1 / 40

Sensor-Based Structural Health Monitoring and Control Group

S P A C E Structures, Propulsion, And Control Engineering C e n t e r. Sensor-Based Structural Health Monitoring and Control Group. Research Team Members: Prof Helen Boussalis (CSULA) Prof Sami F Masri (USC) Jessica Alvarenga (CSULA) Armen Derkevorkian (USC). Outline.

denise
Download Presentation

Sensor-Based Structural Health Monitoring and Control Group

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. S P A C E Structures, Propulsion, And Control Engineering C e n t e r Sensor-Based Structural Health Monitoring and Control Group Research Team Members: Prof Helen Boussalis (CSULA) Prof Sami F Masri (USC) Jessica Alvarenga (CSULA) Armen Derkevorkian (USC) NASA Grant URC NCC NNX08BA44A

  2. Outline • Background • Objective • Theory • Modeling of 2D Beam and 3D Wing • Future Work • Timeline NASA Grant URC NCC NNX08BA44A

  3. Background NASA Grant URC NCC NNX08BA44A

  4. Helios Wing • Ultra-lightweight, unmanned, solar-powered flying wing aircraft • Long wingspan and high flexibility • Experienced large deformations during flight • Wing tip deflections could reach 40ft • Midair breakup at 3000ft altitude Helios Wing In-flight breakup NASA Grant URC NCC NNX08BA44A

  5. In-flight Deformation Monitoring • Need to develop method to monitor deformations of highly flexible structures during flight • As wingtip deflections approach limitations, emergency maneuvers may be initiated • Ground-based pilots • Flight control system NASA Grant URC NCC NNX08BA44A

  6. Existing Methods of Inflight Monitoring Electro-optical flight deflection detection • Requires onboard cameras and wing mounted targets • Heavy and requires lots of equipment Strain gages • Requires a high number of sensors in order to observe higher deflection modes of these flexible structures • The more strain sensing stations are used, the heavier the load on the wing • Too heavy and impractical for most weight conscious aircraft NASA Grant URC NCC NNX08BA44A

  7. Newly Proposed Method • Fiber Optic Sensors with Fiber-Bragg Gratings • Immune to E&M/RF interference and radiation • Light weight and small (thin fibers) • Ability to multiplex 100’s of sensors onto a single fiber • Potential for embedment into structures Reflector Laser Light Loss Light Reflected Light (IR) NASA Grant URC NCC NNX08BA44A

  8. Application • Validation of fiber optic sensor measurements and real-time wing shape sensing on NASA’s Ikhana Vehicle NASA Grant URC NCC NNX08BA44A

  9. In-Flight Shape Detection Algorithms • Deflection Shape Algorithms based on strain data • Validation with classical beam theory, and finite element analysis (FEA) • Promising results, with much room for improvement NASA Grant URC NCC NNX08BA44A

  10. Structural Health Monitoring (SHM) • Objectives • System Identification • Damage Detection • Broad applications in civil, mechanical, and aerospace industries • Special importance after natural disasters (earthquakes), during key flying missions (Helios) NASA Grant URC NCC NNX08BA44A

  11. Structural Health Monitoring (SHM) • Destructive Evaluation (DE) • Physical Decomposition to locate damage • Non-Destructive Evaluation (NDE) • Based on vibration signatures (Acc, Vel, Dsp) • Enables real-time monitoring • Involves sophisticated algorithms NASA Grant URC NCC NNX08BA44A

  12. Non-Destructive Evaluation (NDE) • Parametric Techniques • Involves major assumptions about the model • Prior knowledge about the parameters • Advantages • Well-Developed techniques, such as least-square, Kalman Filter, Eigen Value Realization Algorithm (ERA) along with the Natural Excitation Technique (NExT), among others. • Track certain parameters in great detail which allows detecting changes “damages” NASA Grant URC NCC NNX08BA44A

  13. Non-Destructive Evaluation (NDE) • Non-Parametric Techniques • No knowledge about the model is required • “Black-Box” or “Unknown-Structures” approach • Applicability on linear and non-linear systems • Well-developed algorithms such the neural networks NASA Grant URC NCC NNX08BA44A

  14. Objective NASA Grant URC NCC NNX08BA44A

  15. Vision • Objectives: Develop and implement innovative methods for utilizing fiber-optic strain sensors for structural health monitoring and control applications in aerospace systems, with emphasis on using on-line aeroelastic shape estimation methods under realistic flight conditions. • Approach: Conduct analytical and experimental studies on a subset of challenging research issues to develop and evaluate a variety of modeling, monitoring and control strategies. • Applicability: Results of the research will be useful in the monitoring and control of a wide variety of current as well as future generations of aircraft and aerospace structures. NASA Grant URC NCC NNX08BA44A

