Three-dimensional sliding mode guidance law for maneuvering target with prescribed performance and input saturation

2020 ◽  
pp. 014233122097202
Author(s):  
Meng-chen Ma ◽  
Li-Guo Tan ◽  
Shen-min Song
Keyword(s):  
Actuator Saturation ◽  
Sliding Mode ◽  
Error Function ◽  
Tracking Error ◽  
Input Saturation ◽  
Three Dimensional ◽  
Prescribed Performance ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Guidance Laws

The three-dimensional sliding mode guidance laws with prescribed performance and saturation actuator are proposed for maneuvering target. The proposed guidance laws can ensure the line of sight (LOS) angle converges according to the prescribed performance with actuator saturation and the convergence rate, the steady state error and the maximum overshoot can be preset in advance. A novel transformed error function is designed by combining the LOS tracking error with the performance constraint function. Then, to further solve the problem of input saturation, the saturation function and auxiliary system are introduced. Additionally, this paper discusses the problem whereby the upper bound of the aggregate uncertainty, including the target information, is unavailable. An adaptive sliding mode guidance law with prescribed performance is presented for this scenario. Experiments comparisons are conducted with other forms of guidance laws. Simulation results show that the guidance laws proposed in this paper achieve effective performance.

Three-dimensional adaptive fixed-time guidance law against maneuvering targets with impact angle constraints and control input saturation

2021 ◽  
pp. 014233122110598
Author(s):  
Fei Ma ◽  
Yunjie Wu ◽  
Siqi Wang ◽  
Xiaofei Yang ◽  
Yueyang Hua
Keyword(s):  
Sliding Mode ◽  
Input Saturation ◽  
Three Dimensional ◽  
Fixed Time ◽  
Impact Angle ◽  
Guidance System ◽  
Control Input ◽  
Guidance Law ◽  
The Stability ◽  
And Control

This paper presents an adaptive fixed-time guidance law for the three-dimensional interception guidance problem with impact angle constraints and control input saturation against a maneuvering target. First, a coupled guidance model formulated by the relative motion equation is established. On this basis, a fixed-time disturbance observer is employed to estimate the lumped disturbances. With the help of this estimation technique, the adaptive fixed-time sliding mode guidance law is designed to accomplish accurate interception. The stability of the closed-loop guidance system is proven by the Lyapunov method. Simulation results of different scenarios are executed to validate the effectiveness and superiority of the proposed guidance law.

Fixed-time three-dimensional guidance law with input constraint and actuator faults

2020 ◽  
pp. 095441002097197
Author(s):  
Peng Li ◽  
Qi Liu ◽  
Chen-Yu He ◽  
Xiao-Qing Liu
Keyword(s):  
Fault Tolerant ◽  
Sliding Mode ◽  
Input Saturation ◽  
Three Dimensional ◽  
Impact Angle ◽  
Actuator Faults ◽  
Input Constraint ◽  
Guidance Law ◽  
The Impact ◽  
Impact Angle Constraint

This paper investigates the three-dimensional guidance with the impact angle constraint, actuator faults and input constraint. Firstly, an adaptive three-dimensional guidance law with impact angle constraint is designed by using the terminal sliding mode control and nonhomogeneous disturbance observer. Then, in order to solve the problem of the input saturation and actuator faults, an adaptive anti-saturation fault-tolerant three-dimensional law is proposed by using the hyperbolic tangent function based on the passive fault-tolerant control. Finally, the effectiveness of the designed guidance laws is verified by using the Lyapunov function and simulation.

A generalized design method for three-dimensional guidance laws

2016 ◽  
Vol 231 (1) ◽  
pp. 47-60 ◽  
Author(s):  
Sheng Sun ◽  
Di Zhou ◽  
Jingyang Zhou ◽  
Kok Lay Teo
Keyword(s):  
Lyapunov Function ◽  
Sliding Mode ◽  
Three Dimensional ◽  
Line Of Sight ◽  
Generalized Function ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Target Acceleration ◽  
Guidance Laws ◽  
Proportional Navigation Guidance

