title: Презентация на тему: MSC.Flightloads 5.4

text:
Aircraft Description
Wingspan: 12 m
Chord: 2 m
Leading Edge: 0.3 at of datum
Nose: 2 m forward of datum
Length: 7 m
Model Description
Boundary Conditions
Workshop # 3a: Tasks
Run a modal analysis.
Check .f06 file
Identify:
3 rigid body modes
Elastic modes
Attach .xdb in Patran
Identify:
3 rigid body modes
Significant elastic modes
Workshop # 3a: Results
Workshop # 3b: Tasks
Workshop # 3b: Aerodynamic Mesh Regions
Workshop # 3b: Aerodynamic Mesh
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Click to edit Master title style
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Second level
Third level
Fourth level
Fifth level
FLDS120, Section 5.4, June 2002
SECTION 5.4

CASE STUDY AND WORKSHOPS
Anti-Symmetric Example
Mode 4
Mode 5
Mode 6
Mode 7
Aero Mesh
Regions

Shown on top of structural mesh
Suggested aero mesh
14994.60
0.46
11016.44
0.39
7650.31
0.33
4896.20
0.26
2754.11
0.20
1224.05
0.13
306.01
0.07
Q
Mach No
Subcase 6
Subcase 6
Subcase 6
Model Description
Boundary Conditions
Workshop # 3a: Tasks
Run a modal analysis.
Check .f06 file
Identify:
3 rigid body modes
Elastic modes
Attach .xdb in Patran
Identify:
3 rigid body modes
Significant elastic modes
Workshop # 3a: Results
Workshop # 3b: Tasks
Workshop # 3b: Aerodynamic Mesh Regions
Workshop # 3b: Aerodynamic Mesh
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Boundary Conditions
Workshop # 3a: Tasks
Run a modal analysis.
Check .f06 file
Identify:
3 rigid body modes
Elastic modes
Attach .xdb in Patran
Identify:
3 rigid body modes
Significant elastic modes
Workshop # 3a: Results
Workshop # 3b: Tasks
Workshop # 3b: Aerodynamic Mesh Regions
Workshop # 3b: Aerodynamic Mesh
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Boundary Conditions
Workshop # 3a: Tasks
Run a modal analysis.
Check .f06 file
Identify:
3 rigid body modes
Elastic modes
Attach .xdb in Patran
Identify:
3 rigid body modes
Significant elastic modes
Workshop # 3a: Results
Workshop # 3b: Tasks
Workshop # 3b: Aerodynamic Mesh Regions
Workshop # 3b: Aerodynamic Mesh
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Boundary Conditions
Workshop # 3a: Tasks
Run a modal analysis.
Check .f06 file
Identify:
3 rigid body modes
Elastic modes
Attach .xdb in Patran
Identify:
3 rigid body modes
Significant elastic modes
Workshop # 3a: Results
Workshop # 3b: Tasks
Workshop # 3b: Aerodynamic Mesh Regions
Workshop # 3b: Aerodynamic Mesh
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Boundary Conditions
Workshop # 3a: Tasks
Run a modal analysis.
Check .f06 file
Identify:
3 rigid body modes
Elastic modes
Attach .xdb in Patran
Identify:
3 rigid body modes
Significant elastic modes
Workshop # 3a: Results
Workshop # 3b: Tasks
Workshop # 3b: Aerodynamic Mesh Regions
Workshop # 3b: Aerodynamic Mesh
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Workshop # 3a: Tasks
Run a modal analysis.
Check .f06 file
Identify:
3 rigid body modes
Elastic modes
Attach .xdb in Patran
Identify:
3 rigid body modes
Significant elastic modes
Workshop # 3a: Results
Workshop # 3b: Tasks
Workshop # 3b: Aerodynamic Mesh Regions
Workshop # 3b: Aerodynamic Mesh
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Run a modal analysis.
Check .f06 file
Identify:
3 rigid body modes
Elastic modes
Attach .xdb in Patran
Identify:
3 rigid body modes
Significant elastic modes
Workshop # 3a: Results
Workshop # 3b: Tasks
Workshop # 3b: Aerodynamic Mesh Regions
Workshop # 3b: Aerodynamic Mesh
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Workshop # 3a: Results
Workshop # 3b: Tasks
Workshop # 3b: Aerodynamic Mesh Regions
Workshop # 3b: Aerodynamic Mesh
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Workshop # 3b: Tasks
Workshop # 3b: Aerodynamic Mesh Regions
Workshop # 3b: Aerodynamic Mesh
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Workshop # 3b: Tasks
Workshop # 3b: Aerodynamic Mesh Regions
Workshop # 3b: Aerodynamic Mesh
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Workshop # 3b: Aerodynamic Mesh Regions
Workshop # 3b: Aerodynamic Mesh
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Workshop # 3b: Aerodynamic Mesh Regions
Workshop # 3b: Aerodynamic Mesh
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Workshop # 3b: Aerodynamic Mesh
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Suggested aero mesh
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Workshop # 3b: Manoeuver
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
14994.60
0.46
11016.44
0.39
7650.31
0.33
4896.20
0.26
2754.11
0.20
1224.05
0.13
306.01
0.07
Q
Mach No
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Trim Variables
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
14994.60
0.46
11016.44
0.39
7650.31
0.33
4896.20
0.26
2754.11
0.20
1224.05
0.13
306.01
0.07
Q
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Steady roll:
Aileron deflection: 15º
Roll rate to be determined
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Investigate roll rate at varying speeds
Roll Rate is derived from Trim Variable ROLL
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
14994.60
0.46
11016.44
0.39
7650.31
0.33
4896.20
0.26
2754.11
0.20
1224.05
0.13
306.01
0.07
Q
Workshop # 3b: Roll Rate
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
14994.60
0.46
11016.44
0.39
7650.31
0.33
4896.20
0.26
2754.11
0.20
1224.05
0.13
306.01
0.07
Q
Workshop # 3b: Aileron Deflection
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Workshop # 3b: Deformed Structure
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Workshop # 3b: Rigid Aerodynamic Loads
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Subcase 6
Workshop # 3b: Elastic Increments
Workshop # 3c: Tasks
Subcase 6
Workshop # 3c: Tasks
Subcase 6
Subcase 6
Workshop # 3c: Tasks
Subcase 6
Workshop # 3c: Tasks
14994.60
0.46
11016.44
0.39
7650.31
0.33
4896.20
0.26
2754.11
0.20
1224.05
0.13
306.01
0.07
Q


title: Презентация на тему: MSC.Mvision - 05-2

text:
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Second level
Third level
Fourth level
Fifth level
MVI320, Section 5, June 2001


title: Презентация на тему: MSC.Dytran - 11

text:
A surface is a collection of 2 dimensional facets that can be used in loads and boundary constraintsA surface is defined as a set of segmentsIt can have a three dimensional goemetrySurfaces do not have physical properties like mass, inertia or thickness but only have a geometrical importance
Page *
Introduction to Lagrange
Chapter 11 - Surfaces
MSC.Dytran Seminar Notes

*
*
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Second level
Third level
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Fifth level
*
*
CHAPTER 11 - CONCEPT OF SURFACES
CONTENTS
 Surface Definition

 Surface Creation

 Surface Usage
SURFACE DEFINITION
SURFACE CREATION

Surface created directly from elements

	SURFACE, 1,, ELEM, 10	SET1, 10, 1, THRU, 499Surface created from properties

	SURFACE, 2,, PROP, 20
	SET1, 20, 101, 102, 103
	PSHELL,101, 1 , .01
	PSHELL,102, 2 , .01
	PSHELL,103, 1 , .01

SURFACE CREATION

Surface created from materials

	SURFACE, 2,, MAT, 30
	SET1, 30, 1, 2
	PSHELL,101, 1 , .01
	PSHELL,102, 2 , .01
	PSHELL,103, 1 , .01
	MAT1, 1, 3E7, , .33, 7800.
	DMATEP,2, 7850., 210.E9, 0.3

SURFACE CREATION (continued)

Surface created from mixed definitions

	SURFACE, 2,, MAT, 30, PROP, 20, ELEM, 10
	SET1, 30, 1
	SET1, 20, 102
	SET1, 10, 1, THRU, 499
	PSHELL,101, 1 , .01
	PSHELL,102, 2 , .01
	PSHELL,103, 1 , .01
	MAT1, 1, 3E7, , .33, 7800.
Surfaces on Solid elements
Surfaces can also be defined on faces of solid elementsThe CFACE entry defines a segment on the relative face on an elementExample: 	Surface 10 is defined with two faces	The relative face 4 of element 1296 is defined as 	cface number 301 and is part of set 22	The relative face 4 of element 1297 is defined as 	cface number 302 and is also part of set 22 	SURFACE, 10, , SEG, 22
	CFACE, 301, 22, 1296, 4
 	CFACE, 302, 22, 1297, 4
DEFINING CFACES
Because most pre-processors do not support writing CFACEs, they can be defined indirectly
 Defining CFACEs by using CQUAD4 and/or CTRIA3 elements with a thickness of 9999.
	SURFACE,20,,SEG,22		PSHELL, 22, 204, 9999.	CQUAD, 301, 22, 1296, 4 	CQUAD, 302, 22, 1297, 4
is the same as
	SURFACE,20,,SEG,22		CFACE, 301, 22, 1296, 4 	CFACE, 302, 22, 1297, 4
 Defining CFACEs by using PLOAD4 entry with pressure 9999.	SURFACE,20,,SEG,22 		PLOAD4, 22, 1296, 9999.	PLOAD4, 22, 1297, 9999.
 is the same as
	SURFACE,20,,SEG,22 		CFACE, 301, 22, 1296, 4	CFACE, 302, 22, 1297, 4
Rigid Connection

	RCONN, 1, SURF, SURF, 7, 8

Rigid Body Definition

	RIGID, 25, 333, 200.,, 1., 1., 1.
	SURFACE, 333,, PROP, 111

SURFACE USAGE
Contact surface

	CONTACT,1,SURF,SURF,202,102
	SURFACE, 102, , PROP, 103
	SURFACE, 202, , MAT, 203
SURFACE USAGE
Slave
Surface
Master
Surface
General coupling surface

