1 / 25

Boiler Xpress 1 Final Presentation April 26, 2001

Boiler Xpress 1 Final Presentation April 26, 2001. Kacie Burton Kevin Dahya Kerem Koray Mellisa Glaser Wael Nour Tanya Tuinstra. Project Objective. Write a MATLAB computer program for dynamic modeling and control system design of fixed wing aircraft

rhea-cook
Download Presentation

Boiler Xpress 1 Final Presentation April 26, 2001

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. Boiler Xpress 1Final PresentationApril 26, 2001 Kacie Burton Kevin Dahya Kerem Koray Mellisa Glaser Wael Nour Tanya Tuinstra

  2. Project Objective • Write a MATLAB computer program for dynamic modeling and control system design of fixed wing aircraft • Use Boiler Xpress geometry, mass, and aerodynamic data • Produce stability and control derivatives • Determine 4th order TF, Q(s)/E(s), R(s)/R(s), and P(s)/A(s) • Determine 12th order TF, Q(s)/E(s), R(s)/R(s), and P(s)/A(s) • Design 3 stability augmentation systems • Pitch rate feedback to elevator to increase  of Short Period mode • Yaw rate feedback to rudder to increase  of Dutch Roll mode • Roll rate feedback to aileron to decrease time constant of roll mode

  3. How we did it… • Modified Cessna182.m to apply to the BoilerXpress • Calculated control derivatives using Jan Roskam, Methods for Estimating Stability and Control Derivatives of Conventional Subsonic Airplanes • 4th order transfer functions: • BoilerXpressLatSC.m • BoilerXpressLongSC.m • Plotted root loci • 12th order transfer functions and step responses: • FlatEarth.mdl and FlatEarthAnal.m

  4. How we did it… • Modified DesignPitch.m, DesignYaw.m, and DesignRoll.m to use Boiler Xpress 4th order transfer functions • Varied control gain, K, to achieve design damping ratio • Used 6th order transfer functions from DesignPitch.m, DesignYaw.m, and DesignRoll.m to determine n for design damping ratio

  5. Lifting Force: CLO=0.95 CL=4.9174 CL’=0.3333 CLq=5.3879 Side Force: CyO=0 Cy=-0.0484 CyA=0 CyR=0.0353 Cyp=-0.0056 CyR=0.7080 Control Derivative Constants • Reference Positions: • xbarac=0.3412 • xbarcg=0.3412

  6. Pitching Moment: CmO=-0.0400 Cm=-1.8448 Cm’=-0.6329 Cmq=-2.9935 Rolling Moment: Clo=0 Cl=-0.0331 ClA=0.8000 ClR=0 Clp=-0.1500 ClR=0.2467 Control Derivative Constants • Yawing Moment: • Cno=0 • Cn=0.1100 • CnA=-0.1203 • CnR=-0.1280 • Cnp=-0.1233 • CnR=-0.7214

  7. Universal Block Diagram Transfer Function input output + - Gain k

  8. 4th Order Transfer Functions Pitch: Yaw: Roll:

  9. 12th Order Transfer Functions Pitch: Yaw: Roll:

  10. Root Locus for Q(s)/E(s)

  11. Root Locus for R(s)/R(s)

  12. Root Locus for P(s)/A(s)

  13. Output from BoilerXpressLongSC.m

  14. Output from BoilerXpressLongSC.m

  15. Q(s)/E(s) from FlatEarth.m

  16. R(s)/R(s) from FlatEarth.m

  17. Time response comparison for aileron input. Flat Earth Model, Boiler Xpress 0.8 linear sim nonlinear sim 0.6 P (rad/sec) 0.4 0.2 0 0 0.5 1 1.5 2 2.5 3 3.5 4 4.5 5 time (sec) 1.5 linear sim nonlinear sim 1 phi (rad) 0.5 0 0 0.5 1 1.5 2 2.5 3 3.5 4 4.5 5 time (sec) 100 50 0 0 0.5 1 1.5 2 2.5 3 3.5 4 4.5 5 P(s)/A(s) from FlatEarth.m 200 linear sim nonlinear sim 150 Y (ft) time (sec)

  18. Pitch Stability Augmentation System • Incorporated Boiler Xpress and Cessna 182 transfer functions into DesignPitch.m for system comparison • Adjusted gains to meet following criteria • -1.3<K<1.3 •  = 0.707 • For K=0.2885, =0.707 • Damping objective met for pitch stability

  19. Pitch Stability Augmentation System • Used 6th order transfer function from DesignPitch.m to determine n for design damping ratio Pitch Root Locus

  20. Yaw Stability Augmentation System • Incorporated Boiler Xpress and Cessna 182 transfer functions into DesignYaw.m for system comparison • Adjusted gains to meet following criteria • -1.3<K<1.3 •  = 0.26 • For K=0.35, =0.261 • Damping objective met for yaw stability

  21. Yaw Stability Augmentation System • Used 6th order transfer function from DesignYaw.m to determine n for design damping ratio Yaw Root Locus

  22. Roll Stability Augmentation System • Incorporated Boiler Xpress and Cessna 182 transfer functions into DesignRoll.m for system comparison • Adjusted gains to meet following criteria • -1.3<K<1.3 • T = 0.1 • For K=0.0001, T=0.05 • Damping objective not met for roll stability

  23. Roll Stability Augmentation System • Used 6th order transfer function from DesignRoll.m to determine n for design damping ratio Roll Root Locus

  24. Results • Pitch Stability Augmentation System • K=0.2885, n=0.305 rad/sec,=0.707 • Yaw Stability Augmentation System • K=0.35, n=25 rad/sec, =0.261 • Roll Stability Augmentation System • K=0.0001, n=31 rad/sec, =0.65 T=0.05

  25. Conclusions • Stability and control derivatives found for Boiler Xpress • 4th and 12th order transfer functions determined for Boiler Xpress • Desired damping ratio met for pitch and yaw cases within gain limits; roll case did not meet design time constant • Corresponding natural frequencies were found for each case • Purpose is to achieve stable system by adding a control system

More Related