Christopher Schumacher (Team Lead)
Brian Douglas
Christopher Erickson
Brad Lester
Nathan Love
Patrick Mischke
Traci Moe
Vince Zander
October 28, 2011

 Purpose of Design Project and Requirements
 Preliminary Design
 Deliverables
 Areas of Analysis
 B+ vs. A Work Qualifications
 Gantt Chart
 Summary

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Design a canard aircraft that is comparable to the SR22 in performance
Conduct in-depth analysis on 5 areas of the aircraft
Use the analysis to evaluate the preliminary aircraft design
Primary
 Roll Takeoff Distance: 1028 ft.
 Climb Gradient: 864 ft/ nmi
 Roll Landing Distance: 1141 ft.
 Minimum Full Fuel Payload : 180 lb
 Similar Loading Flexibility to the SR22 within Approved CG Limits
Secondary
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High Speed Cruise
Extended Range: 700 nmi
Increased Payload: 468 lb with fuel for this mission

Design Specifications
Wing Area 144.9 square ft
Wingspan 38.5 ft
MTOW 3400 lb
Empty Weight
Full Fuel Load
Maximum Range
2250 lb
664 lb
+1000 nmi
Rate of Climb
Takeoff Distance
1400 ft/min
1020 ft
Landing Ground Roll 1014 ft
Aircraft Length 26 ft http://www.airshareselite.com/aircraft/sr22.php
www.modelairplanenews.com MediaNewsCirrus-SR22.jpg

Design Estimates
Wing Area
Wingspan
MTOW
Empty Weight
Fuel Approximation
145 square ft
35 - 36 ft
3200 ± 200 lb
2000 ± 100 lb
+550 lb
Wing Loading
Range
AR
L/D Ratio
Rate of climb
≤ 23.5 lb/ft 2
+800 nmi
8.5
16
+1304 ft/min

 Integrated Aircraft Design Model
 Landing Gear Design
 Wing Configuration Design
 Control Surface and Loading Stability Design
 Canard Configuration Design
Grades will be based on the depth of research and analysis and not dependent on meeting the requirements

 Using values obtained through initial sizing, construct a
CAD model
 Gather design specifications from individual groups for specific component design
 Use these specifications to develop an integrated model of the final aircraft

B+ Work
 Full exterior CAD design of the original design
A Work
 Full exterior CAD design of the optimized design

 Stability Analysis based on CG and Mounting Locations
 Determine Loading Cases
 Tire Selection
 Stroke Calculations for Landing Gear Damping
 Initial Size Estimates and Stress Analysis
 Modeling
 Finite Element Analysis

B+ Work
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Design a landing gear system
Tire Selection
Material Selection
Geometry Selection
Stress Analysis
CAD Model of Landing Gear
A Work

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
FEA of one landing gear structure
Suggestions for improvement

Show how it integrates to the entire design
Analyze interactions with rest of aircraft

 Select a Main Wing Airfoil and Design Planform
 Determine All Relevant Aerodynamic Coefficients
 Analyze Alterations and Customize Airfoil Shape and Size for Performance Optimization
 Customized Sectioned Wing for Improved Stall
Performance whycirrus.com/images/wing.jpg

B+ Work
 Design a sectioned wing
A Work
 Fully analyze for :
 Center of Pressure
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Moment Coefficient
Lift Curve Slope
Span Wise Geometry
(including wash out analysis)

 Main goal is developing the process for analyzing weight loading and stability capabilities.
 Using weights, coefficients of lift, distances, and equations from individual groups to arrange the aircraft design for project requirements.
 Develop Matlab coding and use ‘ball and stick’ moment and force approximations to conduct analysis.

B+ Work

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Calculate Weights and Moments
Control Surface Loading Limits
Show Loading and Stability
Capabilities for Initial Aircraft
Design
Compare Aircraft Capabilities with
FAA Regulations
Compare Initial Aircraft with SR22
Capabilities
A Work


Show Loading and Stability
Capabilities for Optimized
Aircraft Design
Compare Optimized Aircraft
Design with SR22 Capabilities

 Determine relationship between canard and other aspects of aircraft
 Manipulate canard sizing to our benefit
 Analyze flow interactions between the canard and the main wing www.manchesteruniversitypress.co.uk/uploads/docs/s2_10.pdf

B+ Work

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Design a Canard
Analyze interactions between the canard and wing
 Calculate forces and moments on the canard
A Work


Optimize configuration for integrated aircraft
Fully Analyze:
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Center of Pressure
Lift Curve Slope
Coefficient of Lift

 Purpose of Design Project and Requirements
 Preliminary Design
 Deliverables
 Areas of Analysis
 B+ vs. A Work Qualifications
 Gantt Chart