164results about "Aircraft floors" patented technology

A fastening device for releasable connection to a perforated rail of an aircraft and a method of assembly for such a fastening device. The fastening device comprises a housing having at least one locking head portion fixedly connected to the housing, at least one shear pin and an actuating pin. The locking head portion is insertable into a rail hole of the perforated rail and slidable along the longitudinal direction of the perforated rail to a locking position in which the locking head portion engages a slot portion of the perforated rail. The shear pin can be engaged with a rail hole of the perforated rail by axial displacement. The actuating pin is rotatably arranged relative to the housing and connected to the shear pin in such a way that a rotation of the actuating pin causes an axial displacement of the shear pin relative to the housing.

A structure system for installation into a fuselage structure in an interior of an aircraft is proposed, the system comprising at least one first carrier element, at least one second carrier element, at least one elongate frame element having a first end and a second end, at least one first attachment device for attaching the first carrier element to the fuselage structure or to an element coupled with the fuselage structure, at least one first coupling device mounted to the first end for coupling the first carrier element to the at least one frame element, and at least one second coupling device mounted to the second end for coupling the second carrier element to the at least one frame element, wherein the at least one frame element is adapted for holding at least one component to be installed in the interior, wherein the at least one first carrier element is designed for coupling with the at least one first coupling device, wherein the at least one second carrier element is designed for coupling with the at least one second coupling device, and wherein one of the at least one first coupling device and the at least one second coupling device is adapted to snap into the respective carrier element, to be moved relative to the respective end of the frame element and to be arrested in a desired relative position thereto.

An air drop rack assembly is mounted within the cargo compartment of a cargo aircraft and has a forward part secured to the load deck and an aft part secured to the aircraft cargo ramp. The rack parts have rollers in conveyor assemblies mounted between C-channels which engage skidboards which support smaller aircraft such as gliders or cruise missiles. When the ramp is up two rack parts are tilted with respect to each other. At payload drop, ramp is deployed to bring the rack part conveyor assemblies into alignment. Although the aligned rack parts are spaced apart, when the cargo aircraft is tilted upwardly, the individual payloads on skidboards are discharged out the aircraft aft opening. Cruise missiles or bombs may be supported on a skidboard with a deformable surface, a forward ballast weight, and a spring, such that once launched the skidboard is pushed away from the payload.

A monument for installation in an aircraft passenger cabin comprises a housing extending from the floor upwardly toward the ceiling, the housing including a first configuration configured to receive a wheelchair in a first unfolded condition, and a second configuration configured to receive a stretcher in a second unfolded condition, a first interior space formed in the housing, a staircase disposed within the interior space; a second interior space formed in the housing, a first entrance into the first interior space through a door; a second entrance into the second interior space of the housing, and a securement assembly positionable on the floor, the securement assembly configured to secure one of the wheelchair or the stretcher in place within the interior space.

An aircraft seat connector for mounting an aircraft seat to a mounting rail provided at a floor of an aircraft cabin is provided. The aircraft seat connector comprises a base portion for being introduced into the mounting rail and a seat connection portion. The seat connection portion extends from the base portion and is configured for being releasably coupled to an aircraft seat. The seat connection portion allows for coupling the aircraft seat to the seat connection portion in at least two different spatial orientations.

A method for manufacturing a fuselage structural component (200) for a triangular section of an aircraft is disclosed, comprising the following steps: providing a one-piece sheet (211, 212, 213) of frame material, the sheet having an opening (250), and deforming at least one inner edge of the sheet (211, 212, 213) forming the opening (250) into an inner flange (215, 216, 217), and deforming at least one outer edge of the sheet (211, 212, 213) into an outer flange (214). The one-piece and deformed sheet (211, 212, 213) forms, adjacent to the opening (250), a frame section (210), a bottom support (212), and a vertical support (213).

A safety system for aircraft passenger seats is described. A pallet that can be removably coupled to seats can also be removably coupled to the aircraft floor and one or more brackets, tension fittings, or machined straps that can be coupled to structural beams or components in an aircraft. A keel tension fitting can be attached to a keel beam and then be coupled to the pallet and thereby the seats. By attaching to the keel beam the safety system allows the seating arrangement (pallet and seats) to withstand greater stresses and forces, resulting in increased safety.

