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Lecture 10: Configurations

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

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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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