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NASA Vehicle Sketch Pad User Manual

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User Manual
Vehicle Sketch Pad
Version 1.7.92

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Summary of Contents for NASA Vehicle Sketch Pad

  • Page 1 User Manual Vehicle Sketch Pad Version 1.7.92...
  • Page 2 This model can be processed into formats suitable for engineering analysis. The predecessors to OpenVSP have been developed by JR Gloudemans and others for NASA since the early 1990's. In January 2012, OpenVSP was released as an open source project available to everyone free of charge.

  • Page 3: Table Of Contents

    Table of Contents Chapter 1 Getting Started Quick Start ........................6 Things to Know....................... 6 File Extension ......................6 Figure 3: Navigating between folders ................. 7 Main Screen ........................ 8 Geom Browser ......................8 Basics ..........................9 Mouse Buttons ......................9 View Keys ........................
  • Page 4 Table of Contents Chapter 7 Additional Parts External Store (Ext_Store) .................... 32 Design ........................32 Blank ..........................33 Definition ........................33 Duct ..........................33 Definition ........................33 Shape Tab........................33 Foil Tab ........................34 Propeller (Prop) ......................35 Shape Tab........................35 Station Tab ........................
  • Page 5 Table of Contents Edit ..........................63 Input 1 Tab ........................ 63 Input 2 Tab ........................ 67 Slice Tab ........................69 Control Tab ....................... 71 Execute Tab ......................72 Revert ..........................74 Help ..........................74 About......................... 74 Chapter 9 Modeling Example Wing ..........................

  • Page 6: Chapter 1 Getting Started

    Things to Know File Extension Vehicle Sketch Pad uses the .XML extension for its files. VSP can read .RAM files, however the .XML extension should be used if files are to be edited. Saving Files...
  • Page 7 Getting Started Chapter 1: Opening Files Whenever you are prompted to open/import a file, a window similar to the one shown below will appear. Figure 2: Example of window to open a file The type of file that is being displayed can be managed next to “Show” by using the drop down menu.

  • Page 8: Main Screen

    Getting Started Chapter 1: Main Screen Left mouse button Rotate model Translate model Right mouse button Zoom model Center mouse button (or click scroll wheel) (or left and right buttons together for two-button mouse) Center model in screen “c” or View/Center Menu User Select views F1 to F4: Hold Shift and Function Key to set, press Function Key to view again.

  • Page 9: Basics

    Getting Started Chapter 1: Basics Mouse Buttons The first and most important thing to learn about VSP is how to use the mouse. Click and hold each mouse button to engage that button’s function, and release the button to disengage the function. For example, the left button rotates the model around in the Main Screen;...

  • Page 10: Adding A Part

    Chapter 2 Intro to Modeling in VSP Adding a Part Let’s get into building a model. The first step is to add a part. At the top of the Geom Browser Window, select the part type from the pull-down list. For the following example, select POD.

  • Page 11: Modifying A Part

    I ntro to M odeling in VSP Chapter 2: Modifying a Part VSP allows designers to quickly and easily create nearly any aircraft imaginable. In order to do that, parts must be modified to meet the design vision. The following is organized by each part type.
  • Page 12 I ntro to M odeling in VSP Chapter 2: Name, Material, & Color Select a name and color that are easy to remember and helps to differentiate similar parts. These are especially useful when building very complex models consisting of many parts. The material for the part may also be selected, such as aluminum or glass. Attach to Parent There is a Parent-Child Relationship that can be added to attach separate parts to each other.

  • Page 13: Cross Section Formation (Xform) Tab

    I ntro to M odeling in VSP Chapter 2: Tessellation Users may add more cross sections and points to the edges of each cross-section to make the model more accurate, but those with slow computers will not wish to add too many, as this will begin to slow down the computer.
  • Page 14 I ntro to M odeling in VSP Chapter 2: Location (Loc): Change how the part is located and orientated in the X, Y, and Z directions (X Loc, Y Loc, Z Loc). Rotation (Rot): Rotate the part in the X,Y, and Z directions (X Rot, Y Rot, Z Rot) Origin of Rotation (Rot Orig): This lets the user specify where the origin of rotation is to be placed (0.0 being the leading edge and 1.0 being the trailing edge).

  • Page 15: Design Tab

    Chapter 3 Designing a Pod Design tab The design tab specifically for a pod is shown below: Figure 7: Pod Design tab. Length: Set the length of the pod Fine Ratio: Set the fineness ratio for the pod. VSP User Manual Version 1.7.92...

