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Stellar Refraction-Based SINS/CNS Integrated Navigation System for Aerospace Vehicles

机译：基于恒星折射的SINS / CNS组合导航系统

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摘要

Stellar refraction-based celestial navigation is an attractive method with high accuracy and low cost. Most existing research works only focus on orbit determination problems for orbital vehicles in outer space while its working domain is limited. In order to expand its applicable area and improve information utilization, a new fault-tolerant stellar refraction-based inertial/celestial integrated navigation system is designed in this work, which is supposed to provide accurate position, velocity, and attitude information for aerospace vehicles that either make a maneuvering flight in near space or move in a predetermined Earth orbit in outer space. First, a new nonlinear navigation system dynamic model is established by error-prorogation equations of the strapdown inertial navigation system (SINS) in the Earth-centered inertial (ECI) frame, in which additive quaternion with less model error is used for attitude computation. Secondly, celestial navigation subsystem (CNS) is used to indirectly sense the horizon by utilizing the starlight atmospheric refraction model and determine the vehicle attitude by means of a multistar vector observation method. Thirdly, a fault-tolerant federated unscented Kalman filtering (FFUKF) algorithm is employed to perform information fusion, aiming at improving the navigation accuracy and reliability. Numerical simulations are conducted for an aerospace vehicle either in a near space maneuvering flight or in an orbital flight along a low Earth orbit. The results show that the proposed strategy achieves higher accuracy than traditional methods, and all the navigation parameters can be estimated. Moreover, different measurement faults are introduced in the simulations, and the FFUKF algorithm manages to detect and isolate them and keep the navigation system working in normal operation.
机译：基于恒星折射的天体导航是一种具有高精度和低成本的有吸引力的方法。现有的大多数研究工作仅关注外层空间轨道飞行器的轨道确定问题，而其工作范围有限。为了扩大其适用范围并提高信息利用率，本文设计了一种基于容错恒星折射的惯性/天体组合导航系统，旨在为航天器提供准确的位置，速度和姿态信息。要么在近太空进行机动飞行，要么在外层空间预定的地球轨道中移动。首先，通过以地球为中心的惯性（ECI）框架中的捷联惯性导航系统（SINS）的误差修正方程，建立了一个新的非线性导航系统动力学模型，其中使用模型误差较小的加法四元数进行姿态计算。其次，天体导航子系统（CNS）通过利用星光大气折射模型间接感知地平线，并通过多星矢量观测方法确定车辆姿态。第三，采用容错的联邦无味卡尔曼滤波（FFUKF）算法进行信息融合，以提高导航的准确性和可靠性。在近太空机动飞行或沿低地球轨道的轨道飞行中，对航空航天器进行了数值模拟。结果表明，所提策略比传统方法具有更高的精度，并且可以估计所有的导航参数。此外，在仿真中引入了不同的测量故障，并且FFUKF算法设法对它们进行检测和隔离，并使导航系统保持正常运行。

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