Effects of Clearance on Deployment of Solar Panels on Spacecraft System
-
- ZHAO Yang
- Department of Astronautics Engineering, Harbin Institute of Technology
-
- BAI ZhengFeng
- Department of Astronautics Engineering, Harbin Institute of Technology
この論文をさがす
抄録
This paper establishes a dynamics model for deploying solar panels with clearances by using a practical method and provides a useful way to identify the effects of clearances on spacecraft systems. Considering the clearance of joints, a contact dynamic model is established using the nonlinear spring-damp model and the friction effect is considered by using the Coulomb friction model. Based on the model, numeric simulation of the deployment of a single panel with clearance on a spacecraft is presented. The effects of the clearance on attitude motion of the spacecraft as well as the deployment of a solar panel with joint clearance are analyzed. The simulation results predict the effects of clearance on the attitude motion of a spacecraft system and the deployment dynamics of solar panel preferably. It is useful for engineering design of a spacecraft control system and ground text. This work provides a valuable method for improving the dynamics of spacecraft systems.
収録刊行物
-
- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
-
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 53 (182), 291-295, 2011
一般社団法人 日本航空宇宙学会
- Tweet
詳細情報 詳細情報について
-
- CRID
- 1390001204079295872
-
- NII論文ID
- 10027844865
-
- NII書誌ID
- AA0086707X
-
- ISSN
- 21894205
- 05493811
-
- NDL書誌ID
- 10972271
-
- 本文言語コード
- en
-
- データソース種別
-
- JaLC
- NDL
- Crossref
- CiNii Articles
-
- 抄録ライセンスフラグ
- 使用不可