<?xml version="1.0" encoding="UTF-8"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<!-- ########################################

 # DR400-jsbSim 120 HP by PAF team
 # Oct 2012 : Modified by PAF team
 # 2013 - march 2015 : Modified by Daniel Dubreuil
 # experimental march 2014 : stall and spin, up to flat spin
 # 2019/2020 adapted for -135cdi by Bea Wolf

##########################################-->
<fdm_config xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" name="DR400-135cdi" version="2.0" release="BETA" xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
	<!-- Aircraft Data:	(ref. [2] page 1.03)
		Airfoil: NACA 230135
	-->
	<fileheader>
		<author>Daniel Dubreuil, Guillaume Chauvat, Bea Wolf</author>
		<filecreationdate> 2007-05-01 </filecreationdate>
		<version> 06/2023 </version>
		<description> Robin DR400-135cdi </description>
	</fileheader>
	<reference
		n="1"
		title="Pilot's Operating Handbook Supplement"
		url="https://www.vliegclubseppe.nl/bestanden/2016-poh-robins.pdf"/>
	<reference
		n="2"
		title="DR400/140B Pilot's Operating Handbook and Approved Flight Manual"
		url="https://mfgo.ch/wp-content/uploads/HB-KLM_AFM.pdf"/>
	<reference
		n="3"
		title="Operation and Maintenance Manual CD-135/CD-155"
		url="http://www.tmg-service.de/doc-download/manuals/OM-02-02_4-6_EASA_Version.pdf"/>
	<reference
		n="4"
		title="Type-Certificate Data Sheet MTV-6"
		url="https://www.easa.europa.eu/sites/default/files/dfu/TCDS_P094_issue03_20150319_1.0.pdf"/>
	<refrence
		n="5"
		title="Supplement Airplane Maintenance Manual DR400/135CDI"
		url="http://www.tmg-service.de/doc-download/manuals/AMM-60-02_1-5s.pdf"/>
	<reference
		n="6"
		title="Flight Manual DR 400 - 180 R"
		url="http://www.aecaosta.it/wp-content/uploads/2016/06/ROBIN_DR400_manuale.pdf"/>
	<!-- 					Center of Gravity and AeroRP:		ref. [2] page 2.04
		datum: wing leading edge (rectangular):		0m	-1.70m		0%
				maximal aft			0.564m	-1.136m		33%
				maximal fore			0.205m	-1.495m		12%
				empty CoG			0.214m	-1.486
				AeroRP (guess, CG never behind)	0.570m	-1.13m		33.33%
	-->
	<metrics>
		<wingarea unit="M2">		13.60	</wingarea>		<!--	ref. [2] page 1.03	-->
		<wingspan unit="M">		 8.72	</wingspan>		<!--	ref. [2] page 1.03	-->
		<wing_incidence unit="DEG">	 2.00	</wing_incidence>	<!--	TODO find reference	-->
		<chord unit="M">		 1.71	</chord>		<!--	ref. [2] page 1.02	-->
		<htailarea unit="M2">		 2.88	</htailarea>		<!--	ref. [2] page 1.04	-->
		<htailarm unit="M">		 3.75	</htailarm>		<!--	measured from 3D model	-->
		<vtailarea unit="M2">		 1.63	</vtailarea>		<!--	ref. [2] page 1.04	-->
		<vtailarm unit="M">		 3.95	</vtailarm>		<!--	measured from 3D model	-->
		<location name="AERORP" unit="M">	<!--	see above	-->
			<x>  -1.13 </x>
			<y>  0.00 </y>
			<z>  0.00 </z>
		</location>
		<location name="EYEPOINT" unit="M">	<!--	measured from 3D model	-->
			<x>  -1.31 </x>
			<y>  -0.28 </y>
			<z>  0.55 </z>
		</location>
		<location name="VRP" unit="M">		<!--	3d model origin equals FDM origin	-->
			<x> 0 </x>
			<y> 0 </y>
			<z> 0 </z>
		</location>
