scholarly journals Stochastic Model Predictive Control for Guided Projectiles Under Impact Area Constraints

2014 ◽  
Vol 137 (3) ◽  
Author(s):  
Jonathan Rogers
Keyword(s):  
Stochastic Model ◽  
Uncertainty Propagation ◽  
Uncertainty Modeling ◽  
Guidance System ◽  
Guidance Law ◽  
Impact Area ◽  
Deterministic Control ◽  
Miss Distance ◽  
The Impact ◽  
Stochastic Model Predictive Control

The dynamics of guided projectile systems are inherently stochastic in nature. While deterministic control algorithms such as impact point prediction (IPP) may prove effective in many scenarios, the probability of impacting obstacles and constrained areas within an impact zone cannot be accounted for without accurate uncertainty modeling. A stochastic model predictive guidance algorithm is developed, which incorporates nonlinear uncertainty propagation to predict the impact probability density in real-time. Once the impact distribution is characterized, the guidance system aim point is computed as the solution to an optimization problem. The result is a guidance law that can achieve minimum miss distance while avoiding impact area constraints. Furthermore, the acceptable risk of obstacle impact can be quantified and tuned online. Example trajectories and Monte Carlo simulations demonstrate the effectiveness of the proposed stochastic control formulation in comparison to deterministic guidance schemes.

Design and Simulation of Guidance Law for a Kind of Flight Test Missile

2012 ◽  
Vol 538-541 ◽  
pp. 2887-2891
Author(s):  
Yu Qian ◽  
Xiao Jun Xiang ◽  
Jun Li Yang
Keyword(s):  
Flight Test ◽  
Target Point ◽  
Impact Point ◽  
Integral Term ◽  
Guidance Law ◽  
Velocity Information ◽  
The Difference ◽  
Miss Distance ◽  
Midcourse Guidance ◽  
The Impact

To reduce the miss distance of flight test missile, the midcourse guidance law is studied in this paper. The nonlinear projectile dynamic model is developed at first, and then designed the midcourse guidance law with the impact point prediction information. The guidance law was designed using the difference between predicting impact point and target point. To improve the guidance law’s performance, this research inducted the predicted impact point’s velocity information and integral term into guidance law command. At the end, the simulation was developed. The results of simulation show that the guidance law designed in this study is successful and it can satisfy the test missile’s flight mission requirements.

Study on Autopilot Dynamics with Robust Guidance Law and Terminal Constraint in Mechanical Engineering

2013 ◽  
Vol 644 ◽  
pp. 77-80
Author(s):  
Zhi Ping Li ◽  
Jun Zhou ◽  
Jian Guo Guo
Keyword(s):  
Mechanical Engineering ◽  
Tracking Error ◽  
Vertical Plane ◽  
Lyapunov Stability Theory ◽  
Mathematic Model ◽  
Impact Angle ◽  
Guidance System ◽  
Guidance Law ◽  
The One ◽  
The Impact

A new nonlinear robust guidance law was proposed by considering autopilot dynamics. Firstly, the mathematic model was built according to relationship between target and missile in vertical plane, by introducing the one-order dynamics of autopilot in Mechanical Engineering. Secondly, the nonlinear terminal guidance was obtained by applying the H∞ control theory under the performance index of minimizing the terminal angular constraint tracking error and control energy, and the asymptotic stability of guidance system was strictly proven by Lyapunov stability theory avoiding the estimation of the time-to-go. Finally, an illustrative example was given to show that the guidance law was more robust and both the impact angle and guidance precision were met in the case of no any target information.

Design of Guidance Law with Impact Angle and Impact Time Constraints

2014 ◽  
Vol 945-949 ◽  
pp. 1493-1499 ◽  
Author(s):  
Lin Ping Feng ◽  
Zuo E Fan ◽  
You Gen Zhang
Keyword(s):  
Control Theory ◽  
State Feedback ◽  
Impact Angle ◽  
The State ◽  
Guidance System ◽  
Time Constraints ◽  
Impact Time ◽  
Guidance Law ◽  
Optimal Guidance ◽  
The Impact

In order to achieve the tactical mission of cooperative attack for multi-missiles, in a predetermined direction at a predetermined time, this paper studies the design of guidance law with impact angle and impact time constraints. Firstly, using the optimal control theory, the optimal guidance law is designed to control the impact angle, based the relative motion between missile and target. Then the state feedback guidance law is designed to control the arrival impact time, with the application of feedback linearization control theory. Finally, reference the design idea of two-stage guidance system, the anti-ship missile use two different guidance laws in the process of attacking the target. During the first stage, the state feedback guidance law is used to accurately control the impact time and coarsely control the impact angle. During the second stage, the optimal guidance law is used to accurately control the impact angle. And the correctness and effectiveness of the design method is verified by simulation.

