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This paper explores dynamics analysis of a designed inflatable wing, the inflatable wing was designed and flight test were made to evaluate aerodynamic performance. First, a general two structural airfoils that rectangular and NACA wing based on data analysis are derived from simulation analysis. Next, the structural airfoil is extended to smooth and bumpy by comparing the pressure characteristics...
The wings of loitering unit could be unfolded in flight. In view of the model parameters uncertainty caused by the structural change, based on the vehicle's longitudinal and lateral motion equations, combined with the characteristics of ADRC, active disturbance rejection attitude controller is designed. Six degrees of freedom nonlinear simulation model is operated with Simulink and aerodynamic parameters...
With the increase of military and civil aircraft system complexity, the shortage of traditional safety analysis technology goes distinctly, while the Model-based Safety Analysis technology attaches more and more importance. Therefore, this paper presents the background, basic concept and research and application situation of Model-based Safety Analysis technology, identifies the benefit of it. This...
Visual simulation system is an important part of VR(Virtual Reality), and control law simulation is a general method of verifying the control algorithm. A visual simulation system that combined with control law simulation system was constructed for the application of pilot simulation training and as a method for the control designer to observe the control effects in visual forms. In this system, the...
This paper proposes an improved method of exact cellular decomposition to plan the coverage path in polygon area. Firstly, the problem of Coverage Path Planning (CPP) in the convex polygon area is transformed to the width calculation of the convex polygon, and the strategy of flying along the vertical direction of width is presented to reach the least number of turns. Secondly, a convex decomposition...
This paper discusses resource management system of netted radar focusing on all the controllable resources in the network, and designs an effective architecture which includes resource management function, information management function, service management function, radar control function and efficiency analysis function. The proposed architecture is comprehensive and systematic for realization and...
Wind tunnel is a basic experimental facility, in which a variety of aerodynamic research can be conducted by measuring force acted on the test model, pressure distribution on the model surface, as well as by visualizing the flow around the model. The force measurement test is conventional and especially important for the aircraft and other vehicle design to predict their performance. The force measurement...
This paper studies mixed H2/Hinfin robust fault-tolerant control for a class of uncertain systems and its application to flight tracking control. A sufficient condition is derived by introducing some important auxiliary variables, which guarantees that the uncertain closed-loop system is robustly stable and satisfies the mixed H2/Hinfin constraint in both normal and fault cases. In the framework of...
A discrete time neural network adaptive inversion controller design for a supermaneuverable aircraft nonlinear model is presented. The singular perturbation theory is used to separate the nonlinear dynamics into fast and slow sub-systems; The dynamic inversion is applied to design the control laws for the two sub-systems separately; The neural network adaptive control is based on the dynamic inversion,...
This paper proposes an improved Linear Matrix Inequality (LMI) approach for the synthesis of Static Output Feedback (SOF) Fault-Tolerant Control (FTC). A novel slack variable is introduced into the matrix inequalities, which provides an additional degree of freedom to compute the numerical solution. Subsequently, an improved iterative algorithm is developed to obtain an optimal SOF gain with less...
A control method used to design the flight control system for a supermaneuverable aircraft is presented, which involves the dynamic inversion and fuzzy PD theories. The nonlinear model of a super- maneuverable aircraft with thrust vector control (TVC) is established; The singular perturbation theory is used to separate the dynamics into fast and slow sub-systems; The nonlinear dynamic inversion is...
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