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TheoremProved

Conservation of the Laplace–Runge–Lenz vector

Statement

The vector A=r˙×h−GMr^\mathbf A = \dot{\mathbf r}\times\mathbf h - GM\hat{\mathbf r} is constant in time for motion under an inverse-square force r¨=−GMr3r\ddot{\mathbf r} = -\dfrac{GM}{r^{3}}\mathbf r, has magnitude ∣A∣=GMe|\mathbf A| = GMe, and points from the focus toward periapsis.

Why is it true?

Energy and angular momentum alone fix the size and shape of a Kepler orbit but not its orientation within the plane; the Laplace–Runge–Lenz vector is the extra conserved quantity that pins down where periapsis sits, and its very existence is special to the 1/r21/r^2 force — most central forces do not have such a vector, which is exactly why most central-force orbits (as in the restricted three-body problem below) do not stay on a fixed closed curve.

Proof sketch

Differentiate: dAdt=r¨×h+r˙×h˙−GMdr^dt\dfrac{d\mathbf A}{dt} = \ddot{\mathbf r}\times\mathbf h + \dot{\mathbf r}\times\dot{\mathbf h} - GM\dfrac{d\hat{\mathbf r}}{dt}. Since h\mathbf h is constant (Theorem 1), the middle term vanishes. Using r¨=−GMr2r^\ddot{\mathbf r}=-\dfrac{GM}{r^{2}}\hat{\mathbf r} and h=r×r˙\mathbf h=\mathbf r\times\dot{\mathbf r}, the vector triple product identity r^×(r×r˙)=r(r^⋅r˙)−r˙(r^⋅r)\hat{\mathbf r}\times(\mathbf r\times\dot{\mathbf r}) = \mathbf r(\hat{\mathbf r}\cdot\dot{\mathbf r}) - \dot{\mathbf r}(\hat{\mathbf r}\cdot\mathbf r) gives r¨×h=−GMr2[rr˙ r^−rr˙]=GM(r˙r−r˙rr^)\ddot{\mathbf r}\times\mathbf h = -\dfrac{GM}{r^{2}}\big[r\dot r\,\hat{\mathbf r} - r\dot{\mathbf r}\big] = GM\left(\dfrac{\dot{\mathbf r}}{r} - \dfrac{\dot r}{r}\hat{\mathbf r}\right), where r˙=r^⋅r˙\dot r=\hat{\mathbf r}\cdot\dot{\mathbf r} is the scalar rate of change of the distance rr (used r^⋅r=r\hat{\mathbf r}\cdot\mathbf r=r).

On the other hand, differentiating r^=r/r\hat{\mathbf r}=\mathbf r/r directly gives dr^dt=r˙r−r r˙r2=r˙r−r˙rr^\dfrac{d\hat{\mathbf r}}{dt} = \dfrac{\dot{\mathbf r}}{r} - \dfrac{\mathbf r\,\dot r}{r^{2}} = \dfrac{\dot{\mathbf r}}{r} - \dfrac{\dot r}{r}\hat{\mathbf r} — exactly the same bracketed expression found for r¨×h/GM\ddot{\mathbf r}\times\mathbf h/GM above. So r¨×h=GMdr^dt\ddot{\mathbf r}\times\mathbf h = GM\dfrac{d\hat{\mathbf r}}{dt} identically.

Therefore dAdt=GMdr^dt−GMdr^dt=0\dfrac{d\mathbf A}{dt} = GM\dfrac{d\hat{\mathbf r}}{dt} - GM\dfrac{d\hat{\mathbf r}}{dt} = \mathbf 0, proving A\mathbf A is constant. Evaluating A\mathbf A at periapsis, where r˙\dot{\mathbf r} is purely tangential (perpendicular to r^\hat{\mathbf r}) with speed vp=h/rpv_p=h/r_p, gives r˙×h\dot{\mathbf r}\times\mathbf h pointing along −r^-\hat{\mathbf r} with magnitude h2/rph^{2}/r_p, so A=(h2rp−GM)r^\mathbf A = \left(\dfrac{h^{2}}{r_p}-GM\right)\hat{\mathbf r}; using rp=p/(1+e)=h2GM(1+e)r_p=p/(1+e)=\dfrac{h^{2}}{GM(1+e)} from the orbit equation gives A=GMe r^p\mathbf A = GMe\,\hat{\mathbf r}_p, confirming ∣A∣=GMe|\mathbf A|=GMe pointing exactly toward periapsis. ■\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