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Given a cylindrically shaped space vehicle D 1m height is 07 m average density is 11 gcm3 with a flat solar cell panel on an arm mass of 32 kg effective moment arm is 15 m effective

Given a cylindrically shaped space vehicle (D = 1m, height is 0.7 m, average density is 1.1 g/cm3) with a flat solar cell panel on an arm (mass of 32 kg, effective moment arm is 1.5 m, effective average area facing normally toward sun is 0.6 m2) in a set of essentially frictionless bearings and in a low circular orbit at 160 km altitude with sunlight being received, on the average, about 54% of the time. The top surface of the cylinder and the surface of the solar have solar cells. The satellite is maneuvered so that these two surfaces are always perpendicular to the sun’s rays. The articulated arm between the cylinder and the solar panel is small and its mass and force, due to solar radiation pressure, are also small and can be neglected.

(a) Compute the maximum solar pressure-caused torque and the angular displacement this would cause during 1 day if not corrected.

(b) Using the data from the atmospheric table in Appendix 2 and an arbitrary average drag coefficient of 1.0 for both the body and the flat plate, compute the drag force and torque.

(c) Using stored high-pressure air at 14 × 106 N/m2 initial pressure as the propellant for attitude control, design an attitude control system to periodically correct for these two disturbances (F, Is, t,It , etc.).

 

Jul 23 2020 View more View Less

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