📄 power.htm
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<TITLE>FDC help: Power (Beaver)</TITLE>
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<H2>Subsystem <I><FONT FACE="Arial","Helvetica","Sans Serif">Power (Beaver)</FONT></I></H2>
<I><FONT SIZE=2 FACE="Arial","Helvetica","Sans Serif">Power (Beaver)</FONT></I> is a masked S<SMALL>IMULINK</SMALL> subsystem which is used to compute the engine power and non-dimensional pressure increase across the propeller for the DHC-2 'Beaver' aircraft, using the engine power model from <A HREF="#References">ref.[1]</A>. Power is contained in the subsystem <I><FONT SIZE=2 FACE="Arial","Helvetica","Sans Serif"><A HREF="enggrp.htm">Engine Group</A></FONT></I> of the system <I><FONT SIZE=2 FACE="Arial","Helvetica","Sans Serif"><A HREF="beaver.htm">Beaver</A></FONT></I>. This subsystem also contains the blocks <I><FONT SIZE=2 FACE="Arial","Helvetica","Sans Serif"><A HREF="engmod.htm">Engmod (Beaver)</A></FONT></I> and <I><FONT SIZE=2 FACE="Arial","Helvetica","Sans Serif"><A HREF="fmdims.htm">FMdims</A></FONT></I>.
<H3>Inputvectors: <I>x</I>, <I>uprop</I>, <I>yatm</I></H3>
<PRE> x = [V alpha beta p q r psi theta phi xe ye H]' (states)
uprop= [n pz]' (engine inputs)
yatm = [rho ps T mu g]' (atmospheric properties, computed in
the block <A HREF="atmosph.htm">Atmosph</A>)
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 '' '' '' '' [m] }
{H : altitude above sea-level [m] }
n : engine speed [RPM]
pz : manifold pressure ["Hg]
rho : air density [kg/m^3]
{ps : static pressure [N/m^2] }
{T : air temperature [K] }
{mu : dynamic viscosity [kg/(m*s)] }
{g : acceleration of gravity [m/s^2] }
</PRE>
Variables which are not actually used by <I><FONT SIZE=2 FACE="Arial","Helvetica","Sans Serif">Power (Beaver)</FONT></I> have been displayed between accolades.
<H3>Outputvector: <I>ypow</I></H3>
<PRE> ypow = [dpt P]'
dpt : dimensionless pressure increase across the propeller [-]
P : engine power [Nm/s]
</PRE>
<H3><A NAME= "References">References</A></H3>
<OL>
<LI>R.T.H. Tjee and J.A. Mulder. <I>Stability and Control Derivatives of the De Havilland DHC-2 "Beaver" aircraft</I>. Report LR-556, Delft University of Technology, 1988.
</OL>
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