scholarly journals A Novel INDI based Guidance Law for Fixed Wing Aircrafts: Derivation and Application

2022 ◽  
Author(s):  
Mengtang Li ◽  
Beichen Ding
Keyword(s):  
Control Method ◽  
Control Law ◽  
Control Methods ◽  
Guidance Control ◽  
Transformation Matrices ◽  
Guidance Law ◽  
Univariate Function ◽  
Mathematical Operations ◽  
Guidance Laws ◽  
Derivation Process

In this paper, we comprehensively present and derive two INDI principle based guidance laws for fixed wing aircrafts. More specifically, two control methods are mathematically derived in detail, where the first decouples the lateral and the longitudinal channels while the second takes the interactions into account. The cumbersome mathematical operations involved in the derivation process aim at reaching a more concise control method and also at providing the community with clearer physical concepts behind this formula. The reason for manipulating transformation matrices is to find a univariate function and to isolate the variable as a virtual input. Efficient and modular guidance control law is then permitted. Lastly, the proposed guidance methods are applied to a 6 dof nonlinear platform under various flight modes to demonstrate the feasibility and advantages.

scholarly journals A Novel INDI based Guidance Law for Fixed Wing Aircrafts: Derivation and Application

2022 ◽  
Author(s):  
Mengtang Li ◽  
Beichen Ding
Keyword(s):  
Control Method ◽  
Control Law ◽  
Control Methods ◽  
Guidance Control ◽  
Transformation Matrices ◽  
Guidance Law ◽  
Univariate Function ◽  
Mathematical Operations ◽  
Guidance Laws ◽  
Derivation Process

In this paper, we comprehensively present and derive two INDI principle based guidance laws for fixed wing aircrafts. More specifically, two control methods are mathematically derived in detail, where the first decouples the lateral and the longitudinal channels while the second takes the interactions into account. The cumbersome mathematical operations involved in the derivation process aim at reaching a more concise control method and also at providing the community with clearer physical concepts behind this formula. The reason for manipulating transformation matrices is to find a univariate function and to isolate the variable as a virtual input. Efficient and modular guidance control law is then permitted. Lastly, the proposed guidance methods are applied to a 6 dof nonlinear platform under various flight modes to demonstrate the feasibility and advantages.

Application of optimal control law to laser guided bomb

2018 ◽  
Vol 122 (1251) ◽  
pp. 785-797
Author(s):  
Takieddine Mouada ◽  
Milos V. Pavic ◽  
Bojan M. Pavkovic ◽  
Sasa Z. Zivkovic ◽  
Mirko S. Misljen
Keyword(s):  
Noise Removal ◽  
Control Law ◽  
State Variables ◽  
Linear Quadratic ◽  
State Variable ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Differential Game Theory ◽  
Miss Distance ◽  
Guidance Laws

ABSTRACTThe paper presents a laser guided bomb guidance law based on the linear quadratic differential game theory, where a case of two perpendicular planes with two state variables in each plane has been considered. The Kalman filtering method has been used for noise removal from the measured signals and for estimation of the missing state variable values needed for the optimal guidance law. Optimisation has been conducted with respect to minimisation of the performance index. Comparative analysis of different guidance laws is done. A statistical analysis is performed to obtain the terminal miss distance in dependence on total flight time.

scholarly journals Retraction notice

SIMULATION ◽  
2015 ◽  
Vol 91 (8) ◽  
pp. NP1-NP1 ◽  
Keyword(s):  
Differential Game ◽  
Linear Quadratic ◽  
Guidance Control ◽  
Guidance Law ◽  
Retraction Notice ◽  
Guidance Laws

At the request of the Editor(s) and the Publisher and author(s), the following article “Differential Game Guidance Law for a Kinetic Kill Vehicle and Its Simulation” by Xing-Yuan Xu, Xiao-Na Song and Yuan-Li Cai. Simulation, first published June 10, 2015, DOI 10.1177/0037549715588839 . has been retracted. The Editor has judged that the paper plagiarized the following article, and the authors have agreed to their paper being retracted: “Linear Quadratic Guidance Laws for Imposing a Terminal Intercept Angle” by Vitaly Shaferman and Tal Shima, Journal of Guidance, Control, and Dynamics, Vol. 31, No. 5, DOI 10.2514/1.32836.