  • Page 16: Chapter 4 Designing Wings

    Chapter 4 Designing Wings All Wings There are three tabs that are common between all wing type browsers: Plan, Sect and Foil. These three are explained below, and the ones unique to each type are explained in separate sections. Planform (Plan) Tab The Plan tab is shown in the figure below: Figure 8: Multi-section Wing Plan tab.

  • Page 17: Foil Tab

    Designing W ings Chapter 4: Total Planform In this pane the user sets the planform of the wing as a whole. Span, Projected Span, Chord, Area: These four parameters affect each other but can all be changed to shape the entire wing. Aspect Ratio: Cannot be set but is affected by a change in the span, projected span, or chord.

  • Page 18: Multi-Section (Ms) Wings

    Designing W ings Chapter 4: Figure 9: Multi-section Wing Foil tab. Multi-Section (MS) Wings Section (Sect) Tab The section tab for an MS Wing is shown below. Figure 10: Multi-section Wing Sect tab. VSP User Manual Version 1.7.92...

  • Page 19: Dihedral Angle Of Planes (Dihed)

    Designing W ings Chapter 4: Section ID: Choose a section with which to work. The section chosen will be highlighted with a red box on the main screen. New sections may be added as needed: However, note that new sections will be added to the right of the currently selected section. Number Interpolated Cross Sections (Num Interpolated XSecs) Section (Sect): Increasing the number increases the amount of sections in the part selected.
  • Page 20 Designing W ings Chapter 4: Dihed 1: Adjusts the dihedral angle between the center and the joint of choice. (-360 to 360 degrees) Dihed 2: Adjusts the angle between the selected joint and the next joint or the tip of the wing.

  • Page 21: Hybrid Wing Bodies (Hwb)

    Designing W ings Chapter 4: Deg Per Seg: specify the number of degrees in each segment. Max Num Seg: specify the maximum number of segments in the body. Rotate Foil to Match Dihedral: Rotates a specific airfoil to match the dihedral angle specified above.

  • Page 22: Fillet Tab

    Designing W ings Chapter 4: Figure 12: Section Tab in HWB part Fillet Tab Joint ID Choose which joint is to be modified. Deg Per Seg (for all listed below): Determines how smooth the blend is between sections (1 degree is very smooth, 30 degrees is less smooth). This is the angle of each segment added (5 degree sweep per segment, 10 degree sweep per segment, etc.).
  • Page 23 Designing W ings Chapter 4: Figure 13: Fillet tab in HWB part. Trailing Edge Sweep Fillets % Span Tip: Blends the two sections connected by the joint selected in the XY plane of the trailing edge. Similar to Sweep Fillets, but at trailing edge. Dihedral Fillets % Span Tip: Blends the dihedral angles of the two sections together (creates a smooth curve between the two).

  • Page 24: Exercises

    Designing W ings Chapter 4: Exercises In order to show the capabilities of a Multi-section Wing, the following complex geometries are given as exercises for the reader. Ring Wing 1. Open the Geom Browser and Add an MS Wing part. 2.

  • Page 25: Turning Pipe

    Designing W ings Chapter 4: Turning Pipe Now this following example could be useful in laying out V/STOL aircraft, to show ducting running through the aircraft. For this example, the airfoil of a circle will be used. This file may be opened in Notepad and/or Excel for editing. Remember to save the file as .af! 1.
  • Page 26 Designing W ings Chapter 4: Result: A ninety degree-turned pipe. This can be rotated and moved to suit in the XForm tab. The lengths of the various sections can be adjusted by changing their spans in the Sect tab. Add more turns and whatever else is needed to finish the pipe. An example of the turning pipe is shown below.

  • Page 27: Chapter 5 Designing The Fuselage

    Chapter 5 Designing the Fuselage Shape Tab Figure 16: Fuselage Shape tab. Global Shape Parameters These parameters define the basic qualities of the fuselage.  Note: The more cross sections one adds, the better the camber adjustment will be. Inner Mold Line Definition: Inner Mold Line (IML) is primarily used for jet transports to set a wall thickness and then see how much room is left inside the fuselage for passenger seats, cargo, or other equipment that will be stowed inside.

