| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244120000 | Sectional | 52 |
| 20080210818 | Autonomous, back-packable computer-controlled breakaway unmanned aerial vehicle (UAV) - A modular unmanned aerial vehicle (UAV) having a fuselage, a nose cone, a left wing piece, a right wing piece, and a tail section. The tail section and nose cone each join to the fuselage through mating bulkhead structures that provide quick connection capability while being readily separated so as to enable the UAV to break apart at these connection points and thereby absorb or dissipate impact upon landing. The UAV is capable of rapid assembly in the field for two-man launch and data retrieval, as well as quick disassembly into these five component parts for transport and storage in a highly compact transport case that can be carried as a backpack. | 09-04-2008 |
| 20080210819 | Stringers assembled at a circumferential join of an airplane fuselage - The disclosed embodiments relates to an airplane fuselage produced by assembly, at a circumferential join, at least two sections including a skin and at least one stringer split into two elements and which are assembled at the join between the two sections by at least one splicing plate. The splicing plate includes a web having a bearing surface including two surfaces bearing on lateral faces of the elements of the stringer, the two surfaces being offset by an amount ε substantially equal to an error of alignment between the lateral faces of the elements of the stringer. | 09-04-2008 |
| 20080210820 | AIRCRAFT FLOOR AND METHOD OF ASSEMBLY - The invention relates to aircraft floor assemblies and to methods for their assembly. In one embodiment, an aircraft comprises at least one fuselage section and at least one floor section. At least one system component is installed to the floor section prior to installation of the floor section in the fuselage of the aircraft. In another embodiment, a floor section adapted to be installed in an aircraft includes at least one system component installed to the floor section while it is outside of the aircraft. In yet another embodiment, a method is disclosed for assembling an aircraft. The method comprises installing at least one system component to a floor section, and installing the floor section into a fuselage section of the aircraft. | 09-04-2008 |
| 20080230652 | COMPOSITE BARREL SECTIONS FOR AIRCRAFT FUSELAGES AND OTHER STRUCTURES, AND METHODS AND SYSTEMS FOR MANUFACTURING SUCH BARREL SECTIONS - Composite sections for aircraft fuselages and methods and systems for manufacturing such sections are disclosed herein. A composite section configured in accordance with one embodiment of the invention includes a skin and at least first and second stiffeners. The skin can include a plurality of unidirectional fibers forming a continuous surface extending 360 degrees about an axis. The first stiffener can include a first flange portion bonded to an interior surface of the skin and a first raised portion projecting inwardly and away from the interior surface of the skin. The second stiffener can include a second flange portion bonded to the interior surface of the skin and a second raised portion projecting inwardly and away from the interior surface of the skin. A method for manufacturing a section of a fuselage in accordance with one embodiment of the invention includes positioning a plurality of uncured stiffeners on a mandrel assembly. The method can further include applying a plurality of fiber tows around the plurality of uncured stiffeners on the mandrel assembly. | 09-25-2008 |
| 20080296432 | METHOD OF EXTENDING LENGTH OF AIRCRAFT TO INCREASE INTERIOR SPACE - A method of modifying an aircraft, increasing its length, to increase interior of the aircraft fuselage to accommodate more passenger rows or more freight. The typical aircraft such as the Boeing 757 aircraft includes a fuselage, a wing section and a tail section, wherein the method installs an extension section or plug in the fuselage aft of the wing section and further adjusts the forward center of gravity limits aft. | 12-04-2008 |
| 20090014587 | AIRCRAFT SAFETY SYSTEM - An aircraft ( | 01-15-2009 |
| 20090020646 | ASSEMBLY OF PANELS OF AN AIRPLANE FUSELAGE - An aircraft fuselage including at least two sections kept assembled at a circumferential join, each section having at least one panel. The circumferential join includes at least one inner ring, situated on one face, called the inner face, of the fuselage. The inner ring has a width l | 01-22-2009 |
