APPLICATION OF THE TAGUCHI QUALITY METHOD TO DESIGN NAVIGATION CONSTANTS THAT ARE ROBUST TO TARGET MANEUVERS

2013 ◽  
Vol 37 (2) ◽  
pp. 231-246
Author(s):  
Chien-Chun Kung ◽  
Feng-Lung Chiang ◽  
Ciann-Dong Yang
Keyword(s):  
Quality Control ◽  
Missile Guidance ◽  
Time Constants ◽  
Control Approach ◽  
Guidance Law ◽  
Simulation Results ◽  
Noise Factors ◽  
Guidance Laws

The object of this paper is to present a quality control approach to design the navigation constants for missile guidance law that are robust for target’s maneuverability and missile’s performance. Target’s maneuvers and missile's time constants are considered to be noise factors and Taguchi Quality Method (TQM) is used to conduct matrix experiments and determine the robust navigation constants. From the simulation results for three kinds of guidance laws, we find that robust navigation constants have a greater ability to enhance the interception of targets that are performing uncertain maneuvers with less interception time and smaller miss distances in the hitting phase.

Design of finite-time guidance law based on observer and head-pursuit theory

2021 ◽  
pp. 095441002098456
Author(s):  
Chenqi Zhu
Keyword(s):  
Finite Time ◽  
Three Dimensional ◽  
Hypersonic Vehicle ◽  
Two Dimensional ◽  
Dimensional Model ◽  
Reaching Law ◽  
Guidance Law ◽  
Fast Power ◽  
Simulation Results ◽  
Guidance Laws

In order to improve the guiding accuracy in intercepting the hypersonic vehicle, this article presents a finite-time guidance law based on the observer and head-pursuit theory. First, based on a two-dimensional model between the interceptor and target, this study applies the fast power reaching law to head-pursuit guidance law so that it can alleviate the chattering phenomenon and ensure the convergence speed. Second, target maneuvers are considered as system disturbances, and the head-pursuit guidance law based on an observer is proposed. Furthermore, this method is extended to a three-dimensional case. Finally, comparative simulation results further verify the superiority of the guidance laws designed in this article.

Two composite guidance laws based on the backstepping control and disturbance observers with autopilot lag

2019 ◽  
Vol 41 (10) ◽  
pp. 2957-2969 ◽  
Author(s):  
Chaoyuan Man ◽  
Zhenxing Zhang ◽  
Shihua Li
Keyword(s):  
Disturbance Observer ◽  
Three Dimensional ◽  
Simulation Studies ◽  
Missile Guidance ◽  
Nonlinear Disturbance Observer ◽  
First Order ◽  
Guidance Law ◽  
Control Scheme ◽  
Backstepping Controller ◽  
Guidance Laws

A composite three-dimensional (3D) missile guidance law is proposed for manoeuvering targets with the consideration of the first-order autopilot dynamics without any linearization. This guidance law consists of a backstepping controller and a feedforward compensation based on disturbance observers. In this control scheme, the unknown target acceleration is regarded as part of the lumped disturbance, estimated by a disturbance observer, and then feedforward compensated. The backstepping controller is introduced to deal with unmatched disturbances. Moreover, both the nonlinear disturbance observer (NDOB) and the generalized proportional integral observer (GPIO) are employed in the derivation. Simulation studies demonstrate the effectiveness of the proposed guidance law, and compare the guidance performance of the two composite guidance laws with different disturbance observers.

Evaluation of Guidance Laws Performance Sing Genetic Algorithm

2014 ◽  
Vol 598 ◽  
pp. 723-730
Author(s):  
Mohamed Zakaria ◽  
Talaat Ibrahim ◽  
Alaa El Din Sayed Hafez ◽  
Hesham Abdin
Keyword(s):  
Genetic Algorithm ◽  
Differential Geometry ◽  
Standard Deviation ◽  
Optimization Process ◽  
Line Of Sight ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Simulation Results ◽  
Miss Distance ◽  
Guidance Laws

Several conditions affect the performance of guidance law like target parameters or delayed line of sight rate. A variable navigation ratio is used to enhance the performance of guidance law. In this paper a Genetic Algorithm is used to formulate different forms of variable gains and measure the miss distance. An optimization process is running to find the minimum miss distance. The average values and standard deviation of miss distance for all genetic algorithm individuals are calculated to measure the performance and robustness of guidance law. Two guidance laws are considered proportional navigation (PN) and differential geometry (DG). The simulation results show that the proportional navigation is superior to differential geometry performance in the presence of delayed line of sight rate.

Optimal strategy for target protection with a defender in the pursuit-evasion scenario

2018 ◽  
Vol 15 (3) ◽  
pp. 289-301
Author(s):  
Qilong Sun ◽  
Naiming Qi ◽  
Mingying Huo
Keyword(s):  
Optimal Strategy ◽  
First Order ◽  
Pursuit Evasion ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Evasion Strategy ◽  
Simulation Results ◽  
Guidance Laws

The conflict among three players, an attacker, a defender, and a target, in the pursuit-evasion strategy context is investigated. The problem is derived for a defender launching from the target with the assumption that the guidance laws of the attacker and defender are linear in form. During the endgame, the target lures the attacker close to the defender based on the attacker’s reaction to the target. Two kinds of optimal guidance laws for protecting the target from the attacker are presented first. Showing that the two kinds of guidance laws are flawed, a new optimal guidance law is subsequently derived. Considering that the players’ control efforts are bounded by reality, the relevant parameters corresponding to the optimal guidance laws also need to be analyzed. For adversaries obeying first-order dynamics, the performance of the guidance laws is simulated for different parameters, and under reasonable parameter choices, the simulation results show that the new optimal guidance law can enable the target to assist the defender in effectively intercepting the attacker.

