206results about "Fuselage insulation" patented technology

The invention discloses a composite heat insulation coating structure and method for a high-temperature component of an unmanned aerial vehicle. The structure comprises a heat insulation base material layer made of a high silica glass fiber material and a reflecting layer made of metal foil, and the heat insulation base material layer and the reflecting layer are compounded into a whole. The reflecting layer is used for reflecting heat radiation, and the heat insulation base material layer is used for blocking heat conduction. The problems that a traditional ceramic fiber material is prone to embrittlement and short in service life in a high-temperature vibration environment are effectively solved through a double heat insulation mechanism of reflection-blocking. The coating structure has excellent heat-resistant cyclicity, good flexibility and process adaptability, can perfectly fit special-shaped structures such as a bulkhead and a tail cover of the unmanned aerial vehicle, and remarkably improves the reliability and prolongs the service life of a thermal management system of the unmanned aerial vehicle.

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.

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 invention relates to the technical field of layered products, and particularly discloses a heat-insulating and wave-absorbing skin material as well as a preparation method and application thereof. The heat-insulating and wave-absorbing skin material is of an integrated layered structure based on an aluminum oxide-mullite system, comprising a functional gradient layer with double gradients of fiber density and aperture, an impedance matching layer with a gradient dielectric constant, a resonance wave absorbing layer with a periodic dot matrix formed by silicon carbide and aluminum oxide core-shell microspheres, and a heat insulation layer with a nano-micron double-scale pore structure. According to the preparation method, a green body is constructed mainly through tape casting and silk-screen printing, and then co-sintering integrated forming is carried out. The material has the excellent characteristics of high temperature resistance, toughness, efficient heat insulation, broadband wave absorption and the like, and is suitable for extreme environments such as hypersonic aircraft skin and the like.

Thermal barrier curtain systems include a thermal barrier curtain and port and starboard anchor / hoist strap assemblies. The thermal barrier curtain includes forward and aft flexible air-impervious panels which are sealed about peripheral edges thereof so as to define a central thermal barrier region and separator elements positioned between and attached to the forward and aft panels within the central thermal barrier region so as to define a dead air space therebetween. Each of the port and starboard anchor / hoist strap assemblies includes an elongate strap, upper and lower attachment members positioned at opposed upper and lower ends of the elongate strap, an upper attachment loop adapted to receive and be attached to a respective connection element of the thermal barrier curtain, and an intermediate retaining loop which is adapted to receive and be attached to the lower attachment member of the anchor / hoist assembly.

A heat shield for protecting a part of an aircraft is disclosed including superposed layers providing thermal protection, and one or more layers providing fire protection. The heat shield also may include other layers implementing other functions.

An actively-cooled heat shield system includes a heat shield, a tank, a pump, a heat exchanger, and a turbine. The heat shield defines a windward side of a vehicle. The tank stores a coolant. The pump receives the coolant from the tank and outputs a pressurized coolant. The heat exchanger is integrally connected with the heat shield. The heat exchanger receives the pressurized coolant from the pump, transfers heat from the heat shield to the pressurized coolant to generate a heated fluid, and outputs the heated fluid. The turbine includes an inlet, a shaft, and an outlet. The inlet receives the heated fluid output from the heat exchanger. The shaft is coupled to the pump and includes turbine blades. The shaft rotates and powers the pump when the heated fluid received from the heat exchanger acts on the turbine blades. The outlet outputs the heated fluid.

The application discloses an aircraft cargo hold bottom structure. The aircraft cargo hold bottom structure comprises a machine body, a floor, a heat insulation layer and a connecting piece. The floor is located in the machine body and connected with the machine body, and the floor and the machine body enclose a first cabin. The heat insulation layer is located in the first cabin and connected with the floor through the connecting piece and is spaced apart from the machine body, so that the heat insulation layer is not directly attached to the machine body, the heat insulation layer can avoid absorbing water on the machine body, thereby slowing down aging of the heat insulation layer, and water on the machine body can be normally evaporated and removed, the machine body can be prevented from being in a humid state frequently, and thus corrosion of the machine body is reduced.

