Relative Position Change in Spacecraft Formation by Two Impulses

スポンサーリンク

概要

• 論文の詳細を見る

• This paper proposes a basic method for formation flight based on Hill's equations of motion. It proposes a trajectory design of minimum fuel consumption for spacecraft relative position change by two impulses. Focusing on enlarging the formation size, we consider a problem to obtain the time and phase of the second impulse when the phase of the first impulse is given. First, the phase of the second impulse is obtained as a function of the time of the second impulse. Subsequently, the time of the second impulse is obtained to minimize the total fuel consumption. There are five cases to apply two impulses for minimum fuel consumption which depends on the phase of the first impulse. Numerical studies for enlarging the formation size by applying two impulses are carried out in order to verify the trajectory design.

• 一般社団法人 日本機械学会の論文

著者

• SHIMA Takeya

  Advanced Technology R&D Center, Mitsubishi Electric Corporation

• Yoshikawa Shoji

  Advanced Mechanical Systems Department Central Research Laboratory Mitsubishi Electric Corporation

• YAMADA Katsuhiko

  Graduate School of Engineering, Nagoya University

• JIKUYA Ichiro

  Graduate School of Engineering, Nagoya University

• SHIMA Takeya

  Advanced Technology R&D Center, Mitsubishi Electric Corporation

関連論文

• Boom Deployment Angle Estimation and On-orbit Operation Results of ETS-VIII Large Deployable Reflectors
• Arm path planning of a space robot with angular momentum
• MOTION CONTROL OF TUMBLING SPACECRAFT BY REPETITIVE IMPULSE INPUTS
• Relative Position Change in Spacecraft Formation by Two Impulses
• Relative Position Change of Spacecraft During Formation Flight by Two Impulses (Second Report: Decrease in Formation Size):(Second Report: Decrease in Formation Size)

スポンサーリンク