Abstract: A breakaway mitigation system is provided for addressing breakaway between a tractor and a trailer unit of a truck. The breakaway mitigation system can include a spool assembly, a sensor, and a controller. The spool assembly has a spool body configured to deploy a length of a tether coupled with the spool body and configured to couple with an energy source supply conduit and to retract the length of the tether. The energy source supply conduit is configured to convey a source of energy for use by a motor or by a fuel cell. The sensor is configured to detect the length of the tether that has been deployed. The controller is configured to receive an input corresponding to the detected length and to implement a countermeasure when the detected amount exceeds a threshold value. Mitigation can be provided by a coupler that decouples under a load over a threshold.

Abstract: Systems and methods are disclosed for an apparatus and method for practicing injection techniques through an injectable apparatus. The injectable apparatus may contain a camera that is configured to detect the intensity and color of light attenuated from a testing tool after it is injected into a simulated human or animal body parts. A training tool may be connected to a user display device to generate a display of the injection apparatus as well as the performance parameters of a trainee.

Abstract: A breakaway mitigation system is provided for addressing breakaway between a tractor and a trailer unit of a truck. The breakaway mitigation system can include a spool assembly, a sensor, and a controller. The spool assembly has a spool body configured to deploy a length of a tether coupled with the spool body and configured to couple with an energy source supply conduit and to retract the length of the tether. The energy source supply conduit is configured to convey a source of energy for use by a motor or by a fuel cell. The sensor is configured to detect the length of the tether that has been deployed. The controller is configured to receive an input corresponding to the detected length and to implement a countermeasure when the detected amount exceeds a threshold value. Mitigation can be provided by a coupler that decouples under a load over a threshold.

Abstract: A composite edge of an aircraft wing includes a composite wing box skin panel, attached to an outward wing spar in an attachment region, and a composite ramp, upon an outer surface of, and co-cured with, the composite wing box skin panel. The composite wing box skin panel has a proximal end and a distal end, with an overhanging edge, with substantially constant thickness and ply count in the attachment region. The composite ramp has a maximum ramp thickness at the distal end, the distal end being set back from the overhanging edge, defining a shoulder on the overhanging edge. A composite wing edge skin panel, having a thickness substantially equal to the maximum ramp thickness, is attached to the composite wing box skin panel at the shoulder and adjacent to the distal end of the ramp.

Abstract: A composite edge of an aircraft wing includes a composite wing box skin panel, attached to an outward wing spar in an attachment region, and a composite ramp, upon an outer surface of the composite wing box skin panel. The composite wing box skin panel has a proximal end and a distal end, with an overhanging edge, with substantially constant thickness and ply count in the attachment region, the overhanging edge being without any joggle. The composite ramp has a maximum ramp thickness at the distal end, the distal end being set back from the overhanging edge, defining a shoulder, having a relief radius, on the overhanging edge. A composite wing edge skin panel, having a thickness substantially equal to the maximum ramp thickness, is attached to the composite wing box skin panel at the shoulder and adjacent to the distal end of the ramp.

Abstract: A composite edge of an aircraft wing includes a composite wing box skin panel, attached to an outward wing spar in an attachment region, and a composite ramp, upon an outer surface of, and co-cured with, the composite wing box skin panel. The composite wing box skin panel has a proximal end and a distal end, with an overhanging edge, with substantially constant thickness and ply count in the attachment region. The composite ramp has a maximum ramp thickness at the distal end, the distal end being set back from the overhanging edge, defining a shoulder on the overhanging edge. A composite wing edge skin panel, having a thickness substantially equal to the maximum ramp thickness, is attached to the composite wing box skin panel at the shoulder and adjacent to the distal end of the ramp.

Abstract: A composite edge of an aircraft wing includes a composite wing box skin panel, attached to an outward wing spar in an attachment region, and a composite ramp, upon an outer surface of, and co-cured with, the composite wing box skin panel. The composite wing box skin panel has a proximal end and a distal end, with an overhanging edge, with substantially constant thickness and ply count in the attachment region. The composite ramp has a maximum ramp thickness at the distal end, is the distal end being set back from the overhanging edge, defining a shoulder on the overhanging edge. A composite wing edge skin panel, having a thickness substantially equal to the maximum ramp thickness, is attached to the composite wing box skin panel at the shoulder and adjacent to the distal end of the ramp.