Advanced Modeling Aeronautics Team SAE Aero Design Advanced Class - - PowerPoint PPT Presentation

Advanced Modeling Aeronautics Team

SAE Aero Design Advanced Class Team 210 “Taranis”

Advanced Modeling Aeronautics Team: #210

Agenda

• Overview
• Project Planning & Management
• Requirements Derivation
• Vehicle Sizing
• Propulsion
• Trade Studies
• Configuration Selection
• Use of Materials
• Stability & Control
• Structure Analysis
• Weight Buildup
• Performance Analyses
• Systems Testing & Integration

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Advanced Modeling Aeronautics Team: #210

Overview

• Powerplant: O.S. MAX AXII 2-Stroke 0.46 in3
• Wingspan: 102.5 in
• Foam Core Composite Wing Construction
• Static Cargo Bay within Wing Spars 30.93 in3
• Modular, rapid assembly
• Short Construction Time
• OEW: 13.70 lbf

Advanced Modeling Aeronautics Team: #210

Project Planning

Design

• Objectives

Engineering

• XLFR, MatLab, Python

Manufacturing

• Carbon Fiber Layup, 3D Printing
• Wood Laser Cutting

Flight Test

• Control Surfaces
• Drop Mechanism

Cost

• Mitigation

Advanced Modeling Aeronautics Team: #210

Team Management

Engine Lead Captain Captain Fuselage Lead General Team Wings Lead General Team Empennage Lead General Team Stability & Control Electronics Lead Drop Mechanism Lead Landing Gear

General Team

Captain Visual Representation

Advanced Modeling Aeronautics Team: #210

Requirements Derivation

• Maximize Flight

Score ○ Assumptions ■ Low Accuracy ■ 8 lbf OEW ○ Payload ■ Static vs. Dynamic ■ Accuracy

• Ease of Transport
• Manufacturability
• Takeoff Distance
• Maneuverability

Advanced Modeling Aeronautics Team: #210

Vehicle Sizing

• Maximize Lift
• Power

Constraint

• Minimize Drag
• Structural

Limitations

• Effectiveness of

control surfaces

• Manufacturing

Process

Advanced Modeling Aeronautics Team: #210

Propulsion

• Reliable
• Ogawa Seisakusho

(O.S.) MAX AXII 2-Stroke

• 12x6 APC Propeller
• Static Thrust: 6.0 lbf
• 12000 RPM Static
• Dynamic thrust model

Advanced Modeling Aeronautics Team: #210

Trade Studies

Wings: Straight v. Tapered Airfoils:CH-10, Clark Y, Eppler 214, CR 1, Selig Tail: H-Tail v. Conventional v. V-Tail NACA 12, NACA 14 Landing Gear: Tricycle v. Taildragger

NACA 12 Selig 1223 Tricycle Design

Advanced Modeling Aeronautics Team: #210

Configuration Selection

Feature

Reasoning Conventional Tail

• Reliable, stable configuration

High Aspect Ratio Wing

• Superior lift to drag ratio

Rectangular Mid Wing

• Allows for internal cargo bay & contiguous spar
• Places AC above CG for lateral stability
• Simple, quickly repeatable structure

Tricycle Landing Gear

• Allows for lower drag zero-incidence roll
• Forward gear balances facilitates CG balance

Single Puller Engine

• Improved consistency & reliability over

multiple engine configuration

• Forward engine balances CG with tail

Advanced Modeling Aeronautics Team: #210

Use of Materials

Material 3K Bi-Directional Carbon Fiber/Epoxy Balsa Wood/ Basswood Red Oak Polystyrene Foam Use Fuselage, Wings, Empennage Fuselage, Empennage Firewall Wings Reasoning

• 1 Layer at 0°/90°
• Minimize weight
• Structural

improvement

• Material used

from previous

• Vacuum bag

lay-up

• Cutting/Sanding

for lightening and finishing

• Lightweight
• Easily

accessible and machinable

• Replaceable
• Strong

resistance to bending

• Good

properties in tension and compression

• High density

for CG balancing

• Large

availability from donor.

• Easily shaped

to desired shape.

• Good bending

strength

• Provide

curvature for composite lay-up

Advanced Modeling Aeronautics Team: #210

Stability & Control

8 in 6 in 7.55 in 22 in Main Wing Horizontal Stabilizer Vertical Stabilizer Aspect Ratio 6.83 3.5 2.075 Control Surface Span [in] 15 17.25 Each 21 Control Surface Chord [in] 5 4.27 4.27

Advanced Modeling Aeronautics Team: #210

Aircraft Structures & Methods

• Laser Cutting
• Airfoil Stencils/Tail Ribs/Fuselage
• Accurate and easy assembly
• Carbon Fiber Vacuum Bag Layup
• Fuselage: balsa-carbon composite
• Flat fuselage panels for simple layups
• Continuous fabric for drapability of wings
• 3D Printing
• Plastic is suitable for expected loads
• Used for Landing Gear and Fairings
• Polystyrene Foam
• Hotwire and Drill Shaping

Advanced Modeling Aeronautics Team: #210

Stress Analysis: Empennage, Fuselage, and Wing

Empennage

• Balsa v Basswood Base
• Carbon Fiber

Reinforcement against bending Fuselage

• Failure of Balsa to take

thrust from Engine

• Needed higher integrity

wood for support Wings

• Designed against high

loading and gusts with high Factor of Safety

Wind Gust Load Factor at bank angle 15o No Wind Gust ~1.0 25% Cruise Speed ~1.5 75% Cruise Speed ~3.0

Advanced Modeling Aeronautics Team: #210

Performance Verification

• Testing used to verify

thrust numbers

• Propeller Selection

based upon Dynamic Thrust

Advanced Modeling Aeronautics Team: #210

Weight Management

Predicted Weight: 10.33 lb Actual Weight: 13.70 lb

10.33

Advanced Modeling Aeronautics Team: #210

Advanced Class Flight Systems

Altimeter FPV Camera Pitot Tube Battery Drop Servo Ground Station

Advanced Modeling Aeronautics Team: #210

Questions?