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Nordstern.xml
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2062 lines (1907 loc) · 59.1 KB
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<?xml version="1.0" encoding="utf-8"?>
<!--
Zeppelin LZ 121 "Nordstern" airship flight model for JSBSim.
Copyright (C) 2010 - 2023 Anders Gidenstam (anders(at)gidenstam.org)
This program is free software; you can redistribute it and/or modify
it under the terms of the GNU General Public License as published by
the Free Software Foundation; either version 2 of the License, or
(at your option) any later version.
This program is distributed in the hope that it will be useful,
but WITHOUT ANY WARRANTY; without even the implied warranty of
MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
GNU General Public License for more details.
You should have received a copy of the GNU General Public License
along with this program; if not, write to the Free Software
Foundation, Inc., 59 Temple Place, Suite 330, Boston, MA 02111-1307 USA
-->
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="LZ 121" version="2.0" release="BETA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author>Anders Gidenstam</author>
<email>anders at gidenstam dot org</email>
<filecreationdate>2010-04-20</filecreationdate>
<version>2023-12-06</version>
<description>JSBSim model of the Zeppelin LZ 121 "Nordstern".</description>
<license>
<licenseName>GPL v2+</licenseName>
<licenseURL>http://www.gnu.org/licenses/old-licenses/gpl-2.0.html</licenseURL>
</license>
<note>
This model was created using publicly available data, publicly available
technical reports, textbooks, and guesses. It contains no proprietary or
restricted data. It has been validated only to the extent that it may seem
to "fly right", and possibly to comply to published, publicly known,
performance data (maximum speed, endurance, etc.).
This model is distributed in the hope that it will be useful,
but WITHOUT ANY WARRANTY; without even the implied warranty of
MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
GNU General Public License for more details.
</note>
<reference
refID="PK:1994:LZ120"
author="Peter Kleinheins"
title="LZ 120 „Bodensee“ und LZ 121 „Nordstern“ Luftschiffe im Schatten des Versailler Vertrages"
date="1994"/>
<reference
refID="Vissering:1922:ZS"
author="Harry Vissering"
title="Zeppelin The Story of a Great Achievement"
date="1922"/>
<reference
refID="Flight:1918:MB"
author="Flight"
title="THE 300 H.P. MAYBACH ENGINE."
date="29 Aug. 1918"/>
<reference
refID="DR:1979:Bodensee"
author="Douglas H. Robinson"
title="The Commercial Zeppelins Bodensee and Nordstern"
date="1979"/>
<reference
refID="LD:1924:25YOAC"
author="Dr. Ludwig Dürr"
title="25 Years Of Airship Construction"
date="1924/"/>
<reference
refID="HE:1919:BIPZ"
author="Dr. Hugo Eckener"
title="Brief Instructions and Practical Hints for Piloting Zeppelin Airships for the Flight Personnel of the ''DELAG''"
date="1919"/>
</fileheader>
<!--
==== Metrics ===============================================================
-->
<metrics>
<documentation>
NOTE: The center of the mooring coupler at bow of the hull is the
origo of the body coordinate system.
x/y/z = back/right/up
</documentation>
<documentation>
Summary of technical data in [PK:1994:LZ120] and
[http://de.wikipedia.org/wiki/LZ_120]:
Hull
Length: 130.8 m
Max diameter: 18.71 m
#gas cells: 13
Gas volume: 22500 m^3 hydrogen
Material: "... Baumwolle und war mit Zellonlack getränkt."
"... verlieh dem Schiff ein silbergraues Äußeres."
Engines
Type: Maybach-Reihen-Sechszylinder-Motoren Mb IVa
Number: 4
Power: 240 HP (below 1800 m)
Propellers
Side cars (2):
Engines: 1 (each)
Diameter: 3.2 m
#blades: 2
Reversible.
