This paper focuses on missile guidance methods for a defense trying to protect cooperative aircraft from guided munitions which have the same thrust and maneuvering capabilities as that of missile. A novel law missile-to-missile intercept is developed via simple geometrical approach. The potential demonstrated discussed with some simulation results. Performance comparison conventional also presented. Nomenclature C = BM acceleration command normal velocity vector, m/s 2 BA blue (cooperative...

An integrated guidance and autopilot scheme for a path-following uninhabited aerial vehicle is presented in this study. A fixed-wing aircraft usually performs bank-to-turn maneuver to change its flight direction. The novel approach here, however, assumes that each of the three channels can be independently designed. This concept makes design process simple. virtual target moving on prespecified path introduced facilitate algorithm development. first-/second-order sliding structure with...

A guidance and control system for a trajectory-tracking unmanned aerial vehicle (UAV) is introduced. proportional navigation law applied to flight instead of using traditional tracking-error correction based method. The employs dynamic inversion technique the force generation, which allows UAV maintain high maneuverability, simple velocity obtain desired velocity. trajectory provided with cubic-spline interpolation given waypoints in order simplify making process. Using function along arc,...

This paper introduces an advanced pure pursuit guidance method for chase UAV. The employs a sliding mode approach using proper Lyapunov function, which is based on three-dimensional expression related to line of sight (LOS) angle. In order apply the guidance, simple surface vector and derivation scheme from solution are also introduced. control system determine UAV's commanded bank angle attack , two-time scaled dynamic inversion technique attitude, draws high maneuverability chasing...

This paper introduces a high performance pure pursuit guidance method via sliding mode approach for UAV's rendezvous with cooperative aircraft. A should orient the UAV to predicted position and specified heading constraint that enable continue follow aircraft at desired distance. For scheme accomplish these objectives, chosen waypoint is used guide point an allowable error. Furthermore, has reach proposed admissible time of arrival have same velocity as To this end, dynamic inversion (DI)...

This study focuses on the integrated guidance and autopilot (IGA) design for a path-following uninhabited aerial vehicle (UAV). A second order sliding structure which facilitates smooth bank turn coupled motions is used flight applications. high-order mode (HOSM) differentiator estimation of uncertain surfaces. In to apply IGA system UAV, virtual target, set in pre-specified path, used. The potential proposed method demonstrated through UAV application helical ascent under wind turbulence...

This article introduces a high-performance pure pursuit guidance method via sliding mode approach for an unmanned aerial vehicle's (UAV) rendezvous with cooperative aircraft. A should orient the UAV to predicted position and specified heading constraint that enables continue follow aircraft at desired distance. For scheme accomplish these objectives, chosen waypoint is used guide point allowable error. Furthermore, has reach proposed admissible time of arrival have aircraft's velocity. To...

This paper focuses on missile guidance methods for a 'defense' trying to protect cooperative aircraft from guided munitions that have the same thrust and maneuvering capabilities as of missile. A novel law missile-to-missile intercept is developed by using two line sight (LOS) rates: one LOS constructed protected threat missile, other The proposed derived optimal control theory. resulting form represented 'zero effort miss' with respect an attacking Potential demonstrated some simulation...

This paper focuses on a missile intercept guidance method taking account of uncertainty and disturbance. The proposed law are developed using second order sliding mode approach, along with an disturbance estimator. A novel surface is for the mode-based guidance. unified both non-impact angle constraint impact constraint. guarantees finite time convergence lineof-sight rate (if specified) LOS error associated simple function time-to-go like case proportional navigation against non-maneuvering...

This paper introduces a guidance and control system for chase UAV along with novel velocity control. The controller is designed based on dynamic inversion approach in conjunction pseudo target setting, which allows to take high speed yo-yo maneuvers keep desired relative distance from aircraft. employs the pure pursuit determine UAV’s orientation, two-time scaled technique attitude, enable maneuverability chasing capability. y x , = Components of position vector w.r.t. body axes, [m] I z w v...

This study focuses on an integrated guidance and autopilot (IGA) scheme for a defense missile trying to protect cooperative aircraft from guided munitions which have the same capabilities as that of missile. A higher-order sliding mode (HOSM) approach is used in development IGA. three-dimensional (3D) surface vector introduced handle roll-yaw/-pitch coupled motions IGA system design. Intermediate control variables are carefully selected approximated time derivatives such structure simple...

L a , = derivatives related to lift, and aerodynamic side force, respectively  n m l moments with respect the aileron, elevator, rudder,

This article develops a missile guidance technique for ‘defense missile’ trying to protect cooperative aircraft from guided munitions which have the same thrust and maneuvering capabilities as that of defense missile. A novel law missile-to-missile intercept is developed via geometrical approach. Performance analysed in detail its potential demonstrated with results six degrees-of-freedom simulation comparison conventional law.

In discrete event systems, the supervisor controls events to satisfy control specifications given by formal languages. However a precise description of and systems is required for constructing supervisor. So, this paper proposes method construct based on reinforcement learning partially observed systems. proposed method, are rewards, an optimal derived considering rewards occurrence disabling events. Moreover speed accelerated updating plural Q values. It done utilizing characteristics...

Integrated guidance and control approaches exploit the synergy between of a vehicle. This study focuses on integrated control(autopilot) design for chasing UAV against target aircraft. A second-order sliding structure desired coupled roll pull-up motions is proposed as means to develop an autopilot scheme. For easier synthesis, intermediate variables partial derivatives surface are carefully selected. As consequence, simple sufficient relate actuator input surface. The potential method...

Proportional navigation (PN) is a well-known guidance law for two-vehicle engagement. In the engagement, miss distance (the closest between two vehicles) desired to be zero that can achieved by annulling line-of-sight (LOS) rate. The PN requires information of LOS rate and, if it available, closing velocity relative approaching speed target). system may degrade performance due target maneuvers. Such maneuvers should compensated with system. However, difficult obtain accurate target's...