Advances in Spacecraft Technologies by Jason Hall

By Jason Hall

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If the linear model of the docking mechanism is adopted by the simulated object system, and its parameters are shown in Table3, the dynamic characteristics of the HIL simulation system are described by curve a in the Bode diagram, shown in Figure 24. The dynamic characteristics of the simulated object system are described by curve b. The curve a and curve b superpose with each other at lower frequency. Symbol m1 Nomenclature Mass of chaser vehicle Value 8000kg m2 Mass of target vehicle 12000kg Table 2.

Li, Q. (2008). Fuzzy-immune PID control of a 6-DOF parallel platform for docking simulation. Journal of Zhejiang University (Engineering Science). ; Ye, Z. ; Cong, D. ; Han, J. W. & Li, H. R. (2007). Space docking hybrid simulation prototype experiment system. Chinese Journal of Mechanical Engineering. ; Yang, L. & Qu, G. J. (2004). Dynamics analysis and simulation of spacecraft docking mechanism. 2004, pp. 38-42 (in Chinese) 34 Advances in Spacecraft Technologies Zhang, C. F. (1999). Study on Six-Degree-of-Freedom simulation for docking.

SRP, to propel a spacecraft, potentially providing a continuous acceleration limited only by the lifetime of the sail materials in the space environment. The momentum carried by individual photons is extremely small; at best a solar sail will experience 9 N of force per square kilometre of sail located in Earth orbit (McInnes, 1999), thus to provide a suitably large momentum transfer the sail is required to have a large surface area while maintaining as low a mass as possible. Adding the impulse due to incident and reflected photons it is found that the idealised thrust vector is directed normal to the surface of the sail, hence by controlling the orientation of the sail relative to the Sun orbital angular momentum can be gained or reduced.

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