Abstract: An aircraft including a fuselage, an aircraft fuselage end cargo door, and a fuselage end cargo door mechanism. The aircraft fuselage end cargo door couples to the fuselage at a major joint line. The fuselage end cargo door mechanism including a hinge rotatably coupling an aircraft fuselage end cargo door to a fuselage, the hinge being coupled to both the aircraft fuselage end cargo door and the fuselage so that an axis of rotation of the aircraft fuselage end cargo door, defined by the hinge, relative to the fuselage is located forward of a major joint line between the aircraft fuselage end cargo door and the fuselage, wherein an uppermost portion of the major joint line comprises a joint line radius where a portion of the joint line radius formed by the aircraft fuselage end cargo door pivots within another portion of the joint line radius formed by the fuselage.

Abstract: A fixed-wing cargo aircraft having a kinked fuselage is disclosed. The fuselage contains a continuous interior cargo bay, and includes a forward portion, an aft portion, and a kinked portion forming a junction in the fuselage between the forward and aft portions. The kinked portion contains a transition region of the cargo bay and defines a bend between a forward centerline and an aft centerline. The kinked portion is formed with a forward transverse frame section, a separate aft transverse frame section, and a plurality of longitudinal frame elements extending between the forward and aft frame sections, the forward frame being coupled to an aft end of the forward portion and the aft frame section being coupled to a forward end of the aft portion such that the aft frame section is angled with respect to the forward frame section about a lateral axis of the cargo aircraft.

Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft has an airframe including first and second wings with first and second pylons coupled therebetween. A distributed thrust array is coupled to the airframe including a plurality of propulsion assemblies coupled to the first wing and a plurality of propulsion assemblies coupled to the second wing. A cargo pod is coupled between the first and second pylons. The cargo pod is rotatable between a loading configuration, substantially perpendicular to the wings and a transportation and deployment configuration, substantially parallel to the wings. A flight control system is configured to independently control each of the propulsion assemblies and to autonomously deploy a payload from the cargo pod at a desired location.

Abstract: A vertical take-off and landing (VTOL) aircraft provides transportation to users of a network system. The network system may include multiple aircraft or other types of vehicles to provide multi-model transportation. An aircraft may include a fuselage, a truss coupled to the fuselage, and multiple distributed electric propellers coupled to the truss. The distributed electric propellers may be positioned on at least two different planes. The fuselage may include a cabin having one or more seats for the passengers arranged in a configuration that has a compact footprint, provides legroom, provides visibility to surroundings of the aircraft, or facilitates convenient ingress or egress of passengers. The aircraft may open a port cabin door and starboard cabin door for simultaneous ingress or egress of passengers.

Abstract: Longitudinal lock devices for cargo in aircraft having a locking box fastened beneath the floor of an aircraft include a locking latch connectable to the cargo and coupled to a bar mechanism disposed inside the locking box. The locking latch is moveable in a direction towards extraction of the cargo in flight. The bar mechanism is fixed to the locking box and includes a puppet arm articulated on a second pivot wand a puppet follower articulated on a first pivot, whereby each of the pivots is operably fastened to the locking box (9). The puppet arm comprises a cam profile on a face there of which is cooperative with a puppet roller connected to an electro-mechanical actuator linear by means of a drive rod. The articulations moving the bar mechanism responsively determine locked, armed and released positions for the device.

Abstract: Shoring blocks used as pedestal shoring under the cargo loading ramps of cargo planes and also used as sleeper shoring to support the weight of rolling stock loaded into cargo aircraft provide stackable foam structures of various and applicable shapes and sizes designed for particular cargo aircraft, each foam structure alternatively provided with a protective coating or fabric, reinforced with a stiffener or having fabric webbing integrated within or connecting more than one foam structure.

Abstract: Systems, methods, and apparatus for an aircraft cargo handling system articulating ball mat are disclosed. In one or more embodiments, a method for transferring cargo across a stepped threshold and into a sloped compartment involves moving the cargo across the stepped threshold and onto a ball mat located within the sloped compartment, where the ball mat is configured in a substantially horizontal position. In one or more embodiments, the surface of the ball mat comprises at least one conveyance device (e.g., at least one roller ball and/or at least one caster). The method further involves configuring the ball mat in a sloped position. Further, the method involves moving the cargo off the ball mat and into the sloped compartment.

Abstract: A counterbalance mechanism for counterbalancing weight of a bottom-hinged door (such as a clamshell-type airstair door of an aircraft) includes an operator handle, a hoist rod pivotally connected at one end to the operator handle and at an opposite end thereof to the door near a bottom region thereof. A force accumulator assembly is provided which includes a force biasing member which accumulates and dissipates a bias force when opening and closing the door, respectively, to provide mechanical counterbalance to the weight of the door. A bellcrank assembly operatively connects the operator handle to the force accumulator. In such a manner, weight counterbalancing of the door is achieved.

