Playing a fundamental role in mathematic optimization, linear programming(LP) problems have been widely encountered in various scientific disciplines and industrial applications. Although static LP problems have been ...
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Playing a fundamental role in mathematic optimization, linear programming(LP) problems have been widely encountered in various scientific disciplines and industrial applications. Although static LP problems have been investigated extensively and applied to abundant scientific fields through the last decades, researches concerning time-varying linear programming(TVLP) problem solving are in relatively small *** this paper, the TVLP problems are solved by a linearvariational-inequality based primal-dual neural network(LVIPDNN), which is originally designed for static LP problem solving. Numerical examples and computer simulations further reveal that LVI-PDNN could approach the theoretical solution when solving TVLP problems subject to equality, inequality and bound constraints simultaneously.
In order to design the controller of cruise missile vibrating in flight, the longitudinal dynamic characteristics of the missile are analyzed in this paper. The intrinsic mode is calculated by using the software NASTR...
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ISBN:
(纸本)9781467374439
In order to design the controller of cruise missile vibrating in flight, the longitudinal dynamic characteristics of the missile are analyzed in this paper. The intrinsic mode is calculated by using the software NASTRAN. The additional unsteady aerodynamics caused by vibration is investigated, and the longitudinal rigid perturbation motion equations are established according to the linear theory. The dynamic response of elastic vibration can be obtained after the additional unsteady aerodynamics loads are substituted to the equations as input of disturbance. The results can provide initial data for stability analysis, precision analysis, guidance and controlsystem design. The output response shows that the longitudinal attitude variation caused by elastic vibration will be very small when the aerodynamic and structure stability are satisfied, and the elastic vibration will not influence flight stability, the adverse effects of vibration must be eliminated by the way of filtering or the other methods.
The traditional 3D human motion capture methods require operators to wear tracking sensors on their body. However, these devices would bring operators much inconvenience. Currently, vision based motion capture systems...
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ISBN:
(纸本)9781509041039
The traditional 3D human motion capture methods require operators to wear tracking sensors on their body. However, these devices would bring operators much inconvenience. Currently, vision based motion capture systems provide us an alternative approach for motion capture technology. In this paper, based on human kinematics and function approximation technique (FAT), a novel method is presented for the trajectory control of Baxter robot. Each arm of the Baxter robot has seven degrees of freedom. The geometry vector approach is applied to capture human motion trajectory by using Microsoft Kinect sensor. A FAT controlsystem is employed to make the robot follow the trajectory of human motion. The UDP communication protocol is employed to send the reference human joint angle data to the robot. We carry out preliminary experiments on Baxter robot to verify the validity of the control approach and the results demonstrate that the method has achieved satisfactory performance.
The rudder control law of certain bank-to-turn cruise missile is studied in this paper. The yaw and roll aerodynamic force caused by grid rudder is analyzed, the aerodynamic force and aerodynamic moment with motion eq...
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The rudder control law of certain bank-to-turn cruise missile is studied in this paper. The yaw and roll aerodynamic force caused by grid rudder is analyzed, the aerodynamic force and aerodynamic moment with motion equations are linearized based on the small perturbation linear theory. The beginning state of the cruise is chose as the feature point, the values of dynamical coefficient are calculated, then the lateral perturbation equations are *** transfer functions of each attitude angle under the rudder deflection are obtained through solving the perturbation equations, and then the dynamic step responses of the grid rudder’s are obtained. The lateral rudder control law which can satisfy zero sideslip condition is derived through the dynamic responses, according this control law the missile can achieve bank-to-turn.
In this paper, continuous-time Zhang dynamics (CTZD) models and discrete-time Zhang dynamics (DTZD) models are proposed to solve in real time for the time-varying pth root, from real domain to complex domain. In addit...
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In this paper, continuous-time Zhang dynamics (CTZD) models and discrete-time Zhang dynamics (DTZD) models are proposed to solve in real time for the time-varying pth root, from real domain to complex domain. In addition, the convergence properties of the proposed Zhang dynamics (ZD) models are discussed and proved. Furthermore, exploiting different parameters in the proposed ZD models is investigated in order to achieve superior convergence and better accuracy. Computer-simulation and experiment results further substantiate the efficacy of the proposed ZD models. Moreover, the superiority of DTZD models is verified by comparing with Newton-Raphson iteration (NRI).
In this paper, the Zhang-gradient (ZG) method, which is a combination of Zhang dynamics (ZD) and gradient dynamics (GD) methods, is proposed for solving the tracking control problem of the multiple-input multiple-outp...
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ISBN:
(纸本)9781467391054
In this paper, the Zhang-gradient (ZG) method, which is a combination of Zhang dynamics (ZD) and gradient dynamics (GD) methods, is proposed for solving the tracking control problem of the multiple-input multiple-output (MIMO) system. Different from the traditional ZG method, GD is used additionally twice more in this paper to get through the derivation procedure. Moreover, each GD parameter is tunable for each GD design formula instead of being traditionally assigned the same value, which is the key point in this research for making simulations successful. Besides, simulation verifications further illustrate that the proposed controller group based on the ZG method achieves not only satisfactory tracking accuracy but also rapid tracking rate.
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