| 20090184202 | STRUCTRUAL ELEMENT MADE OF AN ALUMINUM ALLOY INCLUDING AN OPTICAL SENSOR - Provided herein is a method for manufacturing a worked product comprising a fiber sensor therein. Also provided is a wrought product comprising a fiber sensor as well as structural elements and other products including fuselage skin and a wing panel. | 07-23-2009 |
| 20090236473 | PROVIDING SKINS FOR AIRCRAFT FUSELAGES - An aircraft including a space frame fuselage structure. A plurality of panels are connected with the structure and configured to form a skin over the structure. The panels are movable relative to one another so as to prevent loading of the structure from inducing loading in the skin. | 09-24-2009 |
| 20090250554 | SELF-SUPPORTING CABIN STRUCTURE - A cabin structural unit for attaching cabin installation elements is provided for an aircraft. The cabin structural unit is set up in such a way that a cabin installation element is attachable. The cabin structural unit is implemented as self-supporting and fastenable to an aircraft structure. | 10-08-2009 |
| 20090272846 | BONDED METAL FUSELAGE AND METHOD FOR MAKING THE SAME - A bonded metal fuselage for aerospace vehicles includes a monocoque structure having an outer metal skin, metal tear straps bonded to the outer skin and metal stringers bonded to the outer skin and to the tear straps. The outer chords of fuselage frames are fastened directly to tear straps and to the skin, obviating the need for clips to fasten the frames to the stringers. | 11-05-2009 |
| 20100012782 | Aircraft With Modular Structure - An aircraft includes a module carrier for accommodating a plurality of module elements in which in each case at least one system element is integrated. The module elements and system elements are networked among each other such that a desired aircraft model is implemented. | 01-21-2010 |
| 20100025531 | Aircraft-fuselage assembly concept - An aircraft fuselage section includes a first interior tube as well as a second interior tube that are produced in an upstream production step, which interior tubes are subsequently enclosed by an exterior tube. For spacing and in order to provide more stability to the tubes the interior tubes are enclosed by straps that are arranged between the interior tubes and the exterior tube. | 02-04-2010 |
| 20100025532 | SHELL ELEMENT AS PART OF AN AIRCRFAFT FUSELAGE - The present invention provides a shell element as part of an aircraft fuselage, wherein the shell element is formed as a curved sheet-like element and is at least partially or completely of CRP construction. | 02-04-2010 |
| 20100032523 | AIRCRAFT FUSELAGE MADE FROM LONGITUDINAL PANELS AND METHOD OF PRODUCING SUCH A FUSELAGE - The invention relates to an aircraft fuselage comprising a nose cone, a tail section and a central section, the central section comprising longitudinal panels assembled directly with one another, at least one of these longitudinal panels having a length corresponding to the distance between the nose cone and the tail section in order to connect said nose cone with said tail section. | 02-11-2010 |
| 20100133382 | WING-FUSELAGE SECTION OF AN AIRCRAFT - A wing-fuselage section of an aircraft, which wing-fuselage section comprises a wing root at which the wing of the aircraft is connected to the fuselage, a fuselage region with fuselage frame elements that extent across the longitudinal direction of the aircraft, and a wing region with spars that extend in the direction of the wingspan. According to the invention, the spars of the wing region and the fuselage frame elements of the fuselage region form part of an integral assembly that extends at least over a middle part of the wing and the fuselage region, including the wing roots. | 06-03-2010 |
| 20100170987 | CENTRAL SECTION OF AIRCRAFT WITH VENTRAL OR BELLY FAIRING CAPABLE OF MOVEMENT - An aircraft center section includes a center part of an aircraft fuselage, a wing section, a center wing box installed at least partly in the fuselage and providing a junction between the wing section and the fuselage, and a ventral fairing partly enveloping the fuselage and the wing section, with the ventral fairing being attached directly to the wing section and to the fuselage by means of structural elements that can make the ventral fairing a working fairing. | 07-08-2010 |
