orbital | A simple end-to-end testing framework for Go | Unit Testing library

I want to center the column in the middle of my table so that the table header "Information" is centered exactly beneath the h2 header "His career". I have found out that the table is centered, but column 1 is wider than column 3:

I thought that this

I’m learning python and dash and I’m building an application for monitoring my trading.

I’ve adapted the code from : “Live Updating Components” example (Orbital Satellite). It works well on jupyter notebook and repl.it but I have an error when I try it on my computer :

"Traceback (most recent call last): File "orbital.py", line 62, in Input('interval-component', 'n_intervals'))"

“The input argument interval-component.n_intervals must be a list or tuple of dash.dependencies.Inputs.”

I don’t understand why

Here is my code :

I created a simple view designed to show the content of an array that is stored in an Observable Object property:

I made a line mesh with elliptical shape, representing the orbit wiht eccentricity e, and semi-major axis a. The mesh is a child of a group called orbitGroup that contains other objects. Also, I added a gui to change this parameters. Every time gui changes it calls the next function:

I have a function that takes orbital parameters and texture images from a dataset and creates a 3d object (a planet). However for some reason textures aren't being rendered. Using BasicMaterial it works normally, but not with StandardMaterial or PhongMaterial. (There is a point light in the scene), I already tested the textures outside the loop and the function, they work nice. I don´t know what else to do. I let here the code.

I'm in a project in my University and I have to implement the Runge-Kutta 4-order integrator using Python. I know I can use for example Sympy, but the goal here is implement the method, the code is ready written in Fortran language, so basically I have a data base with the correct values of solutions and I have to get similar solutions in my code. However, we have some problems; I did the same several times using linear equations ( first and second order ), however this is a second order nonlinear equation from Newton universal law of gravitation. The code has no error, my problem is what my code is doing wrong that I cannot get the right results.

Below I'll show some of the expected values and the ones i'm getting, after them I'll show the code.

I'd be really pleasured if someone could help me.

RIGHT RESULTS (expected results)

Hi all I am working on rocket trajectory optimization with Dymos. The equations of motion for my model are for a spherical non-rotating Earth

where v is speed of the rocket, gamma is the flightpath angle to local horizontal, h is height above surface, theta is angle along the great circle of the trajectory, m is mass, epsilon is angle of attack, T is trust, D is drag, L is lift. These are quite similar to the equations of motion in the Dymos water rocket example. I used check_partials and my analytic derivatives seem to be correct.

As you can see gamma's rate of change is divided by v, so you have a singularity where v=0 at the beginning of the trajectory. You can get around that by starting v at some small number that's a small fraction of the intended final velocity -- like 1 to m/s for an orbital rocket.

However, the lower I set my initial velocity, the harder I can see the optimizer and grid refinement needs to work to get to a converged solution. For example,

setting final conditions of h=200 km, v= 7668 m/s and gamma=0 (a circular orbit), with v initial = 10 m/s, I have to start with 20 segments of order 6 to be able to reach convergence, and the final grid is like this

Number of Segments = 25 Segment Ends = [-1.0, -0.9833, -0.9667, -0.95, -0.9333, -0.9, -0.85, -0.8, -0.7, -0.6, -0.5, -0.4, -0.3, -0.2, -0.1, 0.0, 0.1, 0.2, 0.3, 0.4, 0.5, 0.6, 0.7, 0.8, 0.9, 1.0] Segment Order = [9, 9, 9, 9, 9, 9, 9, 9, 6, 6, 6, 6, 6, 6, 6, 6, 6, 6, 6, 6, 6, 6, 6, 6, 6]

The optimization time on this converged grid is 45 seconds

if I use v_initial = 1000 m/s, same final conditions, and a starting grid of 20 segments of order 3, the final grid is

Segment Ends = [-1.0, -0.95, -0.9, -0.8, -0.7, -0.6, -0.4, -0.2, 0.0, 0.2, 0.4, 0.6, 0.8, 1.0] Segment Order = [6, 6, 6, 6, 6, 3, 3, 3, 3, 3, 3, 3, 3]

the optimization time on the converged grid is 3.18 seconds.

Given the way grid points are being concentrated towards the beginning of the trajectory makes me think that the singularity in gamma_dot caused by v is the problem.

What can I do to improve performance?

I'm trying to embed an orbital simulation into a tkinter frame, I have the plot working properly I am now just trying to input circles into the graph to represent planets. I have had a look for documentation on how to draw circles in FigureCanvasTkAgg but can't find anything and was hoping someone could help.

Here's the code:

Context: I am not sure if this is the right site to post this question, please let me know if it isn't. My aim is to solve the coupled differential equations given in the code for the Alpha Centauri star system.

Code: