An academic tool intended to assist in developing an intuitive understanding of aircraft design.

Spatial math primitives for MATLAB

Access PX4 autopilot peripherals with UAV Toolbox and automatically build and deploy flight control algorithms with Embedded Coder

Toolbox for angle, coordinate and date conversions and transformations. Version 2.99.

The SGP4 model to calculate orbital state vectors of near-Earth satellites

Precise modeling of satellite's perturbed motion (special perturbations approach)

Ephemeris Data for Aerospace Toolbox

Standard atmosphere gas properties. Support for n-dim inputs, non-standard atmospheres, units, etc.

Vortex Lattice Mehod for steady aerodynamics

Satellite Orbits: Models, Methods and Applications

Xfoil rewritten as MATLAB script

Simulink library of aircraft models

Modeling of satellite's perturbed motion (special perturbations approach)

2-D nozzle using the method of characteristics and CFD on nozzle on curvilinear mesh.

Case Study for DO-178 using MathWorks tools

drawDATCOMaircraft generates an aircraft's thre view drawings from given DATCOM input files.

Geoid Data for Aerospace Toolbox

Given a deflection angle, mach number, and ratio of specific heats, this function returns Beta.

Calculates Temperature, Pressure, Density, Speed of Sound, Gravity, Dynamic/Kinematic Viscosity, k,

Opens LiDAR point data from LAS files. Supports versions up to 1.4.

This GUI lets you plot orbits around Earth interactively.

Transformation from celestial to terrestrial reference system and vice versa

This support package allows you to customize scenes in the Unreal^® Editor and use them in Simulink^®.

Determines visibility times from observer location for specified period. LLA and KML output.

Enables operations using hundreds of supported physical units of measurement and physical constants.

Solves weighted absolute orientation problem using Horn's quaternion-based method.

This code solves the oblique shock wave relations for mach, wedge angle, or shock angle.

Forward Dynamics of Planar 2-DOF Robot Manipulator for continuous time function input tau's and discrete time function input tau's

Main Program to view keplerian orbit (3D) and the ground-track

Wing Designer computes aircraft performance measures from wing and engine parameters.

Computation of neutral temperature and densities in Earth's atmosphere from ground to thermospheric heights.

Source Panel Method applied to Flow around Cylinder. Example 3.19 from Anderson's book

Convert orbital elements to a state vector, or a state vector back to orbital elements.

Read satellite ephemeris data from a NORAD two-line element (TLE) file.

Computes characteristics for coplanar and non-coplanar Hohmann transfers.

This potential flow simulator simulates the flow past bodies of arbitrary shape including airfoils.

quaternion class, vectorized, converts among rotation representations, numerical Euler propagation

variation on the SPHERE command to facilitate plotting of orbital trajectories

This function plot in the same figure the center trajectory and attitude of an aircraft.

Modified SGP4 code for GPS interface

A small but handy tool to quickly explore, analyse and compare airfoil geometry

This function plot in the same figure the center trajectory and attitude of an aircraft.

6-DOF Nonlinear Simulation of Aircraft Flight

Animation of aircraft LQR pitch control system

Generates the NACA 5 digit airfoil coordinates

Convert latitude, longitude,altitude to earth-centered, earth-fixed (ECEF) cartesian coordinate.

Compute and plot characteristics of the circular-restricted three-body problem.

Mohr's circle for a general three-dimensional state of stresses

Computes coherent and spontaneous Rayleigh-Brillouin spectra using s6 (Tenti) or s7 (Pan) models

A set of routines to make carpet plotting easier.

companion software for book

Computation of the total mass-desnity of atmosphere using Jacchia-Bowman model

compute gas turbine engine performance under varying operating condition.

A GUI software I made to calculate the carrier-to-noise-density ratio of a earth-satellite link.

Visualize Classical Orbital Elements

Integrate n-body trajectories from the Earth to the Moon. Includes non-spherical Earth gravity.

Implementation of Levy's flight

Generates an airfoil shape using CST method

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

Orbit Determination from Tracking and Data Relay Satellite Measurements