Dynamics Controls PDR 2 Team Canard October 19
Dynamics & Controls PDR 2 • Team “Canard” • October 19, 2006 Team 1: Dane Batema Drew Capps Kyle Ryan John Tapee AAE 451 Team 1 “Canard” Benoit Blier Patricia Roman Audrey Serra Carlos Vergara
Overview – Stability • Longitudinal Stability – Center of Gravity Location – Tail / Elevator Sizing – Trim Diagram / Desired Static Margin Overview from Previous Presentation • Lateral-Directional Stability – Vertical Tail Sizing with X-Plot – Rudder Size / Dihedral Angle – Ailerons Sizing & Location • Aircraft Transfer Functions – Pitch Rate to Elevator – Roll Rate to Aileron – Yaw Rate to Rudder AAE 451 Team 1 2
Longitudinal Stability… AAE 451 Team 1 3
Longitudinal Stability – Location of CG As initial assumption MATLAB Code used to optimize position of CG Initial assumption proved to work well Static Margin at desired location is: Chosen CG Location: Location of Forward CG: AAE 451 Team 1 4
Longitudinal Stability – Horizontal Tail Sizing Tail Sized using Class I Method (X-Plot) • Initial Tail Size: • Size @10% Static margin • Size @18% Static margin x 2 initial size!!. . Increase of Drag • Tail size set up @ 15% margin AAE 451 Team 1 5
Longitudinal Stability – Elevator Sizing Elevator sized using Historical Data Our Tail volume ratio is: With Surface Ratio of: Flap Efficiency Factor: AAE 451 Team 1 6
Longitudinal Stability – Trim Diagram AAE 451 Team 1 7
Lateral Stability – Directional Control • Vertical Tail Sizing Maximum Yaw Moment Coefficient Best Vertical Tail Area Range of 1% difference from Minimum Side Force Coefficient AAE 451 Team 1 8
Lateral Stability – Directional Control • Rudder Sizing Wing Area Historical Data of Homebuilt Aircraft Vertical Tail Area Rudder Area found by using the corresponding average ratio AAE 451 Team 1 Rudder Area 9
Lateral Stability – Lateral Control The Weathercock Stability The Side-Force Coefficient: Required Rudder Deflection angle to trim at a given sidewash angle The Yawning Moment Coefficient: The Yawning Moment due to Rudder Deflection AAE 451 Team 1 10
Dynamic Stability… AAE 451 Team 1 11
Aircraft Systems Transfer Functions Pitch Rate To Elevator AAE 451 Team 1 12
Aircraft Systems Transfer Functions Yaw Rate To Rudder AAE 451 Team 1 13
Aircraft Systems Transfer Functions Roll Rate To Aileron AAE 451 Team 1 14
Compensated System Gain: -0. 412 Dutch Roll: 0. 96 AAE 451 Team 1 15
Control System Root Locus General Block Diagram + Aircraft Servo - Gyro AAE 451 Team 1 16
Rate Gyro Procedure for setting the rate gyro: 1. Static Test -Dial in the gain -Perturb the aircraft -Make sure the rudder deflects to counter the yaw 2. Flight Test -Select one person to be the gain setter -Test the gain in flight -Insure safe recovery altitude AAE 451 Team 1 17
Questions? . . . Comments? . . . Concerns? . . . Thank you!!!! AAE 451 Team 1 18
- Slides: 18