## Documentation Center |

By Category | Alphabetical List

1D Controller [A(v),B(v),C(v),D(v)] | Implement gain-scheduled state-space controller depending on one scheduling parameter |

1D Controller Blend u=(1-L).K1.y+L.K2.y | Implement 1-D vector of state-space controllers by linear interpolation of their outputs |

1D Observer Form [A(v),B(v),C(v),F(v),H(v)] | Implement gain-scheduled state-space controller in observer form depending on one scheduling parameter |

1D Self-Conditioned [A(v),B(v),C(v),D(v)] | Implement gain-scheduled state-space controller in self-conditioned form depending on one scheduling parameter |

2D Controller [A(v),B(v),C(v),D(v)] | Implement gain-scheduled state-space controller depending on two scheduling parameters |

2D Controller Blend | Implement 2-D vector of state-space controllers by linear interpolation of their outputs |

2D Observer Form [A(v),B(v),C(v),F(v),H(v)] | Implement gain-scheduled state-space controller in observer form depending on two scheduling parameters |

2D Self-Conditioned [A(v),B(v),C(v),D(v)] | Implement gain-scheduled state-space controller in self-conditioned form depending on two scheduling parameters |

3D Controller [A(v),B(v),C(v),D(v)] | Implement gain-scheduled state-space controller depending on three scheduling parameters |

3D Observer Form [A(v),B(v),C(v),F(v),H(v)] | Implement gain-scheduled state-space controller in observer form depending on three scheduling parameters |

3D Self-Conditioned [A(v),B(v),C(v),D(v)] | Implement gain-scheduled state-space controller in self-conditioned form depending on two scheduling parameters |

3DOF (Body Axes) | Implement three-degrees-of-freedom equations of motion with respect to body axes |

3DOF (Wind Axes) | Implement three-degrees-of-freedom equations of motion with respect to wind axes |

3DoF Animation | Create 3-D MATLAB Graphics animation of three-degrees-of-freedom object |

3x3 Cross Product | Calculate cross product of two 3-by-1 vectors |

4th Order Point Mass (Longitudinal) | Calculate fourth-order point mass |

4th Order Point Mass Forces (Longitudinal) | Calculate forces used by fourth-order point mass |

6DOF (Euler Angles) | Implement Euler angle representation of six-degrees-of-freedom equations of motion |

6DOF (Quaternion) | Implement quaternion representation of six-degrees-of-freedom equations of motion with respect to body axes |

6DoF Animation | Create 3-D MATLAB Graphics animation of six-degrees-of-freedom object |

6DOF ECEF (Quaternion) | Implement quaternion representation of six-degrees-of-freedom equations of motion in Earth-centered Earth-fixed (ECEF) coordinates |

6DOF Wind (Quaternion) | Implement quaternion representation of six-degrees-of-freedom equations of motion with respect to wind axes |

6DOF Wind (Wind Angles) | Implement wind angle representation of six-degrees-of-freedom equations of motion |

6th Order Point Mass (Coordinated Flight) | Calculate sixth-order point mass in coordinated flight |

6th Order Point Mass Forces (Coordinated Flight) | Calculate forces used by sixth-order point mass in coordinated flight |

Acceleration Conversion | Convert from acceleration units to desired acceleration units |

Adjoint of 3x3 Matrix | Compute adjoint of matrix |

Aerodynamic Forces and Moments | Compute aerodynamic forces and moments using aerodynamic coefficients, dynamic pressure, center of gravity, center of pressure, and velocity |

Angle Conversion | Convert from angle units to desired angle units |

Angular Acceleration Conversion | Convert from angular acceleration units to desired angular acceleration units |

Angular Velocity Conversion | Convert from angular velocity units to desired angular velocity units |

Besselian Epoch to Julian Epoch | Transform position and velocity components from discontinued Standard Besselian Epoch (B1950) to Standard Julian Epoch (J2000) |

