TLI Orbit Slice View

A plot of the Apollo TLI orbit showing the transition through the Van Allen Belts. This time I've taken a slice along the plane of the orbit to shown how it transitions through the various zones.


The belts are shown in the following contours Blue=0.0001 rads/sec; green 0.001 rads/sec; yellow 0.005 rads/sec; orange 0.01 rads/sec; red 0.05 rads/sec. These levels are for an unprotected target in open space. Total transit time across the blue zone is approximately 90 minutes.

Thanks again to the Bob B for doing the maths to plot the orbit based on the Apollo TLI data.

Category:

Science & Technology

Tags:

• TLI
• Orbit
• Slice
• View
• apollo

[roamingcroat]

@daenumen Right then. I'll just go ahead and take that as an admission of the fact that you haven't the foggiest idea about orbital mechanics.

[daenumen]

@roamingcroat what integrator?

[ApolloWasReal]

@roamingcroat Thanks, you said exactly what I was going to say: if he doesn't realize that orbit integrators start with orbital elements or state vectors, then it's obvious he doesn't know anything at all about the subject.

[roamingcroat]

@daenumen Crikey, how could he start his integrator without your elements? How on Earth would he test *your* trajectory if he doesn't have *your* initial conditions?

Alright, enough of this charade, why can't you just admit you're wrong about the trajectory? Can't you just admit you don't know the first thing about orbital mechanics? There's nothing wrong with that - a lot of people don't. Otherwise, I'm reminded of a certain quote by Mark Twain about opening one's mouth...

[daenumen]

@ApolloWasReal conclude whatever you like, you already have been!

[daenumen]

@ApolloWasReal you shouldnt need them to start your integrator.

[ApolloWasReal]

@daenumen Um, that should have been "I need them to START my integrator". It will then compute the complete spacecraft trajectory starting with the TLI you propose. If it shows the spacecraft reaching the moon in less time and with less delta-V than Apollo/Saturn, it will confirm your claim.

Of course I don't think that's very likely, but go ahead and surprise us.

[ApolloWasReal]

@daenumen Huh? We're all waiting with bated breath for your orbital elements that can get to the moon substantially faster and with less delta-V than Apollo with the Saturn V by ignoring the VA belts. I need them to star my integrator.

As you know, none of us think this is possible. But if you'd like to prove us wrong, please be my guest. Otherwise we'll just conclude that your reluctance to provide them proves that you know you can't do it and are simply unwilling to acknowledge that fact.

[daenumen]

@ApolloWasReal well you wont need my elements then, ill let you tell 'the others'.

[ApolloWasReal]

@daenumen I don't know about you, but I've been working on a state vector propagator (basically a numerical integrator) that can take either a TLE or an initial state vector and run it forward in time and see what happens. The reason for using numerical integration is so I can take all the non-2-body forces into account, including most notably lunar gravity but also solar gravity (or its gradient across the earth/moon system) and the earth's nonspherical shape.

So let's see your TLE.