Space-ground-based integrated measurement and control system applied in near-Earth space

Abstract

The invention discloses a ground-space-based integral measurement and control system applied to a terrestrial space. The system includes a ground measurement and control station; a relay satellite; anair vehicle including an upper antenna, a lower antenna, a radio frequency front end, a transceiving assembly and an air vehicle management computer, wherein the upper antenna and the lower antenna are used for receiving and transmitting of ground-base uplink and downlink signals and space-based forward and backward remote control signals; the radio frequency front end is used for performing filtering hybrid amplification on signals and outputting the signals; the transceiving assembly is used for conversion through modulation and demodulation and for receiving CCSDS remote measurement framesor acquiring positioning information according to remote measurement parameters of the transceiving assembly itself and calculating the optimal direction transmission of the space-based forward remote control signals; the air vehicle management computer is used for transmitting the received positioning information and the calculated optimal direction of the space-based forward remote control signals to the radio frequency front end for transmission switching between the upper antenna and the lower antenna and transmitting selected space-based backward remote control signals to the relay satellite. According to the invention, a ground-based and a space-based remote measurement and remote control links can be implemented at the same time and whole course coverage of flight tasks is realized.

Description

technical field [0001] The invention relates to a space-ground-based integrated measurement and control system applied in near-earth space, and belongs to the technical field of space-ground-based integrated measurement and control system. Background technique [0002] Influenced by factors such as the curvature of the earth, traditional low-Earth orbit vehicles can only achieve key link coverage in the process of the vehicle through multi-point deployment and ship measurement in order to complete the mission. Traditional aerospace vehicle measurement and control systems mostly use the mode of transponder plus receiver, and the system has a large volume and weight. Contents of the invention [0003] The problem to be solved by the invention is the problem that the existing system cannot satisfy the whole link coverage due to factors such as the curvature of the earth. [0004] The technical means to solve the problem is to provide a space-ground-based integrated measureme...

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Problems solved by technology

[0003] The problem to be solved by the invention is that the existing system cannot meet the problem of full link coverage due to factors such as the curvature of the earth

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