Flight Path Simulation, with Euler or Quaternion Option.LTI Stability-and-Control Derivative Calculation at Trimmed Flight Condition.Trim Calculation (for Steady Level Flight at Initial Velocity and Altitude).Model Selection, State Vector and Control Initialization.Control Perturbation History (Test Inputs: rad or 100%). ![]() MODEL and FLIGHT CONDITION SELECTION FLAGS. ![]() The MATLAB code is written in chapter format with a table of contents that identifies the user input and computational modules as chapter sections: Modeling mass variation with thrust and atmospheric state would require the addition of at least one element to the state variable. A known variation of mass with time could be accommodated within the existing twelfth-order system. Aircraft mass is assumed to be constant during the simulation. V/STOL aircraft flight simulation would require more extensive aerodynamic and inertial modeling but could be accommodated within the program framework. With relatively minor extensions, the suite of control effectors can be expanded and closed-loop control can be incorporated. The flat-Earth dynamic equations could be replaced by round, rotating earth equations (Section 3.3 of Flight Dynamics) for 6-DOF launch, orbit, and reentry simulation. The early phase of rocket launch trajectories or the late phase of atmospheric entry could be simulated by declaring the proper initial conditions and vehicle model. Possible additions include simulation of "frozen" random turbulence or microburst wind shear, flight in aggressive maneuvering, and reproduction of accident scenarios. The code has been designed for simplicity and clarity, leaving a challenge for the interested reader to find ways to make the program run faster or more efficiently. Version 2 is a major update to Version 1, including a revised business jet model based on and additional aircraft models. Aircraft control histories, initial conditions, flag settings, and other program control actions are entered by changing variables contained in the code there is no separate user interface. It is a tutorial program, heavily commented to aid interpretation. StengelįLIGHTv2.m provides a six-degree-of-freedom rigid-body simulation of an aircraft, as well as trimming calculations and the generation of a linearized model at any flight condition chosen by the user. Nonlinear Six-Degree-of-Freedom Aircraft Simulation, Version 2 Supplement for Flight Dynamics, Second Edition, Robert F. You can view and edit data in the model workspace directly by using the Model Explorer, which is launched using the Modeling > Design > Model Explorer menu item.Nonlinear Six-Degree-of-Freedom Aircraft Simulation, Version 2 Supplement B. This file is loaded by the model into the model workspace. Parameters for the model are stored in a file named slexAircraftData.m. If you close a model scope, such as for batch simulations, you can later reopen it by double-clicking the "scope" icon on the signal of interest. Found on Simulation > Prepare > Viewers Manager, the Viewers and Generators Manager allows you to instrument your model without having to add blocks to the model. The Viewers and Generators Manager was used in this model to create the model scope for viewing signals, Scope1. A simplified Dryden wind gust model is incorporated to perturb the system. First order linear approximations of the aircraft and actuator behavior are connected to an analog flight control design that uses the pilot's stick pitch command as the set point for the aircraft's pitch attitude and uses aircraft pitch angle and pitch rate to determine commands. ![]() This example shows how to model flight control for the longitudinal motion of an aircraft.
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