optimal control of coupled systems of odes and pdes with applications to hypersonic flight
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Optimal Control of Coupled Systems of ODEs and PDEs with Applications to Hypersonic Flight Part 1 Hans Josef Pesch University of Bayreuth, Germany Part 1: Kurt Chudej, Markus Wächter, Gottfried Sachs, Florent le Bras The 8th International Conference on Optimization: - PowerPoint PPT PresentationTRANSCRIPT
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Optimal Control of Coupled Systems of ODEs and PDEs with Applications to Hypersonic Flight
Part 1
Hans Josef Pesch
University of Bayreuth, Germany Part 1: Kurt Chudej, Markus Wchter, Gottfried Sachs, Florent le Bras
The 8th International Conference on Optimization: Techniques and Applications (ICOTA 8), Shanghai, China, Dec. 10-14, 2010
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Outline Introduction/Motivation The hypersonic trajectory optimization problem The instationary heat constraint Numerical results
The hypersonic rocket car problems Theoretical results New necessary conditions Numerical results
Conclusion
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Outline Introduction/Motivation The hypersonic trajectory optimization problem The instationary heat constraint Numerical results
The hypersonic rocket car problems Theoretical results New necessary conditions Numerical results
Conclusion
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Introduction: Supersonic Aircraft
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Introduction: Hypersonic Passenger Jets
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Introduction: Hypersonic Passenger Jets http://www.reactionengines.co.uk/lapcat_anim.htmlProject LAPCATReading Engines, UK
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Motivation: Hypersonic Passenger Jets Project LAPCATReading Engines, UK2 box constraints1 control-state constraint1 state constraintquasilinear PDEnon-linear boundary conditionscoupled with ODE
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Introduction: The German Snger II ProjectChudej: 1989; Schnepper: 1999 Collaborative Research Center, Munich: 1989 - 2003 air-breathing turbojet - ramjet / scramjet
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Outline Introduction/Motivation The hypersonic trajectory optimization problem The instationary heat constraint Numerical results The hypersonic rocket car problems Theoretical results New necessary conditions Numerical results Conclusion
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Model: Atmosphereairtemperature [K]air density [kg/m]airpressure [bar]altititude [km]Markus Wchter & Gottfried SachsMunich U of Technology, Germany
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Heat conductivityHeat capacityair temperature Model: Atmosphere
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Model: Dynamics: Forces
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Model: Dynamics: Equations of Motion instantaneous fuel consumptionfor thrustTwo-dimensional flight over a great circle of a rotational Earthinstantaneousfuel consumptionfor active cooling
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Model: Dynamics: Boundary ConditionsHouston Rome: 9163 km = 5693 mMunich Houston: 8714 km = 5414 m
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Model: The Optimal Control ProblemObjective functionConstraintsstate constr.: dynamic pressurecontrol-state constr.: load factorangle of attack : box constraints : throttle setting
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Model: Active Engine Cooling
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Model: Active Engine Coolingcontrol-state constraintfuel is reused for thrustinstantaneous fuel consumptionfor coolinginstantaneous fuel consumptionfor thrust
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Numerical Results: State Variableswithwithoutactive coolingvelocity [m/s]altitude [10,000 m]mass [100,000 kg]path length [1,000 km][s][s][s][s]Markus Wchter, Kurt ChudejFlorent Le Bras
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Numerical Results: Control Variablesangle of attack [deg]throttle setting[s][s]
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Outline Introduction/Motivation The hypersonic trajectory optimization problem The instationary heat constraint Numerical results The hypersonic rocket car problems Theoretical results New necessary conditions Numerical results Conclusion Appendix: more applications
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Model: Instationary Heat Constraint: Thermal Protection System
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Model: Instationary Heat Constraint: Equationsquasi-linear parabolic initial-boundary value problemwith nonlinear boundary conditions
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Model: Instationary Heat Constraint: Boundary Conditions (1)radiationconvectionconvectionradiation
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Model: Instationary Heat Constraint: Boundary Conditions (2)in case ofinterior layersmultipointboundary conditionsair temperature after shockto be determined iteratively
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Model: Instationary Heat Constraint: State ConstraintODE-PDE state-constrained optimal control problemPDE: quasilinear parabolic with nonlinear bound. conds.
CONTROL: boundary controls indirectly via ODE states and controls
CONSTRAINT: state constraintState-constraint for the temperature:
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Model: Instationary Heat Constraint: State ConstraintODE-PDE state-constrained optimal control problemState-constraint for the temperature:
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Outline Introduction/Motivation The hypersonic trajectory optimization problem The instationary heat constraint Numerical results The hypersonic rocket car problems Theoretical results New necessary conditions Numerical results Conclusion
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Numerical Method: Semi-Discretization in SpaceconvectionradiationconductionFinite Volume Method: locally and globally conservative second order convergent
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Numerical Method: Semi-Discretization in Space
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Numerical Method: Semi-Discretization in Space1D case
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Numerical Method: Method of Linesb.c. towards airb.c. towards interiorlarge scale multiply constrained ODE optimal control problemcoupled with ODE.DIRCOL (O. v. Stryk) with SNOPT (P. Gill)alternatively: NUDOCCCS (C. Bskens) IPOPT (A. Wchter) with AMPL WORHP (Bskens, Gerdts)
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Numerical Results: Stagnation Point (1D)
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Numerical Results: Stagnation Point: States, Heat Loadsvelocity [m/s]altitude [10,000 m]flight path angle [deg]temperature [K]temperature [K]temperature [K]1st layer2nd layer3rd layerlimittemperature1000 Kon a boundary arc
order concept?[s][s]
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Numerical Results: Stagnation Point: Heat Load vs Fuel+ 1 %- 10 %
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Numerical Results: Lower Surface (near Engine) (2D)stagnation point (1300C)upper surface (600C)lower surface (700C)engine (1350C)leading edge (1200C)
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Numerical Results: in Front of Engine (2D)1st layer2nd layerdue to restrictionof time intervalstate constraintnot activeinfluence of tank
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Numerical Results: close to tank (2D)state constraintnot activedue to restrictionof time interval
Tupolew: Absturz der 4. Maschine in Le Bourget 19731975: Frachtflge zwischen Moskau und Almaty, Kasachstan1977: Passagierflge, 82 Rubel = *monatl. Durchschnittsverdienst der UdSSRLAPCAT: Long Term Advanced Propulsion Concepts and Technologies