Aft car:
Engines: 2
Diameter: 5.2 m
#blades: 2
Gearing: 2:1
Empty weight: 14700 kg
Useful load: 11500 kg
Range: 1700 km
Crew:
"Standardbesatzung: 12 Mann:
Kommandant, „Steuermann“ bzw. Wachhabender (entspr. 1. Offizier),
1 Höhensteuermann, 1 Seitensteuermann, 1 Funker, 1 Steward,
6 Maschinisten"
</documentation>
<!-- Reference quantities. -->
<wingarea unit="M2"> 797.0 </wingarea> <!-- V^(2/3).-->
<wingspan unit="M"> 28.2 </wingspan> <!-- V^(1/3). -->
<chord unit="M"> 28.2 </chord> <!-- V^(1/3). -->
<htailarea unit="M2"> 119.0 </htailarea> <!-- FIX these... -->
<htailarm unit="M"> 54.4 </htailarm> <!-- From CG? -->
<vtailarea unit="M2"> 58.4 </vtailarea>
<vtailarm unit="M"> 54.4 </vtailarm> <!-- From CG? -->
<!-- Total gas volume vol = 22500 m^3 -->
<!-- Aerodynamic Reference Point.
Must be on the axis of symmetry of the hull. -->
<location name="AERORP" unit="M">
<x> 56.4 </x>
<y> 0.0 </y>
<z> 0.0 </z>
</location>
<location name="EYEPOINT" unit="M">
<x> 21.0 </x>
<y> 0.0 </y>
<z> -9.0 </z>
</location>
<!-- Visual Reference Point -->
<location name="VRP" unit="M">
<x> 0.0 </x>
<y> 0.0 </y>
<z> 0.0 </z>
</location>
</metrics>
<!--
==== Mass balance =========================================================
-->
<mass_balance>
<emptywt unit="KG"> 9750 </emptywt>
<documentation>
The empty weight is estimated to consist of:
- The hull structure 7000 (guesstimate from LZ-129 ratio)
- The hull cover 1125 (guesstimate from LZ-129 ratio)
- The empty gas cells 1625 (guesstimate from LZ-129 ratio)
The car and engines etc will be added as point masses.
</documentation>
<documentation>
% Very rough estimation model of the empty weight CG and inertia tensor.
% Assume the empty weight of is to 60% a cylindrical shell and
% to 40% a thin rod (i.e. the keel).
% The keel is located r meters below the centrum line.
m = 9750.0 % KG
r = 7.05 % meter
l = 130.8 % meter
% Very rough estimate of center of gravity (based on the inertial estimate):
CGx = l / 2
CGy = 0
CGz = - 1/6 * pi * r
% Steiners theorem:
% Ixx = \bar{Ixx} + m sqrt(\bar{y}^2 + \bar{z}^2)
% Ixy = \bar{Ixy} + m \bar{x} \bar{y}
% Very rough estimation model of Ixx, Iyy and Izz relative the CG.
Ixx = (0.6*m) * r^2 + (0.6*m) * 1/6 * pi * r + \
(0.4*m) * r * (1 - 1/6*pi)
Iyy = 1/2*(0.6*m) * r^2 + 1/12*(0.6*m)*l^2 + (0.6*m) * 1/6 * pi * r + \
1/12*(0.4*m)*l^2 + (0.4*m) * r * (1 - 1/6*pi)
Izz = 1/2*(0.6*m) * r^2 + 1/12*(0.6*m)*l^2 + \
1/12*(0.4*m) * l^2
Ixy = 0
Ixz = 0
Iyz = 0
</documentation>
<ixx unit="KG*M2"> 325450.0 </ixx>
<iyy unit="KG*M2"> 14081000.0 </iyy>
<izz unit="KG*M2"> 14046000.0 </izz>
<ixy unit="KG*M2"> 0.0 </ixy>
<ixz unit="KG*M2"> 0.0 </ixz>
<iyz unit="KG*M2"> 0.0 </iyz>
<location name="CG" unit="M">
<x> 65.400 </x>
<y> 0.000 </y>
<z> -3.690 </z>
</location>
<!--
=== Ballast ================================================
-->
<documentation>
Ballast according to [Vissering:1922:ZS]:
Frame 10
4x 100 l "Ballasthose" (Emergency ballast)
Frame 20
2x 500 l "Ballastsack" (Trim ballast)
Frame 50
2x 500 l "Ballastsack" (Trim ballast)
Frame 70
2x 500 l "Ballastsack" (Trim ballast)
Frame 105
2x 500 l "Ballastsack" (Trim ballast)
Frame 110
6x 100 l "Ballasthose" (Emergency ballast)
</documentation>
<!-- Real ballast setup. -->