  • Page 28: Profile Tab

    Designing the Fuselage Chapter 5: Explanation: To use IML, first turn the IML on. The on/off buttons are just beneath the IML title bar in the Shape tab. Select a color that will easily differentiate the inner mold line from the fuselage. Then for each fuselage cross section, set the target wall thickness; the actual wall thickness will be shown to the right.

  • Page 29: Cross Section (Xsec) Tab

    Designing the Fuselage Chapter 5: Tangent Angle/Strength Angle Weight: This is the angle between the two sections. Strength 1-2: Changes the shape and placement of the affected section  Note: None of these parameters will work if there are no Interpolated Cross Sections ...
  • Page 30 Designing the Fuselage Chapter 5: Add, Cut, Copy, and Paste Buttons Add: inserts an identical cross section to the right of the current cross section. Cut: removes the current cross section. Copy: copies the current cross section. Paste: will take the previously Cut or Copied cross section and replace the current one with it.

  • Page 31: Chapter 6 Introduction To Havoc

    Chapter 6 Introduction to HAVOC Definition HAVOC is an acronym for Hypersonic Aircraft Vehicle Optimization Code. This part can be imported into that particular code. To find what each adjustment does, refer to the code’s definitions. Modifications The HAVOC part has 3 unique tabs that have many different features that can be adjusted.

  • Page 32: Chapter 7 Additional Parts

    Chapter 7 Additional Parts External Store (Ext_Store) Design  Note: By default, the External Store part will create two external stores each time the user adds this part to the design. To add only one external store at a time, select the XForm tab and select “None” from the Symmetry drop-down box.

  • Page 33: Blank

    Additional Parts Chapter 7: Fineness Ratio (Finess): The fineness ratio is the ratio of length to width. A smaller fineness ratio denotes a wider store. Cd Flat Plate: This parameter is for VSP’s aerodynamic analysis tools. Enter the Cd of the store as if the store were equivalent to a flat plate.

  • Page 34: Foil Tab

    Additional Parts Chapter 7: Figure 21: Duct Shape tab. Foil Tab Figure 22: Duct Foil tab. The Foil tab is identical to the MS Wing’s Foil tab. VSP User Manual Version 1.7.92...

  • Page 35: Propeller (Prop)

    Additional Parts Chapter 7:  Note: In the event that a negative camber for the duct is desired, click the Invert Y button under the Airfoil title bar. Propeller (Prop) Shape Tab Figure 23: Propeller Shape tab. This tab allows the diameter, cone angle, and blade pitch to be set. The Blade Pitch rotates all of the propeller’s blades at the same time.

  • Page 36: Station Tab

    Additional Parts Chapter 7: Station Tab Figure 24: Propeller Station tab. Overview: In this tab, the location, size and twist of the blade are adjusted. Station: This is similar to the Sect ID and Joint ID of the MS Wing Sect and Dihed tabs. Each station denotes a different portion of the propeller.

  • Page 37: Foil Tab

    Additional Parts Chapter 7: Foil Tab Figure 25: Propeller Foil tab. This is identical to the Foil tabs of the MS Wing and HWB parts. Engine Definition This feature is a pre-built jet engine. One can add an S-Duct like on a L1011 or B727 center engine, or like many fighter aircraft.
  • Page 38 Additional Parts Chapter 7: Figure 26: Engine Engine/Nozzle/Duct tab. Engine Parameters RTip: Defines the radius of the front fan. Hub/RTip: The ratio of the bullet size to the fan size. Max/RTip: The ratio of the outside cowling dimensions to the fan radius. Len/RTip: The ratio of engine length to the fan radius.

  • Page 39: Inlet Tab

    Additional Parts Chapter 7: X Off: The distance forward to move the inlet. Y Off: The offset distance from the centerline of the engine. Shape: Adjust the Shape to change the turn of the inlet.  Note: In order to offset the inlet in different directions in the YZ plane, use X Rot under the X Form tab.
  • Page 40 Additional Parts Chapter 7: HL/Thrt: The ratio of tip area to the throat area. Fineness/Aspect Ratios: Lip FR: Determines where along the x-axis the throat is located. H/W: Adjusts the diameter of the cowling.  Note: if the H/W is set to a value other than 1, turn on the duct option, otherwise a discontinuity will appear in the cowling.

  • Page 41: Chapter 8 Main Toolbar Features

    Chapter 8 Main Toolbar Features File Menu Figure 28: Key items under File menu. Insert This is most useful for building rotating groups of parts. For example, if a nacelle for a VTOL aircraft were needed, it would be built in a separate VSP file and then imported to the main file.

