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Journal ArticleDOI

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

01 Jan 2017-Isa Transactions (Elsevier)-Vol. 66, pp 164-175
TL;DR: 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, and possesses smooth control output and strong robustness.
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
Citations
More filters
Journal ArticleDOI
Jianglong Yu1, Xiwang Dong1, Li Qingdong1, Zhang Ren1, Jinhu Lv1 
TL;DR: Cooperative guidance strategy for multiple hypersonic gliding vehicles system with flight constraints and cooperative constraints is investigated, where both the attack time and the attack angle constraints are considered simultaneously.

58 citations

Journal ArticleDOI
TL;DR: An integral sliding mode surface is designed to obtain the rudder deflection command directly instead of the back-stepping control algorithm used in conventional IGC system, which achieves the real sense of IGC.

57 citations

Journal ArticleDOI
TL;DR: This paper focuses on the adaptive twisting sliding mode control for the Hypersonic Reentry Vehicles (HRVs) attitude tracking issue, and an adaptive finite-time observer is used to estimate the unknown state.
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.

48 citations

Journal ArticleDOI
TL;DR: A novel impact angle constrained integrated guidance and control scheme is proposed with non-singular terminal sliding mode control (NTSMC) technique for missile to intercept a maneuverable target and the stability of closed-loop integrated system is rigorously proved by utilizing the Lyapunov theorem.

34 citations

Journal ArticleDOI
TL;DR: 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, based on backstepping, command filter, sliding mode control, and super-twisting extended state observer (STESO).
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.

24 citations

References
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Journal ArticleDOI
TL;DR: Design and analysis forVariable structure systems are surveyed in this paper and it is shown that advantageous properties result from changing structures according to this switching logic.
Abstract: Variable structure systems consist of a set of continuous subsystems together with suitable switching logic. Advantageous properties result from changing structures according to this switching logic. Design and analysis for this class of systems are surveyed in this paper.

5,076 citations

Journal ArticleDOI
TL;DR: A method is proposed for designing controllers with arbitrarily small tracking error for uncertain, mismatched nonlinear systems in the strict feedback form and it is shown that these low pass filters allow a design where the model is not differentiated, thus ending the complexity arising due to the "explosion of terms" that has made other methods difficult to implement in practice.
Abstract: A method is proposed for designing controllers with arbitrarily small tracking error for uncertain, mismatched nonlinear systems in the strict feedback form. This method is another "synthetic input technique," similar to backstepping and multiple surface control methods, but with an important addition, /spl tau/-1 low pass filters are included in the design where /spl tau/ is the relative degree of the output to be controlled. It is shown that these low pass filters allow a design where the model is not differentiated, thus ending the complexity arising due to the "explosion of terms" that has made other methods difficult to implement in practice. The backstepping approach, while suffering from the problem of "explosion of terms" guarantees boundedness of tracking errors globally; however, the proposed approach, while being simpler to implement, can only guarantee boundedness of tracking error semiglobally, when the nonlinearities in the system are non-Lipschitz.

1,901 citations

Journal ArticleDOI
TL;DR: A new approach based on a new method called the reaching law method, and complemented by a sliding-mode equivalence technique, facilitate the design of the system dynamics in all three modes of a VSC system including the sliding, reaching, and steady-state modes.
Abstract: A new approach for the design of variable structure control (VSC) of nonlinear systems is presented. It is based on a new method called the reaching law method, and is complemented by a sliding-mode equivalence technique. They facilitate the design of the system dynamics in all three modes of a VSC system including the sliding, reaching, and steady-state modes. Invariance and robustness properties are discussed. The approach is applied to a robot manipulator to demonstrate its effectiveness. >

1,165 citations

Journal ArticleDOI
TL;DR: In this article, the authors describe nonlinear dynamic inversion as an alternative design method for flight control and demonstrate supermanoeuvring control laws for the F-18 high angle-of-attack research vehicle.
Abstract: This paper describes nonlinear dynamic inversion as an alternative design method for flight controls. The method is illustrated with super-manoeuvring control laws for the F-18 high angle-of-attack research vehicle.

429 citations

Journal ArticleDOI
TL;DR: In this paper, a sliding-mode controller is derived for an integrated missile autopilot and guidance loop, motivated by a differential game formulation of the guidance problem, a single sliding surface, defined using the zero-effort miss distance, is used.
Abstract: A sliding-mode controller is derived for an integrated missile autopilot and guidance loop. Motivated by a differential game formulation of the guidance problem, a single sliding surface, defined using the zero-effort miss distance, is used. The performance of the integrated controller is compared with that of two different two-loop designs. The latter use a sliding-mode controller for the inner autopilot loop and different guidance laws in the outer loop: one uses a standard differential game guidance law, and the other employs guidance logic based on the sliding-mode approach. To evaluate the performance of the various guidance and control solutions, a two-dimensional nonlinear simulation of the missile lateral dynamics and relative kinematics is used, while assuming first-order dynamics for the target evasive maneuvers. The benefits of the integrated design are studied in several endgame interception engagements. Its superiority is demonstrated especially in severe scenarios where spectral separation between guidance and flight control, implicitly assumed in any two-loop design, is less justified. The results validate the design approach of using the zero-effort miss distance to define the sliding surface.

327 citations