<pointmass name="Ballasthose 1L Frame 10"> <!-- n=0 -->
<location unit="M">
<x> 109.8 </x>
<y> -2.5 </y>
<z> -4.5 </z>
</location>
<weight unit="KG"> 100 </weight>
</pointmass>
<pointmass name="Ballasthose 2L Frame 10"> <!-- n=1 -->
<location unit="M">
<x> 109.8 </x>
<y> -1.5 </y>
<z> -4.5 </z>
</location>
<weight unit="KG"> 100 </weight>
</pointmass>
<pointmass name="Ballasthose 1R Frame 10"> <!-- n=2 -->
<location unit="M">
<x> 109.8 </x>
<y> 1.5 </y>
<z> -4.5 </z>
</location>
<weight unit="KG"> 100 </weight>
</pointmass>
<pointmass name="Ballasthose 2R Frame 10"> <!-- n=3 -->
<location unit="M">
<x> 109.8 </x>
<y> 2.5 </y>
<z> -4.5 </z>
</location>
<weight unit="KG"> 100 </weight>
</pointmass>
<pointmass name="Ballastsack L Frame 20"> <!-- n=4 -->
<location unit="M">
<x> 100.0 </x>
<y> -0.6 </y>
<z> -6.3 </z>
</location>
<weight unit="KG"> 500 </weight>
</pointmass>
<pointmass name="Ballastsack R Frame 20"> <!-- n=5 -->
<location unit="M">
<x> 100.0 </x>
<y> 0.6 </y>
<z> -6.3 </z>
</location>
<weight unit="KG"> 500 </weight>
</pointmass>
<pointmass name="Ballastsack L Frame 50"> <!-- n=6 -->
<location unit="M">
<x> 70.0 </x>
<y> -0.6 </y>
<z> -8.2 </z>
</location>
<weight unit="KG"> 500 </weight>
</pointmass>
<pointmass name="Ballastsack R Frame 50"> <!-- n=7 -->
<location unit="M">
<x> 70.0 </x>
<y> 0.6 </y>
<z> -8.2 </z>
</location>
<weight unit="KG"> 500 </weight>
</pointmass>
<pointmass name="Ballastsack L Frame 70"> <!-- n=8 -->
<location unit="M">
<x> 50.0 </x>
<y> -0.6 </y>
<z> -8.2 </z>
</location>
<weight unit="KG"> 500 </weight>
</pointmass>
<pointmass name="Ballastsack R Frame 70"> <!-- n=9 -->
<location unit="M">
<x> 50.0 </x>
<y> 0.6 </y>
<z> -8.2 </z>
</location>
<weight unit="KG"> 500 </weight>
</pointmass>
<pointmass name="Ballastsack L Frame 105"> <!-- n=10 -->
<location unit="M">
<x> 17.5 </x>
<y> -0.6 </y>
<z> -6.7 </z>
</location>
<weight unit="KG"> 500 </weight>
</pointmass>
<pointmass name="Ballastsack R Frame 105"> <!-- n=11 -->
<location unit="M">
<x> 17.5 </x>
<y> 0.6 </y>
<z> -6.7 </z>
</location>
<weight unit="KG"> 500 </weight>
</pointmass>
<pointmass name="Ballasthose 1L Frame 110"> <!-- n=12 -->
<location unit="M">
<x> 10.8 </x>
<y> -1.0 </y>
<z> -5.5 </z>
</location>
<weight unit="KG"> 100 </weight>
</pointmass>
<pointmass name="Ballasthose 2L Frame 110"> <!-- n=13 -->
<location unit="M">
<x> 10.8 </x>
<y> -0.75 </y>
<z> -5.5 </z>
</location>
<weight unit="KG"> 100 </weight>
</pointmass>
<pointmass name="Ballasthose 3L Frame 110"> <!-- n=14 -->
<location unit="M">
<x> 10.8 </x>
<y> -0.5 </y>
<z> -5.5 </z>
</location>
<weight unit="KG"> 100 </weight>
</pointmass>
<pointmass name="Ballasthose 1R Frame 110"> <!-- n=15 -->
<location unit="M">
<x> 10.8 </x>
<y> 0.5 </y>
<z> -5.5 </z>
</location>
<weight unit="KG"> 100 </weight>
</pointmass>
<pointmass name="Ballasthose 2R Frame 110"> <!-- n=16 -->
<location unit="M">
<x> 10.8 </x>
<y> 0.75 </y>
<z> -5.5 </z>
</location>
<weight unit="KG"> 100 </weight>
</pointmass>
<pointmass name="Ballasthose 3R Frame 110"> <!-- n=17 -->
<location unit="M">
<x> 10.8 </x>
<y> 1.0 </y>
<z> -5.5 </z>
</location>
<weight unit="KG"> 100 </weight>
</pointmass>
<!--
=== Crew and payload =======================================