	</metrics>
	<mass_balance>
		<ixx unit="KG*M2">      865 </ixx>
		<iyy unit="KG*M2">      1012 </iyy>
		<izz unit="KG*M2">      1731 </izz>
		<ixy unit="KG*M2">        0 </ixy>
		<ixz unit="KG*M2">        0 </ixz>
		<iyz unit="KG*M2">        0 </iyz>
		<emptywt unit="KG">    585 </emptywt>
		<location name="CG" unit="M">
			<x>  -1.486 </x>
			<y>  0.00 </y>
			<z>  -0.18 </z>
		</location>
		<!--	Front seats arm: (ref. [1] page 2 - 3)
			0.36m - 0.46m
				-> average 0.41m
				x = -1.29m
		-->
		<pointmass name="PILOT">
			<weight unit="KG">75</weight>
			<location name="POINTMASS" unit="M">
				<x> -1.29 </x>
				<y> -0.28 </y>
				<z>  0.05 </z>
			</location>
		</pointmass>
		<pointmass name="COPILOT">
			<weight unit="KG">70</weight>
			<location name="POINTMASS" unit="M">
				<x> -1.29 </x>
				<y>  0.28 </y>
				<z>  0.05 </z>
			</location>
		</pointmass>
		<!--	Rear seats arm: (ref. [1] page 2 - 3)
			1.19m
			x = -0.51m
		-->
		<pointmass name="LEFT_PASSENGER">
			<weight unit="KG">0</weight>
			<location name="POINTMASS" unit="M">
				<x> -0.51 </x>
				<y> -0.28 </y>
				<z>  0.05 </z>
			</location>
		</pointmass>
		<pointmass name="RIGHT_PASSENGER">
			<weight unit="KG">0</weight>
			<location name="POINTMASS" unit="M">
				<x> -0.51 </x>
				<y>  0.28 </y>
				<z>  0.05 </z>
			</location>
		</pointmass>
		<!--	Rear seats arm: (ref. [1] page 2 - 3)
			1.9m
			x = 0.2m
		-->
		<pointmass name="BAGGAGE">
			<weight unit="KG">5</weight>
			<location name="POINTMASS" unit="M">
				<x>  0.2 </x>
				<y>  0.00 </y>
				<z>  0.10 </z>
			</location>
		</pointmass>
	</mass_balance>
	<ground_reactions>
		<contact type="BOGEY" name="NOSE">
			<location unit="M">
				<x> -2.5 </x>
				<y>  0.00 </y>
				<z> -1.02315 </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<rolling_friction> 0.02 </rolling_friction>
			<spring_coeff unit="N/M">      40000 </spring_coeff>
			<damping_coeff unit="N/M/SEC"> 13000 </damping_coeff>
			<max_steer unit="DEG"> 10.00 </max_steer>
			<brake_group>NONE</brake_group>
			<retractable>0</retractable>
		</contact>
		<contact type="BOGEY" name="LEFT_MAIN">
			<location unit="M">
				<x> -0.95314 </x>
				<y> -1.27085 </y>
				<z> -1.044 </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<rolling_friction> 0.02 </rolling_friction>
			<spring_coeff unit="N/M">      65000 </spring_coeff>
			<damping_coeff unit="N/M/SEC"> 24000 </damping_coeff>
			<max_steer unit="DEG">0</max_steer>
			<brake_group>LEFT</brake_group>
			<retractable>0</retractable>
		</contact>
		<contact type="BOGEY" name="RIGHT_MAIN">
			<location unit="M">
				<x> -0.95314 </x>
				<y>  1.27085 </y>
				<z> -1.044 </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<rolling_friction> 0.02 </rolling_friction>
			<spring_coeff unit="N/M">      65000 </spring_coeff>
			<damping_coeff unit="N/M/SEC"> 24000 </damping_coeff>
			<max_steer unit="DEG">0</max_steer>
			<brake_group>RIGHT</brake_group>
			<retractable>0</retractable>
		</contact>
		<contact type="STRUCTURE" name="TAIL">
			<location unit="M">
