NESC SOFIA Structur#16F1DE4...Tab6 - Zimmerman Input Data (Parameter Identification) Segment-0...
Transcript of NESC SOFIA Structur#16F1DE4...Tab6 - Zimmerman Input Data (Parameter Identification) Segment-0...
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SOFIA 747-SP Structural Dynamics
Overview
Starr Ginn ([email protected]) Dryden Flight Research Center
Aerostructures Deputy Branch Chief
& SOFIA Project Engineer
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Certification Requirements
• FAR Part 25.629 requires demonstration that the aircraft has flutter margins of at least 20% in equivalent airspeed beyond the structural design (VD/MD) envelope
• The scope of the SOFIA structural modifications require that flutter margins be demonstrated using a combination of
– Analysis – Ground Vibration Testing – Flight Flutter Testing
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Analysis Process
• Baseline 747SP flutter model – Derived from -100,-200 model – Validated by SOFIA Baseline testing
• SOFIA flutter model – SOFIA mass distribution changes per program Weight & Balance
Reports – SOFIA fuselage stiffness changes per Certification Finite Element
Model – Telescope Assembly & Simulator
• Simulator has no isolation system • TA isolation system has different configurations
– Validation through post-modification testing • Aircraft System and Observatory GVT and flight testing
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Analysis Results
• SOFIA vs. Baseline 747SP flutter margins – Critical flutter mechanism unchanged
– Antisymmetric wing / outboard engine / fuselage
– SOFIA aft fuselage stiffer than Baseline – Parametric studies show that increased fuselage stiffness has a negligible effect on
flutter speeds
– Some interaction of telescope and aircraft modes – No new flutter mechanisms predicted – No dramatic changes in speeds of existing mechanisms
– Wing fuel distribution remains dominant parameter – Flutter margins for all mechanisms predicted to be greater than the
required 20%
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Final flutter predictions
Note: Full outboard wing reserve tanks 2 & 3 full, TA caged and braked, S1ffff fuel condition
Closed Door Predicted Flutter Margin
X - Post-GVT O - Pre-GVT
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ZAERO Flutter compared to NASTRAN
• Wingtip Res2&3 fuel load sensitivity
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ZAERO Flutter compared to NASTRAN
• Wingtip Res2&3 fuel load sensitivity
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Zaero Sensitivity of Aero Modeling
• Increased Aerodynamic Model Fidelity
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Zaero Sensitivity of Aero Modeling
• Increased Aerodynamic Model Fidelity
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Zaero Sensitivity of Aero Modeling
• Increased Aerodynamic Model Fidelity of Engines was very important
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Aircraft Accelerometer Locations
• Segment 1 – Closed Door aircraft handling envelope expansion
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Wing 1st Bending Anti-Sym - Excited with Yaw Rap
Wing 1st Torsion Anti-Sym - Excited with Roll Rap
Aft Fuselage Torsion/Bending - Excited with Yaw Rap
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Segment-0 Flight Test Results
• Flutter Raps vs. Analytical Prediction – – Damping Value Method; Sub-critical Advantage – 15,000 ft
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IADS Flight Test Displays
Tab6 - Zimmerman Input Data (Parameter Identification)
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Segment-0 Flight Test Results
• Flutter Raps vs. Analytical Prediction; Example of Ball park Agreement – Zimmerman Technique; robust near instability – 15,000 ft, Tracking W1B-Anti & W1T-Anti
Flutter Onset Velocity 598 KCAS Mach Number at Flutter 1.14
Flutter Onset Velocity 388 KCAS Mach Number at Flutter 0.76
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Segment-0 Flight Test Results
• Flutter Raps vs. Analytical Prediction; Example of Failed Agreement – Zimmerman Technique; robust near instability – 15,000 ft, Tracking W1B-Anti & Eng-Anti/In-Phase
Flutter Onset Velocity 515 KCAS Mach Number at Flutter 0.99
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Segment-0 Flight Test Results
• Flutter Raps vs. Analytical Prediction; Example of Good Agreement – Zimmerman Technique; robust near instability – 15,000 ft, Tracking W1B-Anti & Aft Fuselage Lateral/Torsion
Flutter Onset Velocity 515 KCAS Mach Number at Flutter 0.99
Flutter Onset Velocity 388 KCAS Mach Number at Flutter 0.76
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• Original Flutter Analysis Remains Valid
– Instability crossings occur only with wing reserve tanks 2 & 3 full (will be empty for initial envelope expansion)
– Flutter onset not predicted to be explosive but rather relatively moderate; pilot should sense vibrations before major structural damage
• Critical Flutter Margin 1.6 Vd (Dive Velocity - Max. A/C Velocity)
– Increase over baseline (result of stiffer nacelles; measured in GVT and modeled for analysis)
Closed Door Analysis for Full Envelope
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Notes:
1. For wing reserve tanks 2&3 full, Mach
0.8, post GVT model correlation, TA caged and braked
2. Rigid body and remainder of analysis elastic modes not plotted here (60 total, usually up to 20 Hz)
Closed Door Analysis for Full Envelope
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• Predicted Flutter Mechanism – Wing first bending, Anti – Sym (1.09 Hz); major effect on flutter speed – Wing first torsion and Outboard nacelle lateral/roll-pitch, Anti – Sym (1.90
Hz); major effect on flutter speed – Inboard Nacelle lateral/torsion, Anti – Sym (2.02 Hz) – Aft fuselage lateral/torsion and Wing fore/aft, Anti – Sym (2.43 Hz)
Wing 1st Bending Anti-Sym
Nacelle Lat/Tors Anti-Sym Wing 1st Torsion Anti-Sym
Aft Fuse Lat/Tors Anti-Sym
Closed Door Analysis for Full Envelope
Frequency Coalescence
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Flight Flutter Envelope Expansion Test Points
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Flt 006 25K ft @ M0.76 First Yaw Rap
Flt 006 25K ft @ M0.76 Repeat Yaw Rap
Wing Tip
Upper Rudder
Vertical Tail
Rudder Position
Wing Tip
Upper Rudder
Vertical Tail
Rudder Position
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Flt 006 25K ft @ 0.79 Mach Roll Rap – No Turbulence
Norm Accel
Wing Tip
Aileron Position
Flt 006 25K ft @ 0.83 Mach Roll Rap - w/ Light Turbulence
Norm Accel
Wing Tip
Aileron Position
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Flt005
Flt006
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28
Flu$erEnvelopeCleared
Closed Door Envelope Cleared to Mmo (0.87M) and Vmo (340 KCAS)
o FAR 25.629, Flutter, is Satisfied by Flight Test to Md (0.92M) and Vd (370 KCAS)
– Damping Margin of 0.03 Maintained – No Large and Rapid Reduction in Damping as Md and Vd are Approached
o FAR 25.1505, Maximum Operating Limit Speed, Also Met by Flight Test – Level Flight Upset to Dive Margins of 0.05M and 30 KCAS
Short Science Open Door Envelope Cleared to Mmo (0.87M) and Vmo (270 KCAS)
o Open Door Configuration Cleared by Closed Door (Same Flutter Modes)