| 20100170988 | SECTION OF AIRCRAFT FUSELAGE IN COMPOSITE MATERIAL WITH A CONSTANT INTERIOR PROFILE - The disclosed embodiments concern an aircraft fuselage section made of composite material with an internal skeleton having frames that form the radial structure of the fuselage and stringers that form the longitudinal structure of said fuselage, and a skin made of composite material, surrounding the internal skeleton, with said skin having an evolving thickness along a longitudinal axis X, with an approximately constant, regular interior profile. The disclosed embodiments also concern a process for manufacturing the skin of an aircraft fuselage section made of composite material, having a draping operation for strips of fibers precoated with resin around a mold, with the number of strips of fibers varying longitudinally depending on the area of the fuselage being considered so as to create a skin with an evolving thickness. | 07-08-2010 |
| 20100282905 | SPLICING OF OMEGA-SHAPED STIFFENERS AT A CIRCUMFERENTIAL JOINT IN AN AIRCRAFT FUSELAGE - An aircraft fuselage produced by assembling, at a circumferential joint, at least two sections, each section including a coating and at least one element of at least one stiffener, the aforementioned two elements having a closed cross section and being assembled by a splicing piece. The elements of the stiffener and the splicing piece are made of composite. The aforementioned splicing piece, which has two flanges, is fixed to the coatings and to the stiffener elements by working fastenings positioned only on the flanges of the aforementioned splicing piece. | 11-11-2010 |
| 20100320321 | METHOD FOR JOINING TWO FUSELAGE SECTIONS BY CREATING A TRANSVERSE BUTT JOINT AS WELL AS TRANSVERSE BUTT JOINT CONNECTION - The invention relates to a method of connecting two fuselage sections ( | 12-23-2010 |
| 20100320322 | TRANSVERSE BUTT CONNECTION BETWEEN TWO FUSELAGE SECTIONS - The invention relates to a transverse butt connection ( | 12-23-2010 |
| 20110024563 | PRESSURE FUSELAGE OF AN AIRCRAFT OR SPACECRAFT WITH PRESSURE CALOTTE - A pressure fuselage of an aircraft or a spacecraft includes at least two fuselage sections disposed longitudinally along the fuselage; at least one pressure calotte disposed in the fuselage so as to form a pressurized area; and an arcuate frame profile having a Y-shaped cross-section with a long profile leg connected to at least one of the at least two fuselage sections and a short profile leg extending at an acute angle from the long profile leg toward an inside of the at least two fuselage sections and attached to the at least one pressure calotte. | 02-03-2011 |
| 20110036946 | AIRCRAFT FLOOR MODULE, STRUCTURE AND METHOD FOR ATTACHING SUCH A MODULE AND AIRCRAFT COMPRISING THEM - A method of fitting-out of an aircraft by laying of a floor, particularly in a cockpit of an aircraft, and such a fitted-out aircraft. The aircraft includes a fuselage part defining an interior volume and at least one internal on-board structure, the on-board structure being secured to the fuselage part and configured to accept a floor module. The method then involves introducing the floor module into the volume and attaching the floor module to the on-board structure. | 02-17-2011 |
| 20110084166 | ARRANGEMENT FOR DIVIDING A SPACE INTO A PLURALITY OF AREAS - The invention relates to an arrangement for dividing a space into a plurality of areas, said arrangement comprising at least one frame with at least one fixing means for holding the frame in corresponding frame receiving elements, and at least one foldable defining means. The frame is formed in such a way that the arrangement essentially fits onto at least one wall of the space when it is fixed, the foldable defining means being able to be held on the frame and preventing an air flow between adjacent areas of the space separated by the arrangement. The arrangement according to the invention enables a thermal separation of two adjacent areas of a space, that can each be air-conditioned differently, without forming an area containing air which is a mixture from two regions at different temperatures. | 04-14-2011 |
