Abstract: A leg-protecting apparatus is arranged in close contact with a body surface of a wearer to cover a thigh, a knee, and a calf of the wearer, including a biomechanically protecting strap arranged to correspond with structural locations and paths of tendons and ligaments of the knee and muscles proximal thereto during an exercise process. The strap comprises a cruciate ligament protecting strap, a patellar tendon protecting strap, a thigh muscle group protecting strap, and a calf muscle group protecting strap. Elastic moduli of the cruciate ligament protecting strap and the patellar tendon protecting strap has a step-change upon a change in a fabric tensile ratio caused by the knee bending of the wearer, wherein the step-change occurs after an initial low tensile modulus stage, during a tensile sudden-change stage, and before a high tensile modulus stage transitioning between the stages as knee angle decreases.

Abstract: A dynamic elastic one-way water-guiding sportswear is formed from a basic cloth. The basic cloth is made from a porous material having capable of dynamically adsorbing and transferring liquid water, and the dynamic transferring and guiding capability for liquid water of the basic cloth is determined based on the stretching ratio of the covered skin. The sportswear comprises an elastic stretchable bands (1_1, 1_2) and a pressure fastening area (2), wherein the elastic stretchable bands (1_1, 1_2) and the pressure fastening area (2) have different mechanics transmission properties. The elastic stretchable bands (1_1, 1_2) are used to provide elastic protection for twisting and stretching driven by the shoulders and legs, and the pressure fastening area (2) is used to fasten and protect the soft tissues of the back and abdomen by providing a pressure thereupon.

Abstract: A leg-protecting apparatus is arranged in close contact with a body surface of a wearer to cover a thigh, a knee, and a calf of the wearer, including a biomechanically protecting strap (A) arranged to correspond with structural locations and paths of tendons and ligaments of the knee and muscles proximal thereto during an exercise process. The strap comprises a cruciate ligament protecting strap (A-1), a patellar tendon protecting strap (A-2), a thigh muscle group protecting strap (A-3), and a calf muscle group protecting strap (A-4). Elastic moduli of the cruciate ligament protecting strap (A-1) and the patellar tendon protecting strap (A-2) has a step-change upon a change in a fabric tensile ratio caused by the knee bending of the wearer, wherein the step-change occurs after an initial low tensile modulus stage, during a tensile sudden-change stage, and before a high tensile modulus stage transitioning between the stages as knee angle decreases.

Abstract: There is provided a method to account for aircraft angle of attack effects in engine noise shielding in aircraft configurations having one or more engines mounted above a wing or a lifting body. The method includes computing a local flow field from a known standard full aircraft configuration oriented at a nonzero angle of attack. The method further includes computing a mean flow field in a test dataset from a small scale aircraft model test configuration oriented at a zero angle of attack. The method further includes matching the local flow field with the mean flow field to identify a selected noise measurement dataset. The method further includes rotating the selected noise measurement dataset in a far field directivity rotation angle to match the nonzero angle of attack, thus resulting in engine noise shielding results for the full aircraft configuration at the nonzero angle of attack.

Abstract: There is provided a method to account for aircraft angle of attack effects in engine noise shielding in aircraft configurations having one or more engines mounted above a wing or a lifting body. The method includes computing a local flow field from a known standard full aircraft configuration oriented at a nonzero angle of attack. The method further includes computing a mean flow field in a test dataset from a small scale aircraft model test configuration oriented at a zero angle of attack. The method further includes matching the local flow field with the mean flow field to identify a selected noise measurement dataset. The method further includes rotating the selected noise measurement dataset in a far field directivity rotation angle to match the nonzero angle of attack, thus resulting in engine noise shielding results for the full aircraft configuration at the nonzero angle of attack.

Abstract: An apparatus and method is provided for attenuating aerospace engine noise and unsteady pressure fluctuations associated with high velocity exhaust flows. The apparatus and method reduce acoustic fatigue damage to aerospace vehicles that may be caused by the reflection of exhaust energy from landing and/or launch platforms. The apparatus includes a passive treatment area associated with the platform operable for reducing the magnitude of the reflected sound waves and unsteady pressure fluctuations from the high velocity exhaust mass flow exiting from the engine. The passive treatment area may include a layer of sound absorptive material, at least one set of roughness elements for disrupting high velocity flow structures. A protective cover may be positioned over the passive treatment area for permitting exhaust flow to pass therethrough while still providing adequate structure to support the weight of the aerospace vehicle.

Abstract: An engine including multiple pulse ducts. Each pulse duct has a hollow interior extending from an upstream end to a downstream end for transporting high-pressure fluid. The high-pressure fluid is expelled from the downstream ends of the pulse tubes during operation of the engine. The engine further includes an ejector adjacent the downstream ends of the plurality of pulse ducts comprising a plurality of segregated compartments. Each compartment is aligned with the downstream end of a corresponding pulse duct of the plurality of pulse ducts to receive the high-pressure fluid expelled from the downstream end of the corresponding pulse duct for preventing high-pressure fluid expelled from each pulse duct from interacting with fluid expelled from each adjacent pulse duct.

Abstract: An apparatus and method is provided for attenuating aerospace engine noise and unsteady pressure fluctuations associated with high velocity exhaust flows. The apparatus and method reduce acoustic fatigue damage to aerospace vehicles that may be caused by the reflection of exhaust energy from landing and/or launch platforms. The apparatus includes a passive treatment area associated with the platform operable for reducing the magnitude of the reflected sound waves and unsteady pressure fluctuations from the high velocity exhaust mass flow exiting from the engine. The passive treatment area may include a layer of sound absorptive material, at least one set of roughness elements for disrupting high velocity flow structures. A protective cover may be positioned over the passive treatment area for permitting exhaust flow to pass therethrough while still providing adequate structure to support the weight of the aerospace vehicle.