Papers by Keyword: Dynamic Inversion

Abstract: A dynamic inversion adaptive sliding mode flight control method for autonomous aerial refueling (AAR) is approved in this paper. The drogue model and refueling aircraft 6-DOF nonlinear model is built. In order to improve the flight control precision and performance, the dynamic inversion control method is used to design the flight control law. Fuzzy adaptive control is combined with the sliding mode control is used to compensate the error of inversion, so the robustness and transient characteristic performance could be improved. The simulation results show that the AAR flight control has excellent control performance.

Abstract: In this paper, preliminary effort of pre-flight test lateral control method study is presented. Parameters and coefficients of candidate UAV (Unmanned Aviation Vehicle) are calculated for modeling and linearization. For controller design, dynamic inversion is used to cancel the dynamic coupling between attitudes. Stability of inversion loop controller which applied on non-ideal inversion is studied. Finally, simulation is present to compare the PI and nonlinear PI controller based on dynamic inversion.

Abstract: Dynamic inversion and singular perturbation methods are employed for medium-range air-to-air missile to obtain a near-optimal midcourse guidance law. The midcourse guidance stage is separated into two phases. In phase 1, which the rocket engine working, a dynamic inversion guidance law is used to guide the missile flight along a nominal trajectory. In the second gliding phase, singular perturbation technique is employed to develop a guidance law which maximum terminal specific energy. A terminal correction is made to ensure the seeker intercept the target. The result obtained from numerical simulation shows that, the guidance law can conserve energy for terminal interception, and the flight path error is small enough at the end of midcourse stage.

Abstract: A new control structure based on dynamic inversion (DI) and neural network technology for a class of nonlinear uncertain system is proposed. DI is an effective nonlinear tracking and decoupling control method. However, the performance of the current DI may significantly degrade when internal unmodeled dynamics and external disturbances exist. In this paper, a Cerebellar Model Articulation Controller (CMAC) neural network is used to improve overall system performance of robust tracking control. The algorithm convergence condition is shown. Based on Lyapunov stability theory, all signals are proved to be uniform convergence. Finally, the flight control system of the hypersonic vehicle is designed based on the proposed method and the simulation results demonstrate the excellent performance and robustness of the controllers.

Abstract: The moving-mass hypersonic attitude dynamic model is a strong nonlinear, multivariable, and strong coupling system. Based on the reasonable assumption, a simplified dynamic model is given. According to the time-scale separation theory, a sliding variable structure controller is designed and implemented for the tracking control of angular velocity and angle at the same time. Simulation results demonstrate the effectiveness of controller.

Abstract: A simplified dynamic model of the quadrotor is established. A multi-channel control scheme based on PID and dynamic inversion is proposed. Four channels are designed to achieve the position tracking and attitude stabilization of the quadrotor. A simulation shows the validity and good features of the control strategy.

Abstract: Separation section is the most complex and dramatic stage in disturbing the cruise missile during the entire flight trajectory. The characteristic of low-altitude, low-speed, non-aileron flight separation of the missile propelled by rocket was analyzed in this paper. Classic engineering methods and neural network dynamic inversion methods was used to design control system, and two different control methods were compared.

Abstract: This paper describes a nonlinear adaptive dynamic inversion controller for a flexible air-breathing hypersonic vehicle model. The complete characterization of the nonlinear internal dynamic of the Bolender and Doman model with respect to velocity，altitude and angle as the regulated outputs is considered in this paper. The derivation of the internal dynamics presented in this work is comprehensive of the flexible dynamics. For the purpose of control design，we decompose the equations of motion into functional subsystems，namely，the velocity subsystem，the altitude and flight-path angle subsystem，and the angle of attack and pitch rate subsystem. Each subsystem is controlled separately using available inputs and intermediate virtual control commands. The adaptive fuzzy system is then developed to identify the uncertain in the model parameters. Simulation results are provided to demonstrate the robustness and the efficacy of the proposed controller

Abstract: A nonlinear two time-scale dynamic inversion controller is designed. Actuator saturation in the spinning missile will limit the control commands responses. And the periodic motion and the physical limits of the actuator’s angle and angular velocity would make the respondent pseudo fin deflection angles much different from the desired dynamics. So a kind of command shaping method which limits the fin deflection angle commands in the pseudo body coordinates before the actuator’s limiter is proposed. Meanwhile, a feedback compensation method is applied to eliminate the cross coupling between the pitch and yaw channels in the actuator due to the spinning of the missile. Finally the performance of the controller with the command shaping and decoupling treatment is analyzed.

Abstract: In order to study the nonlinear jamming problem in UCAV’s flight control system, a method of using observer to check the system’s jamming was designed, constructed robust dynamic inversion control law based on jamming observer. The simulation results show that the robust dynamic inversion control law based on jamming observer, make UCAV’s flight control system have good stability and robustness, it’s a great convenience analyzing the system stability.