The Experts below are selected from a list of 255 Experts worldwide ranked by ideXlab platform
Kunihiko Ohtake - One of the best experts on this subject based on the ideXlab platform.
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Thermal analysis of the thermal protection system for the Re-Entry Vehicle
Computer Methods in Applied Mechanics and Engineering, 1998Co-Authors: Kunihiko OhtakeAbstract:Abstract Thermal analysis methods for Re-Entry Vehicle structure are presented. At first CFD/FEM coupling thermal analysis and a joint component heat conduction analysis for Japanese hypersonic experimental Vehicle are introduced. Then, the finite element modeling problem is treated. Two methods are applied to the heat conduction simulation of fastener jointed structural component.
Samir Bennani - One of the best experts on this subject based on the ideXlab platform.
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A Linear Parameter Varying Controller for a Re-Entry Vehicle Benchmark
Advances in Aerospace Guidance Navigation and Control, 2011Co-Authors: Andres Marcos, Samir BennaniAbstract:In this article the design of a linear parameter varying controller for an atmospheric Re-Entry Vehicle benchmark is presented. The control design approach used is based on the Single Quadratic Lyapunov Function approach. The Re-Entry Vehicle used is a high-fidelity benchmark that includes full nonlinear motion, detailed aerodynamic database, nonlinear actuators, colored sensor models, realistic uncertainties and a control-surface mix logic. The latter logic fully couples the longitudinal and lateral/directional motions and together with the noise and uncertainties used result in a challenging and representative atmospheric Re-Entry benchmark. The results indicate that the LPV controller satisfies all the performance and robustness objectives and alleviates the designer task due to the automated gain-scheduled nature of the approach.
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Nonlinear Worst-Case Analysis of an LPV Controller for Approach-Phase of a Re-Entry Vehicle
AIAA Guidance Navigation and Control Conference, 2009Co-Authors: Prathyush P. Menon, Emmanuel Prempain, Ian Postlethwaite, Declan G. Bates, Samir BennaniAbstract:In this paper, a nonlinear robustness analysis of an LPV controller for the approachphase of a Re-Entry Vehicle is presented. The nonlinear longitudinal equations of motion of the NASA-HL-20 atmospheric Re-Entry Vehicle, a benchmark provided by Deimos Space as a representative of future Re-Entry Vehicles, constitute the open loop model. The analysis is carried out using the optimization-based worst-case analysis tools developed at University of Leicester for Phase I of the European Space Agency (ESA) project – “Robust LPV Gain Scheduling Techniques for Space Applications”. The tools make up an analysis framework using several optimization methods such as local gradient based algorithms, global evolutionary algorithms, dividing rectangles algorithm, hybrid local / global evolutionary algorithms and multi-objective algorithms. In this paper, the worst-case deviations from a predefined Re-Entry profile due to simultaneous variations of multiple uncertain parameters are determined by two optimization methods - hybrid differential evolution and hybrid dividing rectangles. The results demonstrate the flexibility, efficiency and reliability of the optimization-based worst-case analysis, and project it as a useful potential tool for complex controller validations in future space applications.
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WORST-CASE ANALYSIS OF FLIGHT CONTROL LAWS FOR Re-Entry VehicleS
IFAC Proceedings Volumes, 2007Co-Authors: Prathyush P. Menon, Andres Marcos, Ian Postlethwaite, Declan G. Bates, V. Fernandez, Samir BennaniAbstract:Abstract This paper reports results of a joint study between ESA, DEIMOS Space S.L. and the University of Leicester on the robustness analysis of flight control laws for future hypersonic Re-Entry Vehicles. We apply a novel hybridised version of the deterministic global optimisation algorithm, DIviding RECTangles (DIRECT), to perform worst-case analysis of a nonlinear-dynamic inversion (NDI) flight control law for a highly-detailed simulation model of a hypersonic Re-Entry Vehicle. Nonlinear clearance criteria widely used in the European aerospace industry for the clearance of flight control laws for highly manoeuvrable aircraft are developed and applied in the context of the Re-Entry Vehicle flight control problem. The proposed approach is shown to have the potential to improve significantly both the reliability and efficiency of the flight clearance process for future Re-Entry Vehicles.
