Orbit

Gravity fun in java

The following java project contains the java source code and java examples used for gravity fun. Little planets orbitting around bigger ones, Uses gravitational acceleration formulas to orbit planets. This is just a fun project I did quickly so dont expect it to be perfect. (I scaled the sun down so all the other planets wouldn't just be specs)

Calculates eccentric anomaly given mean anomaly and eccentricity of an elliptical orbit. in matlab

The following Matlab project contains the source code and Matlab examples used for calculates eccentric anomaly given mean anomaly and eccentricity of an elliptical orbit. . Since the eccentric anomaly cannot be directly calculated from certain given values, this function performs a simple Newton-Raphson iteration to solve for the eccentric anomaly within a given tolerance (default 10^-8 radians).

Astrodynamics and flight mechanics functions library. in matlab

The following Matlab project contains the source code and Matlab examples used for astrodynamics and flight mechanics functions library. . Keplerian orbits, elliptical, parabolic, hyperbolic orbits, elements conversion. Temporal problem, mean anomaly, eccentric anomaly, true anomaly. MOID. Orbits plot. Position and velocity vectors. Orbital maneuvers: Lambert problem solution, delta-v computation, optimal time-free orbital transfer, optimal multi flyby mission.

Circular restricted three body problem (crtbp) sun earth moon (using symbolic toolbox) in matlab

The following Matlab project contains the source code and Matlab examples used for circular restricted three body problem (crtbp) sun earth moon (using symbolic toolbox). Analysis and simulation of orbits in the circular-restricted three-body problem (CRTBP), where primary and secondary bodies move in circular orbits about the common center of mass, and effect of gravitational attraction of the smallest body are ignored.

The circular restricted three body problem in matlab

The following Matlab project contains the source code and Matlab examples used for the circular restricted three body problem. This is a special case of the general three-body problem where the primary and secondary bodies move in circular orbits about the common center of mass, and the effect of the gravitational attraction of the smallest body and any other perturbations such as solar radiation pressure are ignored.

Single impulse de orbit in matlab

The following Matlab project contains the source code and Matlab examples used for single impulse de orbit. PDF document and MATLAB scripts for computing the characteristics of single impulsive maneuvers required to de-orbit from circular and elliptical Earth orbits. These scripts also provide simple graphic displays of the de-orbit trajectory.

Repeating ground track orbit design in matlab

The following Matlab project contains the source code and Matlab examples used for repeating ground track orbit design. Scripts include (1) time to repeat ground track (nodal period) using Kozai orbit propagation, (2) time to repeat ground track using numerical integration (3) required mean semimajor axis using Wagner's algorithm and (4) required osculating semimajor axis using numerical integration.

Determine arrival velocity of a orbiting object in matlab

The following Matlab project contains the source code and Matlab examples used for determine arrival velocity of a orbiting object . This function determines the arrival velocity of an orbit for a given initial position and velocity and arrival position Inputs:   r1 - initial position   v1 - initial velocity   r2 - arrival position   mu - gravitational parameter Outputs:   v2 - arrival velocity The units of the input variables must agree.

Simulated annealing algorithm for finding periodic orbits in matlab

The following Matlab project contains the source code and Matlab examples used for simulated annealing algorithm for finding periodic orbits. In [CNSNS 16, 2845 (2011)] we propose a method which extends this basin of attraction of standard Newton-based methods to determine periodic orbits by use of systematized trial and error converging procedure.
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