Abstract: A balancing system and method for an engine of an aircraft includes a housing retaining a magnetorheological fluid including magnetic particles within a carrier fluid. Electromagnets are coupled to the housing. The electromagnets are associated with fan blades of the engine. A balancing control unit is in communication with the electromagnets and sensors of the fan blades.

Abstract: A balancing system and method for an engine of an aircraft includes a housing retaining a magnetorheological fluid including magnetic particles within a carrier fluid. Electromagnets are coupled to the housing. The electromagnets are associated with fan blades of the engine. A balancing control unit is in communication with the electromagnets and sensors of the fan blades.

Abstract: Various techniques provide a heat shield assembly and mounting thereof on an aircraft. In one example, a heat shield assembly may include flexible member. The heat shield assembly may further include a plurality of frame members disposed on the flexible member. The heat shield assembly may further include a plurality of mounting structures configured to directly mount the heat shield assembly to a strut of an airplane. Each of the plurality of mounting structures may be disposed on one of the plurality of frame members. Related methods are also provided.

Abstract: Example systems and methods to optimize and integrate of thermal and structural analyses are described herein. An example method includes performing a thermal analysis of a component using a first mesh representing the component to produce a thermal distribution across the component. The first mesh has first nodes based on a first element size. The example method includes using a first mapping file to assign temperature values to second nodes of a second mesh representing the component based on the thermal distribution. The second nodes are based on a second element size different than the first element size. The example method also includes performing a structural analysis of the component using the second mesh and the assigned temperature values to produce gauge sizes for the component and using a second mapping file to assign gauge values to the first nodes of the first mesh based on the gauge sizes.

Abstract: Various techniques provide a heat shield assembly and mounting thereof on an aircraft. In one example, a heat shield assembly may include flexible member. The heat shield assembly may further include a plurality of frame members disposed on the flexible member. The heat shield assembly may further include a plurality of mounting structures configured to directly mount the heat shield assembly to a strut of an airplane. Each of the plurality of mounting structures may be disposed on one of the plurality of frame members. Related methods are also provided.

Abstract: In one example, a strut for mounting a jet engine to a wing of an aircraft includes a plurality of engine mounts and a space frame truss supported from the wing and including front and aft portions, the front portion being coupled to and supporting the engine mounts, the aft portion extending upwardly and rearwardly from an aft end of the front portion. By removing the aft end of the strut from the core exhaust zone of the engine, substantial reductions in the weight and drag of the strut, and a corresponding increase in the specific fuel consumption of the associated aircraft may be achieved.

Abstract: Methods and apparatus for analyzing fatigue of a structure and optimizing a characteristic of the structure based on the fatigue analysis are disclosed herein. An example method disclosed herein includes obtaining mass and unit stress values of a plurality of details of interest of a structural component, calculating fatigue margins for each of the details of interest, identifying among the calculated fatigue margins any negative fatigue margins associated with one or more of the details of interest, and adjusting, via a processor, a dimensional characteristic of each detail of interest associated with the negative fatigue margin(s) until positive fatigue margin(s) at each detail of interest is obtained.

Abstract: In one example, a strut for mounting a jet engine to a wing of an aircraft includes a plurality of engine mounts and a space frame truss supported from the wing and including front and aft portions, the front portion being coupled to and supporting the engine mounts, the aft portion extending upwardly and rearwardly from an aft end of the front portion. By removing the aft end of the strut from the core exhaust zone of the engine, substantial reductions in the weight and drag of the strut, and a corresponding increase in the specific fuel consumption of the associated aircraft may be achieved.

Abstract: In one example embodiment, a strut for mounting a jet engine to a wing of an aircraft includes a plurality of engine mounts and a space frame truss supported from the wing and comprising front and aft portions, the front portion being coupled to and supporting the engine mounts, the aft portion extending upwardly and rearwardly from an aft end of the front portion. By removing the aft end of the strut from the core exhaust zone of the engine, substantial reductions in the weight and drag of the strut, and a corresponding increase in the specific fuel consumption of the associated aircraft may be achieved.

