Transcript 111009_Preliminary_Design_Review

Christopher Schumacher (Team Lead)
Brian Douglas
Christopher Erickson
Brad Lester
Nathan Love
Patrick Mischke
Traci Moe
Vince Zander
October 28, 2011
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
this mission
 Minimum Full Fuel Payload : 180 lb
 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
Takeoff Distance
1020 ft
Landing Ground Roll
1014 ft
Aircraft Length
26 ft
http://www.airshareselite.com/aircraft/sr22.php
www.modelairplanenews.com MediaNewsCirrus-SR22.jpg
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
B+ Work
A Work
 Full exterior CAD design of the
 Full exterior CAD design of the
original design
optimized 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
B+ Work
A Work
 Design a landing gear system
 FEA of one landing gear
 Tire Selection
structure
 Suggestions for improvement
 Show how it integrates to the
entire design
 Analyze interactions with rest
of aircraft
 Material Selection
 Geometry Selection
 Stress Analysis
 CAD Model of Landing Gear
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
B+ Work
A Work
 Design a sectioned wing
 Fully analyze for :
 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
B+ Work
A Work
 Calculate Weights and Moments
 Show Loading and Stability
 Control Surface Loading Limits
Capabilities for Optimized
Aircraft Design
 Compare Optimized Aircraft
Design with SR22 Capabilities
 Show Loading and Stability
Capabilities for Initial Aircraft
Design
 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
B+ Work
A Work
 Design a Canard
 Optimize configuration for
 Analyze interactions between
integrated aircraft
 Fully Analyze:
the canard and wing
 Calculate forces and moments
on the canard
 Center of Pressure
 Lift 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