A communication satellite initially consists of a central bus (mass
PHYSICS · Multi-part · CBSE · Physics · System of Particles and Rotational Motion · System of Particles and Rotational Motion
Problem
A communication satellite initially consists of a central bus (mass 500kg, treated as a solid cuboid whose dimensions remain fixed) with two solar panels (each of mass 20kg) stowed flush against its sides. The satellite is spin-stabilized about an axis perpendicular to the panels.
After achieving its operational orbit, the panels deploy symmetrically, rotating 90∘ outward until they lie flat, extending like wings. Each panel is connected to the bus by a hinge that allows rotation but does not translate.
Mission planners must predict the satellite’s spin rate both before and after deployment and must evaluate what would happen if panel flexibility later became significant.
(a) During the stowed phase, justify whether the satellite can be treated as a single object or whether its internal structure must be considered a rigid system. Support your answer with reference to the planned calculation.
(b) During the deployment maneuver, explain why the satellite cannot be modeled as a single object. Identify which components must be tracked as separate rigid bodies and describe the nature of their motion.
(c) Suppose an analyst nevertheless treats the entire satellite as a single object throughout deployment. Predict qualitatively how this modeling choice will affect the calculated post-deployment spin rate, and explain the physical origin of any error.
(d) After several years, micrometeorite impacts cause the panels to flex noticeably during rotation. Discuss whether the rigid system model remains appropriate and describe one observable effect indicating that an even more detailed model is required.