				<x>  2.82 </x>
				<y>  0.00 </y>
				<z> -0.24 </z>
			</location>
			<static_friction>  0.2 </static_friction>
			<dynamic_friction> 0.2 </dynamic_friction>
			<spring_coeff unit="N/M">      190000 </spring_coeff>
			<damping_coeff unit="N/M/SEC">  15000 </damping_coeff>
		</contact>
		<contact type="STRUCTURE" name="LEFT_WING_EDGE_BOTTOM">
			<location unit="M">
				<x> -1.15 </x>
				<y> -2.7  </y>
				<z> -0.45 </z>
			</location>
			<static_friction>  0.2 </static_friction>
			<dynamic_friction> 0.2 </dynamic_friction>
			<spring_coeff unit="N/M">      190000 </spring_coeff>
			<damping_coeff unit="N/M/SEC">  15000 </damping_coeff>
		</contact>
		<contact type="STRUCTURE" name="RIGHT_WING_EDGE_BOTTOM">
			<location unit="M">
				<x> -1.15 </x>
				<y>  2.7  </y>
				<z> -0.45 </z>
			</location>
			<static_friction>  0.2 </static_friction>
			<dynamic_friction> 0.2 </dynamic_friction>
			<spring_coeff unit="N/M">      190000 </spring_coeff>
			<damping_coeff unit="N/M/SEC">  15000 </damping_coeff>
		</contact>
		<contact type="STRUCTURE" name="LEFT_WING">
			<location unit="M">
				<x> -1.24 </x>
				<y> -4.35 </y>
				<z>  0.04 </z>
			</location>
			<static_friction>  0.2 </static_friction>
			<dynamic_friction> 0.2 </dynamic_friction>
			<spring_coeff unit="N/M">      190000 </spring_coeff>
			<damping_coeff unit="N/M/SEC">  15000 </damping_coeff>
		</contact>
		<contact type="STRUCTURE" name="RIGHT_WING">
			<location unit="M">
				<x> -1.24 </x>
				<y>  4.35 </y>
				<z>  0.04 </z>
			</location>
			<static_friction>  0.2 </static_friction>
			<dynamic_friction> 0.2 </dynamic_friction>
			<spring_coeff unit="N/M">      190000 </spring_coeff>
			<damping_coeff unit="N/M/SEC">  15000 </damping_coeff>
		</contact>
	</ground_reactions>
	<propulsion>
		<engine file="Continental-CD-135">
			<feed>0</feed>
			<thruster file="prop-mt-mtv6">
				<sense>1</sense>
				<location unit="M">
					<x>  -3.255 </x>
					<y>  0.00 </y>
					<z>  0.00 </z>
				</location>
				<orient unit="DEG">
					<pitch> 0.00 </pitch>
					<roll>  0.00 </roll>
					<yaw>  0.00 </yaw>
				</orient>
			</thruster>
		</engine>
		<!--	Main Fuel Tank arm: (ref. [1] page 2 - 3)
			1.12m
			x = -0.58m
		-->
		<tank type="FUEL" number="0">
			<location unit="M">
				<x>  -0.58 </x>
				<y>   0.00 </y>
				<z>  -0.35 </z>
			</location>
			<capacity unit="KG"> 78.59 </capacity>	<!--110L Jet A1-->
			<type>JET-A1</type>			<!-- 0.721 kg/L -->
		</tank>
	</propulsion>
	<flight_control file="Systems/dr400-fcs"/>
	<aerodynamics file="Systems/dr400-aero"/>
	<system file="crash-detect"/>
	<system file="general"/>
	<system file="FADEC"/>
	<system file="engine"/>
	<system file="fuel"/>
	<system file="switches"/>
	<system file="westach_quad"/>
	<external_reactions>
		<force name="pushback" frame="BODY">
			<!--	front wheel axle	-->
			<location unit="M">
				<x>   -2.5 </x>
				<y>    0.0 </y>
				<z>   -0.8 </z>
			</location>
			<direction>
				<x>1</x>
				<y>0</y>
				<z>0</z>
			</direction>
		</force>
	</external_reactions>
</fdm_config>