  • Page 42: Window Menu

    M ain Toolbar Features Chapter 8: Window Menu Figure 29: Key items under Window Menu. Window Split The window split feature allows the user to see more than one view of the model at once. In the Main Screen is the menu Window. It lists One, Four, Two Horizontal, and Two Vertical as options.

  • Page 43: Lighting

    M ain Toolbar Features Chapter 8: Figure 30: Background Window Lighting The lighting on the model can be adjusted in order to see the model better. The default light settings may not show surfaces and textures as well as desired. Note that this feature works best when the model is near completion and is shaded.

  • Page 44: Labels

    M ain Toolbar Features Chapter 8: Labels Ruler: This feature places the dimensions of a part on the model at the given axis, offset, precision (in decimal places), units, and color. Text: This feature allows the user to place a text label at any spot on the model and customize it with color and offset.

  • Page 45: Adjust

    M ain Toolbar Features Chapter 8: Adjust Figure 33: Adjust option in the View Menu (left) and Adjust View control box (right). The Adjust option is most useful when modeling a current airplane with a picture of the aircraft set as the background picture. When using the mouse, it is difficult to line up the model exactly.

  • Page 46: Texture

    M ain Toolbar Features Chapter 8: Texture Figure 35: Texture option in View Menu (left) and Texture . A texture (in .tga format) can be added to an object.  Note: Select the object in the Geom Browser and click on Texture to view the texture on said object.

  • Page 47: Geometry Tools (Geom) Menu

    M ain Toolbar Features Chapter 8: Geometry Tools (Geom) Menu Modify Figure 36: Modify option under the Geometry menu. When Modify is chosen under “Geom,” the program switches the selected window from the main screen to the Geometric browser. This is done so that the user can then choose which part(s) he or she wishes to modify.

  • Page 48: Mesh

    M ain Toolbar Features Chapter 8: Figure 38: Component Geometry Results Window Mesh Figure 39: Mesh option under the Geometry menu (left) and Mesh Window (right). Once selected, it will produce a triangulated, water-tight geometry. The mesh is of low-quality and is not recommended for use in CFD. The mesh is applicable for stereo lithography.
  • Page 49 M ain Toolbar Features Chapter 8: Figure 40: The CFD Mesh option under the Geometry menu. Figure 41 - Mesh Source Controls The above figure shows the panel used to control grid density during the meshing process. This panel is accessed from the Geom menu under CFD Mesh. Max Edge Len: Target edge length all triangles not covered by sources.
  • Page 50 M ain Toolbar Features Chapter 8: Sources: List of sources for this component. Select source to edit. Add Source: Add a new source to the current component. Use the pull down selector to choose the type of source. Delete Source: Delete the current source. Name: Edit the name of the current source.
  • Page 51 M ain Toolbar Features Chapter 8: Figure 42: Source types. Figure 43: Grid density based on sources in Figure 42. VSP User Manual Version 1.7.92...

  • Page 52: Awave Slicing (Awave Slice)

    M ain Toolbar Features Chapter 8: Figure 44: Example aircraft with default sources. Figure 45: Example aircraft mesh; approximately 250,000 triangles AWAVE Slicing (Awave Slice) The Slice tool is useful in determining the area distribution along the aircraft. For example, the designer may want to have the cross sectional area distributed in a bell curve to minimize compressibility drag.
  • Page 53 M ain Toolbar Features Chapter 8: Figure 46: Awave Slicing option under the Geometry menu. Figure 47: Awave slicing options for sample BWB model. Once the parameters are set, click Start Slicing. This command also writes a file to the directory of the vsp.exe named “slice.txt.” When the slice.txt file is opened, it will list the area distribution in two columns: X and Area.

  • Page 54: Mass Properties (Mass Prop)

    M ain Toolbar Features Chapter 8: Mass Properties (Mass Prop) Figure 49: Mass Properties option under Geometry Menu Figure 50: Mass Properties Window Mass Properties Num Slice: specify the number of slices in the model. The more slices there are, the more accurate the results will be.

  • Page 55: Aero Reference (Aero Ref)

    M ain Toolbar Features Chapter 8: I (xx, yy, zz): shows the calculated moment of inertias in the X, Y and Z direction. I (xy, xz, yz): shows the cross products of the moments of inertia. Aero Reference (Aero Ref) Figure 51: Aero Reference option under Geometry Menu Figure 52: Aero Reference Window (left) and Coordinate System (right) Reference Comp...

