diff --git a/examples/canards.xml b/examples/canards.xml new file mode 100644 index 0000000..0f0c712 --- /dev/null +++ b/examples/canards.xml @@ -0,0 +1,606 @@ + + +
+ Canard example + 0.4.0 + + + DLR-SL + 2023-08-07T10:30:00 + Example for Canard wing + 3.5 + + + Martin Siggel + 2012-10-09T15:12:47 + Example for Canard wing + 3.2 + + +
+ + + + Cpacs2Test + + + 1 + 1 + + 0 + 0 + 0 + + + + + name + description + + + 1.0 + 0.5 + 0.5 + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 0.0 + 0.0 + + + +
+ D150_Fuselage_1Section1 + + + 1.0 + 1.0 + 1.0 + + + 0.0 + 0.0 + 0.0 + + + 0 + 0 + 0 + + + + + D150_Fuselage_1Section1 + fuselageCircleProfileuID + + + 1.0 + 1.0 + 1.0 + + + 0 + 0 + 0 + + + 0 + 0 + 0 + + + + +
+
+ D150_Fuselage_1Section2 + + + 1.0 + 1.0 + 1.0 + + + 0.0 + 0.0 + 0.0 + + + 0.5 + 0 + 0 + + + + + D150_Fuselage_1Section2 + fuselageCircleProfileuID + + + 1 + 1 + 1 + + + 0 + 0 + 0 + + + 0 + 0 + 0 + + + + +
+
+ D150_Fuselage_1Section3 + + + 1.0 + 1.0 + 1.0 + + + 0.0 + 0.0 + 0.0 + + + 0 + 0 + 0 + + + + + D150_Fuselage_1Section3 + fuselageCircleProfileuID + + + 1 + 1 + 1 + + + 0 + 0 + 0 + + + 0 + 0 + 0 + + + + +
+ + + + D150_Fuselage_1Positioning1 + -0.5 + 90 + 0 + D150_Fuselage_1Section1ID + + + D150_Fuselage_1Positioning3 + 2 + 90 + 0 + D150_Fuselage_1Section1ID + D150_Fuselage_1Section3ID + + + + + D150_Fuselage_1Segment2 + D150_Fuselage_1Section1IDElement1 + D150_Fuselage_1Section2IDElement1 + + + D150_Fuselage_1Segment3 + D150_Fuselage_1Section2IDElement1 + D150_Fuselage_1Section3IDElement1 + + + + + + + Wing + SimpleFuselage + This wing has been generated to test CATIA2CPACS. + + + 1 + 1 + 1 + + + 0 + 0 + 0 + + + 0 + 0 + 0 + + + +
+ Cpacs2Test - Wing Section 1 + Cpacs2Test - Wing Section 1 + + + 1 + 1 + 1 + + + 0 + 0 + 0 + + + 0 + 0 + 0 + + + + + Cpacs2Test - Wing Section 1 Main Element + Cpacs2Test - Wing Section 1 Main Element + NACA0012 + + + 1 + 1 + 1 + + + 0 + 0 + 0 + + + 0 + 0 + 0 + + + + +
+
+ Cpacs2Test - Wing Section 2 + Cpacs2Test - Wing Section 2 + + + 1 + 1 + 1 + + + 0 + 0 + 0 + + + 0 + 0 + 0 + + + + + Cpacs2Test - Wing Section 2 Main Element + Cpacs2Test - Wing Section 2 Main Element + NACA0012 + + + 1 + 1 + 1 + + + 0 + 0 + 0 + + + 0 + 0 + 0 + + + + +
+
+ Cpacs2Test - Wing Section 3 + Cpacs2Test - Wing Section 3 + + + 1 + 1 + 1 + + + 0 + 0 + 0 + + + 0 + 0 + 0 + + + + + Cpacs2Test - Wing Section 3 Main Element + Cpacs2Test - Wing Section 3 Main Element + NACA0012 + + + 0.3 + 0.3 + 0.3 + + + 0 + 0 + 0 + + + 0.65 + 0 + 0 + + + + +
+ + + + Cpacs2Test - Wing Section 1 Positioning + Cpacs2Test - Wing Section 1 Positioning + 0 + 0 + 0 + Cpacs2Test_Wing_Sec1 + + + Cpacs2Test - Wing Section 2 Positioning + Cpacs2Test - Wing Section 2 Positioning + 0.501 + 0 + 0 + Cpacs2Test_Wing_Sec1 + Cpacs2Test_Wing_Sec2 + + + Cpacs2Test - Wing Section 3 Positioning + Cpacs2Test - Wing Section 3 Positioning + 1 + 0 + 0 + Cpacs2Test_Wing_Sec2 + Cpacs2Test_Wing_Sec3 + + + + + Fuselage Segment from Cpacs2Test - Wing Section 1 Main Element to Cpacs2Test - Wing Section 2 Main Element + Fuselage Segment from Cpacs2Test - Wing Section 1 Main Element to Cpacs2Test - Wing Section 2 Main Element + Cpacs2Test_Wing_Sec1_El1 + Cpacs2Test_Wing_Sec2_El1 + + + Fuselage Segment from Cpacs2Test - Wing Section 2 Main Element to Cpacs2Test - Wing Section 3 Main Element + Fuselage Segment from Cpacs2Test - Wing Section 2 Main Element to Cpacs2Test - Wing Section 3 Main Element + Cpacs2Test_Wing_Sec2_El1 + Cpacs2Test_Wing_Sec3_El1 + + + + + Wing_CS1 + Cpacs2Test_Wing_Sec1_El1 + Cpacs2Test_Wing_Sec3_El1 + + + + + MySkinMat + 0.0 + + + + + + + MyCellMat + 0.0 + + + + 0.8 + 0.8 + + + 1.0 + 1.0 + + + + 0 + WING_CS1 + + + 0 + WING_CS1 + + + + + 0.5 + WING_CS1 + + + 0.5 + WING_CS1 + + + + + + + + + MySkinMat + + + + + + + + Canard + Wing_CS1 + + + + 0.0 + Cpacs2Test_Wing_Seg_2_3 + + + 0.0 + Cpacs2Test_Wing_Seg_2_3 + + + 0.0 + Cpacs2Test_Wing_Seg_2_3 + + + + + 1.0 + Cpacs2Test_Wing_Seg_2_3 + + + 1.0 + Cpacs2Test_Wing_Seg_2_3 + + + 0.0 + Cpacs2Test_Wing_Seg_2_3 + + + + + + + 0.0 + 0.5 + + 0.5 + 0 + 0 + + + + 0.0 + 0.5 + + -0.15 + 0 + 0 + + + + + -1.0 + -30.0 + + + 0.0 + 0.0 + + + 1 + 30 + + + + + + + + + + + + + + + + NACA0.00.00.12 + NACA 4 Series Profile + + 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-0.00126;-0.0030004180415;-0.00471438572941;-0.00640256842113;-0.00806559133343;-0.00970403933653;-0.0113184567357;-0.0129093470398;-0.0144771727147;-0.0160223549226;-0.0175452732434;-0.0190462653789;-0.0205256268372;-0.0219836105968;-0.0234204267471;-0.024836242105;-0.0262311798047;-0.0276053188583;-0.0289586936852;-0.0302912936071;-0.0316030623052;-0.0328938972373;-0.0341636490097;-0.0354121207001;-0.0366390671268;-0.0378441940595;-0.0390271573644;-0.0401875620783;-0.0413249614032;-0.042438855614;-0.043528690869;-0.0445938579126;-0.0456336906587;-0.04664746464;-0.0476343953088;-0.0485936361694;-0.0495242767241;-0.0504253402064;-0.0512957810767;-0.0521344822472;-0.0529402520006;-0.0537118205596;-0.0544478362583;-0.0551468612564;-0.0558073667285;-0.0564277274483;-0.0570062156697;-0.0575409941929;-0.0580301084765;-0.0584714776309;-0.0588628840933;-0.059201961739;-0.0594861821311;-0.0597128385384;-0.059879027262;-0.0599816256958;-0.060017266394;-0.059982306219;-0.05987278938;-0.0596844028137;-0.059412421875;-0.059051643633;-0.0585963041308;-0.0580399746271;-0.0573754299024;-0.0565944788455;-0.0556877432118;-0.054644363746;-0.0534516022043;-0.0520942903127;-0.0505540468987;-0.0488081315259;-0.0468277042382;-0.0445750655553;-0.0419990347204;-0.0390266537476;-0.0355468568262;-0.0313738751622;-0.0261471986426;-0.0189390266528;0.0;0.0189390266528;0.0261471986426;0.0313738751622;0.0355468568262;0.0390266537476;0.0419990347204;0.0445750655553;0.0468277042382;0.0488081315259;0.0505540468987;0.0520942903127;0.0534516022043;0.054644363746;0.0556877432118;0.0565944788455;0.0573754299024;0.0580399746271;0.0585963041308;0.059051643633;0.059412421875;0.0596844028137;0.05987278938;0.059982306219;0.060017266394;0.0599816256958;0.059879027262;0.0597128385384;0.0594861821311;0.059201961739;0.0588628840933;0.0584714776309;0.0580301084765;0.0575409941929;0.0570062156697;0.0564277274483;0.0558073667285;0.0551468612564;0.0544478362583;0.0537118205596;0.0529402520006;0.0521344822472;0.0512957810767;0.0504253402064;0.0495242767241;0.0485936361694;0.0476343953088;0.04664746464;0.0456336906587;0.0445938579126;0.043528690869;0.042438855614;0.0413249614032;0.0401875620783;0.0390271573644;0.0378441940595;0.0366390671268;0.0354121207001;0.0341636490097;0.0328938972373;0.0316030623052;0.0302912936071;0.0289586936852;0.0276053188583;0.0262311798047;0.024836242105;0.0234204267471;0.0219836105968;0.0205256268372;0.0190462653789;0.0175452732434;0.0160223549226;0.0144771727147;0.0129093470398;0.0113184567357;0.00970403933653;0.00806559133343;0.00640256842113;0.00471438572941;0.0030004180415;0.00126 + + + + + + Circle + Profile build up from set of Points on Circle where may Dimensions are 1..-1 + + 0.0;0.0;0.0;0.0;0.0 + 0.0;1.0;0.0;-1.0;0.0 + 1.0;0.0;-1.0;0.0;1.0 + + + + + + + Dummy material + 1.0 + + 1.0 + + + + Dummy material + 1.0 + + 1.0 + + + + Dummy material + 1.0 + + 1.0 + + + + + \ No newline at end of file diff --git a/schema/cpacs_schema.xsd b/schema/cpacs_schema.xsd index 9133d4a..a82f8ee 100644 --- a/schema/cpacs_schema.xsd +++ b/schema/cpacs_schema.xsd @@ -7970,6 +7970,12 @@ cpacs@dlr.de Reference is the parent airfoil height. + + + Optional absolute translation of the hinge point. + This can be used to move the hinge points outside of the wing shape. + +