Abstract: A guiding mechanism is disclosed for moving a cargo door into extended cargo door positions to open and into a retracted cargo door position to close at least one section of an opening of a loading hatch on a fuselage of an aircraft. A first structural component in the form of the cargo door is pivotably supported on a second structural component on a front lateral edge by a pivot joint arranged in a pivoting axis in order to assume the extended cargo door positions on the loading hatch. The guiding mechanism features at least one actuator for moving the cargo door, a supporting device arranged on an actuating element, and a spring mechanism on the actuator for exerting a compressive force.

Abstract: An airship for facilitating transportation to and from one or more locations which are difficult to access or operate such as high above the ground level is disclosed. The airship can also be used in surface missions, The airship includes a cabin and a platform. The cabin is configured on a top portion of the airship. The platform is operatively connected to the cabin. The platform facilitates easy access to the cabin.

Abstract: A foldable ramp for evacuation of a vehicle, the ramp including hingedly connected primary and secondary side members, a primary fixed panel fixedly attached the primary side members, a primary flipping panel extending between the primary side members adjacent the primary fixed panel and having a first end pivotally connected to the primary side members and a second end free from the side members, and a secondary flipping panel extending between the secondary side members and having a first end free from the side members and hingedly connected to the second end of the primary flipping panel and a second end pivotally connected to the secondary side members. The ramp is configurable between a folded and a deployed position, with the panels in the deployed position forming a ramp surface and the panels in the folded position being stacked one against the other.

Abstract: A method and apparatus for operating a cargo ramp system. A ramp having a first end and a second end may be moved between a deployed position and an undeployed position using a movement system. The ramp may be maintained in a substantially horizontal position when the ramp is in the deployed position using a hinge system associated with the first end.

Abstract: A flexible mounting assembly allows relative movement between a top and a bottom structural member of an air frame, for instance, a helicopter. The flexible mounting assembly comprises a vertical frame member and an isolation frame member where one of the vertical frame member and the isolation frame member has a pin and the other of the vertical frame member and the frame isolation member has an aperture adapted to slidingly receive the pin in a way to accommodate relative vertical motion therebetween while substantially restraining lateral movement therebetween. The flexible mounting assembly may also include a horizontal shear wall assembly extending between adjacent vertical frame members that accommodates relative vertical motion between top and bottom structural members while substantially restraining lateral movement therebetween.

Abstract: Attachment bolts and tensioned support systems (e.g., aircraft access systems) are set forth herein. According to one embodiment, an attachment bolt for use in a tensioned support system includes a head portion and a shaft portion extending from the head portion. The head portion has an end face, and the shaft portion has at least one thread and a tip distal to the head portion. A cavity extends entirely through the head and shaft portions and has a linearly extruded segment, an extended diameter at the end face, and an enlarged diameter at the tip. The extended diameter is larger than a diameter of the linearly extruded segment, and the enlarged diameter is larger than the diameter of the linearly extruded segment.

Abstract: The invention relates to an emergency exit hatch for exiting a cabin module for an aircraft in an emergency and entering the cabin module. Said emergency exit hatch comprises a first mechanism for visually inspecting a zone below the emergency exit hatch by at least partly opening the emergency exit hatch by means of the first mechanism, and a second mechanism for entirely opening the emergency exit hatch . The first mechanism is not the same as the second mechanism.

Abstract: The invention relates to floor heating for an aircraft which has a floor (20) made up of heatable panels (18). In order to be able to heat up the panels (18) in an energy-saving way, the same are provided with hollow chambers (26) which pass through them, wherein a feed line (28) for warm waste air originating from the cooling of the aircraft's electronic equipment which is connected to the first hollow chambers (26), conveys hot air to the first hollow chambers (26) when the floor heating system is in operation.

Abstract: A roll-on/roll-off, aircraft-borne sensor pod deployment system having an operator station and a sensor pallet system and method of using same. The operator station has a base platform, a shelter box mounted on the base platform for accommodating a human operator, and a computer installed inside the shelter box. The sensor pallet system has a base platform, a linear system mounted on the base platform, a rotational system mounted on the linear system, a mechanical arm attached to the rotational system, a sensor pod attached to the mechanical arm, and an electrical control system that provides power to the deployment system and controls movements of the sensor pallet system. In operation, the sensor pod can be retracted into a compact, stowing position, or extended out an opening in the aircraft for an unobstructed field of view. The deployment system optionally includes an apparatus and method for sealing the aircraft opening.

Abstract: A door opening and closing mechanism for opening and closing the door from the inside of a fuselage. A door pivotally supported at an opening portion of the fuselage includes first and second position restricting links each having one end pivotally supported on the fuselage with a door driving link having one end pivotally supported on the door. The other end of the second position restricting link is pivotally supported on a middle portion of the door driving link. The door opening/closing operation lever is provided at one end with a grip with the other end pivotally supported on the other end of the door driving link. The middle portion of the door opening/closing operation lever is pivotally supported on the other end of the first position restricting link. By pulling the grip toward the inside of the fuselage and thereafter pushing downward, the door can be closed.

