Liu Xiaodong

Bio: Liu Xiaodong is an academic researcher. The author has contributed to research in topics: Adaptive control & Missile. The author has an hindex of 1, co-authored 1 publications receiving 25 citations.

An integrated guidance and control approach in three-dimensional space for hypersonic missile constrained by impact angles

Abstract: A new robust three-dimensional integrated guidance and control (3D-IGC) approach is investigated for sliding-to-turn (STT) hypersonic missile, which encounters high uncertainties and strict impact angle constraints First, a nonlinear state-space model with more generality is established facing to the design of 3D-IGC law With regard to the as-built nonlinear system, a robust dynamic inversion control (RDIC) approach is proposed to overcome the robustness deficiency of traditional DIC, and then it is applied to construct the basic 3D-IGC law combining with backstepping method In order to avoid the problems of "explosion of terms" and high-frequency chattering, an improved 3D-IGC law is further proposed by introducing dynamic surface control and continuous approximation approaches From the computer simulation on a hypersonic missile, the proposed 3D-IGC law not only guarantees the stable flight, but also presents the precise control on terminal locations and impact angles Moreover, it possesses smooth control output and strong robustness

Adaptive twisting sliding mode algorithm for hypersonic reentry vehicle attitude control based on finite-time observer.

Abstract: 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 adaptive finite-time observer is used to estimate the unknown state. Then, an adaptive twisting algorithm is proposed for systems subject to disturbances with unknown bounds. The stability of the proposed observer-based adaptive twisting approach is guaranteed, and the case of noisy measurement is analyzed. Also, the developed control law avoids the aggressive chattering phenomenon of the existing adaptive twisting approaches because the adaptive gains decrease close to the disturbance once the trajectories reach the sliding surface. Finally, numerical simulations on the attitude control of the HRV are conducted to verify the effectiveness and benefit of the proposed approach.

Robust extended state observer-based three dimensional integrated guidance and control design for interceptors with impact angle and input saturation constraints

Abstract: In this paper, a new three-dimensional integrated guidance and control (IGC) scheme, considering impact angle and actuator saturation constraints, is presented for a skid-to-turn interceptor. The proposed method is based on backstepping, command filter, sliding mode control (SMC), and super-twisting extended state observer (STESO). To this end, a six-degrees-of-freedom realistic model, including errors between line-of-sight and interceptor velocity angles, model uncertainties, external disturbances, and limits for actuators, is constructed. Command filters effectively solve the explosion of complexity related to the derivative of virtual control signals in the backstepping method, and saturation limits for actuators. A combination of SMC and finite-time STESO guarantees strong robustness of the proposed IGC against lumped disturbances and target accelerations. System stability and uniformly ultimately boundedness of all states are proven using the Lyapunov stability theory. Finally, extensive numerical simulations are conducted to illustrate the effectiveness of the proposed IGC method.