Recent content by Keithth G

I've just run this scenario through ADSWNJ's Lagrange MFD for an arbitrary date and this is what I get for EML1: Day 0 0.007 km Day 1 0.048 km Day 2 0.093 km Day 3 0.033 km Day 4 0.176 km Day 5 0.445 km Day 6 0.706 km Day 7 1.105 km Day 8 1.994 km Day 9 3.654 km Day 10...

Thanks, 'Ajaja' Equation (10) gives the standard fifth-order polynomial for 'u' (to use the paper's notation). This polynomial equation is actually valid for both the circular and elliptic three-body theories of Lagrange points - although the paper deals with the former, and not the later...

Hi, 'Ajaja' What is the underlying physical theory of your Lagrange points MFD? Is it CR3BP or the ER3BP? ASDWNJ's Lagrange MFD is based on the latter. From experience, I know that if placed at L1 or L2 of the Earth-Moon system in Lagrange MFD, a vessel will noticeably drift off onto the...

Hi, 'malcontent', to do the scaling, you need to set a scale for mass, distance and time. Suppose 'M' is the mass of the gravitating body (in your case, the Earth); 'T' is the orbital period; and 'R' is the radius of the much smaller secondary body (the Moon) from the primary body (the Earth)...

Hi, 'malcontent' I've been following this thread off and on for the last few weeks. Here's an approach to your problem that you may want to consider. As I understand it, you have developed an integration engine that reproduces a normal Keplerian (i.e., circular, elliptical, parabolic or...

In response to a request from 'dgatsoulis', here are some links to a short series on direct transfer from a (coplanar) Low Earth Orbit to Earth-Moon L2. Part 1: Part 2: Part 3:

In response to a request posted on Youtube, here is a linked to Part 1 of a short video series demonstrating an off-plane transfer from the ISS to EML1. ---------- Post added at 09:41 AM ---------- Previous post was at 09:29 AM ---------- And, finally, Part 3: Enjoy.

And here is a short video demonstrating the effectiveness of the maths set out earlier in this thread to determine the correct parameters for very low-thrust orbit insertion burns. A Shuttle A, with modified low thrust (9000 N) main engines, in a high eccentricity lunar approach orbit...

This post is a largely technical note that continues an exploration of the Ideal Rocket Equation in a perturbed Keplerian gravitational field. It is a continuation of an earlier post entitled "A Generalised Ideal Rocket Equation" in the Maths & Physics section of the Orbiter Forum. These notes...

Although I'm not trying to connect Matlab to Orbiter, I am trying to connect Mathematica to Orbiter. I have the web version of Orb::Connect installed and it works just fine in a browser. But I am trying to connect via lower level HTTP PUSH requests as per the Orb::Connect documentation. This...

Enjo - note that I've added a small piece of code that solves Kepler's equation to find 'r' from BTC's initial estimate of the time before periapsis that the orbit insertion burn should start. Let me know if you have questions.

Enjo, try 'kpgelling'. Thanks.

Enjo Thanks. No spare time at the moment to tinker with this. I may have some Thursday/Friday. Regards

Enjo Thanks. Sunday evening here in HK. I'll have a look at the code tomorrow and post comments. wrt licenses: I'm fine with anything you are fine with. ---------- Post added 11-07-16 at 02:59 AM ---------- Previous post was 11-06-16 at 12:20 PM ---------- No, not familiar with...

Yes, and no. Not all Keplerian cleverness disappears with the introduction of perturbations. Out to the edge of the Earth's SOI at least, the Sun's gravitational contribution is effectively a small, tidal contribution. The real problem is one of time-scale: the spacecraft will spend a long...