scholarly journals Research on Joint Control of On-Ramp Metering and Mainline Speed Guidance in the Urban Expressway Based on MPC and Connected Vehicles

2020 ◽  
Vol 2020 ◽  
pp. 1-8
Author(s):  
Lina Wu ◽  
Yusheng Ci ◽  
Yichen Sun ◽  
Wei Qi
Keyword(s):  
Traffic Safety ◽  
Traffic Control ◽  
Control Method ◽  
Operational Efficiency ◽  
Ramp Metering ◽  
Joint Control ◽  
Connected Vehicles ◽  
Control Methods ◽  
Guidance Control ◽  
Urban Expressway

The traffic operational efficiency of the urban expressway system will affect one of the entire cities. Moreover, the idea that traffic control can improve the traffic operational efficiency of the urban expressway system has been fully confirmed. At present, the main control methods include on-ramp metering and speed guidance control. However, there is a gap in using these two control methods together, such as unclear application conditions and unsystematic methods. In this paper, on-ramp metering and speed guidance control are combined effectively. Based on the research of METANET macroscopic traffic flow model and model predictive control (MPC), a novel joint control method based on MPC and connected vehicles (CVs) for on-ramp metering and speed guidance control of the urban expressway is proposed. Finally, the simulation results show that the proposed control method can effectively improve the traffic efficiency and traffic safety.

scholarly journals THE USE OF MOBILE CONTROL METHODS FOR STABILIZATION OF A SPACECRAFT WITH AEROMAGNETIC DEORBITING SYSTEM

2019 ◽  
Vol 6 (125) ◽  
pp. 41-54
Author(s):  
Anatolii Alpatov ◽  
Erik Lapkhanov
Keyword(s):  
Executive Control ◽  
Permanent Magnets ◽  
Control Method ◽  
Electrical Energy ◽  
Angular Motion ◽  
Control Law ◽  
Control Methods ◽  
Advantages And Disadvantages ◽  
Electromagnetic Control ◽  
Control Devices

The search for optimal control algorithms for spacecrafts is one of the key areas in rocket and space technology. Taking into account certain restrictions and requirements in a specific space mission, the selection of certain executive devices of the spacecraft is carried out and the corresponding control law is synthesized. One of such space missions is the providing of angular motion stabilization of a utilized spacecraft with aeromagnetic deorbiting system. The stabilization of spacecraft angular motion is needed for the orientation of aerodynamic element perpendicular to the vector of atmosphere dynamic flux with the aim of increasing of aerodynamic braking force. In this mission, the main optimization criterion is the minimization of the on-board electrical energy consumption which is needed for the control of angular motion. The original construction of the aeromagnetic deorbiting system consists of aerodynamic flat sails element and executive control devices with permanent magnets. However, not all spacecraft can be equipped with additional executive control devices with permanent magnets. That’s why with the aim of expansion of aeromagnetic deorbiting system application, using extra source of electromagnetic control executive devices is proposed in this research.The purpose of the article is the search of the control law which provides minimal consumption of electrical on-board energy by electromagnetic control executive devices during long-term deorbiting mission. For satisfying this criterion of optimization using of mobile control methods to orientate the spacecraft with aeromagnetic deorbiting system are proposed in this investigation. Computer modeling of orbital motion of spacecraft with aeromagnetic deorbiting system show the efficiency of using proposed mobile methods for angular motion control which realized by electromagnetic devices – magnetorquers. It has been showed that because of using mobile control method consumption of on-board electrical energy significantly less than with classical approach. The advantages and disadvantages have been determined.

Integrated Guidance, Control and Maneuver for Anti-Vessel Missiles Based on Backstepping Method

2011 ◽  
Vol 69 ◽  
pp. 126-131
Author(s):  
Cong Ying Li ◽  
Jin Yong Yu ◽  
Lei Han ◽  
Wen Guang Zhang
Keyword(s):  
Sliding Mode ◽  
Integrated Design ◽  
Control Law ◽  
Backstepping Method ◽  
Guidance Control ◽  
Guidance And Control ◽  
Guidance Law ◽  
Maneuvering Targets ◽  
And Control ◽  
Accuracy Performance

Integrated guidance, control and maneuver for anti-vessel missiles against vessel targets was studied. Firstly, the integrated guidance and autopilot model of the yaw plane was formulated, the guidance and control law was designed based on the backstepping method and sliding mode control theory. For the unavailable information of the vessel target, an estimating method was given. Integration of guidance and maneuver was realized based on a new guidance law. Finally, to verify the effectiveness and rightness of the integrated design scheme, the simulation of some anti-vessel missile against maneuvering targets had been made, the simulation results showed that high accuracy performance of guidance and control system can be got.

