ec130/Models/ec130t2_fdm.xml

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 Copyright (C) 2009 Heiko Schulz, Heiko.H.Schulz@gmx.net
           (C) 2016 Michael Habarta, mhabarta@freenet.de

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 <!--EC130 T2
  Max weight: 2500kg (5512 lbs)
  Min weight: 1565kg (3452 lbs)
  Empty weight: 3159 lbs
  
  Max Range: 

  Length: 12.64m
  width: 2.31m
  width with hstab: 2.73m

  Main Rotor diameter: 10.69m
  Type: Starflex
  Disc area: ?? sqm
  Number of Blades: 3
  Rotor speed: 386rpm
  airfoil:  ONERA OA211  -> Lift/drag curve needed

  Tail rotor diameter: 1m
  Type: Fenestron (TM)
  Number of Blades: 10
  Rotor speed: 3568rpm
  disc area: ?? sqm
  airfoil: ONERA OA209/OA207  -> Lift/drag curve needed
  
  Fuel Capacity: 142.7 US gal = 540liters = 427kg

  1 Turbomeca ARRIEL 2D
  max power: 710kw, power rating (MTOP): 952SHP
  max continous: 638 kw, power rating (MCP): 856SHP
  


  CoG from the Flight Manual:
  
  Datum 133.8inch inches forward of main rotor head center line.
  cg- between 124 inch and 140.9inch from datum
  
  Airspeed Limits Never Exceed Power on: 155 kt at Hp = 0, less 3kt/1000ft
 
  FDM based on datas from Flight Manual EC130 B4, Fenestron data from Dave's All The World Fenestrons and EC135 Flight Manual 
  and help by a forums user with contact to a AS350pilot

  Remark on Aircraft Weight/Mass (mhab):
  =====================================
  Internal Equipment:
  airplane empty mass 3159 lbs is reduced by 180 lbs (= 6 seats each 30 lbs)

  This is done in order to handle differing number of seats (5 or 6) and rescue configuration (4 seats with stretcher).
  In Rescue config 4 seats are removed for 1 stretcher + stretcher-mount.
  For simplicity here 2 seats are removed (front left seat, rear right seat) and the stretcher weight
  is handled like 2 seats (front right seat, rear mid right seat)

  To make up for the weight of empty seats, in the EC130 configuration dialog the sliders for fixed seats are
  defined with min 30 lbs (= seat is always there) and the sliders for optional seats are defined with min 0 lbs.

  The weight for optional seats which are there is set to 30 lbs by nasal scripting.

  External Equipment:
  External Equipment, which is fully optional here, is handled by special weight properties for external equipment
  see "/sim/model/ec130/external/.../weight-lb" below.

  These properties are set by a dedicated nasal function, depending on the fact if the item is active or not.
  This Nasal function  ("external_weights()") - also calculates the sum of the equipment-weight
  and stores it on a dedicated weight property, which is used in the "Weight setting part" of the
  specialized EC130 configuration dialog in order to add up total Gross Weight of the heli.

  Remark: The aerodynamic relevant size of the specific optional parts is defined below as Yasim needs it.

-->

  <airplane mass="2979" version="YASIM_VERSION_32"> <!--equipment reduced!-->

  <!--not necessary for helis, but useful to prevent sliding on ground engine-out-->
  <approach speed="75" aoa="16">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.3"/>
  </approach>

  <cruise speed="100" alt="4">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.5"/>
  </cruise>

  <!--increased ground-effect-factor to 0.2: The AS350 has a low factor, due its round shape. Air from the rotor flows easily around and prevent a good air cushion.
  The EC130 isn't that round, and has a much wder bottom, so I expect a much better air cushion-->
  
  <!-- -ve Elevator Cyclic is Back stick -->
<!-- -ve aileron Cyclic is right stick -->

