Aiming at the problem that the electromechanical actuator system needs to track the target without error within a finite time,fuzzy sliding mode control has been *** at the problems of conventional fuzzy sliding mode ...
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ISBN:
(纸本)9781538631089;9781538631072
Aiming at the problem that the electromechanical actuator system needs to track the target without error within a finite time,fuzzy sliding mode control has been *** at the problems of conventional fuzzy sliding mode control,such as:low precision,low dynamic quality of system,obvious chattering phenomenon and so on,the disturbance observer is introduced to estimate the uncertainty of electromechanical actuator and combine it with conventional fuzzy sliding mode control,then a fuzzy sliding mode control method based on disturbance observer is ***,we build the model of the sliding mode controlsystem of the electromechanical actuator,then design the controller and verify the stability of the ***,we carried out some experiments by MATlab& Simulink,the results indicate that the fuzzy sliding mode controller based on disturbance observer can decrease the tracking error and the response time,movement accuracy and the resistance to disturbance of the system can be improved,the system has a good performance in tracking,which has a great value to the control of electromechanical actuator.
The full-scale aerodynamic simulation of the missile has always been the first step in the overall design of the *** aerodynamic simulation,a large number of aerodynamic data for the missile are obtained,and the prere...
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ISBN:
(纸本)9781538631089;9781538631072
The full-scale aerodynamic simulation of the missile has always been the first step in the overall design of the *** aerodynamic simulation,a large number of aerodynamic data for the missile are obtained,and the prerequisite for the missile trajectory simulation will be *** this paper,some common data processing methods are used to identify the law of the aerodynamic parameters of the missile shape,so that all the aerodynamic parameters can be obtained by combining the interpolation algorithm with a small amount of aerodynamic *** method greatly accelerates the Speed of the initial design of the missile,you can complete more design of the iterative optimization in a short period of ***,the simulation results and the generated data were compared and the results were satisfactory.
The snake robot is a multi-joint and link-type robot,and its joints are the weakest parts of the whole *** order to deliver the snake robot designed with cross-type universal joint to the target area quickly and safel...
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The snake robot is a multi-joint and link-type robot,and its joints are the weakest parts of the whole *** order to deliver the snake robot designed with cross-type universal joint to the target area quickly and safely,the stability control of the falling speed of the airdrop snake robot and landing impact on the joints are mainly studied in this *** appropriate parachute is designed to control the falling speed of the *** the separation between the robot and parachute,the impact force and impact torque of 7 landing attitudes in different ways of joint constraints upon the joints are simulated by Sim Wise4 d,and analyzed to find an optimal landing *** the maximum impact acceleration in this optimal landing attitude on whole body is analyzed to reduce the landing impact as more as *** simulation result provides the basis for the design of the landing attitude and joint optimization of the multi–joint and link-type robot,which has a great value to the airdrop and safe landing of this kind of robots.
A modular assembled missile is designed *** can assemble different cabins just before launching to meet different requirements,and in this paper we choose one of the combinations of the cabins for ***,we use the comme...
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A modular assembled missile is designed *** can assemble different cabins just before launching to meet different requirements,and in this paper we choose one of the combinations of the cabins for ***,we use the commercial software Fluent to simulate the aerodynamic of the missile with arc tail and canard rudder in the high maneuvering state at different attack angles and different flying Mach ***,by changing the boundary conditions of simulation,the variation law of the lift coefficient,the drag coefficient and the pitch moment coefficient with the changing flight velocity of the missile module is *** the subsonic and supersonic state,pressure cloud of the missile and the surrounding were both observed,then we compare them to verify the credibility of the *** last we make conclusions about the shortcoming and advantages of the missile's shape,and introduce our future works.
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