A method of operating an aircraft, comprising the steps of: providing an aircraft engine including a nozzle having a sandwich structure comprising a first skin separated from a second skin by a first hinge member and a second hinge member movably coupled to respective ones of the first and second skin (18, 20) and to one another, each one of the first and second hinge members (32, 42) is comprised of at least two bars forming a triangular subassembly; each bar having a proximal end (36, 46) and a distal end (38, 48); the proximal end (36, 46) of each one of the bars being coupled to a corresponding one of the first and second skins (18, 20) at a corresponding first and second skin joint (40, 50); and the distal end (38, 48) of each one of the bars being coupled to one another at a member joint; and the triangular subassemblies being coupled at the member joint to form a pyramidal assembly; the sandwich structure being configured to allow: movement of the first skin relative to the second skin in an in-plane direction defining a longitudinal direction of the sandwich structure; movement of the first and second hinge member (32, 42) in response to moving the first and second skin in the in-plane direction; and movement of the first skin relative to the second skin in an out-of-plane direction in response to relative movement of the first and second skin (18, 20) in the in-plane direction, and operating the aircraft engine in order to cause the first skin to move relative to the second skin in the in-plane direction as a result of differential heating of the first and second skins (18, 20) or as a result of differential coefficients of thermal expansion of the first skin relative to the second skin. providing an aircraft engine including a nozzle having a sandwich structure comprising a first skin separated from a second skin by a first hinge member and a second hinge member movably coupled to respective ones of the first and second skin (18, 20) and to one another, each one of the first and second hinge members (32, 42) is comprised of at least two bars forming a triangular subassembly; each bar having a proximal end (36, 46) and a distal end (38, 48); the proximal end (36, 46) of each one of the bars being coupled to a corresponding one of the first and second skins (18, 20) at a corresponding first and second skin joint (40, 50); and the distal end (38, 48) of each one of the bars being coupled to one another at a member joint; and the triangular subassemblies being coupled at the member joint to form a pyramidal assembly; the sandwich structure being configured to allow: movement of the first skin relative to the second skin in an in-plane direction defining a longitudinal direction of the sandwich structure; movement of the first and second hinge member (32, 42) in response to moving the first and second skin in the in-plane direction; and movement of the first skin relative to the second skin in an out-of-plane direction in response to relative movement of the first and second skin (18, 20) in the in-plane direction, and each one of the first and second hinge members (32, 42) is comprised of at least two bars forming a triangular subassembly; each bar having a proximal end (36, 46) and a distal end (38, 48); the proximal end (36, 46) of each one of the bars being coupled to a corresponding one of the first and second skins (18, 20) at a corresponding first and second skin joint (40, 50); and the distal end (38, 48) of each one of the bars being coupled to one another at a member joint; and the triangular subassemblies being coupled at the member joint to form a pyramidal assembly; the sandwich structure being configured to allow: movement of the first skin relative to the second skin in an in-plane direction defining a longitudinal direction of the sandwich structure; movement of the first and second hinge member (32, 42) in response to moving the first and second skin in the in-plane direction; and movement of the first skin relative to the second skin in an out-of-plane direction in response to relative movement of the first and second skin (18, 20) in the in-plane direction, and movement of the first skin relative to the second skin in an in-plane direction defining a longitudinal direction of the sandwich structure; movement of the first and second hinge member (32, 42) in response to moving the first and second skin in the in-plane direction; and movement of the first skin relative to the second skin in an out-of-plane direction in response to relative movement of the first and second skin (18, 20) in the in-plane direction, and operating the aircraft engine in order to cause the first skin to move relative to the second skin in the in-plane direction as a result of differential heating of the first and second skins (18, 20) or as a result of differential coefficients of thermal expansion of the first skin relative to the second skin.