Abstract: The present disclosure relates to medicament injection devices. An injection device includes: a movable dosage programming component comprising a rotary encoder system having a predefined angular periodicity, a sensor arrangement including a first optical sensor configured to detect movement of the movable dosage programming component relative to the sensor arrangement during dosing of a medicament, wherein the first optical sensor is configured to operate in a strobe-sampling mode at a first frequency, a second optical sensor configured to detect movement of the rotary encoder system relative to the second optical sensor wherein the second optical sensor is configured to operate in a strobe-sampling mode at a second frequency lower than the first frequency, and a processor arrangement configured to, based on the detected movement, determine a medicament dosage administered by the injection device.

Abstract: Systems and methods for manufacturing aircraft are disclosed. For example, a method for repetitively manufacturing aircraft comprises fractionally pulsing a constituent part down an assembly line by periodically advancing the constituent part down the assembly line by less than a length of the constituent part. The periodic advancing may include advancing the aircraft component by a pulse length that is less than the length of the aircraft component, stopping movement of the aircraft component for a duration and performing work on the aircraft component, and then advancing the aircraft component by the pulse length again. In another example, a method comprises determining a fractional pulse length to fractionally pulse one or more constituent parts of an aircraft based on one or more of a minimum workstation length of one or more assembly line workstations and a minimum section length of one or more work processes to be performed.

Abstract: Systems and methods for manufacturing aircraft are disclosed. For example, an aircraft manufacturing system for repetitively manufacturing aircraft comprises a first manufacturing zone configured to repetitively manufacture first aircraft subassemblies, a second manufacturing zone configured to repetitively manufacture second aircraft subassemblies, and a third manufacturing zone configured to receive the first aircraft subassemblies from the first manufacturing zone, to receive the second aircraft subassemblies from the second manufacturing zone, and to repetitively assemble the first aircraft subassemblies and the second aircraft subassemblies into the aircraft.

Abstract: An aircraft manufacturing system for repetitively manufacturing aircraft comprises a first manufacturing zone configured to repetitively manufacture first aircraft subassemblies, a second manufacturing zone configured to repetitively manufacture second aircraft subassemblies, and a third manufacturing zone configured to receive the first aircraft subassemblies from the first manufacturing zone, to receive the second aircraft subassemblies from the second manufacturing zone, and to repetitively assemble the first aircraft subassemblies and the second aircraft subassemblies into the aircraft.

Abstract: Systems and methods for manufacturing aircraft are disclosed. For example, a method for repetitively manufacturing aircraft comprises fractionally pulsing a constituent part down an assembly line by periodically advancing the constituent part down the assembly line by less than a length of the constituent part. The periodic advancing may include advancing the aircraft component by a pulse length that is less than the length of the aircraft component, stopping movement of the aircraft component for a duration and performing work on the aircraft component, and then advancing the aircraft component by the pulse length again. In another example, a method comprises determining a fractional pulse length to fractionally pulse one or more constituent parts of an aircraft based on one or more of a minimum workstation length of one or more assembly line workstations and a minimum section length of one or more work processes to be performed.

Abstract: Systems and methods for manufacturing aircraft are disclosed. For example, an aircraft manufacturing system for repetitively manufacturing aircraft comprises a first manufacturing zone configured to repetitively manufacture first aircraft subassemblies, a second manufacturing zone configured to repetitively manufacture second aircraft subassemblies, and a third manufacturing zone configured to receive the first aircraft subassemblies from the first manufacturing zone, to receive the second aircraft subassemblies from the second manufacturing zone, and to repetitively assemble the first aircraft subassemblies and the second aircraft subassemblies into the aircraft.

Abstract: A method and apparatus for positioning one component relative to another component. First metrology data may be identified for a first component and second metrology data may be identified for a second component. First locations of first features may be identified on the first component using the first metrology data. Second locations of second features on the second component may be identified using the second metrology data. A transformation may be computed based on the first locations identified and the second locations identified for use in modifying a movement plan of a robotic system for positioning the second component relative to the first component.

Abstract: A method is provided of fabricating a composite stiffener having a curved web and at least one curved flange. A substantially straight length of unidirectional prepreg tape is placed on a carrier. The at least one curved flange is formed by using the carrier to steer a first portion of the tape onto a first curved tool surface. The curved web is formed by using the carrier to form a second portion of the tape onto a second curved tool surface.

Abstract: A method and apparatus for positioning one component relative to another component. First metrology data may be identified for a first component and second metrology data may be identified for a second component. First locations of first features may be identified on the first component using the first metrology data. Second locations of second features on the second component may be identified using the second metrology data. A transformation may be computed based on the first locations identified and the second locations identified for use in modifying a movement plan of a robotic system for positioning the second component relative to the first component.

Abstract: An actuator assembly including one or more actuator arms, wherein each of the actuator arms defines a clasp hole and a clamp-opening hole and a slot running between the clasp hole and clamp-opening hole, and optionally, a second slot running from the clasp hole to a distal end of the actuator arm, thereby creating two clasp fingers. A flex suspension assembly is included with a protrusion, such as a boss and a head on a distal end. The flex suspension assembly is coupled to the actuator arm by resiliently increasing the diameter of the clasp hole so as to allow the boss on the flex suspension assembly to be inserted into the clasp hole. With the boss is inserted, the clasp hole is allowed to revert to its original diameter, thereby clamping the boss in the clasp hole. A method for assembly is also provided.

Abstract: An actuator assembly including one or more actuator arms, wherein each of the actuator arms defines a clasp hole and a clamp-opening hole and a slot running between the clasp hole and clamp-opening hole, and optionally, a second slot running from the clasp hole to a distal end of the actuator arm, thereby creating two clasp fingers. A flex suspension assembly is included with a protrusion, such as a boss and a head on a distal end. The flex suspension assembly is coupled to the actuator arm by resiliently increasing the diameter of the clasp hole so as to allow the boss on the flex suspension assembly to be inserted into the clasp hole. With the boss is inserted, the clasp hole is allowed to revert to its original diameter, thereby clamping the boss in the clasp hole. A method for assembly is also provided.