A surface texture includes a three-dimensional structure, a cross-section of which includes a first serration and a second serration. The first serration has a first peak having a height measured from a base of the three-dimensional structure to a top of the first serration. A valley is formed in between the first serration and the second serration, where the valley has a length measured from a base of the first serration to a base of the second serration. The first serration also has a vertex angle that forms the first peak. A coating that covers at least a portion of the valley, where the valley is designed to remain free of frost.

A surface texture includes a three-dimensional structure, a cross-section of which includes a first serration and a second serration. The first serration has a first peak having a height measured from a base of the three-dimensional structure to a top of the first serration. A valley is formed in between the first serration and the second serration, where the valley has a length measured from a base of the first serration to a base of the second serration. The first serration also has a vertex angle that forms the first peak. A coating that covers at least a portion of the valley, where the valley is designed to remain free of frost.

A method for stiffening a skin panel of a heat shield assembly comprises steps of forming a blank into a stiffener, which includes a base portion and a bead portion that protrudes from the base portion, and connects the base portion to the skin panel.

A method for stiffening a skin panel of a heat shield assembly comprises steps of forming a blank into a stiffener, which includes a base portion and a bead portion that protrudes from the base portion, and connects the base portion to the skin panel.

A thermal management system for transferring heat from a heat load includes a composite structural member that supports a heat load source and a heat transfer member in thermal contact with the composite structural member, and in thermal contact with a heat sink. The system further includes at least one thermally-conductive first fastener that is in thermal contact with the heat transfer member, couples the heat load source to the composite structural member, and conducts heat from the heat load source into the heat transfer member. The heat transfer member conducts heat from the thermally-conductive first fastener to the heat sink.

A thermal management system for transferring heat from a heat load includes a composite structural member that supports a heat load source and a heat transfer member in thermal contact with the composite structural member, and in thermal contact with a heat sink. The system further includes at least one thermally-conductive first fastener that is in thermal contact with the heat transfer member, couples the heat load source to the composite structural member, and conducts heat from the heat load source into the heat transfer member. The heat transfer member conducts heat from the thermally-conductive first fastener to the heat sink.

A rectification structure body 100 of a flying vehicle is provided with a rectification section 30, a heat input control section 20 and a vacuum thermal insulation section 10. The rectification section 30 has a rectification surface 30a and a back surface 30b. The rectification surface 30a rectifies airflow 5 from a travelling direction. The back surface 30b is arranged opposite to the rectification surface 30a. The heat input control section 20 is connected to the back surface 30b. The vacuum thermal insulation section 10 is connected to the heat input control section 20 and its surface is formed of rigid body. In addition, the heat input control section 20 is sandwiched between the back surface 30b and the vacuum thermal insulation section 10.

A rectification structure body 100 of a flying vehicle is provided with a rectification section 30, a heat input control section 20 and a vacuum thermal insulation section 10. The rectification section 30 has a rectification surface 30a and a back surface 30b. The rectification surface 30a rectifies airflow 5 from a travelling direction. The back surface 30b is arranged opposite to the rectification surface 30a. The heat input control section 20 is connected to the back surface 30b. The vacuum thermal insulation section 10 is connected to the heat input control section 20 and its surface is formed of rigid body. In addition, the heat input control section 20 is sandwiched between the back surface 30b and the vacuum thermal insulation section 10.

An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft includes a fuselage extending longitudinally between the forward end of the aircraft and the aft end of the aircraft; a primary wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; a first engine mounted to the primary wing assembly; and a first engine wing assembly extending outward from the first engine.

An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft includes a fuselage extending longitudinally between the forward end of the aircraft and the aft end of the aircraft; a primary wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; a first engine mounted to the primary wing assembly; and a first engine wing assembly extending outward from the first engine.