Abstract: In one example embodiment, a strut for mounting a jet engine to a wing of an aircraft includes a plurality of engine mounts and a space frame truss supported from the wing and comprising front and aft portions, the front portion being coupled to and supporting the engine mounts, the aft portion extending upwardly and rearwardly from an aft end of the front portion. By removing the aft end of the strut from the core exhaust zone of the engine, substantial reductions in the weight and drag of the strut, and a corresponding increase in the specific fuel consumption of the associated aircraft may be achieved.

Abstract: Example systems and methods to optimize and integrate of thermal and structural analyses are described herein. An example method includes performing a thermal analysis of a component using a first mesh representing the component to produce a thermal distribution across the component. The first mesh has first nodes based on a first element size. The example method includes using a first mapping file to assign temperature values to second nodes of a second mesh representing the component based on the thermal distribution. The second nodes are based on a second element size different than the first element size. The example method also includes performing a structural analysis of the component using the second mesh and the assigned temperature values to produce gauge sizes for the component and using a second mapping file to assign gauge values to the first nodes of the first mesh based on the gauge sizes.

Abstract: Methods and apparatus for analyzing fatigue of a structure and optimizing a characteristic of the structure based on the fatigue analysis are disclosed herein. An example method disclosed herein includes obtaining mass and unit stress values of a plurality of details of interest of a structural component, calculating fatigue margins for each of the details of interest, identifying among the calculated fatigue margins any negative fatigue margins associated with one or more of the details of interest, and adjusting, via a processor, a dimensional characteristic of each detail of interest associated with the negative fatigue margin(s) until positive fatigue margin(s) at each detail of interest is obtained.

Abstract: An apparatus, system, and method for the enclosed and automated lubricating of fasteners is disclosed. In one embodiment, the apparatus includes a sleeve having an inside diameter larger than a diameter of the fastener, wherein the sleeve has at least one conduit located therein for dispensing lubricant onto the fastener; and a lubricant supply line coupled to the sleeve for supplying lubricant into the inside diameter of the sleeve for lubricating the fastener. The sleeve also has a pilot for maintaining the sleeve in a centered location about the fastener, wherein the centering ring has a diameter larger than the diameter of the fastener and smaller than the inside diameter of the sleeve. An optional scraper, such as an o-ring, is coupled to the sleeve to remove excess lubricant from the fastener when the fastener is removed from the sleeve.

Abstract: The invention is a test apparatus incorporating high current test pins, forced into contact with a circuit assembly under test by opposing compliant pressure pins. An advantageous test pin for low voltage, high current testing is a solid, one piece test pin. The solid test pin, when supplied with adequate contact force, provides both low resistance and low inductance. The required compliant force is applied to the test circuit, opposite and substantially in line with the solid test pin, by a compliant pressure pin. Since the test pin does not supply the compliant force, it can be designed primarily for the desired electrical parameters of the test contact. The only mechanical considerations for the conductive solid pin are the amount of desired surface contact area, the dominant mechanical parameter in setting the contact resistance, and the body dimensions, which determine the resistance and inductance of the pin itself.

Abstract: The invention is a test apparatus incorporating high current test pins, forced into contact with a circuit assembly under test by opposing compliant pressure pins. An advantageous test pin for low voltage, high current testing is a solid, one piece test pin. The solid test pin, when supplied with adequate contact force, provides both low resistance and low inductance. The required compliant force is applied to the test circuit, opposite and substantially in line with the solid test pin, by a compliant pressure pin. Since the test pin does not supply the compliant force, it can be designed primarily for the desired electrical parameters of the test contact. The only mechanical considerations for the conductive solid pin are the amount of desired surface contact area, the dominant mechanical parameter in setting the contact resistance, and the body dimensions, which determine the resistance and inductance of the pin itself.

Abstract: For use with a power converter having a current sensor that senses an output current of the converter and generates a proportional voltage and a controller having an overvoltage protection circuit associated therewith. The overvoltage protection circuit includes a voltage sense input coupled to an output of the converter and a first reference voltage input, an integrated protection circuit, method of providing current-limiting and short-circuit protection and power converter employing the same. In one embodiment, the integrated protection circuit includes an operation amplifier circuit, coupled between the current sensor and the controller, that generates a voltage signal and causes the controller to limit a current supplied by the converter to the output when the proportional voltage exceeds a second reference voltage.