Implement threedegreesoffreedom equations of motion of simple variable mass with respect to wind axes
Equations of Motion/3DOF
The Simple Variable Mass 3DOF (Wind Axes) block considers the rotation in the vertical plane of a windfixed coordinate frame about a flat Earth reference frame.
The equations of motion are
$$\begin{array}{l}\dot{V}=\frac{{F}_{{x}_{wind}}}{m}\frac{\dot{m}Vr{e}_{{x}_{wind}}}{m}g\mathrm{sin}\gamma \\ \dot{\alpha}=\frac{{F}_{{z}_{wind}}}{mV}+q+\frac{g}{V}\mathrm{cos}\gamma \frac{\dot{m}Vr{e}_{{z}_{wind}}}{mV}\\ \dot{q}=\dot{\theta}=\frac{{M}_{{y}_{body}}{\dot{I}}_{yy}q}{{I}_{yy}}\\ \dot{\gamma}=q\dot{\alpha}\\ {\dot{I}}_{yy}=\frac{{I}_{yyfull}{I}_{yyempty}}{{m}_{full}{m}_{empty}}\dot{m}\end{array}$$
where the applied forces are assumed to act at the center of gravity of the body. Vre_{w} is the relative velocity in the wind axes at which the mass flow ($$\dot{m}$$) is ejected or added to the wind axes.
Specifies the input and output units:
Units  Forces  Moment  Acceleration  Velocity  Position  Mass  Inertia 

 Newton  Newton meter  Meters per second squared  Meters per second  Meters  Kilogram  Kilogram meter squared 
 Pound  Foot pound  Feet per second squared  Feet per second  Feet  Slug  Slug foot squared 
 Pound  Foot pound  Feet per second squared  Knots  Feet  Slug  Slug foot squared 
Select the type of mass to use:
 Mass is constant throughout the simulation. 
 Mass and inertia vary linearly as a function of mass rate. 
 Mass and inertia variations are customizable. 
The Simple Variable
selection conforms to
the previously described equations of motion.
A scalar value for the initial velocity of the body, (V_{0}).
A scalar value for the initial flight path angle of the body, (γ_{0}).
A scalar value for the initial angle between the velocity vector and the body, $$({\alpha}_{0}).$$
A scalar value for the initial body rotation rate, (q_{0}).
A twoelement vector containing the initial location of the body in the flat Earth reference frame.
A scalar value for the initial mass of the body.
A scalar value for the inertia of the body.
A scalar value for the empty mass of the body.
A scalar value for the full mass of the body.
A scalar value for the empty inertia of the body.
A scalar value for the full inertia of the body.
Specify source of gravity:
 Variable gravity input to block 
 Constant gravity specified in Acceleration due to gravity 
A scalar value for the acceleration due to gravity used if internal
gravity source is selected. If gravity is to be neglected in the simulation,
this value can be set to 0. This parameter appears if you set Gravity
source to Internal
.
Select this check box to add a mass flow relative velocity port. This is the relative velocity at which the mass is accreted or ablated.
Input  Dimension Type  Description 

First  Contains the force acting along the wind xaxis, (F_{x}).  
Second  Contains the force acting along the wind zaxis, (F_{z}).  
Third  Contains the applied pitch moment in body axes, (M).  
Fourth  Contains one or more rates of change of mass, $$(\dot{m})$$ (positive if accreted, negative if ablated).  
Fifth (Optional)  Contains the gravity in the selected units.  
Sixth (Optional)  Twoelement vector  Contains one or more relative velocities at which the mass is accreted to or ablated from the body in wind axes. 
Output  Dimension Type  Description 

First  Contains the flight path angle, in radians (γ).  
Second  Contains the pitch angular rate, in radians per second (ω_{y}).  
Third  Contains the pitch angular acceleration, in radians per second squared (dω_{y}/dt).  
Fourth  Twoelement vector  Contains the location of the body, in the flat Earth reference frame, (Xe, Ze). 
Fifth  Twoelement vector  Contains the velocity of the body resolved into the windfixed coordinate frame, (V, 0). 
Sixth  Twoelement vector  Contains the acceleration of the body resolved into the bodyfixed coordinate frame, (Ax, Az). 
Seventh  Scalar  Contain the angle of attack, $$({\alpha}_{0}).$$ 
Eight  Scalar element  Contains a flag for fuel tank status, (Fuel):

Stevens, B. L., and F. L. Lewis, Aircraft Control and Simulation, John Wiley & Sons, New York, 1992.