Tutorial 2

Example 2: TCR-C

This is the second CEASIOM tutorial based on the TCR-C aircraft.
Its goal is to introduce some CEASIOM modules and gives a quick overview of part of the CEASIOM capabilities.
It is also a perfect starting point for a new CEASIOM user.

This tutorial is also available in pdf format


1. Launch CEASIOM

  • Run matlab
  • Set the current folder to the CEASIOM root folder
  • Type “CEASIOM” in the matlab command window

 

 

 

2. Start a new project

  • Choose “Start a new project”

  • Select the default Project folder as the parent folder for your project

  • Give a project title to your project

  • Give a version title to your project

  • Once the window appears, click on menu:

  • Choose AcBuilder (Aircraft Builder) and click ok

 

3. The aircraft builder module: AcBuilder

  • After selecting AcBuilder, this module is automatically loaded with current project


By default, the project is called “model.xml” (project name is displayed in the window title).
You can import and export xml models in the project menu.

  • Check the Components you want in the Components list (Fuselage is mandatory)
    Green hightlight refers to parameters computed from other ones. These cannot be edited.
    Blue hightlight refers to combined parameters, editable inside a GUI
  • Edit if needed the selected component (i.e. Engines1 for example) in the Parameters field.


Most of the fields are defined and described in the “CEASIOM-xmlFileDefinition.pdf” document, available in the Documentation folder

  • Once the component are well selected and defined, select Geometry => Fuel

Here you can see and modify the fuel tank parameters and the wingbox parameters.

  • Then, select Geometry => Geometry (output)


The GEO module computation results are displayed for the different wings and tails. These results are not editable.

  • Now, select Weights & Balance => Weights & Balance


Here you must define the cabin type. The optional parameters will be automatically computed at the call of “Centers of gravity”

  • Here, select Weights & Balance => Centers of gravity


The centers of gravity of the aircraft components are display.

  • At this point, select Technology => Technology


Here you can define the geometry parameters and others, needed in the Aeroelastic module NeoCASS

  • Now, go back to Weights & Balance => Weights & Balance


Look at the System weights (optional 2) parameters.
If the MTOW (Maximum Take Off Weight) equals 0 kg, run “Weights & Balance => Centers of gravity” once again.
Once this field is computed, you can save your model and go on to the next module AMB.
If MTOW equals 0 kg at the AcBuilder closing, you will have an error message at the opening of the next module (AMB).

  • Save your project: Project => Export XML

  • Select a name for you xml file and save

  • Select Project => Close window and click Yes

4. The Weights & Balances module

  • Click on Menu, select Weights & Balances and validate by clicking on “ok”

  • Choose the xml file you want to open. The default choice is the last saved file (here: afterACBuilder.xml)

The weights & balances module is loaded

  • Click on “Load xml file” and check in Matlab interface if it is done. The “Parameters” button becomes active

  • Click on “Parameters”, change the values if desired and validate by clicking on “OK”. The “Constants values” and “Pie charts” buttons will be activated

Note that Torenbeek and Raymer methods require an aircraft with an Horizontal Tail and are then disabled in this case.

  • Click on “Constants values”, change the values if desired and validate by clicking on “OK

  • Click on “Pie charts” to view the breakdown of the weights for each method and then close the window

  • Select one of the five proposed methods (here “Howe”). The “Inertia moments” button becomes active

  • Click on “Inertia moments” to calculate them

  • Click on “CoG graphics” to visualize the different centers of gravity

You can click on “Back” to select another method and redo the calculation by clicking on “Inertia moments”

  • Once you are satisfied with the results, save the results by clicking on “Save”, select a name for the XML file (for example “afterWeightsandBalances.xml”) and validate by clicking on “Save”.

  • Click on the “x” on the top right to close the Weights & Balances module

5. The Aerodynamic Model Builder module: AMB

  • Click on Menu, select AMB and validate by clicking on “ok”

  • Choose the xml file you want to open. The default choice is the last saved file (here: afterAcbuilder.xml )

  • The AMB GUI is loaded: Verify the Ref. Data, coming from AcBuilder, in the right bottom.

  • Then, click on “States”: Edit the minimum, maximum and the number of values you want in the aerodynamic database

  • Click on “Tables” to generate the table

  • Click on “Model” and select the Flight Dynamic Model and the Geometry Symmetry Plane

  • Click on “Aerofoils” to list and edit the airfoils used in the model

  • Click on “GEO LAYOUT” to update the layout at the top left side
  • Click on “GEO DATCOM” to run datcom ac3view

  • Click on “GEO TORNADO”: 4 figures representing the Tornado geometry layout will be displayed

At this point (8 green buttons at the top right side), you can generate an aerodynamic database, using datcom, tornado or edge. Datcom is used in this tutorial.

  • Click on “Potential Solver

  • Select the parameters for tornado and click on “Run”
  • Select “Run on this model” and click on “OK”

  • Select “Brute-force Calculation and click on “OK”

  • This kind of calculation takes a lot of time. Confirm your choice by clicking on “Yes”.


When the computation is over, the Potential Solver button turns green.

  • Save your model and give it a new name (afterAMB.xml for example):

  • Close the AMB GUI

 

5. The Propulsion module: Propulsion

  • Click on Menu, select Propulsion and validate by clicking on “ok”

  • Choose the xml file you want to open. Select the default choice, i.e. the last saved file (here: afterAMB.xml)
  • The Propulsion GUI is loaded

  • Edit the parameters if needed and click on “Run”: the propulsion database is generated

  • Save your model and give it a new name (afterPropulsion.xml for example):
  • Close the Propulsion GUI

 

6. The Simulation and Dynamic Stability Analyser module: SDSA

An exhaustive presentation of SDSA is available in the Documentation/SDSA/51

  • Click on Menu, select SDSA and validate by clicking on “ok”
  • Choose the xml file you want to open. The default choice is the last saved file (here: afterPropulsion.xml)
  • Select AMB_SDSA to analyze a database generated with AMB
  • Select Tornado to analyze a database generated in AMB with tornado Brute-force calculation
  • The SDSA GUI is loaded
  • Select Aircraft => Aerodynamic data
  • An information box appears and the Aero data report is displayed
  • The aerodynamic data are listed and can be plotted
  • Select Stabilty => Eigenvalues
  • Edit altitude and airspeed parameters if needed and click on START stability analysis
  • Eigenvalues are displayed