An Improved Integral Proportional Guidance Law Based on Optimization and Variable Proportional Factors

2012 ◽  
Vol 203 ◽  
pp. 41-45 ◽  
Author(s):  
Guan Tong Yang ◽  
Sheng Jing Tang ◽  
Jie Guo ◽  
Da Lin Zhu
Keyword(s):  
Optimization Scheme ◽  
Image Guided ◽  
Guidance Law ◽  
Simulation Results ◽  
Guidance Laws

For image guided missile, in order to avoid frame collision, the maximum needed frame-angle of the seeker should not exceed the maximum available frame-angle in flight. Subjected to diameter and volume of the seeker, the required frame-angle needs to be reduced. By combination signal of frame-angle, three different improved guidance laws are discussed. By using of special developed optimization scheme, the integral proportional guidance is selected finally for its best effect. For purpose of reducing required overload of the missile, further improvement of the guidance law is generated by using variable proportional factors. The simulation results show that after using of the final improved guidance law, the maximum required frame-angle is reduced by 1.5, the required overload of the missile at the beginning of tracking is reduced from 5.8 to 2.4. According to the results, the effectiveness of the improved guidance law is verified.

Trajectory shaping guidance law design using constraint-combining multiplier

2021 ◽  
pp. 095441002098637
Author(s):  
Min-Guk Seo ◽  
Chang-Hun Lee ◽  
Tae-Hun Kim
Keyword(s):  
Design Method ◽  
Impact Angle ◽  
State Variables ◽  
Flight Trajectory ◽  
Potential Significance ◽  
Guidance Law ◽  
Terminal Constraints ◽  
The Impact ◽  
Guidance Laws ◽  
Impact Angle Constraint

A new design method for trajectory shaping guidance laws with the impact angle constraint is proposed in this study. The basic idea is that the multiplier introduced to combine the equations for the terminal constraints is used to shape a flight trajectory as desired. To this end, the general form of impact angle control guidance (IACG) is first derived as a function of an arbitrary constraint-combining multiplier using the optimal control. We reveal that the constraint-combining multiplier satisfying the kinematics can be expressed as a function of state variables. From this result, the constraint-combining multiplier to achieve a desired trajectory can be obtained. Accordingly, when the desired trajectory is designed to satisfy the terminal constraints, the proposed method directly can provide a closed form of IACG laws that can achieve the desired trajectory. The potential significance of the proposed result is that various trajectory shaping IACG laws that can cope with various guidance goals can be readily determined compared to existing approaches. In this study, several examples are shown to validate the proposed method. The results also indicate that previous IACG laws belong to the subset of the proposed result. Finally, the characteristics of the proposed guidance laws are analyzed through numerical simulations.

3D Nonlinear Guidance Law for Bank-to-Turn Missile

2011 ◽  
Vol 317-319 ◽  
pp. 727-733
Author(s):  
Shuang Chun Peng ◽  
Liang Pan ◽  
Tian Jiang Hu ◽  
Lin Cheng Shen
Keyword(s):  
Three Dimensional ◽  
Lyapunov Theory ◽  
Line Of Sight ◽  
Rate Model ◽  
Guidance Law ◽  
Terminal Constraints ◽  
Guidance Laws ◽  
3D Guidance ◽  
Guidance Model ◽  
Vector Description

A new three-dimensional (3D) nonlinear guidance law is proposed and developed for bank-to-turn (BTT) with motion coupling. First of all, the 3D guidance model is established. In detail, the line-of-sight (LOS) rate model is established with the vector description method, and the kinematics model is divided into three terms of pitching, swerving and coupling, then by using the twist-based method, the LOS direction changing model is built for designing the guidance law with terminal angular constraints. Secondly, the 3D guidance laws are designed with Lyapunov theory, corresponding to no terminal constraints and terminal constraints, respectively. And finally, the simulation results show that the proposed guidance law can effectively satisfy the guidance precision requirements of BTT missile.

SDRE missile guidance law

2010 ◽  
Author(s):  
Feng Tyan ◽  
Jeng Fu Shen
Keyword(s):  
Missile Guidance ◽  
Guidance Law

scholarly journals A Framework of Cloud Model Similarity-Based Quality Control Method in Data-Driven Production Process

2020 ◽  
Vol 2020 ◽  
pp. 1-10
Author(s):  
Sheng Hu ◽  
Shuanjun Song ◽  
Wenhui Liu
Keyword(s):  
Quality Control ◽  
Production Process ◽  
Control Method ◽  
Cloud Model ◽  
Data Driven ◽  
Monitoring Method ◽  
Control Approach ◽  
Acceptable Method ◽  
And Performance ◽  
Model Similarity

Considering the problem that the process quality state is difficult to analyze and monitor under manufacturing big data, this paper proposed a data cloud model similarity-based quality fluctuation monitoring method in data-driven production process. Firstly, the randomness of state fluctuation is characterized by entropy and hyperentropy features. Then, the cloud pool drive model between quality fluctuation monitoring parameters is built. On this basis, cloud model similarity degree from the perspective of maximum fluctuation border is defined and calculated to realize the process state analysis and monitoring. Finally, the experiment is conducted to verify the adaptability and performance of the cloud model similarity-based quality control approach, and the results indicate that the proposed approach is a feasible and acceptable method to solve the process fluctuation monitoring and quality stability analysis in the production process.

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