an open Parabolic or Hyperbolic orbit rather than a closed Elliptical one. Thus, all of the conic sections are possible orbits. The second law is still valid for open orbits (since angular momentum is still conserved), but the third law is inapplicable because the motion is not periodic.

Because electrical forces also obey an inverse square law, Kepler's laws also apply to bodies interacting electrically. If the interaction is repulsive, as in Rutherford Scattering , then the orbit is hyperbolic, with the center of repulsion outside the hyperbola. In the planetary model of the Atom , the Electrons were imagined to orbit the Nucleus exactly like the planets orbiting the Sun, and Niels Bohr even went so far as to attempt to assign specific atomic energy levels to specific elliptical orbits. The Keplerian approximation is successful when the Quantum-mechanical Wavelengths are small compared to the size of the orbit (as in Rutherford scattering, and in some unusual artificially populated electron orbitals with very high values of the principal quantum number).

Kepler's laws do not consider the emission of Radiation . The emission of Gravitational Radiation is negligible in our Solar System , but important in some Stellar System s containing Black Hole s or Neutron Star s (any system involving large masses combined with large accelerations). In the planetary model of the atom, the emission of Electromagnetic Radiation should have led to the collapse of all atoms, and this was a hint that Classical Physics was in need of modification.

Kepler's laws don't incorporate Relativity , so, for example, they don't correctly predict the Precession Of Mercury's Orbit . The successful explanation of this non-Keplerian behavior was one of the most dramatic early successes of General Relativity . Kepler's laws fail even more dramatically in the case of an object orbiting a black hole; here, general relativity predicts that many orbits —those that pass through the Event Horizon — are one-way streets to a dead-end region of Spacetime .

CONNECTION TO NEWTON'S LAWS AND CONSERVATION LAWS

Kepler did not understand why his laws were correct; it was Isaac Newton who discovered the answer to this more than fifty years later. The second law can also be seen as a statement of conservation of Angular Momentum , which is a logical consequence of Newton's laws in the special case of a force that acts along the line connecting two objects.

Kepler's first law

Newton said that "every object in the universe attracts every other object along a line of the centres of the objects, proportional to each object's mass, and inversely proportional to the square of the distance between the objects."

The following assumes that acceleration a is of the form

:

\mathbf{a} = rac{d^2\mathbf{r}}{dt^2} = f(r)\hat{\mathbf{r}}.

Recall that in Polar Coordinate s

:

rac{d\mathbf{r}}{dt} = \dot r\hat{\mathbf{r}} + r\dot	heta\hat{\boldsymbol	heta},

rac{d^2\mathbf{r}}{dt^2} = (\ddot r - r\dot	heta^2)\hat{\mathbf{r}} + (r\ddot	heta + 2\dot r \dot	heta)\hat{\boldsymbol	heta}.

In component form, we have

:

\ddot r - r\dot	heta^2 = f(r),

r\ddot	heta + 2\dot r\dot	heta = 0.

Substituting for

\ddot 	heta

and

\dot r

in the second equation, we have

:

r  { d \dot	heta \over dt } + 2 {dr \over dt} \dot	heta = 0

which simplifies to

:

rac{d\dot	heta}{\dot	heta} = -2rac{dr}{r}.

When integrated, this yields

:

\log\dot	heta = -2\log r + \log\ell,

\log\ell  =  \log r^2 + \log\dot	heta,

\ell = r^2\dot	heta

,

for some constant

\ell

, which can be shown to be the Specific Angular Momentum . Now we substitute. Let

:

r = rac{1}{u},

\dot r = -rac{1}{u^2}\dot u = -rac{1}{u^2}rac{d	heta}{dt}rac{du}{d	heta}= -\ellrac{du}{d	heta},

\ddot r = -\ellrac{d}{dt}rac{du}{d	heta} = -\ell\dot	hetarac{d^2u}{d	heta^2}= -\ell^2u^2rac{d^2u}{d	heta^2}.

The equation of motion in the

\hat{\mathbf{r}}

direction becomes

:

rac{d^2u}{d	heta^2} + u = - rac{1}{\ell^2u^2}f\left(rac{1}{u}
ight).

Newton's law of gravitation relates the force per unit mass to the radial distance as

:

f \left( {1 \over u} 
ight) =  f(r)= - \, { GM \over r^2 } = - GM u^2

where ''G'' is the constant of universal gravitation and ''M'' is the mass of the star.

As a result,

:

rac{d^2u}{d	heta^2} + u = rac{GM}{\ell^2}

This differential equation has the general solution:

:

u = rac{GM}{\ell^2}  \bigg 1 + e\cos(	heta-	heta_0) \bigg .

for arbitrary constants of integration ''e'' and θ₀.

Replacing ''u'' with 1/''r'' and letting θ₀ = 0:

:

r  = { 1 \over u } = rac{ \ell^2 / GM  }{ 1+  e\cos	heta}

This is indeed the equation of a Conic Section with Eccentricity ''e'' and the origin at one focus. Thus, Kepler's first law is a direct result of Newton's law of gravitation and Newton's second law of motion.

Kepler's second law

Assuming Newton's laws of motion, we can show that Kepler's second law is consistent. By definition, the Angular Momentum

\mathbf{L}

of a point mass with mass

m

and velocity

\mathbf{v}

is :

:

\mathbf{L} \equiv \mathbf{r} 	imes \mathbf{p} = \mathbf{r} 	imes  ( m \mathbf{v} )

.

where

\mathbf{r}

is the position vector of the particle and

\mathbf{p}  =  m \mathbf{v}

is the momentum of the particle.

By definition,
:

\mathbf{v} = rac{d\mathbf{r}}{dt}

.

As a result, we have
:

\mathbf{L} = \mathbf{r} 	imes mrac{d\mathbf{r}}{dt}

.