	COUPLE, 1, 100, INSIDE, ON, ON
	SURFACE, 100, , ELEM, 11
SURFACE USAGE
ALE coupling surface

	ALE, 1, 100, 101
	SURFACE, 777, , ELEM, 5
	SURFACE, 101, , SEG, 12
SURFACE USAGE
Lagrange Mesh
Euler Mesh
Euler
Material
ALE Coupling Surface
SURFACE USAGE
The same surface can be used for different applications

Example:	Surface 333 is rigid, has contact with another surface	and is used as a coupling surface

	SURFACE, 333, , PROP, 103

	RIGID, 25, 333, 200.,, 1., 1., 1.
	COUPLE, 1, 333, INSIDE, ON, ON
	CONTACT,1,SURF,SURF,202,333
	SURFACE, 202, , MAT, 203
A surface is a collection of 2 dimensional facets that can be used in loads and boundary constraintsA surface is defined as a set of segmentsIt can have a three dimensional goemetrySurfaces do not have physical properties like mass, inertia or thickness but only have a geometrical importance
Introduction to Lagrange
Chapter 11 - Surfaces
MSC.Dytran Seminar Notes

Click to edit Master text styles
Second level
Third level
Fourth level
Fifth level
CONTENTS
 Surface Definition

 Surface Creation

 Surface Usage
SURFACE DEFINITION
SURFACE CREATION

Surface created directly from elements

	SURFACE, 1,, ELEM, 10	SET1, 10, 1, THRU, 499Surface created from properties

	SURFACE, 2,, PROP, 20
	SET1, 20, 101, 102, 103
	PSHELL,101, 1 , .01
	PSHELL,102, 2 , .01
	PSHELL,103, 1 , .01

SURFACE CREATION

Surface created from materials

	SURFACE, 2,, MAT, 30
	SET1, 30, 1, 2
	PSHELL,101, 1 , .01
	PSHELL,102, 2 , .01
	PSHELL,103, 1 , .01
	MAT1, 1, 3E7, , .33, 7800.
	DMATEP,2, 7850., 210.E9, 0.3

SURFACE CREATION (continued)

Surface created from mixed definitions

	SURFACE, 2,, MAT, 30, PROP, 20, ELEM, 10
	SET1, 30, 1
	SET1, 20, 102
	SET1, 10, 1, THRU, 499
	PSHELL,101, 1 , .01
	PSHELL,102, 2 , .01
	PSHELL,103, 1 , .01
	MAT1, 1, 3E7, , .33, 7800.
Surfaces on Solid elements
Surfaces can also be defined on faces of solid elementsThe CFACE entry defines a segment on the relative face on an elementExample: 	Surface 10 is defined with two faces	The relative face 4 of element 1296 is defined as 	cface number 301 and is part of set 22	The relative face 4 of element 1297 is defined as 	cface number 302 and is also part of set 22 	SURFACE, 10, , SEG, 22
	CFACE, 301, 22, 1296, 4
 	CFACE, 302, 22, 1297, 4
DEFINING CFACES
Because most pre-processors do not support writing CFACEs, they can be defined indirectly
 Defining CFACEs by using CQUAD4 and/or CTRIA3 elements with a thickness of 9999.
	SURFACE,20,,SEG,22		PSHELL, 22, 204, 9999.	CQUAD, 301, 22, 1296, 4 	CQUAD, 302, 22, 1297, 4
is the same as
	SURFACE,20,,SEG,22		CFACE, 301, 22, 1296, 4 	CFACE, 302, 22, 1297, 4
 Defining CFACEs by using PLOAD4 entry with pressure 9999.	SURFACE,20,,SEG,22 		PLOAD4, 22, 1296, 9999.	PLOAD4, 22, 1297, 9999.
 is the same as
	SURFACE,20,,SEG,22 		CFACE, 301, 22, 1296, 4	CFACE, 302, 22, 1297, 4
Rigid Connection

	RCONN, 1, SURF, SURF, 7, 8

Rigid Body Definition

	RIGID, 25, 333, 200.,, 1., 1., 1.
	SURFACE, 333,, PROP, 111

SURFACE USAGE
Contact surface

	CONTACT,1,SURF,SURF,202,102
	SURFACE, 102, , PROP, 103
	SURFACE, 202, , MAT, 203
SURFACE USAGE
Slave
Surface
Master
Surface
General coupling surface

	COUPLE, 1, 100, INSIDE, ON, ON
	SURFACE, 100, , ELEM, 11
SURFACE USAGE
ALE coupling surface

	ALE, 1, 100, 101
	SURFACE, 777, , ELEM, 5
	SURFACE, 101, , SEG, 12
SURFACE USAGE
Lagrange Mesh
Euler Mesh
Euler
Material
ALE Coupling Surface
SURFACE USAGE
The same surface can be used for different applications

Example:	Surface 333 is rigid, has contact with another surface	and is used as a coupling surface

	SURFACE, 333, , PROP, 103

	RIGID, 25, 333, 200.,, 1., 1., 1.
	COUPLE, 1, 333, INSIDE, ON, ON
	CONTACT,1,SURF,SURF,202,333
	SURFACE, 202, , MAT, 203
A surface is a collection of 2 dimensional facets that can be used in loads and boundary constraintsA surface is defined as a set of segmentsIt can have a three dimensional goemetrySurfaces do not have physical properties like mass, inertia or thickness but only have a geometrical importance

MSC.Dytran Seminar Notes
Click to edit Master title style
Click to edit Master text styles
Second level
Third level
Fourth level
Fifth level
SURFACE DEFINITION
A surface is a collection of 2 dimensional facets that can be used in loads and boundary constraintsA surface is defined as a set of segmentsIt can have a three dimensional goemetrySurfaces do not have physical properties like mass, inertia or thickness but only have a geometrical importance
A surface is a collection of 2 dimensional facets that can be used in loads and boundary constraintsA surface is defined as a set of segmentsIt can have a three dimensional goemetrySurfaces do not have physical properties like mass, inertia or thickness but only have a geometrical importance
SURFACE DEFINITION
A surface is a collection of 2 dimensional facets that can be used in loads and boundary constraintsA surface is defined as a set of segmentsIt can have a three dimensional goemetrySurfaces do not have physical properties like mass, inertia or thickness but only have a geometrical importance
A surface is a collection of 2 dimensional facets that can be used in loads and boundary constraintsA surface is defined as a set of segmentsIt can have a three dimensional goemetrySurfaces do not have physical properties like mass, inertia or thickness but only have a geometrical importance
A surface is a collection of 2 dimensional facets that can be used in loads and boundary constraintsA surface is defined as a set of segmentsIt can have a three dimensional goemetrySurfaces do not have physical properties like mass, inertia or thickness but only have a geometrical importance
A surface is a collection of 2 dimensional facets that can be used in loads and boundary constraintsA surface is defined as a set of segmentsIt can have a three dimensional goemetrySurfaces do not have physical properties like mass, inertia or thickness but only have a geometrical importance
SURFACE CREATION

Surface created directly from elements

	SURFACE, 1,, ELEM, 10	SET1, 10, 1, THRU, 499Surface created from properties

	SURFACE, 2,, PROP, 20
	SET1, 20, 101, 102, 103
	PSHELL,101, 1 , .01
	PSHELL,102, 2 , .01
	PSHELL,103, 1 , .01

SURFACE CREATION

Surface created from materials

	SURFACE, 2,, MAT, 30
	SET1, 30, 1, 2
	PSHELL,101, 1 , .01
	PSHELL,102, 2 , .01
	PSHELL,103, 1 , .01
	MAT1, 1, 3E7, , .33, 7800.
	DMATEP,2, 7850., 210.E9, 0.3

Surfaces on Solid elements
SURFACE, 20, , SEG, 22
PHELL, 22, 204, 9999.
CQUAD4, 301, 22, 1296, 4
CQUAD4, 302, 22, 1297, 4
SURFACE, 20, , SEG, 22
CFACE,301,22,1296,4
CFACE,302,22,1297,4
SURFACE, 20, , SEG, 22
PLOAD4,22,1296,9999.
PLOAD4,22,1297,9999.
SURFACE, 20, , SEG, 22
PHELL, 22, 204, 9999.
CQUAD4, 301, 22, 1296, 4
CQUAD4, 302, 22, 1297, 4
SURFACE, 20, , SEG, 22
PHELL, 22, 204, 9999.
CQUAD4, 301, 22, 1296, 4
CQUAD4, 302, 22, 1297, 4
SURFACE, 20, , SEG, 22
CFACE,301,22,1296,4
CFACE,302,22,1297,4
SURFACE, 20, , SEG, 22
PLOAD4,22,1296,9999.
PLOAD4,22,1297,9999.
SURFACE, 20, , SEG, 22
CFACE,301,22,1296,4
CFACE,302,22,1297,4
SURFACE, 20, , SEG, 22
PHELL, 22, 204, 9999.
CQUAD4, 301, 22, 1296, 4
CQUAD4, 302, 22, 1297, 4
SURFACE, 20, , SEG, 22
CFACE,301,22,1296,4
CFACE,302,22,1297,4
SURFACE, 20, , SEG, 22
PLOAD4,22,1296,9999.
PLOAD4,22,1297,9999.
SURFACE, 20, , SEG, 22
CFACE,301,22,1296,4
CFACE,302,22,1297,4
SURFACE, 20, , SEG, 22
PHELL, 22, 204, 9999.
CQUAD4, 301, 22, 1296, 4
CQUAD4, 302, 22, 1297, 4
SURFACE, 20, , SEG, 22
CFACE, 301, 22, 1296, 4
CFACE, 302, 22, 1297, 4
SURFACE, 20, , SEG, 22
PLOAD4, 22, 1296, 9999.
PLOAD4, 22, 1297, 9999.
SURFACE, 20, , SEG, 22
CFACE, 301, 22, 1296, 4
CFACE, 302, 22, 1297, 4
Rigid Connection

