飞控系统初始姿态角自动生成方法研究  

Research on Automatic Generation Method of Initial Attitude Angle for Flight Control Systems

作　　者：符冰[1] 周本川 FU Bing;ZHOU Benchuan(China Airborne Missile Academy,Luoyang 471009;National Key Laboratory of Air-based Information Perception and Fusion,Luoyang 471009)

机构地区：[1]中国空空导弹研究院,洛阳471009 [2]空基信息感知与融合全国重点实验室,洛阳471009

出　　处：《导航与控制》2025年第1期83-89,共7页Navigation and Control

摘　　要：随着现代飞行器对飞控系统精度要求的持续提升,飞控系统的测试工作变得日益重要。在飞控系统测试过程中,初始姿态角的准确输入对于评估飞行器的导航性能至关重要。传统的手动输入方式存在效率低下、易出错等问题,为解决这些问题,基于产品自身输出的角速度及速度增量信息,提出了一种产品姿态角自动生成的方法,并通过试验验证了其有效性。试验结果表明,该方法能够有效替代手动输入,并成功应用于产品测试、交付等各个流程,将姿态设定时间从平均30 min缩短至5 min,时间缩短了83.33%,同时避免了人为错误,显著提升了飞控系统测试流程的效率和可靠性。With the continuous improvement of precision requirements for flight control systems in modern aircraft,the testing work of flight control systems has become increasingly important.Accurate input of initial attitude angle is crucial for evaluating the navigation performance of the aircraft during the flight control system testing process.The traditional manual input method has problems such as low efficiency and error susceptibility.To solve these problems,a method for automatically generating product attitude angles based on the angular velocity and velocity increment information output by the product itself is proposed,and its effectiveness is verified through experiments.The experimental results show that this method can effectively replace manual input and has been successfully applied in various processes such as product testing and delivery.It reduces the attitude setting time from an average of 30 min to 5 min,with a time reduction of 83.33%.At the same time,it avoids human errors and significantly improves the efficiency and reliability of the flight control system testing process.

关 键 词：飞控系统 测试 初始姿态角 自对准算法 

分 类 号：TJ76[兵器科学与技术—武器系统与运用工程]