一种小型弹载混合式光纤惯导系统设计

为解决混合式惯导在小型弹载惯导系统的应用问题，在论述混合式惯导技术特点的基础上，提出小型弹载混合式惯导系统所涉及的三项关键技术：小型化设计技术，抗振动高可靠锁紧技术和基于降维Kalman滤波的抗扰动自标定技术。重点对第三项技术提出具体的技术方案和实现途径。在建立惯导误差模型的基础上，根据姿态精度因子(ADOP)可观测度设计出混合式惯导系统的自标定流程，进行了卡尔曼滤波的降维处理和抗干扰观测量设计。开展了原理样机的标定试验、力学环境试验和导航精度试验工作，试验结果校验了技术方案的可行性和自标定算法的正确性，为其在小型战术导弹中的应用提供了工程借鉴。

Design of A Small Missile borne Hybrid Optical Fiber Inertial Navigation System

In order to solve the problem of a hybrid inertial navigation system applied in a small missile-borne inertial navigation system, the characteristics of this technology are discussed and three key technologies for the small missile-borne hybrid inertial navigation system are proposed, i.e. the technology of miniaturization, anti-vibration and high-reliability locking, and self-calibration of anti-disturbance based on the reduced-dimension Kalman filter. The specific technical solutions and ways for the third technology are proposed. Firstly, based on the error model of the inertial navigation system, the self-calibration flow of the hybrid inertial navigation system is designed according to the observability of the attitude precision factor (ADOP). Secondly, the dimension reduction and anti-jamming observation design of the Kalman filter are carried out. Finally, the calibration test, mechanical environment test and navigation test are carried out. The experimental results verify the feasibility of the technical scheme and the correctness of the self-calibration algorithm, and provide engineering reference for its applications in small tactical missiles.