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.

An aircraft seat connector (40) for mounting an aircraft seat (20) to a mounting rail (17) provided at a floor of an aircraft cabin (16) is provided. The aircraft seat connector (40) comprises a base portion (42) for being introduced into the mounting rail (17) and a seat connection portion (50). The seat connection portion (50) extends from the base portion (42) and is configured for being releasably coupled to an aircraft seat (20). The seat connection portion (50) allows for coupling the aircraft seat (20) to the seat connection portion (50) in at least two different spatial orientations.

The invention relates to a lateral guide (10) for guiding and / or securing cargo items, in particular containers and / or pallets, in an aircraft, comprising at least one lateral guide device (11) and at least one holding unit (12) for the lateral guide device (11), wherein the holding unit (12) comprises a longitudinally extending (v) mounting frame (13) and at least one locking device (14) arranged on the mounting frame (13), the locking device having a plurality of recesses (15) extending transversely to the longitudinal direction (v), wherein the lateral guide device (11) can be inserted into at least one of the recesses (15) at different positions (A, B, C, D, E) and can be locked in the inserted state at the different positions (A, B, C, D, E) by the locking device (14), wherein the lateral guide device (11) has at least one contact element (16).which, in the inserted state, can be brought into engagement with or is in engagement with at least one longitudinally displaceable fixing element (17) of the fixing device (14), wherein the fixing element (17) has at least one fixing contour (23) with which the fixing element (17) engages in a fixing position in the cross-sectional contour (22) of the opening (21) for fixing the side guide device (11) in a form-fitting manner, wherein the fixing contour (23) and the cross-sectional contour (22) are mushroom-shaped.

Shock-resistant chamber wall for use on a ship comprising a wall panel extending vertically between an upper and a lower deck with flat wall sides oriented perpendicular to the decks, a floor profile with a vertical leg and a horizontal leg, which is firmly connected to a lower deck, wherein the wall panel is firmly connected to the vertical leg of the floor profile, means for vertical guidance which are connected to an upper deck and guide the wall panel, a shock-absorbing insert which is arranged between the wall panel and the upper deck.

The utility model belongs to the technical field of machine manufacturing, and relates to a floor seat nest protection device. The device is formed by combining a first protection piece and a second protection piece, the upper end face of the first protection piece is of a square or circular structure, and a first plug is arranged on the lower end face of the first protection piece; the upper end face of the second protection piece is of a circular arc and square combined structure, and a second plug is arranged on the lower end face. And the first plug and the second plug are respectively matched with seat nests at corresponding positions on the machine body in a plugging manner. The seat pit can be effectively protected, the protection piece has the advantages of being light in weight and low in material and machining cost, the maintenance period can be shortened, and cost is reduced.

An aircraft (10, 10") has an aft main cargo cabin (50) with a low deck floor (52), and a rear access (60) configured to provide access to the aft main cargo cabin from behind the fuselage (20). The deck floor of the aft main cargo cabin is lower than a first deck floor (32) of a forward main cabin (30) of a forward section of the fuselage. The aft main cargo cabin has a second height (H2) that is greater than the first height (H1) of the forward main cabin, allowing the aft main cargo cabin to accommodate oversize cargo with larger dimension(s). The aircraft may be built with such an aft main cargo cabin and rear access, or may be a modified aircraft that includes such an aft main cargo cabin and rear access. Related methods of reconfiguring a base aircraft into a modified aircraft having such an aft main cargo cabin and rear access are also disclosed.

A profile rail for a floor of a vehicle has a base made of a first material and a top portion exposed during use of the profile rail in the floor of the vehicle. The top portion has a cold sprayed coating of a second material that is at least one of harder, more wear-resistant, or less corrosive as the first material. The top portion has a seat rail crown having a first hook element produced entirely from the second material.

The unfaired aeronautical propulsion system comprises a propeller extending around a main axis and having at least one variable-pitch rotor blade around a rotor pitch axis. For each variable-pitch rotor blade, the relative position of maximum thickness (x°_EPmax) decreases from a first relative height (R1) between 20% and 40% to a second relative height (R2) between 55% and 100%, where the relative position of maximum thickness (x°_EPmax) is between 15% and 35%, preferably between 20% and 30%. (See Figure 5 for abbreviations.)

