A large squint attitude maneuver method for fast-sounding SAR satellites

A technology of attitude maneuvering and large squint, which is applied in the direction of instruments, measuring devices, and utilization of re-radiation, etc., can solve the problem of increasing the weight, power consumption and development cost of the whole star, increasing the complexity of squint SAR image processing, and reducing the efficiency of military target observation and other issues to achieve the effect of improving observation efficiency and identification ability

Active Publication Date: 2021-02-09
XIAN INSTITUE OF SPACE RADIO TECH
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Problems solved by technology

However, these TR units and networks will greatly increase the weight, power consumption and development cost of the entire star
The above problems can be effectively avoided by driving the antenna beam scanning through the maneuvering of fast-response SAR satellites. However, very precise control requirements will be put forward for fast-response SAR satellites. Otherwise, the attitude deviation of the satellite will directly lead to the deviation of the beam pointing, reducing military The observation efficiency of the target increases the complexity of squint SAR image processing

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  • A large squint attitude maneuver method for fast-sounding SAR satellites
  • A large squint attitude maneuver method for fast-sounding SAR satellites
  • A large squint attitude maneuver method for fast-sounding SAR satellites

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[0030] In order to ensure that the antenna beam is accurately pointed to the target during the large squint observation of the fast-response SAR satellite, and at the same time the Doppler frequency change of the distance to each sampling point meets the imaging requirements, the present invention adopts figure 1 The given process is designed: the first step is to calculate the scene according to the position vector of the center of the target scene in the geocentric fixed coordinate system, the time of the satellite passing through the scene orbit segment, and the position velocity vector of the satellite passing through the scene orbit segment in the geocentric fixed coordinate system The moment when the relative velocity between the center and the satellite is zero; the second step is to calculate the moment of the squint observation center, the satellite position vector and the velocity vector in the geocentric fixed coordinate system at the moment of the squint observation ...

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Abstract

A fast-response SAR satellite large squint attitude maneuvering method, the steps are as follows: 1) determine the moment when the relative velocity between the center of the scene and the satellite is zero; Position vector and velocity vector; 3) Calculate the imaging start time and end time of the squint observation; 4) Calculate the satellite attitude maneuver parameters at the center of the squint observation; Maneuver with the attitude maneuver parameters at the center time; 6) Reserve the beam to be marked on the distance angle and azimuth angle in the coordinate system of the satellite body, and correct the beam pointing according to the beam pointing calibration value after the orbit. The invention guarantees that the antenna beam is accurately pointed to the target when the fast-response SAR satellite is observed with a large squint, and at the same time, the Doppler frequency change of the distance to each sampling point satisfies the imaging requirement.

Description

technical field [0001] The invention belongs to the technical field of space microwave remote sensing, and relates to a large squint attitude maneuvering method of a fast-response SAR satellite. Background technique [0002] In order to improve the observation efficiency and identification ability of spaceborne SAR for military targets, it is necessary to conduct multiple multi-angle observations and imaging of military targets in the left / right side-looking single track from front-sight to rear-sight range. If the phase scanning method is used to realize the front / rear-sight beam scanning in the left / right-sight single track, a huge number of TR modules, feeding networks, and thermal control networks are required to ensure the electrical performance of the antenna beam during scanning. However, these TR units and networks will greatly increase the weight, power consumption and development cost of the entire star. The above problems can be effectively avoided by driving the...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01S13/90
Inventor 贺荣荣贺保平吴疆杨娟娟高阳党红杏谭小敏冯帆
Owner XIAN INSTITUE OF SPACE RADIO TECH
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