  <rotor name="main"
       x="1.9" y="0.0" z="1.325" 
       nx="0.05" ny="0" nz="1." fx="1" fy="0" fz="0" ccw="0"
      maxcollective="17.5" mincollective="-2.2"
       mincyclicele="-17.0"  maxcyclicele="12.5"
       mincyclicail="-5" maxcyclicail="7"
       diameter="10.69" numblades="3" 
       weightperblade="66" 
       twist="10.7" 
       chord="0.30" 
       rpm="380" 
       relbladecenter="0.5" 
       dynamic="0.8"
       rellenflaphinge="0.05" 
       delta3="0" delta="0.25" 
       pitch-a="10" pitch-b="15" 
       flapmin="-13" flapmax="13" 
       flap0="-7.5" flap0factor="0" phi0="180"
       notorque="0" dragfactor="0.30" 
        translift-ve="0.1" 
       translift-maxfactor="10" 
       ground-effect-constant="0.5" 
       taper="1"
       number-of-segments="10" 
       number-of-parts="10" 
       rel-len-where-incidence-is-measured="0.5" 
       rel-len-blade-start="0.15"

       airfoil-lift-coefficient="6.3" 
       airfoil-drag-coefficient0="0.0074" 
       airfoil-drag-coefficient1="0.05" 
       incidence-stall-zero-speed="18" 
       incidence-stall-half-sonic-speed="9" 
       lift-factor-stall="0.18" 
       drag-factor-stall="8.0" 
       stall-change-over="5.5" 
       cyclic-factor="1.0" 
       rotor-correction-factor="0.9" 
       downwashfactor ="1.1" 
       balance="0.999905">

    <control-input axis="/controls/flight/aileron-trim" control="CYCLICAIL" split="true"/>
    <control-input axis="/controls/flight/aileron" control="CYCLICAIL"
             src0="-1.0" src1="1.0"
             dst0="-1" dst1="1"/>
    <control-input axis="/controls/flight/elevator-trim" control="CYCLICELE" split="true"/>
    <control-input axis="/controls/flight/elevator" control="CYCLICELE"
             src0="-1.0" src1="1.0"
             dst0="-1" dst1="1"/>
    <control-input axis="/controls/engines/engine[0]/throttle" control="COLLECTIVE"
             src0="0.0" src1="1.0"
             dst0="1.0" dst1="-1.0"/>
  </rotor>

  <!--flapmin/max guessed from a real fenestron with 1-3degrees. S0 +/-1.5, lift coefficient 3.85, drag 0.00385.Bug me-->
  <rotor name="tail"  x="-4.4" y="-0.125" z="0.109"
      nx="0.00" ny="1" nz="-0.00" fx="1" fy="0" fz="0" ccw="0"
      maxcollective="-21.8" mincollective="39.2"
      diameter="1" numblades="10" weightperblade="0.64" relbladecenter="0.5"
      dynamic="1.4" rpm="3568" rellenflaphinge="0.35" delta3="0" translift="0" delta="0.5" twist="-7.0"
      pitch-a="10"
      pitch-b="15"
      flapmin="-2"
      flapmax="2"
      flap0="0"
      airfoil-lift-coefficient="4.55"
      airfoil-drag-coefficient0="0.005675"
      airfoil-drag-coefficient1="0.15"
      notorque="0"
      taper="1"
      chord="0.05"
      number-of-segments="5"
      number-of-parts="4"
      rel-len-blade-start="0.35"
      incidence-stall-zero-speed="34"
      incidence-stall-half-sonic-speed="33"
      lift-factor-stall="0.18"
      stall-change-over="5.5"
      drag-factor-stall="8"
      rotor-correction-factor="0.8">

    <control-input axis="/controls/flight/rudder" control="COLLECTIVE" invert="true"
             src0="-1.0" src1="1.0"
             dst0="-1.0" dst1="1.0"/>
    <control-input axis="/controls/engines/engine[1]/throttle" control="COLLECTIVE"
             src0="0.0" src1="1.0"
             dst0="0.0" dst1="0.5"/>
  </rotor>

