Recent content by Paul Gray

Homework Statement Analyse the interruption of solar observation of a satellite on a sun-synchronous orbit (altitude 900km above Earth's surface). The orbit crosses the equatorial plane at the day/night border and the orbital plane should follow this border as close as possible. a) Draw the...

@gneill: Thank you very much for your help. Your hint actually helped me solving my problem. Adjusting the [deg/day] to [rad/rev] gave me a value in the range of [-1;1] . Hence I was able to solve for i.

Homework Statement A satellite is launched into a circular sun-synchronous orbit at a height of 900km above Earth's surface. What is the implication on the orbit's inclination (in deg) and on the change of the position of the right ascension of the ascending node per day.Homework Equations The...

Thank you, I got it :).

Thank you for your ongoing help :). I'm not sure if it is just the angular speed of the Earth, because my exercise sheet asks for the angular speed in the exact same question, which comes after the question for the true anomaly change. So I would calculate the angular speed twice in two...

Thank you very much voko. The numbers are not as important as the logic is :). The minus in front of -2.139*10^{-3} still bugs me. How can I get rid of it? Can I neglect it?

Thank you both very much for your input. I think I understood the question b). It is asked for the angle \angle \text{Earth }\text{Sun }\text{Mars}. Hence it has to be as following \angle ESM = \omega_E * t_h - (44.3371^\circ + \omega_M \cdot t_h) = 0.9863 \cdot 258.8 - (44.3371^\circ + 0.5242...

Using the hint voko provided I get the following answer \Delta\Omega = - \frac{3\pi J_2 R_E^2}{a^2 (1-e^2)^2} \cdot \cos i = \frac{3\pi 1082.7 \cdot 10^{-6} 6378^2}{26544^2 (1-0.72^2)^2} \cdot \cos 63.4 = -2.139 \cdot 10^{-3} [\frac{rad}{rev}] One revolution takes 1 [rev] = T = 2\pi...

Hello again :), I have to solve a rather extensive task. Most important are questions a) and c). I appreciate any help :)! Homework Statement The task: Determine characteristics of a Hohmann transfre towards, when circular planetary orbits around the Sun with R_E = 149.6 \cdot 10^6 km...

That's a simple but clever answer. I will give it a shot as soon as possible :). Thank you ...

Hello there :), Homework Statement We have a molniya orbit with an eccentricity of e = 0.72 and a semi-major axis a = 26554 [km]. The task: Calculate the angular displacement of the ascending node Ω after 100 sidereal days Homework Equations Moreover I know from Wikipedia that a...