Driving mechanism for synthetic aperture radar satellite

A technology of synthetic aperture radar and driving mechanism, which is applied in the direction of radio wave reflection/re-radiation, utilization of re-radiation, measurement devices, etc., and can solve the problem that the installation stress of the solar cell array and the driving mechanism cannot be effectively controlled, directly measured and determined, Repeatability is difficult to guarantee and other problems, to achieve the effect of improving the lighting situation, simplifying the work of precision measurement, and avoiding repeated work

Active Publication Date: 2013-12-18
SHANGHAI SATELLITE ENG INST
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Problems solved by technology

However, since the installation datum of the solar array (the intersection of the solar cell array docking flange surface of the driving mechanism and the axis of the driving mechanism) is virtual and cannot be directly measured and determined, it is impossible to directly locate and drill holes on the mounting plate using the traditional method , installation, even if it is barely installed, it will face the problem of frequent disassembly and assembly, the measurement workload is heavy and the repeatability is difficult to guarantee, and the installation stress between the solar cell array and the driving mechanism cannot be effectively controlled

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  • Driving mechanism for synthetic aperture radar satellite
  • Driving mechanism for synthetic aperture radar satellite
  • Driving mechanism for synthetic aperture radar satellite

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Embodiment Construction

[0012] The present invention will be further described in detail below in conjunction with the drawings and specific embodiments:

[0013] Such as figure 1 , 2 As shown, the satellite payload (antenna) requires an oblique view of the ground. Accordingly, in addition to the oblique installation of the floor (installed with infrared earth sensors, measurement and control antennas, digital antennas, etc.), in order to minimize the sun The interference torque generated by the battery array 20 on the solar tracking orientation affects the control accuracy of the satellite, and the illumination of the solar battery array 20 is ensured to the greatest extent. The driving mechanism 1 and 2 are designed to be inclined by 15° in consideration of the satellite orbit and other factors. According to the design requirements of the solar cell array 20, the side where the cell sheets 3 and 4 are attached must face the outer side of the star 10 in the folded state. Considering the situation of th...

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Abstract

The present invention relates to a solar cell array driving mechanism oblique mounting technology, belongs to the field of radar satellite configuration design, and concretely discloses a driving mechanism for a synthetic aperture radar satellite. Two driving mechanisms are respectively installed on a positive and a negative Y separator plate of the satellite body and obliquely installed at an angle of 15 degrees together with the surfaces with solar cells bonded thereon, and the solar cell arrays of the two driving mechanisms are installed in an antisymmetric manner. The driving mechanism for synthetic aperture radar satellite of the invention is obliquely installed by an angle according to the angle of oblique flying of the satellite, thereby reducing the influence on the satellite control precision caused by the interference moment, wherein the interference moment is generated by that the solar cell arrays tracks and toward the sun, and enlarging the effective illuminating area of the solar battery arrays.

Description

Technical field [0001] The invention relates to a driving mechanism of a synthetic aperture radar satellite. Background technique [0002] A certain satellite is my country's first X-band synthetic aperture radar satellite, with two driving mechanisms, which are respectively installed on the ±Y partition of the satellite. Since the antenna used as the satellite load needs to be viewed obliquely to the ground, and the antenna is installed upright, the satellite body needs to fly obliquely. In order to ensure the energy supply of the entire satellite, and to reduce the influence of the interference torque generated by the solar array on the solar tracking orientation on the satellite control accuracy, it is necessary to install the driving mechanism on the satellite obliquely to correct the angle of the satellite's oblique flight. The solar array has the best light. However, because the installation datum of the solar array (the intersection of the driving mechanism's solar array...

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Application Information

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IPC IPC(8): G01S7/02G01S7/36G01S13/90
Inventor 张丙良孙永岩訾海峰吴以平
Owner SHANGHAI SATELLITE ENG INST
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