空间飞行器的有效屏蔽效能

A. Rashid
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引用次数: 0

摘要

已经开发了一个数学公式来预测空间飞行器从内部到外部的屏蔽效果。该公式表明,该空间飞行器的屏蔽效能随其外部观测点的变化而变化。提出了一种测量航天器屏蔽效能的可行方法。航天器内设备的电磁兼容性取决于航天器的屏蔽效能。在空间飞行器内部设备产生干扰信号的情况下,安装在外部的天线接收所需信号。这种干扰信号穿透结构并被外部天线接收。通过电缆屏蔽、设备外壳屏蔽和车辆结构屏蔽,可以降低这种干扰信号的幅度。该结构从内到外的屏蔽效能取决于源在空间飞行器内部的位置、飞行器结构上的孔径和垫片以及电缆穿透飞行器结构的方法。太空飞行器的一个典型例子是GPS卫星。它由四个天线系统组成:1)由螺旋天线阵列组成的l波段天线系统。(2)由锥形螺旋组成的遥测、跟踪和指挥天线系统。(3)超高频偶极子天线和(4)W-Sensor天线,如图1所示。测量空间飞行器屏蔽效能的典型方法如图2所示。该方法将空间飞行器结构绕其轴线旋转,利用空间飞行器内部的源,测量结构上各点的电场强度。需要改变空间飞行器内部源位置,以考虑源位置对空间飞行器屏蔽效能的影响;生成。在给定频率下结构的最小屏蔽效能应被接受为结构的真实屏蔽效能。如果不能接受这样的真实屏蔽效能值,则可以在结构上实施各种技术来提高其屏蔽效能。Ch2294-7/86/000-0062 $01.00©1986 ieee 62
本文章由计算机程序翻译,如有差异,请以英文原文为准。
The Effective Shielding Effectiveness of a Space Vehicle
A mathematical formula has been developed to predict the shielding effectiveness, from inside to outside, of a space vehicle. Such a formula shows that the shielding effectiveness of such a space vehicle varies as the point of observation on the outside of the space vehicle is varied. A possible method of measuring the shielding effectiveness of a space vehicle is presented. The electromagnetic compatibility of equipments inside a space vehicle depends upon the shielding effectiveness of the space vehicle. Antennas mounted externally receives desired signals in the presence of interfering signals generated by equipments within the space vehicle. Such interfering signals penetrate the structure and are received by the external antennas. The amplitude of such interfering signals may be reduced by cable shielding, equipment case shielding and vehicle structural shielding. The shielding effectiveness of the structure, from inside to outside, depends upon the location of the source inside the space vehicle, the apertures and shims on the vehicle structure, and the method of cable penetrations through the vehicle structure. A typical example of a space vehicle is the GPS satellite. It consists of four antenna systems: i) an L-band antenna system consisting of a helex antenna array. (2) telemetry, tracking and command antenna system consisting of conical spirals. (3) an UHF dipole and (4) a W-Sensor antenna as shown in figure 1. A typical method of measuring the shielding effectiveness of a space vehicle is shown in figure 2. In this method, the space vehicle structure is rotated about its axis and the electric field intensity, at various points on the structure, may be measured with the source located inside the space vehicle. The location of the source inside the space vehicle needs to be varied to take into account the effect of source location on the shielding effectiveness of the ; ructure. The measured minimum shielding effectiveness of the structure at a given frequency should be accepted as the true shielding effectiveness of the structure. If such a true shielding effectiveness value is unacceptable, various techniques may be implemented on the structure to increase its shielding effectiveness. CH2294-7/86/000-0062 $01.00©1986 IEEE 62
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