	RCONN, 1, SURF, SURF, 7, 8

Rigid Body Definition

	RIGID, 25, 333, 200.,, 1., 1., 1.
	SURFACE, 333,, PROP, 111

SURFACE USAGE
SURFACE USAGE
General coupling surface

	COUPLE, 1, 100, INSIDE, ON, ON
	SURFACE, 100, , ELEM, 11
SURFACE USAGE
ALE coupling surface

	ALE, 1, 100, 101
	SURFACE, 777, , ELEM, 5
	SURFACE, 101, , SEG, 12
SURFACE USAGE
Lagrange Mesh
Euler Mesh
Euler
Material
ALE Coupling Surface
SURFACE USAGE
SURFACE, 20, , SEG, 22
PSHELL, 22, 204, 9999.
CQUAD4, 301, 22, 1296, 4
CQUAD4, 302, 22, 1297, 4
SURFACE, 20, , SEG, 22
CFACE, 301, 22, 1296, 4
CFACE, 302, 22, 1297, 4
SURFACE, 20, , SEG, 22
PLOAD4, 22, 1296, 9999.
PLOAD4, 22, 1297, 9999.
SURFACE, 20, , SEG, 22
CFACE, 301, 22, 1296, 4
CFACE, 302, 22, 1297, 4


title: Презентация на тему: MSC.Dytran - 16

text:
START
TIME=99999
CEND
ENDTIME=2.0e-3
CHECK=NO
TITLE= test_container for fast coupling
TLOAD=1
TIC=1
SPC=1
$ Output result for request: elem
TYPE (elem) = ARCHIVE
ELEMENTS (elem) = 1
SET 1 = 1 THRU 200 301 THRU 700 101 THRU 300 701 THRU 900
ELOUT (elem) = EFFPL-MID EFFPL-OUT EFFPL-IN EFFST-MID EFFST-OUT EFFST-IN, TXX-MID TXX-OUT TXX-IN FAIL-MID FAIL-OUT FAIL-IN
TIMES (elem) = 0 thru end by 0.125e-3
SAVE (elem) = 10000
$ Output result for request: euler
TYPE (euler) = ARCHIVE
ELEMENTS (euler) = 2
SET 2 = ALLEULHYDRO
ELOUT (euler) = XVEL YVEL ZVEL SIE PRESSURE FMAT
TIMES (euler) = 0 thru end by 0.125e-3
SAVE (euler) = 10000
$
TYPE(pres2) = ARCHIVE
SAVE(pres2) = 9999
CPLSOUT(pres2) = XVEL,YVEL,ZVEL,PRESSURE,DENSITY,SIE,SSPD
CPLSURFS(pres2) = 32
SET 32 = 1,2
times(pres2) = 0 THRU END BY 0.125e-3
$
$------- Parameter Section ------
PARAM,INISTEP,1.0e-7
PARAM,MINSTEP,1.0e-9
$ Tolerance between ale surface and lagrangian surface
PARAM,STRNOUT,YES
$
$ params defining new solver
PARAM,LIMITER,ROE
PARAM,RKSCHEME,3
$
$ param defining new coupling calculation
PARAM,FASTCOUP,INPLANE,FAIL
$
$
$------- BULK DATA SECTION -------
BEGIN BULK
$
$ --- Define 2819 grid points ---
$
$ ========== PROPERTY SETS ==========
$
$            * Aluminum *
PSHELL, 1, 1, 0.1
$
$            * water *
PEULER1,2,,HYDRO,18
$
TICEUL,18,,,,,,,,+
+,SPHERE,400,2,4,7,,,,+
+,ELEM,500,2,5,6,,,,+
+,ELEM,600,2,6,5
$
SPHERE,400,,5.0,6.0,5.0,3.0
SET1,500,2001,THRU,35000    $ The EULER INSIDE THE bottom box is water
SET1,600,35001,THRU,50000      $ THE REST OF EULER IS WATER TOO
$
TICVAL,4,,DENSITY,2.466-05,SIE,8.618E09   $ Initialize explosive
TICVAL,5,,DENSITY,0.0935E-3,SIE,0         $ SIE=0 for water
$ use 3.206E08 for 14.7 psi, 5.0817E08 for 23.3 psi
TICVAL,6,,DENSITY,0.0935E-3,SIE,0         $ SIE=0 for water
$TICVAL,7,,DENSITY,0.0935E-3,SIE,0         $ SIE=0 for water
$
$ ========= MATERIAL DEFINITIONS ==========
$ -------- Material Aluminum id =1
DMATEP,1,2.5977E-4,10.5E+6,0.33,,,1,1
YLDVM, 1, 48000.
FAILMPS, 1, 0.22
$
$ -------- Material water id =2
DMAT, 29.35e-05, 2
EOSPOL, 2, 319083.
$
$ ----- LBC-name = bottom_surface (water & explosive)  ----
SURFACE, 1, ELEM, 3
SET1, 3, 1, THRU, 200, 301, THRU, 700
COUPLE1,1,1,OUTSIDE,,,,,,+
+,,1,,1
MESH,1,BOX,,,,,,,+
+,-0.2,-0.2,-0.2,10.5,10.5,10.5,,,+
+,30,30,30,,2001,2001,EULER,2
$
$ ----- LBC-name = top_surface (air initially but then converted to water)
SURFACE, 2, ELEM, 4
SET1, 4, 101, THRU, 300, 701, THRU, 900
$
COUPLE1, 2, 2, OUTSIDE, , , , , , +
+, , 2, , 1
MESH,2,BOX,,,,,,,+
+,-0.2,9.8,-0.2,10.5,6.0,10.5,,,+
+,15,15,15,,35001,35001,EULER,2
$
COUP1FL,1,1.1463E-07,3.206E+08
$
COUP1INT,1,1,2
$
FLOWDEF, 1, , HYDRO, , , , , , +
+, FLOW, BOTH
$
ENDDATA

MSC.Dytran Seminar Notes
Click to edit Master title style
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Second level
Third level
Fourth level
Fifth level
Tij
Tij
Fface = Tij · A

