MATLAB Simulation of variable-mass rigid-body 6DOF 1.0

SIXDOFVM Calculate aircraft variable-mass rigid-body six-degrees-of-freedom equations of motion using MATLAB ODE45 solver. =-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-= Inputs: =-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-= Forces = 3x1 vector of forces in body coordinates Moments = 3x1 vectory of moments in body coordinates dMass = mass rate of change for the aircraft dInertia = 3x3 Inertia Tensor matrix rate of change tarray = time series vector OPTIONAL INPUTS: Ipos_i = 3x1 vector of initial position Ivel_b = 3x1 vector of initial velocity (body) Irates_b = 3x1 vector of initial body rates Imass = initial mass of aircraft IInertia = initial 3x3 Inertia Tensor matrix Ieuler = 3x1 vector of initial euler angles =-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-= Outputs: =-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-= t = simulation time y(1:3) = body rates y(4:6) = velocity in body coordinates y(7:9) = position in body coordinates

Requirements:	No special requirements
Platforms:	Matlab
Keyword:	3d 3x3,  Aircraft Dinertia,  Body,  Forces,  Inertia,  Initial,  Inputs,  Mass,  Matlab Ode,  Outputs,  Position,  Simulation,  Tensor Matrix Ieuler,  Tensor Matrix Rate,  Time,  Time Series Vector,  Variablemass Rigidbody Sixdegreesoffreedom,  Vector,  Vectory,  Velocity
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