Hardware-in-the-Loop Simulation And Performance Analysis For Terminal Guidance Of The Guided Bomb

Terminal guidance is an important stage to improve the precision of guided bomb.The hardware-in-the-loop simulation of the terminal guidance is a necessary step for the design of the guided bomb,and it is also an important content in the testing processing of guided weapon equipment.As the hardware-in-the-loop simulation can't be a lot of simulation and the equipment constraint,it is significant to analyze the influence of some significant guidance parameters and disturbance noise on the miss distance through the mathematical methods.In this paper,for the guidance and control system of guided bomb,hardware-in-the-loop simulation of the terminal guidance system and the performance analysis based on the adjoint method are carried out.The main research contents are as follows:Firstly,a six-degree-of-freedom mathematical model of missile is established under the emission coordinate system.The guidance law with angle constraint is deduced.And then the complete guidance control system program is established.This article will use the MATLAB and YHSIM for mathematical simulation to verify the feasibility of the guidance and control program.Secondly,according to the designing scheme of hardware-in-the-loop simulation of the guided weapons,this paper will complete the programming of the YH-SIM,the debugging of the turntable and IMU,the parameter debugging of the control system on the bomb computer,and the equipment communication test.Then the simulation of the missile-borne computer,real-time simulation computer,rudder,five-axis digital control turntable and navigation system(IMU)in the loop is ultimately completed.Then,for the constraint of hardware-in-the-loop simulation technology and the linearized problem of the adjoint model,the linear perturbation equations of vertical and lateral directions are established by the method of small perturbation and freezing coefficient.Next this paper will compare the linearized model with the nonlinear model to verify whether the derived linearization equation is correct.Finally,based on the previous linearization equation,the adjoint model of the terminal guidance loop is set up.The influence of the disturbance inputs(heading error and disturbance torque),two line of sight rate measurement noise(range independent noise and glint noise)and the noise of random target maneuver on the terminal guidance accuracy is analyzed.