# US 11,028,886 B2 · Indicator system for torque limiter > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,028,886 B2 - Document ID: US11028886B2 - Status: Granted - Kind: B2 - Application number: 16/059,272 - Filed: 2018-08-09 - Published: 2019-02-28 - Granted: 2021-06-08 - Earliest claimed: 2017-08-24 - Assignees: Goodrich Actuation Systems Limited - Applicants: Goodrich Actuation Systems Limited - Inventors: Jeremy Kracke - Web page: https://patentgrep.com/patent/US11028886B2 ## CPC - F16D 43/20: controlled by torque, e.g. overload-release clutches, slip-clutches with means by which torque varies the clutching pressure - F16D 43/2024: {the axially moving part being coaxial with the rotation, e.g. a gear with face teeth} - F16D 43/206: moving axially between engagement and disengagement - F16D 67/00: Combinations of couplings and brakes; Combinations of clutches and brakes (combinations of couplings and clutches F16D47/02; conjoint control of brake systems and driveline clutches in vehicles B60W10/02, B60W10/18) - F16D 11/14: with clutching members movable only axially (F16D11/02, F16D11/08 take precedence) - F16D 59/00: Self-acting brakes, e.g. coming into operation at a predetermined speed - F16D: COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES ## Abstract There is provided an indicator system for a torque limiter. The system comprises a first component extending around an axis (A) and comprising one or more radially extending cam surfaces, and a second component in combination with a third component. The third component is fixed against rotation relative to the second component, but is axially movable relative to the second component. The third component comprises one or more notches, each receiving one of the radially extending cam surfaces. Upon relative rotation between the first component and the combination of the second component and the third component, a surface of each of the notches is configured to ride up a corresponding cam surface of the first component, causing the third component to move axially away from the second component. ## Claims ### Claim 1 An indicator system for a torque limiter for an aircraft flight control surface actuator, the indicator system comprising: a first component extending around an axis (A) and comprising one or more radially extending cam surfaces; a second component in combination with a third component, wherein the third component is fixed against rotation relative to the second component, but is axially movable relative to the second component; and an indicator member configured to move upon axial movement of the third component away from the second component when an applied torque to one of the first component or the second component exceeds a predetermined or specified amount, wherein the third component comprises one or more notches, each receiving one of the radially extending cam surfaces, and upon relative rotation between the first component and the combination of the second component and the third component, a surface of each of the notches is configured to ride up a corresponding cam surface of the first component, such that the third component moves axially away from the first component, thereby causing the third component to move axially away from the second component, and wherein the indicator system further comprises a rotationally fixed housing, wherein the indicator member is a lever arm pivotably connected to the housing and configured to move out of a first cavity in the housing upon axial movement of the third component away from the first and second components, so as to provide a visual indication that the torque limiter has tripped upon inspection. ### Claim 2 (depends on 1) The indicator system as claimed in claim 1, wherein the second component comprises one or more axially extending slots and the third component comprises one or more radially extending protrusions each configured to slot into one of the axially extending slots, so as to prevent relative rotation between the second component and the third component whilst allowing axial movement between the second component and the third component. ### Claim 3 (depends on 1) The indicator system as claimed in claim 1, wherein the radially extending cam surfaces, and the corresponding notches are V-shaped. ### Claim 4 (depends on 1) The indicator system as claimed in claim 1, wherein the third component is in sliding engagement with the first component, such that the third component is able to slide axially along the first component. ### Claim 5 (depends on 4) The indicator system as claimed in claim 4, wherein the third component comprises an inner circumferential surface configured to slide onto an outer circumferential surface of the first component. ### Claim 6 (depends on 1) The indicator system as claimed in claim 1, wherein the combination of the second component and the third component is located concentrically around the first component. ### Claim 7 (depends on 1) The indicator system as claimed in claim 1, wherein one or more of the first component, the second component and the third component are in the form of a substantially annular body. ### Claim 8 (depends on 1) The indicator system as claimed in claim 1, wherein the first component comprises a plurality of axially extending splines configured to slot into corresponding splines located on a shaft of the torque limiter. ### Claim 9 (depends on 1) The indicator system as claimed in claim 1, wherein the first component comprises a first portion configured to support the third component in a sliding engagement in use, and a second portion comprising the radially extending cam surfaces, wherein the first portion is axially displaced from the second portion. ### Claim 10 A torque limiter for an aircraft flight control surface actuator, the torque limiter comprising: an indicator system comprising: a first component extending around an axis (A) and comprising one or more radially extending cam surfaces; a second component in combination with a third component, wherein the third component is fixed against rotation relative to the second component, but is axially movable relative to the second component; and an indicator member configured to move upon axial movement of the third component away from the second component when an applied torque to one of the first component or the second component exceeds a predetermined or specified amount, wherein the third component comprises one or more notches, each receiving one of the radially extending cam surfaces, and upon relative rotation between the first component and the combination of the second component and the third component, a surface of each of the notches is configured to ride up a corresponding cam surface of the first component, such that the third component moves axially away from the first component, thereby causing the third component to move axially away from the second component, and wherein the indicator member is a lever arm pivotably connected to a rotationally fixed housing portion of the torque limiter and configured to move out of a first cavity in the housing portion of the torque limiter upon axial movement of the third component away from the first and second components, so as to provide a visual indication that the torque limiter has tripped upon inspecting the torque limiter. ### Claim 11 (depends on 10) The torque limiter as claimed in claim 10, comprising: a first shaft operatively attached to the first component such that the first component rotates with the first shaft; a second shaft operatively attached to the second component such that the second component rotates with the second shaft; wherein upon the applied torque to one of the first shaft or the second shaft exceeding the predetermined or specified amount, the first component is configured to rotate relative to the second component and cause the third component to move axially away from the second component as aforesaid. ### Claim 12 (depends on 11) The torque limiter as claimed in claim 11, further comprising: a movable abutment movable with the third component and configured to displace a pin located in a second cavity of the housing portion of the torque limiter upon axial movement of the third component away from the second component, wherein the pin is configured to displace the indicator member out of the first cavity in the housing portion to provide the visual indication that the torque limiter has tripped. ### Claim 13 A method of indicating that a torque limiter for an aircraft flight control surface actuator has tripped, the method comprising: transferring torque between a first shaft and a second shaft; rotating a first component relative to a second component when an applied torque to one of the first shaft or the second shaft exceeds a predetermined or specified amount, the first component extending around an axis (A) and comprising one or more radially extending cam surfaces; axially moving a third component upon rotation of the first component relative to the second component, the third component being fixed against rotation relative to the second component; and moving an indicator member upon axial movement of the third component away from the second component; wherein the third component comprises one or more notches, each receiving one of the radially extending cam surfaces, and upon relative rotation between the first component and the combination of the second component and the third component, a surface of each of the notches is configured to ride up a corresponding cam surface of the first component, such that the third component moves axially away from the first component, thereby causing the third component to move axially away from the second component, and wherein the indicator member is a lever arm pivotably connected to a rotationally fixed housing portion of the torque limiter and configured to move out of a first cavity in the housing portion of the torque limiter upon axial movement of the third component away from the first and second components, so as to provide a visual indication that the torque limiter has tripped upon inspecting the torque limiter.