(DE) The present invention relates to a transport drone with a main body having a wing at its upper part and a transport compartment at its lower part, through which a transport object, for example a car, can be inserted and removed forwards and backwards; and a buoyancy element with several tubes connected to the lower part of the main body and which are inflatable and deflatable by means of air pressure. In this configuration, the tubes, which expand and contract by means of air pressure, are connected along the lower perimeter of the main body. By means of the sequential expansion and contraction of the tubes, the drone can not only land on the water surface by means of the buoyancy force, but also, if it tips over on the water surface, hover above the water surface by means of the sequential expansion and contraction of the tubes, thus preventing it from falling into the water.

The present invention makes it possible for various flying devices to land.　A takeoff / landing device (91) for a flying device (3) comprises a first support part (92A) that can support at least a portion of the flying device (3) and a second support part (92B) that can support at least a portion of the flying device (3) and, with the first support part (92A), is to support the flying device (3) to allow the flying device (3) to take off and land. The first support part (92A) and the second support part (92B) are separated in the horizontal direction, and the space between the first support part (92A) and the second support part (92B) is unobstructed in the vertical direction.

A floor module for a power generation system may comprise: a housing (222) including a flexible top plate (236); a plurality of generator assemblies (240) disposed within the housing, each generator in the plurality of generator assemblies comprising: a moveable portion (420) disposed adjacent to the flexible top plate, the moveable portion including a shaft (426) extending away from the flexible top late; and a piezoelectric transducer (450) aligned with the shaft, the piezoelectric transducer configured to compress in response to the moveable portion translating toward the piezoelectric transducer from a force on the flexible top plate.

A nose landing gear assembly for an aircraft. A nose landing gear assembly includes a hydraulic strut, a front strut including a front strut first end and a front strut second end. The front strut first end is pivotably coupled to a nose gear bay of a high wing aircraft about a first pivot axis. The assembly also includes a rear strut including a rear strut first end and a rear strut second end. The rear strut first end is pivotably coupled to the nose gear bay about a second pivot axis and the rear strut second end is pivotably coupled to the hydraulic strut. An actuator includes an actuator first end and an actuator second end. The actuator second end is coupled to the nose gear bay and the actuator first end is coupled to the front strut. The actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.

An auxiliary guide assembly is disclosed. The auxiliary guide assembly including a head (212) including a guiding surface (208A, 208B) and an overriding surface, a pinion (218), a hub (214) configured to receive the pinion, a union unit (216) configured to secure the pinion to the hub, the union unit rotationally coupled to the pinion and the head, a solenoid (220) coupled to the hub, the solenoid configured to receive a first electric polarity, a reciprocating rod (222) disposed through the solenoid, the reciprocating rod having a first rod end including a rack (224) operatively coupled to the pinion, and an armature (230) adjacent the solenoid and configured to engage the reciprocating rod, the armature moves in a first direction in response to the solenoid receiving the first electric polarity, the armature moving the reciprocating rod in the first direction, and the head rotates in a second direction in response to the reciprocating rod moving in the first direction.

A rail system for a compartment of a vehicle, the rail system comprising: a rail with a main extension direction, fixing elements capable of being fixed at different positions on the rail for holding mounting elements on the rail, and a covering device for covering the rail. The covering device has a plurality of flat, row-aligned covering elements extending along the rail, wherein the covering elements are respectively mounted to pivot between a closed state and an open state, wherein in the closed state, the respective covering element is placed on the rail; and in the open state, the respective covering element is removed from the rail, and wherein the fixing element has an engaging element designed to fall under the covering element and move the covering element from the closed state to the open state when the fixing element is moved along the rail.