Calculate Range | Calculate range between two crafts given their respective positions |

Centrifugal Effect Model | Implement mathematical representation of centrifugal effect for planetary gravity |

CIRA-86 Atmosphere Model | Implement mathematical representation of 1986 CIRA atmosphere |

COESA Atmosphere Model | Implement 1976 COESA lower atmosphere |

Create 3x3 Matrix | Create 3-by-3 matrix from nine input values |

Crossover Pilot Model | Represent crossover pilot model |

Custom Variable Mass 3DOF (Body Axes) | Implement three-degrees-of-freedom equations of motion of custom variable mass with respect to body axes |

Custom Variable Mass 3DOF (Wind Axes) | Implement three-degrees-of-freedom equations of motion of custom variable mass with respect to wind axes |

Custom Variable Mass 6DOF (Euler Angles) | Implement Euler angle representation of six-degrees-of-freedom equations of motion of custom variable mass |

Custom Variable Mass 6DOF (Quaternion) | Implement quaternion representation of six-degrees-of-freedom equations of motion of custom variable mass with respect to body axes |

Custom Variable Mass 6DOF ECEF (Quaternion) | Implement quaternion representation of six-degrees-of-freedom equations of motion of custom variable mass in Earth-centered Earth-fixed (ECEF) coordinates |

Custom Variable Mass 6DOF Wind (Quaternion) | Implement quaternion representation of six-degrees-of-freedom equations of motion of custom variable mass with respect to wind axes |

Custom Variable Mass 6DOF Wind (Wind Angles) | Implement wind angle representation of six-degrees-of-freedom equations of motion of custom variable mass |

Density Conversion | Convert from density units to desired density units |

Determinant of 3x3 Matrix | Compute determinant of matrix |

Digital DATCOM Forces and Moments | Compute aerodynamic forces and moments using Digital DATCOM static and dynamic stability derivatives |

Direction Cosine Matrix Body to Wind | Convert angle of attack and sideslip angle to direction cosine matrix |

Direction Cosine Matrix Body to Wind to Alpha and Beta | Convert direction cosine matrix to angle of attack and sideslip angle |

Direction Cosine Matrix ECEF to NED | Convert geodetic latitude and longitude to direction cosine matrix |

Direction Cosine Matrix ECEF to NED to Latitude and Longitude | Convert direction cosine matrix to geodetic latitude and longitude |

Direction Cosine Matrix ECI to ECEF | Convert Earth-centered inertial (ECI) to Earth-centered Earth-fixed (ECEF) coordinates |

Direction Cosine Matrix to Quaternions | Convert direction cosine matrix to quaternion vector |

Direction Cosine Matrix to Rotation Angles | Convert direction cosine matrix to rotation angles |

Direction Cosine Matrix to Wind Angles | Convert direction cosine matrix to wind angles |

Discrete Wind Gust Model | Generate discrete wind gust |

Dryden Wind Turbulence Model (Continuous) | Generate continuous wind turbulence with Dryden velocity spectra |

Dryden Wind Turbulence Model (Discrete) | Generate discrete wind turbulence with Dryden velocity spectra |

Dynamic Pressure | Compute dynamic pressure using velocity and air density |

Earth Nutation | Implement Earth nutation |

ECEF Position to LLA | Calculate geodetic latitude, longitude, and altitude above planetary ellipsoid from Earth-centered Earth-fixed (ECEF) position |

ECI Position to LLA | Convert Earth-centered inertial (ECI) coordinates to geodetic latitude, longitude, altitude (LLA) coordinates |

EGM96 Geoid | Calculate geoid height as determined from EGM96 Geopotential Model |

Estimate Center of Gravity | Calculate center of gravity location |

Estimate Inertia Tensor | Calculate inertia tensor |

Flat Earth to LLA | Estimate geodetic latitude, longitude, and altitude from flat Earth position |

FlightGear Preconfigured 6DoF Animation | Connect model to FlightGear flight simulator |

