COURSE: Advanced Aeroelasticity
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1 SESSION WEEK COURSE: Advanced Aeroelasticity MASTER: Aerospace Engineering YEAR: 1st TERM: 2nd La asignatura tiene 28 sesiones que se distribuyen a lo largo de 14 semanas. Los laboratorios pueden situarse en cualquiera de ellas. Semanalmente el alumnos tendrá dos sesiones, excepto en un caso que serán tres 1 1 6F DESCRIPTION WEEKLY PLANNING Advanced Aeroelasticity. Getting Started. Course presentation Aeroelasticity as a multidisciplinary task History of aeroelasticity Revisiting Wing Divergence Revisiting Control reversal Revisiting flutter Revisiting dynamic landing Revisiting gust and turbulence response Revisiting buffet Root Cause Analysis (RCA): failed equipment. Prepare a table of possible GROUPS (mark ) LECTU RES SEMIN ARS SPECI AL ROOM FOR SESSIO N (Comp uter class room, audiovisual class room) Indic ate YES/ NO If the sessi on need s 2 teac hers WEEKLY PROGRAMMING FOR STUDENT DESCRIPTION CLASS HOURS HOME WORK HOURS (Max. 7h week) 1,6 2 Página 1 de 6
2 F 3 20F causes and the way to verify if this is the right cause. Present to the student a RCA fish-bone diagram and disregard some of the options like manufacturing quality etc. Environmental Vibration RCA failed equipment analysis brainstorming. Causes of the environmental vibration in an aircraft. Differential Diagnosis. Measuring environmental vibration. Revisiting DSP. Aliasing, leakage, In lack of measurements: MIL-STD-810 & RTCA-DO-160 Establishing Requirements for Environmental Vibration Qualification Tracking equipment qualification test 1 dof vibration equations Engineering with only 1 dof: isolators Root Cause Analysis (RCA): EVIS failure Powerplant Dynamics RCA EVIS failure brainstorming Powerplant dynamics issues. Differential diagnosis. Sudden engine stoppage Windmilling Propeller dynamics. Propeller massbalance Propeller blade dynamics Root Cause Analysis (RCA): Blade rupture in a C-295 Portuguese aircraft F Impacts RCA propeller rupture brainstorming Causes of impacts in aircraft design. Differential diagnosis. Impacts on aircraft caused by external impactor Bird strike Ice impacts Stones, runway debris Impacts of the aircraft Crashworthiness WUL Ditching Ballistic limit. Some analytical formulas 1 dof vibration equation sensitivity of a response to t Root Cause Analysis (RCA): DASS flare ignition sequence. Página 2 de 6
3 5 5 6M Getting started with MSC.NASTRAN RCA flare ignition sequence brainstorming Introduction to FEM & MSC.NASTRAN GRIDS. B.C. CELAS elements. OUTPUT request 2 dof system. Coupling between dofs Root Cause Analysis (RCA) Perform Homework RCA M 7 20M Normal Modes RCA brainstorming Normal modes in an aircraft. Differential diagnosis. The very basic normal modes Wing bending mode 2D plunge mode Wing torsion mode 2D pitch mode Aileron rotation sensitivity to actuator stiffness Mode shape identification. Brainstorming. Identification of bending modes (lifting surfaces; fuselages) Identification of torsion modes (lifting surfaces; fuselages) Identification of control surface rotation modes Normal modes. What for? Brainstorming. Introducing Generic Transport Aircraft model (NASTRAN format) Model geometry: grid points Model connectivity: BAR elements Model properties: PBAR elements. MAT elements. Mass model properties: CONM2 GTA normal modes Homework: starting from the complete aircraft dynamic model derive half symmetric and half antisymmetric model. Perform Homework: derive half (S) and half(a) model starting from a complete aircraft model. Partial Exam 1 Study Partial Exam 1 1,6 7 Página 3 de 6
4 M 9 10A 10 17A 3D unsteady aerodynamics: DLM RCA brainstorming Revisiting 2D unsteady aerodynamics (Wagner, Küssner, Theodosen) Revisiting 3D unsteady aerodynamics (B. Rodden and the Doublet Lattice Method DLM) Model geometry: CAERO Model properties: PAERO Interpolation: SPLINES GTA unsteady aerodynamic model Static Aeroelasticity. Trim Solution. Control Surface Effectiveness. Relevance of the static aeroelastic problem. Airworthiness regulations on static aeroelasticity The very basic normal modes Wing bending mode 2D plunge mode Wing torsion mode 2D pitch mode Aileron rotation sensitivity to actuator stiffness Relevance of Divergence Briefing on 2D divergence analytical solution Relevance of Control surface effectiveness Briefing on 2D control surface effectiveness Brainstorming on what is needed to solve the static aeroelastic problem using the FE technique. GTA Trim solution (NASTRAN SOL 144) Spanwise evolution of vertical deformation and twist GTA Divergence solution GTA Aileron effectiveness Homework: determine elevator effectiveness Flutter Relevance of flutter. Airworthiness regulations on flutter Briefing on flutter solver mathematics Brainstorming on what is needed to solve the flutter problem using the FE technique. GTA Flutter solution (NASTRAN SOL 145) GTA V-g plot Homework: determine aileron massbalance to prevent flutter Prepare Partial1 exam. Perform Homework: determination of elevator effectiveness. determination of aileron massbalance to prevent flutter. Página 4 de 6
5 A 12 8M Dynamic Landing Relevance of dynamic landing Airworthiness regulations on dynamic landing Briefing on dynamic landing solver mathematics Brainstorming on what is needed to solve the dynamic landing problem using the FE technique. GTA dynamic landing solution (NASTRAN SOL 145) 1D envelopes of bending, shear and torque due to dynamic landing Homework: determine and plot wing root 2D envelopes Discrete Tuned Gust (DTG) Relevance of DTG analysis Airworthiness regulations on DTG Briefing on DTG solver mathematics Brainstorming on what is needed to solve the DTG problem using the FE technique. GTA DTG solution (NASTRAN SOL 146) 1D envelopes of bending, shear and torque due to DTG Homework: determine wing root 2D envelopes of DTG and compare with Dynamic landing determine and plot wing root 2D envelopes. determine wing root 2D envelopes of DTG and compare with Dynamic landing M Continuous Turbulence (CT) Relevance of CT analysis Airworthiness regulations on CT Briefing on CT solver mathematics Brainstorming on what is needed to solve the CT problem using the FE technique. GTA CT solution (NASTRAN SOL 146) 1D envelopes of bending, shear and torque due to DTG Homework: determine wing root 2D envelopes of CT (equal probability ellipses) and compare with DTG & Dynamic Landing about the lecture determine wing root 2D envelopes of CT (equal probability ellipses) and compare with DTG & Dynamic Landing M Partial Exam 2 Study Partial Exam 2. 1, Final Exam: 1-Jun-2014 [16:00 20:00] 1,6 Subtotal Total 1 (Hours of class plus student homework hours between weeks 1-14) 73 Página 5 de 6
6 15 Tutorials, handing in, etc 0,5 0, Assessment 0,5 0,5 Subtotal Total 2 (Hours of class plus student homework hours between weeks 15-18) 2 TOTAL (Total 1 + Total 2. Maximum 90 hours) 75 Página 6 de 6
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