Taking the derivative of both sides with respect to time, we have

:

rac{d\mathbf{L}}{dt} =  (\mathbf{r} 	imes \mathbf{F})  + \left( rac{d\mathbf{r}}{dt}  	imes  mrac{d\mathbf{r}}{dt} 
ight)
=  ( \mathbf{r} 	imes \mathbf{F} )  +  ( \mathbf{v} 	imes \mathbf{p} ) = 0

Now that we have

V_B

, we can find the rate at which the planet is sweeping out area in the ellipse. This rate remains constant, so we can derive it from any point we want, specifically from point B.

:

rac{dA}{dt}=rac{rac{1}{2}\cdot(1+\epsilon)a\cdot V_B \,dt}{dt}= \begin{matrix}rac{1}{2}\end{matrix} \cdot(1+\epsilon)a\cdot V_B

= \begin{matrix}rac{1}{2}\end{matrix} \cdot(1+\epsilon)a\cdot \sqrt{rac{GM\cdot(1-\epsilon)}{a\cdot(1+\epsilon)}} =
 \begin{matrix}rac{1}{2}\end{matrix} \cdot\sqrt{GMa\cdot(1-\epsilon)(1+\epsilon)}

However, the total area of the ellipse is equal to

\pi a \sqrt{(1-\epsilon^2)}a

. (That's the same as

\pi a b

, because

b=\sqrt{(1-\epsilon^2)}a

). The time the planet take out to sweep out the entire area of the ellipse equals the ellipse's area, so,

:

T\cdot rac{dA}{dt}=\pi a \sqrt{(1-\epsilon^2)}a

T\cdot \begin{matrix}rac{1}{2}\end{matrix} \cdot\sqrt{GMa\cdot(1-\epsilon)(1+\epsilon)}=\pi \sqrt{(1-\epsilon^2)}a^2

T=rac{2\pi \sqrt{(1-\epsilon^2)}a^2}{\sqrt{GMa\cdot(1-\epsilon)(1+\epsilon)}} =rac{2\pi a^2}{\sqrt{GMa}}=
rac{2\pi}{\sqrt{GM}}\sqrt{a^3}

T^2=rac{4\pi^2}{GM}a^3.

However, if the mass ''m'' is not negligible in relation to ''M'', then the planet will orbit the sun with the exact same velocity and position as a very small body orbiting an object of mass

M+m

(see Reduced_mass ). To integrate that in the above formula, ''M'' must be replaced with

M+m

, to give

:

T^2=rac{4\pi^2}{G(M+m)}a^3.

Q.E.D.

SOLUTION FOR THE MOTION AS A FUNCTION OF TIME

The Keplerian Problem assumes an orbit with semimajor axis ''a'', semiminor axis ''b'', and Eccentricity ε. To convert the laws into predictions, Kepler began by adding the orbit's auxiliary circle (that with the major axis as a diameter) and defined these points:

''c'' center of auxiliary circle and ellipse

''s'' sun (at one focus of ellipse); $\mbox{length }cs=aarepsilon$

''p'' the planet

''z'' perihelion

''x'' is the projection of the planet to the auxiliary circle; then $\mbox{area }sxz=rac ab\mbox{area }spz$

''y'' is a point on the circle such that $\mbox{area }cyz=\mbox{area }sxz=rac ab\mbox{area }spz$

True Anomaly $T=\angle zsp$ , the planet as seen from the sun

Eccentric Anomaly $E=\angle zcx$ , ''x'' as seen from the centre

Mean Anomaly $M=\angle zcy$ , ''y'' as seen from the centre

Then

:

\mbox{area }cxz=\mbox{area }cxs+\mbox{area }sxz

=\mbox{area }cxs+\mbox{area }cyz

rac{a^2}2E=aarepsilonrac a2\sin E+rac{a^2}2M

giving Kepler's equation

:

M=E-arepsilon\sin E

.

To connect ''E'' and ''T'', assume

r=\mbox{length }sp

then

:

aarepsilon+r\cos T=a\cos E

and

r\sin T=b\sin E

r=rac{a\cos E-aarepsilon}{\cos T}=rac{b\sin E}{\sin T}

an T=rac{\sin T}{\cos T}=rac barac{\sin E}{\cos E-arepsilon}=rac{\sqrt{1-arepsilon^2}\sin E}{\cos E-arepsilon}

which is ambiguous but useable. A better form follows by some trickery with Trigonometric Identities :

:

anrac T2=\sqrtrac{1+arepsilon}{1-arepsilon}	anrac E2

(So far only laws of geometry have been used.)

Note that

\mbox{area }spz

is the area swept since perihelion; by the second law, that is proportional to time since perihelion. But we defined

\mbox{area }spz=rac ba\mbox{area }cyz=rac barac{a^2}2M

and so ''M'' is also proportional to time since perihelion—this is why it was introduced.

We now have a connection between time and position in the orbit. The catch is that Kepler's equation cannot be rearranged to isolate ''E''; going in the time-to-position direction requires an iteration (such as Newton's Method ) or an approximate expression, such as
:

E\approx M+\left(arepsilon-rac18arepsilon^3
ight)\sin M+rac12arepsilon^2\sin 2M+rac38arepsilon^3\sin 3M

via the Lagrange Reversion Theorem . For the small ε typical of the planets (except Pluto ) such series are quite accurate with only a few terms; one could even develop a series computing ''T'' directly from ''M''. {Link without Title}

SEE ALSO

Circular Motion

Gravity

Two-body Problem

Free-fall Time

EXTERNAL LINKS

Crowell, Benjamin, ''Conservation Laws'', http://www.lightandmatter.com/area1book2.html , an online book that gives a proof of the first law without the use of calculus.

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Kepler's Laws Of Planetary Motion