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When threatened by a pursuer, an evading aircraft launches two defenders to accomplish a cooperative evasion, constituting a four-aircraft interception engagement. Under the assumption that the pursuing aircraft adopts the augmented proportional guidance law and first-order dynamics, a cooperative intercept mathematical model with an intercept angl...
Citations
... Because the sine theorem and the LOS angle information between the two pursuers are used to accomplish the cooperative distance measurement [7] , the relative distance between the pursuers and the target cannot be calculated when the LOS separation angle is equal to zero, and the estimation error is very large when it is particularly small. Therefore, the problem of detection configuration [7][8][9][10][11] should also be considered in the process of multi-interceptor guidance design. ...
For the case that two pursuers intercept an evasive target, the cooperative strategies and state estimation methods taken by pursuers can seriously affect the guidance accuracy for the target, which performs a bang For the case that two pursuers intercept an evasive target, the cooperative strategies and state estimation methods taken by pursuers can seriously affect the guidance accuracy for the target, which performs a bang-bang evasive maneuver with a random switching time. Combined Fast multiple model adaptive estimation (Fast MMAE) algorithm, the cooperative guidance law takes detection configuration affecting the accuracy of interception into consideration. Introduced the detection error model related to the line-of-sight (LOS) separation angle of two interceptors, an optimal cooperative guidance law solving the optimization problem is designed to modulate the LOS separation angle to reduce the estimation error and improve the interception performance. Due to the uncertainty of the target bang-bang maneuver switching time and the effective fitting of its multi-modal motion, Fast MMAE is introduced to identify its maneuver switching time and estimate the acceleration of the target to track and intercept the target accurately. The designed cooperative optimal guidance law with Fast MMAE has better estimation ability and interception performance than the traditional guidance law and estimation method via Monte Carlo simulation.
... When the distance information is combined with cooperative angle measurement of multiple aircraft [7], the relative distance between the multiple aircraft and the target cannot be estimated when they are collinear, and the estimation error is very large when they are approximately collinear. Therefore, the problem of detection configuration [7], [8], [12]- [14] should also be considered in the process of multiinterceptor guidance design. ...
... Combined with (14), the measurement equation of the pursuer can be obtained as ...
We consider the scenario where two pursuers are required to intercept an enemy evader that launches a decoy. Under the assumption that all four aircrafts have first-order linear dynamic characteristics, a cooperative guidance law is designed in two stages: the unidentified decoy stage and the discriminated decoy stage. In the unidentified decoy stage, the predictive guidance law is designed based on the method of the highest probability interval (HPI). This guidance law can maximize the probability of intercepting the real target despite the decoy’s presence, thus providing an interception maneuver advantage for later cooperative guidance to the real target. In the discriminated decoy stage, based on the optimal control theory, an optimal guidance law considering the detection configuration is designed, which reduces the estimation error in the detection process and improves the interception performance. Simulation results verify the feasibility of the phased cooperative guidance law.
... In view of the above analysis, this study extends the finite-time theory to a SLS, and conduct the stability analysis of both states and output concurrently, which is the conspicuous improvement compared with the results derived in the current study. As a matter of fact, solving the problem of the SLS satisfying both the FTB and FTOS can allow practical engineering applications to be better achieved [32][33][34]. ...
This study discusses the finite–time output stability (FTOS) for the impulse switching linear system (SLS) when the norm–bounded state constraint is simultaneously considered during a scheduled finite–time period. This system is a typical hybrid system whose state trajectory instantaneously jumps according to a predetermined resetting law. The sufficient conditions of both state boundedness and output stability are proposed for the SLS in finite–time period when two typical classes of input signals are involved. Based on the linear matrix inequality, the design method of a controller using state feedback is represented to ensure state boundedness and output stability concurrently for the closed–loop system, which can effectively avoid states and the output reaching large and unacceptable values at certain points in finite time. An effective solution to the controller using a linear discretization approach is also achieved. Two simulation examples verify the proposed methods.
... The dominance regions were presented and analyzed to provide a complete solution to the game. Unlike previous research, two defenders were launched from the target to protect itself [22,23]. In Reference [23], the cooperation between the defenders and the target was one-way which meant one defender received the information from the target and another defender sent information to the target. ...
... The Hamiltonian functions corresponding to equations (23) and (22) are given by ...
The active defense scenario in which the attacker evades from the defender and pursues the target is investigated. In this scenario, the target evades from the attacker, and the defender intercepts the attacker by using the optimal strategies. The evasion and the pursuit boundaries are investigated for the attacker when the three players use the one-to-one optimal guidance laws, which are derived based on differential game theory. It is difficult for the attacker to accomplish the task by using the one-to-one optimal guidance law; thus, a new guidance law is derived. Unlike other papers, in this paper, the accelerations of the target and the defender are unknown to the attacker. The new strategy is derived by linearizing the model along the initial line of sight, and it is obtained based on the open-loop solution form as the closed-loop problem is hard to solve. The results of the guidance performance for the derived guidance law are presented by numerical simulations, and it shows that the attacker can evade the defender and intercept the target successfully by using the proposed strategy.
In this paper, two cooperative guidance schemes with impact angle and time constraints are proposed for multiple missiles cooperatively intercepting a maneuvering target in the presence or absence of a leader missile. First, cooperative interception with impact angle constraint is formulated based on the relative motion equation between the interceptors. Subsequently, the design of the guidance law is divided into two stages: In the first stage, based on finite-time consensus theory and the super-twisting control algorithm, the cooperative guidance law in the direction of the line of sight (LOS) is derived to control the impact time so that all missiles can simultaneously intercept the target in finite time. Then, based on finite-time sliding mode control and the super-twisting control algorithm, a finite-time convergence cooperative guidance law in the normal direction to the LOS is developed to control the intercept angle and the LOS angle rate so that each missile can accurately hit the target at a desired angle. Finally, by controlling the consensus error of flight time in the presence of a leader missile, a finite-time cooperative guidance method in the “leader-follower” scenario is derived for simultaneous arrival at the target. The proposed methods can effectively suppress chattering and ensure fast convergence in finite time. Simulation experiments are conducted to verify the effectiveness of the proposed cooperative guidance schemes.
This paper develops a multiaircraft cooperative detection scheme for effectively improving the accuracy when detecting the highly maneuvering target, where the cooperative estimate and observation trajectory planning of multiaircraft are addressed simultaneously. Based on the error compression ratio of the Markov matrix, an adaptive IMM algorithm is proposed for single detection, the convergence characteristic of which is theoretically proven meanwhile. Then, an adaptive IMM-information filtering algorithm is derived by embedding information filtering into the adaptive IMM algorithm for the fusion of the detection information. Next, the coordinated planning of observation trajectories is achieved for multiaircrafts by relying on receding horizon optimization (RHO) and the detection information. The cooperative detection and trajectory planning scheme is illustrated by the simulation results.
