Unit 2.5 Kepler's Problem

Question 1

Kepler’s problem

Answer 1

It is difficult to predict where an object will be in the future using only COEs because the true anomaly will not change at a constant rate for an elliptical orbit.

Question 2

Eccentric Anomaly (E)

Answer 2

Using a superimposed auxiliary circle onto the orbit, a new angle can be measured from the center of the orbit (follows the True anomaly, v)
This is a stepping stool constant to address Kepler’s problem.

Question 3

Mean Anomaly (M)

Answer 3

Used to propagate the orbit in time. It rotates at a constant rotation rate. Equal to true anomaly at all points.
Tells the operator: how far through the orbit has traveled through its orbit at that time.

Question 4

Mean Motion, 𝑴̇ or n,

Answer 4

Rotation rate of the Mean anomaly, will always be a ‘constant’
Tells the operator: how quickly the satellite orbits the earth, e.g. 14 times per day

Question 5

Equal at perigee and apogee

Answer 5

Mean, eccentric and true anomaly