AN ADAPTIVE PROPORTIONAL NAVIGATION GUIDANCE LAW FOR INTERCEPTION OF A MANEUVERING TARGET

2005 ◽  
Vol 29 (2) ◽  
pp. 195-209
Author(s):  
Dany Dionne ◽  
Hannah Michalska
Keyword(s):  
A Priori ◽  
Time Instant ◽  
Proportional Navigation ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Hierarchical Decision ◽  
On Line ◽  
Priori Information ◽  
Miss Distance ◽  
Proportional Navigation Law

A new adaptive proportional navigation law for interception of a maneuvering target is presented. The approach employs a bank of guidance laws and an on-line governor to select the guidance law in effect at each time instant. The members of the bank are the proportional navigation law and a companion law suitable for a target moving with a constant acceleration. The governor is a hierarchical decision rule which uses the outputs from a maneuver detector and the available a-priori information about the expected number of evasive maneuvers. Simulation results demonstrate that the adaptive approach leads to a reduction in the miss distance as compared with cases where only a single non-adaptive guidance law is available.

Performance analysis of differential geometric guidance law against high-speed target with arbitrarily maneuvering acceleration

2018 ◽  
Vol 233 (10) ◽  
pp. 3547-3563 ◽  
Author(s):  
Ke-Bo Li ◽  
Wen-Shan Su ◽  
Lei Chen
Keyword(s):  
High Speed ◽  
Control System Design ◽  
Proportional Navigation ◽  
Full Account ◽  
Guidance And Control ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Classical Differential Geometry ◽  
Relative Dynamics ◽  
And Control

The interception of high-speed target with an arbitrary maneuvering acceleration causes serious troubles to the guidance and control system design of airborne missile. A novel guidance law based on the classical differential geometry curve theory was proposed not long ago. Although it is believed and numerically demonstrated that this differential geometric guidance law (DGGL) is superior to the classical pure proportional navigation (PPN) in intercepting high-speed targets, its performance has not been thoroughly analyzed. In this paper, using the Lyapunov-like approach, the performance of DGGL against the high-speed target with an arbitrary but upper-bounded maneuvering acceleration is well studied. The upper bounds of the LOS rate and commanded acceleration of DGGL are obtained, and conditions that guarantee the capture of this type of maneuvering target are also presented. The nonlinear relative dynamics between the missile and target is taken into full account. Finally, the proposed theoretical findings are demonstrated by numerical simulation examples.

An Approach to On-Line Uncertainty Evaluation in Non-Contact Temperature Measurements

2014 ◽  
Vol 613 ◽  
pp. 173-181 ◽  
Author(s):  
Anton Ionov ◽  
Boris Ionov ◽  
Nadezhda Chernysheva ◽  
Egor Plotkin
Keyword(s):  
A Priori ◽  
Temperature Measurements ◽  
Contact Temperature ◽  
Uncertainty Evaluation ◽  
External Information ◽  
Basic Algorithm ◽  
Suggested Technique ◽  
Uncertainty Calculation ◽  
On Line ◽  
Priori Information

The article is devoted to the suggested technique of on-line uncertainty calculation in non-contact temperature measurements, which can be used as a basic algorithm for smart measuring systems, e.g. intelligent radiation thermometers. As the initial data for uncertainty evaluation we use a priori information about heat detector characteristics, calibration curves along with their related uncertainties, estimated ambient temperature and external information of correction factor that should be inputted in a probabilistic form. We suggest utilizing models based on a characteristic function, in order to evaluate the combined uncertainty. In our opinion, the discussed principles are applicable for lots of other areas of measurement, especially, where it is critical to improve effectiveness of subsequent decision-making.

Generalized optimal impact-angle-control guidance with terminal acceleration response constraint

2017 ◽  
Vol 231 (14) ◽  
pp. 2515-2536 ◽  
Author(s):  
Hui Wang ◽  
Jiang Wang ◽  
Defu Lin
Keyword(s):  
General Expression ◽  
Impact Angle ◽  
Acceleration Response ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Terminal Constraints ◽  
Miss Distance ◽  
Guidance Laws ◽  
Impact Angle Constraint

To study the optimal impact-angle-control guidance problem with multiple terminal constraints, a generalized optimal impact-angle-control guidance law with terminal acceleration response constraint (GOIACGL-TARC) is proposed. In the deriving, a time-to-go − nth power weighted object function is adopted to derived the GOIACGL-TARC and a general expression of GOIACGL-TARC is presented. Based on the general expression of GOIACGL-TARC, three guidance laws, GOIACGL-TARC1/TACC0/TACC1 are proposed and the inheritance relationship between GOIACGL-TACC0/TACC1/TARC1 and the conventional optimal guidance law with impact angle constraint is demonstrated. Performance analysis of the proposed guidance laws shows that in the case of GOIACGL-TACC0, the terminal acceleration is not zero at n = 0 and only as n > 0, the terminal acceleration converges to zero; in the case of GOIACGL-TACC1 and GOIACGL-TARC1, GOIACGL-TARC1 can guarantee the acceleration response to reach the exactly zero value but GOIACGL-TACC1 cannot, which can only guarantee the acceleration command to reach the exactly zero value. It is pointed out that compared with the biased proportional navigation guidance law, GOIACGL-TARC1 has an outstanding guidance performance in acceleration response, miss distance, and terminal impact angle error.

