Research On The Control Method Of Air-to-air Missiles Based On Side Jet And Aerodynamics Compound Control

As the air combat environment becomes more and more complex, air-to-airmissiles have become the key factor in capturing air supremacy. A main researchdirection is the over-the-shoulder launch of an air-to-air missile. If the air-to-air missilehas the ability of over-the-shoulder launch, then the target would be omnidirectionalattacked.In this paper, sliding mode control is used to design the control law of missileattitude. The simulations reveal that this kind of control law realizes the agile turnstably. In addition, the studies of terminal guidance process are also included in thethesis. More details are as follows.First, the mathematical model of an air-to-air missile is established. Consideringthe agile turn in pitching plane, the mathematical model of missile motion and thedynamic model of the missile attitude control system are established. Due to thechange of the aerodynamic force with the change of the angle of attack, the dynamicmodels of the missile attitude control system include small angle-of-attack attitudecontrol model and large angle-of-attack attitude control model.Second, the control law of missile attitude are designed. The pitch anglecommands are given by using the numerical optimization method firstly. Then, we usetwo kinds of second-order sliding mode control methods, twisting method andsuper-twisting method, to design the control laws of missile attitude.Finally, simulations are conducted for the two kinds of control systems. From theresults of the simulations, we can see that the missile realizes the agile turn stably. Inaddition, the results also show that attitude control with second-order sliding modecontrol method can inhibit the chattering of the system more obviously thanconventional sliding mode control...