  16. Preliminary Tasks Task 1: Development and validation of a NASTRAN model for a 2D beam and a 3D wing Task 2: Computational studies with NASTRAN model for shape determination from strain measurements under deterministic excitation Task 3: Computational studies with NASTRAN model for shape determination from strain measurements under stochastic aerodynamic loads Task 4: Damage detection studies based on NASTRAN model to assess sensitivity of strain measurements to damage type, severity, location, and orientation, under uncertain conditions NASA Grant URC NCC NNX08BA44A

  17. In-flight deformation shape sensing theory NASA Grant URC NCC NNX08BA44A

  18. Development of Deflection Equations NASA Grant URC NCC NNX08BA44A

  19. Classical Beam Theory • Classical Beam Differential Equation: M(x): bending moment E: Young modulus I: moment of inertia • By relating the bending moment to the associated bending strain at the top or bottom fiber: σ(x): bending stress c: half-beam depth NASA Grant URC NCC NNX08BA44A

  20. Cantilever Tubular Spar Δl : spacing between sensing stations c: half-beam depth γi: torsion strain sensing station xi: strain sensing station M: bending moment ε: bending strain θ: slope angle y: deflection NASA Grant URC NCC NNX08BA44A

  21. Bending: Slope Equations • Slope Equation from Classical Beam Theory: • Noting that at the built-in end, tan θ0=0, gives: • Final Equation θi+1 θi θi-1 NASA Grant URC NCC NNX08BA44A

  22. Bending:Deflection Equations • Deflection equation from slope equation: • Noting that at the built-in end, y0=tan θ 0=0. • Final Equation θi+1 yi+1 θi yi yi-1 θi-1 NASA Grant URC NCC NNX08BA44A

  23. 2D Beam NASA Grant URC NCC NNX08BA44A

  24. FEMAP Model 2D Beam Element • 55 Nodes • 40 Elements • Aluminum • 0.1 unit thickness • 10 units in length • 2unit deep • Deterministic point load = 60 pounds • Beam fixed in all 6 degree of freedom at root • Deformation shows wing deflection • Contour shows bending-strain measurements NASA Grant URC NCC NNX08BA44A

  25. Calculation of Strain • Case 1: Strain sensing station located in the middle of an element • Case 2: Strain sensing station located at the juncture of two elements xi e xi Deformation of an infinitesimal rectangular material element [Sanpaz 2008] i- i+ e e δi: represents the displacement measurements e: represents the finite-element span-wise length xi:the i-th sensing station NASA Grant URC NCC NNX08BA44A

  26. 2D Beam Results NASA Grant URC NCC NNX08BA44A

  27. 2D Beam Results NASA Grant URC NCC NNX08BA44A

  28. 2D Beam Results • Calculation of error: e: error a: reference measurement (FEA) ã:analyzed measurement (Case1 and 2) || . ||: norm NASA Grant URC NCC NNX08BA44A

  29. 3D Wing NASA Grant URC NCC NNX08BA44A

  30. FEMAP Wing Model • 138 Nodes • 284 Elements • 6 deterministic point loads each 250 lbs • Pressure distribution along upper and lower wing skins • Varying half-beam depth and width along span NASA Grant URC NCC NNX08BA44A

  31. 3D Wing Details NASA Grant URC NCC NNX08BA44A

  32. 3D Wing Details NASA Grant URC NCC NNX08BA44A

  33. Potential Placement of Fiber Sensors NASA Grant URC NCC NNX08BA44A

  34. Wing Deflection Contour shows deflection values in y-direction NASA Grant URC NCC NNX08BA44A

  35. Future Work NASA Grant URC NCC NNX08BA44A

  36. Future Tasks • Validation of: • Combined Bending and Torsion (CBT) Theory • Perturbation Method • Stepwise Method • Modeling artificial damage in 3D model • Error analysis and classification NASA Grant URC NCC NNX08BA44A

  37. Timeline NASA Grant URC NCC NNX08BA44A

  38. Timeline NASA Grant URC NCC NNX08BA44A

  39. References Emmons, M., Karnani, S., Trono, S., Mohanchandra, K., Richards, W., and Carman, G. 2010. Strain Measurement Validation Of Embedded Fiber Bragg Gratings. International Journal of Optomechatronics, 4(1):22-33. Ko, W. and Richards, W. 2009. Method for real-time structure shape-sensing. Ko, W., Richards, W., and Tran, V. 2007. Displacement Theories for In-Flight Deformed Shape Predictions of Aerospace Structures. Sanpaz. 2008. Deformation of an infinitesimal rectangular material element. Wikepedia, Accessed January 27, 2011. http://en.wikipedia.org/wiki/File:2D_geometric_strain.png NASA Grant URC NCC NNX08BA44A

  40. Questions? Thank You NASA Grant URC NCC NNX08BA44A

More Related