Biased optimal guidance law with specified velocity rendezvous angle constraint

2015 ◽  
Vol 119 (1220) ◽  
pp. 1287-1299 ◽  
Author(s):  
X. Xu ◽  
Y. Liang
Keyword(s):  
High Speed ◽  
Terminal Phase ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Terminal Time ◽  
Optimal Guidance ◽  
Simulation Results ◽  
Miss Distance ◽  
Simplified Mathematical Model ◽  
Distance Setting

Abstract In order to increase the effectiveness of interceptor missile, velocity rendezvous angle control is required in the terminal phase. The purpose of this paper is to obtain an optimal guidance law which can achieve specified velocity rendezvous angle as well as zero terminal miss distance. A biased optimal guidance law based on a simplified mathematical model is deduced for interceptors engaging against invasion aircraft. Different from previous literatures on this issue, the presented guidance law suitable for intercepting high-speed maneuvering target. Another advantage is, under centimeter level miss distance setting, the guidance law needs smaller guidance command near the terminal time, which can successfully avoid command saturation. Simulation results demonstrate the effectiveness of the presented guidance law.

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.

scholarly journals Adaptive Fuzzy Sliding Mode Guidance Law considering Available Acceleration and Autopilot Dynamics

2018 ◽  
Vol 2018 ◽  
pp. 1-10 ◽  
Author(s):  
Yulin Wang ◽  
Shengjing Tang ◽  
Wei Shang ◽  
Jie Guo
Keyword(s):  
Sliding Mode ◽  
Variable Structure ◽  
Adaptive Sliding Mode Control ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Target Acceleration ◽  
Neural Network System ◽  
Fuzzy Sliding Mode ◽  
Miss Distance ◽  
Terminal Guidance

Terminal guidance law for missiles intercepting high maneuvering targets considering the limited available acceleration and autopilot dynamics of interceptor is investigated. Conventional guidance laws based on adaptive sliding mode control theory were designed to intercept a maneuvering target. However, they demand a large acceleration for interceptor at the end of the terminal guidance, which may have acceleration saturation especially when the target acceleration is close to the available acceleration of interceptor. In this paper, a terminal guidance law considering the available acceleration and autopilot dynamics of interceptor is proposed. Then, a fuzzy system is utilized to approximate and replace the variable structure term, which can handle the unknown target acceleration. And an adaptive neural network system is adopted to compensate the effects caused by the designed overlarge acceleration of interceptor such that the interceptor with small available acceleration can intercept the high maneuvering target. Simulation results show that the guidance law with available acceleration and autopilot dynamics (AAADG) is highly effective for reducing the acceleration command and achieving a small final miss distance.

Optimal Sliding-Mode Terminal Guidance Law Design of Airborne Boost-Phase Ballistic Missile Interception

2010 ◽  
Vol 40-41 ◽  
pp. 15-20
Author(s):  
Yan Kai Cui ◽  
Li Fu ◽  
Xiao Geng Liang ◽  
Ling Luo
Keyword(s):  
Control Theory ◽  
Sliding Mode ◽  
Ballistic Missile ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Motion Characteristic ◽  
Vehicle Motion ◽  
Proportional Navigation Law ◽  
Terminal Guidance

Aiming at terminal guidance law design of airborne boost-phase ballistic missile interception under acceleration of target without availability, we study on optimal sliding-mode terminal guidance law design of Kinetic-Kill Vehicle. Motion characteristic and infrared characteristic of ballistic missile are analyzed basing on founding ballistic missile boost-phase motion equations. Optimal terminal guidance law of Kinetic-Kill Vehicle is designed basing on undershoot quantity least and energy minimum. Optimal guidance law and augmented proportional navigation law having the same form is proved in theory. Optimal sliding-mode terminal guidance law is designed under acceleration of target without availability, using optimal control theory and sliding-mode control theory. Simulation show that optimal sliding-mode terminal guidance law satisfies required index, reaching the aim to direct hit the target. The correctness and effectiveness of the optimal sliding-mode guidance law are proved.

Application of Super Twisting Guidance Law Based on Extended State Observer

2013 ◽  
Vol 433-435 ◽  
pp. 1009-1014 ◽  
Author(s):  
Yang Chong ◽  
Ke Zhang
Keyword(s):  
Sliding Mode ◽  
External Disturbance ◽  
State Observer ◽  
Extended State Observer ◽  
Extended State ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Target Acceleration ◽  
Twisting Algorithm ◽  
Miss Distance

In order to intercept high maneuvering target, a super twisting guidance law based on extended state observer (ESO) is proposed. The target acceleration can be defined as external disturbance which can be estimated in ESO and compensated in super twisting guidance law. The super twisting algorithm can effectively decrease the undesired charting which exists in normal sliding mode control. The simulation results which are verified via computer show that this guidance law has strong robustness, target acceleration can be estimated and compensated, and has good miss distance.

Research on Improved Extended Proportional Navigation Guidance

2013 ◽  
Vol 347-350 ◽  
pp. 980-984
Author(s):  
De Long Feng ◽  
Suo Chang Yang ◽  
Yun Zhi Yao ◽  
Ying Xi Liu
Keyword(s):  
Relative Motion ◽  
Motion Model ◽  
Improved Method ◽  
Proportional Navigation ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Simulation Results ◽  
Set Up ◽  
Proportional Navigation Guidance

This paper proposed an improved method on the basis of the extended proportional guidance law. The method solved the weak observability problem of system sate in guided missile attacking maneuvering target. It is simple in form and easy for engineering implementation. This paper set up relative motion model and the observability theory indexes. The improved propotional guidance law is simulated using the MATLAB language. The simulation results show that the method is reasonable, effective and improving the observability.

Sign in / Sign up

Export Citation Format

Share Document