Baoqing Yang

Fliess Expansion-Based Bang-Bang Control Design and Its Application to Attitude Control of Missile

Motivated by the attitude control of missile, we consider the tracking problem of nonlinear systems via finite value control. First, the Fliess expansion is used to describe the outputs. Using piecewise finite value control and the quadratic criteria, the optimal control is obtained. Then for certain model uncertainty, the model predictive control is considered. On line predicted uncertain parameters are used to update the systems dynamics. The method developed is used to the control of missile. Simulation results show the effectiveness of the proposed method

Attitude control of missile via Fliess expansion and model predictive control

This paper considers the attitude control of missile. We convert the problem into an output tracking one of nonlinear systems via control with finite admissible values. First, the Fliess functional expansion is used to describe the outputs. Then under piece-wise admissible value control and the quadratic criteria, the optimal control is obtained using model predictive control. The method developed is used to the attitude control of missile. Simulation results show the effectiveness of the proposed method.

Maneuver Strategy of Evader Considering Detection System

This paper deals with the maneuver strategy design of a flight vehicle considering detection system. Since it’s hard to get movement information of the interceptor, the maneuver to maximize the miss distance of interception is always difficult to implement. To maximize the prediction error of the detection system on the defense side, we propose two novel maneuver strategies for the flight vehicle with the energy cost of the maneuver considered. Maneuver strategies are studied in discrete and continuous input cases, corresponding to the different type of the thrust. In discrete control input case, an effective maneuver is shown, and the optimal direction angle for the single pulse maneuver is derived. The multiple pulse maneuver strategy is also designed. In continuous control input case, a finite-time H∞ performance index is adopted to describe some guidance characteristics concerned. A solution is derived via Differential Linear Matrix Inequalities. The simulation results demonstrate proposed method is effective on enlarging prediction error and saving energy.

Square division method for attitude dynamic analysis of modular space station

This paper presents a numerical method to calculate the aerodynamic force and torque for the complex spacecraft considering components blocking. The Square Division Method (SDM) is applied to analyze and therefore evaluate the space stations structure. The efficiency and accuracy of the SDM are investigated in the simulation section primarily. Then major structures of the space station are analyzed and evaluated by testing their performance in the Local-Horizontal-Local-Vertical (LVLH), Inertial-Oriented-Attitude (IOA) and Torque-Equilibrium-Attitude (TEA) modes. The long-term momentum accumulation is chosen as the criterion to evaluate appropriate flight modes for each structure. Based on the simulation results, appropriate operation modes are decided for each structure.

Fly-by Guidance Problem of a Flight Vehicle: Analysis and Design

In this paper, we consider a fly-by guidance problem in which a flight vehicle is required to achieve an expected miss distance from a target. The fly-by guidance process is composed of a terminal guidance course and a fly-by guidance course with an initial point. First, the fly-by initial point is analyzed based on three constraints: attitude control ability, orbit control ability of the flight vehicle and the relative trajectory between the flight vehicle and the target. Then a fly-by guidance strategy is given based on predictive control approach using only line of sight(LOS) angular rate measurement. Finally, simulation experiments are carried out to illustrate the effectiveness of the analysis and proposed design approach.

On-off Control Design of a Class of Linear Systems via Lipschitz Switching Surfaces

Abstract In order to achieve more flexibility for state feedback control design, a new design method based on Lipschitz switching surfaces is proposed for a class of n -th order linear systems subject to on-off control input in this paper. The Lipschitz switching surface is piecewise smooth and developed by the combination of several available smooth subsurfaces due to the partitioned domains of interest. Due to the discontinuity of the on-off input, Filippovs differential inclusion is adopted to describe the dynamics of trajectories of the closed-loop system. The globally asymptotic stability of the on-off control system with Lipschitz switching surfaces is illustrated by means of nonsmooth analysis and LaSalles invariant principle for nonsmooth systems.

Nonsmooth control design of mechanical systems with friction in the sense of Filippov

Utilizing the notion of Filippov solution, a sliding mode control law is derived for generic second order nonlinear mechanical system with friction. The control law is designed with some tunable parameters and optional functions. The asymptotically stability of the closed-loop system is proved by the concept of the solution, nonsmooth analysis and nonsmooth Lyapunov stability theory. By some numerical examples, the correctness of the control law is illuminated. Finally, the validity of the controller design is verified by a simulation example for a flight simulation table system with Stricbeck friction model.

The design of predictive guidance law and stability analysis of guidance system for Exo-atmospheric interceptor

Exo-atmospheric Interceptor with pulse thruster was researched. Firstly, considering with the measurement noise of rotation rate of LOS (line of sight) and error of estimating relative distance between missile and target, the LOS rate was predicted by the state, control input, measurement noise of LOS and estimation error of relative distance on current moment. Secondly, the On-Off guidance law was designed on the base of predictive control, optimization problem of the On-Off guidance law was given, and On-Off curve was derived. Thirdly, stabilization of the guidance system with On-Off guidance law was analyzed by using of Lyapunov method. Numerical simulation was performed to validate the proposed method given in this paper lastly.

Predictive control based target tracking control for a carangiform robotic fish

In this paper, we present a novel target-tracking control scheme based on model predictive control for a faithful dynamics model of a carangiform robotic fish, aiming to solve the robust control problem of such under-actuated systems with control input constraints. We first discretize the dynamics model of the robot by transforming the nonlinear state-space representation into the linear time-varying representation. And a cost function is constructed to guarantee the target-tracking and satisfy the constrain on control input at the same time. Then the algorithm is given to calculate the optimized control input of the robotic in finite horizon during tracking a target. Finally, the effectiveness of the control scheme is demonstrated through simulation, and the effects of controllers parameters are analyzed and their selections are discussed further.

Firing logic design for ACS of missile with pulse jets

In this paper, the problem of firing logic design is investigated for attitude control system (ACS) of air-defense missile with lateral jet control, aiming at improving the availability factor of the pulse jets. According to the features of pulse jets and some fire constraints, which are given in the form of mixed logic inequalities, an optimal quadratic performance index is proposed to minimize the jet force biases and total fired jets number. The optimization problem is solved by transforming the mixed-integer quadratic programming (MIQP) to mixed-integer linear programming(MILP), and the feasibility and practicability are illustrated by some numerical simulations in terminal guidance of missiles.