-->
<documentation>
Payload storage along the keel according to [Vissering:1922:ZS]:
Frame 40-45 (between the frames)
4x Gepäcknetz für 200 kg
Frame 75 (2 fore and 1 aft right of the frame)
3x Gepäcknetz für 200 kg
</documentation>
<pointmass name="Control car payload"> <!-- n=18 -->
<weight unit="KG"> 1500.0 </weight>
<location name="POINTMASS" unit="M">
<x> 21.0 </x>
<y> 0.0 </y>
<z> -8.5 </z>
</location>
</pointmass>
<pointmass name="Frame 40L Cargo"> <!-- n=19 -->
<weight unit="KG"> 80.0 </weight>
<location name="POINTMASS" unit="M">
<x> 78.5 </x>
<y> -1.0 </y>
<z> -8.0 </z>
</location>
</pointmass>
<pointmass name="Frame 40R Cargo"> <!-- n=20 -->
<weight unit="KG"> 80.0 </weight>
<location name="POINTMASS" unit="M">
<x> 78.5 </x>
<y> 1.0 </y>
<z> -8.0 </z>
</location>
</pointmass>
<pointmass name="Frame 45L Cargo"> <!-- n=21 -->
<weight unit="KG"> 100.0 </weight>
<location name="POINTMASS" unit="M">
<x> 76.5 </x>
<y> -1.0 </y>
<z> -8.2 </z>
</location>
</pointmass>
<pointmass name="Frame 45R Cargo"> <!-- n=22 -->
<weight unit="KG"> 100.0 </weight>
<location name="POINTMASS" unit="M">
<x> 76.5 </x>
<y> 1.0 </y>
<z> -8.2 </z>
</location>
</pointmass>
<pointmass name="Frame 75R Aft Cargo"> <!-- n=23 -->
<weight unit="KG"> 100.0 </weight>
<location name="POINTMASS" unit="M">
<x> 46.5 </x>
<y> 1.0 </y>
<z> -8.7 </z>
</location>
</pointmass>
<pointmass name="Frame 75L Fore Cargo"> <!-- n=24 -->
<weight unit="KG"> 100.0 </weight>
<location name="POINTMASS" unit="M">
<x> 43.5 </x>
<y> -1.0 </y>
<z> -8.7 </z>
</location>
</pointmass>
<pointmass name="Frame 75R Fore Cargo"> <!-- n=25 -->
<weight unit="KG"> 100.0 </weight>
<location name="POINTMASS" unit="M">
<x> 43.5 </x>
<y> 1.0 </y>
<z> -8.7 </z>
</location>
</pointmass>
<!--
=== Crew ===================================================
-->
<pointmass name="Watch Officer"> <!-- n=26 -->
<weight unit="KG"> 85 </weight>
<location unit="M">
<x> 22.0 </x>
<y> 0.5 </y>
<z> -9.9 </z>
</location>
</pointmass>
<pointmass name="Rudder Man"> <!-- n=27 -->
<weight unit="KG"> 85 </weight>
<location unit="M">
<x> 20.5 </x>
<y> 0.0 </y>
<z> -9.9 </z>
</location>
</pointmass>
<pointmass name="Elevator Man"> <!-- n=28 -->
<weight unit="KG"> 85 </weight>
<location unit="M">
<x> 22.2 </x>
<y> -0.5 </y>
<z> -9.9 </z>
</location>
</pointmass>
<pointmass name="Steward"> <!-- n=29 -->
<weight unit="KG"> 85 </weight>
<location unit="M">
<x> 33.0 </x>
<y> 0.5 </y>
<z> -9.9 </z>
</location>
</pointmass>
<pointmass name="Rigger"> <!-- n=30 -->
<weight unit="KG"> 85 </weight>
<location unit="M">
<x> 51.0 </x>
<y> 0.0 </y>
<z> -8.4 </z>
</location>
</pointmass>
<!--
=== Engines ================================================
-->
<pointmass name="Left Engine Car">
<weight unit="KG"> 550.0 </weight>
<location name="POINTMASS" unit="M">
<x> 60.0 </x>
<y> -6.5 </y>
<z> -10.0 </z>
</location>
</pointmass>
<pointmass name="Right Engine Car">
<weight unit="KG"> 550.0 </weight>
<location name="POINTMASS" unit="M">
<x> 60.0 </x>
<y> 6.5 </y>
<z> -10.0 </z>
</location>
</pointmass>
<pointmass name="Aft Engine Car">
<weight unit="KG"> 800.0 </weight>
<location name="POINTMASS" unit="M">
<x> 90.0 </x>
<y> 0.0 </y>
<z> -11.0 </z>
</location>
</pointmass>
<!--
