Model aided airborne integrated navigation system based on an improved square-root unscented H∞ filter

• Published in: Transactions of the Institute of Measurement and Control 2019-03, Vol.41 (5), p.1290-1300
• Main Authors: Shen, Jieliang, Su, Yan, Liang, Qing, Zhu, Xinhua
• Format: Article
• Language: English
• Subjects: Aircraft; Aircraft configurations; Algorithms; Computer simulation; Covariance matrix; Dynamic models; Economic models; Extended Kalman filter; Fixed wings; Flight tests; Global navigation satellite system; H-infinity control; Inertial navigation; Navigation satellites; Navigation systems; Nonlinear equations; Nonlinearity
• ISSN: 0142-3312; 1477-0369
• DOI: 10.1177/0142331218776718

An inertial navigation system (INS) aided with an aircraft dynamic model (ADM) is developed as a novel airborne integrated navigation system, coping with the absence of a global navigation satellite system. To overcome the shortcomings of the conventional linear integration of INS/ADM based on an extended Kalman filter, a nonlinear integration method is proposed. Fast-update ADM makes it possible to utilize a direct filtering method, which employs nonlinear INS mechanics as system equations and a nonlinear ADM as observation equations, substituting the indirect filtering based on linear error equations. The strong nonlinearity generally calls for an unscented Kalman filter to accomplish the fusion process. Dealing with the model uncertainty, the inaccurate statistical characteristics of the noise and the potential nonpositive definiteness of the covariance matrix, an improved square-root unscented H∞ filter (ISRUHF) is derived in the paper, in which the robust factor γ is further expanded into a diagonal matrix Γ , to improve the accuracy and robustness of the integrated navigation system. Corresponding simulations as well as real flight tests based on a small-scale fixed-wing aircraft are operated and ISRUHF shows superiority compared with the commonly used fusion algorithm.