A Novel Switching Control Method for Hypersonic Flying Vehicle

2014 ◽  
Vol 668-669 ◽  
pp. 419-422 ◽  
Author(s):  
Juan Wang ◽  
Ji Long Liu ◽  
Min Wang ◽  
Yu Zhe Wang
Keyword(s):  
Attitude Control ◽  
Control Method ◽  
Rapid Development ◽  
Switching Control ◽  
Control Law ◽  
Control Methods ◽  
Control Performance ◽  
Precise Control ◽  
Simulation Results

With the rapid development of aeronautics technology, hypersonic flying vehicle is playing an increasingly important role, yet control methods on such vehicle were stilled confined with classical PID (proportional, integration and differentiation) or its variations. In order to have better control performance, a switching control method was used to design the attitude control law for hypersonic missile, which guaranteed higher angle precise control than PID. Simulation results showed the effectiveness and the superiority of the proposed switching methods over the classical PID and other typical switching methods.

Fault Tolerant Guidance of Under-Actuated Satellite Formation Flying Using Inter-Vehicle Coulomb Force

2019 ◽  
Vol 2 (1) ◽  
pp. 43-52
Author(s):  
Alireza Alikhani ◽  
Safa Dehghan M ◽  
Iman Shafieenejad
Keyword(s):  
Fault Tolerance ◽  
Formation Flying ◽  
Fault Tolerant ◽  
Coulomb Force ◽  
Control Law ◽  
Triangular Form ◽  
Satellite Formation Flying ◽  
Satellite Formation ◽  
Guidance Law ◽  
Tolerance Approach

In this study, satellite formation flying guidance in the presence of under actuation using inter-vehicle Coulomb force is investigated. The Coulomb forces are used to stabilize the formation flying mission. For this purpose, the charge of satellites is determined to create appropriate attraction and repulsion and also, to maintain the distance between satellites. Static Coulomb formation of satellites equations including three satellites in triangular form was developed. Furthermore, the charge value of the Coulomb propulsion system required for such formation was obtained. Considering Under actuation of one of the formation satellites, the fault-tolerance approach is proposed for achieving mission goals. Following this approach, in the first step fault-tolerant guidance law is designed. Accordingly, the obtained results show stationary formation. In the next step, tomaintain the formation shape and dimension, a fault-tolerant control law is designed.

scholarly journals Disturbance compensation-based output feedback adaptive control for shape memory alloy actuator system

2021 ◽  
Vol 18 (1) ◽  
pp. 172988142199399
Author(s):  
Xiaoguang Li ◽  
Bi Zhang ◽  
Daohui Zhang ◽  
Xingang Zhao ◽  
Jianda Han
Keyword(s):  
Adaptive Control ◽  
Shape Memory Alloy ◽  
Shape Memory ◽  
Control Method ◽  
Control Law ◽  
Reference Trajectory ◽  
Disturbance Compensation ◽  
Comparison Results ◽  
Control Scheme ◽  
Actuator System

Shape memory alloy (SMA) has been utilized as the material of smart actuators due to the miniaturization and lightweight. However, the nonlinearity and hysteresis of SMA material seriously affect the precise control. In this article, a novel disturbance compensation-based adaptive control scheme is developed to improve the control performance of SMA actuator system. Firstly, the nominal model is constructed based on the physical process. Next, an estimator is developed to online update not only the unmeasured system states but also the total disturbance. Then, the novel adaptive controller, which is composed of the nominal control law and the compensation control law, is designed. Finally, the proposed scheme is evaluated in the SMA experimental setup. The comparison results have demonstrated that the proposed control method can track reference trajectory accurately, reject load variations and stochastic disturbances timely, and exhibit satisfactory robust stability. The proposed control scheme is system independent and has some potential in other types of SMA-actuated systems.

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.

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