Other

Korea Aerospace Research Institute

Shi Hwan Oh

Hye Jin Lee

Seon Ho Lee

Yong Bok Kim

Hong Youl Moon

Hyun Ho Seo

Ki Lyuk Yong

Hong Taek Choi

Jo Ryeong Yim

Provided is a deployment test apparatus including a fixing frame configured to fix a first portion of a target object in which the first portion is hingedly coupled to a second portion, a rotation axis module including a rotary shaft and disposed on one side of the fixing frame, a rotary arm radially extending from the rotary shaft in an upper portion of the fixing frame, and a support module connected to the rotary arm to clamp the second portion of the target object to be floated, wherein when deploying the target object, the deployment test apparatus is configured to reduce an external force applied to the target object.

Deployment test apparatus of a folded solar panel

Provided are an attitude control system and method of a spacecraft of an artificial satellite that may enhance a maneuverability and a controllability by simultaneously applying a reaction wheel and a thruster among drive units used to maneuver an attitude of the spacecraft of the artificial satellite. The attitude control system may include: a thruster-based attitude controller which control firing time of thrusters mounted on the spacecraft; and a reaction wheel-based attitude controller controlling driving of a reaction wheel mounted on the spacecraft. The spacecraft may include a plurality of reaction wheels. When a defect occurs in the spacecraft due to a partial malfunction of the reaction wheels, an attitude maneuverability of the spacecraft may be corrected by simultaneously applying the thruster-based attitude controller and the reaction wheel-based attitude controller.

Method for improving maneuverability and controllability by simultaneously applying both reaction wheel-based attitude controller and thruster-based attitude controller

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Daejeon, South Korea

Shi Hwan Oh