scholarly journals Impact Time Guidance Law Considering Autopilot Dynamics Based on Variable Coefficients Strategy for Maneuvering Target

2015 ◽  
Vol 2015 ◽  
pp. 1-10 ◽  
Author(s):  
Wei Shang ◽  
Jie Guo ◽  
Shengjing Tang ◽  
Yueyue Ma ◽  
Yao Zhang
Keyword(s):  
Finite Time ◽  
Sliding Mode ◽  
Variable Coefficients ◽  
Guidance System ◽  
Impact Time ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Convergence Control ◽  
Unknown Disturbance ◽  
The Impact

This paper investigates the terminal guidance problem for the missile intercepting a maneuvering target with impact time constraint. An impact time guidance law based on finite time convergence control theory is developed regarding the target motion as an unknown disturbance. To further improve the performance of the guidance law, an autopilot dynamics which is considered as a first-order lag is taken into consideration. In the proposed method, the coefficients change with the relative distance between missile and target. This variable coefficient strategy ensures that the missile impacts the target at the desired time with little final miss distance. Then it is proved that states of the guidance system converge to sliding mode in finite time under the proposed guidance law. Numerical simulations are presented to demonstrate the effectiveness of the impact time guidance law with autopilot dynamics (ITGAD).

Three-dimensional cooperative interception guidance law with impact time constraint

2021 ◽  
pp. 095441002110105
Author(s):  
Li Hongxia ◽  
Deng Yifan ◽  
Yuanli Cai
Keyword(s):  
Finite Time ◽  
Control Method ◽  
Three Dimensional ◽  
Time Constraint ◽  
Lyapunov Theory ◽  
Guidance System ◽  
Consensus Protocol ◽  
Impact Time ◽  
Guidance Law ◽  
The Impact

This article proposes a new terminal cooperative guidance law with impact time constraint in three-dimensional (3D) engagement. Two parts are comprised by this guidance scheme to control the impact time and fulfill the interception. The guidance law along the line-of-sight (LOS) direction is first designed based on finite time consensus protocol to share time-to-go values among missiles and reach the consensus. Meanwhile, the guidance law on the LOS normal direction is developed based on the fast finite time control method to achieve the interception. The stability analysis of the proposed guidance law based on the Lyapunov theory is also demonstrated in detail. Moreover, the maneuvering target can be intercepted successfully under the presented control algorithm, and the guidance system can fulfill stability within finite time. Additionally, the effectiveness and applicability of the proposed guidance scheme are explicitly verified through simulation tests.

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 Empirical Stochastic Model of Multi-GNSS Measurements

Sensors ◽  
2021 ◽  
Vol 21 (13) ◽  
pp. 4566
Author(s):  
Dominik Prochniewicz ◽  
Kinga Wezka ◽  
Joanna Kozuchowska
Keyword(s):  
Stochastic Model ◽  
Density Ratio ◽  
Functional Model ◽  
Optimal Solution ◽  
Global Navigation Satellite Systems ◽  
Unknown Parameters ◽  
Short Baseline ◽  
Stochastic Parameters ◽  
Dependent Model ◽  
The Impact

The stochastic model, together with the functional model, form the mathematical model of observation that enables the estimation of the unknown parameters. In Global Navigation Satellite Systems (GNSS), the stochastic model is an especially important element as it affects not only the accuracy of the positioning model solution, but also the reliability of the carrier-phase ambiguity resolution (AR). In this paper, we study in detail the stochastic modeling problem for Multi-GNSS positioning models, for which the standard approach used so far was to adopt stochastic parameters from the Global Positioning System (GPS). The aim of this work is to develop an individual, empirical stochastic model for each signal and each satellite block for GPS, GLONASS, Galileo and BeiDou systems. The realistic stochastic model is created in the form of a fully populated variance-covariance (VC) matrix that takes into account, in addition to the Carrier-to-Noise density Ratio (C/N0)-dependent variance function, also the cross- and time-correlations between the observations. The weekly measurements from a zero-length and very short baseline are utilized to derive stochastic parameters. The impact on the AR and solution accuracy is analyzed for different positioning scenarios using the modified Kalman Filter. Comparing the positioning results obtained for the created model with respect to the results for the standard elevation-dependent model allows to conclude that the individual empirical stochastic model increases the accuracy of positioning solution and the efficiency of AR. The optimal solution is achieved for four-system Multi-GNSS solution using fully populated empirical model individual for satellite blocks, which provides a 2% increase in the effectiveness of the AR (up to 100%), an increase in the number of solutions with errors below 5 mm by 37% and a reduction in the maximum error by 6 mm compared to the Multi-GNSS solution using the elevation-dependent model with neglected measurements correlations.

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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