Nonlinear differential geometric guidance for maneuvering target

Ye, Jikun; Lei, Humin; Xue, Dongfeng; Li, Jiong; Shao, Lei

doi:10.1109/jsee.2012.00092

Cited by 13 publications

(10 citation statements)

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“…Figure 4 demonstrates the relationship of missile–target motion, where

represent the velocity of missile and target, respectively,

are the trajectory inclination angular of missile and target, respectively, and

is the distance between missile and target. The relative motion equation between missile and target is given as follows:

where

, and

represent the command acceleration of missile and target, respectively [ 26 ].…”

Section: System Modeling and Problem Formulationmentioning

confidence: 99%

Backstepping Sliding Mode Control for Radar Seeker Servo System Considering Guidance and Control System

Wang

Lei

et al. 2018

Sensors

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This paper investigates the design of a missile seeker servo system combined with a guidance and control system. Firstly, a complete model containing a missile seeker servo system, missile guidance system, and missile control system (SGCS) was creatively proposed. Secondly, a designed high-order tracking differentiator (HTD) was used to estimate states of systems in real time, which guarantees the feasibility of the designed algorithm. To guarantee tracking precision and robustness, backstepping sliding-mode control was adopted. Aiming at the main problem of projectile motion disturbance, an adaptive radial basis function neural network (RBFNN) was proposed to compensate for disturbance. Adaptive RBFNN especially achieves online adjustment of residual error, which promotes estimation precision and eliminates the “chattering phenomenon”. The boundedness of all signals, including estimation error of high-order tracking differentiator, was especially proved via the Lyapunov stability theory, which is more rigorous. Finally, in considered scenarios, line of sight angle (LOSA)-tracking simulations were carried out to verify the tracking performance, and a Monte Carlo miss-distance simulation is presented to validate the effectiveness of the proposed method.

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“…Figure 4 demonstrates the relationship of missile–target motion, where

represent the velocity of missile and target, respectively,

are the trajectory inclination angular of missile and target, respectively, and

is the distance between missile and target. The relative motion equation between missile and target is given as follows:

where

, and

represent the command acceleration of missile and target, respectively [ 26 ].…”

Section: System Modeling and Problem Formulationmentioning

confidence: 99%

Backstepping Sliding Mode Control for Radar Seeker Servo System Considering Guidance and Control System

Wang

Lei

et al. 2018

Sensors

Self Cite

View full text Add to dashboard Cite

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“…Dhananjay et al [10] investigated the capturability of the planar DGGL. Ye et al [11] proposed a nonlinear DGGL based on nonlinear control theory to handle the influence caused by the target maneuvering acceleration. Unlike Chou et al s' method, Ariff et al [12] proposed a novel differential geometric guidance algorithm based on the involute of the target, and White et al [13] studied planar interception engagement and presented a two-dimensional (2D) geometric guidance law which was thought to be better than classic proportional navigation (PN).…”

Section: Introductionmentioning

confidence: 99%

Performance analysis of three-dimensional differential geometric guidance law against low-speed maneuvering targets

Chen

2018

Astrodyn

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The performance of the three-dimensional differential geometric guidance law with proportional navigation formation against a target maneuvering arbitrarily with time-varying normal acceleration is thoroughly analyzed using the Lyapunov-like approach. The validation of this guidance law is firstly proved, and then the performance issues such as capturability, heading error control efficiency, line of sight rate convergence, and commanded acceleration requirement are analyzed, under the condition that the missile is initially flying toward the target with a speed advantage. It is proved that an intercept can occur and the line of sight rate and missile commanded acceleration can be limited in certain ranges, if the initial heading error is small and the navigation gain is sufficiently large. The nonlinear relative dynamics between the missile and the target is taken into full account, and the analysis process is simple and intuitive, due to the use of a convenient line of sight rotating coordinate system. Finally, the new theoretical findings are validated by numerical simulations.

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“…The proportional navigation (PN) has been widely used because of its simplicity, ease of implementation, and effectiveness in practical systems [1][2][3][4][5]. Due to the fact that end of the line of sight (LOS) angular rate rapidly rotating easily leads to overload saturation when PN against maneuvering target, many scholars modified traditional PN guidance law to improve the performance of guidance law [6][7][8][9].…”

Section: Introductionmentioning

confidence: 99%

Novel Fractional Order Calculus Extended PN for Maneuvering Targets

Lei

2017

International Journal of Aerospace Engineering

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Based on the theory of fractional order calculus (FOC), a novel extended proportional guidance (EPN) law for intercepting the maneuvering target is proposed. In the first part, considering the memory function and filter characteristic of FOC, the novel extended PN guidance algorithm is developed based on the conventional PN after introducing the properties and operation rules of FOC. Further, with the help of FOC theory, the average load and ballistics characteristics of proposed guidance law are analyzed. Then, using the small offset kinematic model, the robustness of the new guidance law against autopilot parameters is studied theoretically by analyzing the sensitivity of the closed loop guidance system. At last, representative numerical results show that the designed guidance law obtains a better performance than the traditional PN for maneuvering target.

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Nonlinear differential geometric guidance for maneuvering target

Cited by 13 publications

References 0 publications

Backstepping Sliding Mode Control for Radar Seeker Servo System Considering Guidance and Control System

Backstepping Sliding Mode Control for Radar Seeker Servo System Considering Guidance and Control System

Performance analysis of three-dimensional differential geometric guidance law against low-speed maneuvering targets

Novel Fractional Order Calculus Extended PN for Maneuvering Targets

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