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Integrated vs decoupled fault detection filter & flight control law designs for a Re-Entry Vehicle
2006 IEEE Conference on Computer Aided Control System Design 2006 IEEE International Conference on Control Applications 2006 IEEE International Sympos, 2006Co-Authors: H. Castro, Samir Bennani, Andres MarcosAbstract:An integrated design of a robust fault detection filter and control system for a Re-Entry Vehicle is presented. The integrated architecture is based on the four-block Youla parametrization which allows to better and directly trade-off filter and control design objectives in the face of disturbances and uncertainties. Hinfin -optimization techniques are used to design the integrated controller/filter system for a Re-Entry Vehicle with actuator faults in the transonic flight regime where the aerodynamics are highly uncertain. Finally the resulting integrated controller/filter properties are compared with a decoupled fault detection filter and flight control designs. The integrated design obtained successfully identifies the desired faults for the nominal and uncertain cases. Moreover, the integrated design minimizes the faults effects on the system response better than the decoupled design. Lastly, it is clearly shown that the actuator activity is directly related with the faults introduced
Erwin Mooij - One of the best experts on this subject based on the ideXlab platform.
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Passivity analysis for a winged Re-Entry Vehicle
2014Co-Authors: Erwin MooijAbstract:Application of simple adaptive control (SAC) theory to the design of guidance and control systems for winged Re-Entry Vehicles has been proven successful. To apply SAC to these non-linear and non-stationary systems, it needs to be Almost Strictly Passive (ASP), which is an extension of the Almost Strictly Positive Real (ASPR) condition for linear, time-invariant systems. To fulfill the ASP condition, the controlled, non-linear system has to be minimum-phase (i.e., the zero dynamics is stable), and there is a specific condition for the product of output and input matrix. Earlier studies indicate that even the linearised system is not ASPR. The two problems at hand are: 1) the system is non-minimum phase when flying with zero bank angle, and 2) whenever there is hybrid control, e.g., yaw control is established by combined reaction and aerodynamic control for the major part of flight, the second ASPR condition cannot be met. In this paper we look at both issues, the former related to the guidance system and ...
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Optimal Terminal-Area Strategies and Energy-Tube Concept for a Winged Re-Entry Vehicle
AIAA Guidance Navigation and Control Conference, 2009Co-Authors: S. De Ridder, Erwin MooijAbstract:A guidance algorithm for the Terminal Area of a winged Re-Entry Vehicle can use reference trajectories or predicting capabilities. In both cases, it is important to know the limits of the Vehicle capabilities and the best strategy for a ight in the vertical plane. This paper describes optimal trajectories and strategies for both a maximum-range and a maximum-dive ight. O-nominal
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Stability Analysis of an Adaptive Guidance and Control System applied to a Winged Re -entry Vehicle
AIAA Guidance Navigation and Control Conference and Exhibit, 2005Co-Authors: Erwin Mooij, Dutch Space, I. Barkana, Willow GroveAbstract:The design and analysis of a Model Reference Adaptive Guidance and Control system to control the motion of a winged re -entry Vehicle during hypersonic bank reversals is discussed. This design makes use of Simple Adaptive Control theory, which aims at tra cking the output of a reference model. The reference model is a linearized state -space representation of the non -linear re -entry Vehicle, stabilized by an output feedback controller. A stepwise approach is followed, beginning with separating the translatio nal and rotational motion. Linearized state -space systems are used to study the open -loop stability and to define sufficient conditions for application of Direct Adaptive Control theory, which are later on repeated for the non -linear, time -varying system. Subsequently, the linearized systems are applied as reference model and used to tune the adaptive gains. The design of guidance system and attitude controller is done separately, after which both systems are integrated into a combined GNC system. Non -linea r simulations, finally, show the robust performance of the integrated system.
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Re-Entry Vehicle design optimization with integrated trajectory uncertainties
AIAA CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference, 2005Co-Authors: J. Fatemi, Erwin Mooij, Dutch Space, S.p. Gurav, A. Andreykiv, F. Van KeulenAbstract:In the present paper uncertainty-based design optimization of Re-Entry Vehicles is investigated. The goal is to optimally design the Thermal Protection System (TPS) of a reentry Vehicle to minimize the thermally induced deformations mismatch between adjacent parts of the TPS as the Vehicle is heated during the Re-Entry. Uncertainties of different nature, typically originating from the Vehicle configuration and the Re-Entry trajectory are considered in this work. The design approach is based on a bounded-but-unknown uncertainty optimization technique that assumes a continuous variation of both the design parameters and the uncertainties. The results of the proposed approach are compared with those of a deterministic approach, where the design is optimized for a nominal load profile.