=== Structure ==============================================
-->
<pointmass name="Mooring cone">
<!-- Pure guess. -->
<weight unit="KG"> 200.0 </weight>
<location name="POINTMASS" unit="M">
<x> 0.0 </x>
<y> 0.0 </y>
<z> 0.0 </z>
</location>
</pointmass>
<pointmass name="Control car">
<!-- Pure guess. -->
<weight unit="KG"> 3000.0 </weight>
<location name="POINTMASS" unit="M">
<x> 30.0 </x>
<y> 0.0 </y>
<z> -9.0 </z>
</location>
</pointmass>
</mass_balance>
<!--
==== Ground reactions ======================================================
-->
<ground_reactions>
<!--
=== Landing gears ===================================================
-->
<contact type="BOGEY" name="CAR_BUMPER_BAG">
<location unit="M">
<x> 21.33 </x>
<y> 0.00 </y>
<z> -11.80 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<rolling_friction> 0.5 </rolling_friction>
<spring_coeff unit="N/M"> 50000 </spring_coeff>
<damping_coeff unit="N/M/SEC"> 10000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="BOGEY" name="AFT_ENGINE_CAR_BUMPER_BAG">
<location unit="M">
<x> 90.00 </x>
<y> 0.00 </y>
<z> -12.70 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<rolling_friction> 0.5 </rolling_friction>
<spring_coeff unit="N/M"> 50000 </spring_coeff>
<damping_coeff unit="N/M/SEC"> 10000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!--
=== Other contact points ============================================
-->
<!-- These should induce structural failure. -->
<contact type="STRUCTURE" name="NOSE">
<location unit="M">
<x> 0.0 </x>
<y> 0.0 </y>
<z> 0.0 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<spring_coeff unit="N/M"> 100000 </spring_coeff>
<damping_coeff unit="N/M/SEC"> 20000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="LEFT_ENGINE_CAR">
<location unit="M">
<x> 60.0 </x>
<y> -7.0 </y>
<z> -11.0 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<spring_coeff unit="N/M"> 100000 </spring_coeff>
<damping_coeff unit="N/M/SEC"> 20000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="RIGHT_ENGINE_CAR">
<location unit="M">
<x> 60.0 </x>
<y> 7.0 </y>
<z> -11.0 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<spring_coeff unit="N/M"> 100000 </spring_coeff>
<damping_coeff unit="N/M/SEC"> 20000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="LOWER_FIN">
<location unit="M">
<x> 120.0 </x>
<y> 0.0 </y>
<z> -8.0 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<spring_coeff unit="N/M"> 100000 </spring_coeff>
<damping_coeff unit="N/M/SEC"> 20000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="TAIL">
<location unit="M">
<x> 130.8 </x>
<y> 0.0 </y>
<z> 0.0 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<spring_coeff unit="N/M"> 100000 </spring_coeff>
<damping_coeff unit="N/M/SEC"> 20000 </damping_coeff>
</contact>
</ground_reactions>
<!--
==== Propulsion ============================================================
-->
<propulsion>
<documentation>
4 Maybach Mb IVa high altitude engine.
[Vissering:1922:ZS]:
260 HP above 10000ft
From engine performance table, assuming that Maybach 1918 is MbIVa:
260 HP, 1400 RPM, 390 kg, 0.200 kg/(hp hr)
[PK:1994:LZ120] for Bodensee:
Side engines had a propeller diameter of 3.2 m
The aft engine had a propeller diameter of 5.2 m geared down about 2:1.
