Design of an orbital debris radar ground demonstration

IEEE Aerospace Applications Conference Pub Date : 1900-01-01 DOI:10.1109/AERO.1989.82427

I. Paz, J. R. Carl, R. Shaw, J. Kovitz, G. Arndt

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引用次数: 5

Abstract

The authors describe a breadboard radar system that is being designed and tested at the Johnson Space Center for dealing with the space debris problem that could present a growing threat to the planned Space Station Freedom. The major problems that the design of such a system faces are due to the small radar cross section (RCS) of such debris (below -30 dBm/sup 2/), the high closing velocities of the particles with respect to the space station (10 km/sec and higher), and the stringent constraints imposed on its implementation as a spaceborne system. These constraints include weight, prime power consumption, maintenance, and reliability. The authors discuss the preliminary implementation of a ground demonstration radar for testing concepts, technologies, and performance envelopes that will eventually carry over to the space-borne debris detection and tracking radar. Simulation results and techniques developed for predicting system performances and for evaluating antenna parameters are given. The design process of the electronically steered phased array antenna is briefly described and block diagrams for the implementation of the radar system are given.<>

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轨道碎片雷达地面演示设计

作者描述了一种面包板雷达系统，该系统正在约翰逊航天中心设计和测试，用于处理可能对计划中的“自由”空间站构成日益严重威胁的空间碎片问题。这种系统设计面临的主要问题是由于这种碎片的雷达横截面(RCS)小(低于-30 dBm/sup /)，粒子相对于空间站的高接近速度(10公里/秒或更高)，以及对其作为星载系统实施的严格限制。这些限制包括重量、主要功耗、维护和可靠性。作者讨论了地面演示雷达的初步实施，用于测试概念、技术和性能信封，最终将延续到天基碎片探测和跟踪雷达。给出了预测系统性能和评估天线参数的仿真结果和技术。简述了电子控制相控阵天线的设计过程，给出了雷达系统的实现框图。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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IEEE Aerospace Applications Conference

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