Abstract: A method of automated timing of engine startup for an aircraft is provided. The method comprises receiving data inputs regarding a number of factors influencing a time to departure for the aircraft and receiving data inputs regarding a number of factors influencing time to start and set takeoff power for a number of engines on the aircraft. An engine startup countdown is calculated based on a comparison of a nominal time to departure with a nominal minimum time to start and set takeoff power for the engines, wherein the nominal time to departure is based on the first data inputs and the nominal minimum time to start and set takeoff power is based on the second data inputs. Upon completion of the countdown an engine start signal is sent.

Abstract: Sound-attenuating heat exchangers and methods of utilizing the same are disclosed herein. The sound-attenuating heat exchangers include an aerodynamically shaped layer, a base, an intermediate layer, and a cooled fluid containment body. The aerodynamically shaped layer defines an aerodynamically shaped surface, an opposed intermediate layer-facing surface, and a plurality of apertures. The intermediate layer defines a shaped layer-facing surface and an opposed base-facing surface. The base defines a base surface. The intermediate layer-facing surface at least partially defines a sound-attenuating volume. The base surface at least partially defines an elongate cooling conduit. The sound-attenuating volume is distinct from the elongate cooling conduit and the intermediate layer at least partially fluidly isolates the sound-attenuating volume from the elongate cooling conduit. The cooled fluid containment body at least partially defines a cooled fluid containment conduit.

Abstract: A method of automated timing of engine startup for an aircraft is provided. The method comprises receiving data inputs regarding a number of factors influencing a time to departure for the aircraft and receiving data inputs regarding a number of factors influencing time to start and set takeoff power for a number of engines on the aircraft. An engine startup countdown is calculated based on a comparison of a nominal time to departure with a nominal minimum time to start and set takeoff power for the engines, wherein the nominal time to departure is based on the first data inputs and the nominal minimum time to start and set takeoff power is based on the second data inputs. Upon completion of the countdown an engine start signal is sent.

Abstract: Dendritic heat exchangers and methods of utilizing the same are disclosed herein. The dendritic heat exchangers include an elongate housing extending between a first end and a second end. The elongate housing defines a housing volume, a first fluid inlet, a first fluid outlet, a second fluid inlet, and a second fluid outlet. The dendritic heat exchangers also include a heat exchange structure extending within the housing volume. The heat exchange structure is configured to receive a second fluid inlet stream from the second fluid inlet and to provide a second fluid outlet stream to the second fluid outlet. The heat exchange structure includes a plurality of dendritic tubulars. Each dendritic tubular includes an inlet region, which defines an inlet conduit, and a branching region. The branching region defines a plurality of branch conduits that extends from the inlet conduit. The methods include methods of utilizing the dendritic heat exchangers.

Abstract: Sound-attenuating heat exchangers and methods of utilizing the same are disclosed herein. The sound-attenuating heat exchangers include an aerodynamically shaped layer, a base, an intermediate layer, and a cooled fluid containment body. The aerodynamically shaped layer defines an aerodynamically shaped surface, an opposed intermediate layer-facing surface, and a plurality of apertures. The intermediate layer defines a shaped layer-facing surface and an opposed base-facing surface. The base defines a base surface. The intermediate layer-facing surface at least partially defines a sound-attenuating volume. The base surface at least partially defines an elongate cooling conduit. The sound-attenuating volume is distinct from the elongate cooling conduit and the intermediate layer at least partially fluidly isolates the sound-attenuating volume from the elongate cooling conduit. The cooled fluid containment body at least partially defines a cooled fluid containment conduit.

Abstract: Dendritic heat exchangers and methods of utilizing the same are disclosed herein. The dendritic heat exchangers include an elongate housing extending between a first end and a second end. The elongate housing defines a housing volume, a first fluid inlet, a first fluid outlet, a second fluid inlet, and a second fluid outlet. The dendritic heat exchangers also include a heat exchange structure extending within the housing volume. The heat exchange structure is configured to receive a second fluid inlet stream from the second fluid inlet and to provide a second fluid outlet stream to the second fluid outlet. The heat exchange structure includes a plurality of dendritic tubulars. Each dendritic tubular includes an inlet region, which defines an inlet conduit, and a branching region. The branching region defines a plurality of branch conduits that extends from the inlet conduit. The methods include methods of utilizing the dendritic heat exchangers.

Abstract: An apparatus installed on an aircraft, comprising: a sleeve or duct having a trailing lip area; a plurality of petals arranged side by side with gaps therebetween, one end of each petal being attached or pivotably coupled to the lip area; and a plurality of elastomeric seals configured and disposed to close the gaps between adjacent petals. Each elastomeric seal comprises a first portion that moves with a portion of a first petal that is in contact therewith, a second portion that moves with a portion of a second petal that is in contact there, and a third portion which is stretched as the first and second petals move further apart from each other. Petal deflection is actuated by a system comprising a flexible member, a motor, a shaft driven by the motor, and an arm projecting from the shaft. One end of the flexible member is attached to the arm, the flexible member being movable to deflect the petals inward in response to a shaft rotation.

Abstract: An apparatus installed on an aircraft, comprising: a sleeve or duct having a trailing lip area; a plurality of petals arranged side by side with gaps therebetween, one end of each petal being attached or pivotably coupled to the lip area; and a plurality of elastomeric seals configured and disposed to close the gaps between adjacent petals. Each elastomeric seal comprises a first portion that moves with a portion of a first petal that is in contact therewith, a second portion that moves with a portion of a second petal that is in contact there, and a third portion which is stretched as the first and second petals move further apart from each other. Petal deflection is actuated by a system comprising a flexible member, a motor, a shaft driven by the motor, and an arm projecting from the shaft. One end of the flexible member is attached to the arm, the flexible member being movable to deflect the petals inward in response to a shaft rotation.