Fnode = (1/4) · Fface
Inside
Outside
START
TIME=99999
CEND
ENDTIME=2.0e-3
CHECK=NO
TITLE= test_container for fast coupling
TLOAD=1
TIC=1
SPC=1
$ Output result for request: elem
TYPE (elem) = ARCHIVE
ELEMENTS (elem) = 1
SET 1 = 1 THRU 200 301 THRU 700 101 THRU 300 701 THRU 900
ELOUT (elem) = EFFPL-MID EFFPL-OUT EFFPL-IN EFFST-MID EFFST-OUT EFFST-IN, TXX-MID TXX-OUT TXX-IN FAIL-MID FAIL-OUT FAIL-IN
TIMES (elem) = 0 thru end by 0.125e-3
SAVE (elem) = 10000
$ Output result for request: euler
TYPE (euler) = ARCHIVE
ELEMENTS (euler) = 2
SET 2 = ALLEULHYDRO
ELOUT (euler) = XVEL YVEL ZVEL SIE PRESSURE FMAT
TIMES (euler) = 0 thru end by 0.125e-3
SAVE (euler) = 10000
$
TYPE(pres2) = ARCHIVE
SAVE(pres2) = 9999
CPLSOUT(pres2) = XVEL,YVEL,ZVEL,PRESSURE,DENSITY,SIE,SSPD
CPLSURFS(pres2) = 32
SET 32 = 1,2
times(pres2) = 0 THRU END BY 0.125e-3
$
$------- Parameter Section ------
PARAM,INISTEP,1.0e-7
PARAM,MINSTEP,1.0e-9
$ Tolerance between ale surface and lagrangian surface
PARAM,STRNOUT,YES
$
$ params defining new solver
PARAM,LIMITER,ROE
PARAM,RKSCHEME,3
$
$ param defining new coupling calculation
PARAM,FASTCOUP,INPLANE,FAIL
$
$
$------- BULK DATA SECTION -------
BEGIN BULK
$
$ --- Define 2819 grid points ---
$
$ ========== PROPERTY SETS ==========
$
$            * Aluminum *
PSHELL, 1, 1, 0.1
$
$            * water *
PEULER1,2,,HYDRO,18
$
TICEUL,18,,,,,,,,+
+,SPHERE,400,2,4,7,,,,+
+,ELEM,500,2,5,6,,,,+
+,ELEM,600,2,6,5
$
SPHERE,400,,5.0,6.0,5.0,3.0
SET1,500,2001,THRU,35000    $ The EULER INSIDE THE bottom box is water
SET1,600,35001,THRU,50000      $ THE REST OF EULER IS WATER TOO
$
TICVAL,4,,DENSITY,2.466-05,SIE,8.618E09   $ Initialize explosive
TICVAL,5,,DENSITY,0.0935E-3,SIE,0         $ SIE=0 for water
$ use 3.206E08 for 14.7 psi, 5.0817E08 for 23.3 psi
TICVAL,6,,DENSITY,0.0935E-3,SIE,0         $ SIE=0 for water
$TICVAL,7,,DENSITY,0.0935E-3,SIE,0         $ SIE=0 for water
$
$ ========= MATERIAL DEFINITIONS ==========
$ -------- Material Aluminum id =1
DMATEP,1,2.5977E-4,10.5E+6,0.33,,,1,1
YLDVM, 1, 48000.
FAILMPS, 1, 0.22
$
$ -------- Material water id =2
DMAT, 29.35e-05, 2
EOSPOL, 2, 319083.
$
$ ----- LBC-name = bottom_surface (water & explosive)  ----
SURFACE, 1, ELEM, 3
SET1, 3, 1, THRU, 200, 301, THRU, 700
COUPLE1,1,1,OUTSIDE,,,,,,+
+,,1,,1
MESH,1,BOX,,,,,,,+
+,-0.2,-0.2,-0.2,10.5,10.5,10.5,,,+
+,30,30,30,,2001,2001,EULER,2
$
$ ----- LBC-name = top_surface (air initially but then converted to water)
SURFACE, 2, ELEM, 4
SET1, 4, 101, THRU, 300, 701, THRU, 900
$
COUPLE1, 2, 2, OUTSIDE, , , , , , +
+, , 2, , 1
MESH,2,BOX,,,,,,,+
+,-0.2,9.8,-0.2,10.5,6.0,10.5,,,+
+,15,15,15,,35001,35001,EULER,2
$
COUP1FL,1,1.1463E-07,3.206E+08
$
COUP1INT,1,1,2
$
FLOWDEF, 1, , HYDRO, , , , , , +
+, FLOW, BOTH
$
ENDDATA
START
TIME=99999
CEND
ENDTIME=2.0e-3
CHECK=NO
TITLE= test_container for fast coupling
TLOAD=1
TIC=1
SPC=1
$ Output result for request: elem
TYPE (elem) = ARCHIVE
ELEMENTS (elem) = 1
SET 1 = 1 THRU 200 301 THRU 700 101 THRU 300 701 THRU 900
ELOUT (elem) = EFFPL-MID EFFPL-OUT EFFPL-IN EFFST-MID EFFST-OUT EFFST-IN, TXX-MID TXX-OUT TXX-IN FAIL-MID FAIL-OUT FAIL-IN
TIMES (elem) = 0 thru end by 0.125e-3
SAVE (elem) = 10000
$ Output result for request: euler
TYPE (euler) = ARCHIVE
ELEMENTS (euler) = 2
SET 2 = ALLEULHYDRO
ELOUT (euler) = XVEL YVEL ZVEL SIE PRESSURE FMAT
TIMES (euler) = 0 thru end by 0.125e-3
SAVE (euler) = 10000
$
TYPE(pres2) = ARCHIVE
SAVE(pres2) = 9999
CPLSOUT(pres2) = XVEL,YVEL,ZVEL,PRESSURE,DENSITY,SIE,SSPD
CPLSURFS(pres2) = 32
SET 32 = 1,2
times(pres2) = 0 THRU END BY 0.125e-3
$
$------- Parameter Section ------
PARAM,INISTEP,1.0e-7
PARAM,MINSTEP,1.0e-9
$ Tolerance between ale surface and lagrangian surface
PARAM,STRNOUT,YES
$
$ params defining new solver
PARAM,LIMITER,ROE
PARAM,RKSCHEME,3
$
$ param defining new coupling calculation
PARAM,FASTCOUP,INPLANE,FAIL
$
$
$------- BULK DATA SECTION -------
BEGIN BULK
$
$ --- Define 2819 grid points ---
$
$ ========== PROPERTY SETS ==========
$
$            * Aluminum *
PSHELL, 1, 1, 0.1
$
$            * water *
PEULER1,2,,HYDRO,18
$
TICEUL,18,,,,,,,,+
+,SPHERE,400,2,4,7,,,,+
+,ELEM,500,2,5,6,,,,+
+,ELEM,600,2,6,5
$
SPHERE,400,,5.0,6.0,5.0,3.0
SET1,500,2001,THRU,35000    $ The EULER INSIDE THE bottom box is water
SET1,600,35001,THRU,50000      $ THE REST OF EULER IS WATER TOO
$
TICVAL,4,,DENSITY,2.466-05,SIE,8.618E09   $ Initialize explosive
TICVAL,5,,DENSITY,0.0935E-3,SIE,0         $ SIE=0 for water
$ use 3.206E08 for 14.7 psi, 5.0817E08 for 23.3 psi
TICVAL,6,,DENSITY,0.0935E-3,SIE,0         $ SIE=0 for water
$TICVAL,7,,DENSITY,0.0935E-3,SIE,0         $ SIE=0 for water
$
$ ========= MATERIAL DEFINITIONS ==========
$ -------- Material Aluminum id =1
DMATEP,1,2.5977E-4,10.5E+6,0.33,,,1,1
YLDVM, 1, 48000.
FAILMPS, 1, 0.22
$
$ -------- Material water id =2
DMAT, 29.35e-05, 2
EOSPOL, 2, 319083.
$
$ ----- LBC-name = bottom_surface (water & explosive)  ----
SURFACE, 1, ELEM, 3
SET1, 3, 1, THRU, 200, 301, THRU, 700
COUPLE1,1,1,OUTSIDE,,,,,,+
+,,1,,1
MESH,1,BOX,,,,,,,+
+,-0.2,-0.2,-0.2,10.5,10.5,10.5,,,+
+,30,30,30,,2001,2001,EULER,2
$
$ ----- LBC-name = top_surface (air initially but then converted to water)
SURFACE, 2, ELEM, 4
SET1, 4, 101, THRU, 300, 701, THRU, 900
$
COUPLE1, 2, 2, OUTSIDE, , , , , , +
+, , 2, , 1
MESH,2,BOX,,,,,,,+
+,-0.2,9.8,-0.2,10.5,6.0,10.5,,,+
+,15,15,15,,35001,35001,EULER,2
$
COUP1FL,1,1.1463E-07,3.206E+08
$
COUP1INT,1,1,2
$
FLOWDEF, 1, , HYDRO, , , , , , +
+, FLOW, BOTH
$
ENDDATA
START
TIME=99999
CEND
ENDTIME=2.0e-3
CHECK=NO
TITLE= test_container for fast coupling
TLOAD=1
TIC=1
SPC=1
$ Output result for request: elem
TYPE (elem) = ARCHIVE
ELEMENTS (elem) = 1
SET 1 = 1 THRU 200 301 THRU 700 101 THRU 300 701 THRU 900
ELOUT (elem) = EFFPL-MID EFFPL-OUT EFFPL-IN EFFST-MID EFFST-OUT EFFST-IN, TXX-MID TXX-OUT TXX-IN FAIL-MID FAIL-OUT FAIL-IN
TIMES (elem) = 0 thru end by 0.125e-3
SAVE (elem) = 10000
$ Output result for request: euler
TYPE (euler) = ARCHIVE
ELEMENTS (euler) = 2
SET 2 = ALLEULHYDRO
ELOUT (euler) = XVEL YVEL ZVEL SIE PRESSURE FMAT
TIMES (euler) = 0 thru end by 0.125e-3
SAVE (euler) = 10000
$
TYPE(pres2) = ARCHIVE
SAVE(pres2) = 9999
CPLSOUT(pres2) = XVEL,YVEL,ZVEL,PRESSURE,DENSITY,SIE,SSPD
CPLSURFS(pres2) = 32
SET 32 = 1,2
times(pres2) = 0 THRU END BY 0.125e-3
$
$------- Parameter Section ------
PARAM,INISTEP,1.0e-7
PARAM,MINSTEP,1.0e-9
$ Tolerance between ale surface and lagrangian surface
PARAM,STRNOUT,YES
$
$ params defining new solver
PARAM,LIMITER,ROE
PARAM,RKSCHEME,3
$
$ param defining new coupling calculation
PARAM,FASTCOUP,INPLANE,FAIL
$
$
$------- BULK DATA SECTION -------
BEGIN BULK
$
$ --- Define 2819 grid points ---
$
$ ========== PROPERTY SETS ==========
$
$            * Aluminum *
PSHELL, 1, 1, 0.1
$
$            * water *
PEULER1,2,,HYDRO,18
$
TICEUL,18,,,,,,,,+
+,SPHERE,400,2,4,7,,,,+
+,ELEM,500,2,5,6,,,,+
+,ELEM,600,2,6,5
$
SPHERE,400,,5.0,6.0,5.0,3.0
SET1,500,2001,THRU,35000    $ The EULER INSIDE THE bottom box is water
SET1,600,35001,THRU,50000      $ THE REST OF EULER IS WATER TOO
$
TICVAL,4,,DENSITY,2.466-05,SIE,8.618E09   $ Initialize explosive
TICVAL,5,,DENSITY,0.0935E-3,SIE,0         $ SIE=0 for water
$ use 3.206E08 for 14.7 psi, 5.0817E08 for 23.3 psi
TICVAL,6,,DENSITY,0.0935E-3,SIE,0         $ SIE=0 for water
$TICVAL,7,,DENSITY,0.0935E-3,SIE,0         $ SIE=0 for water
$
$ ========= MATERIAL DEFINITIONS ==========
$ -------- Material Aluminum id =1
DMATEP,1,2.5977E-4,10.5E+6,0.33,,,1,1
YLDVM, 1, 48000.
FAILMPS, 1, 0.22
$
$ -------- Material water id =2
DMAT, 29.35e-05, 2
EOSPOL, 2, 319083.
$
$ ----- LBC-name = bottom_surface (water & explosive)  ----
SURFACE, 1, ELEM, 3
SET1, 3, 1, THRU, 200, 301, THRU, 700
COUPLE1,1,1,OUTSIDE,,,,,,+
+,,1,,1
MESH,1,BOX,,,,,,,+
+,-0.2,-0.2,-0.2,10.5,10.5,10.5,,,+
+,30,30,30,,2001,2001,EULER,2
$
$ ----- LBC-name = top_surface (air initially but then converted to water)
SURFACE, 2, ELEM, 4
SET1, 4, 101, THRU, 300, 701, THRU, 900
$
COUPLE1, 2, 2, OUTSIDE, , , , , , +
+, , 2, , 1
MESH,2,BOX,,,,,,,+
+,-0.2,9.8,-0.2,10.5,6.0,10.5,,,+
+,15,15,15,,35001,35001,EULER,2
$
COUP1FL,1,1.1463E-07,3.206E+08
$
COUP1INT,1,1,2
$
FLOWDEF, 1, , HYDRO, , , , , , +
+, FLOW, BOTH
$
ENDDATA


title: Презентация на тему: MSC.Mvision - 12-1

text:
Click to edit Master title style
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Second level
Third level
Fourth level
Fifth level
MVI320, Section 12, June 2001


title: Презентация на тему: MSC.Mvision - 11-1

text:
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Second level
Third level
Fourth level
Fifth level
MVI320, Section 11, June 2001


title: Презентация на тему: MSC.Mvision - 10-1

text:
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Second level
Third level
Fourth level
Fifth level
MVI320, Section 10, June 2001
1
2
3
4
5
6
9
10

