A Common Bus Structure for Avionics and Satellites (CBSAS) (10) as shown in FIG. 1 is comprised of a module lid (14), module floor (38), module stack base (16), module compression bolts (22) and stackable modules (12). Stackable modules (12) are sub-dividable to create module scaled chamber volumes (45) individually as required, while stackable modules (12) simultaneously create at least one collectively continuous raceway sealed chamber volume (44) perpendicular to individual stackable modules (12) in the vertical direction where no module floor (38) is present, in order to internally electrically interconnect the contents of any stackable module (12) with the contents of any other stackable module (12) via internal connector raceway system (24). Raceway sealed chamber volume (44) therefore collectively and continuously traverses all present stackable modules (12) positioned between module lid (14) and module stack base (16). Modules are interchangeable and inter-connectable in any order, and contain all required electronic or mechanical components required for CBSAS (10) to function as a single box consolidated avionics system that is equally functional in the atmosphere or the vacuum of space, while also being fully functional as a single complete stand-alone satellite system. CBSAS (10) enables a paradigm shift in the aerospace industry whereby all legacy and current multiple black-box systems on aerospace platforms such as missiles, rockets, satellites and aircraft are extremely inefficient when compared to the size, weight and power attributes of CBSAS (10). The ability for CBSAS (10) to be instantly employable as either a single box consolidated avionics system for use within the atmosphere or in space while also being fully functional as a stand-alone satellite enables a hardware, firmware and software capability never before manifested in the aerospace industry.

A Common Bus Structure for Avionics and Satellites (CBSAS) (10) as shown in FIG. 1 is comprised of a module lid (14), module floor (38), module stack base (16), module compression bolts (22) and stackable modules (12). Stackable modules (12) are sub-dividable to create module scaled chamber volumes (45) individually as required, while stackable modules (12) simultaneously create at least one collectively continuous raceway sealed chamber volume (44) perpendicular to individual stackable modules (12) in the vertical direction where no module floor (38) is present, in order to internally electrically interconnect the contents of any stackable module (12) with the contents of any other stackable module (12) via internal connector raceway system (24). Raceway sealed chamber volume (44) therefore collectively and continuously traverses all present stackable modules (12) positioned between module lid (14) and module stack base (16). Modules are interchangeable and inter-connectable in any order, and contain all required electronic or mechanical components required for CBSAS (10) to function as a single box consolidated avionics system that is equally functional in the atmosphere or the vacuum of space, while also being fully functional as a single complete stand-alone satellite system. CBSAS (10) enables a paradigm shift in the aerospace industry whereby all legacy and current multiple black-box systems on aerospace platforms such as missiles, rockets, satellites and aircraft are extremely inefficient when compared to the size, weight and power attributes of CBSAS (10). The ability for CBSAS (10) to be instantly employable as either a single box consolidated avionics system for use within the atmosphere or in space while also being fully functional as a stand-alone satellite enables a hardware, firmware and software capability never before manifested in the aerospace industry.

An engine mount assembly for coupling an engine to an airframe. The engine mount assembly includes a torsion bar coupled between the engine and the airframe. The torsion bar has upper and lower tapered bosses. Upper and lower arm assemblies couple the engine to the torsion bar. Each arm assembly has an end bell crank with a tapered socket that is adapted to receive a respective tapered boss therein to secure the end bell cranks to the torsion bar such that the end bell cranks rotate with the torsion bar responsive to movements of the engine.

A control device of the pitch of blades of a rotor of a propeller is provided. The control device includes: a radial shaft; a pivot connected to the blade, the rotation of the radial shaft driving the rotation of the pivot for the modification of the pitch of the blade; an insert fixed rigidly to the pivot so as to block their relative displacement, the radial shaft being configured to drive in rotation the insert; at least one peg passing through the insert and the pivot for transmission of the rotation of the insert to the pivot; and a heat insulation element arranged between the insert and the pivot, whereof the thermal conductivity is less than the thermal conductivity of the pivot and of the radial shaft.

A blended wing aircraft including a blended wing fuselage and at least one embedded gas turbine engine in the fuselage. The gas turbine engine includes an inlet duct formed with a generally elliptical shape that includes a first set of ellipse sections along an upper portion of the inlet duct and a second set of ellipse sections along a lower portion of the inlet duct. The inlet duct includes a vertical centerline. The first set of ellipse sections at a throat of the inlet duct is larger in area than an area of an upstream most end of the second set of ellipse sections. The area of the second set of ellipse sections increases toward a downstream end of the inlet duct. A fan section has an axis of rotation that is spaced from the vertical centerline and is disposed within an inlet duct orifice. The inlet duct is upstream of the fan section.

A blended wing aircraft including a blended wing fuselage and at least one embedded gas turbine engine in the fuselage. The gas turbine engine includes an inlet duct formed with a generally elliptical shape that includes a first set of ellipse sections along an upper portion of the inlet duct and a second set of ellipse sections along a lower portion of the inlet duct. The inlet duct includes a vertical centerline. The first set of ellipse sections at a throat of the inlet duct is larger in area than an area of an upstream most end of the second set of ellipse sections. The area of the second set of ellipse sections increases toward a downstream end of the inlet duct. A fan section has an axis of rotation that is spaced from the vertical centerline and is disposed within an inlet duct orifice. The inlet duct is upstream of the fan section.

An aircraft propulsion system comprises first and second co-axial propulsors, one of the first and second propulsor being positioned forward of the other propulsor. A first electric motor is configured to drive the first propulsor, and a second electric motor is configured to drive the second propulsor. The first electric motor comprising a rotor radially inwardly of the stator, and the second electric motor comprises a rotor radially outwardly of the stator. The stator of the first electric motor is mounted to the stator of the second electric motor.

A system for electric aircraft navigation includes a sensor configured to detect a navigation signal, a flight controller, wherein the flight controller is configured to receive the navigation signal, identify a navigation status as a function of the navigation signal, and determine an aircraft adjustment as a function of the navigation status, and a pilot display, wherein the pilot display is configured to display the aircraft adjustment to a user, and present an autonomous function configured to enact the aircraft adjustment automatically.

A feed-through assembly for a bulkhead for moving and static engine components. The feed-through assembly can be configured to include flexible convolutions that allow for movement and sealing of the engine component relative to the bulkhead. In one aspect, a flexible convoluted spherical element can be provided in the feed-through assembly. In another aspect, a flexible convoluted bellow element can be provided in the feed-through assembly. These flexible convoluted elements can have multiple convolution sections including convolution sections with varying stiffness. The convolution sections can be configured to allow movement of the shaft relative to the bulkhead, including, transverse deflection and tilt.

A feed-through assembly for a bulkhead for moving and static engine components. The feed-through assembly can be configured to include flexible convolutions that allow for movement and sealing of the engine component relative to the bulkhead. In one aspect, a flexible convoluted spherical element can be provided in the feed-through assembly. In another aspect, a flexible convoluted bellow element can be provided in the feed-through assembly. These flexible convoluted elements can have multiple convolution sections including convolution sections with varying stiffness. The convolution sections can be configured to allow movement of the shaft relative to the bulkhead, including, transverse deflection and tilt.