Wake Vortex in Flight Simulation

Transcription

1 Titel der Präsentation, Datum WakeNet2-Europe Simulator Engineering and Projects Hamburg May 10 11, How it started. FSEM 2 1

2 Available on the following simulators / B /400/500 (AE) / A319 (AE) / B ER (THALES) 3 Validation / Subjectively tuned by Pilot during simulator acceptance 4

3 AE Simulator 5 THALES Simulator 6

4 7 'Title Wake Vortex Model 'Module_ID A319VFWV 'Documentation Aerodynamics SDD 'Application wake Vortex oefficient Buildup 'Author Unknown 'Date 20/04/2001 'Entry_point WVORTEX 'System Flight 'Subsystem Aerodynamics 'Iteration_rate 30 Hz, 33ms 'Process SP WAKE VORTEX PROGRAM PREPARED FOR A.E. DILLARD, AFS-408 BY ADVANED SIMULATION ORPORATION FAA Level Full Flight Simulator Oklahoma ity, Oklahoma Theory: ======= The wake vortex model is designed for operation in a real time simulation environment. It uses the aerodynamics model provided by Boeing and a qualified environment model to provide the reqired wind fields. Reasonable simulation of aircraft flight dynamics is the intention of this model. The software implementation of this model is designed for use in a AE manufactured flight training device. This model simulates the effects of an aircraft passing through a single wake vortex or a pair of wake vortices. The orientation, magnitude, and duration of the vortex may be modified through the instructor facility of the simulator. The wake vortices in this model are assumed to have their axes parallel to the plane of the ground. The angle the vortex makes with the longitudinal axis of the plane may be varied. The instructor may preset the relative position of the vortex with respect to the simulator's trajectory. Vortices modeled as purely crossing vortices (perpendicular to the trajectory of the aircraft) use a wind field which emulates that of a wing passing through a vortex. The wind field affects the angle of attack and the airspeed of the aircraft which causes vertical and longitudinal effects. Vortices modeled as trailing or skewed vortices (not perpendicular to the trajectory of the aircraft) use aerodynamic coefficient modifications which cause force and moment changes as the aircraft passes through the vortex. Roll and lift coefficients are modified. Refer to: Journal of Aircraft, Vol. 33, No. 2, March-April 1996: Vortex Wakes of Two Transports Measured in 80 x 120 Foot Wind Tunnel. (V.J.Rossow, et.al., NASA Ames Research enter, Moffet Field, A ) 8

5 AIRRAFT-DEPENDENT DATA A319 data: Wing data: DATA MA_319 / / DATA B_319 / / The A wing span is ft. The fuselage diameter is ft. Therefore, if each wing is split into ten sections, each segment is 4.95 ft wide. A wing chord data are estimated for lateral distances of: feet from the aircraft centerline. DATA HRD_319 & /6.1, 6.7, 7.9, 9.2, 10.4, 11.0, 12.2, 13.4, 16.5, 18.9, & 18.9, 16.5, 13.4, 12.2, 11.0, 10.4, 9.2, 7.9, 6.7, 6.1 / DATA WSWP_319 / 27.0 / DATA FDIAM319 / / DATA A0_319 / 5.67 / DATA M_319 / 0.3 / DATA AOAST319 / 15.0 / Horizontal stabilizer data: DATA HMA_319 / 8.86 / DATA HB_319 / / The A horizontal stabilizer span is 40'10". Therefore, if each side is split into 4 sections, each segment is 5.10 ft wide. A stabilizer chord data are estimated for lateral distances of: feet from the aircraft centerline. DATA HHD_319 & / 4.9, 7.3, 9.8, 12.2, 12.2, 9.8, 7.3, 4.9 / 9 10

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7 13 14 Vielen Dank! Stefan Simon Lufthansa Flight Training Tel. 069/ Fax 069/