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Extra resources for Advances in Spacecraft Technologies
The parameters of the motion simulator are shown in Table 1. 9 ×108 Pa 20N/(m·s-1) Kce Total flow-pressure coefficient 9 ×10 −12 m3/(s·Pa) Table 1. Parameters for single DOF motion simulator The control structure of the motion simulator is shown in Figure 22. By tuning the controller Gprefilter , the performance of the motion simulator can be described as: when the frequency of the input signal is 10Hz, the amplitude error is not larger than 2dB and the phase error is no larger than 70 degrees.
3. The IKAROS mission is envisaged as a technology demonstrated towards a power sail spacecraft, using the large deployable structure to host thin-film solar cells to generate large volumes of power to drive a SEP system (Kawaguchi, 2010). In addition to the traditional view of solar sailing as a very large structure several organisations, including NASA and the Planetary Society, are developing CubeSat based solar sails. Indeed, NASA flew the first CubeSat solar sails on board the third SpaceX Falcon 1 launch on 2 August 2008 which failed approximately 2 minutes after launch.
Thesis. Harbin, China: Harbin Institute of Technology, Feb. 89-98 (in Chinese) Huang, Q. ; Jiang, H. ; Zhang, S. Y. & Han, J. W. (2005). Spacecraft docking simulation using HIL simulator with Stewart platform. Journal of Chinese Mechanical Engineering. 3, Mar. ; Guan, H. H. (1999). Study on dynamics of mechano-electronic springdamper system with differential connections. J. Tsinghua Univ. (Sci. 8, Aug. ; Uchiyama, M. (2001). Analytical and experimental evaluation of impact dynamics on a high-speed zero G motion simulator.