Orbit maneuvering method for ground exploration of on-orbit satellite

Abstract

The invention provides an orbit maneuvering method for ground exploration of an on-orbit satellite. The covering capability of a satellite load wave beam in the direction of a ground target is calculated through a satellite earth-fixed system ephemeris; the encountering time difference of the ground target and a satellite load ground projection is calculated according to the orbit maneuvering time and by comparing the longitude of the ground target and the longitude of the satellite passing the latitude circle same as that of the ground target; and the orbit period of the satellite for meeting the exploration requirement is calculated through the encountering time difference and the number of operation circles, and accordingly the adjustment amount required by the satellite orbit maneuvering semi-major axis is obtained, the minimum control amount in the satellite-control window period and the corresponding grounding target covering time are screened out, and the control amount is the orbit maneuvering control amount which can furthest save fuel under the restrained condition. Exploring of the ground target by orbit maneuvering in the specific time period is achieved in the short time in the mode of furthest saving the fuel.

Description

technical field [0001] The invention belongs to the field of on-orbit spacecraft measurement and control management, and relates to an orbit maneuver calculation method for realizing on-orbit satellite surveying of ground targets. Background technique [0002] Earth reconnaissance satellites are generally in a return orbit, and the designed return orbit allows the payload to conduct repeated surveys of fixed areas on the ground. Short-term surveys of ground targets can be carried out with a variety of payloads through a multi-satellite network. Due to the fact that the areas surveyed before the satellite network are different, the survey coverage gap of the new target will be too large in some periods after the network is established. In order to shorten the maximum revisit interval for new targets, it is necessary to complete orbital maneuvers for some satellites in the network in a short time, so that these satellites cover the survey targets within a specified time perio...

AI Technical Summary

Problems solved by technology

The existing technology is only for the fixed survey target of the standard design orbit of the satellite to perform orbital maneuvering for a long time with the perturbation force of the earth, and does not have the orbital maneuvering for other targets with special needs, and at the same time, it cannot complete the coverage of the new target within a specified period of time. Reconnaissance, the maximum reconnaissance coverage gap cannot be greatly shortened in a multi-satellite temporary network

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