S. De Ridder - One of the best experts on this subject based on the ideXlab platform.
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Study on optimal Trajectories and Energy Management Capabilities of a Winged Re-Entry Vehicle during the Terminal Area
2009Co-Authors: S. De RidderAbstract:The unpowered entry of a winged Re-Entry Vehicle, such as the HORUS-2B, consists of a hypersonic atmospheric Re-Entry phase, a Terminal Area Energy Management (TAEM) phase and a approach and landing phase. The TAEM is the subject of this thesis study. During the TAEM, the Vehicle is brought to the correct interface position with the landing phase, on the extension of the centerline of the runway with the correct amount of energy and the correct heading. The most characteristic feature of the TAEM phase is the so-called Heading Alignment Cylinder (HAC). The Vehicle performs a turn around the HAC to align with the runway. During actual Re-Entry flights, flight conditions at the beginning of the terminal area will not always be nominal and several variations in entry position, energy, heading angle and flight-path angle can occur. Therefore, the main question of this thesis work is formulated as: Can the safe return of a winged Re-Entry Vehicle through the terminal area be guaranteed for a wide range of initial conditions?
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Optimal Terminal-Area Strategies and Energy-Tube Concept for a Winged Re-Entry Vehicle
AIAA Guidance Navigation and Control Conference, 2009Co-Authors: S. De Ridder, Erwin MooijAbstract:A guidance algorithm for the Terminal Area of a winged Re-Entry Vehicle can use reference trajectories or predicting capabilities. In both cases, it is important to know the limits of the Vehicle capabilities and the best strategy for a ight in the vertical plane. This paper describes optimal trajectories and strategies for both a maximum-range and a maximum-dive ight. O-nominal
Prathyush P. Menon - One of the best experts on this subject based on the ideXlab platform.
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Nonlinear Worst-Case Analysis of an LPV Controller for Approach-Phase of a Re-Entry Vehicle
AIAA Guidance Navigation and Control Conference, 2009Co-Authors: Prathyush P. Menon, Emmanuel Prempain, Ian Postlethwaite, Declan G. Bates, Samir BennaniAbstract:In this paper, a nonlinear robustness analysis of an LPV controller for the approachphase of a Re-Entry Vehicle is presented. The nonlinear longitudinal equations of motion of the NASA-HL-20 atmospheric Re-Entry Vehicle, a benchmark provided by Deimos Space as a representative of future Re-Entry Vehicles, constitute the open loop model. The analysis is carried out using the optimization-based worst-case analysis tools developed at University of Leicester for Phase I of the European Space Agency (ESA) project – “Robust LPV Gain Scheduling Techniques for Space Applications”. The tools make up an analysis framework using several optimization methods such as local gradient based algorithms, global evolutionary algorithms, dividing rectangles algorithm, hybrid local / global evolutionary algorithms and multi-objective algorithms. In this paper, the worst-case deviations from a predefined Re-Entry profile due to simultaneous variations of multiple uncertain parameters are determined by two optimization methods - hybrid differential evolution and hybrid dividing rectangles. The results demonstrate the flexibility, efficiency and reliability of the optimization-based worst-case analysis, and project it as a useful potential tool for complex controller validations in future space applications.
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WORST-CASE ANALYSIS OF FLIGHT CONTROL LAWS FOR Re-Entry VehicleS
IFAC Proceedings Volumes, 2007Co-Authors: Prathyush P. Menon, Andres Marcos, Ian Postlethwaite, Declan G. Bates, V. Fernandez, Samir BennaniAbstract:Abstract This paper reports results of a joint study between ESA, DEIMOS Space S.L. and the University of Leicester on the robustness analysis of flight control laws for future hypersonic Re-Entry Vehicles. We apply a novel hybridised version of the deterministic global optimisation algorithm, DIviding RECTangles (DIRECT), to perform worst-case analysis of a nonlinear-dynamic inversion (NDI) flight control law for a highly-detailed simulation model of a hypersonic Re-Entry Vehicle. Nonlinear clearance criteria widely used in the European aerospace industry for the clearance of flight control laws for highly manoeuvrable aircraft are developed and applied in the context of the Re-Entry Vehicle flight control problem. The proposed approach is shown to have the potential to improve significantly both the reliability and efficiency of the flight clearance process for future Re-Entry Vehicles.
