📄 dimless.htm

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      FDC help: Dimless
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    <h2>
      Subsystem <i>Dimless</i>
    </h2>
    <p><i>Dimless</i> computes the dimensionless
    rotational velocities <i>pb/2V</i>, <i>qc/V</i>, and <i>rb/2V</i>. Of
    course, the computation itself is trivial if the elements of the state
    vector <i>x</i> are known, but since these variables may be needed more
    than once it is still useful to compute them in a separate block.</p>
    <p><i>Dimless</i> is contained in the subsystem <i><a href=
    "aerogrp.htm">Aerodynamics Group (Beaver)</a></i> of the <i><a href="beaver.htm">Beaver</a></i> model. Other blocks in that subsystem are: <i><a
    href="aeromod.htm">Aeromod (Beaver)</a></i> and <i><a href=
    "fmdims.htm">FMdims</a></i>.</p> 
    <h3>
      Inputvector: <i>x</i>
    </h3>
<pre>
  x = [V alpha beta p q r psi theta phi xe ye H]&#39;        (states)

  V    : airspeed [m/s]
 {alpha: angle of attack [rad]                                  }
 {beta : sideslip angle [rad]                                   }
  p    : roll rate [rad/s]
  q    : pitch rate [rad/s]
  r    : yaw rate [rad/s]
 {psi  : yaw angle [rad]                                        }
 {theta: pitch angle [rad]                                      }
 {phi  : roll angle [rad]                                       }
 {xe   : x-coordinate in Earth-fixed reference frame [m]        }
 {ye   : y-coordinate &#39;&#39;     &#39;&#39;          &#39;&#39;      &#39;&#39;  [m]        }
 {H    : altitude above sea-level [m]                           }
</pre>
    <p>The state variables which are not actually needed by <i>Dimless</i> have
    been displayed between curly braces.</p> 
    <h3>
      Outputvector: <i>ydl</i>
    </h3>
<pre>
  ydl = [pb/2V qc/V rb/2V]&#39; (dimensionless rotational velocities).

  pb/2V: dimensionless roll-rate  (b = wing span)
  qc/V : dimensionless pitch-rate (c = cbar = mean aerodynamic chord)
  rb/2V: dimensionless yaw-rate   (b = wing span)
</pre>
    <h3>
      Parameters to be defined in the Matlab workspace
    </h3>
    <ul>
      <li>
        <i>GM1</i>: vector with some important geometrical properties of the
        &#39;Beaver&#39; aircraft, and the mass of the aircraft (which is
        assumed to be constant during the motions of interest). Here, the wing
        span <i>b</i> and the mean aerodynamic chord <i>cbar</i> are extracted
        from <i>GM1</i>. <i>GM1</i> can be loaded into the workspace from file
        by running the utility <i><a href="datload.htm">DATLOAD</a></i>. Run
        <i><a href="modbuild.htm">MODBUILD</a></i> first if the datafile does
        not yet exist.
      </li>
    </ul>
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