4 Maybach Mb IVa-Höhenleistungsmotoren (6 cylinder inline)
190 kW max above 1800 m
180 kW max below 1800 m
2.2 kg/kW (implying an engine weight of 418kg)
Specific fuel consumption: 270 g/kWh @ 1400 RPM
Cruise consumption: about 45 kg/h (per engine)
Power settings (page 46 on the Bodensee test flights):
AK (all out): 1460 rpm (130.5 km/h @ 4 engines)
Marsch (cruise): 1360 rpm (119.6 km/h @ 4 engines)
[Flight:1918:MB, pp. 960 - 965, 995 - 1000]
Technical description of captured Maybach 300 HP aircraft engine.
Seems very similar to the Mb IVa.
Bore: 165 mm
Stroke: 180 mm (Computed from bore, compression ratio
and clearance volume)
Compression ratio: 5.94:1
Clearance volume: 778.9 cm^3
[DR:1979:Bodensee]
The side engines had reversing gear and no reduction gear.
The rear engines had a 26:49 ratio reduction gear.
[LD:1924:25YOAC, pages 78 - 79]
Bore: 165 mm
Stroke: 180 mm
Compression ratio: 6.08:1
"The performance of the engine on the ground was limited to 245 hp as at
this level the carburettor was not yet fully open; full flow was not
achieved until an altitude of 1800 m had been reached. Performance up to
this height was consequently maintained at 245 hp. Fuel consumption was
200 gm/hp hour. When dry the engine weighed 400 kg (1916), later 390 kg."
</documentation>
<!--
=== Engine ================================================
-->
<!-- Left engine -->
<engine file="eng_Maybach_Mb_IVa">
<feed>4</feed>
<feed>6</feed>
<feed>8</feed>
<feed>10</feed>
<thruster file="prop_Zeppelin3m">
<location unit="M">
<x> 62.5 </x>
<y> -6.5 </y>
<z> -10.0 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<!-- Right engine -->
<engine file="eng_Maybach_Mb_IVa">
<feed>5</feed>
<feed>7</feed>
<feed>9</feed>
<feed>11</feed>
<thruster file="prop_Zeppelin3m">
<location unit="M">
<x> 62.5 </x>
<y> 6.5 </y>
<z> -10.0 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<!-- Aft engines -->
<engine file="eng_Maybach_Mb_IVa">
<feed>0</feed>
<feed>1</feed>
<feed>2</feed>
<feed>3</feed>
<thruster file="prop_Zeppelin3m">
<location unit="M">
<x> 92.50 </x>
<y> 0.00 </y>
<z> -11.20 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<engine file="eng_Maybach_Mb_IVa">
<feed>0</feed>
<feed>1</feed>
<feed>2</feed>
<feed>3</feed>
<thruster file="prop_Zeppelin3m">
<location unit="M">
<x> 92.50 </x>
<y> 0.00 </y>
<z> -11.20 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<!--
=== Fuel tanks ============================================
-->
<documentation>
Fuel tanks according to [Vissering:1922:ZS]:
Along the keel walkway.
Frame 40 (aft of)
4x "Benzinfass" the two on the right jettisonable.
Frame 50 (fore and aft of)
4x "Benzinfass"
Frame 70 (fore and aft of)
4x "Benzinfass" all jettisonable.
According to [PK:1994:LZ120] for Bodensee:
12 "Benzinfass" of 260 l / 185 kg each.
4 "Ölfass" of 60 kg each. One close each engine.
