Pointing mechanism for use in an electric propulsion system of a spacecraft and electric propulsion system for use in a spacecraft
A pointing mechanism for use in an electric propulsion system of a spacecraft, the pointing mechanism comprises a mobile plate adapted to receive a thruster and defining a thrust vector of the thruster received on the mobile plate. The pointing mechanism further comprises a rotary actuator coupled to the mobile plate by means of a connecting element, the rotary actuator being configured to rotate the connecting element about a rotational axis of the rotary actuator such that the thrust vector defined by the mobile plate rotates about the rotational axis, wherein the thrust vector is inclined relative to the rotational axis.
1. A pointing mechanism for use in an electric propulsion system of a spacecraft, the pointing mechanism comprising:
a mobile plate adapted to receive a thruster and defining a thrust vector of the thruster received on the mobile plate, and
a rotary actuator coupled to the mobile plate by means of a connecting element, the rotary actuator being configured to rotate the connecting element about a rotational axis of the rotary actuator such that the thrust vector defined by the mobile plate rotates about the rotational axis, wherein the thrust vector is inclined relative to the rotational axis.
2. The pointing mechanism according to claim 1 , wherein the pointing mechanism further comprises:
a control unit configured to control the rotary actuator in order to, upon rotating the connecting element by means of the rotary actuator:
set the pointing mechanism into a first operating position, in which the thrust vector defined by the mobile plate does not pass through a center of gravity of the spacecraft, such that a first torque applied onto the spacecraft is generated, or
into a second operating position different from the first operating position, in which the thrust vector defined by the mobile plate does not pass through the center of gravity of the spacecraft, such that a second torque applied onto the spacecraft is generated,
wherein the first torque and the second torque are directed in opposite directions.
3. The pointing mechanism according to claim 2 , wherein the control unit is configured to operate the rotary actuator in response to at least one control parameter transmitted to the control unit from an attitude control system of the spacecraft configured to generate at least one compensation torque which is directed parallel to the first and second torque, the control parameter being indicative of a saturation state of the at least one compensation torque.
4. The pointing mechanism according to claim 3 , wherein the control unit is configured to, upon rotating the connecting element by means of the rotary actuator, set the pointing mechanism into its first operating position when the control parameter falls below a first threshold value and to set the pointing mechanism into its second operating position when the control parameter exceeds a second threshold value being greater than the first threshold value.
5. The pointing mechanism according to claim 1 , wherein a tilt angle between the thrust vector of the mobile plate and the rotational axis of the rotary actuator is maintained constant when the rotary actuator rotates the connecting element about the rotational axis.
6. The pointing mechanism according to claim 5 , wherein at least one of
the tilt angle between the thrust vector and the rotational axis is greater than an error angle of the thruster vector defined by the mobile plate, or
the tilt angle between the thrust vector and the rotational axis is between 0.5° and 5°.
7. The pointing mechanism according to claim 5 , wherein the tilt angle between the thrust vector and the rotational axis is 2°.
8. The pointing mechanism according to claim 1 , wherein at least one of:
the thrust vector of the mobile plate is perpendicular to the mobile plate, or
the mobile plate is coupled to the connecting element such that the mobile plate is inclined relative to the rotational axis at an inclined angle which is maintained constant when the rotary actuator rotates the connecting element about the rotational axis.
9. The pointing mechanism according to claim 1 , wherein the connecting element is a connecting shaft provided in the form of a cylindrical segment having a first front surface connected to the rotary actuator and a second front surface coupled to the mobile plate.
10. The pointing mechanism according to claim 9 , wherein the connection shaft is provided in the form of a hollow cylindrical segment.
11. The pointing mechanism according to claim 9 , wherein the first front surface is in the form of a circular surface.
12. The pointing mechanism according to claim 9 , wherein the second front surface is in the form of an elliptical surface.
13. The pointing mechanism according to claim 9 , wherein the second front surface of the connecting shaft is inclined relative to the rotational axis.
14. The pointing mechanism according to claim 9 , wherein the pointing mechanism further comprises a coupling means for coupling the connecting element to the mobile plate, the coupling means having a swashplate configured to translate a rotational motion of the connecting element in a reciprocating motion of the mobile plate.
15. The pointing mechanism according to claim 14 , wherein the coupling means is designed and configured such that a rotational degree of freedom around the thrust vector between the connecting element and the mobile plate is provided and wherein forces occurring in a direction along the thrust vector are transmitted between the connecting element and the mobile plate.
16. The pointing mechanism according to claim 15 , wherein the coupling means comprises a ball bearing arranged between the connecting element and the mobile plate such that a rotational degree of freedom around the thrust vector between the connecting element and the mobile plate is provided, and wherein forces occurring a direction along the thrust vector are transmitted between the connecting element and the mobile plate.
17. The pointing mechanism according to claim 16 , wherein the ball bearing is arranged between the second front surface and the mobile plate.
18. The pointing mechanism according to claim 15 , wherein the pointing mechanism further comprises an anti-rotating device which is configured to prevent the mobile plate form being rotated around the rotational axis relative to a spacecraft structure.
19. The pointing mechanism according to claim 18 , wherein the anti-rotating device is provided in the form of a movable bearing, via which the mobile plate is coupled to the spacecraft structure, the movable bearing being designed and configured such that a degree of freedom in a direction along the rotational axis is provided and wherein a torque occurring in a direction along the rotational axis is transmitted between the mobile plate and the spacecraft structure.
20. An electric propulsion system for use in a spacecraft equipped with a pointing mechanism according to claim 1 .