The true proportional navigation guidance law, the augmented proportional navigation guidance law, or the adaptive sliding-mode guidance law, is designed based on the planar target-to-missile relative motion dynamics. By a proper construction of a nonlinear Lyapunov function for the line-of-sight angular rates in the three-dimensional guidance dynamics, it is shown that the three guidance laws mentioned above are able to ensure the asymptotic convergence of the angular rates as they are directly applied to the three-dimensional guidance environment. Furthermore, considering the missile autopilot dynamics as a first-order lag, we design three-dimensional nonlinear guidance laws by using the backstepping technique for three cases: (1) the target does not maneuver; (2) the information of target acceleration can be acquired; and (3) the target acceleration is not available but its bound is known a priori. In the first step of the backstepping design of the control law, there is no need to cancel the nonlinear coupling terms in the three-dimensional guidance dynamics in such way that the final expressions of the proposed guidance laws are significantly simplified. Thus, the proposed nonlinear Lyapunov function for the line-of-sight angular rates is a generalized function for designing three-dimensional guidance laws. Simulation results of a missile interception mission show that the proposed guidance laws are highly effective.

scholarly journals Profile-Tracking-Based Adaptive Guidance Law against Maneuvering Targets

2019 ◽  
Vol 2019 ◽  
pp. 1-17
Author(s):  
Jingshuai Huang ◽  
Hongbo Zhang ◽  
Guojian Tang ◽  
Weimin Bao
Keyword(s):  
Convergence Rate ◽  
Sliding Mode ◽  
Tracking Error ◽  
Small Neighborhood ◽  
Terminal Sliding Mode ◽  
Control Approach ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Adaptive Guidance ◽  
The One

For the terminal guidance problem of a missile intercepting a maneuvering target, a profile-tracking-based adaptive guidance law is proposed with inherent continuity in this paper. To flexibly and quantitatively control the convergence rate of the line-of-sight rate, a standard tracking profile is designed where the convergence rate is analytically given. Then, a nonsingular fast terminal sliding-mode control approach is used to track the profile. By estimating the square of the upper bound of target maneuver, an adaptive term is constructed to compensate the maneuver. Therefore, no information of target acceleration is required in the derived law. Stability analysis shows that the tracking error can converge to a small neighborhood of zero in finite time. Furthermore, a guidance-command-conversion scheme is presented to convert the law into the one appropriate for endoatmospheric interceptions. Simulation results indicate that the proposed law is effective and outperforms existing guidance laws.

Continuous reaching law based three-dimensional finite-time guidance law against maneuvering targets

2018 ◽  
Vol 41 (2) ◽  
pp. 321-339 ◽  
Author(s):  
Yu-Jie Si ◽  
Shen-Min Song
Keyword(s):  
Finite Time ◽  
Sliding Mode ◽  
Traditional Approach ◽  
Three Dimensional ◽  
Terminal Sliding Mode ◽  
Reaching Law ◽  
Closed Loop Systems ◽  
Guidance Law ◽  
Effective Performance ◽  
Guidance Laws

Three-dimensional finite-time guidance laws are proposed in this paper. Differing from the traditional approach that considers homing guidance problems as two identical and perpendicular channels, guidance laws proposed in this paper employ the coupled three-dimensional engagement dynamics to improve the guidance precision. A new reaching law is adopted to guarantee guidance laws continuous, which eliminates the chattering phenomenon caused by discontinuous terms. Moreover, the guidance law accelerates the convergence rate of closed-loop systems and avoids the singularity. Afterwards, the paper discusses the problem that the upper bound of the lumped uncertainty including the target information is unavailable. Therefore, to deal with this problem, another adaptive guidance law is presented, which can also guarantee the finite-time convergence of guidance systems. Numerical simulations have demonstrated that the two guidance laws have effective performance and outperform traditional terminal sliding mode guidance laws.

A robust hybrid nonlinear guidance law for intercepting a non-cooperative maneuvering target

2019 ◽  
Vol 124 (1273) ◽  
pp. 429-445
Author(s):  
Xiaodong Yan ◽  
Shi Lyu
Keyword(s):  
Control Method ◽  
Sliding Mode ◽  
Fixed Time ◽  
Small Region ◽  
Lower Sensitivity ◽  
Prescribed Performance ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Delay Control ◽  
Two Phases

