# Aerospace Blockset Blocks

 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 AER Convert Earth-centered inertial (ECI) coordinates to azimuth coordinates 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) World Magnetic Model 2015 Calculate Earth's magnetic field at specific location and time using World Magnetic Model 2015 (WMM2015)
 Zonal Harmonic Gravity Model Calculate zonal harmonic representation of planetary gravity