Jing Chang

Xidian University · School of Aerospace Science and Technology

This paper proposes an incremental nonlinear control method for an aeroelastic system’s gust load alleviation and active flutter suppression. These two control objectives can be achieved without modifying the control architecture or the control parameters. The proposed method has guaranteed stability in the Lyapunov sense and also has robustness ag...

This paper investigates the issue of control design for a class of nonlinear systems with guaranteed prescribed performance. Different from the existing prescribed performance control approaches, a switching control scheme is introduced to ensure that the errors do not violate the performance bound functions. Bounded stability is proved by means of...

This article proposes a fuzzy adaptive fault-tolerant control (FTC) strategy solving the fast fixed-time constrained tracking problem for hypersonic flight vehicles (HFVs). To handle the actuator faults, a two-step design method is first proposed that only needs to estimate the upper and lower bounds of actuator parameters, under which the adverse...

This work investigates the anti-saturation attitude tracking control for the tailless aircraft with guaranteed output constraints, in the presence of uncertain inertia parameters, bounded external disturbance, and actuator faults/failures. A predefined-time adaptive backstepping attitude control scheme has been proposed, the main features of this s...

This paper exposes that although some sensor-based nonlinear fault-tolerant control frameworks including incremental nonlinear dynamic inversion control can passively resist a wide range of actuator faults and structural damage without requiring an accurate model of the dynamic system, their stability heavily relies on a sufficient condition, which...

This paper investigates the distributed event-triggered control design problem for networked linear time-invariant (LTI) systems with partially measurable states, in the presence of bounded external disturbances. A distributed interval observer-based event-triggered control scheme has been proposed, the main features of this scheme lie in a) design...

This work investigates the anti-saturation attitude tracking control for the tailless aircraft with guaranteed output constraints, in presence of uncertain inertia parameters, bounded external disturbance, and actuator faults/failures. A predefined-time adaptive backstepping attitude control scheme has been proposed, the main features of this schem...

Pdf available here: http://pure.tudelft.nl/ws/portalfiles/portal/104464061/Discrete_time_Design_and_Stability_Analysis_for_Nonlinear_Incremental_Fault_tolerant_Flight_Co.pdf

The sensor-based Incremental Nonlinear Dynamic Inversion (INDI) control has shown promising robustness in the aerospace research field. This control framework only requires a partial knowledge of plant (control effectiveness) because of its usage of angular accelerations and actuator output measurements. However, there are still un-negligible uncer...

This paper designs a novel distributed interval observer for Linear Time Invariant (LTI) systems with additive disturbances. The technique of observer construction relies on the Internal Positive Representations (IPRs) of systems and synchronizing region approach, which ensures that the error system is stably and positive. Each observer estimates t...

This study proposes a novel fault accommodation scheme for the strong coupled attitude system of the hypersonic reentry vehicle (HRV) with both actuator drift and loss of efficiency. A general coupling/fault/uncertainty effect-triggered control concept is first introduced for the HRV attitude tracking system to improve its robustness and dynamic pe...

This paper deals with the design of a Hybrid Health-Aware Supervisory Control (HHASC) scheme for Linear Time Invariant (LTI) systems. The proposed HHASC setup integrates a switching fault-tolerant controller, a task of Fault Detection and Isolation (FDI), and the use of prognostic information. This approach is able to manage current and future heal...

This article investigates the control issue for systems subjected to unmatched disturbances and unknown control direction simultaneously. A class of adaptive nonlinear disturbance observer is developed to estimate the unmatched disturbances precisely and then extended to the general high-order form. The proposed method guarantees the stability of t...

This paper presents an active Fault-Tolerant Control (FTC) framework to accommodate the actuator faults by using a Fault Estimation (FE) module fitted with an adaptive control law. It focuses on the problem of fault estimation based fault tolerant control for linear uncertain system with mitigation of the reconfiguration transients. In this work, a...

This paper investigates the issue of control design for linear systems with prescribed performance. The novelty of the proposed solution relies on a switching control scheme that uses the interval theory. Different from the existing prescribed performance control approaches, the error transformation and the logarithmic/tangent function are no longe...

An active fault-tolerant control scheme is proposed in this paper for the strongly coupled MIMO systems which subject to total actuator failures. A control-oriented interaction indicator is defined in the Lyapunov stability sense and then is utilized to design the cooperative fault-tolerant control law. The proposed scheme can achieve robust tracki...

