초록 ▼

An improved method for satellite station keeping is disclosed. The method provides for station keeping of a three axis stabilized satellite 10 using only two thrusters 20 and 22. The thrusters 20 and 22 can be ion or liquid propulsion thrusters and are mounted on the anti-nadir face 18 of the satell

An improved method for satellite station keeping is disclosed. The method provides for station keeping of a three axis stabilized satellite 10 using only two thrusters 20 and 22. The thrusters 20 and 22 can be ion or liquid propulsion thrusters and are mounted on the anti-nadir face 18 of the satellite 10. The north thruster 20 is canted at an angle Q16 of the satellite 10 in a northern direction and the south thruster 22 is canted at the angle Q16 in a southern direction. Both thrusters 20 and 22 are also translated to the east or west along an east-west axis 14 of the satellite 10 and swiveled at variable angles a1 and a2 respectively. A specific teaching of the invention discloses techniques for determining the angles a1 and a2 and the firing positions for the thrusters 20 and 22 to maintain the satellite 10 in a stationary orbit. In a specific embodiment, a backup thruster 24 is provided to counter the radial acceleration buildup from a failure of one of the thrusters 20 or 22. Also, in a specific embodiment, first and second slide mechanisms are provided to translate the first and second thrusters 20 and 22 to the east or west along the east-west axis 14 of the satellite 10 for a change in the angles a1 or a2 in order to maintain the lines of thrust from the thrust of the thrusters 20 and 22 respectively through the center-of-gravity of the satellite 10.

대표청구항 ▼

An improved method for station keeping of three-axis stabilized satellites comprising the steps of: a) mounting first and second thrusters on the anti-nadir face of a satellite; b) canting said first thruster at an angle Qa1 in a second direction from said face of said satellite with the line of for

An improved method for station keeping of three-axis stabilized satellites comprising the steps of: a) mounting first and second thrusters on the anti-nadir face of a satellite; b) canting said first thruster at an angle Qa1 in a second direction from said face of said satellite with the line of force from the thrust of said first thruster passing through the center-of-gravity of said satellite; c) canting said second thruster at an angle Qa2 in said second direction from said face of said satellite with the line of force from the thrust of said second thruster passing through the center-of-gravity of said satellite; d) providing first and second servo mechanisms to control the angles a1 and a2 respectively; e) providing first and second slide mechanisms to translate said first and second thrusters respectively along said face of said satellite in said second direction to maintain said lines of force from said thrusters through said center-of-gravity of said satellite for a change in said angles a1 or a2 respectively; and f) firing said first and second thrusters for the required length of time and with the appropriate angles for a1 and a2 to maintain the proper stationary orbit.