Satellite orbit correction method

Abstract

The invention relates to a satellite orbit correction method. The method at least comprises the steps of determining first antenna adjustment control information based on orbital transfer environmentmonitoring information; determining the required estimated consumption of a satellite thruster for executing the specific event; determining orbital transfer demand mixing proportionality coefficientsrespectively corresponding to the satellite thruster and an inflatable antenna and a first control instruction and a second control instruction corresponding to the orbital transfer demand mixing proportionality coefficients based on the first antenna adjustment control information and the estimated consumption; enabling the inflatable antenna to receive the first control instruction in a mannerof performing aerodynamic force compensation on the satellite thruster receiving the second control instruction; and performing at least one adjustment and correction based on second aerodynamic forceinformation associated with an area involved in the ignition orbital transfer position obtained at a second moment to execute at least one related specific event.

Description

[0001] This case is a divisional case of the application number 201910042936.3, the application date is January 17, 2019, the application type is an invention patent, and the name is a volume-controllable inflatable antenna and its deployment volume control method. technical field [0002] The invention relates to the technical field of aerospace technology, in particular to a satellite orbit correction method. Background technique [0003] The orbit of low-orbit satellites can quickly reach the predetermined orbit and start work because of its relatively low operating altitude. In addition, low-orbit satellites have a relatively short orbital period, and the time interval for passing the same point is less, and they are more frequent in reconnaissance than traditional satellites, so they can obtain more information. But at the same time, because the orbital height of low-orbit satellites is lower than that of traditional satellites, the aerodynamic force on low-orbit satell...

AI Technical Summary

Problems solved by technology

[0008] Chinese patent (publication No. CN103928743B) discloses a loading and unfolding control mechanism of a rib-type air-inflatable unfolding parabolic antenna, which belongs to the technical field of rib-type air-inflating unfolding paraboloid antennas, and solves the problem that there is currently no effective The loading mechanism and the problem of being unable to effectively control its deployment process include a loading mechanism and a deployment control mechanism; the connecting parts of the loading mechanism are arranged below the fixed disk of the deployment control mechanism and are connected by bolts, and the loading mechanism The number of blades is the same as the number of support bars and rib pressing bars of the deployment control mechanism. The support bars are set corresponding to the gaps between the blades, and there are gaps on both sides of each blade.

However, in the orbit transfer optimization method provided by this patent, only a single power assist method using aerodynamic force is used, resulting in an extremely low utilization rate of aerodynamic force. the method of spacecraft control still suffers from low fuel savings and long transfer times

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