The present invention relates to a method of controlling an angular momentum of a satellite, which is capable of controlling the angular momentum of the satellite without using a thruster or a magnetorquer. The method of controlling the angular momentum of a satellite that orbits around a planet includes: a first revolving step in which the satellite orbits the planet such that a first disturbance torque is generated; and a second revolving step in which the satellite orbits the planet such that a second disturbance torque is generated, wherein the angular momentum generated by the first disturbance torque is negated by the second disturbance torque. Accordingly, it is possible to provide a satellite, in which a reaction wheel in the satellite is controlled so as not to have a speed equal to or greater than a predetermined level, leading to a stable flight, and use of the magnetorquer or thruster is minimized, leading to long-term operation of the satellite.
본 발명은 인공위성의 각운동량 조절방법에 관한 것으로, 행성을 공전하는 인공위성의 자세제어를 통한 각운동량 조절방법에 있어서, 제1외란토크가 발생되도록 인공위성이 행성을 공전하는 제1공전단계 및 제2외란토크가 발생되도록 인공위성이 행성을 공전하는 제2공전단계를 포함하며, 상기 제1외란토크에서 발생된 각운동량을 제2외란토크가 상쇄시키도록 이루어져, 인공위성 내 반작용 휠이 일정 수준 이상의 속도가 되지 않도록 하여 보다 안정적인 비행이 이루어지며, 자장토커나 추력기의 사용을 최소화하여 장기간 운용가능한 인공위성을 제공할 수 있는 인공위성의 각운동량 조절방법이다.
Control method of angular momentum of a satellite
인공위성의 각운동량 조절방법
2018-07-12
Patent
Electronic Resource
Korean
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