</documentation>
<!-- Tanks at frame 40. n = 0 - 3 -->
<tank type="FUEL">
<location unit="M">
<x> 81.9 </x>
<y> -0.8</y>
<z> -7.8 </z>
</location>
<type>AVGAS</type>
<capacity unit="KG"> 185.0 </capacity>
<contents unit="KG"> 150.0 </contents>
</tank>
<tank type="FUEL">
<location unit="M">
<x> 81.9 </x>
<y> 0.8</y>
<z> -7.8 </z>
</location>
<type>AVGAS</type>
<capacity unit="KG"> 185.0 </capacity>
<contents unit="KG"> 150.0 </contents>
</tank>
<tank type="FUEL">
<location unit="M">
<x> 80.9 </x>
<y> -0.8</y>
<z> -7.8 </z>
</location>
<type>AVGAS</type>
<capacity unit="KG"> 185.0 </capacity>
<contents unit="KG"> 150.0 </contents>
</tank>
<tank type="FUEL">
<location unit="M">
<x> 80.9 </x>
<y> 0.8</y>
<z> -7.8 </z>
</location>
<type>AVGAS</type>
<capacity unit="KG"> 185.0 </capacity>
<contents unit="KG"> 150.0 </contents>
</tank>
<!-- Tanks at frame 50. n = 4 - 7 -->
<tank type="FUEL">
<location unit="M">
<x> 71.5 </x>
<y> -0.8</y>
<z> -8.0 </z>
</location>
<type>AVGAS</type>
<capacity unit="KG"> 185.0 </capacity>
<contents unit="KG"> 150.0 </contents>
</tank>
<tank type="FUEL">
<location unit="M">
<x> 71.5 </x>
<y> 0.8</y>
<z> -8.0 </z>
</location>
<type>AVGAS</type>
<capacity unit="KG"> 185.0 </capacity>
<contents unit="KG"> 150.0 </contents>
</tank>
<tank type="FUEL">
<location unit="M">
<x> 68.5 </x>
<y> -0.8</y>
<z> -8.0 </z>
</location>
<type>AVGAS</type>
<capacity unit="KG"> 185.0 </capacity>
<contents unit="KG"> 150.0 </contents>
</tank>
<tank type="FUEL">
<location unit="M">
<x> 68.5 </x>
<y> 0.8</y>
<z> -8.0 </z>
</location>
<type>AVGAS</type>
<capacity unit="KG"> 185.0 </capacity>
<contents unit="KG"> 150.0 </contents>
</tank>
<!-- Tanks at frame 70. n = 8 - 11 -->
<tank type="FUEL">
<location unit="M">
<x> 51.5 </x>
<y> -0.8</y>
<z> -8.0 </z>
</location>
<type>AVGAS</type>
<capacity unit="KG"> 185.0 </capacity>
<contents unit="KG"> 150.0 </contents>
</tank>
<tank type="FUEL">
<location unit="M">
<x> 51.5 </x>
<y> 0.8</y>
<z> -8.0 </z>
</location>
<type>AVGAS</type>
<capacity unit="KG"> 185.0 </capacity>
<contents unit="KG"> 150.0 </contents>
</tank>
<tank type="FUEL">
<location unit="M">
<x> 48.5 </x>
<y> -0.8</y>
<z> -8.0 </z>
</location>
<type>AVGAS</type>
<capacity unit="KG"> 185.0 </capacity>
<contents unit="KG"> 150.0 </contents>
</tank>
<tank type="FUEL">
<location unit="M">
<x> 48.5 </x>
<y> 0.8</y>
<z> -8.0 </z>
</location>
<type>AVGAS</type>
<capacity unit="KG"> 185.0 </capacity>
<contents unit="KG"> 150.0 </contents>
</tank>
</propulsion>
<!--
=== Gas cell ==============================================================
-->
<system name="Gas heat exchange - external factors">
<!-- External environment properties -->
<!-- Not yet used. -->
<property>environment/sun-angle-rad</property>
<property>environment/sun-radiation-norm</property>
<!-- Gas cell constants -->
<!-- Base conductivity [lb / (K ft sec)] (Guess) -->
<property value="0.05">buoyant_forces/heat-coeffs/base-conductivity</property>
<!-- Emissivity [0,1] (Guess) -->
<property value="0.1">buoyant_forces/heat-coeffs/emissivity</property>
<channel name="Conductivity">
<!-- The heat transfer to/from the cell should increase with the
airflow over the cell (or over the hull surrounding the cell).
Exactly how is still a mystery to me, so I'll just assume it is
proportional to qbar for now.
-->
<fcs_function name="buoyant_forces/heat-coeffs/conductivity">
<function>
<sum>
<property>buoyant_forces/heat-coeffs/base-conductivity</property>
<product>