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1. Astrodynamics calculator omega inclination software#
2. Astrodynamics calculator omega inclination professional#

I also have no formal training in orbital mechanics but do have a lot of hours in KSP. You will have to do the ascending/descending node thing though as the bodies aren't coplanar.

You can get a feel for how this works intuitively in the game Kerbal Space Program ( r/kerbalspaceprogram) by sending a craft from Kerbin (Earth) to Duna (Mars). If Earth and Mars aren't coplanar (as in RL) then to do it most efficiently you'd perform this correction maneuver as part of the inclination change at the ascending/descending node of your solar orbit and that of Mars to ensure that your solar orbit's inclination is aligned with that of Mars to allow a good intercept. You'd then capture directly into a polar orbit with a capture burn at the Mars periapsis Please let me know if what i'm asking isn't particularly clear.Īssuming Earth and Mars are coplanar, then it would require a very small correction burn (likely single digit delta-v) in solar orbit, very soon after performing the Hohmann transfer maneuver in Earth orbit, to change the Mars equatorial approach to a polar one. If the answer is that we'd encounter mars along this "incoming polar" trajectory, how sizable (subjectively) is the thrust we have to apply during the first part of our hohman transfer? is it a few meters per second of delta V that over the course of the whole orbit allows us to comfortably sail over the top of mars or would achieving that outcome require a massive expenditure of delta V?Īpologies if some of my lingo isnt up to par, I'm still pretty new to this. Will this then result in us approaching mars flying over the top of it (bottom diagram in image 2), or would we still pass by it practically "equatorially", with the offset from the equator being on the order of 1 degree?īasically the question i'm trying to answer is whats the most efficient sequence of maneuvers to get a satellite into a martian polar orbit, could it be done with a small "vertical" burn at the start of the hohmann transfer that then puts us in a position where we sail above the planet and simply circularize into a polar orbit, or would we still only approach it with a 1 degree inclination and have to do an additional maneuver to raise the inclination? Now instead of a hohmann transfer solely along this plane, suppose we do a small burn that changes our inclination (around the sun) by 1 degree.

The simplest hohmann transfer from earth to mars would then mean that the incoming satellite approaches mars at a zero inclination, and assuming no capture burn is done it will fly past it along its equator. I'm trying to conceptually figure out the most efficient way of accomplishing this goal, but my lack of formal training in orbital mechanics means I'm missing some of the key intuitions.Īssume for a moment that earth and mars orbit along a perfect plane, and that the equators of both planets are aligned with this plane. So, precession, nutation, and polar motion vary the gravity forces over time.A project team I'm involved with is trying to put a hypothetical satellites in a polar orbit around mars. So, although I disabled all the perturbations but $J_2$, there is still precession, nutation, and polar motion, which changed slightly the ECEF attitude with respect to ECI. So, once the user defines the orbital elements, they are transformed to ECI coordinates, then the gravity perturbations are calculated in ECEF and transformed to ECI, and the integration is in ECI.

Astrodynamics calculator omega inclination professional#

Professional programs like STK and GMAT use the latter expression. $$[\bar$ is the geocentric latitude, and $r_I$,$r_J$,$r_K$ are expressed in ECEF. Both spacecraft have the same initial mean orbital elements: This time I propagated 2 spacecraft in a $J_2$ gravity field (gravity degree 2 and gravity order 0, no higher gravitational harmonics, no drag, no sun radiation pressure, no third bodies).

Astrodynamics calculator omega inclination software#

As a continuation of my previous post regarding the use of the software GMAT (General Mission Analysis Tool) ( website, YouTube) for propagating spacecraft, I have an additional question.