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Download ASTROS User`s Reference Manual for Version 20.
Transcript
USER’S MANUAL Finally, the trim parameters that were computed for the current flight condition are shown. In general, these are the angle of attack in degrees, the pitch rate in deg/s, and the SYMMETRIC control surface deflection angle(s) in degrees. In each case, the rigid and flexible "trim" state is shown (the rigid is informational only) and the parameter is labeled as COMPUTED if it was a free parameter in the trim analysis or USER INPUT if it was a fixed user input trim parameter. Only those parameters explicitly called out on the TRIM bulk data entry are listed. The ANTISYMMETRIC trim print is similar except that the degrees of freedom that are available result in coefficients for side force, rolling moment and yawing moment. CY ,Cl ,CN β β β = Yaw angle (β), in both radians and degrees. CY ,Cl ,CN r r r = Yaw rate (r), in both radians and degrees. CY ,Cl ,CN p p p = Roll rate (p), in both radians and degrees. CY ,Cl ,CN δ δ δ = User defined control surface deflection(s) (δ), in both radians and degrees. These nondimensional factors are implicitly defined in the following equations: Side Force _ rb pb + CY + CY δi fo r i = 1 ,..., nANTI = qS CY β + CY 2V 2V β δ r p i Roll Moment _ rb pb = qSb Cl β + Cl + Cl + Cl δi fo ri = 1 ,..., nANTI 2V 2V β δ r p i Yaw Moment _ rb pb = qSb CN β + CN + CN + CN δi fo ri = 1 ,..., nANTI β δ r 2V p 2V i b = reference semispan nANTI = The number of antisymmetric control surfaces where, These quantities are shown in three forms as shown in Table 8-24: (1) (2) (3) ASTROS The stability derivative for the rigid aerodynamic model as computed directly from the forces acting on the aerodynamic boxes (termed DIRECT in the output). This output always appears since it comes directly from the aerodynamic model. The stability derivative for the rigid aerodynamic model as computed from the forces transformed to the structural degrees of freedom (termed SPLINEd in the output). This output only appears if the associated DOF is SUPORTed. The flexible derivative which includes corrections for the flexibility and inertia relief effects. This output only appears if the associated DOF is SUPORTed. OUTPUT FEATURES 8-33
