MathLabs
TheoremProved

Kepler's Third Law

Statement

For a bound orbit (ellipse) of semi-major axis aa around a total mass MM, the orbital period TT satisfies T2=4π2GMa3T^{2} = \dfrac{4\pi^{2}}{GM}a^{3}.

Why is it true?

This links the size of an orbit directly to how long it takes to complete, with no dependence on eccentricity — a fact used every time astronomers weigh a star or planet by timing a smaller body's orbit around it.

Proof sketch

By Theorem 1, the areal sweep rate dA/dt=h/2dA/dt=h/2 is constant, so integrating over one full period TT gives the total enclosed area A=h2TA = \tfrac{h}{2}T. For an ellipse with semi-major axis aa and semi-minor axis bb, geometry gives A=πabA=\pi ab. Equating the two: A=πab=h2TA = \pi a b = \dfrac{h}{2}T.

Next, tie hh to the shape via Binet's equation: the semi-latus rectum of the orbit is p=h2/GMp=h^{2}/GM, and for an ellipse the standard relations b=a1−e2b=a\sqrt{1-e^{2}} and p=a(1−e2)=b2/ap=a(1-e^{2})=b^{2}/a hold. Combining p=h2/GMp=h^{2}/GM with p=b2/ap=b^{2}/a gives h2=GMb2ah^{2}=\dfrac{GMb^{2}}{a}, so h=GMb2a=bGMah = \sqrt{\dfrac{GMb^{2}}{a}} = b\sqrt{\dfrac{GM}{a}}.

Substitute this expression for hh into πab=h2T\pi ab=\tfrac{h}{2}T and solve for TT: T=2πabh=2πabbGM/a=2πaaGM=2πa3GMT=\dfrac{2\pi ab}{h}=\dfrac{2\pi ab}{b\sqrt{GM/a}}=2\pi a\sqrt{\dfrac{a}{GM}}=2\pi\sqrt{\dfrac{a^{3}}{GM}}. Squaring both sides gives T2=4π2GMa3T^{2} = \dfrac{4\pi^{2}}{GM}a^{3}, which is Kepler's third law — and it holds for every ellipse regardless of ee, since ee canceled out completely. ■\blacksquare

Topics that use this theorem

Step-by-step proofs

No step-by-step proof yet for this theorem.

References

  1. Carl D. Murray, Stanley F. Dermott (1999). Solar System Dynamics
  2. Alain Chenciner, Richard Montgomery (2000). A remarkable periodic solution of the three-body problem in the case of equal masses
  3. NASA Science (2024). Webb's Orbit at Sun-Earth Lagrange Point 2 (L2)
  4. NASA Science (2024). Basics of Spaceflight: A Gravity Assist Primer