基于光学增强的GNSS/INS系统完整性监测

A. Schwithal, C. Tonhäuser, S. Wolkow, M. Angermann, P. Hecker, N. Mumm, F. Holzapfel
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引用次数: 9

摘要

可靠的飞机制导是当今现代飞机实现高水平安全的主要贡献者之一。特别是在飞机靠近周围交通和地面障碍物的着陆阶段,任何未被发现的偏离预期飞行路径都可能导致灾难性的后果。今天的自动着陆系统基于不同的地面制导技术,例如仪表着陆系统(ILS)。它们性能良好,但在安装和维护成本方面昂贵,因此只能在较大的机场使用。相比之下,较小的通用航空(GA)飞机和区域机场通常没有配备上述命名的着陆系统。因此,本文提出了一种替代的低成本通用飞机自主着陆系统,该系统不需要任何类型的地面导航设备。该系统由一个经典的GNSS/INS系统组成,该系统由一个用于完整性监测的新型光学定位系统增强。监视器确保由导航系统或制导系统引起的任何偏差都将提醒飞行员并触发自动复飞机动。本文概述了开发的系统架构,并给出了基本的监控算法。该系统的设计符合国际民航组织提出和公布的所需导航性能(RNP)概念。该系统仍在开发中,并在一架双引擎多尼尔128飞机上进行了实际飞行试验,在不伦瑞克机场的各种进近过程中进行了测试,见图1。本文对系统在正常运行时的性能进行了深入分析,并讨论了定位系统和飞行控制偏差造成的误差预算。最后,将模拟的传感器误差应用于记录的飞行数据,以验证在必要时间内进行故障检测的能力。下面的分析展示了系统目前已经实现的性能,并识别了与所需系统性能相关的潜在差距。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Integrity monitoring in GNSS/INS systems by optical augmentation
Reliable aircraft guidance is one of the main contributors to the high level of safety that is achieved today on modern aircraft. Especially during the landing phase, where aircraft are close to other surrounding traffic and ground obstacles, any undetected deviation from the desired flight path may lead to catastrophic consequences. Automatic landing systems today are based on different ground-based guidance techniques, for example the Instrument Landing System (ILS). They perform well but are expensive in terms of installation and maintenance costs and therefore are only available on bigger airports. In contrast smaller General Aviation (GA) aircraft and regional airports often are not equipped with the above named landing systems. Therefore, this paper presents an alternate low cost aircraft autonomous landing system for GA aircraft, which does not require any type of ground-based navigation equipment. The system consists of a classical GNSS/INS system that is augmented by a new optical positioning system for integrity monitoring. The monitor ensures that any deviation caused by either the navigation system or the guidance system will alert the pilot and trigger an automatic go-around maneuver. This paper outlines the developed system architecture and presents the basic monitoring algorithms. The system was designed in compliance with the Required Navigation Performance (RNP) concept introduced and published by ICAO. The system is still under development and was tested during real flight trials onboard a twin-engine Dornier 128 aircraft during various approaches on Braunschweig airport, see figure 1. This paper presents a profound analysis of the achieved system performance during normal operation and discusses the error budgets that result from the positioning system on the one hand and the flight control deviation on the other. Finally, simulated sensor errors were applied to the recorded flight data in order to demonstrate the fault detection capability within the necessary time to alert. The following analysis presents the performance that can already be achieved by the system today and identify potential gaps with respect to the required system performance.
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