Design Of Guidance And Control System Of Rotating Rocket And Its Semi-physical Simulation Experiment

With the rapid development of modern guidance control theory,guidance modification becomes the development trend of rotary rocket.Compared with the traditional rocket,the guidance and control system of this kind of rocket adopts the configuration mode of "full strapdown laser semi-active seeker +MEMS IMU+single-channel electric steering engine".Aiming at the configuration characteristics,a new guidance control system is designed in this paper,and the line-of-sight angular rate extraction of the full strapdown seeker and the control method of the single-channel steering gear are studied.In order to verify the correctness of the design of guidance and control system,this paper,under the existing laboratory conditions,through the improvement of the general control console,turntable and other equipment,combined with advanced simulation concept,builds a semi-physical simulation system suitable for this type of rotating rocket,and completes the semi-physical simulation experiment.In this paper,the definition of coordinate system is given,the transformation matrix of coordinate system is derived,and the equations of motion of rotating rocket are enumerated.Secondly,the guidance control system is designed from two aspects: stability control loop and guidance control loop.The overload pilot and three-loop pilot are modeled,the parameters of single-channel control are designed,and the control parameters in the guidance control system are obtained.The guidance mode of guidance control system is clarified and its guidance law is derived.According to the characteristics of full strapdown seeker,the line of sight angular rate is extracted by CKF filtering algorithm,and the guidance information required by the missile computer is obtained.This control mode of single channel steering gear system with two reversals in one cycle is designed.The design of filtering algorithm and guidance control system is verified by mathematical simulation.Then according to the composition and working principle of the guidance and control system of this type of rotating rocket,a set of distributed architecture with high real-time,high safety and high automation hardware-in-the-loop simulation system is constructed by combining the existing equipment in the laboratory.After that,the hardware and software of the semi-physical simulation system is designed in combination with the underlying signal characteristics such as the missile guidance and control system workflow and communication protocol,and the software and hardware simulation environment of the semi-physical simulation system is built to ensure that the simulation system meets the extremely high real-time requirements of the missile guidance and control system.Finally,the semi-physical simulation experiment of the missile guidance and control system is carried out,the semi-physical simulation experiment outline is compiled,and the test items and process are defined.Through the simulation experiment of different initial launch conditions,the control parameters and structure are iterated,and finally the hitting accuracy meets the missile index requirements.