Ecosyste.ms: Awesome
An open API service indexing awesome lists of open source software.
https://github.com/nsarrazin/astropynamics
A pure Python library to solve common orbital mechanics problem
https://github.com/nsarrazin/astropynamics
numpy orbital-mechanics plotly python3
Last synced: 19 days ago
JSON representation
A pure Python library to solve common orbital mechanics problem
- Host: GitHub
- URL: https://github.com/nsarrazin/astropynamics
- Owner: nsarrazin
- Created: 2017-09-29T20:12:58.000Z (about 7 years ago)
- Default Branch: master
- Last Pushed: 2017-10-01T18:32:43.000Z (about 7 years ago)
- Last Synced: 2024-12-03T13:26:02.235Z (22 days ago)
- Topics: numpy, orbital-mechanics, plotly, python3
- Language: Python
- Size: 18.6 KB
- Stars: 9
- Watchers: 3
- Forks: 1
- Open Issues: 0
-
Metadata Files:
- Readme: README.md
Awesome Lists containing this project
README
# AstroPynamics
A pure Python library to solve common orbital mechanics problem
## Orbit definition
### Basic class methods
The Orbit class includes a few class methods which allows for fast and easy Orbit generation.
Regardless of the input elements all orbits requires the following inputs :
* primBody = a Body object used to determine the gravitational parameter
* name = Every orbit created needs a name
#### fromElements
This uses the basic set of keplerian elements :
* Semi-major Axis (a)
* Eccentricity (e)
* Inclination (i)
* Longitude of the ascending node (lAn)
* Argument of Periapsis (aPe)
* True Anomaly (tAn)
```python
from orbits.orbit import Orbit
from examples import Sun
import numpy as np
earthOrbit = Orbit.fromElements(a=149597887.1558, e=0.01671022, i = np.radians(0.00005), lAn = np.radians(348.7394), primBody=Sun, aPe=np.radians(114.2078), tAn=6.23837308813, name="Earth Orbit")
print(earthOrbit)
```
Which prints :
```
ID - Earth Orbit
primBody - Sun
a - 149597887.1558
e - 0.01671022
i - 8.726646259971648e-07
lAn - 6.086650761429513
aPe - 1.99330214145918
tAn - 6.23837308813
epoch - 2000-01-01 00:00:00.000
````
#### fromApsis
fromApsis replaces the semimajor axis and the eccentricity by the height of the Apoapsis (hPa) and Periapsis (hPe)
```python
marsOrbit = Orbit.fromApsis(hPa = 247644270.465, hPe=220120745.788, i = np.radians(1.85061), lAn = np.radians(49.57854), primBody=Sun, aPe=np.radians(286.4623), tAn=0.40848952017, name="Mars Orbit")
print(marsOrbit)
```
Which prints :
```
ID - Mars Orbit
primBody - Sun
a - 233882508.1265
e - 0.05884049409567938
i - 0.03229923767033226
lAn - 0.8653087613317094
aPe - 4.999710317835753
tAn - 0.40848952017
epoch - 2000-01-01 00:00:00.000
```
#### fromStateVector
This replaces the set of keplerian elements by a position 3D vector and a velocity 3D vector
```python
from examples import Earth
testOrbit = Orbit.fromStateVector((-6045, -3490, 2500), (-3.457, 6.618, 2.533), primBody=Earth, name = "State Vector Demo")
print(testOrbit)
```
Which prints :
```
ID - State Vector Demo
primBody - Earth
a - 8788.081767279667
e - 0.17121118195416898
i - 2.6747036137846094
lAn - 4.455464041223287
aPe - 0.35025511728002945
tAn - 0.496472955354359
epoch - 2000-01-01 00:00:00.000
```
### Universal multi-rev Lambert solver
Orbits can also be generated using a multi revolution universal Lambert solver. It uses the following inputs:
* r1 - 3D position vector
* r2 - 3D position vector
* tof - Time of flight between r1 and r2 in seconds
And the following are optional :
* nRev - The number of full revolution completed (default is 0)
* DM - The direction of motion, if left empty the solver will determine the optimal one
```python
lambertDemo = Orbit.fromLambert((5000,10000,2100), (-14600,2500,7000), 3600, primBody=Earth, name="Lambert Demo")
print(lambertDemo)
```
Which will output :
```
ID - Lambert Demo
primBody - Earth
a - 20002.884935993607
e - 0.4334874513211504
i - 0.5269331332631371
lAn - 0.7784202841672524
aPe - 0.535923312928038
tAn - 6.123135458171056
epoch - 2000-01-01 00:00:00.000
```
The universal solver also supports hyperbolic trajectory :
```python
from orbits.hyperbola import Hyperbola
lambertDemo = Hyperbola.fromLambert((5000,10000,2100), (-14600,2500,7000), 1500, primBody=Earth, name="Lambert Hyperbola")
print("SMA - {}, eccentricity - {}".format(lambertDemo.a, lambertDemo.e))
```
Will output :
```
SMA - -2918.7342956582274, eccentricity - 4.215326772456562
```
It also supports multi-rev generation :
## Plotting
### plotlyManager
TODO
### Plotting body
TODO
### Plotting orbits
TODO
### Plotting points
TODO
### Animation
TODO
## Maneuvers
## Trajectory optimization
### getC3
### Porkchop Generator