1091results about "Fuselage frames" patented technology

A craft is provided comprising: a propulsion system; a fuselage coupled with the propulsion system, wherein the fuselage is configured to carry a payload and fuel for the propulsion system; and a pre-assembled wing coupled with the fuselage; wherein the craft is designed to take-off without using a runway and does not have landing gear to land.

The invention discloses a distributed electric propulsion box type wing ground effect aircraft which comprises a main fuselage, the two sides of the main fuselage are connected with one ends of sweepback wing main wings, one ends of two empennages above the tail of the main fuselage are connected with the main fuselage through vertical tails, and the other ends of the two empennages are connected with the other ends of the two main wings through end plates respectively. The empennage is connected with a plurality of high ducted fans directly driven by a motor, an elevator and an aileron are arranged at the rear part of the empennage, a rudder is arranged at the rear part of the vertical fin, and the elevator, the aileron and the rudder are controlled by a flight control system and are mutually independent. The ground-effect aircraft provided by the invention adopts a box-type wing structure formed by combining the sweepback main wing and the sweepforward empennage, has better aerodynamic performance in a take-off and climbing low-speed flight state, and can provide larger lift force and better maneuvering characteristics.

An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The first wing can be coupled to the boom by a (first) articulated joint. The propulsion assembly can be coupled to the boom by a (second) articulated joint. The articulated joints can provide various adjustments between the wing(s) and the boom (e.g., stowed, deployed, anhedral, dihedral, sweep, angle of attack, collective pitch control, the cyclic pitch control, etc.) and between the propulsion system and the boom (e.g., to move between vertical flight and horizontal flight). A payload can be connected to the boom with one of the articulated joints whereby the articulated joint adjusts a position of the payload during flight to maintain desired flight characteristics and stabilize the payload.

The present application discloses an aircraft. The aircraft comprises a first wing and a second wing, a fuselage to which the first wing and the second wing are mounted, a first engine operatively mounted to the first wing, and a second engine operatively mounted to the second wing. The aircraft is configured to vertically take-off and land. The first engine and the second engine are used for both (i) vertical take-off and landing, and (ii) horizontal flight.

An aircraft, such as a rotorcraft, may have at least one area designated to house at least one fuel cell and at least one aircraft structure that may translate, during a drop impact of the aircraft, into the area designated to house the fuel cell. At least one shaped fuel cell may be provided and deployed therein, in accordance with the present systems and methods. Each respective shaped fuel cell may define at least one respective through-voids defined through the respective shaped fuel cell, and / or at least one respective edge cavity defined along an edge of the shaped fuel cell, wherein the respective through-void and / or the respective edge cavity correspond to the respective aircraft structure that may translate, during the drop impact of the aircraft, into the area of the aircraft designated to house the respective fuel cell to receive and accommodate the respective structure during the drop impact.

The invention provides an aircraft framework and an aircraft, the aircraft framework is used for the aircraft flying in the atmosphere, the aircraft framework comprises a cage serving as a framework main body, the cage bears the self weight and the flight load of the whole aircraft, at least two first turbojet engines can be contained in the cage, and the first turbojet engines are arranged in the cage; the cage is open at least in the lower portion and used for allowing the jet flow of the first turbojet engine to pass through. Through the arrangement of the cage which is a skeleton main body, a power source device of the aircraft is collected and gathered, so that the miniaturization of the whole aircraft is realized.

The invention discloses a serial helicopter cockpit with a variable configuration. A front cabin and a rear cabin are sequentially arranged from front to back to form a serial structure; the rear cabin floor is erected and installed through a rear cabin structural framework and a rear cabin wall plate in the rear cabin windshield assembly, so that the height of the rear cabin floor is adjusted, and the rear cabin floor is higher than the front cabin floor. The front cabin windshield assembly, the front cabin instrument assembly and the rear cabin instrument assembly are adjustable in the height direction and the heading direction, the rear cabin floor and the rear cabin windshield assembly are adjustable in the height direction, and the front cabin seat and the rear cabin seat are adjustable in the height direction and the heading direction. Control boards and control lever systems in the front cabin control assembly and the rear cabin control assembly are adjustable; by adjusting the height, front-back position or roll angle of each component in the tandem helicopter cockpit, the tandem helicopter cockpit is placed in a to-be-assessed configuration for implementation of assessment. According to the method, the problem that instance evaluation and onboard verification are difficult to perform on the appearance of the cockpit and the arrangement of cockpit equipment at the initial stage of design is solved.

