Abstract: A bale weighing kit includes a scale, an elongated support channel configured to couple with the scale and support a baler, and an anchor brace configured to couple with the support channel and laterally constrain movement of the support channel with respect to a ground support surface. The anchor brace includes an anchor plate with a surface configured to receive and support a portion of the scale.

Abstract: A front-loading refuse vehicle includes: a chassis; a cab coupled to a portion of the chassis, a hopper coupled to the chassis of the cab, and an arm assembly configured to move a refuse container from a location on one side of the refuse collection vehicle. The arm assembly includes a refuse container holder and a boom configured to move the refuse container holder relative to the chassis between an extended position and a retracted position. The boom includes a band including a bistable material reversibly configurable between a stowed configuration and a deployed configuration.

Abstract: A seat base includes a plurality of linear actuators each having a first end pivotally mounted to a base member and a second end pivotally mounted to a seat member. A controller is adapted for controlling an extension length of each of the plurality of linear actuators in a coordinated manner for adjusting a position of the seat member with six degrees-of-freedom and for damping vibration of the seat member. An active vibration mitigation method for reducing vibrations of an aircraft seat includes receiving vibration data from one or more accelerometers mounted to the aircraft seat and determining a vibration profile based on the vibration data. When vibration mitigation is warranted, control signals for damping vibration are determined and transmitted to a plurality of linear actuators adapted to support the aircraft seat.

Abstract: A seat base includes a plurality of linear actuators each having a first end pivotally mounted to a base member and a second end pivotally mounted to a seat member. A controller is adapted for controlling an extension length of each of the plurality of linear actuators in a coordinated manner for adjusting a position of the seat member with six degrees-of-freedom and for damping vibration of the seat member. An active vibration mitigation method for reducing vibrations of an aircraft seat includes receiving vibration data from one or more accelerometers mounted to the aircraft seat and determining a vibration profile based on the vibration data. When vibration mitigation is warranted, control signals for damping vibration are determined and transmitted to a plurality of linear actuators adapted to support the aircraft seat.

Abstract: A composite core with non-traditional geometries includes multiple elongate tubes arranged in a two-dimensional array. Each tube is made of a composite material. Each tube includes multiple curved sides. Each curved side inwardly curves toward a longitudinal axis passing through a geometric center of the tube to form a valley on an outer surface of the tube. An end of a first curved side connects to an end of a second curved side to form a crest on the outer surface of the tube. At least one crest formed on an outer surface of a first tube in the two-dimensional array contacts at least one valley formed on an outer surface of an adjacent second tube in the two-dimensional array.

Abstract: A seat base includes a plurality of linear actuators each having a first end pivotally mounted to a base member and a second end pivotally mounted to a seat member. A controller is adapted for controlling an extension length of each of the plurality of linear actuators in a coordinated manner for adjusting a position of the seat member with six degrees-of-freedom and for damping vibration of the seat member. An active vibration mitigation method for reducing vibrations of an aircraft seat includes receiving vibration data from one or more accelerometers mounted to the aircraft seat and determining a vibration profile based on the vibration data. When vibration mitigation is warranted, control signals for damping vibration are determined and transmitted to a plurality of linear actuators adapted to support the aircraft seat.

Abstract: In the present disclosure, a method may include forming a three-dimensional composite fiber pre-form by three-dimensionally weaving a plurality of composite fibers. The composite fiber pre-form includes a plurality of open cells formed adjacent to and interlocked with each other, and a composite fiber forms at least a portion of a first side of a first open cell and at least a portion of a second side of a second open cell. The first open cell and the second open cell are adjacent to and interlocked with each other.

Abstract: A composite core with non-traditional geometries includes multiple elongate tubes arranged in a two-dimensional array. Each tube is made of a composite material. Each tube includes multiple curved sides. Each curved side inwardly curves toward a longitudinal axis passing through a geometric center of the tube to form a valley on an outer surface of the tube. An end of a first curved side connects to an end of a second curved side to form a crest on the outer surface of the tube. At least one crest formed on an outer surface of a first tube in the two-dimensional array contacts at least one valley formed on an outer surface of an adjacent second tube in the two-dimensional array.

Abstract: A composite core with non-traditional geometries includes multiple elongate tubes arranged in a two-dimensional array. Each tube is made of a composite material. Each tube includes multiple curved sides. Each curved side inwardly curves toward a longitudinal axis passing through a geometric center of the tube to form a valley on an outer surface of the tube. An end of a first curved side connects to an end of a second curved side to form a crest on the outer surface of the tube. At least one crest formed on an outer surface of a first tube in the two-dimensional array contacts at least one valley formed on an outer surface of an adjacent second tube in the two-dimensional array.

Abstract: In the present disclosure, a method may include forming a three-dimensional composite fiber pre-form by three-dimensionally weaving a plurality of composite fibers. The composite fiber pre-form includes a plurality of open cells formed adjacent to and interlocked with each other, and a composite fiber forms at least a portion of a first side of a first open cell and at least a portion of a second side of a second open cell. The first open cell and the second open cell are adjacent to and interlocked with each other.

Abstract: A composite core with non-traditional geometries includes multiple elongate tubes arranged in a two-dimensional array. Each tube is made of a composite material. Each tube includes multiple curved sides. Each curved side inwardly curves toward a longitudinal axis passing through a geometric center of the tube to form a valley on an outer surface of the tube. An end of a first curved side connects to an end of a second curved side to form a crest on the outer surface of the tube. At least one crest formed on an outer surface of a first tube in the two-dimensional array contacts at least one valley formed on an outer surface of an adjacent second tube in the two-dimensional array.