Split type lens and split type static linear array infrared horizon sensor

Abstract

The invention relates to a split type static linear array infrared horizon sensor which comprises at least one group of split type lens and split type installation base matched with each other. In the split type lens, an imaging light path is connected with a linear array detector which is connected with a multi-path selector, the multi-path selector is connected with a preamplifier and an FPGA (Field Programmable Gate Array) chip respectively, the preamplifier is connected with an analog-digital converter and the FPGA chip respectively, the analog-digital converter is connected with the preamplifier and the FPGA chip respectively, the FPGA chip is used for respectively generating control signals of the multi-path selector, the preamplifier and the analog-digital converter, performing signal processing on transmitted digital signals and then transmitting the digital signals to a CAN (Controller Area Network) interface chip, and the CAN interface chip is connected with a CAN bus through a CAN bus interface and used for transmitting the signals which are processed by the FPGA chip to the back-end digital processing part through the CAN bus. According to the split type static linear array infrared horizon sensor, the degree of generalization of the infrared horizon sensor is increased, the development process is simplified, and the project cost is saved.

Description

technical field [0001] The invention relates to the technical field of space science instruments, in particular to a modular split-type static linear array infrared horizon instrument applied to attitude measurement of spacecraft. Background technique [0002] Any object in nature with a temperature higher than absolute zero (minus 273.15 degrees Celsius) will radiate heat to the surroundings. Infrared radiation is a part of heat radiation and is an invisible light adjacent to visible light. The intensity and spectral composition of infrared radiation depends on the radiation temperature of the object. General infrared detection uses the difference in infrared radiation between the target and the background to obtain target and background information. As a commonly used satellite attitude sensor, the infrared horizon is based on the detection of the radiation transition between the earth and space to obtain the attitude offset of the satellite (vertical line) relative to th...

AI Technical Summary

Problems solved by technology

[0006] 1) It is difficult to meet the general requirements of the orbital height: the lens opening angle of the infrared horizon determines the orbital height of the applicable satellite, and the research and development of the existing static linear array infrared horizon is generally for a certain orbital height range (such as 750kM to 900kM) or even a specific mission, the mission versatility of the horizon is poor

[0007] 2) It is difficult to meet the attitude measurement requirements: due to the limitation of the lens angle and quantity of the integrated installation, the existing static linear array infrared horizon can only determine the attitude when the spacecraft is pointing to the ground, and cannot adapt to the various attitudes of the spacecraft Measurement requirements under

[0008] 3) It is difficult to meet the structural design requirements of the spacecraft: the existing infrared horizon is installed in a fixed position (generally in the direction of the nadir), which is not conducive to the optimization of the overall structure design of the satellite

[0009] 4) Unable to flexibly change the redundant configuration: the lens redundancy setting of the infrared horizon varies according to the reliability requirements of the mission for the spacecraft, and different mission funding and reliability requirements determine its impact on the adapted infrared horizon. There are different requirements for the number of lenses. Due to the limitation of the lens angle and quantity of the integrated installation of the existing static line array infrared horizon, the lens redundancy configuration cannot be adjusted, and redundant and flexible configuration cannot be realized.

[0010] Therefore, it is necessary to provide a new static linear array infrared horizon, improve the general capability and configuration flexibility of the infrared horizon, meet the diverse needs of future space missions, and avoid the prolongation of project time caused by a large number of repeated development of the infrared horizon , waste of human resources, increased research and development costs, and increased mission risks

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