Research On The Low-cost Navigation System For The Precise Landing Of The First Stage Of The Rocket

In recent years,with the launch of high-intensity and high-density launch vehicles from various countries around the world,the issue of control over the fall of rocket debris has attracted more and more attention.Aiming at the constraints of the available space of the first stage of the rocket,severe temperature changes during the recycling process,and complicated electromagnetic environment,the current traditional navigation systems cannot meet the demand.Therefore,under the consideration of power consumption and volume,it is necessary to develop a low-cost,high-reliability navigation system.This article takes the development of a sub-class recovery integrated navigation system for a certain launch vehicle as the background,and aims to reduce costs and ensure the accuracy and reliability of the integrated navigation system.The following four aspects are studied in the design of the navigation system:(1)Since the MIMU/GNSS integrated navigation method is selected to reduce development costs,the calibration and compensation algorithm of the MIMU error model in the "three-in-one" integrated navigation unit is mainly studied.And the effectiveness of the compensation algorithm is verified by experiments.At the same time,the design of inertial navigation solution and Kalman filter based on geographic system are detailed.(2)Aiming at the design requirements of the navigation system hardware platform for a sub-level flight environment,the design scheme of the overall architecture of the navigation flight control computer is given,and the main modules in the circuit are introduced in detail.Combined with the problems found during the design and debugging stage,the precautions for circuit design are given.(3)In order to ensure that the navigation flight control computer can normally perform navigation and control command calculation complete the long-distance data interaction with the servo,and ensure the reliability of the rocket take-off and separation signal detection under the environment of strong electromagnetic interference,the electromagnetic immunity characteristics of navigation flight control computer are studied from two aspects of conducted immunity and radiation immunity.(4)The reliability test and flight test of flight control computer verify that the reliability and accuracy of the integrated navigation system designed in this paper meet the requirements.