| 20110089291 | COUPLING DEVICE FOR COUPLING FUSELAGE SECTIONS; COMBINATION OF A COUPLING DEVICE AND AT LEAST ONE FUSELAGE SECTION; AND METHOD FOR PRODUCING THE COUPLING DEVICE - A coupling device for connecting fuselage sections, in each case forming a transverse abutting region for creating an aircraft fuselage comprising fuselage sections with a fuselage skin, a multitude of annular frame elements and stringers, wherein the coupling device has a rib-like design and includes: a strip-shaped transverse splicing plate for coupling the fuselage skins, a rib, which extends in the middle on the transverse splicing plate, for coupling an annular frame element, and a multitude of rib-like stringer coupling parts that extend on both sides of the transverse splicing plate, for coupling the stringers, as well as a method for producing the coupling device from a solid, rectangular, material trip of suitable thickness and length. | 04-21-2011 |
| 20110168840 | Aircraft frame and method for obtaining the same - An aircraft frame and a method for obtaining an aircraft frame, which frame is made of composite material, and which frame comprises several partitions ( | 07-14-2011 |
| 20110180665 | AIRCRAFT FUSELAGE ELEMENT - The invention relates to an aircraft fuselage element. According to the invention, -said fuselage element being a one-piece component, it comprises a closed wall ( | 07-28-2011 |
| 20110303791 | Fuselage Section of an Aircraft and Method for the Production of the Fuselage Section - In accordance with the method, an inside layer of a fuselage section skin made from first fibers is placed on a manufacturing surface, the first fibers being placed in one or more first fiber directions. On the inside layer, a stiffening structure is formed from stiffening fibers, the stiffening fibers being placed in one or more stiffening fiber directions. An outside layer of the fuselage section skin, comprising fourth fibers, is placed on the stiffening structure formed from stiffening fibers, the fourth fibers being placed in one or more fourth fiber directions. The stiffening structure is designed and developed in such a way that the fuselage section does not require an additional stiffening structure, is connected with the fuselage section skin, and comprises the inside layer, the stiffening structure, and the outside layer; in particular, an additional stiffening structure in the form of stringers and frames is not required. | 12-15-2011 |
| 20120074260 | REAR FUSELAGE OF AN AIRCRAFT - Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising two upper lugs, two lower lugs and a detachable balancer fitting. The balancer fitting is an adjustable fitting, being locked in a Z and Y directions of a Cartesian axis and being movable along an X direction of the Cartesian axis providing guidance for the tail cone end and the rest of the rear fuselage. | 03-29-2012 |
| 20120104167 | FUSELAGE ELEMENT COMPRISING A FUSELAGE SEGMENT AND JUNCTION MEANS, FUSELAGE PORTION, FUSELAGE AND AIRCRAFT - The invention relates to a fuselage element ( | 05-03-2012 |
| 20120132750 | METHOD FOR PRODUCING AN AIRCRAFT FUSELAGE AND AIRCRAFT FUSELAGE - Disclosed is a method for the manufacture of an aircraft fuselage with at least two fuselage barrels wherein connecting segments are firstly prepared for the formation of a transverse joint region for a later transverse joint, and the fuselage barrels are then constructed around the connecting segments; also disclosed is an aircraft fuselage with ring-type connecting segments for the formation of such a transverse joint. | 05-31-2012 |
| 20120153082 | SPLICE AND ASSOCIATED METHOD FOR JOINING FUSELAGE SECTIONS - A splice and an associated method are provided in order to efficiently join structures, such as adjacent fuselage sections. A splice for joining fuselage sections may include a strap configured to bridge the fuselage sections, a shear tie overlying the strap and a fitting positioned between the strap and the shear tie such that the strap and the shear tie are spaced apart. At least the strap and the fitting may be formed of a composite material. The fitting may have an H-shape and may have first and second longitudinally extending sections that extend beyond opposite sides of the strap. Each longitudinally extending section is configured to overlie at least two stringers of a respective fuselage section. The fitting may also have a medial portion upon which the shear tie is seated. | 06-21-2012 |
