Advances in Spacecraft Technologies by Jason Hall

By Jason Hall

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39. Bode diagram in X direction 0 dB -2 -4 -6 10 -1 10 0 10 1 10 2 Frequency, Hz Φ, deg 0 -100 -200 10 0 10 1 Frequency, Hz Fig. 40. Bode diagram in Y direction 10 2 Hardware-In-the Loop Simulation System Construction for Spacecraft On-orbit Docking Dynamics, Ideas, Procedural and Validation 29 If the dynamic characteristics of the HIL simulation system is not properly reconstructed with the time delay compensator, then if it is used to simulate the validation model (shown in Figure 37), the dynamic process of the HIL simulation system is divergent, shown in Figure 41 and Figure 42.

The “grab-and-go” architecture, identified as the most preferential for solar sailing required a mission duration of 5 – 6 years depending on the launch vehicle, while a similar all chemical propulsion mission could be completed in only 2 years, although requiring a slightly larger launch vehicle (McInnes et al, 2003a). A very similar scenario was found in the analysis of the Venus Sample Return mission (McInnes et al, 2003b). However, it was found that due to the increased launch mass sensitivity to returned mass the use of a solar sail for the Earth return stage offered potential real benefits; note the solar sail attached mass for this scenario was 323 kg requiring a sail of less than 100-m side length at an assembly loading of 6 gm-2, with 20 % design margin.

The Battelle laboratories recommendations were acted upon at NASA-JPL in an Advanced Mission Concepts Study for Office of Aeronautics and Space Technology (OAST) in FY1976 (Uphoff, 1975). During the continuation of the Battelle laboratories study Jerome Wright discovered a trajectory that would allow a relatively highperformance solar sail to rendezvous with comet Halley at its perihelion in the mid-1980’s by spiralling towards the Sun and then changing the orbit inclination by almost 180 deg (Wright & Warmke, 1976).

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