Force Conversion | Convert from force units to desired force units |

Gain Scheduled Lead-Lag | Implement first-order lead-lag with gain-scheduled coefficients |

Generate Run Script | Generate FlightGear run script on current platform |

Geocentric to Geodetic Latitude | Convert geocentric latitude to geodetic latitude |

Geodetic to Geocentric Latitude | Convert geodetic latitude to geocentric latitude |

Geoid Height | Calculate undulations/height |

Horizontal Wind Model | Transform horizontal wind into body-axes coordinates |

Ideal Airspeed Correction | Calculate equivalent airspeed (EAS), calibrated airspeed (CAS), or true airspeed (TAS) from each other |

Incidence & Airspeed | Calculate incidence and airspeed |

Incidence, Sideslip & Airspeed | Calculate incidence, sideslip, and airspeed |

International Geomagnetic Reference Field 11 | Calculate Earth's magnetic field and secular variation using 11th generation of International Geomagnetic Reference Field |

Interpolate Matrix(x) | Return interpolated matrix for given input |

Interpolate Matrix(x,y) | Return interpolated matrix for given inputs |

Interpolate Matrix(x,y,z) | Return interpolated matrix for given inputs |

Invert 3x3 Matrix | Compute inverse of 3-by-3 matrix |

ISA Atmosphere Model | Implement International Standard Atmosphere (ISA) |

Julian Date Conversion | Calculate Julian date or modified Julian date |

Julian Epoch to Besselian Epoch | Transform position and velocity components from Standard Julian Epoch (J2000) to discontinued Standard Besselian Epoch (B1950) |

Lapse Rate Model | Implement lapse rate model for atmosphere |

Length Conversion | Convert from length units to desired length units |

Linear Second-Order Actuator | Implement second-order linear actuator |

LLA to ECEF Position | Calculate Earth-centered Earth-fixed (ECEF) position from geodetic latitude, longitude, and altitude above planetary ellipsoid |

LLA to ECI Position | Convert latitude, longitude, altitude (LLA) coordinates to Earth-centered inertial (ECI) coordinates |

LLA to Flat Earth | Estimate flat Earth position from geodetic latitude, longitude, and altitude |

Mach Number | Compute Mach number using velocity and speed of sound |

Mass Conversion | Convert from mass units to desired mass units |

MATLAB Animation | Create six-degrees-of-freedom multibody custom geometry block |

Moments About CG Due to Forces | Compute moments about center of gravity due to forces applied at a point, not center of gravity |

Moon Libration | Implement Moon librations |

Non-Standard Day 210C | Implement MIL-STD-210C climatic data |

Non-Standard Day 310 | Implement MIL-HDBK-310 climatic data |

Nonlinear Second-Order Actuator | Implement second-order actuator with rate and deflection limits |

NRLMSISE-00 Atmosphere Model | Implement mathematical representation of 2001 United States Naval Research Laboratory Mass Spectrometer and Incoherent Scatter Radar Exosphere |

Pack net_fdm Packet for FlightGear | Generate net_fdm packet for FlightGear |

Pilot Joystick | Provide joystick interface on Windows platform |

Pilot Joystick All | Provide joystick interface in All Outputs configuration on Windows platform |

Planetary Ephemeris | Implement position and velocity of astronomical objects |

Precision Pilot Model | Represent precision pilot model |

Pressure Altitude | Calculate pressure altitude based on ambient pressure |

Pressure Conversion | Convert from pressure units to desired pressure units |

Quaternion Conjugate | Calculate conjugate of quaternion |

Quaternion Division | Divide quaternion by another quaternion |

Quaternion Inverse | Calculate inverse of quaternion |

Quaternion Modulus | Calculate modulus of quaternion |

Quaternion Multiplication | Calculate product of two quaternions |

Quaternion Norm | Calculate norm of quaternion |

Quaternion Normalize | Normalize quaternion |

Quaternion Rotation | Rotate vector by quaternion |

Quaternions to Direction Cosine Matrix | Convert quaternion vector to direction cosine matrix |