1003


title: Презентация на тему: MSC.Mvision - 08-1

text:
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Second level
Third level
Fourth level
Fifth level
MVI320, Section 8, June 2001
0
3
0
3
1
1
1
29 Msi
0.101
28.51  Msi
0.10123
1.0
0.001


title: Презентация на тему: MSC.Mvision - 07-1

text:
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Second level
Third level
Fourth level
Fifth level
MVI320, Section 7, June 2001
67. ksi
4
PROPERTY
US11T(±1 ksi)
70. F
3
ENVIRONMENT
Temperature (±1.5 F)
T6 0.040-0.125 inch Plate
2
SPECIMEN
Treatment
Thickness
 Form
7075 Aluminum Alloy
1
MATERIAL
Common Name
67. ksi
4
PROPERTY
US11T(±1 ksi)
70. F
3
ENVIRONMENT
Temperature (±1.5 F)
T6 0.040-0.125 inch Plate
2
SPECIMEN
Treatment
Thickness
 Form
7075 Aluminum Alloy
1
MATERIAL
Common Name


title: Презентация на тему: MSC.Mvision - 14-1

text:
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Fifth level
MVI320, Section 14, June 2001


title: Презентация на тему: MSC.Mvision - 08-2

text:
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Fifth level
MVI320, Section 8, June 2001


title: Презентация на тему: MSC.Flightloads 1.2

text:
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
Results Evaluation
New in MSC.FlightLoads 2001
Basic SOL 145 Job Creation
Unsteady Aerodynamic Database Creation/Reuse
Definition of M-k Pair Sets
Nondimensional k OR
Dimensional k Range via Velocity and Cyclic Frequency Ranges
Subcase and Job Definition
PK, PKNL, K, KE
M-k Pairs from Defined Sets for each Subcase
Simplified Eigenvector Extraction Requests
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
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Second level
Third level
Fourth level
Fifth level
FLDS120, Section 1.2, December 2001
CAD
MSC.NASTRAN
MSC.PATRAN
MSC.FlightLoads & Dynamics
CATIA
Pro/ENGINEER
UNIGRAPHICS
IGES
AP203
ACIS
MSC.NASTRAN
JAVA
C, C++
Etc.
PCL
DMAP
MSC.PATRAN
MSC.NASTRAN
FlightLoads
BEGIN BULK
$ 1.0g Cruise: Total Load
FORCE, 100, 1056,, 742.
FORCE, 100, 1057,,234.
MOMENT, 100, 1057,, -796.
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
Results Evaluation
New in MSC.FlightLoads 2001
Basic SOL 145 Job Creation
Unsteady Aerodynamic Database Creation/Reuse
Definition of M-k Pair Sets
Nondimensional k OR
Dimensional k Range via Velocity and Cyclic Frequency Ranges
Subcase and Job Definition
PK, PKNL, K, KE
M-k Pairs from Defined Sets for each Subcase
Simplified Eigenvector Extraction Requests
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MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
Results Evaluation
New in MSC.FlightLoads 2001
Basic SOL 145 Job Creation
Unsteady Aerodynamic Database Creation/Reuse
Definition of M-k Pair Sets
Nondimensional k OR
Dimensional k Range via Velocity and Cyclic Frequency Ranges
Subcase and Job Definition
PK, PKNL, K, KE
M-k Pairs from Defined Sets for each Subcase
Simplified Eigenvector Extraction Requests
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
Basic SOL 145 Job Creation
Unsteady Aerodynamic Database Creation/Reuse
Definition of M-k Pair Sets
Nondimensional k OR
Dimensional k Range via Velocity and Cyclic Frequency Ranges
Subcase and Job Definition
PK, PKNL, K, KE
M-k Pairs from Defined Sets for each Subcase
Simplified Eigenvector Extraction Requests
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
Basic SOL 145 Job Creation
Unsteady Aerodynamic Database Creation/Reuse
Definition of M-k Pair Sets
Nondimensional k OR
Dimensional k Range via Velocity and Cyclic Frequency Ranges
Subcase and Job Definition
PK, PKNL, K, KE
M-k Pairs from Defined Sets for each Subcase
Simplified Eigenvector Extraction Requests
New in MSC.FlightLoads 2001
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New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
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New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
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New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
Basic SOL 145 Job Creation
Unsteady Aerodynamic Database Creation/Reuse
Definition of M-k Pair Sets
Nondimensional k OR
Dimensional k Range via Velocity and Cyclic Frequency Ranges
Subcase and Job Definition
PK, PKNL, K, KE
M-k Pairs from Defined Sets for each Subcase
Simplified Eigenvector Extraction Requests
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
New in MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
User Interface
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
Database Archive/Reuse
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
MSC.FlightLoads in the Process
MSC.FlightLoads 2001
MSC.FlightLoads 2001
MSC.FlightLoads 2001
MSC.NASTRAN
JAVA
C, C++
Etc.
PCL
DMAP
MSC.PATRAN
MSC.NASTRAN
FlightLoads
MSC.FlightLoads 2001
MSC.FlightLoads 2001
MSC.FlightLoads 2001
MSC.FlightLoads 2001
MSC.FlightLoads 2001
MSC.FlightLoads 2001
MSC.FlightLoads 2001
MSC.FlightLoads 2001
MSC.FlightLoads 2001
MSC.FlightLoads 2001
MSC.FlightLoads 2001
MSC.FlightLoads 2001
MSC.FlightLoads 2001


title: Презентация на тему: MSC.Mvision - 09-1

text:
FORTRAN TRANSPOSE
FORTRAN TRANSPOSE
C TRANSPOSE
C TRANSPOSE
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MVI320, Section 9, June 2001
FORTRAN TRANSPOSE
FORTRAN TRANSPOSE
C TRANSPOSE
C TRANSPOSE


title: Презентация на тему: MSC.Mvision - 13-1

text:
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MVI320, Section 13, June 2001


title: Презентация на тему: MSC.Mvision - 01-2

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MVI320, Section 1, June 2001
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title: Презентация на тему: MSC.Mvision - 01-5

text:
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MVI320, Section 1, June 2001


title: Презентация на тему: MSC.Mvision - 01-3

text:
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MVI320, Section 1, June 2001
pwd
pwd
cp
more
cd
Is
Is


title: Презентация на тему: MSC.Mvision - 06-1

text:
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MVI320, Section 6, June 2001
Write Text
Read Text
Session
Save Spd As
Save Spd
Open Spd
New
Insert Rows
Clear Spreadsheets
Clear Formula
Clear
Paste
Copy
Cut
Debug
Footnote
Fill Right
Fill Down
Delete Cells
Insert Cells
Insert Columns
Goto
Recompute All
Allow cell Auto-recompute
Inhibit cell Auto-recompute
Paste Function
Change Databank
Select
Save Db
Show Summary Build Messages
Show All
      Build Messages
Create Builder
Log File
User Defined Format
Preset Formats
Columns
Remove curve from plot
Add curve to plot
Display cell format
Display cell formula
Display default cell data


title: Презентация на тему: MSC.Mvision Appendix B

text:
Unix Quick Reference
Unix Quick Reference (Cont.)
Unix Quick Reference (Cont.)
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MVI320, Appendix B, August 2001
APPENDIX B
Unix Quick Reference
Unix Quick Reference (Cont.)
Unix Quick Reference (Cont.)


title: Презентация на тему: MSC.Dytran - 08

text:
MSC.Dytran Seminar Notes
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G
n
Defines the minimum pressure or spall characteristics of the materialPMINC- Constant PMIN model	The spall pressure has a constant value.
Pressure
Volume
PMINC
SPALLATION (PMIN) MODELS
Defines the Criterion for Failure of the MaterialFAILMPS- Maximum Plastic Strain Failure ModelDefines the equivalent plastic strain at which ductile failure of the material occurs.FAILEXn- User Defined FailureDefine Failure in a User Subroutine.FAILEST- Maximum equivalent stress and minimum timestepTotal failure occurs when the equivalent stress exceeds the defined value and the element timestep drops below a specified limit.FAILMES- Maximum equivalent stressFailure occurs when the equivalent stress exceeds a defined maximum value.FAILPRS- Maximum pressureFailure occurs when the hydrodynamic pressure exceeds a defined maximum.FAILSDT- Max equivalent plastic strain and min timestepFailure occurs when the equivalent plastic strain exceeds a specified value and the element timestep drops below a specified limit.
FAILURE MODELS
Example of the definition of steel material (MID = 333) with properties:Density	=	7830 kg/m3Bulk Modulus =	1.69 1011 N/m2Shear Modulus =	8.18 1010 N/m2Yield Stress =	5. 108 N/m2Spallation =	-3.8 10 9 N/m2Failure =		50% plastic strain		DMAT, 333, 7830., 444, 555, 666, 777, 888	EOSPOL, 444, 1.69 E11	SHREL, 555, 8.18 E10	YLDVM, 666, 5.E8	FAILMPS, 777, .5	PMINC, 888, -3.8 E9For a discussion on the use of the polynomial equation of state and the use of the elastic constraints (Youngs modulus, Bulk modulus) see the modeling section.
MATERIAL DEFINITION EXAMPLE
PMINC
Defines the minimum pressure or spall characteristics of the materialPMINC- Constant PMIN model	The spall pressure has a constant value.
SPALLATION (PMIN) MODELS
Defines the Criterion for Failure of the MaterialFAILMPS- Maximum Plastic Strain Failure ModelDefines the equivalent plastic strain at which ductile failure of the material occurs.FAILEXn- User Defined FailureDefine Failure in a User Subroutine.FAILEST- Maximum equivalent stress and minimum timestepTotal failure occurs when the equivalent stress exceeds the defined value and the element timestep drops below a specified limit.FAILMES- Maximum equivalent stressFailure occurs when the equivalent stress exceeds a defined maximum value.FAILPRS- Maximum pressureFailure occurs when the hydrodynamic pressure exceeds a defined maximum.FAILSDT- Max equivalent plastic strain and min timestepFailure occurs when the equivalent plastic strain exceeds a specified value and the element timestep drops below a specified limit.
FAILURE MODELS
Example of the definition of steel material (MID = 333) with properties:Density	=	7830 kg/m3Bulk Modulus =	1.69 1011 N/m2Shear Modulus =	8.18 1010 N/m2Yield Stress =	5. 108 N/m2Spallation =	-3.8 10 9 N/m2Failure =		50% plastic strain		DMAT, 333, 7830., 444, 555, 666, 777, 888	EOSPOL, 444, 1.69 E11	SHREL, 555, 8.18 E10	YLDVM, 666, 5.E8	FAILMPS, 777, .5	PMINC, 888, -3.8 E9For a discussion on the use of the polynomial equation of state and the use of the elastic constraints (Youngs modulus, Bulk modulus) see the modeling section.
MATERIAL DEFINITION EXAMPLE
n


