By Fred P. J. Rimrott (auth.)

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**Extra info for Introductory Orbit Dynamics, 1st Edition**

**Example text**

ET r = en! X en2 ien! 19) where erT is the unit vector pointing towards the transfer point T, and en) and en2 are unit vectors normal to the old and new orbital planes. 21) As an example, take two circular orbits of 7000 krn radius each about the Earth. Orbit 1 is in the equatorial plane, orbit 2 has an inclination of 20°. The line of intersection of the two orbits extends from Earth centre to the first point of Aries.

If the mission profile provides for a temporary parking of a satellite on a parking orbit, then the subsequent insertion into the final orbit again represents a transfer. In the case of rendezvous of two satellites, the initial orbit of the satellite to be transferred, and the orbit of the target satellite are generally known. The orbit of the target satellite is the final orbit for the transfer satellite. Not only original and final orbit are of significance, but also time of arrival and point of arrival on the target orbit.

Vl z ... \ 0 .... « :0: 0 \ \ dl \ \ z « \- ::> '" .... 8. True anomaly of insertion point VO 48 3. 9. Insertion point and locus of vacant focus. 1 Given is r, a, ~o. Derive an expression for the eccentricity of an ellipse e = /(r, a, ~o) b = ? 10. Orbits resulting from various insertion speeds. 2 3. ) of the orbit, the orbit eccentricity is given by where P. S90°, with v. v. :, -;:; v. :, -;:; v. 1- v. :, -;:; r -V-;:; fli:. 2. What is the value assumed bye, when fli: ? -V-;:; v. 4 A satellite, inserted into its orbit at a height of 629 kIn above the Earth sphere surface at a flight path angle of P.