1. ZONAIR Analysis for JSF Flight Loads
P. C. Chen
D. H. Lee
D. D. Liu
7430 E. Stetson Drive, Suite 205, Scottsdale, AZ , Tel (480) , Fax (480) ,

2. ZONAIR Analysis for JSF Flight Loads
A ZONAIR JSF panel model has been generated from the CFD surface mesh provided by LMCO
JSF NASTRAN model solution was provided by LMCO to give
Generalized mass and stiffness matrices for flexible loads
Grid points for spline
Two sets of trim analysis were performed
Rigid loads computed by ZONAIR
Rigid loads interpolated from CFD solutions to ZONAIR panels
NASTRAN static analysis was performed using the NASTRAN FORCE/MOMENT bulk data cards generated by ZONAIR trim analysis
Sectional loads (shear, bending moment, and torsion) and elastic-to-rigid ratio of CL, CM, etc. were generated.

3. ZONAIR Panel Model CFD GRID ZONAIR (4314 PANELS)
ZONAIR panel model is generated as follow
Creating surface geometry from the JSF CFD surface mesh using PATRAN
Generating CQUAD4 and CTRIA3 applying mapped mesh on the surface geometry
Panel edge alignment with hinge lines of control surface is modeled
Flow-through boundary condition is specified on the inlet panels
CFD GRID
ZONAIR
(4314 PANELS)

4. Comparison of Cp between ZONAIR and CFD solutions at M=0. 9, AoA=0
Comparison of Cp between ZONAIR and CFD solutions at M=0.9, AoA=0.0 deg.
CFD
ZONAIR

5. Interpolated Cp on ZONAIR Panels from CFD Solutions at M=0. 9, AoA= 0
Interpolated Cp on ZONAIR Panels from CFD Solutions at M=0.9, AoA= 0.0 deg.
The interpolated CFD Cp is used as the rigid loads for flexible load analysis
AIC matrix computed by ZONAIR
Stiffness matrix from NASTRAN
Spline matrix
Rigid loads
Inertia loads
CFD
ZONAIR+CFD

6. Generation of SPLINE Matrix
The thin plate spline method (3D spline) is used to generate the spline matrix
ZONAIR outputs graphical files to allow visual inspection of the accuracy of the spline matrix
NASTRAN Modes
Deformed ZONAIR Modes Hz
Mode 4 Hz
Mode 5 Hz
Mode 6

7. Flexible-to-Rigid Ratio v.s. Dynamic Pressure at =0.90
CL
CM
CLh
CMh

8. Trim Analysis at M=0.90 and Sea Level
9.0 g pull-up is specified as the trim conditions
Two trim equations: Lift=9.0g and moment=0.0
Two trim variables: angle of attack and horizontal tail deflection angle
Two sets of trim analysis are performed: rigid loads computed by ZONAIR and interpolated from CFD solutions
Rigid load by ZONAIR
Rigid load by CFD
=12.673o
=13.771o
=24.988o
=26.182o

9. Sectional Loads of 9g Pull-Up at M=0.90, Sea Level
Sectional Shear Force
Sectional Bending Moment
Sectional Torsional Moment about ¼ Chord
ZONAIR
ZONAIR
ZONAIR
ZONAIR + CFD
ZONAIR + CFD
ZONAIR + CFD

10. NASTRAN Static Analysis using ZONAIR Generated Loads
ZONAIR trim analysis generates loads in terms of NASTRAN FORCE/MOMENT bulk data cards at structural grid points
User can insert the file into the NASTRAN input deck for subsequent detailed stress analysis

11. Ease of Adding Underwing Stores
Two macroelements can be specified:
CAERO7: thin wing modeling with thickness effects simulated by source sheet
BODY7: automated panel/grid generation of body of revolution
Pylons and store fins can be modeled by CAERO7 and store body can be modeled by BODY7
Front View