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Towerless phase correction method for simulating target position characteristics based on offset antenna

A technology for simulating targets and antennas, applied in the field of aerospace measurement and control, can solve the problem of high cost, and achieve the effect of simple calibration process

Active Publication Date: 2020-11-24
北京航天驭星科技有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

The traditional calibration method needs to build a calibration tower tens of meters high to assist in the completion, which is relatively expensive

Method used

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  • Towerless phase correction method for simulating target position characteristics based on offset antenna

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Embodiment Construction

[0022] The specific embodiments of the present invention will be further described below in conjunction with the accompanying drawings. It should be noted here that the descriptions of these embodiments are used to help understand the present invention, but are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below may be combined with each other as long as they do not constitute a conflict with each other.

[0023] In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", " Back", "Left", "Right", "Vertical", "Horizontal", "Top", "Bottom", "Inner", "Outer", "Clockwise", "Counterclockwise", "Axial", The orientation or positional relationship indicated by "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawi...

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Abstract

The invention relates to the technical field of spaceflight measurement and control. The invention specifically discloses a towerless phase correction method for simulating target position characteristics based on an offset antenna. The method comprises the steps: in an equipment joint test or tracking exercise period, performing phase correction by using a target signal source meeting a far-fieldcondition, transmitting a frequency point signal through an offset antenna after phase correction is completed, feeding in a sum and difference signal downlink, and recording azimuth and pitch angleerror voltage and polarity thereof output by a demodulator; before a target is tracked, transmitting the frequency point signal through the offset antenna, and adjusting a phase shifter and a gain control coefficient to enable the magnitude and polarity of azimuth and pitch angle error voltage to be equal to those of a previous recorded value. According to the invention, the phase calibration function can be quickly realized before satellite tracking under the condition of no tower, the precision is equivalent to that of calibration tower phase calibration, and the phase calibration process issimple.

Description

technical field [0001] The invention relates to the technical field of aerospace measurement and control, in particular to a towerless phasing method for simulating target position characteristics based on an offset feed antenna. Background technique [0002] At present, most ground station antennas of aerospace measurement and control systems adopt a single-pulse dual-channel tracking system. Because the sum and difference signals are transmitted in different channels, the phase difference of the sum and difference signals drifts with time. In order to ensure the tracking function, the tracking satellite The phase consistency of the sum and difference channels must be calibrated, that is, the phase correction process is completed. The traditional calibration method needs to build a calibration tower tens of meters high to assist in the completion, which is relatively expensive. Contents of the invention [0003] The technical problem to be solved by the present invention...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01R25/00G01R29/10H04B17/12
CPCG01R25/00G01R29/10H04B17/12
Inventor 梁立明陈新宁尚建忠苏新军王新宏王青松
Owner 北京航天驭星科技有限公司
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