Quaternions to Rotation Angles | Determine rotation vector from quaternion |

Radius at Geocentric Latitude | Estimate radius of ellipsoid planet at geocentric latitude |

Receive net_ctrl Packet from FlightGear | Receive net_ctrl packet from FlightGear |

Relative Ratio | Calculate relative atmospheric ratios |

Rotation Angles to Direction Cosine Matrix | Convert rotation angles to direction cosine matrix |

Rotation Angles to Quaternions | Calculate quaternion from rotation angles |

Self-Conditioned [A,B,C,D] | Implement state-space controller in self-conditioned form |

Send net_fdm Packet to FlightGear | Transmit net_fdm packet to destination IP address and port for FlightGear session |

Simple Variable Mass 3DOF (Body Axes) | Implement three-degrees-of-freedom equations of motion of simple variable mass with respect to body axes |

Simple Variable Mass 3DOF (Wind Axes) | Implement three-degrees-of-freedom equations of motion of simple variable mass with respect to wind axes |

Simple Variable Mass 6DOF (Euler Angles) | Implement Euler angle representation of six-degrees-of-freedom equations of motion of simple variable mass |

Simple Variable Mass 6DOF (Quaternion) | Implement quaternion representation of six-degrees-of-freedom equations of motion of simple variable mass with respect to body axes |

Simple Variable Mass 6DOF ECEF (Quaternion) | Implement quaternion representation of six-degrees-of-freedom equations of motion of simple variable mass in Earth-centered Earth-fixed (ECEF) coordinates |

Simple Variable Mass 6DOF Wind (Quaternion) | Implement quaternion representation of six-degrees-of-freedom equations of motion of simple variable mass with respect to wind axes |

Simple Variable Mass 6DOF Wind (Wind Angles) | Implement wind angle representation of six-degrees-of-freedom equations of motion of simple variable mass |

Simulation Pace | Set simulation rate for improved animation viewing |

SinCos | Compute sine and cosine of angle |

Spherical Harmonic Gravity Model | Implement spherical harmonic representation of planetary gravity |

Symmetric Inertia Tensor | Create inertia tensor from moments and products of inertia |

Temperature Conversion | Convert from temperature units to desired temperature units |

Three-Axis Accelerometer | Implement three-axis accelerometer |

Three-Axis Gyroscope | Implement three-axis gyroscope |

Three-Axis Inertial Measurement Unit | Implement three-axis inertial measurement unit (IMU) |

Turbofan Engine System | Implement first-order representation of turbofan engine with controller |

Tustin Pilot Model | Represent Tustin pilot model |

Unpack net_ctrl Packet from FlightGear | Unpack net_ctrl variable packet received from FlightGear |

Velocity Conversion | Convert from velocity units to desired velocity units |

Von Karman Wind Turbulence Model (Continuous) | Generate continuous wind turbulence with Von Kármán velocity spectra |

WGS84 Gravity Model | Implement 1984 World Geodetic System (WGS84) representation of Earth's gravity |

Wind Angles to Direction Cosine Matrix | Convert wind angles to direction cosine matrix |

Wind Angular Rates | Calculate wind angular rates from body angular rates, angle of attack, sideslip angle, rate of change of angle of attack, and rate of change of sideslip |

Wind Shear Model | Calculate wind shear conditions |

World Magnetic Model 2000 | Calculate Earth's magnetic field at specific location and time using World Magnetic Model 2000 (WMM2000) |

World Magnetic Model 2005 | Calculate Earth's magnetic field at specific location and time using World Magnetic Model 2005 (WMM2005) |

World Magnetic Model 2010 | Calculate Earth's magnetic field at specific location and time using World Magnetic Model 2010 (WMM2010) |

Zonal Harmonic Gravity Model | Calculate zonal harmonic representation of planetary gravity |

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