fmsort.hlp

MATLAB在飞行动力学和控制中应用的工具

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FMSORT is a Simulink subsystem, used to sort the different con-
tributions 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 contribu-
tions. 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 V dot, alpha dot,
and beta dot and to make the proper changes to FMSORT!
    Currently, only four contributions to the external forces and
moments, acting upon the aircraft, are taken into account: the
aerodynamic forces and moments, forces and moments which arise
due to the operation of the powerplant (including slipstream ef-
fects), forces due to the influence of gravity, and additional
contributions due to a non-steady atmosphere. It is not difficult
to add more contributions to this list: just unmask the block
FMSORT to find out how it works.

Inputvectors: FMaero, FMprop, Fgrav, Fwind.
===========================================
  FMaero = [Xa  Ya  Za  La  Ma  Na]'  (aerodynamic forces and mo-
           ments, coming from the subsystem 'Aerodynamics Group')

  FMprop = [Xp  Yp  Zp  Lp  Mp  Np]'  (engine forces and moments,
                        coming from the subsystem 'Engine Group')

  Fgrav  = [Xgr Ygr Zgr]'        (gravity forces, coming from the
                                                   block GRAVITY)

  Fwind = [Xw  Yw  Zw]'        (wind forces from the block FWIND)

where:

  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)

Outputvectors: Ftot and Mtot.
=============================
  Ftot = [Fx Fy Fz]'                     (total body-axes forces)
  Mtot = [L  M  N ]'                    (total body-axes moments)

where:

  Fx, Fy, Fz: total forces along the aircraft's body-axes [N]
  L, M, N   : total moments along the aircraft's body-axes [Nm]

More info:
==========
See AEROGRP.HLP, AEROMOD.HLP, ENGGRP.HLP, ENGMOD.HLP, GRAVITY.HLP
and FWIND.HLP for more info about the different contributions to
the external forces and moments.

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The FDC toolbox, Copyright Marc Rauw 1994-1998.