End-game guidance laws for dual-control missiles

2005 ◽  
Vol 219 (2) ◽  
pp. 157-170 ◽  
Author(s):  
T Shima ◽  
O M Golan
Keyword(s):  
Flight Control ◽  
Performance Criterion ◽  
Guidance System ◽  
Single Shot ◽  
Dual Control ◽  
Monte Carlo Simulation Study ◽  
Guidance Law ◽  
Noisy Measurements ◽  
And Control ◽  
Guidance Laws

New guidance laws derived for a dual-control missile are studied. Their performance is compared with that of a conventional guidance system with flight control that distributes the commands among the two control channels. A Monte Carlo simulation study is performed where the target executes random evasive manoeuvres. The interceptor, represented by linear high-order manoeuvring dynamics with bounded forward and aft controls, acquires noisy measurements and uses a state estimator. Using the single-shot kill probability as a performance criterion, the superiority of the new guidance and control architecture is shown. It is also shown that the best performance is obtained by the bounded controls differential game guidance law. Sensitivity to the selection of the interceptor first-order time constant, a design parameter in the guidance law derivation, is also investigated.

A Review of Guidance Laws Applicable to Unmanned Underwater Vehicles

2003 ◽  
Vol 56 (1) ◽  
pp. 15-29 ◽  
Author(s):  
W. Naeem ◽  
R. Sutton ◽  
S. M. Ahmad ◽  
R. S. Burns
Keyword(s):  
Autonomous Underwater Vehicles ◽  
Underwater Vehicles ◽  
Guidance System ◽  
Unmanned Underwater Vehicles ◽  
Guidance And Control ◽  
Autonomous Operation ◽  
Guidance Law ◽  
Guidance Strategies ◽  
And Control ◽  
Guidance Laws

The main problem in bringing autonomy to any vehicle lies in the design of a suitable guidance law. For truly autonomous operation, the vehicle needs to have a reliable Navigation, Guidance and Control (NGC) system of which the guidance system is the key element that generates suitable trajectories to be followed. In this review paper, various guidance laws found in the literature and their relevance to autonomous underwater vehicles (AUVs) are discussed. Since existing guidance laws for underwater vehicles have emulated from tactical airborne missile systems, a number of approaches for the missile guidance systems are considered. Finally, potential guidance strategies for AUVs are proposed.

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.

Sliding mode guidance for impact time and angle constraints

2017 ◽  
Vol 232 (16) ◽  
pp. 2961-2977 ◽  
Author(s):  
Shashi Ranjan Kumar ◽  
Debasish Ghose
Keyword(s):  
Constant Velocity ◽  
Sliding Mode ◽  
Impact Angle ◽  
Time Error ◽  
Impact Time ◽  
Guidance Law ◽  
Terminal Constraints ◽  
Noisy Measurements ◽  
The Impact ◽  
Guidance Laws

This paper proposes a guidance strategy, which caters to both impact angle and impact time terminal constraints. This guidance scheme is based on switching between impact time and impact angle guidance laws. Unlike the existing impact time guidance laws, the proposed guidance strategy takes into account the curvature of the trajectory due to requirement of impact angle. The guidance law is derived using sliding mode control theory with the switching surface based on impact time error. The interceptor first corrects its course to nullify the impact time error and then aims to achieve interception with desired impact angle. In order to reduce transitions between the two guidance laws, a novel hysteresis loop is introduced in the switching conditions. The guidance law is initially designed for stationary targets, and later it is extended to constant velocity targets using the notion of predicted interception point. In order to validate the efficacy of the proposed guidance strategy, simulation results are presented with constant as well as realistic time-varying speed interceptor models for different engagement scenarios against stationary and constant velocity targets. The performance of the guidance law is evaluated under noisy measurements and the presence of system lag and its performance is compared with other existing guidance laws.

scholarly journals Guidance and Control Method for Vehicle with Strap-down Seeker

2019 ◽  
Vol 291 ◽  
pp. 01003
Author(s):  
Li Fugui ◽  
Jia Shengwei ◽  
Tong Zeyou ◽  
Zhao Changjian ◽  
Li Yahui ◽  
...  
Keyword(s):  
Kalman Filter ◽  
Extended Kalman Filter ◽  
Control Method ◽  
Guidance System ◽  
Measurement Unit ◽  
Flight Vehicle ◽  
Guidance And Control ◽  
Guidance Law ◽  
Optimal Guidance ◽  
And Control

Guidance and control method was presented in this paper for flight vehicle with a strap-down seeker. Firstly, an extended Kalman filter was constructed in LOS (line of sight) coordinate system to estimate the guidance signal based on the information measured by strap-down seeker and inertial measurement unit. Secondly, an optimal guidance law which could reduce the target maneuvering and guidance system dynamics was proposed. Thirdly, three-loop acceleration autopilot with pseudo-angle of attack feedback was presented to control the flight vehicle. Finally, the proposed methods were simulated under typical condition. The simulation results demonstrated that the proposed methods were valid, and good performance could be achieved by the guidance and control method with the guidance signal estimated by the extended Kalman filter.

