Research On Modeling And Control Of Small Loitering Missile

Loitering missile is an important product of the improvement of the informational warfare, whichis a new smart munition containing various high-techs. According to the tactical requirements of thesmall loitering missile, this paper will separate the sample loitering missile’s characteristics into twoparts: the Missile characteristics and the UAV (Unmanned Aerial Vehicle) characteristics, and dosome focus research on the UAV characteristics. Therefore, the main work of this thesis is onmodeling of the sample loitering missile, object characteristics analysis, and flight control law design.Firstly, this thesis introduces the characteristics of the loitering missile briefly，decomposes theLoitering Missile flight, and points out the research direction of the simplified configurationaccording to the design requirements.Secondly, according to the flight phase of the loitering missile，this thesis establishes a sampleUAV mathematical model, analyzes every phase’s stability and control characteristics, researches theflight characteristics in the main loitering phase from the control perspective, and finds the key to theflight control solution according to the object analysis results.Thirdly, this thesis mainly designs the flight control system in the light of the loitering phase. Thefirst step is designing the control law of the full configuration. According to the results of theconventional control method and the lateral characteristics of the loitering missile, then, the thesispropose a control solution based on rolling angle rate. Through some comparative analysis in the mainproperties, this thesis proves that sample loitering missile prefers the lateral control solution based onrolling angle rate. In the end, the thesis proposes a simplified configuration control solution based onthe full configuration solution, and proves the feasibility of the simplified configuration controlsolution through a comparative analysis of the conventional solution.At last, in the MATLAB simulation environment based on M language, the loitering missile’swhole process autonomous flight simulation is realized. The simulation results show that themathematical model of the sample loitering missile is available, flight control solution is feasible, andconfirm the basic flight properties of the full configuration control solution.