ABSTRACTThis paper has proposed a new robust hybrid nonlinear guidance law, which accounts for a missile’s terminal line-of-sight (LOS) angle constraint, in order to intercept a non-cooperative maneuvering target. The proposed hybrid nonlinear guidance strategy consists of two phases; in the first phase, a guidance law named PIGL is derived from prescribed performance control and the inertial delay control method. In PIGL, a revised prescribed performance function is put forward, and a prescribed performance controller with unknown uncertainties is then derived. The controller smoothly drives both the LOS angle and its rate to a predesigned small region under unknown uncertainties that are induced by target’s maneuvers within a fixed time. Then, a guidance law named SIGL is activated, which is derived from sliding mode control and inertial delay control. By driving the desired sliding mode variable to zero within a finite time, the SIGL guidance law is able to achieve high terminal interception accuracy. The robustness of both of the proposed sub-guidance laws has been proved explicitly in this paper. The hybrid guidance law has the advantage of a tunable convergence rate of the LOS angle and the rate of the LOS angle at the beginning period, by which an excessive large initial maneuver can be avoided. Meanwhile, the hybrid guidance law also has the advantage of lower sensitivity to errors in the estimation of the time-to-go.

Design of 3-Dimensional Guidance Law of Missile Based on Discrete Sliding Mode

2013 ◽  
Vol 816-817 ◽  
pp. 976-980
Author(s):  
Nuan Wen ◽  
Zheng Hua Liu ◽  
Le Chang
Keyword(s):  
Discrete Time ◽  
Relative Motion ◽  
Sliding Mode ◽  
Dimensional Space ◽  
Three Dimensional ◽  
New Approach ◽  
3 Dimensional ◽  
Guidance Law ◽  
Guidance Laws ◽  
Three Dimensional Space

In this article, a new approach to design discrete-time sliding-mode guidance laws is presented based on the target-missile relative motion equation in three-dimensional space. This method significantly reduced system chattering and could be easily achieved on engineering. Furthermore, effectiveness of the proposed guidance laws is demonstrated through simulation by comparing with the traditional proportional guidance laws.

scholarly journals Cooperative Intercepting Guidance Law for Large Maneuvering Target with Impact Angle Constraint

2020 ◽  
Vol 38 (6) ◽  
pp. 1257-1265
Author(s):  
Zhengyu Guo ◽  
Chaolei Wang ◽  
Hang Qian ◽  
Zhiguo Han ◽  
Jingxian Zhang
Keyword(s):  
Finite Time ◽  
Sliding Mode ◽  
Three Dimensional ◽  
Impact Angle ◽  
Attack Angle ◽  
Lateral Acceleration ◽  
Terminal Sliding Mode ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Terminal Guidance

A distributed multi-missile cooperative guidance law based on the finite time theory is proposed to solve the terminal guidance problem of three-dimensional multi-missiles cooperative interception of large maneuvering target. According to the finite time consistency theory, an adaptive guidance law based on the integral sliding mode is designed to ensure that all missiles can reach the target at the same time in the terminal guidance process. The longitudinal and lateral acceleration of the line of sight are based on the guidance law of the fast terminal sliding mode surface. The terminal attack angle is constrained, so that the terminal attack Angle can reach the expected value in finite time. The simulation results show that the designed guidance law can achieve the cooperative attack on the maneuvering targets.

scholarly journals Target Tracking Enhancement by Three-Dimensional Cooperative Guidance Law Imposing Relative Interception Geometry

Aerospace ◽  
2020 ◽  
Vol 8 (1) ◽  
pp. 6
Author(s):  
Xiaoma Liu ◽  
Yang Han ◽  
Peng Li ◽  
Hongwu Guo ◽  
Wenqi Wu
Keyword(s):  
Target Tracking ◽  
Three Dimensional ◽  
Fixed Time ◽  
Target Range ◽  
Estimation Model ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Dynamic Strategy ◽  
Guidance Laws ◽  
Relative Geometry

The problem that two cooperative missiles intercept a maneuvering target while imposing a desired relative geometry is investigated in the paper. Firstly, a three-dimensional (3D) estimation model for cooperative target tracking is proposed and the observability of the missile-target range measurement is analyzed. In order to enhance the estimation performance, a two-level cooperative interception guidance architecture is proposed which combines a coordination algorithm with a novel 3D fixed-time convergent guidance law considering line of sight (LOS) angle constraints, such that the desired relative geometry can be imposed quickly and steadily by a dynamic strategy. The effectiveness and superiority of the proposed guidance law is evidenced through the numerical simulations comparing with other guidance laws.

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