The Experts below are selected from a list of 318 Experts worldwide ranked by ideXlab platform
Yuri B Shtessel - One of the best experts on this subject based on the ideXlab platform.
-
Launch Vehicle attitude control using sliding mode control and observation techniques
Journal of The Franklin Institute-engineering and Applied Mathematics, 2012Co-Authors: James E Stott, Yuri B ShtesselAbstract:In determining flight controls for Launch Vehicle systems, several uncertain factors must be taken into account, including a variety of payloads, a wide range of flight conditions and different mission profiles, wind disturbances and plant uncertainties. Crewed Vehicles must adhere to human rating requirements, which limit the angular rates. Sliding mode control algorithms that are inherently robust to external disturbances and plant uncertainties are very good candidates for improving the robustness and accuracy of the flight control systems. Recently emerging Higher Order Sliding Mode (HOSM) control is even more powerful than the classical Sliding Mode Controls (SMC), including the capability to handle systems with arbitrary relative degree. This paper proposes sliding mode Launch Vehicle flight controls using classical SMC driven by the sliding mode disturbance observer (SMDO) and higher-order multiple and single loop designs. A case study on the SLV-X Launch Vehicle studied under a joint DARPA/Air Force program called the Force Application and Launch from CONtinental United States (FALCON) program is shown. The intensive simulations demonstrate efficacy of the proposed HOSM and SMC-SMDO control algorithms for Launch Vehicle attitude control.
James E Stott - One of the best experts on this subject based on the ideXlab platform.
-
Launch Vehicle attitude control using sliding mode control and observation techniques
Journal of The Franklin Institute-engineering and Applied Mathematics, 2012Co-Authors: James E Stott, Yuri B ShtesselAbstract:In determining flight controls for Launch Vehicle systems, several uncertain factors must be taken into account, including a variety of payloads, a wide range of flight conditions and different mission profiles, wind disturbances and plant uncertainties. Crewed Vehicles must adhere to human rating requirements, which limit the angular rates. Sliding mode control algorithms that are inherently robust to external disturbances and plant uncertainties are very good candidates for improving the robustness and accuracy of the flight control systems. Recently emerging Higher Order Sliding Mode (HOSM) control is even more powerful than the classical Sliding Mode Controls (SMC), including the capability to handle systems with arbitrary relative degree. This paper proposes sliding mode Launch Vehicle flight controls using classical SMC driven by the sliding mode disturbance observer (SMDO) and higher-order multiple and single loop designs. A case study on the SLV-X Launch Vehicle studied under a joint DARPA/Air Force program called the Force Application and Launch from CONtinental United States (FALCON) program is shown. The intensive simulations demonstrate efficacy of the proposed HOSM and SMC-SMDO control algorithms for Launch Vehicle attitude control.
Sophie Missonnier - One of the best experts on this subject based on the ideXlab platform.
-
multidisciplinary system optimisation on the design of cost effective space Launch Vehicle
World Congress of Structural and Multidisciplinary Optimisation, 2017Co-Authors: Cedric Dupont, Andrea Tromba, Sophie MissonnierAbstract:This paper presents the methodology and the optimization strategy applied by Bertin Technologies for over 10 years to perform space Launch Vehicle design and implemented by using the property software platform HADES V15.0. The problem formulation consists in finding the best Launch Vehicle concept i.e. the one maximising performances (payload mass on final orbit) and minimising Launch cost while satisfying technical, mission and architecture constraints. The strategy is based on a Multidisciplinary Design Feasible (MDF) approach coupled with the use of Genetic Algorithms (GA) for global optimization, and Gradient-Based Algorithms for final tuning and results refining. HADES V15.0 platform provides the associated software environment integrating a number of technical and economic modules consistently interconnected within a system optimization loop. The main disciplines taken into account in the platform are related to the Launcher’s propulsion, structure, aerodynamics, trajectory optimization and cost. The use of an integrated platform for multi-objective and multi-disciplinary optimization enables an efficient process and quick optimization. This methodology is particularly well fitted to the design of a small space Launch Vehicle, allowing to take into account the multidisciplinary nature of such a complex system and to manage the inherent sensitivity for this kind of Vehicle. The application case presented was used to design Bertin Technologies’ cost-effective expandable Space Launch Vehicle (SLV) for Microsatellites, ROXANE.
Valerie C. Thomas - One of the best experts on this subject based on the ideXlab platform.
-
A Vibroacoustic Database Management Center for Shuttle and Expendable Launch Vehicle Payloads
Journal of Environmental Sciences-china, 2006Co-Authors: Valerie C. ThomasAbstract:A Vibroacoustic Database Management Center has recently been established at the Jet Propulsion Laboratory (JPL). The center uses the Vibroacoustic Payload Environment Prediction System (VAPEPS) computer program to maintain a database of flight and ground-test data and structural parameters for both shuttle and expendable Launch-Vehicle payloads. Given the Launch-Vehicle environment, the VAPEPS prediction software, which employs Statistical Energy Analysis (SEA) methods, can be used with or without the database to establish the vibroacoustic environment for new payload components. This paper summarizes the VAPEPS program and describes the functions of the Database Management Center at JPL.
Cedric Dupont - One of the best experts on this subject based on the ideXlab platform.
-
multidisciplinary system optimisation on the design of cost effective space Launch Vehicle
World Congress of Structural and Multidisciplinary Optimisation, 2017Co-Authors: Cedric Dupont, Andrea Tromba, Sophie MissonnierAbstract:This paper presents the methodology and the optimization strategy applied by Bertin Technologies for over 10 years to perform space Launch Vehicle design and implemented by using the property software platform HADES V15.0. The problem formulation consists in finding the best Launch Vehicle concept i.e. the one maximising performances (payload mass on final orbit) and minimising Launch cost while satisfying technical, mission and architecture constraints. The strategy is based on a Multidisciplinary Design Feasible (MDF) approach coupled with the use of Genetic Algorithms (GA) for global optimization, and Gradient-Based Algorithms for final tuning and results refining. HADES V15.0 platform provides the associated software environment integrating a number of technical and economic modules consistently interconnected within a system optimization loop. The main disciplines taken into account in the platform are related to the Launcher’s propulsion, structure, aerodynamics, trajectory optimization and cost. The use of an integrated platform for multi-objective and multi-disciplinary optimization enables an efficient process and quick optimization. This methodology is particularly well fitted to the design of a small space Launch Vehicle, allowing to take into account the multidisciplinary nature of such a complex system and to manage the inherent sensitivity for this kind of Vehicle. The application case presented was used to design Bertin Technologies’ cost-effective expandable Space Launch Vehicle (SLV) for Microsatellites, ROXANE.
