october 28, 2011 christopher schumacher (team lead) brian douglas christopher erickson brad lester...
TRANSCRIPT
Preliminary Design Review AEM 4331 Senior Design
Cirrus Canard Design
October 28, 2011Christopher Schumacher (Team Lead)Brian DouglasChristopher EricksonBrad LesterNathan LovePatrick MischkeTraci MoeVince Zander
OverviewPurpose of Design Project and RequirementsPreliminary DesignDeliverables
Areas of AnalysisB+ vs. A Work Qualifications
Gantt ChartSummary
Purpose of Design & Requirements
Primary Secondary 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
High Speed Cruise Extended Range: 700 nmi Increased Payload: 468 lb with fuel for
this mission
Design a canard aircraft that is comparable to the SR22 in performanceConduct in-depth analysis on 5 areas of the aircraftUse the analysis to evaluate the preliminary aircraft design
SR22Design Specifications
www.modelairplanenews.com MediaNewsCirrus-SR22.jpg
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
Takeoff Distance 1020 ft
Landing Ground Roll 1014 ft
Aircraft Length 26 ft
http://www.airshareselite.com/aircraft/sr22.php
Preliminary DesignDesign 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 GroupsIntegrated Aircraft Design ModelLanding Gear DesignWing Configuration DesignControl Surface and Loading Stability DesignCanard Configuration Design
Grades will be based on the depth of research and analysis and not dependent on meeting the requirements
Integrated Aircraft Design ModelUsing values obtained through initial sizing, construct a
CAD modelGather design specifications from individual groups for
specific component designUse these specifications to develop an integrated model
of the final aircraft
Deliverables: Aircraft DesignB+ Work A WorkFull exterior CAD design of the
original designFull exterior CAD design of the
optimized design
Landing Gear Design ProcessStability Analysis based on CG and Mounting LocationsDetermine Loading CasesTire SelectionStroke Calculations for Landing Gear DampingInitial Size Estimates and Stress AnalysisModelingFinite Element Analysis
Deliverables: Landing GearB+ Work A WorkDesign a landing gear systemTire SelectionMaterial SelectionGeometry SelectionStress AnalysisCAD Model of Landing Gear
FEA of one landing gear structure
Suggestions for improvementShow how it integrates to the
entire designAnalyze interactions with rest
of aircraft
Wing Configuration ProcessSelect a Main Wing Airfoil and Design PlanformDetermine All Relevant Aerodynamic CoefficientsAnalyze Alterations and Customize Airfoil Shape and Size
for Performance OptimizationCustomized Sectioned Wing for Improved Stall
Performance
whycirrus.com/images/wing.jpg
Deliverables: Wing ConfigurationB+ Work A WorkDesign a sectioned wing Fully analyze for :
Center of PressureMoment Coefficient Lift Curve SlopeSpan Wise Geometry
(including wash out analysis)
Controls and Loading Design ProcessMain 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 LoadingB+ Work A WorkCalculate Weights and MomentsControl Surface Loading LimitsShow Loading and Stability
Capabilities for Initial Aircraft Design
Compare Aircraft Capabilities with FAA Regulations
Compare Initial Aircraft with SR22 Capabilities
Show Loading and Stability Capabilities for Optimized Aircraft Design
Compare Optimized Aircraft Design with SR22 Capabilities
Canard Configuration ProcessDetermine relationship
between canard and other aspects of aircraftManipulate canard sizing
to our benefitAnalyze flow interactions
between the canard and the main wing
www.manchesteruniversitypress.co.uk/uploads/docs/s2_10.pdf
Deliverables: Canard ConfigurationB+ Work A WorkDesign a CanardAnalyze interactions between
the canard and wing Calculate forces and moments
on the canard
Optimize configuration for integrated aircraft
Fully Analyze:Center of PressureLift Curve SlopeCoefficient of Lift
Gantt Chart
SummaryPurpose of Design Project and RequirementsPreliminary DesignDeliverables
Areas of AnalysisB+ vs. A Work Qualifications
Gantt Chart
Questions