Blocks in Aerospace Blockset

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 07 Implement Horizontal Wind Model 07
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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