| With the rapid development of aerospace technology,the ability to defend against enemy’s air strikes and enhance the air penetration capability of their own high-value aircraft has received increasing attention.In this paper,the interception guidance law design and the active defense cooperative interception guidance design are the main research lines.On the one hand,it is necessary to improve dynamic performance of the guidance command in the process of designing the interception guidance law.Meanwhile,reducing the design difficulty of the guidance control gains is required.For example,reducing the deviation sensitivity of the guidance command with the preset state to improve the dynamic characteristics of the guidance command(smooth and continuous guidance command,reducing cumulative control consumption and command tracking error,etc.),as well as improving the robustness of the interception guidance law(reduced target maneuver Interference,modeling uncertainty,etc.);reducing the key design parameters of the interception guidance law,and expanding the selection range of parameters,as well as reducing the design difficulty of the guidance law control gain.On the other hand,considering the high-value aircraft and active defense missiles in the active defense of air defense missiles,the design of the interception guidance law is faced with the establishment of nonlinearity with uncertainties in both incomplete cooperative mode and fully coordinated mode.The dynamic model,the anti-aircraft missile attacking the own aircraft interception guidance law may be unknown in advance.Meanwhile,the design process of the active defense cooperative interception guidance law needs to solve the problem of reducing the terminal interception accuracy with the active defender’s residual interception time,and appropriately reducing the aircraft’s or active defense missile’s control consumption in the process of maneuvering,reducing the difficulty of designing the control gain in the interception guidance law,and improving the dynamic characteristics of the guidance command.By considering the uncertain effects of target maneuvering and system modeling,this paper systematically studies the following two aspects of guidance law design by using sliding mode control method,disturbance observer technology,dynamic surface control technology,inertial delay control technology and prescribed performance control method:1)When intercepting the maneuvering target at the end of interception phase,it is necessary to meet the terminal line-ofsight angle constraint.In the two-dimensional and three-dimensional space,new types of terminal interception guidance law are designed based on whether or not to consider the interceptor missile’s autopilot characteristics;2)The active defense cooperative interception problem,based on the threat of enemy air defense missile attack and the incomplete cooperative condition of the protected aircraft and active defense missile,the active defense missile to intercept the air defense missile homing the protected target needs to be designed;Meanwhile,the cooperative interception guidance law of the protected target and the active defense missile is designed under the condition of complete coordination.The main innovations of this paper are as follows:1)New type of terminal interception guidance laws based on sliding mode and prescribed performance control method are proposed.The design problem of the new terminal guidance laws considering the terminal line-of-sight angle constraint in the 2D and 3D space interception process is researched.New prescribed performance functions are constructed to achieve the goal of improving the dynamic characteristics of the missile guidance commands,meanwhile,the difficulty of designing the guidance gains is reduced,and the design requirement for ensuring terminal interception accuracy is ensured and robustness of the final interception guidance laws are guaranteed;2)A hybrid guidance strategy under the condition of fully cooperative active defense mode is proposed,and the active defense cooperative guidance law of high-value aircraft and active defense missiles under the condition of proportional interception guidance law for air defense missiles is studied and realized.Under the nonlinear framework,the goal of combining the prescribed performance and inertia delay control type guidance law and the sliding mode and inertia delay control type guidance law is achieved,which reduces the sensitivity of the hybrid guidance strategy with time-to-go of the active defense missile,and reduces the guidance control parameters.Accordingly,difficulty of designing the cooperative guidance law is reduced,and the design goal of active defense missile interception accuracy is guaranteed;3)The analytical cooperative interception guidance law under the condition of fully cooperative active defense mode is proposed,and the active defense cooperative interception of the unknown situation of the air defense missile guidance law under the nonlinear framework is researched,By setting the two constraints of zeroing the relative line-of-sight angle as well as zeroing the relative residual time deviation,the design requirements of the cooperative interception guidance law are designed by using the sliding mode control method and the inertial delay control technology,and the numerical allocation mode of the guidance command in the full cooperative mode is avoided.Under the condition of linear or nonlinear guidance laws may be adopted by the air defense missile to home the protected target,the technical requirements of the active defense missile to procisely intercept the air defense missile in advance can be guaranteed. |