A fixed-wing cargo aircraft having a fuselage wing cutout supported by box beam longerons is disclosed. The fuselage contains a continuous interior cargo bay, and includes a forward portion, an aft portion, and a cutout defined by a plurality of structural elements configured to transfer a wing load to the fuselage, the structural elements including opposite starboard and port longeron beams each spanning a longitudinal length of the cutout. The starboard and port longeron beams have an enclosed box beam construction, which can include a plurality of panel sections, at least one of the plurality of panel sections comprising a skin panel of the fuselage. The cutout can have forward and aft frame beams each having an enclosed box beam construction that form a structural perimeter of the cutout with the starboard and port longeron beams.

The invention belongs to the technical field of anti-impact design of aviation structures, and particularly relates to an anti-falling and anti-collision fuselage lower energy absorption structure. According to the structure, the cross section of a machine body frame is arc-shaped; two ends of the cabin floor beam are connected with the fuselage frame; the fuselage lower cross beam is arranged below the passenger cabin floor cross beam in parallel, the two ends of the fuselage lower cross beam are connected with the fuselage frame, and a containing space is formed between the fuselage lower cross beam and the passenger cabin floor cross beam. The two fuselage lower part inclined struts are symmetrically arranged, each fuselage lower part inclined strut comprises a first inclined strut section and a second inclined strut section, the end part of each first inclined strut section is connected with the fuselage frame, and the end part of each second inclined strut section is connected with the fuselage lower part cross beam; the first inclined strut section, the second inclined strut section, the fuselage lower cross beam and the fuselage frame jointly form a parallelogram-like structure; the upper ends of the fuselage lower stand columns are connected with the passenger cabin floor cross beam, and the lower ends of the fuselage lower stand columns are connected with the fuselage lower inclined struts. The falling collision load peak value can be reduced.

The invention discloses a mounting method of a passenger plane decorating plate, a mounting structure of the decorating plate comprises a sheet-shaped decorating plate with a rounded L-shaped section, a structural plate of a ceiling and a guide rail of a hanging bracket, the inner side of the upper end of the decorating plate is fixedly connected with a connecting block, the connecting block is fixedly connected with a plug pin, the structural plate is provided with a snap spring seat, and the snap spring seat is fixedly connected with the plug pin. Hooks are arranged on the inner side of the lower end of the decorative plate. Hook grooves are formed in the lower ends of the guide rails. The installation method comprises the following steps that S1, hooks of the decorative plate are clamped into hook grooves in the lower ends of the guide rails; s2, enabling the plug pin to be aligned with a clamp spring seat on the structural plate; s3, the plug pin is inserted into the clamp spring seat to complete insertion and fixation; and S4, rubber strips are installed in the hook grooves. The decorative plate can be mounted and dismounted without using tools, so that the working efficiency is improved.

The invention relates to a self-adaptive energy-absorbing conformal head cap of an air-water cross-medium aircraft, which is mainly applied to aircrafts capable of switching motion between two media of air and water. The head cap comprises a top cover, a skin combination, an energy absorption mechanism, a shape preserving mechanism and a modular adaptive interface, wherein the skin combination comprises an outer-layer skin and an inner-layer skin; the energy absorption mechanism is arranged in the inner-layer skin; the conformal structure is arranged between the inner-layer skin and the outer-layer skin; the modular adaptive interface comprises a base and a switching section, the base is connected with one end of the inner-layer skin, and the switching section is connected with the aircraft body; and the top cover is connected with the other end of the inner-layer skin. Stable hydrodynamic performance and low underwater resistance can be provided under different water entry speeds and angles, head appearance damage caused in the deformation process of a traditional energy absorption structure is effectively avoided, and the key technical problems in design of the air-water cross-medium aircraft are solved.

A connector for truss work members to a support structure for a mounting interface of a trusswork. The connector has a body with a first portion and a second portion. A central opening is provided in the body having an inner wall configured for receiving a connection end of a truss member. The first portion and the second portion are arranged concentrically. The first portion has first circumferential edge sections, and the second portion has second circumferential edge sections. The first and second circumferential edge sections are spaced apart by gap sections that are configured to receive connecting flanges of a support structure. The gap sections are forming segments along a virtual surface that is curved at least in one direction.