  <rotorgear
      max-power-engine="710"
      max-power-rotor-brake="100"
      rotorgear-friction="2.6"
      engine-prop-factor="0.015"
      engine-accel-limit="100"
      yasimdragfactor="19"
      yasimliftfactor="18">

    <control-input axis="/controls/engines/engine[0]/magnetos" control="ROTORGEARENGINEON"/>
    <control-input axis="/controls/rotor/brake" control="ROTORBRAKE"
             src0="0.0" src1="1.0"
             dst0="0.0" dst1="1.0"/>
    <control-input axis="/controls/rotor/reltarget" control="ROTORRELTARGET"
             src0="0.0" src1="2.0"
             dst0="0.0" dst1="2.0"/>
    <control-input axis="/controls/rotor/maxreltorque" control="ROTORENGINEMAXRELTORQUE"
             src0="0.0" src1="2.0"
             dst0="0.0" dst1="2.0"/>
  </rotorgear>

  <cockpit x="3.7" y="0.65" z="-0.1"/>

  <!-- Fuselage -->
  <fuselage ax="5.30" ay="0" az="-0.65"
            bx="-.50" by="0" bz="-0.20"
            cx="1.0" cy="1.0" cz="1.0"
            width="2.10"
            taper="0.32"
            midpoint="0.30"/>

  <fuselage ax="2.907" ay="0" az="0.602"
            bx="0.473" by="0" bz="0.522"
            cx="1.0" cy="1.0" cz="1.0"
            width="0.65"
            taper="0.75"
            midpoint="1.0"/>

  <!-- Tail boom-->
  <fuselage ax="0.285" ay="0" az="-0.365"
            bx="-3.445" by="0" bz="-0.170"
            cz="0.3"
            width="0.8"
            taper="0.4"
            midpoint="0"/>

  <!--upper tailboom-->
  <fuselage ax="0.379" ay="0" az="0.123"
            bx="-3.445" by="0" bz="0.080"
            cz="0.3"
            width="0.2"
            taper="1.0"
            midpoint="0"/>

  <mstab x="1.152" y="0.369" z="-1.030"
         taper="1.0"
         effectiveness="2"
         length="1.2"
         chord="0.550"
         sweep="0"
         incidence="1"
         dihedral="-35">
    <stall aoa="27" width="0" peak="1.5"/>
  </mstab>

  <!-- horizontal stabilizers -->
  <hstab x="-2.95" y="0.16" z="-0.2"
         taper="1.0"
         effectiveness="2"
         length="1.2"
         chord="0.550"
         sweep="0"
         incidence="+2.5">
    <stall aoa="27" width="0" peak="1.5"/>
  </hstab>

  <!-- main rotor downwash force on stabilizers          -->
  <!-- idea: yasim doesn't handle this, thruster is used -->
  <!-- rotor torque increases and airspeed reduces it    -->
  <thruster x="-2.95" y="0.00" z="-0.2" vx="0" vy="0" vz="-1" thrust="60">
    <control-input axis="/rotors/main/torque"     src0="0" src1="6000" dst0="0" dst1="+1.0" control="THROTTLE"/>
    <control-input axis="/velocities/airspeed-kt" src0="0" src1="75"   dst0="0" dst1="-1.0" control="THROTTLE"/>
  </thruster>

  <vstab x="-4.066" y="0" z="0.251"
         taper=".7"
         length="1.84"
         effectiveness="2"
         chord="1.40"
         sweep="37"
         incidence="-7">
    <stall aoa="16" width="4" peak="2.5"/>
  </vstab>

  <!--lower fin-->
  <vstab x="-4.031" y="0" z="-0.461"
         taper=".7"
         length="0.40"
         effectiveness="2"
         chord="1.20"
         sweep="37"
         incidence="0"
         dihedral="-90">
    <stall aoa="16" width="4" peak="2.5"/>
  </vstab>

