## Examples in the Use of Kepler's Equation

We will show how to use Kepler's Equation which is

M = E - e sin E

to get the time, t, or position, n, in orbit. An addition relationships

cos n = [cos E - e]/[1 - e cos E]

and

cos E = [cos n + e]/[1 + e cos n]

will be needed.
• E = eccentric anomaly measured from perihelion about the center of the elliptical orbit
• e = eccentricity of the orbit
• M = mean anomaly = 2p t/P
• t = time since perihelion passage
• P = period of the orbit
• n = true anomaly = angle of the object in obit relative to the perihelion

EXAMPLES: An orbit with e = 0.20
1. Determine the fraction of a period required to travel 1/6 of an orbit past perihelion (60o).
2. Determine the angular position past perihelion after 1/6 of the orbital period.

Example 1.
n = 60o
cos E = (cos 60o + 0.2)/(1 + e cos 60o) = 0.46667
E = 1.08528 radians = 62o.18
M = 1.08528 - 0.20 sin(1.08528 radians) = 0.90839
t/P = M/(2p) = 0.14458

Example 2.
t/P = 1/6 = 0.16667
M = 2p/6 = p/3
Iterative Solution: Kepler's equation must be solved for the eccentric anomaly, E, but the equation is transandental and has no algebraic solution. The solution must be done numerically. As long as the eccentricity is not near 1, an interative solution as follows works well.

• E1 = M + e sin M
• E2 = M + e sin E1
• E3 = M + e sin E2
• E4 = M + e sin E3
• ....
This is repeated until two succeeding values of E are the same within the precision desired.

Using the values of M and e for this example we get

• E1 = 1.2350
• E2 = 1.2360
• E3 = 1.2361