| 20120223187 | DIAMOND SHAPED WINDOW FOR COMPOSITE AND/OR METALLIC AIRFRAME - An aircraft fuselage may include a barrel section having a side region. The fuselage may include a first cutout and a second cutout formed in the side region in side-by-side relation to one another. The fuselage may provide a direct load path extending along the barrel section. The load path may extend substantially continuously from a lower portion of the side region generally under the first cutout to an upper portion of the side region generally over the second cutout. | 09-06-2012 |
| 20120318919 | AIR VEHICLE MOUNTED TRANSMITTING OR RECEIVING EQUIPMENT - Disclosed is an air vehicle mounted or mountable transmitting and/or receiving equipment including a transmitting and/or receiving turret allowing at least a forward field of view, the device being mounted or mountable on a fuselage such that it extends away from the fuselage to which it is mounted; and a fairing mounted to the fuselage adjacent the device at a rearward side of the device for reducing aerodynamic drag, the fairing being retractable by, for example, an electrically driven mechanism, to afford the device a rearward (arrow R), or more effective rearward, field of view for transmitting and/or receiving. | 12-20-2012 |
| 20130256457 | FUSELAGE SEGMENT AND METHOD FOR MANUFACTURING A FUSELAGE SEGMENT - The invention pertains to a fuselage segment ( | 10-03-2013 |
| 20130292514 | METHOD AND SYSTEMS FOR USE IN ASSEMBLING A FUSELAGE - A fuselage assembly is provided. The fuselage assembly includes a first barrel section including a body that extends from a first end to a second end and a second barrel section coupled to said first barrel section. The second barrel section includes a body that extends from a first end to a second end, and the second end of the first barrel section is coupled to the second end of the second barrel section. At least one member maintains a coupling between the first barrel section and the second barrel section. The at least one member induces a compressive force to at least one of the first barrel section and the second barrel section. | 11-07-2013 |
| 20140001311 | Joining Composite Fuselage Sections Along Window Belts | 01-02-2014 |
| 20140061384 | MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL - An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | 03-06-2014 |
| 20140117157 | Circumference Splice for Joining Shell Structures - The disclosed shell structure splice and method may include a first panel having a first edge, a second panel having a second edge, the second edge being positioned in edgewise alignment with the first edge to form a splice joint, a strap bridging the splice joint and attached to the first panel and the second panel, the strap having a first tapered region and a second tapered region, a first fitting having a tapered section and a flat section, the tapered section being attached to the first tapered region of the strap, and a second fitting having a tapered section and a flat section, the tapered section being attached to the second tapered region of the strap. | 05-01-2014 |
| 20140151504 | Aircraft fuselage structure and method - An aircraft fuselage structure having a first fuselage barrel section and a second fuselage section barrel which are joined by tension fasteners extending through frame holes. A shank diameter of the fasteners is smaller than a respective frame hole diameter. A first positive locking element and a second positive locking element is provided forming a form-fit area with the first positive locking element in the circumferential direction. A method for producing such an aircraft fuselage section is also provided. | 06-05-2014 |
| 20140175224 | AIRCRAFT NOSE WITH COCKPIT AND AVIONICS BAY MODULES INTEGRATED THEREIN - An aircraft nose comprising a primary fuselage structure, and housed inside said structure, a cockpit, and an avionics bay containing a plurality of avionics racks designed to receive electrical and/or electronic equipment. The cockpit and the avionics bay are each made in the form of a distinct module that is suitable for being installed in a single operation inside the primary fuselage structure. The use of modules for integrating in the aircraft nose makes it possible to reduce considerably the time required for fitting out the nose on the final assembly line of the aircraft. | 06-26-2014 |
