Mass.dat

The mass.dat file defines the mass properties of the aircraft. Several masses, water ballast and fuel tanks can be defined. At least one mass must be defined for the simulation to work.

General options

mtow = <float>

Defines the maximum allowed takeoff weight. This is used by the GUI and will flash up all red when something's too heavy.

cg_limits = [ <front limit> <rear limit> ]

Mass

An aircraft mass would be defined like this:

# Mass of aircraft minus pilot and motor
mass {
   name           = fuselage_wings
   mass           = 440.0
   inertia        = [ 3000.0  1200.0 3300.0 ]
   position       = [ -0.450  0.0 0.0 ]
}

The parameters are supposed to be self-explaining. The inertia and positions are in x - y - z, with x pointing forwards, y to the right and z down.

With that defined, the mass of the pilot can be defined:

# Pilot's mass, assume no inertia (wrong)
seat {
   name           = pilot
   mass           = 85.0
   min_mass       = 60.0
   max_mass       = 125.0
   inertia        = [   0.0    0.0    0.0 ]
   position       = [   0.5    0.0    0.0 ]
}

Notice that the name of the part is called "seat" instead of "mass". This is so that the GUI can figure out that this is a pilot's seat and that the pilot weight can be adjusted. The inertia of the pilot is normally not very important so you can set it to zero if you don't know it. mass defines the default mass, and the limits are set with min_mass and max_mass.

Even more masses can be defined. This shows the use of a movable mass defining the electric motor in the Antares 20E model:

# Motor mass, will move with motor
mass {
   name           = motor
   mass           = 35.0
   inertia        = [    0.0    0.0    0.0 ]
   position       = [    1.5    0.0    0.0 ]

   delta_position = [    1.0    0.0    0.0 ]
   pylon_mix      = [    1.0    0.0    0.0 ]
}

Notice the delta_position and pylon_mix entries. These define that the position will shift 1.0 meters forwards when the pylon is extended. This can also be used to define a movable mass controlled by the aircraft stick, to control a hangglider! For example, this is the mass.dat file from a hangglider model:

mass {
   name           = wing
   mass           = 35.9
   inertia        = [  100.0   10.0  100.0 ]
   position       = [   -1.0    0.0    0.0 ]
}

seat {
   name           = pilot
   mass           = 75
   min_mass       = 60.0
   max_mass       = 125.0
   inertia        = [   10.0  100.0  100.0 ]
   position       = [   -1.3    0.0    1.5 ]
   delta_position = [    0.45   1.0    0.0 ]

   aileron_mix    = [    0.0   -1.0    0.0 ]
   elevator_mix   = [    1.0    0.0    0.0 ]
   rudder_mix     = [    0.0    0.0    0.0 ]
   pylon_mix      = [    0.0    0.0    0.0 ]
}

This will move the position of the pilot 0.45 meters forwards using the elevator control, and 1.0 meter sideways using the aileron control.

Water ballast

A water ballast tank is mirrored so only one side will have to be defined. The Capacity and default level indicates the sum of both (left+right). When mirrored the y coordinate of the tank is forced to zero. Use "mirror = false" to disable and define each wing individually.

The following is the water ballast tanks as defined on the Antares model. The Antares has two individual tanks in each wing that can be opened either with only the outer tank (number 1) or both (1+2). This is defined by using the valve_number entry.

# water ballast inner wing
water {
   name           = inner
   position       = [    0.0    0.0    0.0 ]
   capacity       = 60.0
   valve_size     = 0.13
   y_inner        = 3.5
   y_outer        = 8.8

   default_level  = 60.0
 
   valve_number   = 2
   valve_position = [ 0.0 -3.5 -0.0 ]
   valve_max_flow = 25.0
}

# water ballast outer wing
water {
   name           = outer
   position       = [    0.0    0.0    0.0 ]
   capacity       = 40.0
   valve_size     = 0.13
   y_inner        = 3.5
   y_outer        = 8.8
 
   default_level  = 40.0
 
   valve_number   = 1
   valve_position = [ 0.0 -6.0 -0.1 ]
   valve_max_flow = 25.0
}

Fuel tank

Aargh.