https://github.com/abdalazezahmed/oribital-mechanics-matlab
Some Orbital Mechanics Matlab Codes. Heavily based on the "Orbital Mechanics for Engineers, Howard D. Curtis" book.
https://github.com/abdalazezahmed/oribital-mechanics-matlab
ground-track matlab orbit-determination orbit-propagation orbit-propagators orbital-mechanics orbital-simulation two-body-problem two-body-simulation
Last synced: 2 days ago
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Some Orbital Mechanics Matlab Codes. Heavily based on the "Orbital Mechanics for Engineers, Howard D. Curtis" book.
- Host: GitHub
- URL: https://github.com/abdalazezahmed/oribital-mechanics-matlab
- Owner: AbdAlazezAhmed
- License: gpl-3.0
- Created: 2022-01-09T15:08:15.000Z (over 3 years ago)
- Default Branch: main
- Last Pushed: 2023-04-17T21:32:08.000Z (about 2 years ago)
- Last Synced: 2025-03-24T10:05:36.041Z (3 months ago)
- Topics: ground-track, matlab, orbit-determination, orbit-propagation, orbit-propagators, orbital-mechanics, orbital-simulation, two-body-problem, two-body-simulation
- Language: MATLAB
- Homepage:
- Size: 149 KB
- Stars: 7
- Watchers: 1
- Forks: 2
- Open Issues: 0
-
Metadata Files:
- Readme: README.md
- License: LICENSE
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README
# Oribital-Mechanics-Matlab
Some Orbital Mechanics Matlab Codes. Heavily based on the "Orbital Mechanics for Engineers, Howard D. Curtis" book.
## Orbit Initialization
---
You can initialize an Orbit in these ways depending on the available input/initial conditions:
* **$R_0$ and $V_0$**
* **Orbital Elements**
* **Two Line Elements *(TLE)***
* **Orbit Determination**
* **GIBBS**
You must choose the method used to solve for future epochs from:
* **Kepler Equation**
* **Cowell Method**
You can specify the time-span of the calculation using the `dt` arguement
### Code Example
* An **Orbit** with **Orbital Elements** of the starting state and **Kepler Equation** as the solving method:
```matlab
orb1 = Orbit('OE','f(t)',r_p = 6700,r_a = 10000,...
theta_0 = 230*pi/180, Omega_0 = 270*pi/180,i = 60*pi/180,...
omega_0 = 45*pi/180, dt = 5.1610e5);
```
* An **Orbit** with **$R_0$ and $V_0$** of the starting state and **Cowell Method** as the solving method with **Atmospheric Drag** effect :
```matlab
orb2 = Orbit('RV','Cowell',drag = true,R_0 = [-3670,-3870,4400],V_0 = [4.7,-7.4,1], dt = 5.1610e5);
```
* An **Orbit** with **Two Line Elements *(TLE)*** of the starting state and **Kepler Equation** as the solving method:
```matlab
orb3 = Orbit('TLE','f(t)',drag = false,tle='ISS.txt', dt = 5.1610e5);
```
* An **Orbit** with **GIBBS** method used to determine the starting state and **Kepler Equation** as the solving method:
```matlab
orb4 = Orbit('GIBBS','f(t)',R1 = [-294.32,4265.1,4265.1],...
R2 = [ -1365.5,3637.6,6346.8],R3 = [-2940.3,2473.7, 6555.8], dt = 5.1610e4);
```
## Solving Orbit
---
To solve the orbit problem call the `solveOrbit()` method
### Code Examples
```matlab
orb3 = orb3.solveOrbit();
```
## Plotting Ground Tracks
---
To plot the **Ground Tracks** use the `plot()` method
For 3D tracks use `plot3()` method
### Code Examples
For plotting **Ground Tracks**:
```matlab
orb3.plot();
```
For plotting 3D tracks:
```matlab
orb3.plot3();
```
## Orbit Perturbation
---
This code takes in consideration **J2** perturbation
with optional terms being :
- **Atmospheric Drag**
# Progress
### Todo
- [ ] Clean the class code
- [ ] Improve Orbit Transfer code, use the method in chapter 6, and write its Documentation
### Done ✓
- [x] Working code foundation *(tested on the textbook's examples)*.