Electrical Design And Realization Of An Integrated Navigation System

With the rapid development of modern science and technology theory and military industrial technology,navigation,aviation,aerospace and other fields require higher and higher comprehensive navigating performance.With the development of microelectronics technology and computer technology,the integrated navigation system consist of multiple navigation systems has been deeply studied.Because of the different application scenarios,the method of designing requirements of navigation equipment is also different.It has become one of the most important research directions in the field of integrated navigation to design an accurate and fast navigating information collection and achieve controlling function for specific application scenarios.In this paper,we design an integrated navigation system based on Inertial Navigation System and Global Positioning System according to the practical engineering requirements.It implements the function of collecting and storing information on speed,position and attitude quickly and accurately during the falling process of the test bomb in real time.Moreover,the system adds control functions which can open the parachute based on the measured information.This thesis analysed the functional requirements of integrated navigation system,proposed a feasible general scheme according to functional requirements and performance indicators,and made a demonstration of device selection used in this system.This article detailedly designed the circuit according to the general scheme,including navigation solution module design,timing control module design,explosive bolt control module design,power module design and so on;The software design of the underlying function has been completed.The functions of data acquisition,data integration and storage,and communication among modules are realized by controlling external devices with FPGA.ARM is used to complete the integrated navigation solution and timing umbrella opening control functions.The system has been debugged and tested for many times.The test result proved that the integrated navigation system could quickly and accurately collect the velocity,position and attitude information of the test missile during its landing.It achieves the design requirements of high accuracy and the anticipated design goal,small size and low cost.