Rotatable assembly

Patent metadata

Field	Value
Publication number	US-10040580-B2
Application number	US-201414900992-A
Country	US
Kind code	B2
Filing date	Jun 27, 2014
Priority date	Jun 27, 2013
Publication date	Aug 7, 2018
Grant date	Aug 7, 2018

Abstract

The invention relates to a gear assembly (10) for use in a space craft for control of a moveable component thereof. The assembly comprises a load gear (11) in engagement with a drive gear (12) and an auxiliary gear (13). The drive gear (12) is coupled to a drive motor (14) so as to drive the load gear (11) in a first rotational direction. The auxiliary gear (13) is coupled to a retardation device (15) that is configured to passively resist the load gear (11) from rotating in the first rotational direction.

First claim

The invention claimed is:

1. A rotatable gear assembly for use in a space craft for control of a moveable component thereof, the assembly comprising:
a load gear in engagement with a drive gear and with an auxiliary gear,
wherein the drive gear is coupled to a drive motor so as to drive the load gear in a first rotational direction;
wherein the auxiliary gear is coupled to a retardation device that is configured to passively resist the load gear from rotating in the first rotational direction;
wherein the drive motor comprises a drive rotor that is incrementally rotatable between a plurality of discrete positions and the retardation device comprises a stepper motor that has a stepper rotor that is rotatable between a plurality of discrete detent positions, and wherein when the drive rotor is in a discrete position the stepper rotor is offset from its nearest detent position; and
wherein the rotatable gear assembly further comprises a controller to control operation of the drive motor and the stepper motor, the controller being configured to control the stepper motor to be in an unpowered state when the drive motor is powered to drive the load gear.

2. A rotatable assembly according to claim 1 , wherein the drive gear and the load gear respectively have teeth in meshing engagement, and the load gear and the auxiliary gear have teeth in meshing engagement, and wherein the rotatable assembly is configured such that when the drive motor is in a discrete position, the load gear is held stationary by the teeth of the drive gear and load gear in said meshing engagement abutting to exert a force on the load gear in one direction, and the teeth of the auxiliary gear and the load gear in said meshing engagement abutting to exert a force on the load gear in an opposite direction.

3. A rotatable assembly according to claim 1 , wherein the stepper motor is configured to generate a detent torque that urges the load gear in a second rotational direction opposite to the first rotational direction when the drive rotor is in a discrete position.

4. A rotatable assembly according to claim 3 , wherein when the drive rotor is in a discrete position the stepper rotor is offset from its nearest offset position by an offset angle in the second rotational direction.

5. A rotatable assembly according to claim 4 , wherein the offset angle is between o percent and 50 percent of the angle between adjacent discrete positions of the drive rotor.

6. A rotatable assembly according to claim 1 , wherein backlash is provided between the drive and load gears and comprises an angle by which the load gear can rotate without corresponding movement of the drive gear, and wherein an angle between adjacent discrete positions of the drive rotor is greater than the angle of the backlash.

7. A rotatable assembly according to claim 1 , wherein the stepper motor is configured to be in an unpowered state when the drive motor drives the load gear.

8. A rotatable assembly according to claim 1 , wherein the drive motor is a first stepper motor and the retardation device is a second stepper motor, wherein the assembly is configured such that the second stepper motor is unpowered and provides detent torque on the load gear in a second, opposite direction when the first stepper motor drives the load gear in the first direction, and wherein the second stepper motor can be powered to drive the load gear in the second direction whilst the first stepper motor is unpowered and provides detent torque on the load gear in the first direction.

9. A rotatable assembly according to claim 1 , comprising a second drive gear and a second auxiliary gear that each engage with the load gear, wherein the second drive gear is coupled to a second drive motor that is configured to rotate the drive gear in a second rotational direction opposite the first rotational direction and the second auxiliary gear is coupled to a second retardation device that is configured to passively resist the load gear from rotating in said opposing rotational direction.

10. A rotatable assembly according to claim 9 , wherein the second drive motor comprises a second drive rotor that is rotatable in the second rotational direction between a plurality of discrete positions and the second retardation device comprises a second stepper motor that has a second stepper rotor that is rotatable between a plurality of discrete detent positions, and wherein when the second drive rotor is in a discrete position the second stepper rotor is offset from its nearest detent position.

11. A rotatable assembly according to claim 10 , further comprising third and fourth auxiliary gears that are coupled to third and fourth stepper motors respectively that comprise third and fourth stepper rotors that are rotatable between a plurality of detent positions and wherein the third and fourth stepper rotors are offset from their respective detent positions when the first and second drive rotors are each in a discrete position.

12. A space craft structure comprising a moveable component coupled to, and controlled by a rotatable assembly according to claim 1 .

Assignees

• Airbus Defence & Space Ltd

Inventors

• Garland Martin
• Bamford Stephen
• White Carl

Classifications

• H02K7/116 Primary

  with gears · CPC title

• F16H57/12

  Arrangements for adjusting or for taking-up backlash not provided for elsewhere · CPC title

• B64G1/222 Primary

  for deploying structures between a stowed and deployed state · CPC title

• B64G1/24

  Guiding or controlling apparatus, e.g. for attitude control · CPC title

• B64G1/2229

  characterised by the deployment actuating mechanism (inflating B64G1/2227) · CPC title