Technologies for providing emergency egress routes for a blended wing body aircraft are described herein. In some examples, the emergency egress routes are through a side cabin bulkhead and aft one or more cargo holds. In some examples, the blended wing body aircraft has wings that are high geometry wings. In these examples, the emergency egress routes do not penetrate an aft spar, reducing weight and increasing the integrity of the aircraft.

Technologies for providing emergency egress routes for a blended wing body aircraft are described herein. In some examples, the emergency egress routes are through a side cabin bulkhead and aft one or more cargo holds. In some examples, the blended wing body aircraft has wings that are high geometry wings. In these examples, the emergency egress routes do not penetrate an aft spar, reducing weight and increasing the integrity of the aircraft.

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

The disclosure provides a penetrating high wing structure of civil aircraft with blended-wing-body, wherein the structure comprises a left wing, a right wing and a high wing penetrating central wing. The left wing and the right wing are symmetrically arranged and connected to two sides of the high wing penetrating central wing through fasteners respectively, and the high wing penetrating central wing is arranged on the top of the main body. The left wing and the right wing both comprise wing ribs and wing spars that are arranged in a crisscross way. The disclosure proposes a penetrating high wing structure, wherein the wing and the body are designed as a whole so that the wings will not damage the continuity of the internal space of the body, which improves the load transfer efficiency of the structure and reduces the fasteners used for connection, thus reducing the weight of the body.

The disclosure provides a penetrating high wing structure of civil aircraft with blended-wing-body, wherein the structure comprises a left wing, a right wing and a high wing penetrating central wing. The left wing and the right wing are symmetrically arranged and connected to two sides of the high wing penetrating central wing through fasteners respectively, and the high wing penetrating central wing is arranged on the top of the main body. The left wing and the right wing both comprise wing ribs and wing spars that are arranged in a crisscross way. The disclosure proposes a penetrating high wing structure, wherein the wing and the body are designed as a whole so that the wings will not damage the continuity of the internal space of the body, which improves the load transfer efficiency of the structure and reduces the fasteners used for connection, thus reducing the weight of the body.

A High Altitude Pseudo Satellite (HAPS) aircraft is disclosed, the aircraft including at least one aeroelastic span loaded fixed wing, an aspect ratio greater than 15 and wing loading less than 6 kg/m.sup.2, where the at least one wing has a plurality of spoilers distributed across the span of the wing and each spoiler being chordwise located adjacent the centre of pressure of the wing. The HAPS aircraft further includes a control system for controlling the spoilers, sensors which allow at least one of the quantity or quantities selected from the group comprising the amount of lift at points or regions along the wing span the pitch and roll at points or regions along the wing span, the bending and torsional strain at points or regions along the wing span, or the net speed and roll and pitch angle of the wing to be determined by the control system, and the spoiler being activatable to reduce the lift experienced by the wing in the location of the spoiler in response to the quantities determined by control system.

A High Altitude Pseudo Satellite (HAPS) aircraft is disclosed, the aircraft including at least one aeroelastic span loaded fixed wing, an aspect ratio greater than 15 and wing loading less than 6 kg/m.sup.2, where the at least one wing has a plurality of spoilers distributed across the span of the wing and each spoiler being chordwise located adjacent the centre of pressure of the wing. The HAPS aircraft further includes a control system for controlling the spoilers, sensors which allow at least one of the quantity or quantities selected from the group comprising the amount of lift at points or regions along the wing span the pitch and roll at points or regions along the wing span, the bending and torsional strain at points or regions along the wing span, or the net speed and roll and pitch angle of the wing to be determined by the control system, and the spoiler being activatable to reduce the lift experienced by the wing in the location of the spoiler in response to the quantities determined by control system.

A passenger vertical take-off and landing aircraft includes a flying wing comprising a passenger compartment, a first set of rotors positioned at least partially forward of a leading edge of the flying wing, and a second set of rotors positioned at least partially rearward of a trailing edge of the flying wing. The first set of rotors may include at least four rotors and the second set of rotors may comprise at least two rotors. The first set of rotors, the second set of rotors, both, or neither may be tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft.

A passenger vertical take-off and landing aircraft includes a flying wing comprising a passenger compartment, a first set of rotors positioned at least partially forward of a leading edge of the flying wing, and a second set of rotors positioned at least partially rearward of a trailing edge of the flying wing. The first set of rotors may include at least four rotors and the second set of rotors may comprise at least two rotors. The first set of rotors, the second set of rotors, both, or neither may be tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft.

A coupled landing gear apparatus for an aircraft including at least a nose gear disposed forward of a neutral point of an aircraft by a first distance and at least a main gear disposed aft of the neutral point of the aircraft by a second distance. The at least a nose gear and the at least a main gear are in communication with one another.