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Lecture 10: Configurations

This lecture covers critical aspects of aircraft configuration, focusing on design responsibilities, component placement, and weight management for optimal performance. Topics include calculating center-of-gravity range, integrating CAD renderings, and considerations for weapon systems across various mission roles. The design case studies of the F-16 and F-18 illustrate essential parameters like wing loading and control issues, while emphasizing the importance of reducing design rework and assembly defects using digital modeling. Practical recommendations for weight estimation and subsystem integration are also provided.

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Lecture 10: Configurations

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  1. Lecture 10: Configurations Jason Mickey For AE 440 A/C Lecture September 2009

  2. Configuration Responsibilities • Design and determine the location, relationship and weights of primary component parts • Calculate the center-of-gravity range and moments of inertia (to Stability) • Integrate and control all external dimensions, including cross-sectional and plan-form aspects (wing data from Aerodynamics; non-wing data to Aerodynamics) • Integrate all configurations with CAD renderings • Get structural component dimensions and design and optimize remaining internal component placement

  3. Design Considerations F-16 design included multiple weapons and multiple mission roles with high performance Key parameters included: -wing loading -thrust loading -control issues (at M~1 & M>1) -empty-weight fraction -pilot g tolerances

  4. Design Considerations Grumman QSP Concept Selection

  5. 3-View • Important quantitative aspect • Located near the front • Introduce overall features of the design

  6. Design Considerations

  7. F-18 Internal Configuration

  8. X-32 3-D Solid Model Digital modeling reduces design rework, minimizes scrap, and significantly lowers assembly defects

  9. Weights and Balances Ixx, Iyy, Izz About c.g. Needed for Stability

  10. Center-of-gravity Travel Configure fuel system and payload placement to minimize travel

  11. Systems • Electrical • Hydraulic • Auxiliary • Avionics

  12. (AE 441) Electrical

  13. (AE 441) Hydraulic

  14. (AE 441) Auxiliary and Avionics • Air Conditioners • Bleed-air • Avionics locations • Cross-flow for engine restart

  15. Samples of Configurations from Previous CDRs

  16. AE 440 3-View/Isometric View

  17. AE 440 Selection Reasoning • “The best LSA configuration for internal configuration reasons would be the LWT because having the fuel in the wings creates a more stable platform as it lowers the y-axis center of gravity which is discussed further in Section 6.4…”

  18. AE 441 Final Configuration

  19. AE 441 Final Configuration

  20. Weight Buildup

  21. CDR Suggestions • Re-estimate aircraft weight/size every week • Design deployment aspects & work with cost • Incorporate data for external configuration • Place components for internal configuration • Communicate design problems and conflicts • Get details on sub-systems size, weight, cost • Trade studies: e.g. size vs. payload weight

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