  <!-- ballast - tensors recalculated 

  CoG should be according to POH: 
  x= +1.598
  y = 0
  z = -0.13(not known - guessed)
  
  -->

  <!-- 0: -->
  <ballast x="5.298"  y="+0.0" z="  -0.13" mass="472.5"/>
  <!-- 1: -->
  <ballast x="-1.988" y="-0.0" z="  -0.13" mass="472.5"/>

  <!-- 2: -->
  <ballast x="1.598" y="+1.70" z="  -0.13" mass="472.5"/>
  <!-- 3: -->
  <ballast x="1.598" y="-1.70" z="  -0.13" mass="472.5"/>

  <!-- 4: -->
  <ballast x="1.598" y="+0.0" z="   1.42" mass="472.5"/>
  <!-- 5: -->
  <ballast x="1.598" y="-0.0" z="  -1.68" mass="472.5"/>

  <!-- pilot -->
  <weight x="3.674" y="+.676" z="-.681" mass-prop="/sim/weight[0]/weight-lb"/>
  <!-- co-pilot -->
  <weight x="3.674" y="-.040" z="-.681" mass-prop="/sim/weight[1]/weight-lb"/>
  <!-- front left passenger -->
  <weight x="4.170" y="-.350" z="-.681" mass-prop="/sim/weight[2]/weight-lb"/>
  <!-- front right passenger -->
  <weight x="3.674" y="-.730" z="-.681" mass-prop="/sim/weight[3]/weight-lb"/>
  <!-- rear left passenger -->
  <weight x="2.755" y="+.699" z="-.681" mass-prop="/sim/weight[4]/weight-lb"/>
  <!-- rear middle left passenger -->
  <weight x="2.755" y="+.232" z="-.681" mass-prop="/sim/weight[5]/weight-lb"/>
  <!-- rear middle right passenger -->
  <weight x="2.755" y="-.259" z="-.681" mass-prop="/sim/weight[6]/weight-lb"/>
  <!-- rear right passenger -->
  <weight x="2.755" y="-.707" z="-.681" mass-prop="/sim/weight[7]/weight-lb"/>
  <!-- luggage left -->
  <weight x="1.900" y="+.500" z="-.550" mass-prop="/sim/weight[8]/weight-lb"/>
  <!-- luggage right -->
  <weight x="1.900" y="-.500" z="-.550" mass-prop="/sim/weight[9]/weight-lb"/>
  <!-- luggage back -->
  <weight x="0.760" y="+0.00" z="-.600" mass-prop="/sim/weight[10]/weight-lb"/>
  <!-- luggage basket left -->
  <weight x="2.000" y="+1.45" z="-1.20" mass-prop="/sim/weight[11]/weight-lb"/>
  <!-- luggage basket right -->
  <weight x="2.000" y="-1.45" z="-1.20" mass-prop="/sim/weight[12]/weight-lb"/>

  <!--weight by the additional things like emergency floats, skiboxes, FLIR...-->
  <weight x="4.317" y="+0.000" z="-0.400" size="0.01"  mass-prop="/sim/model/ec130/external/wirecutter/weight-lb"/><!--L-->
  <weight x="4.290" y="+0.700" z="-1.200" size="0.03"  mass-prop="/sim/model/ec130/external/mirror/weight-lb"/><!--L-->
  <weight x="4.732" y="+1.050" z="-1.180" size="0.25"  mass-prop="/sim/model/ec130/external/searchlight_a800/weight-lb"/><!--L-->

  <weight x="4.435" y="-1.094" z="-1.186" size="0.50"  mass-prop="/sim/model/ec130/external/FLIR/weight-lb"/><!--R-->
  <weight x="2.382" y="-1.495" z="-1.167" size="0.30"  mass-prop="/sim/model/ec130/external/searchlight/weight-lb"/><!--R-->

