| | Patent 5067673: Essentially passive method for inverting the orientation of a dual spin spacecraft |
 | | Generally speaking, dual spin satellites are spacecrafts which are generally comprised of a gyroscopic spinning body, oftentimes referred to as a rotor, rotatably coupled by a despin motor and bearing assembly to a relatively stationary body, oftentimes referred to as a despun platform. |
 | | First of all, the useful life of the spacecraft can be significantly extended, since the amount of fuel required for these inversion maneuvers is typically 1/3 or so of the total fuel supply of a dual spin spacecraft fixed in a highly-inclined orbit. |
 | | Prior to actually initiating the spacecraft inversion maneuver, however, it is necessary to determine whether the satellite 10 is nutationally stable at that particular point in time, which is primarily dependent upon the amount of propellant remaining in the rotor-mounted fuel tanks (not shown) and the mass distribution of the satellite 10 at that time. |
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