Abstract
The effects of hinge clearance on the deployment of solar panels were studied. The contact dynamics model was established using the nonlinear equivalent spring-damp model and the friction effect was considered by using the Coulomb friction model. Then the models were incorporated into ADAMS, and a large number of numeric simulations of deployment of a single panel on a satellite were made. The regularity of contact forces in clearance was studied in detail and the effects of clearance on attitude motion of the satellite and deployment of solar panels were analyzed. The simulation results can predict the effects of clearance on satellite attitude motion and deployment dynamics of solar panels preferably. It can be a reference for engineering design of satellite control system and ground test.
| Original language | English |
|---|---|
| Pages (from-to) | 11-14 |
| Number of pages | 4 |
| Journal | Harbin Gongye Daxue Xuebao/Journal of Harbin Institute of Technology |
| Volume | 41 |
| Issue number | 3 |
| State | Published - Mar 2009 |
Keywords
- Clearance
- Contact model
- Dynamics simulation
- Solar panel
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