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Unformatted text preview: Structural Health Monitoring Demonstrator (SHMD) Group Members: Joshua Siler Stas Yerusky Joe Welch David Harsanyi Seth Limp Natasha Wall Brian Hutto Bryan Engle Paul Reiber Mission Overview
Mission Overview SHMD usage – Mechanical Engineering and Aviation Technology collaborative research project – Test in flight electronic structural health monitoring devices for unmanned aerial vehicles (UAV) Secondary missions – Forest air sampling
– Law enforcement aerial surveillance Aircraft Design Specs All metal aircraft construction powered by a O100 4 cylinder, 2 stroke engine
– Engine hp
Landing speed Desired empty weight
Pay load 72hp at 4100 RPM
100 pounds First Spiral Test Overview
First Spiral Test Overview Physically build and model various sheet metal beams – Ibeam
– Two bend
– Open channel Stress test using – CATIA FEA
– Physically mounted beam and piston Materials
Materials All Aluminum Construction – IBEAM
– Web .032 2024T3 Angles .063 6061T6
Cap Strips .032 2024T3
Stiffeners .032 2024 T3 – AD47055 Universal Head Rivets
– AD47044 Universal Head Rivets Construction
Construction 3 Foot IBeam – 4 Hours For Completion
– 118 Rivets Total
– End Weight of 2.58 Lbs. 3 Flanged Lightning Holes were added to help reduce weight Found to be a insufficient weight loss method due to height of the web Testing
Testing In our circumstances the cantilever testing apparatus is being used to load a structural representation of our wing spars, as if loaded by the lifting force our wings would present. TEST STAND
TEST STAND Loads on the Spar
Loads on the Spar Shear forces Twisting/Bending – The upwards loading of the spar translates into compressive shear on the upper surface (upper spar caps) and a tensile stress on the lower spar caps. The moment is the highest at the spar root (connection point to the test stand) and lowest at the spar tip. Over all specifications and Over all specifications and Predicted Failures The constructed I & U beams used extruded 90deg. Spar caps of .063 and .125 respectively,
All test spars were 3ft long and 4inches high
Weights and predicted Failure:
– I = 1335g failing @ 400 lbs
U = 1171g failing @ 850 lbs
C = 723g failing @ 430 lbs Actual Failure in pounds
Actual Failure in pounds Constructed I beam = 981 lbs Constructed U beam = 740 lbs Bent C channel = 250 lbs CCHANNEL
CCHANNEL Prediction Calculations
Prediction Calculations Cantilever Beam Bending
Tested for estimated failures
Major Failure Mode Bending Compression
Fcy typical = 36 ksi. to 40 ksi.
Equation to predict failure: I P = load, I is Inertia, x is the distance to the load from the root and y is the max distance from the Neutral Axis of the beam. Hand Calculation First Beam
Hand Calculation First Beam Ibeam style design
Failure: compression 1000 lbs.
Actual: compression/torsion 990 lbs. Hand Calculation Second Hand Calculation Second Beam Two bend style design
Failure: compression 417 lbs.
Actual: compression/torsion 390 lbs. Hand Calculation Third Beam
Hand Calculation Third Beam Open channel style design
Failure: compression 823 lbs.
Actual: compression/torsion ??? lbs. CATIA FEA Test First Beam
CATIA FEA Test First Beam Failure Point Ibeam style design
Failure: compression 1100 lbs
Web failure CATIA Calculation Second Beam
CATIA Calculation Second Beam Failure Point Two bend style design
Failure: compression 450 lbs
Cchannel structure failed CATIA Calculation Third Beam
CATIA Calculation Third Beam Failure Point Open channel style design
Failure: compression 300 lbs
Web failure Design And Future Spiral
Design And Future Spiral Conceptual design – Airplane design
– Airfoil design Future Spiral – Choosing an airfoil
– Wind tunnel testing Conceptual Wing Design
Conceptual Wing Design 24x2ft box wing design Straight or swept wing Tapered wing/ Winglets Cruise speed130 MPH Landing speed 50 MPH Future Spiral
Future Spiral NACA airfoil that fits parameters – Is it what we need?
– Can we build it? Foam wing section Wind tunnel testing – Velocity profile
– Stall testing ...
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This note was uploaded on 01/15/2012 for the course AAE 490 taught by Professor Andrisani during the Fall '09 term at Purdue University-West Lafayette.
- Fall '09