An unmanned aerial vehicle according to certain embodiments generally includes a chassis, a power supply mounted to the chassis, a control system operable to receive power from the power supply, at least one rotor operable to generate lift under control of the control system, and a winch mounted to the chassis. The winch includes a reel and a motor. The reel has a line wound thereon, the line having a free end. The reel includes a circumferential channel in which a wound portion of the line is wound onto the reel. The circumferential channel includes an inner portion, an outer portion, and a passage connecting the inner portion and the outer portion. The motor is operable to rotate the reel under control of the control system to thereby cause the line to wind onto and off of the reel, thereby causing the free end of the line to raise and lower.

A frame assembly for unmanned aerial vehicle comprising: at least two parallel first frame members, a second frame member orthogonal to the first frame member, and a fixing member fixed to each of the first and second frame members.

A blended wing body (BWB) aircraft comprising a first composite part comprising, a first dry carbon fiber sheet having a width greater than 3 inches and comprising a first layer comprising dry carbon fibers, a second layer disposed on top of the first layer comprising dry carbon fibers, a stitching extending through the first dry carbon fiber sheet, wherein the stitching is configured to bind the first dry carbon fiber sheet together, and a resin matrix, wherein the stitching and the first dry carbon fiber sheet are embedded within the resin matrix to create a single unified structure. BWB aircraft further comprises a blended wing body, having no clear demarcation along a leading edge of the BWB aircraft from a wing to a nose of the blended wing body, and wherein the first composite part comprises a portion of the blended wing body.

The utility model belongs to the technical field of flexible structure design, and particularly relates to a perimeter-variable fuselage frame structure which comprises sliding groove sections, sliding key sections, corrugated beams, height-variable supporting columns and length-variable supporting rods. The corrugated beams are arranged on the outer sides of the sliding key sections and the sliding groove sections and are provided with wave crest and wave trough structures; the sliding key sections and the sliding groove sections are located on the inner sides of the corrugated beams, arranged at intervals and distributed in a staggered mode. The corrugated beams, the sliding key sections and the sliding groove sections are all of arc-shaped structures, and wave crests and wave troughs of the corrugated beams are arranged in the radial direction of the arc-shaped structures; the sliding key section and the sliding groove section are mutually nested to form an arc-shaped supporting sliding way, and the wave trough of the corrugated beam slides on the arc-shaped supporting sliding way; the height-variable supporting column and the length-variable supporting rod are hinged to the two ends of the sliding key section respectively. The shape of the fuselage can be greatly changed, the large-size fuselage can provide a large space to carry more fuel, and the small-size fuselage is beneficial for reducing flight resistance and improving the fuel utilization rate.

The invention discloses an aircraft nose cone. The aircraft nose cone comprises a cone section, a first connecting part, a second connecting part and a movable part. The plurality of cone sections are connected in sequence to form a nose cone; a plurality of first connecting parts and a plurality of second connecting parts are arranged on every two adjacent cone sections at intervals in the circumferential direction of the cone sections, and the first connecting parts and the second connecting parts are in one-to-one correspondence; one end of the movable part is hinged with the first connecting part, and the other end of the movable part is connected with the second connecting part through a universal joint; wherein the movable part is suitable for deforming to drive the two adjacent cone sections to move relatively so as to drive the nose cone to deform. According to the aircraft nose cone, under the condition that the structure is simplified, the deformation stability and flexibility of the nose cone can be guaranteed, and any-angle deformation of the nose cone is achieved.

The invention belongs to the technical field of flexible structure design, and particularly relates to a variable-arc-length arched beam structure which comprises a sliding groove section, a sliding key section, a corrugated beam, a variable-height supporting column and a variable-length supporting rod. The corrugated beams are arranged on the outer sides of the sliding key sections and the sliding groove sections and are provided with wave crest and wave trough structures; the sliding key sections and the sliding groove sections are located on the inner sides of the corrugated beams, arranged at intervals and distributed in a staggered mode. The corrugated beams, the sliding key sections and the sliding groove sections are all of arc-shaped structures, and wave crests and wave troughs of the corrugated beams are arranged in the radial direction of the arc-shaped structures; when the shape and the arc length of the arched beam are changed, the variable-height supporting columns and the variable-length supporting rods can automatically generate height changes, then the sliding key sections and the sliding groove sections are driven to relatively slide, and meanwhile the corrugated beams evenly distribute the arc length changes to the positions between the adjacent wave crests, so that external loads are evenly distributed to the arched beam. Therefore, the size of the fuselage is correspondingly reduced along with fuel consumption.

