Maik Justus: Helicopter configuration documentation
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@ -101,7 +101,11 @@ vstab: A "vertical" stabilizer. Like hstab, this is just another
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with the solver computation, so you can have none, or as
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with the solver computation, so you can have none, or as
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many as you like.
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many as you like.
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stall: A subelement of a wing (or hstab/vstab) that specifies the
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mstab: A mirrored horizontal stabilizer. Exactly the same as wing, but
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not involved with the solver computation, so you can have none,
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or as many as you like.
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stall: A subelement of a wing (or hstab/vstab/mstab) that specifies the
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stall behavior.
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stall behavior.
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aoa: The stall angle (maximum lift) in degrees. Note that
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aoa: The stall angle (maximum lift) in degrees. Note that
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this is relative to the wing, not the fuselage (since
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this is relative to the wing, not the fuselage (since
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@ -303,6 +307,10 @@ control: This element, which can appear in two different contexts,
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FLAP1 - The flap1 deflection of a wing.
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FLAP1 - The flap1 deflection of a wing.
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SLAT - The slat extension of a wing.
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SLAT - The slat extension of a wing.
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SPOILER - The spoiler extension for a wing.
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SPOILER - The spoiler extension for a wing.
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CYCLICAIL - The "aileron" cyclic input of a rotor
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CYCLICELE - The "elevator" cyclic input of a rotor
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COLLECTIVE - The collective input of a rotor
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ROTORENGINEON - If not equal zero the rotor is rotating
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invert: Negate the value of the property before setting on
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invert: Negate the value of the property before setting on
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the object.
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the object.
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split: Applicable to wing control surfaces. Sets the
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split: Applicable to wing control surfaces. Sets the
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@ -324,3 +332,102 @@ control: This element, which can appear in two different contexts,
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axis: As above, the name of the input property.
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axis: As above, the name of the input property.
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value: A floating point number that the property is expected
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value: A floating point number that the property is expected
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to hold.
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to hold.
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rotor: A rotor. Used for simulating helicopters. You can have one, two
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or even more.
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If you specify a rotor, you do not need to specify a wing or hstab,
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the settings for approach and cruise will be ignored then. Instead
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stored results from the c182 will be used.
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name: The name of the rotor.
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(some data is stored at /rotors/name/)
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The rpm, cone angle, yaw angle and roll angle are stored
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for the complete rotor. For every blade the position
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angle, the flap angle and the incidence angle are stored.
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All angles are in degree, positive values always mean "up".
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This is not completely tested, but seem to work at least
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for rotors rotating counterclockwise.
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x,y,z: The position of the rotor center
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nx,ny,nz: The normal of the rotor (pointing upwards, will be
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normalized by the computer)
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fx,fy,fz: A Vector pointing forward, if not perpendicular to the
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normal it will be corrected by the computer
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diameter: The diameter in meter
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numblades: The number of blades
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weightperblade: The weight per blade in pounds
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relbladecenter: The relative center of gravity of the blade. Maybe
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not 100% correct interpreted; use 0.5 for the start and
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change in small steps
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rpm: rounds per minute.
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ccw: determines if the rotor rotates clockwise (="false") or
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counterclockwise (="true"), (if you look on the top of the
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normal, so the bo105 has counterclockwise rotor)
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maxcollective: The maximum of the collective incidence in degree
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mincollective: The minimum of the collective incidence in degree
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maxcyclicele: The maximum of the cyclic incidence in degree for
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the elevator like function
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mincyclicele: The minimum of the cyclic incidence in degree for
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the elevator like function
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maxcyclicail: The maximum of the cyclic incidence in degree for
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the aileron like function
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mincyclicail: The minimum of the cyclic incidence in degree for
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the aileron like function
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pitch_a: A collective incidence angle, used for the next token
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forceatpitch_a: The force, the rotor is producing when the incident
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angle is equal pitch_a. I.e. hover-pitch and a force
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equivalent to the weight. (in pounds of force)
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pitch_b: A collective incidence angle, used for the next token
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poweratpitch_b: the power the rotor needs at pitch_b. (i.e. at the
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bo105 the main rotor consumes bout 90% of the engine power,
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and 9% the tail rotor. In kW. Used for calculation of the
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torque.
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poweratpitch_0: the power the rotor needs at zero pitch.
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In kW. Used for calculation of the torque.
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notorque: If set to "true" the calculated torque is always zero.
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Very helpful while adjusting rotor parameters.
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flapmin: Minimum flapping angle. (Should normally never reached)
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flapmax: Maximum flapping angle. (Should normally never reached)
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flap0: Flapping angle at no rotation, i.e. -5
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dynamic: this changes the reactions peed of the rotor to an input.
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normally 1 (Maybe there are rotors with a little faster
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reaction, than use a value a little greater than one.
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A value greater than one will result in a more inert,
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system. Maybe it's useful for simulating the rotor of the
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Bell UH1
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rellenflaphinge: The relative length from the center of the rotor
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to the flapping hinge. Can be taken from pictures of the
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helicopter (i.e. 0 for Bell206, about 0.05 for most
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rotors) For rotors without flapping hinge (where the blade
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are twisted instead, i.e. Bo 105, Lynx) use a mean value,
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maybe 0.2. This value has a extreme result in the behavior
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of the rotor
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delta3: Some rotors have a delta3 effect, which results in a
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decreasing of the incidence when the rotor is flapping.
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A value of 0 (as most helicopters have) means no change in
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incidence, a value of 1 result in a decreases of one degree
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per one degree flapping.
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So delta3 is the proportional factor between flapping and
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decrease of incidence. I.e. the tail rotor of a Bo105 has
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a delta3 of 1.
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delta: A factor for the damping constant for the flapping. 1 means
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a analytical result, which is only a approximation. Has a
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very strong result in the reaction of the rotor system on
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control inputs.
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If you know the flapping angle for a given cyclic input you
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can adjust this by changing this value. Or if you now the
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maximum roll rate or ...
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translift: Helicopters have "translational lift", which is due to
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turbulence and hard to calculate, so this simulation uses
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a phenomenological ansatz. Use .1 for the start value
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dragfactor: The drag of the rotating rotor perpendicular to the
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rotor plane is larger than the drag of the not rotating
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rotor. Hard to calculate, so it is added phenomenological
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Any rotor needs a <control> subelement for the engine
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(ROTORENGINEON) and can have <control> subelements for the cyclic
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(CYCLICELE, CYCLICAIL) and collective (COLLECTIVE) input.
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The rotor simulation is very "beta" and not finished yet. So don't
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spend too much time to adjust a flight behavior to the smallest
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details now.
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