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changing the number of Inport and/or Outport blocks will cause connection problems
for the open-loop simulation models, the autopilot models, the interface to the
aircraft trimming program, and the workspace input/output functions. Although it
is not difficult to correcting these problems, it does require a lot of attention, especially
for users who are not yet fully familiar with the toolbox.
In order to maintain the integrity of the toolbox, it is advised always to keep
safety copies of the original files on your system, which will allow you to quickly restore
errors when necessary (of course, it is always possible to re-install the complete
package if things really go wrong). It is also recommended to use distinct filenames
for your own adaptations of the FDC models and tools to prevent possible mix-ups in
the future. Don’t let that stop you from experimenting, though: this is Open Source
software for a reason!
Users who now decide to start working with the toolbox right away should not
be surprised if they are, at times, confronted with some disturbing error messages.
Over the years the programs have been equipped with some basic error-trapping
subroutines, but that doesn’t make this toolbox entirely error-proof. If you are not
keen on reading before experimenting, it is recommended to at least study the relevant
helpfiles and read chapter 13, which contains some examples of the practical
use of this toolbox.
7.13. About the block and function reference chapters 115
7.13 About the block and function reference chapters
In the next three chapters, the SIMULINK implementation of the aircraft model, the
wind and turbulence models, and the radio-navigation models will be discussed
in detail. These chapters will list all subsystems and blocks in alphabetical order,
providing a short description, a list of equations (or a list of subsystems and blocks
for subsystems which don’t contain any individual equations), lists of input and
output signals1, an overview of the block or subsystem parameters, and an overview
of important connections to other blocks or subsystems.
The description of the elements from the aircraft model in chapter 8 also includes
the path in the aircraft model, starting with the interface level Beaver level 1, and
the location of the block-library containing the element, starting with FDCLIB. For
the description of the wind and turbulence elements in chapter 9 and the radionavigation
elements in chapter 10 the locations in the main library FDCLIB and the
wind or navigation libraries Windlib or Navlib will be included.
Chapters 11 and 12 describe the analytical functions and support utilities for the
FDC toolbox. Together with the model reference chapters, this completes the ‘reference
guide’ for the basic FDC models and tools. Practical applications of the toolbox
will be elaborated later in chapter 13, and in chapters 14 and 15, which describe a
case-study of the Beaver autopilot.
1To avoid signal clutter, the FDC models make extensive use of vector signals. If a vector signal is
used as input to a block, this doesn’t necessarily mean that all elements from this vector are actually
needed; in general only a subset of these elements is used by the block equations.
Chapter 8
Aircraft model block reference
The previous chapter provided an introduction to the FDC software, describing the
installation process and the general architecture of the models and libraries. In this
chapter we will take a closer look at the dynamics model of the DeHavilland DHC-2
Beaver aircraft, which is the core element of the FDC toolbox. First, the structure of
this model will be outlined and compared with the theoretical basis from chapter 3.
Next, all individual blocks and subsystems from the aircraft model will be described
in alphabetical order. Hereafter, chapters 9 and 10 will provide similar information
for the wind, turbulence, and radio-navigation models.
8.1 The aircraft model and its subsystem equivalents
The SIMULINK implementation of the nonlinear aircraft model has been based on
the block-diagram structure from figure 3.2 of chapter 3. The resulting SIMULINK
model has been shown in figure 8.1. This model differs from figure 3.2 in that it
gathers all output signals on the right-hand side of the block-diagram, which results
in a stairway-like structure in which subsequent blocks are shifted to the right and
downwards. Also, the axis-transformations have been integrated in the forces and
moments blocks, and a separate block for computing additional observation variables
has been included directly below the subsystem ‘Aircraft equations of motion’.
But despite these differences, the overall structure of figure 3.2 should be clearly
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