| Aerospace Blockset™ | |
Block Reference |  Alphabetical List |
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| Second Order Linear Actuator | Implement second-order linear actuator |
| Second Order Nonlinear Actuator | Implement second-order actuator with rate and deflection limits |
| Aerodynamic Forces and Moments | Compute aerodynamic forces and moments using aerodynamic coefficients, dynamic pressure, center of gravity, center of pressure, and velocity |
| Digital DATCOM Forces and Moments | Compute aerodynamic forces and moments using Digital DATCOM static and dynamic stability derivatives |
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| 3DoF Animation | Create 3-D MATLAB® Graphics animation of three-degrees-of-freedom object |
| 6DoF Animation | Create 3-D MATLAB® Graphics animation of six-degrees-of-freedom object |
| MATLAB Animation | Create six–degrees-of-freedom multibody custom geometry block |
| FlightGear Preconfigured 6DoF Animation | Connect model to FlightGear flight simulator |
| Generate Run Script | Generate FlightGear run script on current computer |
| Pack net_fdm Packet for FlightGear | Generate net_fdm packet for FlightGear |
| Send net_fdm Packet to FlightGear | Transmit net_fdm packet to destination IP address and port for FlightGear session |
| Pilot Joystick | Provide joystick interface on Windows® platform |
| Pilot Joystick All | Provide joystick interface on Windows® platform |
| Simulation Pace | Set simulation rate for improved animation viewing |
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| CIRA-86 Atmosphere Model | Implement mathematical representation of 1986 CIRA atmosphere |
| COESA Atmosphere Model | Implement 1976 COESA lower atmosphere |
| ISA Atmosphere Model | Implement International Standard Atmosphere (ISA) |
| Lapse Rate Model | Implement lapse rate model for atmosphere |
| Non-Standard Day 210C | Implement MIL-STD-210C climatic data |
| Non-Standard Day 310 | Implement MIL-HDBK-310 climatic data |
| NRLMSISE-00 Atmosphere Model | Implement mathematical representation of 2001 United States Naval Research Laboratory Mass Spectrometer and Incoherent Scatter Radar Exosphere |
| Pressure Altitude | Calculate pressure altitude based on ambient pressure |
| EGM96 Geoid | Calculate geoid height as determined from EGM96 Geopotential Model |
| WGS84 Gravity Model | Implement 1984 World Geodetic System (WGS84) representation of Earth's gravity |
| 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) |
| 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 |
| Horizontal Wind Model | Transform horizontal wind into body-axes coordinates |
| Von Karman Wind Turbulence Model (Continuous) | Generate continuous wind turbulence with Von Kármán velocity spectra |
| Wind Shear Model | Calculate wind shear conditions |
| Dynamic Pressure | Compute dynamic pressure using velocity and air density |
| 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 |
| Mach Number | Compute Mach number using velocity and speed of sound |
| Radius at Geocentric Latitude | Estimate radius of ellipsoid planet at geocentric latitude |
| Relative Ratio | Calculate relative atmospheric ratios |
| 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 |
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| 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 |
| 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 |
| 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 |
| 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 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 |
| 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 |
| 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 |
| 4th Order Point Mass (Longitudinal) | Calculate fourth-order point mass |
| 4th Order Point Mass Forces (Longitudinal) | Calculate forces used by fourth-order point mass |
| 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 |
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| 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 |
| Gain Scheduled Lead-Lag | Implement first-order lead-lag with gain-scheduled coefficients |
| 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 |
| Self-Conditioned [A,B,C,D] | Implement state-space controller in self-conditioned form |
| Calculate Range | Calculate range between two crafts given their respective positions |
| 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) |
| Estimate Center of Gravity | Calculate center of gravity location |
| Estimate Inertia Tensor | Calculate inertia tensor |
| Moments About CG Due to Forces | Compute moments about center of gravity due to forces applied at a point, not center of gravity |
| Symmetric Inertia Tensor | Create inertia tensor from moments and products of inertia |
| Turbofan Engine System | Implement first-order representation of turbofan engine with controller |
|
| Besselian Epoch to Julian Epoch | Transform position and velocity components from discontinued Standard Besselian Epoch (B1950) to Standard Julian Epoch (J2000) |
| 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 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 |
| ECEF Position to LLA | Calculate geodetic latitude, longitude, and altitude above planetary ellipsoid from Earth-centered Earth-fixed (ECEF) position |
| Flat Earth to LLA | Estimate geodetic latitude, longitude, and altitude from flat Earth position |
| Geocentric to Geodetic Latitude | Convert geocentric latitude to geodetic latitude |
| Geodetic to Geocentric Latitude | Convert geodetic latitude to geocentric latitude |
| Julian Epoch to Besselian Epoch | Transform position and velocity components from Standard Julian Epoch (J2000) to discontinued Standard Besselian Epoch (B1950) |
| LLA to ECEF Position | Calculate Earth-centered Earth-fixed (ECEF) position from geodetic latitude, longitude, and altitude above planetary ellipsoid |
| Quaternions to Direction Cosine Matrix | Convert quaternion vector to direction cosine matrix |
| Quaternions to Rotation Angles | Determine rotation vector from quaternion |
| Rotation Angles to Direction Cosine Matrix | Convert rotation angles to direction cosine matrix |
| Rotation Angles to Quaternions | Calculate quaternion from rotation angles |
| Wind Angles to Direction Cosine Matrix | Convert wind angles to direction cosine matrix |
| 3x3 Cross Product | Calculate cross product of two 3-by-1 vectors |
| Adjoint of 3x3 Matrix | Compute adjoint of matrix |
| Create 3x3 Matrix | Create 3-by-3 matrix from nine input values |
| Determinant of 3x3 Matrix | Compute determinant of matrix |
| Invert 3x3 Matrix | Compute inverse of 3-by-3 matrix using determinant |
| 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 |
| SinCos | Compute sine and cosine of angle |
| Acceleration Conversion | Convert from acceleration units to desired acceleration units |
| 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 |
| Density Conversion | Convert from density units to desired density units |
| Force Conversion | Convert from force units to desired force units |
| Length Conversion | Convert from length units to desired length units |
| Mass Conversion | Convert from mass units to desired mass units |
| Pressure Conversion | Convert from pressure units to desired pressure units |
| Temperature Conversion | Convert from temperature units to desired temperature units |
| Velocity Conversion | Convert from velocity units to desired velocity units |
| Missile Guidance System | Blocks — Alphabetical List | |
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