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Flight control system plays an important role in the process of missile designing. The quality of flight control system will affect the missile's performance significantly. In this article, we design a flight control system using variable structure control theory. Firstly, we establish a mathematical model of the missile and the basic content of variable structure control theory is introduced. Next...
A finite time convergent sliding-mode guidance law with hysteresis switching is proposed for the guidance considering thrust constraint and second-order dynamics of divert thruster. Firstly, the mathematical model of relative movement considering the second-order dynamic delay of engine is set up according to the planar relative motion of missile and target. Secondly, based on the principle of nullifying...
A new cooperative guidance law based on terminal sliding mode with strengthened condition is designed to solve multi-attacker-one-target simultaneous attack problem. The strengthened condition can guarantee state convergency and eliminate chattering. Accurate time-to-go can be kept during state moving on the sliding mode. The impact time can be given before intercepting target. Numerical simulations...
A tail-controlled BTT missile with flaps control is presented. First, we derive the nonlinear system model of the six-degree-of-freedom with two inputs. Based on choosing the angle-of-attack and roll angle as output variables, the internal dynamics of the system are analyzed by using differential geometry method, and are proved to be stabilized. An autopilot is designed by using the feedback linearization...
Aiming at the consensus of leader-follower multi-warhead networked cooperative attack system with stochastic multi-step time-varying delay in the free flight segment of ballistic missile, considering the actual situation, a three-dimensional integrated guidance model of leader-follower multi-warhead cooperative attack system is established. Based on the established model, considering the effect of...
In order to intercept against the fixed, uniform and maneuvering target with a certain impact angle accurately, a circular navigation guidance method based on sliding mode control is proposed in this paper. According to the geometrical analysis of the circular trajectory in a two-dimensional plane, the conclusion that only if impact angle is given, two of any points on the guidance face have a unique...
Distributed group cooperative guidance (DGCG) problems for multiple missiles with switching directed communication topologies are dealt with. In contrast to traditional cooperative guidance utilized to intercept one single target, the group cooperative guidance is applicable to multiple targets. In the group cooperative attack, multi-missile system are classified into multiple subgroups, and each...
To intercept stationary targets at desired impact angle, the three-dimensional terminal guidance problem has been investigated in this paper. Different from the traditional method of decoupling the engagement dynamics into two mutually orthogonal two-dimensional planes, the guidance law design is studied using three-dimensional coupled engagement dynamics. Because of the short terminal guidance time,...
This paper proposes an online adaptive dynamic programming (ADP) based algorithm to solve the simultaneous attack problem with multiple missiles against a maneuvering target. In contrast to typical cooperative strategy, in this paper we considerate the optimality of the strategy as well as the convergence of the system. To obtain the optimal control, we adopt a new architecture called ‘cost function-based...
This paper investigates the missile attitude control problem. The model used in this paper is with respect to the Euler attitude angles and their derivatives which can be measured and computed easily. A robust practical finite-time control algorithm is proposed based on the terminal sliding mode approach. It is proved that all of the signals in the closed-loop system are bounded and the tracking error...
An inertial stability and tracking control method based on parameter identification is presented for the nonlinear driving missile launcher. Nonlinear driving structure of the missile launcher is analyzed, and the kinematic relationships and dynamical equations are described. Nonlinear driving part will be identified by the polynomials fitting function. Compared with the traditional inertial stability...
Advanced homing missile's guidance law for highly maneuvering targets, requires the information of both inertial Line of Sight (LOS) angular rate and maneuvering target acceleration. Nevertheless, the semi-strapdown seeker is not able to measure the LOS angular rate directly and the differential operations commonly used in traditional methods will amplify sensor's measurement errors, causing poor...
Based on backstepping control technique, a novel adaptive integrated guidance and control (IGC) law is presented for missile intercepting maneuvering target with input saturation. To deal with the uncertainties in the IGC system, adaptive control technique is utilized to estimate the upper bounds of the uncertainties. Moreover, an auxiliary system is designed to cope with the input saturation. The...
For deadzone, parameters variations and disturbances in missile servo control system, a robust adaptive fuzzy fast terminal sliding mode controller was proposed to compensate deadzone, uncertainties and other disturbances. An adaptive fuzzy logic controller for the deadzone dynamic compensation was adopted in feedforward loop. The variations of hinge moment were identified online requiring no prior...
Fire distribution of the ship-to-air missiles is an important issue in the anti-missile operational process of the warship formation. In the paper, an algorithm for fire distribution of the ship-to-air missiles is designed and optimized based on the market auction mechanism, and then the influences of the launch time window, the available fire channels, and several dynamic random events such as the...
An internal model based guidance law is investigated, which is applied to a short-range homing missile against a sinusoidally weaving target. In practice, it's difficult to measure the target maneuver directly, which is the key to improve the guidance performance. The main idea of this paper is to use an adaptive internal model to generate the estimate of the target maneuver. It's different from the...
To attack targets with towed decoys, a method of estimation of line-of-sight angle rate in precision guidance process is proposed. The motion model of the target and the towed decoy is established as the basis of estimation of the line-of-sight angle. Then the estimate of line-of-sight angle rate is obtained by means of observation from the high-gain observer for a second-order system. Finally, a...
In this paper, the synthesis method, self-stable region (SSR) approach, is applied to uncertain and time delay system. The chattering phenomenon is the main drawback of sliding mode control (SMC), and the response delay of actuators is a primary cause. However, the existence of time delay is common in real world. The SSR approach is an improvement for SMC method. A simple second order system with...
An optimal guidance law of reentry vehicle both with terminal interception and impact angle constraint is derived, and tow types of optimal guidance law expressions “Proportional Navigation + Angle Constraint (PN+AC)” and “Velocity Pursuit + Angle Constraint (VP+AC)” are given with lag-free dynamic system. Then, simulations of non-dimensional miss distance and impact angle error base on statistical...
An optimal impact angle control guidance law is proposed in this paper. The missile system is approximated under the small heading error assumption and the impact angle control guidance law is derived based on the approximated system to minimize the energy cost. The proposed guidance law has a form of biased PNG law and it's in accord with the previous result of PNG in the form acceleration command...
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