title: Презентация на тему: MSC.Mvision - 01-4


title: Презентация на тему: MSC.Mvision - 05-1

text:
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MVI320, Section 5, June 2001
Crossplot
 & spreadsheet
Data Viewer
Material Browser
Crossplot
 & spreadsheet
Data Viewer
Material Browser


title: Презентация на тему: MSC.Mvision Appendix A

text:
One Set of Mnemonics (PDA Rule)
Material Property Mnemonics
Query Operators
Examples of Queries
CLICK TO EDIT MASTER TITLE STYLE
MVI320, Appendix A, August 2001
APPENDIX A
One Set of Mnemonics (PDA Rule)
Material Property Mnemonics
Query Operators
Examples of Queries
One Set of Mnemonics (PDA Rule)
Material Property Mnemonics
Query Operators
Examples of Queries


title: Презентация на тему: MSC.Mvision Appendix D

text:
Data, Attribute and File Limits
MSC.Mvision Reserved Words
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MVI320, Appendix D, August 2001
APPENDIX D
Data, Attribute and File Limits
MSC.Mvision Reserved Words


title: Презентация на тему: MSC.Mvision - 02-1

text:
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MVI320, Section 2, June 2001


title: Презентация на тему: MSC.Mvision - 01-1

text:
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MVI320, Section 1, June 2001
Mvision Builder
Patran Materials
Mvision Evaluator
Mvision Pro
Enterprise Mvision
Uses FrameMaker
For reporting
+
4207
4200


title: Презентация на тему: MSC.Mvision Appendix C

text:
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MVI320, Appendix C, August 2001
APPENDIX C
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title: Презентация на тему: MSC.Flightloads 5.2

text:
Post the Structural Model
Structural Deformation
Aerodynamic Forces on Rigid Aircraft
Elastic Increments
Inertia Loads
Workshop # 1: Flight Cases

All subcases have angle of attack and canard angle as free variables
In Subcase 4 a Pitch Rate of 0.000356 is used to balance the 4G pull
Workshop # 1: Model Data
Wing Span (full model) = 40 ft
Wing Area (full model)=  400 ft2
Mean Chord = 10 ft
Workshop # 1: Tasks
Create the Flight Loads model as shown in the case study. Try  increasing the fidelity of the aeromesh to better capture the aero pressure gradients.
Go through the exercise using the steps outlined on the next page
Workshop # 1: Analysis Steps

