FDC 1.4 – A SIMULINK Toolbox for Flight Dynamics and Contro(101)

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to adapt the RESULTS program too. RESULTS is not able to detect changes in the
definitions of the matrices In and Out itself and it does not offer any internal errorchecking
mechanisms to protect against incorrect sizing or definition of the output
matrices. The source file RESULTS.M is located in the PROGRAMS subdirectory.
12.6.4 RESPLOT
RESPLOT is a very simple MATLAB script that plots time-trajectories of the most important
input and output signals of the Beaver model. These signals are: the airspeed
V, the angle of attack a, the sideslip angle b, the altitude H, the angular velocities p,
q, and r, the Euler angles y, q, and j, the control surface deflections de, da, and dr, and
the wind velocity components uw, vw, and ww.
The purpose of RESPLOT is to offer a quick overview of the simulation results
only; advanced plotting functions or other visualisation tools are not provided. To
change the appearance of the plots, or display other results, the RESPLOT.M sourcefile
must be edited. RESPLOT.M can be found in the PROGRAMS directory.
Before running RESPLOT, all relevant time-trajectories need to be present in the
MATLAB workspace. This can be ensured by first running RESULTS (after running a
simulation involving the Beaver model). RESPLOT does not include error-checking
routines to verify the availability of the required variables, it just quits with a hard
error if those variables cannot be found in the workspace.

Appendix A
Symbols and definitions
This appendix defines the symbols used in this report, and all relevant reference
frames and sign conventions. The units of measurements usually conform to S.I.
conventions. Only in some incidental cases, usually involving equations obtained
from other literature, non-standard units have been applied. If this is the case, the
applied units will be mentioned specifically in the main text.
Due to the very large number of variables, it could not always be avoided to use
the same symbols for multiple purposes, but most of the times this is not a serious
problem, because the meaning of a particular symbol usually follows directly from
the context in which it is used. In the few cases where there is a real chance of
symbols getting mixed-up, these particular symbols may be overlined, to provide
the necessary distinction.
A list of variable names and acronyms used in the FDC toolbox has been included
in appendix E. Several important aircraft model parameters have been listed in appendix
B, while appendix C explains the format which was used to implement the
aircraft model parameters in SIMULINK.
A.1 List of symbols
a [ ms−1 ] speed of sound
ax,k [ g ] kinematic acceleration along XB-axis
ay,k [ g ] kinematic acceleration along YB-axis
az,k [ g ] kinematic acceleration along ZB-axis
Ax [ g ] output of accelerometer (specific force) in c.g. along XB-axis
Ay [ g ] output of accelerometer (specific force) in c.g. along YB-axis
Az [ g ] output of accelerometer (specific force) in c.g. along ZB-axis
b [ m ] wing-span
c [ m ] mean aerodynamic chord
CD [ rad ] course datum (selected VOR bearing)
C1 [ – ] engine model parameter
C2 [ – ] engine model parameter
Cl [ – ] non-dimensional moment about XB-axis (rolling moment)
Cm [ – ] non-dimensional moment about YB-axis (pitching moment)
Cn [ – ] non-dimensional moment about ZB-axis (yawing moment)
CX [ – ] non-dimensional force along XB-axis
CY [ – ] non-dimensional force along YB-axis
286 Appendix A. Symbols and definitions
CZ [ – ] non-dimensional force along ZB-axis
D [ N ] total aerodynamic drag
dgs [ m ] distance from aircraft to nominal glideslope line
dloc [ m ] distance from aircraft to extended runway centerline
dpt [ – ] Dpt
12
rV2 = non-dimensional pressure increase across propeller
FB body-fixed reference frame, see section A.7.1
FE Earth-fixed reference frame, see section A.7.1
FM measurement reference frame, see section A.7.1
FR special body-fixed reference frame for the Beaver, see section A.7.1
FS stability reference frame, see section A.7.3
FV vehicle-carried vertical reference frame, see section A.7.1
FW flight-path reference frame, see section A.7.1
Fx [ N ] total external force along XB-axis, see figure 2.1
Fy [ N ] total external force along YB-axis, see figure 2.1
Fz [ N ] total external force along ZB-axis, see figure 2.1
fpa [ g ] flight-path acceleration
g [ ms−2 ] acceleration of gravity
h [ m ] pressure altitude
h [ s ] step-size for numerical integration
H [ m ] geopotential altitude
Hf [ m ] height above aerodrome level
　
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