📄 fmsort.htm
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<TITLE>FDC help: FMsort</TITLE>
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<H2>Subsystem <I><FONT FACE="Arial","Helvetica","Sans Serif">FMsort</FONT></I></H2>
<I><FONT SIZE=2 FACE="Arial","Helvetica","Sans Serif">FMsort</FONT></I> is a subsystem of the system <I><FONT SIZE=2 FACE="Arial","Helvetica","Sans Serif"><A HREF="beaver.htm">Beaver</A></FONT></I>, used to sort the different contributions to the external forces and moments which act upon the aircraft and to compute the total external forces and moments in the body-axes reference frame by summing the different contributions. Note: the aerodynamic forces and moments for the DHC-2 'Beaver' are expressed in the body-axes reference frame in stead of the more common wind or flight-path axes. If aerodynamic lift and drag are used in stead, it is necessary to implement the transformation equations in the equations for <I>dV/dt</I>, <I>d(alpha)/dt</I>, and <I>d(beta)/dt</I> and to change <I><FONT SIZE=2 FACE="Arial","Helvetica","Sans Serif">FMsort</FONT></I> accordingly.
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Currently, only four contributions to the external forces and moments, acting upon the aircraft, are taken into account: the <A HREF="aerogrp.htm">aerodynamic forces and moments</A>, <A HREF="enggrp.htm">propulsive forces and moments</A> (including slipstream effects), forces due to the influence of <A HREF="gravity.htm">gravity</A>, and additional <A HREF="fwind.htm">contributions due to non-steady atmosphere</A>. It is not difficult to add more contributions to this list: just unmask the block <I><FONT SIZE=2 FACE="Arial","Helvetica","Sans Serif">FMsort</FONT></I> to find out how it works.
<H3>Inputvectors: <I>FMaero</I>, <I>FMprop</I>, <I>Fgrav</I>, <I>Fwind</I></H3>
<PRE> FMaero = [Xa Ya Za La Ma Na]' (aerodynamic forces and mo-
ments, coming from the subsystem <A HREF="aerogrp.htm">Aerodynamics Group</A>)
FMprop = [Xp Yp Zp Lp Mp Np]' (engine forces and moments,
coming from the subsystem <A HREF="enggrp.htm">Engine Group</A>)
Fgrav = [Xgr Ygr Zgr]' (gravity forces, coming from the
block <A HREF="gravity.htm">Gravity</A>)
Fwind = [Xw Yw Zw]' (wind forces from the block <A HREF="fwind.htm">Fwind</A>)
Xa, Ya, Za : aerodynamic forces in body-axes [N]
La, Ma, Na : aerodynamic moments in body-axes [Nm]
Xp, Yp, Zp : propulsive forces in body-axes [N]
Lp, Mp, Np : propulsive moments in body-axes [Nm]
Xgr, Ygr, Zgr: gravity forces in body-axes [N]
Xw, Yw, Zw : wind forces in body-axes [N] (correction terms
for non-steady atmosphere, may also include the
influence of atmospheric turbulence)
</PRE>
<H3>Outputvectors: <I>Ftot</I> and <I>Mtot</I></H3>
<PRE> Ftot = [Fx Fy Fz]' (total body-axes forces)
Mtot = [L M N ]' (total body-axes moments)
Fx, Fy, Fz: total forces along the aircraft's body-axes [N]
L, M, N : total moments along the aircraft's body-axes [Nm]
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