Abstract: When a single door for opening and closing an opening in a body is opened outward with its lower part as a fulcrum, a plurality of plate-shaped steps of a foldable boarding ramp provided on an inner face of the door are swung in association with one another from a stored position along the inner face of the door to a deployed position to be used for ingress and egress of the passengers. Since the boarding ramp is folded into the stored position, it does not impair the space of a passenger compartment. Further, since the steps are folded into a position so as not to interfere with a window provided in an upper part of the door, they do not give an oppressed feeling to the passengers in the passenger compartment. The step is deployed to cover the window provided in the upper part of the door during use.

Abstract: A foldable boarding ramp is operatively connected to a door opening provided in a body and is selectively extendable to the ground. The foldable boarding ramp is stored in a folded state inside a fairing covering a connecting portion between the body and a main wing. Thus, a reduction in the space of a passenger compartment and a cargo compartment due to the storage of the folded boarding ramp is prevented. In addition, an increase in air resistance can be suppressed without providing a dedicated fairing for covering the boarding ramp. Further, an interlocking member connects together a door for opening and closing the door opening and the boarding ramp when the door is opened. The boarding ramp may be automatically deployed to improve convenience.

Abstract: An ejection device for an aircraft hatch having at least one articulation hinge. The articulation hinge is provided with a lower element designed to be mounted in rotation on structure of the aircraft, and an upper element designed to be joined to the hatch panel. The lower element and the upper element are connected to one another in a reversible manner. The ejection device has guide means in which the upper element of the articulation hinge is engaged, to hold the upper element in the axis of rotation (A) of the lower element during the activation of the hatch. The upper element of the articulation hinge can be separated from the guide means beyond a critical swing angle, so that the upper element is separated from the lower element of the articulation hinge. The invention also concerns an ejectable hatch for an aircraft.

Abstract: When a single door for opening and closing an opening in a body is opened outward with its lower part as a fulcrum, a plurality of plate-shaped steps of a foldable boarding ramp provided on an inner face of the door are swung in association with one another from a stored position along the inner face of the door to a deployed position to be used for ingress and egress of the passengers. Since the boarding ramp is folded into the stored position, it does not impair the space of a passenger compartment. Further, since the steps are folded into a position so as not to interfere with a window provided in an upper part of the door, they do not give an oppressed feeling to the passengers in the passenger compartment. The step is deployed to cover the window provided in the upper part of the door during use.

Abstract: A landing arrangement for an aircraft comprises an aircraft support assembly (22) to support the aircraft (10) when the aircraft is on the ground. The aircraft support assembly (2) is movable between a first ground engaging condition (22b) in which the aircraft nose (24) is spaced above the ground by a first distance (X) and a second ground engaging condition (22C) in which the aircraft nose (24) is spaced above the ground by a second distance (Y). The second distance (Y) is less than the first distance (X).

Abstract: A less-than-200-seat-class airplane includes a fuselage having a horizontal diameter value of a cross-section greater than a vertical diameter value of the cross-section. The cross-section is perpendicular to the longitudinal axis of the fuselage. The fuselage includes a passenger cabin and at least one cargo compartment located below the passenger cabin.

Abstract: Boarding device for aircraft and flying wings equipped with such a device. The boarding device consists of at least one tunnel (20) connected to the outside of the aerodynamic shell (12) of the aircraft. More precisely, the tunnel is attached to the trailing edge of the fairing (12) and it extends aft approximately parallel to the longitudinal axis of the aircraft. A door (22) closes off the opening between the passenger cabin (10) and the tunnel (20). The rear part (26) of the tunnel (20) is articulated and/or detachable. In order to evacuate the passengers in an emergency, the front, fixed part of the tunnel (24) can be fitted with an inflatable escape slide or an articulated floor.

Abstract: An aircraft having a cabin within a wing of the aircraft includes an access opening in an aft end of the cabin adjacent a trailing edge of the wing, and a trailing edge portion of the wing juxtaposed with the access opening and including at least one pivotable panel which is pivotable into an open position so as to form a passage in the trailing edge portion for entry therethrough and through the access opening into the cabin. The trailing edge portion in one embodiment comprises upper and lower panels which are normally in converging relation such that the passage to the access opening of the cabin is normally closed, but which are pivotable relative to each other for creating the passage. The lower panel preferably is pivotable into a generally horizontal position so that it serves as a ramp for loading and unloading persons and cargo into and from the cabin. The upper and/or lower panel in another embodiment may be pivoted during flight so as to serve as a control surface for the aircraft.

Abstract: An aircraft door is slidable along a door path between open and closed positions. The door is guided by one or more tracks. Riders carried by the door are engaged to the tracks. Each rider includes a roller held for rotation about a roller axis which is fixed relative to the door. Each roller axis extends generally horizontally and generally transverse to the track. Each track includes a first portion extending generally parallel to the aircraft fuselage and a second portion having a continuously curving transition to the first portion and extending partially inboard from the first portion. The second portion of the track guides the door into and out of the opening in the fuselage, allowing the door to achieve a substantially flush condition when in its closed position.