  • Page 56: Structural Modeling

    M ain Toolbar Features Chapter 8: M.A.C.: the mean aerodynamic chord for the wing Area: the area of the body, which can be updated manually. Span: the span of the wing, which can be updated manually. Aero Center a.c. (X, Y, Z): displays the aerodynamic centers of the model in the X, Y, and Z direction.
  • Page 57 M ain Toolbar Features Chapter 8: Figure 54: Multi-Section Wing Figure 54 displays the multi-section wing used in this example. To add structural components, select Geom/Structure from the menu. Figure 55: Skin Definition GUI VSP User Manual Version 1.7.92...
  • Page 58 M ain Toolbar Features Chapter 8: Figure 55 shows the interface used to define the structure and in particular the upper skin thickness. Default Element Size: target edge size for the mesh Thickness Scale: Scale the thickness of all ribs, spars and skins Section ID: Which wing section to edit (1 of 2 in this case).
  • Page 59 M ain Toolbar Features Chapter 8: Figure 56: Spar Editor Figure 56 shows the spar editor. Spar ID: Select the current spar to edit. Remember, only spars in this section are available. Add Spar: Add a spar to this section Delete Spar: Delete the current (red) spar Thickness: Set spar thickness Density: Set spar material density...
  • Page 60 M ain Toolbar Features Chapter 8: Figure 57: Final Mesh Figure 57 shows the mesh resulting from pushing the Export FEA Mesh button. Several files are exported after the meshing is completed: feageom.dat: The mesh geometry for Calculix (6 node triangles and 8 node quads) feanodethick.dat: Thickness of each node for Calculix NASTRAN.dat: geometry for NASTRAN feamess.dat: Mass of the ribs, spar and skins based in the input densities...
  • Page 61 M ain Toolbar Features Chapter 8: Figure 58 shows the stress results for Calculix for the wing mesh generated in VSP. Listed below is the input file for this run: *INCLUDE,INPUT=feageom.dat *INCLUDE,INPUT=fixed.nam *BOUNDARY NFIXED,1,3 *MATERIAL,NAME=AL *ELASTIC 70000.0,0.33,20.0 *DENSITY 1.894e-9 *SHELL SECTION,ELSET=Eallquads,MATERIAL=AL 0.05 *SHELL SECTION,ELSET=Ealltris,MATERIAL=AL 0.05...

  • Page 62: Script

    M ain Toolbar Features Chapter 8: Figure 60: Parameters Link Manager Window The Link option can be used to connect two parameters together so that any changes made to the model will not affect that connection. For example, consider if a engine is linked with the fuselage with respect to length at a certain distance along the fuselage from the end.

  • Page 63: Script Output

    M ain Toolbar Features Chapter 8: Script Output Figure 62: Script Output option in Scrip menu (left) and Scrip Output window (right) Vorview Edit The Edit option under the Vorview menu is shown in the figure below: Input 1 Tab Base File Name Specify the name of the file of the figure being used.
  • Page 64 M ain Toolbar Features Chapter 8: Figure 63: Edit option in Vorview Menu (left) and Vorview Window (right) Will not run the 5 x 5 matrix but instead only the cases below: XMACH ALPHA  Note: Do not try to perform the Neutral Point analysis (IAC = 1) with ISWEEP = 1 because the calculations do not work out correctly ITRMAX: Maximum number of Gauss Seidell Iterations IDETAIL: controls the amount of information presented in the Vorlax Output window.
  • Page 65 M ain Toolbar Features Chapter 8: SPC: Leading edge suction/vortex multiplier. The corresponding cases for various SPC values are shown below: Case 1.00 100% leading edge suction 0.25 25% leading edge suction -1.00 100% vortex lift (Polhamus analogy) -0.25 25% vortex lift (Polhamus analogy) FLOATX: Longitudinal vortex wake flotation factor FLOATY: Lateral Vortex wake flotation factor Card 5: Flight Condition...
  • Page 66 M ain Toolbar Features Chapter 8: WSPAN: Total wing span Card 8 LTAIL: the distance (in feet) from the wing quarter chord (C/4) to the quarter chord of horizontal tail measured in the free-stream “X” direction. ZTAIL: the distance (in feet) from the wing quarter chord to the quarter chord of the horizontal tail measured in vertical “Z”...

