Abstract: One example of a mount for a rotorcraft comprises a structural support member, a bracket, and an elastomer. The bracket is configured to attach to a component of the rotorcraft. The component of the rotorcraft produces vibrations at a first frequency. The structural support member configured to transfer a weight of the component of a rotorcraft to an airframe of the rotorcraft. A rotor system of the aircraft vibrates the airframe of the rotorcraft at a second frequency. The elastomer is located between a structural support member and a bracket. The elastomer is configured to attenuate noise caused by the vibrations at the first frequency by isolating the vibrations at the first frequency from reaching the airframe of the rotorcraft while the airframe vibrates at the second frequency.

Abstract: One example of a mount for a rotorcraft comprises a structural support member, a bracket, and an elastomer. The bracket is configured to attach to a component of the rotorcraft. The component of the rotorcraft produces vibrations at a first frequency. The structural support member configured to transfer a weight of the component of a rotorcraft to an airframe of the rotorcraft. A rotor system of the aircraft vibrates the airframe of the rotorcraft at a second frequency. The elastomer is located between a structural support member and a bracket. The elastomer is configured to attenuate noise caused by the vibrations at the first frequency by isolating the vibrations at the first frequency from reaching the airframe of the rotorcraft while the airframe vibrates at the second frequency.

Abstract: A thermal management system and method includes: a drive shaft; one or more fans or impellers in fluid communication with at least a portion of the drive shaft; and one or more air management baffles configured to direct air flow between the impeller and the portion of the drive shaft. In one embodiment, the system and method further includes insulation positioned about the at least a portion of the drive shaft.

Abstract: One example of a mount for a rotorcraft comprises a structural support member, a bracket, and an elastomer. The bracket is configured to attach to a component of the rotorcraft. The component of the rotorcraft produces vibrations at a first frequency. The structural support member configured to transfer a weight of the component of a rotorcraft to an airframe of the rotorcraft. A rotor system of the aircraft vibrates the airframe of the rotorcraft at a second frequency. The elastomer is located between a structural support member and a bracket. The elastomer is configured to attenuate noise caused by the vibrations at the first frequency by isolating the vibrations at the first frequency from reaching the airframe of the rotorcraft while the airframe vibrates at the second frequency.

Abstract: One example of a duct support for a rotorcraft includes a stabilizing mechanism configured to transfer a weight of a duct to an airframe of the rotorcraft, where the duct undergoes thermal expansion. The stabilizing mechanism includes a first stabilizing member attached to the duct, a second stabilizing member attached to the rotorcraft, and a coupling mechanism where the coupling mechanism is configured to couple the first stabilizing member to the second stabilizing member and accommodate thermal expansion of the duct by allowing for movement of the first stabilizing member relative to the second stabilizing member. In an example, the duct is an exhaust duct of an engine of the rotorcraft and heat from the engine cause the exhaust duct to undergo the thermal expansion.

Abstract: One example of a fairing for a rotorcraft includes an outer mold line portion (OML portion) and a bearing portion extending from the OML portion. The OML portion provides at least a portion of an outer mold line of the rotorcraft. Both the OML portion and the bearing portion shield a portion of a structural member. The bearing portion can protect the portion of the structural member from damage resulting from foot traffic associated with accessing an area nearby the structural member.

Abstract: A method determines the performance index of subterranean rock. In one embodiment, a performance index method determines a performance index for subterranean rock of an area. The area includes a well. The method includes determining a time period during producing the well. The method also includes determining the performance index from data of the time period from the equation PI=(q/dd)*(cum./GPI). The term PI is the performance index, and the term q is the average daily rate of the well for the time period. The term dd is the average drawdown per day of the well for the time period, and the term cum. is the cumulative production of the well for the time period. The term GPI is the gross perforated interval of the well for the time period.

Abstract: One example of a duct support for a rotorcraft includes a stabilizing mechanism configured to transfer a weight of a duct to an airframe of the rotorcraft, where the duct undergoes thermal expansion. The stabilizing mechanism includes a first stabilizing member attached to the duct, a second stabilizing member attached to the rotorcraft, and a coupling mechanism where the coupling mechanism is configured to couple the first stabilizing member to the second stabilizing member and accommodate thermal expansion of the duct by allowing for movement of the first stabilizing member relative to the second stabilizing member. In an example, the duct is an exhaust duct of an engine of the rotorcraft and heat from the engine cause the exhaust duct to undergo the thermal expansion.

Abstract: One example of a mount for a rotorcraft comprises a structural support member, a bracket, and an elastomer. The bracket is configured to attach to a component of the rotorcraft. The component of the rotorcraft produces vibrations at a first frequency. The structural support member configured to transfer a weight of the component of a rotorcraft to an airframe of the rotorcraft. A rotor system of the aircraft vibrates the airframe of the rotorcraft at a second frequency. The elastomer is located between a structural support member and a bracket. The elastomer is configured to attenuate noise caused by the vibrations at the first frequency by isolating the vibrations at the first frequency from reaching the airframe of the rotorcraft while the airframe vibrates at the second frequency.

Abstract: One example of a fairing for a rotorcraft includes an outer mold line portion (OML portion) and a bearing portion extending from the OML portion. The OML portion provides at least a portion of an outer mold line of the rotorcraft. Both the OML portion and the bearing portion shield a portion of a structural member. The bearing portion can protect the portion of the structural member from damage resulting from foot traffic associated with accessing an area nearby the structural member.

Abstract: The present invention includes a thermal management system and method including: a drive shaft; one or more fans or impellers in fluid communication with at least a portion of the drive shaft; and one or more air management baffles configured to direct air flow between the impeller and the portion of the drive shaft. In one embodiment, the system and method further includes insulation positioned about the at least a portion of the drive shaft.

Abstract: A method determines the performance index of subterranean rock. In one embodiment, a performance index method determines a performance index for subterranean rock of an area. The area includes a well. The method includes determining a time period during producing the well. The method also includes determining the performance index from data of the time period from the equation PI=(q/dd)*(cum./GPI). The term PI is the performance index, and the term q is the average daily rate of the well for the time period. The term dd is the average drawdown per day of the well for the time period, and the term cum. is the cumulative production of the well for the time period. The term GPI is the gross perforated interval of the well for the time period.

Abstract: A method and system determines the performance index of subterranean rock. A performance index is determined for subterranean rock of an area. The area includes a well. A time period is determined during producing the well. The performance index is also determined from data of the time period from the equation PI=(q/dd)*(cum./GPI). The term PI is the performance index, and the term q is the average daily rate of the well for the time period. The term dd is the average drawdown per day of the well for the time period, and the term cum. is the cumulative production of the well for the time period. The term GPI is the gross perforated interval of the well for the time period.

Abstract: A method determines the performance index of subterranean rock. In one embodiment, a performance index method determines a performance index for subterranean rock of an area. The area includes a well. The method includes determining a time period during producing the well. The method also includes determining the performance index from data of the time period from the equation PI=(q/dd)*(cum./GPI). The term PI is the performance index, and the term q is the average daily rate of the well for the time period. The term dd is the average drawdown per day of the well for the time period, and the term cum. is the cumulative production of the well for the time period. The term GPI is the gross perforated interval of the well for the time period.