Research On The Terminal Impact Angle Constraint Terminal Guidance Method Of Anti-ship Missile

Anti-ship missile is one of the necessary weapons for future wars, and itreceives more and more attentions from the major military powers all over the worldfor its capability of sea-skimming flight during the initial and middle guidancephases, and thus effectively covering the tracks. Proceeding to the21st century, thecountries of certain economic strength are all in great efforts to develop the warships,to form sea fleets and even aircraft carrier battle groups. Therefore, in order tocounter the large navy ship formation up to the hilt in a future war, anti-ship missilehas become extremely indispensable. The anti-ship missiles should be able to notonly hit the target accurately, but also hit a key component in the best attitude,leading to killing at one hit. Therefore, with the anti-ship missile as researchobjective, this paper designed its terminal guidance law under the three constraints ofthe overloads, the miss distance and the terminal impact angle. The main contents areas follows.First, this paper, according to the relevant principles of aerodynamics andtheoretical mechanics, combined with the characteristics and motions of the anti-shipmissile, established a mathematical model of the missile movement; according to themotion of a navy ship, presented the mathematical model of the target movement;moreover, in order to facilitate the following research on the terminal guidancemethod, this section also briefed on the basic theoretical knowledge of thesliding-mode variable-structure control and inverse design method in nonlinearcontrol theory.Second, based on the attitude constraint at the time that anti-ship missile hits thetarget, this paper defined the terminal impact angle, presented the necessary andsufficient conditions of the missile to hit the target with terminal impact angleconstraint, and derived the relevance between the expected terminal impact angle andthe desired line-of-sight. In addition, since the proportional guidance law is the mostwidely used and most mature one among the classical guidance laws, so the biasedproportional guidance law was designed on the basis of constrained requirements.Again, taking into account the disadvantage of traditional methods in dealingwith guidance problems and the inherent advantage of the various control methods in nonlinear control theory, the degree thesis use the Sliding Mode Variable Structurecontrol theory and Backstepping to solve the multiple-constraint terminal guidanceproblem of anti-ship missile, and made use of relevant theory to design asliding-mode variable-structure guidance law and inversion guidance law, and then,analyzed the feasibility of these two guidance laws theoretically.Finally, based on the traditional PID controller design method, this paperdesigned the three-channel attitude controller of the anti-ship missile, so as tosimulate and test the guidance laws designed above; and took whole trajectorysimulation of anti-ship missiles, analyzed the kinestate of the missile on the entirecourse of the campaign, and proved the effectiveness of the guidance laws.Furthermore, we also analyzed two key factors in guidance accuracy, which are themeasurement error in the seeker and the wind disturbance.