Design And Implementation Of Rocket Borne High Precision Parachute Landing Measurement And Control System

With the continuous improvement of China’s national strength,the space field is developing rapidly,and the launch frequency and launch quality of China’s carrier rockets are constantly improving.However,the main type of carrier rockets at present are all disposable rockets,that is,during the launching process,after the main part of the rocket and booster are separated,the command system loses control of the booster,causing the separated rocket body to fall irregularly.This result will cause a very large safety hazard to the landing zone.Therefore,it is of great significance to monitor the position and control the drop point of the separated body after finishing the launch mission through the high-precision measurement and control system.Relying on XX booster recovery project,cooperating with the parachute control equipment,this high-precision measurement and control system on the rocket-borne realizes the control of parachate-openinga and return of the position information of the booster according to the falling speed and position in the arrow-mounted environment after the booster separation is completed.In this paper,the following three problems are studied :(1)How to realize the high precision navigation computer hardware platform that meets the rocket-borne environment? In this paper,a navigation platform based on FPGA+DSP is designed,and the circuit design from front-end sensor to final data acquisition is illustrated in detail.The design of high-precision navigation computer on rockets is realized.(2)How to realize real-time multi-sensor data synchronization and what kind of navigation algorithm is used to make the navigation result accuracy meet the requirements of rocket-borne environment? In this design,the navigation algorithm combined the sensor acquisition synchronization technology and the time registration technology are adopted.The enhanced Kalman filter model is adopted to meet the accuracy requirements in the rocket-borne environment.(3)How to realize the data return after calculation in the rocket-borne environment? In this design,the state detection module is used to transmit the attitude,position and speed of the rocket before launching,and the Beidou short message module is used to transmit the information after the booster separation.This paper analyzes the Beidou communication protocol and the baseband coding protocol adopted by the state detection module in detail,and completes the design of the related RF circuit.In this paper,the design verification is carried out in the real object way.Through the overall test of the high-precision measurement and control system,the working condition of each independent platform and the whole system are verified.Finally,the feasibility of the design and the reliability of the system are verified by being installed on a rocket during the actual launch.