  <weight x="2.047" y="+1.411" z="-1.176" size="0.30"  mass-prop="/sim/model/ec130/external/basket_left/weight-lb"/><!--OL-->
  <weight x="2.047" y="-1.411" z="-1.176" size="0.30"  mass-prop="/sim/model/ec130/external/basket_right/weight-lb"/><!--OR-->

  <!-- wide luggage boxes -->
  <weight x="1.420" y="+0.860" z="-0.550" size="0.10"  mass-prop="/sim/model/ec130/external/luggage_left_wide/weight-lb"/><!--OL-->
  <weight x="1.420" y="-0.860" z="-0.550" size="0.10"  mass-prop="/sim/model/ec130/external/luggage_right_wide/weight-lb"/><!--OR-->

  <weight x="2.213" y="+1.245" z="-1.626" size="0.10"  mass-prop="/sim/model/ec130/external/float_deflated_left/weight-lb"/><!--ML-->
  <weight x="2.213" y="-1.245" z="-1.626" size="0.10"  mass-prop="/sim/model/ec130/external/float_deflated_right/weight-lb"/><!--MR-->
  <weight x="2.213" y="+1.401" z="-1.362" size="0.70"  mass-prop="/sim/model/ec130/external/float_inflated_left/weight-lb"/><!--IL-->
  <weight x="2.213" y="-1.401" z="-1.362" size="0.70"  mass-prop="/sim/model/ec130/external/float_inflated_right/weight-lb"/><!--IR-->

  <weight x="1.350" y="+1.245" z="-1.800" size="0.05" mass-prop="/sim/model/ec130/external/snowshoe_left/weight-lb"/><!--SL-->
  <weight x="1.350" y="-1.245" z="-1.800" size="0.05" mass-prop="/sim/model/ec130/external/snowshoe_right/weight-lb"/><!--SR-->

  <weight x="1.794" y="+0.000" z="-1.280" size="0.10"  mass-prop="/sim/model/ec130/external/hoist/weight-lb"/><!--HS-->

  <!-- left skid -->
  <gear x="+3.325" y="+1.22" z="-1.770" skid="1"  compression="0.10" spring="0.8" sfric="0.8" dfric="0.9" stiction="1"/>
  <gear x="+1.028" y="+1.22" z="-1.770" skid="1"  compression="0.10" spring="0.8" sfric="0.8" dfric="0.9" stiction="1"/>

  <!-- right skid -->
  <gear x="+3.325" y="-1.22" z="-1.770" skid="1"  compression="0.10" spring="0.8" sfric="0.8" dfric="0.9" stiction="1"/>
  <gear x="+1.028" y="-1.22" z="-1.770" skid="1"  compression="0.10" spring="0.8" sfric="0.8" dfric="0.9" stiction="1"/>

  <!-- tail skid -->
  <gear x="-4.252" y="+0.00" z="-1.034" skid="1" compression="0.15" spring="0.5" damp="1" sfric="1" dfric="1" stiction="1"/>

  <!-- back end fenestron -->
  <gear x="-5.430" y="+0.00" z="+0.000" skid="1" compression="0.1" spring="0.5" damp="1" sfric="1" dfric="1"/>

  <!-- wire cutter -->
  <gear x="+4.923" y="+0.00" z="-1.431" skid="1" compression="0.1" spring="1.0" damp="1" sfric="1" dfric="1"/>

  <!-- canopy front -->
  <gear x="+5.184" y="+0.00" z="-1.100" skid="1" compression="0.1" spring="1.0" damp="1" sfric="1" dfric="1"/>

  <!--left float-->
  <gear x="+4.100" y="+1.474" z="-1.470"  compression="0.4" spring="1" sfric="0.8" dfric="0.7"
        on-water="1" on-solid="0" ignored-by-solver="1" reduce-friction-by-extension="1.0"  speed-planing="25" spring-factor-not-planing="0.7">

    <control-input axis="/controls/gear/floats-inflat" control="EXTEND"/>
    <control-output control="EXTEND" prop="/gear/gear[5]/position-norm"/>
    <control-speed control="EXTEND" transition-time="0.25"/>
  </gear>

