Design of Controllers for Missile Guidance System

For backward status of a missile guidance device monitoring methods, developed a set of ground monitoring system based on virtual instrument technology. The system meets the standard test of a certain type of missile guidance device, the data acquisition card and controller of PXI bus as the hardware platform, using LabVIEW as the software development platform, The acquisition of analog signal, video signal and serial communication set in one, it can detect the performance and parameters of the guidance device, and monitoring the flight trajectory of the missile qualitatively. The application results show that the monitoring system is stable and reliable, improve the efficiency and accuracy of monitoring, and has a certain popularization value.

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Investigation into Air Interception Guidance Algorithms for Autonomous Aerial Hard Docking of Dissimilar Platforms

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.629.214 ◽

2014 ◽

Vol 629 ◽

pp. 214-218

Author(s):

Omar Kassim Ariff ◽

E. Salami ◽

M.T. Ahmad ◽

T.H. Go

Keyword(s):

Guidance System ◽

Missile Guidance ◽

Proportional Navigation ◽

Terminal Constraints ◽

Rigid Connection ◽

The Moment ◽

Further Development ◽

Rotary Wing ◽

Guidance Laws ◽

Specific Scenario

Autonomous aerial hard docking is the process where an aircraft approaches and forms a rigid connection with another aircraft. After the docking process is complete, it is not necessary for the lift and propulsion system of the docked aircraft to be operating. Docking allows the larger aircraft to carry the small aircraft outside its airframe, thereby extending the range of endurance of the smaller aircraft. In this paper, we investigate specific scenario where docking occurs between a rotary wing aircraft and a fixed wing aircraft. To perform the above procedure, a guidance system on each platform has to ensure interception while satisfying the primary interception condition of velocity vector co-linearity at the moment of intercept of the two trajectories or flight paths. Pursuit guidance and proportional navigation were assessed as candidates for further development for the terminal docking phase. Since the platforms are in quasi-perfect knowledge of each other, the pursuer evader scenario is replaced by the pursuer-pursuer scenario. The novelty of this work lies in the formulation of terminal constraints, as well as the findings obtained. This paper concludes that contrary to the missile guidance scenario, pursuit based guidance laws provide superior baseline laws from which AAHD guidance and navigation laws can be developed.

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Advanced missile guidance system against a very high speed maneuvering target

10.2514/6.1989-3445 ◽

1989 ◽

Cited By ~ 7

Author(s):

TAKESHI KURODA ◽

FUMIAKI IMADO

Keyword(s):

High Speed ◽

Guidance System ◽

Missile Guidance ◽

Maneuvering Target ◽

Very High

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Partial Stabilization Approach to 3-Dimensional Guidance Law Design

Journal of Dynamic Systems Measurement and Control ◽

10.1115/1.4004575 ◽

2011 ◽

Vol 133 (6) ◽

Cited By ~ 4

Author(s):

T. Binazadeh ◽

M. J. Yazdanpanah

Keyword(s):

System Dynamics ◽

The State ◽

Guidance System ◽

Missile Guidance ◽

State Variables ◽

New Approach ◽

3 Dimensional ◽

Guidance Law ◽

Maneuvering Targets

In this paper, a new approach to design the 3-dimensional missile guidance law, based on partial stabilization, is presented. The approach is based on the classification of the state variables within the guidance system dynamics with respect to their required stabilization properties. The resulting guidance law enables the missile to intercept highly maneuvering targets within a finite interception time. Effectiveness of the proposed guidance law is demonstrated through analysis and simulations.

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Ballistic missile guidance system test in an aircraft pod

AIAA Guidance, Navigation, and Control Conference and Exhibit ◽

10.2514/6.2000-4387 ◽

2000 ◽

Cited By ~ 1

Author(s):

Michael Murphy ◽

Shawn Armacost ◽

Raymond Barnes ◽

Kevin Templin ◽

Dennis Krepp

Keyword(s):

Ballistic Missile ◽

Guidance System ◽

Missile Guidance

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The Static Unbalance Analysis and Its Measurement System For Gimbals Axes of an Inertial Stabilization Platform

Metrology and Measurement Systems ◽

10.1515/mms-2015-0002 ◽

2015 ◽

Vol 22 (1) ◽

pp. 51-68 ◽

Cited By ~ 2

Author(s):

Hui Yang ◽

Yan Zhao ◽

Min Li ◽

Falin Wu

Keyword(s):

Measurement System ◽

Small Angle ◽

Guidance System ◽

Measuring System ◽

Static Balance ◽

Missile Guidance ◽

Reciprocating Motion ◽

Balance Condition ◽

System A ◽

Mass Eccentricity

Abstract To reduce the influence of the static unbalance on an infrared missile guidance system, a new static unbalance measure system for the gimbals axes has been developed. Considering the coupling effects caused by a mass eccentricity, the static balance condition and measure sequence for each gimbal axis are obtained. A novel static unbalance test approach is proposed after analyzing the dynamic model of the measured gimbal axis. This approach is to drive the measured gimbal axis to do sinusoidal reciprocating motion in a small angle and collect its drive currents in real time. Then the static unbalance of the measured gimbal axis can be obtained by the current multi-cycle integration. Also a measuring system using the proposed approach has been developed. A balanced simulator is used to verify the proposed approach by the load and repeatability tests. The results show the proposed approach enhances the efficiency of the static unbalance measurement, and the developed measuring system is able to achieve a high precision with a greater stability.

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Adaptive neural FOPID controller applied for missile guidance system

IECON 2017 - 43rd Annual Conference of the IEEE Industrial Electronics Society ◽

10.1109/iecon.2017.8216499 ◽

2017 ◽

Cited By ~ 1

Author(s):

Murad Yaghi ◽

Mehmet Onder Efe

Keyword(s):

Guidance System ◽

Missile Guidance

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GPS Inertial Missile Guidance System

Pakistan Journal of Engineering Technology & Science ◽

10.22555/pjets.v4i2.207 ◽

2015 ◽

Vol 4 (2) ◽

Author(s):

Osama Sarfaraz

Keyword(s):

Target Position ◽

Guidance System ◽

Missile Guidance ◽

Radio Waves ◽

Current Position ◽

Google Maps ◽

Main Component ◽

Missile System

The task of this work is to design the guidance system for the missile which would guide the missile accurately to hit the target as directed. Guidance is the main component of the missile system which helps in hitting the target accurately. The missile can be guided by the number of ways which includes by using laser, GPS infrared or radio waves on its way to the target. This paper proposes a model to guide the missile with the help of GPS and INS. This model requires a computer or controller which should be installed in the missile to control the missile flight according to the guidance provided by GPS and INS. The system works by knowing the missile current position and the position of the target. The position of the target is known by using Google maps which is feed in the missile controller before the missile is launched. Missile current position is known by using GPS while the missile current orientation and heading is known by using INS. Missile current position is compared with the target position to calculate the desired heading towards the target, then missile controller auto pilots the missile according to the desired heading towards target to hit the target.

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