Solenoid/magnetic hold brake with power off magnet hold function
A PDU for use in an aircraft includes a wheel configured to convey cargo through a portion of the aircraft. The PDU further includes an armature rotatably coupled to the wheel. The PDU further includes a brake pad. The PDU further includes a hold solenoid configured to compress the armature against the brake pad by a brake amount in order to apply a hold braking force to the wheel by resisting rotation of the armature. The PDU further includes a release solenoid configured to apply a force to separate the armature from the brake pad in order to allow the armature to rotate. The PDU further includes a magnet configured to compress the armature against the brake pad by a drag amount that is less than the brake amount in order to apply a drag braking force to the wheel by resisting rotation of the armature.
1. A power drive unit (PDU) having a magnetic hold brake for use in an aircraft, the PDU comprising:
a wheel configured to convey cargo through a portion of the aircraft;
an armature rotatably coupled to the wheel;
a brake pad;
a hold solenoid configured to compress the armature against the brake pad by a brake amount in order to apply a hold braking force to the wheel by resisting rotation of the armature;
a release solenoid configured to apply a force to separate the armature from the brake pad in order to allow the armature to rotate; and
a magnet configured to compress the armature against the brake pad by a drag amount that is less than the brake amount in order to apply a drag braking force to the wheel by resisting rotation of the armature.
2. The PDU of claim 1 , wherein:
the hold solenoid is configured to compress the armature against the brake pad in response to receiving a first electrical signal;
the release solenoid is configured to apply the force to separate the armature from the brake pad in response to receiving a second electrical signal; and
the magnet is configured to compress the armature against the brake pad regardless of whether any element of the PDU is receiving power.
3. The PDU of claim 1 , wherein the hold braking force is greater than the drag braking force.
4. The PDU of claim 1 , further comprising:
a motor configured to generate torque; and
a motor shaft coupled to the motor and the armature and configured to transfer the torque from the motor to the armature.
5. The PDU of claim 4 , wherein the hold braking force is sufficient to resist rotation of the wheel regardless of whether the torque is transferred from the motor to the armature.
6. The PDU of claim 1 , wherein the hold solenoid further includes a hold solenoid coil and a hold solenoid housing, and the hold solenoid coil and the magnet are located in the hold solenoid housing.
7. The PDU of claim 6 , wherein the hold solenoid is positioned about an axis of rotation, and the magnet is located radially inward from the hold solenoid coil.
8. The PDU of claim 1 , wherein the brake pad and the armature are sandwiched between the hold solenoid and the release solenoid.
9. The PDU of claim 1 , wherein:
the hold solenoid is configured to compress the armature against the brake pad by applying a first magnetic flux to the armature to compress the brake pad between the armature and the hold solenoid; and
the release solenoid is configured to apply the force to separate the armature from the brake pad by applying a second magnetic flux to the armature to urge the armature away from the brake pad.
10. A power drive unit (PDU) having a magnetic hold brake for use in an aircraft, the PDU comprising:
a wheel configured to convey cargo through a portion of the aircraft;
an armature rotatably coupled to the wheel;
a brake pad;
a hold solenoid configured to compress the armature against the brake pad in order to apply a hold braking force to the wheel by resisting rotation of the armature;
a release solenoid configured to apply a force to separate the armature from the brake pad in order to allow the armature to rotate; and
a magnet configured to compress the armature against the brake pad in order to apply a drag braking force to the wheel by resisting rotation of the armature, the hold braking force being greater than the drag braking force.
11. The PDU of claim 10 , wherein:
the hold solenoid is configured to compress the armature against the brake pad in response to receiving a first electrical signal;
the release solenoid is configured to apply the force to separate the armature from the brake pad in response to receiving a second electrical signal; and
the magnet is configured to compress the armature against the brake pad regardless of whether any element of the PDU is receiving power.
12. The PDU of claim 10 , further comprising:
a motor configured to generate torque; and
a motor shaft coupled to the motor and the armature and configured to transfer the torque from the motor to the armature.
13. The PDU of claim 12 , wherein the hold braking force is sufficient to resist rotation of the wheel regardless of whether the torque is transferred from the motor to the armature.
14. The PDU of claim 10 , wherein the hold solenoid further includes a hold solenoid coil and a hold solenoid housing, and the hold solenoid coil and the magnet are located in the hold solenoid housing.
15. The PDU of claim 14 , wherein the hold solenoid is positioned about an axis of rotation, and the magnet is located radially inward from the hold solenoid coil.
16. The PDU of claim 10 , wherein the brake pad and the armature are sandwiched between the hold solenoid and the release solenoid.
17. The PDU of claim 10 , wherein:
the hold solenoid is configured to compress the armature against the brake pad by applying a first magnetic flux to the armature to compress the brake pad between the armature and the hold solenoid; and
the release solenoid is configured to apply the force to separate the armature from the brake pad by applying a second magnetic flux to the armature to urge the armature away from the brake pad.
18. A power drive unit (PDU) having a magnetic hold brake for use in an aircraft, the PDU comprising:
a wheel configured to convey cargo through a portion of the aircraft;
an armature rotatably coupled to the wheel;
a motor configured to generate torque;
a motor shaft coupled to the motor and the armature and configured to transfer the torque from the motor to the armature;
a brake pad;
a hold solenoid having a hold solenoid housing and a hold solenoid coil located in the hold solenoid housing and configured to compress the armature against the brake pad by a brake amount in order to apply a hold braking force to the wheel by resisting rotation of the armature;
a release solenoid configured to apply a force to separate the armature from the brake pad in order to allow the armature to rotate; and
a magnet located in the hold solenoid housing and configured to compress the armature against the brake pad by a drag amount that is less than the brake amount in order to apply a drag braking force to the wheel by resisting rotation of the armature.
19. The PDU of claim 18 , wherein:
the hold solenoid is configured to compress the armature against the brake pad in response to receiving a first electrical signal;
the release solenoid is configured to apply the force to separate the armature from the brake pad in response to receiving a second electrical signal; and
the magnet is configured to compress the armature against the brake pad regardless of whether any element of the PDU is receiving power.
20. The PDU of claim 18 , wherein the hold solenoid is positioned about an axis of rotation, and the magnet is located radially inward from the hold solenoid coil.