FLDS120, Section 5.2, June 2002
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MSC Corporate Overview Speaker Notes
Nas111 Section 5.2, August 2001
Lumped Masses
Wing
Canard
GRID     363             26.7783 1.25    0.
GRID*    364                             27.5           -5.57318-6
*        0.
$ Loads for Load Case : Constraints
SPCADD   2       4       6
$ Displacement Constraints of Load Set : fix_246
SPC1     4       246     90      97      98      99      100
$ Displacement Constraints of Load Set : fix_1
SPC1     6       1       90
$ Loads for Load Case : constraints
$
$ Aeroelastic Model Parameters
PARAM   AUNITS  0.031081
$
100
99
98
97
90
246
4
SPC1
-etc.-
G4
G3
G2
G1
C
SID
SPC1
10
9
8
7
6
5
4
3
2
1
6
4
2
SPCADD
-etc.-
S5
S4
S3
S2
S1
SID
SPCADD
10
9
8
7
6
5
4
3
2
1
GRID     363             26.7783 1.25    0.
GRID*    364                             27.5           -5.57318-6
*        0.
$ Loads for Load Case : Constraints
SPCADD   2       4       6
$ Displacement Constraints of Load Set : fix_246
SPC1     4       246     90      97      98      99      100
$ Displacement Constraints of Load Set : fix_1
SPC1     6       1       90
$ Loads for Load Case : constraints
$
$ Aeroelastic Model Parameters
PARAM   AUNITS  0.031081
$
X43
Z4
Y4
X4
X12
Z1
Y1
 X1
1
4
3
0
1000
1000
CAERO1
5.
0.
7.5
13.
5.
0.
0.
13.
IGID
LCHORD
LSPAN
NCORD
NSPAN
CP
PID
EID
CAERO1
10
9
8
7
6
5
4
3
2
1
$ Aeroelastic Model Parameters
PARAM   AUNITS  0.031081
$
$ Global Data for Steady Aerodynamics
AEROS   0       0       10.     40.     200.
$
$ Flat Aero Surface: ls_canard
PAERO1  1000
CAERO1  1000    1000    0       3       4                       1
        13.     0.      0.      5.      13.     7.5     0.      5.
$
$ Flat Aero Surface: ls_wing
PAERO1  1100
CAERO1  1100    1100    0       8       4                       1
        25.     0.      0.      10.     13.453  20.     0.      9.999999
$
$ Surface Spline: sp_wing
AELIST  1       1100    1101    1102
1000
PAERO1
B6
B5
B4
B2
B1
PID
PAERO1
10
9
8
7
6
5
4
3
2
1
$ Aeroelastic Model Parameters
PARAM   AUNITS  0.031081
$
$ Global Data for Steady Aerodynamics
AEROS   0       0       10.     40.     200.
$
$ Flat Aero Surface: ls_canard
PAERO1  1000
CAERO1  1000    1000    0       3       4                       1
        13.     0.      0.      5.      13.     7.5     0.      5.
$
$ Flat Aero Surface: ls_wing
PAERO1  1100
CAERO1  1100    1100    0       8       4                       1
        25.     0.      0.      10.     13.453  20.     0.      9.999999
$
$ Surface Spline: sp_wing
AELIST  1       1100    1101    1102
ct_can Markers
1
0
3
1
ct_can
 1
AESURF
TQULIM
TQLLIM
HMULIM
HMLLIM
PULM
PLLIM
CREFS
CREFC
1.047
-1.047
37.5
 5
LDW
EFF
ALID2
CID2
ALID1
CID1
LABEL
ID
AESURF
10
9
8
7
6
5
4
3
2
1
AELIST  2       1000    1001    1002    1003    1004    1005    1006
        1007    1008    1009    1010    1011
SET1    11      200     201     202     203     204     205     206
        207     208     209     210     211     212     213     214
        215     216     217     218     219     220     221     222
        223     224     225     226     227     228     229     230
        231     232     233     234
SPLINE4 11      1000    2               11      0.      IPS     BOTH
$
$ Control Device: ct_can
AELIST  3       1000    1001    1002    1003    1004    1005    1006
        1007    1008    1009    1010    1011
AESURF  1       ct_can  1       3       0               1.
        5.      37.5    -1.047  1.047
$
$ FEM Rigid Body DOFs
SUPORT1 1       90      35
AELIST  2       1000    1001    1002    1003    1004    1005    1006
        1007    1008    1009    1010    1011
SET1    11      200     201     202     203     204     205     206
        207     208     209     210     211     212     213     214
        215     216     217     218     219     220     221     222
        223     224     225     226     227     228     229     230
        231     232     233     234
SPLINE4 11      1000    2               11      0.      IPS     BOTH
$
$ Control Device: ct_can
AELIST  3       1000    1001    1002    1003    1004    1005    1006
        1007    1008    1009    1010    1011
AESURF  1       ct_can  1       3       0               1.
        5.      37.5    -1.047  1.047
$
$ FEM Rigid Body DOFs
SUPORT1 1       90      35
1006
1005
1004
1003
1002
1001
1000
 3
AELIST
-etc.-
E5
E4
E3
E2
E1
SID
AELIST
10
9
8
7
6
5
4
3
2
1
sp_wing Markers
sp_canard Markers
$ Flat Aero Surface: ls_wing
PAERO1  1100
CAERO1  1100    1100    0       8       4                       1
        25.     0.      0.      10.     13.453  20.     0.      9.999999
$
$ Surface Spline: sp_wing
AELIST  1       1100    1101    1102    1103    1104    1105    1106
        1107    1108    1109    1110    1111    1112    1113    1114
        1115    1116    1117    1118    1119    1120    1121    1122
        1123    1124    1125    1126    1127    1128    1129    1130
        1131
SET1    10      100     111     112     121     122     302     304
        306     310     312     326     328     330     332     334
        336     354     356     358     362     364
SPLINE4 10      1100    1               10      0.      FPS     BOTH
        10      10
$
$ Surface Spline: sp_canard
AELIST  2       1000    1001    1002    1003    1004    1005    1006
        1007    1008    1009    1010    1011
SET1    11      200     201     202     203     204     205     206
        207     208     209     210     211     212     213     214
        215     216     217     218     219     220     221     222
        223     224     225     226     227     228     229     230
        231     232     233     234
SPLINE4 11      1000    2               11      0.      IPS     BOTH
$
BOTH
FPS
0.
10
1
1100
 10
SPLINE4
MELEM
NELEM
10
10
USAGE
METH
DZ
SETG
AELIST
CAERO
EID
SPLINE4
10
9
8
7
6
5
4
3
2
1
302
122
121
112
111
100
 10
SET1
-etc.-
G6
G5
G4
G3
G2
G1
SID
SET1
10
9
8
7
6
5
4
3
2
1
$
$ Surface Spline: sp_wing
AELIST  1       1100    1101    1102    1103    1104    1105    1106
        1107    1108    1109    1110    1111    1112    1113    1114
        1115    1116    1117    1118    1119    1120    1121    1122
        1123    1124    1125    1126    1127    1128    1129    1130
        1131
SET1    10      100     111     112     121     122     302     304
        306     310     312     326     328     330     332     334
        336     354     356     358     362     364
SPLINE4 10      1100    1               10      0.      FPS     BOTH
        10      10
$
$ Surface Spline: sp_canard
AELIST  2       1000    1001    1002    1003    1004    1005    1006
        1007    1008    1009    1010    1011
SET1    11      200     201     202     203     204     205     206
        207     208     209     210     211     212     213     214
        215     216     217     218     219     220     221     222
        223     224     225     226     227     228     229     230
        231     232     233     234
SPLINE4 11      1000    2               11      0.      IPS     BOTH
$
$
PARAM   GRDPNT  90
$
PARAM   WTMASS  .031081
$
PARAM   AUNITS  .031081
$
SUPORT1 1       90      35
$
The PARAM,GRDPNT entry causes the grid point weight generator to be executed using grid point 90 as the reference point.  Then the inertia matrix, the transfer matrix from basic to principal axes and other pertinent inertia data are printed.
The PARAM,WTMASS,ginv causes all the structural masses and mass densities to be multiplied by ginv (i.E., By one over the acceleration of gravity).  The dynamic pressure supplied for aerodynamic force calculations will not be multiplied by ginv.
The PARAM, AUNITS, ginv permits the accelerations on the trim entry to be specified in units of load factor (i.e., in g's)
$
PARAM   GRDPNT  90
$
PARAM   WTMASS  .031081
$
PARAM   AUNITS  .031081
$
SUPORT1 1       90      35
$
$ Aeroelastic Model Parameters
PARAM   AUNITS  0.031081
$
$ Global Data for Steady Aerodynamics
AEROS   0       0       10.     40.     200.
$
$ Flat Aero Surface: ls_canard
PAERO1  1000 $
200
40
10
0
 0
AEROS
SYMXY
SYMXZ
REFS
REFB
REFC
RCSID
ACSID
AEROS
10
9
8
7
6
5
4
3
2
1
$
$ Rigid Body Motion Trim Variables: AESTAT
AESTAT  2       ANGLEA
AESTAT  3       SIDES
AESTAT  4       ROLL
AESTAT  5       PITCH
AESTAT  6       YAW
AESTAT  7       URDD1
AESTAT  8       URDD2
AESTAT  9       URDD3
AESTAT  10      URDD4
AESTAT  11      URDD5
AESTAT  12      URDD6
$
$ Trim Parameters for Subcase: 1
TRIM    1       .6      99.     SIDES   0.      ROLL    0.
        PITCH   0.      YAW     0.      URDD1   0.      URDD2   0.
        URDD3   1.      URDD4   0.      URDD5   0.      URDD6   0.
$
$ Trim Parameters for Subcase: 2
TRIM    2       1.2     395.    SIDES   0.      ROLL    0.
        PITCH   0.      YAW     0.      URDD1   0.      URDD2   0.
        URDD3   1.      URDD4   0.      URDD5   0.      URDD6   0.
$
$ Trim Parameters for Subcase: 3
TRIM    3       1.2     2057.   SIDES   0.      ROLL    0.
        PITCH   0.      YAW     0.      URDD1   0.      URDD2   0.
        URDD3   1.      URDD4   0.      URDD5   0.      URDD6   0.
$
$ Trim Parameters for Subcase: 4
TRIM    4       1.2     395.    SIDES   0.      ROLL    0.
        PITCH   .000682 YAW     0.      URDD1   0.      URDD2   0.
        URDD3   4.      URDD4   0.      URDD5   0.      URDD6   0.
0.
URDD2
0.
URDD1
0.
YAW
0.
PITCH
-etc.-
UX3
LABEL3
0.
ROLL
0.
SIDES
99.
.6
1
TRIM
0.
URDD6
0.
URDD5
0.
URDD4
1.
URDD3
AEQR
UX2
LABEL2
UX1
LABEL1
Q
MACH
ID
TRIM
10
9
8
7
6
5
4
3
2
1
ANGLEA
2
AESTAT
LABEL
ID
AESTAT
10
9
8
7
6
5
4
3
2
1
$
$ Rigid Body Motion Trim Variables: AESTAT
AESTAT  2       ANGLEA
AESTAT  3       SIDES
AESTAT  4       ROLL
AESTAT  5       PITCH
AESTAT  6       YAW
AESTAT  7       URDD1
AESTAT  8       URDD2
AESTAT  9       URDD3
AESTAT  10      URDD4
AESTAT  11      URDD5
AESTAT  12      URDD6
$
$ Trim Parameters for Subcase: 1
TRIM    1       .6      99.     SIDES   0.      ROLL    0.
        PITCH   0.      YAW     0.      URDD1   0.      URDD2   0.
        URDD3   1.      URDD4   0.      URDD5   0.      URDD6   0.
$
$ Trim Parameters for Subcase: 2
TRIM    2       1.2     395.    SIDES   0.      ROLL    0.
        PITCH   0.      YAW     0.      URDD1   0.      URDD2   0.
        URDD3   1.      URDD4   0.      URDD5   0.      URDD6   0.
$
$ Trim Parameters for Subcase: 3
TRIM    3       1.2     2057.   SIDES   0.      ROLL    0.
        PITCH   0.      YAW     0.      URDD1   0.      URDD2   0.
        URDD3   1.      URDD4   0.      URDD5   0.      URDD6   0.
$
$ Trim Parameters for Subcase: 4
TRIM    4       1.2     395.    SIDES   0.      ROLL    0.
        PITCH   .000682 YAW     0.      URDD1   0.      URDD2   0.
        URDD3   4.      URDD4   0.      URDD5   0.      URDD6   0.
Segment of NASTRAN Input Deck
$ Direct Text Input for Global Case Control Data
SUBCASE 1
$ Subcase name : 1g_lowspeed_high_alt
   SUBTITLE=constraints
   SPC = 2
   DISPLACEMENT(SORT1,REAL)=ALL
   SPCFORCES(SORT1,REAL)=ALL
   STRESS(SORT1,REAL,VONMISES,BILIN)=ALL
TRIM = 1
AESYMXZ = Symmetric
AESYMXY = Asymmetric
SUPORT1 = 1
AEROF = ALL
APRES = ALL
$ Direct Text Input for this Subcase
SUBCASE 2
$ Subcase name : 1g_supersonic_high_alt
   SUBTITLE=constraints
   SPC = 2
   DISPLACEMENT(SORT1,REAL)=ALL
   SPCFORCES(SORT1,REAL)=ALL
   STRESS(SORT1,REAL,VONMISES,BILIN)=ALL
TRIM = 2
AESYMXZ = Symmetric
AESYMXY = Asymmetric
SUPORT1 = 1
AEROF = ALL
APRES = ALL
$ Direct Text Input for this Subcase
SUBCASE 3
$ Subcase name : 1g_supersonic_low_alt
   SUBTITLE=constraints
   SPC = 2
   DISPLACEMENT(SORT1,REAL)=ALL
   SPCFORCES(SORT1,REAL)=ALL
   STRESS(SORT1,REAL,VONMISES,BILIN)=ALL
TRIM = 3
AESYMXZ = Symmetric
AESYMXY = Asymmetric
SUPORT1 = 1
AEROF = ALL
APRES = ALL
$ Direct Text Input for this Subcase
SUBCASE 4
$ Subcase name : 4g_supersonic_high_alt
   SUBTITLE=constraints
   SPC = 2
   DISPLACEMENT(SORT1,REAL)=ALL
   SPCFORCES(SORT1,REAL)=ALL
   STRESS(SORT1,REAL,VONMISES,BILIN)=ALL
TRIM = 4
AESYMXZ = Symmetric
AESYMXY = Asymmetric
SUPORT1 = 1
AEROF = ALL
APRES = ALL
Flight Loads
MSC.Nastran
*.F06 file
*.xdb file
 AEROELASTIC TRIM VARIABLES

                                      ID     LABEL                 TYPE                 TRIM STATUS      VALUE OF UX
                   case 1          1     CT_CAN        CONTROL SURFACE            FREE      1.646823E-01  RADIANS
                                       2     ANGLEA             RIGID BODY                     FREE      7.851344E-02  RADIANS

                   case 2          1     CT_CAN        CONTROL SURFACE            FREE      1.287052E-02  RADIANS
                                       2     ANGLEA             RIGID BODY                     FREE     -2.400998E-04  RADIANS

                   case 3          1     CT_CAN        CONTROL SURFACE            FREE      5.978550E-02  RADIANS
                                       2     ANGLEA             RIGID BODY                    FREE      6.726912E-03  RADIANS

                   case 4          1     CT_CAN        CONTROL SURFACE            FREE      2.391420E-01  RADIANS
                                       2     ANGLEA             RIGID BODY                    FREE      2.690765E-02  RADIANS
1.542
4
13.70
4
0.386
3
3.426
3
-0.014
2
0.737
2
4.498
1
9.435
1
40,000 ft
395
1.2
4g_supersonic_high_alt
40,000 ft
395
1.2
1g_supersonic_low_alt
1,000 ft
2057
1.2
1g_supersonic_low_alt
40,000 ft
99
0.6
1g_subsonic_high_alt
Altitude
Dynamic Pressure
Mach Number
Subcase Name

The structural data in Flds_FSWing_class_file.bdf  is imported into the database.
The structural grid points to the be used in splinning are grouped.
The geometry for the aero surface is created.
The structural symmetry boundary conditions are applied
The load case for the boundary conditions is created.
The wing and canard aero surfaces are defined.
The canard is defined as a control surface.
The wing and canard aero surfaces are splined to the structure.
The trim conditional are set up and the analysis is carried out.
The Stability Derivatives are investigated.
The aero loading and resultant structural loading are investigated.