| 20140175225 | AIRCRAFT COCKPIT HAVING A LOWERED FLOOR FOR WALKING ON - A cockpit for an aircraft nose, the cockpit having a floor that acts solely as a floor for the crew to walk on and that is lower than the height of the cabin floor situated behind the cockpit. The cockpit also has a stair connected to the floor in order to enter and leave the cockpit. This arrangement enlarges the volume of the cockpit and enables equipment to be housed therein that previously used to be housed in the zone that is difficult to access that is situated under the cockpit and that also contains the bay for storing landing gear. | 06-26-2014 |
| 20140175226 | Avionics cargo hold module having an upper integrated floor - An integral avionics bay module. The module has a structure that has an integral cabin floor on top that closes the structure. Installing such an integral avionics bay structure in a single operation inside a primary fuselage structure considerably reduces the integration time on the final assembly line for the aircraft. | 06-26-2014 |
| 20140209743 | AIRCRAFT FRAME - An aircraft frame comprising a first partial aircraft frame configured to be attached to a first aircraft fuselage segment and a second partial aircraft frame configured to be attached to a second aircraft fuselage segment is provided. The first partial aircraft frame and the second partial aircraft frame are configured to be connected to each other to be in a connected configuration forming the aircraft frame such that the first fuselage segment and the second fuselage segment are connectable. | 07-31-2014 |
| 20150034765 | REAR FUSELAGE SECTION OF AN AIRCRAFT - A rear fuselage section of an aircraft comprises at least one closed frame constructed as a unitary body, and a horizontal tail plane comprising a box-type central element and two lateral torsion boxes, said horizontal tail plane trimmable with respect to a pivot axis. The horizontal tail plane is mounted at the closed frame and the pivot axis is contained in a horizontal plane below the lowest end of said closed frame. | 02-05-2015 |
| 20150108273 | MODULAR AIRCRAFT FLOOR TRACK ADAPTER SYSTEM - A modular floor track adapter system including a plurality of adapter plates laterally sized to span existing aircraft floor beams, each of the plurality of adapter plates shaped to interlock with an adjacent adapter plate in a side-by-side arrangement and including a series of holes for attaching seat track crown sections and panel attachment tabs for securing an aircraft floor panel thereto. | 04-23-2015 |
| 20150291273 | METHOD OF JOINING PANELS FOR AN AIRFRAME - A method of joining two panels of an airframe or fuselage structure of an aircraft or spacecraft, including: preparing an edge region of a first panel to form a first joining surface; preparing an edge region of a second panel to form a second joining surface; aligning the panels with one another such that the joining surfaces abut or interface one another forming a joint area; and joining the panels at the joining surfaces in the joint area. In an embodiment, the preparing steps include machining, and cutting, the edge regions of the first and second panels in a single operation to form the first and second joining surfaces substantially simultaneously. In another embodiment, the first and second joining surfaces are substantially planar and extend at an oblique angle with respect to a primary plane or surface of the respective first and second panels. | 10-15-2015 |
| 20160009361 | AIRCRAFT FLOOR INCORPORATING A GROUND PLANE | 01-14-2016 |
| 20160130015 | UNIVERSAL MOUNTING PANEL FOR A ROTARY-WING DRONE - The drone body ( | 05-12-2016 |
| 20160152316 | AERIAL VEHICLE WITH FRAME ASSEMBLIES | 06-02-2016 |
| 20160194094 | METHOD FOR JOINING TWO FUSELAGE SECTIONS AND MOUNTING DEVICE | 07-07-2016 |
| 20160375978 | Stiffened fuselage component as well as method and apparatus for manufacturing a stiffened fuselage component - A stiffened fuselage component made of a fiber reinforced composite material, in particular for use in an aircraft, comprises a skin element and a plurality of elongated stiffening elements forming a stiffening element pattern comprising a plurality of node points and being attached to an inner surface of the skin element. At least some of the node points are defined by an intersection of at least two stiffening elements at an acute angle or an obtuse angle. At least some of the elongated stiffening elements are shaped so as to define an internal cavity delimited by an inner surface of the stiffening elements and covered by the skin element. | 12-29-2016 |
