orbit | Python package for Bayesian forecasting | Predictive Analytics library

I am trying to solve a low thrust optimal control problem for Earth orbits, i.e. going from one orbit to another. The formulation of the problem includes six states (r_1, r_2, r_3, v_1, v_2, v_3) and 3 controls (u_1, u_2, u_3) with a simplified point model of gravity. When I specify the full initial state and half of the final state, the solver converges and yields a good solution. When I try the full final state, the problem is over constrained.

My thought on how to remedy this is to allow the trajectory to depart the initial orbit at any point along the orbital curve and join the final orbit an any point along the final orbital curve, giving it more degrees of freedom. Is there a way to constrain the initial and final values of all 6 states to a cspline curve? This is what I have tried so far:

I'm really struggling here and I can't get it right, not even knowing why. I'm using p5.js in WEBGL mode, I want to compute the position of on point rotated on the 3 axes around the origin in order to follow the translation and the rotation given to object through p5.js, translation and rotatation on X axis, Y axis and Z axis.

The fact is that drawing a sphere in 3d space, withing p5.js, is obtained by translating and rotating, since the sphere is created at the center in the origin, and there is no internal model giving the 3d-coordinates.

After hours of wandering through some math too high for my knowledge, I understood that the rotation over 3-axis is not as simple as I thought, and I ended up using Quaternion.js. But I'm still not able to match the visual position of the sphere in the 3d world with the coordinates I have computed out of the original point on the 2d-plane (150, 0, [0]).

For example, here the sphere is rotated on 3 axis. At the beginning the coordinates are good (if I ignore the fact that Z is negated) but at certain point it gets completely out of sync. The computed position of the sphere seems to be completely unrelated:

It's really hours that I'm trying to solve this issue, with no result, what did I miss?

Here it follows my code:

in my program I defined a data type called Lyapunov_orbit that contains 8 fields, then I used it to read data from external .txt file (see below where I report only a few lines for convenience because the file has about 4000 lines). I need to perform some operations by using such structure (as to find minimum and maximum value of an array) but to handle it I had to declare an "auxiliary" variable called vec_J_cst because if I try to directly use my data strucutre, I get some errors (the structure-name is invalid or missing).

Here is the .txt file:

I have permission to modify this executable.

A game called Emperor of the Fading Suns has spaceships in it. When you launch into orbit with a specific ship, said ship lose one movement point. Game\OllyDB DEC BYTE PTR DS:[EAX+2F] reduces movement points by one

I want to alter this so that you have 0 movement points left.

I have tried a lot of stuff, but the reality is that I simply don't have enough experience to understand what I need to overwrite (assemble) in order to achieve 0 movement point per takeoff. Changing out DEC with INC works.

My beginning strategy went to this: MOV BYTE PTR DS:[EAX+2F], 0
(I am a novice at assembly)

Longer list of code for context:

Thanks for the tip, I'm really excited about making this a function so I don't have words to describe how happy I am for anyone to tell me how to do this. If there is additional info required then I'll post a longer version and link to it.

I have a multi module project with a plugin and fragment to test this plugin. The build is done through maven/tycho. Maven v.3.8.4 and Tycho v2.6.0.

In the fragment I have 3 Unit and 1 Integration test, in the test folder:

I use the following code in order to get the city the iss is flying over. I used the code from the astro-pi tutorial(https://projects.raspberrypi.org/en/projects/code-for-your-astro-pi-mission-space-lab-experiment/2):

I have a animation of an orbit written in python. I want a legend that the label is a time "dt". This time updates (increases) along the orbit. For example, in the first frame of the gif the legend should be "dt", in the second, dt + dt and so on. I tried something that didn't work. Maybe I'm not using the correct commands. The error that appearas: TypeError: __init__() got multiple values for argument 'frames' . Does someone know how to do this legend? The code is above.

I'm trying to create a basic scene with an orbitercontrols that can rotate around the center, i.e. always looking at (0,0,0). I want it to behave like this https://threejs.org/examples/misc_controls_orbit.html exactly. But in my version if I click and drag to the left/right, the camera just spins in a circle always looking at (0,0,0). How can I fix this?

I'm trying to make a tiny solar system in java with simple orbits (no gravity or anything fancy).

I want: A moon orbiting around a planet, orbiting around a sun.

My issue: The "moon" has an eliptical orbit instead of an circular one.

The code i use: