ACSYNT. Program Overview/User Orientation Phoenix Integration, Inc.

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2 What is? Parametric design tool for aircraft synthesis... Concept Development Preliminary Design Detailed Design Lots of Designs Tradeoff Studies Requirements Optimization In-depth analysis Narrowed to few designs Detailed optimization Detailed analysis Subsystem design & optimization

3 Is... Component-based CAD Conceptual level synthesis tool Tool for tradeoff studies Multidisciplinary Capable of optimization Only part of a complete design diet

4 Is Not... CFD FEM Airfoil Design Tool Primitive-Based CAD (i.e. AutoCAD) Detailed Design Animation Tool Flight Simulator

5 Learning Curve Steep Recommendations: Read the user guide Look at examples (input/output) Experiment Rewarding if mastered

6 Getting Started Things You ll Need Know your mission Have a good three-view Collect as much info about engine Payloads, fixed weights Airfoil type Ballpark estimate of weight

7 Program Kernals Analysis Design Tools Geometry Modeler

8 Starting 1) login with userid, password 2) type cd acsynt 3) type acsynt

9 File Selection Screen 1) From main menu select FILE You should see the following screen... File Types Geometry Analysis

10 Input Conventions Parameter Templates Text-Based Input Graphical Spreadsheet

11 Geometry Overview 3D Bspline surfacing Modeller allows Airfoil types Body components Pods Gen pods Cross section buildup

12 Building Geometry (Intro) Think in cross sections Cannot directly analyze: Joined Wings Box Wings Biplanes Tips Start with basic components first You can model more than you can analyze

13 Building Geometry (1) Add Component

14 Building Geometry (2) Modify Component

15 Graphic file support Graphic file support CAD: IGES Export Graphics (XV): GIF, JPEG, TIFF, BMP

16 Laying out a Mission Phase-based mission Point performance BCA/BCM Max rate climbs Weapons release Takeoff Climb Accel Cruise Combat Loiter Descent Hover

17 Convergence Iterative Weight Sizing Process W est Geometry W calc =F(W est ) Trajectory Aero Propulsion W calc Weights

18 Aerodynamics Minimum Drag Transonic (M DD ) Component buildup Data correlation (Geom, alpha) Skin Friction Sommer-Short (TR R-123, 1962) Wave Drag Induced Drag Momentum theory / area rule est. (Sears-Haack) AEROX - NASA TM X-73,208 Semi-empirical based on compressible theory

19 Aerodynamic Zones 1. Incompressible 2. Shock Free 3. Leading-Edge Mach-Limited 4. Surface Mach-Limited 5. Supersonic Attached Shock 6. Supersonic Detached-Shock

20 Weights Component-based empirical methods Generate standard statements Fixed vs. Computed W = Input Value : Fixed W = F(WGTO) : Computed Slopes, Tech Factors W = SLOPE(I)*W W = TECH(I)*W Component Pounds Kilograms Percent Slope Tech Fixed Airframe Structure No Wing No Fuselage No Horizontal Tail ( Low) No Vertical Tail No Nacelles No Landing Gear No Propulsion No Engines ( 2) No Fuel System No Fixed Equipment No Hyd & Pneumatic No Electrical No Avionics No Instrumentation No De-ice & Air Cond No Aux Power System No Furnish & Eqpt No Seats and Lavatories No Galley No Misc Cockpit No Cabin Finishing No Cabin Emergency Equip No Cargo Handling No Flight Controls No Empty Weight Operating Items No Flight Crew ( 2) No Crew Baggage and Provisions No Flight Attendents ( 6) No Unusable Fuel and Oil No Passenger Service No Cargo Containers No Operating Weight Empty Fuel Payload No Passengers (239) No Baggage No Cargo No Calculated Weight No Estimated Weight

21 Propulsion Cycle Analysis Installation Effects Scaling factors (T, SFC) Find a suitable compressor map/backbone Input Deck More accurate More time consuming Less scalable J-85 TF-30 JT-8D JT-9D CF-6 M,h T SFC PWCC Throttle (2.7/4k) (14/25k) (14.5k) (50k) (50k)

22 Design Tools IR Analysis Area Plot

23 Design Tools Carpet Plots Aero Plots