A finite-time-convergent composite guidance law with strong fault-tolerant performance

Chen, Feng; He, Guangjun; He, Qi

doi:10.1177/0954410018793280

Cited by 8 publications

(5 citation statements)

References 31 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…To design an interception trajectory that satisfies the specific LOS angle constraint, only the interception situation of the longitudinal plane is analyzed. The interceptor as well as the target is regarded as a mass point, and the engagement geometry of the interceptor and the target is shown in Figure 1 [22].…”

Section: Interception Model For Low-altitude Targetsmentioning

confidence: 99%

A Composite Guidance Law for Suppressing Measurement Noise of LOS Angular Rate

Feng

2019

Mathematical Problems in Engineering

Self Cite

View full text Add to dashboard Cite

To effectively intercept a low-altitude target in clutter background, a nonsingular fast terminal sliding mode guidance law is designed. The designed guidance law can fully exploit the fast convergence characteristics of linear sliding mode control and the finite-time-convergent characteristics of terminal sliding mode control to ensure that the line-of-sight (LOS) angle converges to a desired angle in a limited time at a faster rate. Utilizing the smooth switching characteristics of the hyperbolic tangent function similar to the saturation function, a finite-time-convergent differentiator is designed. Meanwhile, a new finite-time-convergent disturbance observer designed on the tracking differentiator can effectively track the ideal LOS angular rate, suppress the measurement noise, and make a smooth estimation of the target maneuvering acceleration in clutter background. Combining the estimated value of the disturbance observer, the sign function with switch coefficient is introduced to design a composite nonsingular fast terminal sliding mode guidance law. The simulation results show that the composite guidance law can not only effectively suppress the measurement noise of the LOS angular rate and improve the accuracy of low-altitude target intercepting, but also greatly reduce the energy consumption in the interception process.

show abstract

Section: Interception Model For Low-altitude Targetsmentioning

confidence: 99%

A Composite Guidance Law for Suppressing Measurement Noise of LOS Angular Rate

Feng

2019

Mathematical Problems in Engineering

Self Cite

View full text Add to dashboard Cite

show abstract

“…In References [10,[17][18][19][20], an ESO is used to observe and compensate for the target maneuver in real time, solve the problem of excessive overload in the terminal guidance process effectively, and provide the flight vehicle with a higher interception accuracy. References [7,21,22] adopt an FTDO to estimate the target maneuver. The guidance laws and observers in the above references can accurately hit targets and accurately estimate target maneuvers under normal adversarial scenarios.…”

Section: Introductionmentioning

confidence: 99%

Design of Convergent and Accurate Guidance Law with Finite Time in Complex Adversarial Scenarios

Ding,

Wang,

et al. 2024

Aerospace

View full text Add to dashboard Cite

The target can deceive the flight vehicle by releasing an infrared decoy to make the line-of-sight (LOS) angle rate deflect greatly, thus causing the flight vehicle to miss the target. Therefore, in order to accurately strike the target in complex adversarial scenarios, this paper proposes a finite-time convergence guidance law (FTCG) combined with a finite-time disturbance observer (FTDO). The complex adversarial scenario is established by combining the relative motion model between the flight vehicle and the target and the motion model of the infrared decoy. Based on this, considering the dynamic characteristic of the flight vehicle’s autopilot, a guidance model is obtained. Utilizing sliding mode control theory and finite-time control theory, an FTCG of the LOS angle rate is designed. Then, the finite-time convergence of the guidance law is proved and the total convergence time is derived. Finally, for the target maneuvering that is difficult to measure in the guidance law, an FTDO is used to estimate and compensate for the target maneuvering in the guidance law. Simulation results show that the FTCG can make the LOS angle rate quickly converge and accurately strike the target in different scenarios, with a good guidance accuracy and robustness. Compared with the sliding mode guidance law (SMGL) and the adaptive sliding mode guidance law (ASMGL) based on an extended state observer (ESO), the advantages of the designed guidance law are illustrated. Finally, FTCG is extended to be three dimensional and compared with the proportional navigation guidance law (PNG) to further illustrate its effectiveness in a three-dimensional coordinate system.

show abstract

“…However, only in the last few years there has been some research work on fault tolerant control (FTC) combined with integrated guidance and control (IGC). Such as actuator faults [13][14][15] , sensor fault [16] , the magnitude loss fault of the guidance command [17] , fin failures [18] .In two references about STT missile, for time-varying actuator faults and multi-source uncertainties, a reconfigurable IGC structure was constructed by Wang et al, and guaranteed high hit accuracy of the missile [14] . In [15], an impact angle constrained fuzzy fault-tolerant integrated guidance control method was proposed by Guo et al for unstable aerodynamics and multiple disturbances.…”

Section: Introductionmentioning

confidence: 99%

Reinforcement Learning Adaptive Risk-Sensitive Fault-Tolerant IGC Method for a Class of STT Missile with Non-Affine Characteristics, Stochastic Disturbance and Unknown Uncertainties

Wang

Hao

2023

Preprint

View full text Add to dashboard Cite

In this paper, a novel reinforcement learning adaptive risk-sensitive fault-tolerant stochastic non-affine integrated guidance and control (NAIGC) method is proposed for a class of skid-to-turn (STT) missiles. The cost standard of the risk-sensitive index we coveted can be arbitrarily small, ensured by solving a specific inequality. Firstly, an extended integration system is introduced to solve the challenging control problem posed by the non-affine form of the control signal, taking into account the non-affine nature in the missile. Secondly, for random noise and unknown non-linearities in NAIGC systems, a reinforcement learning actor-critic adaptive risk-sensitive control method is proposed to ensure the input-state stability of the system. Subsequently, hyperbolic tangent functions and adaptive boundary estimation are used to reduce disturbance-induced jitter and actuator fault-induced bias in the control system. In addition, the proposed control strategy improves the missile's interception performance against maneuvering targets and reduces the conservatism of existing adaptive robust control methods. Ultimately, not only is the stability of the NAIGC closed-loop system demonstrated using Lyapunov theory, but the effectiveness and superiority of the method is also verified through numerical simulations.

show abstract

A finite-time-convergent composite guidance law with strong fault-tolerant performance

Cited by 8 publications

References 31 publications

A Composite Guidance Law for Suppressing Measurement Noise of LOS Angular Rate

A Composite Guidance Law for Suppressing Measurement Noise of LOS Angular Rate

Design of Convergent and Accurate Guidance Law with Finite Time in Complex Adversarial Scenarios

Reinforcement Learning Adaptive Risk-Sensitive Fault-Tolerant IGC Method for a Class of STT Missile with Non-Affine Characteristics, Stochastic Disturbance and Unknown Uncertainties

Contact Info

Product

Resources

About