  • Page 67: Input 2 Tab

    M ain Toolbar Features Chapter 8: on the model has a DCP less than the above prediction the vortex is assumed to have burst and DCP is set to zero for that subpanel Hence, CK1 and CK2 can be used to adjust the slope and intercept of the prediction for DCP Card 10 IAC: a value of 1 will turn on the auto calculation of aerodynamic center...
  • Page 68 M ain Toolbar Features Chapter 8: ALPHA_TRIM: for ITRIM with a value of 2, this is the angle of attack that is used, and it’s also an array of NTRIM points. Figure 64: Input 2 tab in Vorview Window CLTRIM: for ITRIM with a value of 1, this is the desired C .

  • Page 69: Slice Tab

    M ain Toolbar Features Chapter 8: Card 12 REINF: free-stream Reynolds number REFLEN: reference length used to calculate REINF IDRAG: when the value is 0, no viscous drag is calculated. When the value is 1, a viscous drag calculation is performed. ...
  • Page 70 M ain Toolbar Features Chapter 8: Figure 65: Slice tab in Vorview window (left) and example of key slices in MS Wing part (right). Add Key Slice Enable: places a key slice at the centroid and allows for the location to be adjusted. The enabled key slice with be outlined in bright red.

  • Page 71: Control Tab

    M ain Toolbar Features Chapter 8: Y slider: use the arrow buttons to specify a new location, or manually input a value in the box to the right. Num Region Slices: increase/decrease the number of interpolated slices by using the arrow buttons.

  • Page 72: Execute Tab

    M ain Toolbar Features Chapter 8: Chord: specify the chord of the control surface Color: specify the color of the control surface Refl: specify whether the control surface is reflected Sym: specify whether the control surface is symmetric or asymmetric Hinge: specifies the location of the hinge moment.
  • Page 73 M ain Toolbar Features Chapter 8: Figure 67: Execute tab in Vorview window (left) and example of Vorlax result on MS Wing part (right) Display Xsec Surf: click to show the original cross section surface Sub Polys: displays the subdivided polygons on the cross section surface Slices: displays the key slices on the cross section surface Camber: shows the camber on the cross section surface.

  • Page 74: Revert

    M ain Toolbar Features Chapter 8: Revert The Revert option on the main menu toolbar is similar to an “undo” button. When clicked, VSP will undo any changes made to the figure, as long as the part is still highlighted in Geom Browser under the “Active” label. Once the part is no longer highlighted (either by clicking “Aircraft”...

  • Page 75: Chapter 9 Modeling Example

    Chapter 9 Modeling Example The following exercise will guide the user through the process of designing a conventional single engine general aviation aircraft. For the purposes of this modeling exercise, a Cessna 210 Centurion will be the aircraft that is modeled. Wing First set a background image of the top view of the aircraft to be modeled.

  • Page 76: Fuselage Layout

    M odeling Ex am ple Chapter 9: Figure 71: Top and profile views of Cessna 210 with main wing, vertical tail, and tailplane. Note the pronounced extension of the vertical tail into the fuselage space; this will ensure a smooth transition between surfaces when the fuselage is added.

  • Page 77: Prop

    M odeling Ex am ple Chapter 9: At this point, the aircraft should look roughly as follows: Figure 72: Top and profile views of Cessna 210. Prop This is one of the easier steps. Just locate the prop correctly, and change the stations on the prop to suit.

  • Page 78: Landing Gear

    M odeling Ex am ple Chapter 9: The process for adding and modifying landing gear is discussed below. Although landing gear will not be added to the sample model, it is important to ensure that models have landing gear if certain flight regime behaviors such as gear-down performance, etc. are to be analyzed correctly.

  • Page 79: Tips

    Chapter 10 Tips and Troubleshooting Tips When designing the models there is a need to learn the distance between two points. One solution is to add a fuselage that is the length of what is to be measured, and just use simple circular cross sections. Move the first and last cross section out to the ends to form a cylinder.

  • Page 80: Glossary

    Glossary Bullet The hub on the center of the fan for a jet engine. Finess Ratio Ratio of length to width. Fixed Offset A type of Parent Child Relationship where the child’s location is a Button fixed offset from the parent Geom Browser The window that has the list of parts.
  • Page 81 M odeling Ex am ple Chapter 9: UV Button A type of Parent Child Relationship where the child’s location follows a point on the surface of the parent. Note: this point can be adjusted with the sliders and/or the number box to the right of the button.

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