To provide a technique relating to stanchions for supporting a floor system in an aircraft.SOLUTION: A stanchion 34 for an aircraft includes a first composite body defining a first channel 50A having a first web extending between a first pair of spaced apart flanges. The first composite body also includes a first multitude of longitudinal segments each having a ply count that varies between adjacent longitudinal segments of the first multitude of longitudinal segments. The stanchion also includes a second composite body defining a second channel 50B having a second web extending between a second pair of flanges. The second composite body also includes a second multitude of longitudinal segments each having a ply count that varies between adjacent longitudinal segments of the second plurality of longitudinal segments with the first composite body being fixed relative to the second composite body.SELECTED DRAWING: Figure 2

The present invention relates to a drone for transportation, comprising: a main body having a wing part formed at the upper part thereof and a transportation space formed at the lower part thereof in a penetrating manner such that a vehicle-like object to be transported can enter and exit in the front-rear direction; and a buoyancy part coupled to the lower end of the main body, the buoyancy part having a plurality of tube bodies coupled thereto, the tube bodies being expanded and contracted by air pressure. According to the structure, in addition, expansion and contraction pipe bodies driven by air pressure are combined on the periphery of the lower portion of the main body, the pipe bodies conduct expansion and contraction movement in sequence, the ship can stably float on the water surface by means of buoyancy, when the ship overturns, the pipe bodies can expand and contract in sequence, and therefore the ship automatically floats upwards and breaks away from the water surface, and the water immersion accident is effectively avoided.

The invention relates to a quick coupling system (10) for fastening and / or converting a component of an aircraft cargo hold (100), in particular a cargo system component (101) and / or a cover (102), on at least one structural part (103) of an aircraft structure (104), comprising: - at least one fastening journal (11) which is mountable on the structural part (103) and has a journal longitudinal axis (LA), - at least one connection region (12) which is arranged or configured on the component and has at least one through-opening (13), the fastening journal (11) being at least section-wise accommodatable or accommodated in the through-opening in the journal longitudinal axis direction and / or transversely to the journal longitudinal axis (LA) with formation of a first form fit, and - at least one locking mechanism (14) which is arranged on the component and has at least one engagement element (15a-c), the engagement element being movably supported on the component in such a way that, by means of a translational or rotational movement of the engagement element (15a-c), a second form fit can be formed or is formed with the fastening journal (11), the structural part (103) or a counterpart (16) which is mountable on the structural part (103), the second form fit preventing a movement of the component in the journal longitudinal axis direction and / or transversely to the journal longitudinal axis (LA).

A system includes a freight carrier, front catch element and rear catch element, the front edge of the base element of the freight carrier having front engagement elements, and the rear edge has rear engagement elements. The front catch element has front floor engagement devices to engage locking elements so movement of the front catch element in the floor surface plane and perpendicular thereto is prevented. The front catch element has front engagement devices to engage the front engagement elements. The rear catch element has rear floor engagement devices to engage locking elements in rails so movement of the rear catch element in the floor surface plane and perpendicularly thereto is prevented. The rear catch element has rear engagement devices to engage the rear engagement elements so movement of the rear catch element relative to the base element parallel to the plane of the supporting surface and perpendicular to the plane towards the supporting surface is prevented.

A floor crossbeam structure is positioned at a connection of a pressure floor and a pressure end frame of an aircraft, the floor crossbeam structure comprising a first profile member and a second profile member, which are configured in a structure that abuts a stringer of the pressure floor and a post of the pressure end frame, a connecting angle member having an inner side and an outer side, the outer side fixedly engaging the first profile member and the second profile member, and a plurality of corner boxes fixedly mounted in the inner side of the connecting angle member.

The invention relates to the technical field of general aircrafts, in particular to a detachable floor structure for an airplane belly opening. According to the technical scheme, the detachable floor structure for the airplane belly opening comprises a left side floor and a right side floor which form a main body floor of an airplane belly; the left side opening floor is arranged on the inner side of the left side floor and used for forming a machine belly opening; the frame is arranged around the opening and is used for supporting the edge of the opening; the at least one open framework cross beam and the at least one open framework longitudinal beam are erected on the framework and form a main bearing framework in an open area; and the adjustable connecting plate is connected between the left open floor and the open framework longitudinal beam or the frame and is used for finely adjusting the mounting position of the left open floor. The floor with the opening in the left side can be quickly disassembled and assembled, approaching and maintenance of equipment in the machine belly opening are greatly facilitated, and the working efficiency is improved.