Investigation of High-Angle-of-Attack Maneuver-Limiting Factors Part II. Piloted Simulation Assessment of Bihrle Departure Criteria

Item

Title
Investigation of High-Angle-of-Attack Maneuver-Limiting Factors Part II. Piloted Simulation Assessment of Bihrle Departure Criteria
Date
1980
Index Abstract
Coming Soon
Photo Quality
Not Needed
Report Number
AFWAL TR 80-3141 Part 2
Creator
Mitchell, David G.
Johnston, Donald E.
Corporate Author
Systems Technology, Inc.
Laboratory
Flight Dynamics Laboratory
Extent
50
Identifier
ADA101647
Access Rights
Approved for public release; distribution unlimited
Distribution Classification
1
Contract
F33615-76-C-3072
DoD Project
2403
DoD Task
240305
DTIC Record Exists
No
Distribution Change Authority Correspondence
None
Abstract
The high-angle-of-attack, low-speed stall/departure characteristics of the F-4J and F-14A are analyzed, using a six-degree-of-freedom mathematical model with nonlinear aerodynamics. Cause-effect relationships are investigated for maneuver limiting factors including wing rock, nose slice, and rolling departures. Cross-derivatives of L alpha, N alpha, and M beta alter key transfer function parameters. A piloted simulation validates analytic predictions and demonstrates that departure warning, susceptibility, and severity are strongly influenced by the static cross-derivatives. A connection between roll numerator parameter values and pilot perception of departure susceptibility and severity is identified. Potential modifications for the high AOA sections of the MIL-F- 8785B Flying Qualities Specification are proposed: a criterion for the real part of the roll numerator root, further recommendations for minimizing departure susceptibility and certain sideslip influences, and a flying quality rating form for assessing departure and recovery characteristics. Part I, Analysis and Simulation, presents a summary of the complete investigation and results. Part II, Piloted Simulation Assessment of Bihrle Departure Criteria, presents a detailed comparison of analytical prediction and piloted simulation results for a specific set of programmed control deflections. Part III, Appendices -- Aerodynamic Models, contains the detailed aerodynamic models employed in the F- 4J and F-14A high-angle-of-attack analysis and validation and the equations of motion, aerodynamic models, control system configurations, etc., employed in the piloted simulation.
Report Availability
Full text available
Date Issued
1980-12-01
Provenance
AFRL/VACA
Type
report
Format
1 online resource
Subject
Mathematical Models
Aircraft
Performance (Engineering)
Jet Fighters
Recovery
Transfer Functions
Equations of Motion
Parameters
Matrices (Mathematics)
Deflection
Angle of Attack
Low Velocity
Stalling
Nonlinear Systems
Mathematical Prediction
Aerodynamic Characteristics
Sideslip
Closed Loop Systems