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Preliminary Design Review AEM 4331 Senior Design Cirrus Canard Design.pptx

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					           Preliminary Design Review
                                 AEM 4331 Senior Design
                                   Cirrus Canard Design

Christopher Schumacher (Team Lead)      October 28, 2011
Brian Douglas
Christopher Erickson
Brad Lester
Nathan Love
Patrick Mischke
Traci Moe
Vince Zander
Overview
 Purpose of Design Project and Requirements
 Preliminary Design
 Deliverables
   Areas of Analysis
   B+ vs. A Work Qualifications
 Gantt Chart
 Summary
Purpose of Design & Requirements
 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                                       Secondary
   Roll Takeoff Distance: 1028 ft.            High Speed Cruise
   Climb Gradient: 864 ft/ nmi                Extended Range: 700 nmi
   Roll Landing Distance: 1141 ft.            Increased Payload: 468 lb with fuel for
   Minimum Full Fuel Payload : 180 lb          this mission
   Similar Loading Flexibility to the SR22
    within Approved CG Limits
SR22
                                                     Design Specifications
Wing Area                          144.9 square ft
Wingspan                           38.5 ft
MTOW                               3400 lb
Empty Weight                       2250 lb
Full Fuel Load                     664 lb
Maximum Range                      +1000 nmi
Rate of Climb                      1400 ft/min
                                                       www.modelairplanenews.com MediaNewsCirrus-SR22.jpg
Takeoff Distance                   1020 ft
Landing Ground Roll                1014 ft
Aircraft Length                    26 ft
http://www.airshareselite.com/aircraft/sr22.php
Preliminary Design
                                     Design Estimates
Wing Area            145 square ft
Wingspan             35 - 36 ft
MTOW                 3200 ± 200 lb
Empty Weight         2000 ± 100 lb
Fuel Approximation   +550 lb

Wing Loading         ≤ 23.5 lb/ft2
Range                +800 nmi
AR                   8.5
L/D Ratio            16
Rate of climb        +1304 ft/min
Deliverable Design Groups
 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
Integrated Aircraft Design Model
 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
Deliverables: Aircraft Design
                A Work
                B+ Work
                  Full exterior CAD design of the
                   optimized design
                   original design
Landing Gear Design Process
 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
Deliverables: Landing Gear
                A Work
                B+ Work
                   FEA of a landing gear system
                    Design one landing gear
                   structure
                    Tire Selection
                
                   Suggestions for improvement
                    Material Selection
                
                   Show how Selection
                    Geometry it integrates to the
                   entire Analysis
                    Stress design
                
                   Analyze interactions with rest
                    CAD Model of Landing Gear
                    of aircraft
Wing Configuration Process
 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
Deliverables: Wing Configuration
                 A Work
                 B+ Work
                   Fully analyze for :
                  Design a sectioned wing
                       Center of Pressure
                       Moment Coefficient
                       Lift Curve Slope
                       Span Wise Geometry
                        (including wash out analysis)
Controls and Loading Design Process
 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.
Deliverables: Controls and Loading
                                       A Work
                                       B+ Work
 Calculate Weights and Moments         Show Loading and Stability
 Control Surface Loading Limits         Capabilities for Optimized
 Show Loading and Stability             Aircraft Design
  Capabilities for Initial Aircraft     Compare Optimized Aircraft
  Design                                 Design with SR22 Capabilities
 Compare Aircraft Capabilities with
  FAA Regulations
 Compare Initial Aircraft with SR22
  Capabilities
Canard Configuration Process
 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
Deliverables: Canard Configuration
                 A Work
                 B+ Work
                    Optimize configuration for
                     Design a Canard
                    integrated aircraft between
                     Analyze interactions
                    Fully Analyze:
                     the canard and wing
                      Center of Pressure
                     Calculate forces and moments
                       Lift canard
                     on the Curve Slope
                      Coefficient of Lift
Gantt Chart
Summary
 Purpose of Design Project and Requirements
 Preliminary Design
 Deliverables
   Areas of Analysis
   B+ vs. A Work Qualifications
 Gantt Chart
Questions

				
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