  <gear x="+0.148" y="+1.474" z="-1.470"  compression="0.4" spring="1" sfric="0.8" dfric="0.7"
        on-water="1" on-solid="0" ignored-by-solver="1" reduce-friction-by-extension="1.0"  speed-planing="25" spring-factor-not-planing="0.7">

    <control-input axis="/controls/gear/floats-inflat" control="EXTEND"/>
    <control-output control="EXTEND" prop="/gear/gear[6]/position-norm"/>
    <control-speed control="EXTEND" transition-time="0.25"/>
  </gear>

  <!--right float-->
  <gear x="4.1" y="-1.474" z="-1.470"  compression="0.4" spring="1" sfric="0.8" dfric="0.7"
        on-water="1" on-solid="0" ignored-by-solver="1" reduce-friction-by-extension="1.0"  speed-planing="25" spring-factor-not-planing="0.7">

    <control-input axis="/controls/gear/floats-inflat" control="EXTEND"/>
    <control-output control="EXTEND" prop="/gear/gear[7]/position-norm"/>
    <control-speed control="EXTEND" transition-time="0.25"/>
  </gear>

  <gear x="0.148" y="-1.474" z="-1.470"  compression="0.4" spring="1" sfric="0.8" dfric="0.7"
        on-water="1" on-solid="0" ignored-by-solver="1" reduce-friction-by-extension="1.0"  speed-planing="25" spring-factor-not-planing="0.7">
    <control-input axis="/controls/gear/floats-inflat" control="EXTEND"/>
    <control-output control="EXTEND" prop="/gear/gear[8]/position-norm"/>
    <control-speed control="EXTEND" transition-time="0.25"/>
  </gear>

  <!-- left snowshoe -->
  <gear x="+1.028" y="+1.22" z="-1.847" skid="1" compression="0.1" spring="0.5"  sfric="0.5" dfric="0.4"/>
    <control-input axis="sim/model/ec130/snowshoes" control="EXTEND"/>
    <control-output control="EXTEND" prop="/gear/gear[9]/position-norm"/>
    <control-speed control="EXTEND" transition-time="0.2"/>

  <!-- right snowshoe -->
  <gear x="+1.028" y="-1.22" z="-1.847" skid="1" compression="0.15" spring="0.5"  sfric="0.5" dfric="0.4"/>
    <control-input axis="sim/model/ec130/snowshoes" control="EXTEND"/>
    <control-output control="EXTEND" prop="/gear/gear[10]/position-norm"/>
    <control-speed control="EXTEND" transition-time="0.2"/>

  <tank x="1.90" y="0.0" z="-.03" capacity="941" /><!-- 538.7l -->

  <!-- rotor vibration 
  <thruster x="1.9" y="0.0" z="0.325" vx="1" vy="0" vz="0" thrust="2000">
    <control-input axis="/rotors/main/vibration/longitudinal" src0="-1" src1="1" dst0="-1" dst1="1" control="THROTTLE"/>
  </thruster>
  <thruster x="1.9" y="0.0" z="0.325" vx="0" vy="1" vz="0" thrust="2000">
    <control-input axis="/rotors/main/vibration/lateral" src0="-1" src1="1" dst0="-1" dst1="1" control="THROTTLE"/>
	
	
  </thruster>
  -->
  
  
  
  
   <thruster  x="1.9" y="0.0" z="1.325"   vx="1" vy="0" vz="0" thrust="6000">
    <control-input axis="/rotors/main/vibration/longitudinal" src0="-1" src1="1" dst0="-1" dst1="1" control="THROTTLE"/>
  </thruster>

  <thruster x="1.9" y="0.0" z="1.325"  vx="0" vy="1" vz="0" thrust="6000">
    <control-input axis="/rotors/main/vibration/lateral" src0="-1" src1="1" dst0="-1" dst1="1" control="THROTTLE"/>
  </thruster>

</airplane>