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In today's world satellites have an immense and profound role in a country's financial, social and military development
and having the technology of creation and launching satellites is a yard stick to a country's progress. Each satellite, like
any other advanced machine is consisted of many subsystems in order to do its mission, among those, the attitude
Control subsystem has the duty of stabilizing and orientation. Depending on the type of stabilization and control laws,
different actuators like momentum wheels, reaction wheels, magnetic torquers and etcetera are used. Due to its smaller
shape and weight, lower cost and minimal power consumption, the magnetic torquer is frequently used in low-earth orbit
satellites. A magnetic torquer is consisted of a winding wire and a magnetic core that with the current of electricity
passing through the winding wire, a magnetic dipole moment is produced. In reaction to the earth's magnetic field, this
moment produces the required torque. Thus, having a broader understanding of the specification of the magnetic torquer
before using it in the satellite is quite necessary. As a result, in this paper we try to show how to make such system in the
laboratory. A magnetorquer is manufactured that the main idea is to estimate the magnetic dipole moment from the
magnetic field measurement by this magnetic torquer. To achieve this, first we talk about the theories of creating such
device and test system, then we will delve into the more technical aspects of designing such subsystem. In the end, from
the output results, the performance curve of the magnetic torquer is produced and the linear areas and scale coefficients
are determined.
This paper presents test methodology, experimental setup and test results of manufacturing a torque rod with CK30
ferromagnetic alloy core.
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