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Keith Hout Patrick Dempsey Bridget Fitzpatrick Heather Garber Jong Soo Mok

ORION AEROSPACE. Stability Control and Flight Performance PDR October 24, 2000. Keith Hout Patrick Dempsey Bridget Fitzpatrick Heather Garber Jong Soo Mok. ORION AEROSPACE. Overview: Stability, Control and Performance. -Class I Sizing of Tails -Class I Sizing of Control Surfaces

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Keith Hout Patrick Dempsey Bridget Fitzpatrick Heather Garber Jong Soo Mok

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  1. ORION AEROSPACE Stability Control and Flight Performance PDR October 24, 2000 Keith Hout Patrick Dempsey Bridget Fitzpatrick Heather Garber Jong Soo Mok

  2. ORION AEROSPACE Overview: Stability, Control and Performance -Class I Sizing of Tails -Class I Sizing of Control Surfaces -Static Margin, Aerodynamic Center Location, C.G. Location -Trim Diagram -Class 2 Analysis of Tails -X-Plots -Important Stability Derivatives and Comparison

  3. ORION AEROSPACE Overview: Stability, Control and Performance -Short Period Mode parameters -S&C Tasks Remaining -Performance Parameters -Gyles AeroDesign

  4. ORION AEROSPACE Class I Sizing of Tails • Tail Volume Coefficient Method (Raymer) • Picked coefficients based on past 451 designs

  5. ORION AEROSPACE Class I Sizing of Tails • Results

  6. ORION AEROSPACE Class I Sizing of Control Surfaces • Historical Data (Raymer) • Guidelines • Ailerons: (.15 - .25)c and (0.5 – 0.9)b • Elevators: (.25 - .50)c and (~.9)b • Rudders: (.25 - .50)c and (~.9)b • Selected: • Ailerons: .15c and full span • Elevators: .40c and full span • Rudder: .40c and full span

  7. ORION AEROSPACE e CL S d h - a h h x x ( 1 ) acwing body h ach / a CL S d = a w w x e CL S d h + - a h h 1 X ( 1 ) h ach a CL S d a w w Static Margin, CG, and Aerodynamic Center • Static Margin Desired is 18% • Mark Peters suggests 15% as lower limit (some past 451 designs flew around 10%) XLE=0.91’ XCG=1.01’ XACWING=1.26’ X=1.28’ XACHT=5.60’

  8. ORION AEROSPACE Trim Diagram CLCruise=.7 CLTurn=.98 CLMax=1.37 iw=2.2o ih=-3o

  9. ORION AEROSPACE Class II Analysis of Tails

  10. ORION AEROSPACE Class II Analysis of Tails

  11. ORION AEROSPACE Pertinent Stability Derivatives Comparison All units are rad-1

  12. ORION AEROSPACE Short Period Mode

  13. ORION AEROSPACE Tasks Remaining • Refine tail sizes due to new findings • Ensure CG can be obtained at current location, if not move wing location • Construct trim triangle • Find control surface deflection limits • Dynamic Analysis

  14. Performance ORION AEROSPACE -Dto = (1.44*Wto^2)/(rho*S*g*T) -Gamma = asin((T-D)/W) -Psidot = (g*(n^2-1))/Vmax Performance Values

  15. Performance ORION AEROSPACE -E = W*min -Battery energy total = 2592 Wmin Aircraft Energy

  16. ORION AEROSPACE Giles AeroDesign

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