Force balance sensor and method therefor
AssigneeThe Boeing Company
InventorsMichael Thomas Fox, Eric Anton Howell, Jeffrey Michael Roach
Life of this patent
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Abstract
A force balance sensor including a mechanical strain amplification system including a sensor torsion member having a first end and a second end spaced from one another along a longitudinal axis of the sensor torsion member, at least one strain sensor coupled to the sensor torsion member between the first and second ends, a first torsional stiffening member coupled to the first end of the sensor torsion member, and a second torsional stiffening member coupled to the second end of the sensor torsion member, wherein the first torsional stiffening member and the second torsional stiffening member are coupled to a torque member.
Claims22
A force balance sensor comprising:
- a mechanical strain amplification system including
- a sensor torsion member having a first end and a second end spaced from one another along a longitudinal axis of the sensor torsion member;
- at least one strain sensor coupled to the sensor torsion member between the first and second ends;
- a first torsional stiffening member coupled to the first end of the sensor torsion member;
- and
- a second torsional stiffening member coupled to the second end of the sensor torsion member,
- wherein:
- the first torsional stiffening member and the second torsional stiffening member are coupled to a torque member so that both of the sensor torsion member and the torque member extend between and are couple to each the first torsional stiffening member and the second torsional stiffening member to effect torque transfer between the first torsional stiffening member and the second torsional stiffening member;
- and
- each of the first torsional stiffening member and the second torsional stiffening member are configured to transfer torque from the torque member to a respective end of the sensor torsion member.
An aircraft comprising:
- an airframe;
- a control surface having a control surface frame pivotally coupled to the airframe with a torque member;
- a first actuator is coupled to a first end of the torque member and is configured to pivot the control surface about a longitudinal axis of the torque member;
- a second actuator is coupled to a second end of the torque member and is configured to pivot the control surface about the longitudinal axis;
- a force balance sensor including
- a mechanical strain amplification system including
- a sensor torsion member having a first end and a second end spaced from one another along a longitudinal axis of the sensor torsion member,
- at least one strain sensor coupled to the sensor torsion member between the first and second ends,
- a first torsional stiffening member coupled to the first end of the sensor torsion member, and
- a second torsional stiffening member coupled to the second end of the sensor torsion member,
- wherein the first torsional stiffening member and the second torsional stiffening member are coupled to the torque member of the control surface.
Dependencies are inferred from the claim text.