Post the Structural Model
Structural Deformation
Aerodynamic Forces on Rigid Aircraft
Elastic Increments
Inertia Loads
Workshop # 1: Flight Cases

All subcases have angle of attack and canard angle as free variables
In Subcase 4 a Pitch Rate of 0.000356 is used to balance the 4G pull
Workshop # 1: Model Data
Wing Span (full model) = 40 ft
Wing Area (full model)=  400 ft2
Mean Chord = 10 ft
Workshop # 1: Tasks
Create the Flight Loads model as shown in the case study. Try  increasing the fidelity of the aeromesh to better capture the aero pressure gradients.
Go through the exercise using the steps outlined on the next page
Workshop # 1: Analysis Steps

Structural Deformation
Aerodynamic Forces on Rigid Aircraft
Elastic Increments
Inertia Loads
Workshop # 1: Flight Cases

All subcases have angle of attack and canard angle as free variables
In Subcase 4 a Pitch Rate of 0.000356 is used to balance the 4G pull
Workshop # 1: Model Data
Wing Span (full model) = 40 ft
Wing Area (full model)=  400 ft2
Mean Chord = 10 ft
Workshop # 1: Tasks
Create the Flight Loads model as shown in the case study. Try  increasing the fidelity of the aeromesh to better capture the aero pressure gradients.
Go through the exercise using the steps outlined on the next page
Workshop # 1: Analysis Steps

Aerodynamic Forces on Rigid Aircraft
Elastic Increments
Inertia Loads
Workshop # 1: Flight Cases

All subcases have angle of attack and canard angle as free variables
In Subcase 4 a Pitch Rate of 0.000356 is used to balance the 4G pull
Workshop # 1: Model Data
Wing Span (full model) = 40 ft
Wing Area (full model)=  400 ft2
Mean Chord = 10 ft
Workshop # 1: Tasks
Create the Flight Loads model as shown in the case study. Try  increasing the fidelity of the aeromesh to better capture the aero pressure gradients.
Go through the exercise using the steps outlined on the next page
Workshop # 1: Analysis Steps

Aerodynamic Forces on Rigid Aircraft
Elastic Increments
Inertia Loads
Workshop # 1: Flight Cases

All subcases have angle of attack and canard angle as free variables
In Subcase 4 a Pitch Rate of 0.000356 is used to balance the 4G pull
Workshop # 1: Model Data
Wing Span (full model) = 40 ft
Wing Area (full model)=  400 ft2
Mean Chord = 10 ft
Workshop # 1: Tasks
Create the Flight Loads model as shown in the case study. Try  increasing the fidelity of the aeromesh to better capture the aero pressure gradients.
Go through the exercise using the steps outlined on the next page
Workshop # 1: Analysis Steps

Elastic Increments
Inertia Loads
Workshop # 1: Flight Cases

All subcases have angle of attack and canard angle as free variables
In Subcase 4 a Pitch Rate of 0.000356 is used to balance the 4G pull
Workshop # 1: Model Data
Wing Span (full model) = 40 ft
Wing Area (full model)=  400 ft2
Mean Chord = 10 ft
Workshop # 1: Tasks
Create the Flight Loads model as shown in the case study. Try  increasing the fidelity of the aeromesh to better capture the aero pressure gradients.
Go through the exercise using the steps outlined on the next page
Workshop # 1: Analysis Steps

Elastic Increments
Inertia Loads
Workshop # 1: Flight Cases

All subcases have angle of attack and canard angle as free variables
In Subcase 4 a Pitch Rate of 0.000356 is used to balance the 4G pull
Workshop # 1: Model Data
Wing Span (full model) = 40 ft
Wing Area (full model)=  400 ft2
Mean Chord = 10 ft
Workshop # 1: Tasks
Create the Flight Loads model as shown in the case study. Try  increasing the fidelity of the aeromesh to better capture the aero pressure gradients.
Go through the exercise using the steps outlined on the next page
Workshop # 1: Analysis Steps

Elastic Increments
Inertia Loads
Workshop # 1: Flight Cases

All subcases have angle of attack and canard angle as free variables
In Subcase 4 a Pitch Rate of 0.000356 is used to balance the 4G pull
Workshop # 1: Model Data
Wing Span (full model) = 40 ft
Wing Area (full model)=  400 ft2
Mean Chord = 10 ft
Workshop # 1: Tasks
Create the Flight Loads model as shown in the case study. Try  increasing the fidelity of the aeromesh to better capture the aero pressure gradients.
Go through the exercise using the steps outlined on the next page
Workshop # 1: Analysis Steps

Inertia Loads
Workshop # 1: Flight Cases

All subcases have angle of attack and canard angle as free variables
In Subcase 4 a Pitch Rate of 0.000356 is used to balance the 4G pull
Workshop # 1: Model Data
Wing Span (full model) = 40 ft
Wing Area (full model)=  400 ft2
Mean Chord = 10 ft
Workshop # 1: Tasks
Create the Flight Loads model as shown in the case study. Try  increasing the fidelity of the aeromesh to better capture the aero pressure gradients.
Go through the exercise using the steps outlined on the next page
Workshop # 1: Analysis Steps

Workshop # 1: Flight Cases

All subcases have angle of attack and canard angle as free variables
In Subcase 4 a Pitch Rate of 0.000356 is used to balance the 4G pull
Workshop # 1: Model Data
Wing Span (full model) = 40 ft
Wing Area (full model)=  400 ft2
Mean Chord = 10 ft
Workshop # 1: Tasks
Create the Flight Loads model as shown in the case study. Try  increasing the fidelity of the aeromesh to better capture the aero pressure gradients.
Go through the exercise using the steps outlined on the next page
Workshop # 1: Analysis Steps

Workshop # 1: Flight Cases

All subcases have angle of attack and canard angle as free variables
In Subcase 4 a Pitch Rate of 0.000356 is used to balance the 4G pull
Workshop # 1: Model Data
Wing Span (full model) = 40 ft
Wing Area (full model)=  400 ft2
Mean Chord = 10 ft
Workshop # 1: Tasks
Create the Flight Loads model as shown in the case study. Try  increasing the fidelity of the aeromesh to better capture the aero pressure gradients.
Go through the exercise using the steps outlined on the next page
Workshop # 1: Analysis Steps

Workshop # 1: Tasks
Create the Flight Loads model as shown in the case study. Try  increasing the fidelity of the aeromesh to better capture the aero pressure gradients.
Go through the exercise using the steps outlined on the next page
Workshop # 1: Analysis Steps

40,000 ft
395
1.2
4g_supersonic_high_alt
40,000 ft
395
1.2
1g_supersonic_low_alt
1,000 ft
2057
1.2
1g_supersonic_low_alt
40,000 ft
99
0.6
1g_subsonic_high_alt

Workshop # 1: Analysis Steps

Workshop # 1: Analysis Steps

The structural data in Flds_FSWing_class_file.bdf  is imported into the database.
The structural grid points to the be used in splinning are grouped.
The geometry for the aero surface is created.
The structural symmetry boundary conditions are applied
The load case for the boundary conditions is created.
The wing and canard aero surfaces are defined.
The canard is defined as a control surface.
The wing and canard aero surfaces are splined to the structure.
The trim conditional are set up and the analysis is carried out.
The Stability Derivatives are investigated.
The aero loading and resultant structural loading are investigated.

X43
Z4
Y4
X4
X12
Z1
Y1
 X1
1
4
3
0
1000
1000
CAERO1
5.
0.
7.5
13.
5.
0.
0.
13.
IGID
LCHORD
LSPAN
NCORD
NSPAN
CP
PID
EID
CAERO1
10
9
8
7
6
5
4
3
2
1
$ Aeroelastic Model Parameters
PARAM   AUNITS  0.031081
$
$ Global Data for Steady Aerodynamics
AEROS   0       0       10.     40.     200.
$
$ Flat Aero Surface: ls_canard
PAERO1  1000
CAERO1  1000    1000    0       3       4                       1
        13.     0.      0.      5.      13.     7.5     0.      5.
$
$ Flat Aero Surface: ls_wing
PAERO1  1100
CAERO1  1100    1100    0       8       4                       1
        25.     0.      0.      10.     13.453  20.     0.      9.999999
$
$ Surface Spline: sp_wing
AELIST  1       1100    1101    1102

$
PARAM   GRDPNT  90
$
PARAM   WTMASS  .031081
$
PARAM   AUNITS  .031081
$
SUPORT1 1       90      35
$

$
PARAM   GRDPNT  90
$
PARAM   WTMASS  .031081
$
PARAM   AUNITS  .031081
$
SUPORT1 1       90      35
$

$
PARAM   GRDPNT  90
$
PARAM   WTMASS  .031081
$
PARAM   AUNITS  .031081
$
SUPORT1 1       90      35
$


title: Презентация на тему: MSC.Mvision - 03-1

text:
MATERIALS BROWSER

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Second level
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MVI320, Section 3, June 2001
40
>
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">"
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DESIG LIKE 'AL*'
E11T/DENS>10
E11T>E22T
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**
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title: Презентация на тему: MSC.Mvision - 04-1

text:
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MVI320, Section 4, June 2001
Close Data Viewer
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title: Презентация на тему: MSC.Mvision - 00-1

text:
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Second level
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MSC.Software Corporation
2 MacArthur Place
Santa Ana, CA 92707, USA
Tel:  (714) 540-8900
Fax: (714) 784-4056
Web: http://www.mscsoftware.com
United States
MSC.Patran Support
Tel: 1-800-732-7284
Fax: (714) 979-2990
Tokyo, Japan
Tel: 81-3-3505-0266
Fax: 81-3-3505-0914
Munich, Germany
Tel: (+49)-89-43 19 87 0
Fax: (+49)-89-43 61 716
August 2001
MVI320 Course Notes
P/N  MV*V3.4*Z*Z*Z*SM-MVI320-NT1
MSC.Software Corporation
2 MacArthur Place
Santa Ana, CA 92707, USA
Tel:  (714) 540-8900
Fax: (714) 784-4056
Web: http://www.mscsoftware.com
United States
MSC.Patran Support
Tel: 1-800-732-7284
Fax: (714) 979-2990
Tokyo, Japan
Tel: 81-3-3505-0266
Fax: 81-3-3505-0914
Munich, Germany
Tel: (+49)-89-43 19 87 0
Fax: (+49)-89-43 61 716
August 2001
MVI320 Course Notes
P/N  MV*V3.4*Z*Z*Z*SM-MVI320-NT1


title: Презентация на тему: MSC.Mvision Workshop 1

text:
Step 7.  Materials File:  Exit MVISION
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MVI320, Workshop 1, August 2001
c
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e
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h
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c
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title: Презентация на тему: MSC.Mvision Workshop 00 1