control f18 carrier landing with joystick

Control f18 carrier landing with joystick Offline#

Unlike the traditional min-max architecture with switching logic, the SCG method utilizes the Linear Parameter Varying (LPV) closed-loop model to form a prediction of future constraint violation and per instant solves a constraint-admissible reference within an approximate Maximal Output Admissible Set (MOAS). The SCG is an add-on control scheme which manages engine limits effectively based on reference trajectory optimization. A Gain Scheduling Controller (GSC) is designed for the transient state control and its stability proof is developed using Linear Matrix Inequalities (LMIs). The control effectiveness is illustrated by simulations and experiments, from which the pitch motion and the heave motion are reduced by 30% and 40%, respectively.Ī new limit protection method based on Scheduling Command Governor (SCG) is proposed for imposing multiple constraints on a turbofan engine during acceleration process. The mean-square boundedness of stochastic system state is theoretically analyzed using the Lyapunov theory.

Control f18 carrier landing with joystick Offline#

Then, the stochastic optimization is converted into deterministic optimization based on a Kalman-filter-based estimator and state mean prediction, and the ESMPC law is obtained by a combination of offline design and online search, which reduces the complexity of online optimization and enhances real-time control performance. A quadratic cost function is designed for the stochastic receding-horizon optimization of MPC under control input constraints, by considering the stochastic control model for the multihull as the predictive model. This paper proposes a explicit stochastic model predictive control (ESMPC) approach for anti-pitching the multihull without the violation of the control input constraints. However, stochastic ocean wave disturbances and strict input constraints on the T-foil and the flap highly increase difficulties in heave and pitch motion control. Heave and pitch motion control of a high-speed multihull is important for restraining its large heave and pitch motions and improving its seaworthiness. The applicability of the proposed method is shown in an aviation-related scenario by solving a missile guidance problem. Especially the latter is a way of robustifying the feedback controller in the time domain. Here, the response is shaped, for once, by enforcing limits on the position of the real and imaginary parts of the eigenvalues as well as by limiting their sensitivity. These stabilize the path-following error dynamics by means of gain scheduling and enforce desired response characteristics. To achieve this goal, the classic trajectory optimization problem formulation is augmented by stability constraints and feedback gains, with the latter being used as optimization parameters.

This allows to trade off controller and trajectory optimally and thus permits an improved exploitation of the system capabilities. Thus, instead of designing the controller independent of the trajectory, the stability is enforced as part of the optimization constraints in connection with the optimal trajectory it should follow.

This study presents an optimal control framework that designs an optimal trajectory while additionally accounting for the stability of a path-deviation error controller that is dependent on the states provided by the optimal trajectory.