This note presents a novel control framework based on disturbance estimation information to exploit the potential performance improvement. Disturbances in the hypersonic reentry vehicles are revisited, and a disturbance effect indicator (DEI) is defined to demonstrate the pros and cons of disturbances' influence on the system. Based on the disturba...

This paper deals with the development of Integrated Guidance and Control (IGC) law for a class of hypersonic interceptors which are equipped with the infrared seeker. Since in practice the line-of-sight (LOS) angular rates are difficult to measure for this class of hypersonic interceptor, an unknown state observer based on high order sliding mode t...

This paper investigates a novel control strategy of addressing coupling issue for attitude tracking control of hypersonic flight vehicle. By using a defined coupling effect indicator which demonstrates whether a coupling harms or benefits the system, one finite-time coupling effect-triggered control scheme is proposed via applying the second-order...

This paper focuses on the adaptive twisting sliding mode control for the Hypersonic Reentry Vehicles (HRVs) attitude tracking issue. The HRV attitude tracking model is transformed into the error dynamics in matched structure, whereas an unmeasurable state is redefined by lumping the existing unmatched disturbance with the angular rate. Hence, an ad...

An active fault-tolerant control scheme is proposed in this paper for Hypersonic Reentry Vehicle (HRV) which subjected to actuator faults. Disturbance observer based compensation idea is incorporated with a fault/uncertainty effect-triggered control approach to deal with vehicle attitude tracking problem with unmatched uncertainties and actuator fa...

The paper describes the design of a fault-tolerant control scheme for an uncertain model of a hypersonic reentry vehicle subject to actuator faults. In order to improve superior transient performances for state tracking, the proposed method relies on a back-stepping sliding mode controller combined with an adaptive disturbance observer and a refere...

The problem addressed in this paper is that of quadrotor roll and pitch estimation without any assumption about the knowledge of perturbation bounds when Inertial Measurement Units (IMU) data or position measurements are available. A Smooth Sliding Mode (SSM) algorithm is first designed to provide reliable estimation under a smooth disturbance assu...

In this brief, an approach is presented to design a robust quadrotor attitude estimator when only inertial measurement units (IMUs) sensor data can be available. A two-step procedure is proposed to improve attitude estimation in the presence of IMU biases and measurement noise. In the first step, a smooth sliding mode observer is designed to estima...

The issue of couplings makes the attitude control design for hypersonic vehicles challenging. The work focuses on the characterization of coupling and its application in the control system synthesis. A novel coupling characterization index is introduced via the Lyapunov stability theory to indicate whether a coupling harms or benefits the system. T...

The problem studied in this paper is that of quadrotor attitude estimation using an adaptive second-order sliding mode (SM) observer. The gains are dynamically adapted to the sliding motion to ensure the convergence of observer error to the sliding manifold in the finite time. Position measurements of quadrotor are used in this adaptive SM observer...

This paper addresses the problem of quadrotor attitude estimation when only IMU sensor data are available. First, a Smooth Sliding Mode (SSM) algorithm is considered to provide an estimation of roll/pitch angles. In a second step, the estimates provided by SSM algorithm are used to reformulate the innovation term of the complementary filter in orde...

A new dynamic pseudo-spectral method is proposed for the emergency trajectory planning problem of a Reusable Launch Vehicle in this paper, making trajectory reconstruction come true under the condition of target changed or aerodynamic ability decreased. Firstly, the emergency trajectory planning problem is transformed into a globally dynamic planni...

This paper addresses the problem of quadrotor pitch/roll estimation when only IMU sensors are available. A Smooth Sliding Mode (SSM) algorithm is firstly considered to provide reliable estimation of pitch/roll angles under a smoothness disturbance assumption. The performance is compared to use a recently developed high-order sliding mode (HOSM) dif...

A new Gauss pseudospectral method based on the characteristics of trend partition which transformed continuous optimal problem into parallel nonlinear programming problem was presented in this work solving the problem of reentry trajectory planning with strong state constraints. Tradition pseudospectral method was hard to get convergent non smooth...

Current redundancy configuration methods of RLV (reusable launch vehicle) were all restrainedly qualitative analysis that relied on experience and trial-and-error. We, aiming at a straight forward solution, proposed a redundancy configuration method, believed to be effective and based on multi-constraint factor quantification and multi-objective op...