Orbit maneuver

[ESA1]

Hi!

I need help with calculating a problem that deals with a satellite in orbit. The question is:

Uou're doing a first-order analysis on a new satellite in an elliptical orbit (e=0.20) at 700 km altitude. Can you design the orbit so no maneuvers are necessary to maintain it? Hint: consider secular J2 perturbations only

So, how should I solve this? J2= 10^-3 btw
Thanks!

 

[boogabooga]

gravity.pdf in the Orbiter/Doc/Technotes folder describes how J2 affects an orbit.

The question is ambiguous. What are you trying to maintain?

Constant LAN, constant AOP, sun-synchronous?

 

[Urwumpe]

Look at the perturbation formulas - if you enter the given numbers, which values do you need to define so that the long-term perturbations are neutralized (what is neutralized after every Orbit is not important for the question).

For example, there is one inclination that allows orbits to be safe from perturbations of inclination. Which one is it?

And please give us some of the credits for your homework.

 

[garyw]

And please give us some of the credits for your homework.

Indeed. If that's not a copy n paste homework question I don't know what is. :lol:

 

[Urwumpe]

Indeed. If that's not a copy n paste homework question I don't know what is. :lol:

I actually had nearly the same question in my "Spaceflight I" lecture homeworks. :lol:

 

[Linguofreak]

Indeed. If that's not a copy n paste homework question I don't know what is. :lol:

Yeah the "hint" part is a dead giveaway (unless the post were structured as a challenge to which the OP obviously knew the answer, which isn't the case). Also the fact that it's a new member with 1 post.

 

[C3PO]

Yeah the "hint" part is a dead giveaway

This is where education differs from 'real life'.

In class: The 'problem' is constructed in a way that 'fishes' for a particular solution, often using a very simple physical model.

At work: You have to make a judgment on which parts of a (usually) very complex model are important to the solution.

Most subjects have to be taught using simple models initially. But I often encounter people with college+ education that are trying to solve 'real' problems using only the simple classroom models. :facepalm: [\OT]

 

[boogabooga]

Look at the perturbation formulas - if you enter the given numbers, which values do you need to define so that the long-term perturbations are neutralized (what is neutralized after every Orbit is not important for the question).

For example, there is one inclination that allows orbits to be safe from perturbations of inclination. Which one is it?

And please give us some of the credits for your homework.

It's still ambiguous, because any one inclination will not neutralize both AOP and LAN.