An aircraft with a mid-market passenger capacity, wherein the aircraft comprises, a blended wing body aircraft having a main body and wings with no clear demarcation between the wings and the main body along a leading edge of the aircraft, wherein the main body is structured to comprise a passenger cabin configured to have a mid-market passenger capacity, wherein the main body is structured to comprise a structural element, the structural element extending vertically from a lower surface of the main body toward an upper surface of the main body, and at least a propulsor, the at least a propulsor attached to the main body and configured to propel the aircraft.

Aspects relate to systems and methods for folding wings on an aircraft. An exemplary system includes a blended wing body, where the blended wing body includes a main body and at least a wing, a hinge located on the at least a wing and configured to allow folding of the at least a wing, an actuation system configured to fold the at least a wing, and a controller configured to control the at least an actuation system.

Aircraft with fuel tanks stored aft of the main body and method of manufacturing an aircraft with fuel tanks stored aft of the main body. Aircraft includes a blended wing body, wherein the blended wing body includes a main body and a cabin at least partially located within the main body. The aircraft further including a plurality of fuel tanks located at least partially aft of the cabin within the main body and configured to store liquified gas fuel. The fuel tanks may include a multi-lobe geometry.

A system and method for a blended wing body aircraft with permanent tanks is presented. The aircraft comprises a blended wing body and at least a tank permanently attached the blended wing body. The at least a tank is configured to store liquified gas fuel and further comprises at least a vent configured to vent gaseous fuel from the at least a tank and an insulation to reduce thermal transfer to the liquified gas fuel inside of the at least a tank.

A system for a blended wing body aircraft with a combustion engine is illustrated. The aircraft comprises a blended wing body, at least a fuel source located within the blended wing body and configured to store a fuel, wherein the fuel includes liquid hydrogen, and at least a propulsor configured to propel the blended wing body aircraft. The at least a propulsor comprises a combustion engine configured to burn the fuel from the fuel source and produce mechanical work to power the at least a propulsor.

In an aspect, an aircraft fueling apparatus is disclosed. The apparatus includes at least a container comprising a fuel tank configured to store liquified gas fuel. The apparatus may also include a translocation device configured to carry the at least a container. An orientation guidance track may also be included in the apparatus. The orientation guidance track may be configured to direct a movement of the translocation device to a first position.

A system for modular aircraft includes at least a common component, wherein the at least a common component includes at least a flight component. The system includes at least a modular component, wherein the at least modular component includes at least a fuselage component and a collar component. The system includes at least an interface component, wherein the at least an interface component is configured to connect the at least a common component at a first end to the at least a modular component at a second end.

An aircraft with a multi-walled fuel tank and method of manufacturing is presented. The aircraft includes a blended wing body and a fuel tank attached to the blended wing body configured to store liquified gas fuel. The fuel tank includes an inner wall, outer wall, and interstitial volume in between that is filled with insulation. The interstitial volume includes a reflective film layer and a structural insulation layer.

Aspects relate to an aircraft having a controllable center of gravity and methods of controlling the center of gravity. An exemplary aircraft having a controllable center of gravity includes a first tank configured to store a first portion of a ballast, a second tank configured to store a second portion of the ballast disposed substantially aft of the first tank, at least a pipe configured to provide fluidic communication between the first tank and the second tank, at least a pump configured to pump the ballast bidirectionally between the first tank and the second tank by way of the at least a pipe, and a controller in communication with the at least a pump and configured to control a ballast ratio of the first portion of the ballast relative the second portion of the ballast and affect an aircraft center of gravity.

An aircraft with a lifting body fuselage profile having a nose end, tail end and having an upper surface between the nose and the tail end and a lower surface between the nose and the tail end. The profile of the upper surface having a section of a first ellipse starting at the nose end and a first circle arc transitioning from the first ellipse section to the tail end. The profile of the lower surface having a second circle arc transitioning from the section of the first ellipse of the upper surface at the nose end and transitioning to a straight line. The profile of the lower surface having a third circle arc transitioning from the straight line and a fourth circle arc transitioning from the third circle arc and ending at the tail end.