High-orbit SAR satellite task orbit design method for remote sensing task

Abstract

The invention discloses a high-orbit SAR satellite task orbit design method for a remote sensing task. The high-orbit SAR satellite task orbit design method comprises the following steps: (1) acquiring a maximum propellant carrying capacity constraint of an SAR satellite; (2) determining the maximum visual range capability of the SAR satellite load; (3) determining the value range of each orbit parameter of the high-orbit SAR satellite; (4) traversing each orbit parameter of the high-orbit SAR satellites according to the respective preset interval step length to obtain N orbits, and calculating the actual coverage area of the satellite load of each orbit and the revisit time of the remote sensing observation target; and (5) carrying out propellant analysis in the whole life cycle on the orbits meeting the requirements of the high-orbit remote sensing task coverage area and the remote sensing observation target revisit time, and extracting the orbits meeting the maximum propellant carrying capacity constraint of the SAR satellite as the final high-orbit SAR satellite task orbits. According to the method, the high-orbit SAR satellite can conform to the imaging characteristics of the SAR load, can meet the requirement of a remote sensing task, and can meet engineering constraints.

Description

technical field [0001] The invention belongs to the field of satellite orbit design, and relates to a high-orbit SAR satellite task orbit design method based on remote sensing task requirements. Background technique [0002] At present, my country's first high-orbit SAR payload remote sensing satellite is already under engineering development. At present, remote sensing satellites mainly use low-orbit satellites, and high-orbit satellites that use geosynchronous orbits are mostly used in the fields of communication and navigation, and the design parameters are mainly on-orbit longitude and orbit inclination, and relatively few orbit parameters need to be designed. High-orbit satellites can realize large-scale real-time observation of a specific area of ​​the earth. Compared with low-orbit satellites, satellites have the advantages of large imaging area and short revisit time. Due to the particularity of the visible range of SAR payloads and the orbital characteristics of hi...

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Problems solved by technology

[0004] The technical problem solved by the present invention is: there is no mature orbit scheme design method for high-orbit SAR satellites at present, and the orbit scheme design methods for conventional geostationary orbit communication satellites, high-orbit optical remote sensing satellites and high-orbit navigation satellites cannot be applied to high-orbit SAR satellites. The orbit design of orbiting SAR satellites is based on the requirements of remote sensing tasks, fully considering the top-level requirements such as observation area and revisit time in remote sensing tasks, the imaging characteristics of SAR payloads that need to form relative motion with the ground, and the impact caused by the limitation of the maximum launch capacity of the launch vehicle. The engineering constraints of satellite propellant carrying capacity provide a high-orbit SAR satellite mission orbit design method for remote sensing tasks, so that high-orbit SAR satellites can not only meet the imaging characteristics of SAR payloads but also meet the needs of remote sensing tasks, and can meet engineering constraints

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