preliminary design review aem 4331 senior design cirrus canard design

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 fthttp://www.airshareselite.com/aircraft/sr22.php

Preliminary DesignDesign Estimates

Wing Area 145 square ftWingspan 35 - 36 ftMTOW 3200 ± 200 lbEmpty Weight 2000 ± 100 lbFuel Approximation +550 lb

Wing Loading ≤ 23.5 lb/ft2

Range +800 nmiAR 8.5L/D Ratio 16Rate 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