The present disclosure provides a battery load support structure of a fuselage, the battery load support structure including a battery mount support formed in a longitudinal direction of a floor frame of the fuselage, a battery unit inputted into an opened lower side of the floor frame and fastened to the battery mount support, and a joint unit configured to support the battery mount support and connected to a plurality of framework members that constitutes the floor frame.

An aircraft that is certifiable for freighter transport is disclosed herein. The aircraft can include a hybrid fuselage including a plurality of modular sections, wherein the plurality of modular sections includes a first section, a second section, and an intermediate section, and wherein the intermediate section is disposed intermediate the first section and the second section. The aircraft can further include a plurality of systems traversing the plurality of modular sections and a plurality of structural components configured to mechanically couple the intermediate section to the first section and the second section of the plurality of modular sections. The first section and the second section are configured for use with a fuselage of a passenger aircraft, and wherein the intermediate section is configured for use with a fuselage of a freighter aircraft.

A crash load distribution structure of a fuselage, includes a floor frame defining a fuselage floor, a skid member fastened to the lower portion of the floor frame, and a crash box coupled to the skid member and extending to the lower portion of the floor frame, and configured to selectively deform in a crash load direction when an oblique crash occurs thereto.

The invention relates to the technical field of layered composite fabrics, in particular to a flame-retardant-fiber-based multilayer flame-retardant composite fabric for an aircraft cabin and a preparation method of the flame-retardant-fiber-based multilayer flame-retardant composite fabric. The preparation method comprises the following steps: reacting acrylic acid with DOPO to prepare modified DOPO; reacting the epoxy POSS with the modified DOPO to prepare a composite flame retardant; reacting the hydrophilic grafted polyamide with a composite flame retardant and amino-modified nano-montmorillonite to prepare modified polyamide; carrying out melt spinning and chopping on the modified polyamide to obtain flame-retardant fibers; the flame-retardant fibers are spun into flame-retardant yarns, then the flame-retardant yarns are spun into a fabric, and a surface fabric is obtained; the flame-retardant fibers and the polyester fibers are blended to obtain blended yarns, and then the blended yarns are spun into a fabric to obtain a bottom layer fabric; and compounding the surface layer fabric and the bottom layer fabric to obtain the composite fabric. The prepared composite fabric has excellent flame retardant property and antistatic property, and can be applied to aviation cabins.

The invention belongs to the field of composite material wallboard design, and provides a stiffened wallboard which comprises a first skin, a second skin and a connecting piece, a first stringer is arranged at the top of the first skin, a second stringer is arranged at the top of the second skin, the first skin is connected with the bottom of the second skin through the first stringer, and the second skin is connected with the connecting piece through the second stringer. The first stringers and the second stringers are distributed in a staggered mode, the connecting pieces are connected with the first skin through the first transverse connecting band plates or connected with the second skin through the second transverse connecting band plates, and connection of the first skin or the second skin is achieved. According to the scheme, the two connected wall plate layers are designed, so that larger out-of-plane loads can be borne in the thickness direction, and the structural stability is improved; and the stringers are distributed in a staggered manner, so that bearing force can be more uniformly distributed in a limited space, the stress caused by out-of-plane load is uniformly transmitted to the two wall plate layers, and the structural stability is further improved.

Disclosed is a fuselage 100, 100', 100" of or for an aircraft. The fuselage comprises a shell 10, at least one hydrogen tank 20, an energy absorbing structure 30 arranged between the shell 10 and the at least one hydrogen tank 20, and a support structure 40, 40' supporting at least a portion of the at least one hydrogen tank 20 within the shell 10. The support structure 40, 40' comprises an interstitial section 52, 54i located between the at least one hydrogen tank 20 and the energy absorbing structure 30. Furthermore, the support structure 40, 40' comprises a strut system 60 supporting the at least said portion of the one hydrogen tank 20 against the interstitial section 52. The support structure 40' may further brace at least said portion or at least a further portion of the at least one hydrogen tank 20, 20b in a roof section 100R of the fuselage, e.g. by means of one or various support elements 70'. Further disclosed is an aircraft comprising such fuselage 100, 100', 100".

A blended wing body (BWB) aircraft including a blended wing body having a main body and wings with no clear demarcation between the wings and the main body along leading edges of the BWB aircraft, a passenger cabin located within the main body and more than one passenger bays located within the passenger cabin, wherein a perimeter of at least one passenger bay is demarcated by at least a divider and wherein the at least one passenger bay is substantially parallel to at least one leading edge of the BWB aircraft.