The Analysis of Miss Distance Sensitivity to Target Maneuvers for the Terminal Guidance System

2011 ◽  
Vol 128-129 ◽  
pp. 710-713
Author(s):  
Yu Yao ◽  
Xing Dan Wang ◽  
Bao Qing Yang ◽  
Jian Guo
Keyword(s):  
Sensitivity Analysis ◽  
Control System ◽  
Flight Control ◽  
Guidance System ◽  
Flight Control System ◽  
Guidance Law ◽  
Miss Distance ◽  
Terminal Guidance ◽  
Dynamics Characteristic

This paper gives a new definition, the Miss Distance Sensitivity to Target Maneuvers (MDSTM), which evaluates the robustness of the Terminal Guidance System (TGS) and gives the degree of exact miss distance caused by the inaccurate estimates of target maneuver. In this paper, the criterion of sensitivity analysis is the ratio of miss distance to target maneuver. The form of the TPN is investigated and then the GTPN guidance law is also proposed. Then, considering cases that the flight control system without dynamics and the dynamics characteristic can not be ignored, the MDSTM performance of TGS governed with TPN and GTPN for step acceleration target maneuvers are analyzed. Finally, the sensitivity analysis results of the system are listed in the paper, and the conclusions of how the effect the MDSTM were given in the end of the paper.

scholarly journals Lateral Control Implementation for an Unmanned Aerial Vehicle

2013 ◽  
Vol 2013 ◽  
pp. 1-14 ◽  
Author(s):  
R. Samar ◽  
M. Zamurad Shah ◽  
M. Nzar
Keyword(s):  
Flight Control ◽  
Flight Test ◽  
Practical Method ◽  
Roll Angle ◽  
Test Results ◽  
Guidance And Control ◽  
Yaw Rate ◽  
Guidance Law ◽  
Aerial Vehicle ◽  
And Control

This paper presents practical aspects of guidance and control design for UAV and its flight test results. The paper focuses on the lateral-directional control and guidance aspects. An introduction to the mission and guidance problem is given first. Waypoints for straight and turning flight paths are defined. Computation of various flight path parameters is discussed, including formulae for real-time calculation of down-range (distance travelled along the desired track), cross-track deviation, and heading error of the vehicle; these are then used in the lateral guidance algorithm. The same section also describes how to make various mission-related decisions online during flight, such as when to start turning and when a waypoint is achieved. The lateral guidance law is then presented, followed by the design of a robust multivariable H∞ controller for roll control and stability augmentation. The controller uses the ailerons and rudder for control of roll angle and stabilization of yaw rate of the vehicle. The reference roll angle is generated by the nonlinear guidance law. The sensors available on-board the vehicle do not measure yaw rate; hence, a practical method of its estimation is proposed. The entire guidance and control scheme is implemented on the flight control computer of the actual aerial vehicle and taken to flight. Flight test results for different mission profiles are presented and discussed.

scholarly journals Autonomous Underwater Vehicles and Field of View in Underwater Operations

2021 ◽  
Vol 9 (3) ◽  
pp. 277
Author(s):  
Isaac Segovia Ramírez ◽  
Pedro José Bernalte Sánchez ◽  
Mayorkinos Papaelias ◽  
Fausto Pedro García Márquez
Keyword(s):  
Autonomous Underwater Vehicles ◽  
Underwater Vehicles ◽  
Field Of View ◽  
Guidance System ◽  
Control Algorithms ◽  
Deep Waters ◽  
Underwater Cameras ◽  
Optimal Resolution ◽  
Acquisition Processes ◽  
And Control

Submarine inspections and surveys require underwater vehicles to operate in deep waters efficiently, safely and reliably. Autonomous Underwater Vehicles employing advanced navigation and control systems present several advantages. Robust control algorithms and novel improvements in positioning and navigation are needed to optimize underwater operations. This paper proposes a new general formulation of this problem together with a basic approach for the management of deep underwater operations. This approach considers the field of view and the operational requirements as a fundamental input in the development of the trajectory in the autonomous guidance system. The constraints and involved variables are also defined, providing more accurate modelling compared with traditional formulations of the positioning system. Different case studies are presented based on commercial underwater cameras/sonars, analysing the influence of the main variables in the measurement process to obtain optimal resolution results. The application of this approach in autonomous underwater operations ensures suitable data acquisition processes according to the payload installed onboard.

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.

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.

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