用于重复通道干涉测量变形的UAVSAR设计现状

S. Hensley, K. Wheeler, G. Sadowy, T. Miller, S. Shaffer, R. Muellerschoen, Cathleen E. Jones, H. Zebker, S. Madsen, P. Rosen
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引用次数: 0

摘要

美国宇航局喷气推进实验室目前正在实施一种可重构极化l波段合成孔径雷达(SAR),专门用于获取机载重复跟踪干涉(RTI) SAR数据,也称为差分干涉测量。微分干涉测量法可以提供关键的形变测量,这对地震和火山的科学研究很重要。使用精确的实时GPS和传感器控制的飞行管理系统,该系统将能够以极高的精度飞行预定路径。飞行控制系统的预期性能将约束飞行路径在一个10米直径的管约所需的飞行轨迹。该雷达将被设计用于无人机(无人驾驶Arial飞行器),但最初将在最低限度驾驶飞行器(MPV)上进行演示,如Scaled Composites公司制造的Proteus或NASA湾流III型飞机。该雷达设计为全极化雷达,带宽为80 MHz(2米距离分辨率),范围为16公里。天线是一个电子操纵沿着轨道,以确保实际的天线指向可以控制独立的风向和速度。该天线支持的其他功能包括仰角单脉冲选项和脉冲对脉冲重定向能力,这将使一些新颖的操作模式成为可能。该系统名义上将在45000英尺(13800米)的高空运行,该项目最初是由NASA地球科学与技术办公室(ESTO)资助的仪器孵化器项目(IIP)。
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Status of a UAVSAR Designed for Repeat Pass Interferometry for Deformation Measurements
NASA's Jet Propulsion Laboratory is currently implementing a reconfigurable polarimetric L-band synthetic aperture radar (SAR), specifically designed to acquire airborne repeat track interferometric (RTI) SAR data, also known as differential interferometric measurements. Differential interferometry can provide key deformation measurements, important for the scientific studies of Earthquakes and volcanoes. Using precision real-time GPS and a sensor controlled flight management system, the system will be able to fly predefined paths with great precision. The expected performance of the flight control system will constrain the flight path to be within a 10 m diameter tube about the desired flight track. The radar will be designed to operate on a UAV (Unpiloted Arial Vehicle) but will initially be demonstrated on a minimally piloted vehicle (MPV), such as the Proteus built by Scaled Composites or on a NASA Gulfstream III. The radar design is a fully polarimetric with an 80 MHz bandwidth (2 m range resolution) and 16 km range swath. The antenna is an electronically steered along track to assure that the actual antenna pointing can be controlled independent of the wind direction and speed. Other features supported by the antenna include an elevation monopulse option and a pulse-to-pulse resteering capability that will enable some novel modes of operation. The system will nominally operate at 45,000 ft (13800 m). The program began out as an Instrument Incubator Project (IIP) funded by NASA Earth Science and Technology Office (ESTO).
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