A variable fuselage fuel tank structure of a high-speed aircraft comprises a fuselage fixing structure, an external flexible heat insulation skin and an internal skin bearing framework. The machine body fixing structure comprises a lower wall plate and an upper wall plate; the edges of the lower wall plate and the upper wall plate are connected, and the upper wall plate is provided with a fuel circulating hole; the outer flexible heat insulation skin is connected with the edge of the upper wall plate; the external flexible heat-insulating skin comprises a flexible fabric heat-proof outer layer and a microporous aerogel heat-insulating inner layer; the inner skin bearing framework is connected to the inner side of the outer flexible heat insulation skin and comprises reinforcing longitudinal beams, elastic elements and high-temperature-resistant rubber. The longitudinal beams are connected to the inner side of the outer flexible heat insulation skin in the longitudinal direction. A plurality of groups of elastic elements are respectively connected between two adjacent longitudinal beams, are distributed along the longitudinal direction, and are connected to the inner side of the external flexible heat insulation skin; and the high-temperature-resistant rubber is filled between the longitudinal beam and the elastic element, is filled in the elastic element and is adhered to the inner side of the external flexible heat-insulating skin.

The rotary locking type machine head comprises a machine body and a machine head body, a plurality of positioning grooves are formed in a partition frame of the machine body in an annular array mode, and each positioning groove is of an L-shaped structure and comprises an inlet part and a locking part; a positioning ring is arranged on the rear end face of the machine head, a plurality of positioning protruding blocks are arranged on the outer ring of the positioning ring in an annular array mode, the number of the positioning protruding blocks is the same as that of the positioning grooves, the positioning protruding blocks and the positioning grooves are in one-to-one correspondence, and the positioning protruding blocks are embedded into the positioning grooves and then rotate to be fixed. By arranging the positioning groove, the positioning ring and the positioning convex block, the machine body and the machine head can be quickly disassembled and assembled, and compared with traditional bolt connection, the machine is quicker, more reliable and more efficient, positioning is convenient, mounting can be conducted without the help of redundant tools, and the mounting cost is reduced.

The invention belongs to the technical field of aircraft structure design, and discloses a fuselage frame preparation process and a fuselage frame. According to the fuselage frame preparation process, preparation of the first woven preformed body and the second woven preformed body is achieved through the weaving operation of the weaving machine, the preparation efficiency and the structural integrity of the first woven preformed body and the second woven preformed body are improved, and the influence of manual operation on the fuselage frame forming quality is avoided. The preparation of the first weaving body and the second weaving body is realized by cutting operation of cutting guide parts arranged on the first weaving auxiliary core mold and the second weaving auxiliary core mold in advance, so that the preparation precision is guaranteed, and the forming quality of the fuselage frame is improved. The invention further provides the machine body frame, the machine body frame is prepared through the machine body frame preparation technology, the manual operation participation degree is reduced in the machine body frame preparation process, the influence of manual operation errors on the forming quality of the machine body frame is avoided, the forming quality and forming efficiency of the machine body frame are improved, and the manual labor intensity is relieved.

The present invention relates to a crash-load absorbing attachment fitting (1; 101; 201; 301; 401), comprising a first and second part (3, 6; 103, 106; 203, 206; 303, 306; 403, 406) that are joined to each other at a joint (10; 110; 210; 310; 410), the first and second parts being load-bearing parts. The joint is configured such that the joint is capable of transferring, during normal use of the crash-load absorbing attachment fitting, a load (F) which is below a pre-determined load-absorption activation threshold value between the first and second parts, and such that the joint breaks when the load reaches or exceeds the pre-determined load-absorption activation threshold value. The crash-load absorbing attachment fitting further comprises a destroyer device (15; 115; 215; 315; 415), wherein the destroyer device is rigidly connected to and / or rigidly supported by one of the first and second parts and wherein the destroyer device is arranged so as to be capable of destructively acting on the other one of the first and second parts after breaking of the joint. Moreover, the invention proposes an aircraft or spacecraft (91) comprising a tank for storing hydrogen, in particular liquefied hydrogen, and at least one such crash-load absorbing attachment fitting (1; 101; 201; 301; 401), the tank being attached to a structural member (78) of the aircraft or spacecraft using the crash-load absorbing attachment fitting.