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Its thickness and positioning are adjusted so as to tune the final design in terms of motorization torque, stability, stiffness. Therefore, the selected hinges have to meet certain constraints for the satellite to work since the movement of panels has to be controlled without any damage and should be brought to rest and locked when fully deployed. These constraints are also very important since if they fail, then the whole satellite becomes unusable. (Givois, 2001)
The hinges must have a maximum panel acceleration and deceleration of 200 deg/sec/sec and a maximum angular velocity of 400 deg/sec. Individual panels should not exceed a weight of 200 grams while the cost of each hinge should be approximately £400. Figure 1 below shows the relationship between angle versus time, velocity versus time, acceleration versus time and torque versus time for both hinges. (Donzier, 1997)
This comprise of two components i.e. a powered drive hinge and a multiple degree-of-freedom floating hinge. Powered deployment is a result of High Output Paraffin (HOP) linear motor that is acting through a redundant metal band. Deployment is initiated by provision of power to the actuator. One the panel is deployed in position, a bar latch gets into position hence locking the panel in a fully deployed position. (Starsys, p.51)
It comprises of two hinges i.e. a spring powered drive and a multiple degree-of-freedom floating hinge. This provides exceptional stiffness for vibration loads without need of for a high tolerance alignment. Deployment energy is provided by a double coil torsion spring on the drive hinge. (Starsys, p.53)
The hinge mechanism consist of a passive and powered constant torque hinge. The powered hinge is deigned to take axial and radial loads while the passive hinge has axial play to allow panel thermal displacements. This system provides a near constant torque for any deployment up to an angle of 180o. Each hinge consists of an axle,
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