The invention relates to a sound-absorbing structure comprising a honeycomb structure (52) which includes at least one cell (60, 60') delimited by at least one wall (58') and at least one partitioning system (62). The latter comprises at least one subassembly (64, 64') positioned within the cell (60, 60') and designed to divide it into at least two cavities, as well as at least one tab (78, 78') connected to the subassembly (64, 64') and having a hook shape (84) positioned astride one of the first and second end edges (58.1', 58.2') of the wall (58'). This tab (78, 78') facilitates the placement of each partitioning system (62) and its retention within the cell (60, 60'). The invention also relates to an aircraft comprising at least one such structure and a method for assembling such a structure.

The invention provides an aircraft composite heat insulation plate based on welding forming, a flap lower wall plate and an assembling method, and the aircraft composite heat insulation plate based on welding forming comprises an upper frame and a lower frame which are sequentially stacked to form a frame assembly; the outer edge of the outer skin and the frame assembly are aligned and stacked, the lower surface of the outer skin abuts against the lower frame, and the upper frame, the lower frame and the outer skin are formed at a time in a welding mode; the aerogel layer is arranged on the lower surface of the outer skin and located in the frame assembly. The invention has the beneficial effects that the nano porous structure of the aerogel limits the motion of gas molecules and reduces convective heat transfer, and the complex nano skeleton increases the heat conduction path, improves the heat radiation absorption, reduces the solid heat conduction and radiative heat transfer, and can tolerate the high temperature of 650 DEG C in the jet flow area of an engine.

A shielded, multi-layer heatshield material for hypersonic flight applications includes an ablative / insulative structure having a thickness and providing both thermal insulation and a first ablation resistance, and a separate shield layer bound to an outer surface of the ablative / insulative structure, the shield layer being thinner than the ablative / insulative structure while providing a second higher ablation resistance greater than the first ablation resistance. In one arrangement the ablative / insulative structure includes a carbon / carbon composite layer attached to a syntactic carbon foam layer, using carbon fiber stitched loops for reinforcement, and the shield layer is a carbide outer layer. In another arrangement the ablative / insulative structure includes a silica composite layer attached to a silica insulative foam layer, using stitched loops for reinforcement, and the shield layer is a ceramic outer layer.

The invention relates to a sound absorption structure and an aircraft. The sound absorbing structure comprises at least one honeycomb structure (52) comprising at least one partition enclosure (62) fixed in one of the cells (60) of the honeycomb structure (52) and connected to at least one partition (58) delimiting said cell (60), the partition enclosure (62) separates an inner region (ZI) located inside the partition enclosure (62) from an outer region (ZE) located in the unit (60) and outside the partition enclosure (62), the partition enclosure (62) comprising at least one through-hole (70) configured to communicate the inner region (ZI) with the outer region (ZE). This configuration makes it possible to simply define several regions in the same cell, thereby helping to increase the spectrum of attenuating acoustic waves. The aircraft comprises at least one such sound absorbing structure.

The invention discloses an aerogel heat insulation pad with a heat conduction layer and a preparation method of the aerogel heat insulation pad. The heat insulation pad is formed by clamping a heat conduction layer between two aerogel layers, and the heat conduction layer can disperse heat to the whole plane from a local concentration point and dissipate the heat to the air through the aerogel layers. By optimizing the material and structural design of the heat conduction layer, the heat dissipation and soaking capacity of the aerogel layer in the cross section direction is remarkably improved, and meanwhile the heat insulation performance of aerogel is reserved. The heat insulation pad has excellent heat management performance and is suitable for the fields of electronic equipment heat dissipation, aerospace heat management, building heat preservation and the like.

The subject matter of the invention is an acoustic absorption structure comprising a unit structure interposed between an acoustic resistive layer and a reflective layer, the unit structure comprising walls delimiting cells, and for at least one cell, the unit structure comprising: at least one and at most three L-shaped partitions, the at least one and at most three L-shaped partitions are impermeable and spaced apart from each other, and define a straight compartment and at least one L-shaped compartment; and an angled, acoustically resistive porous separator in each L-shaped compartment, the angled, acoustically resistive porous separator having a perforation rate of less than or equal to 15%, and dividing the L-shaped compartment into a first region and a second region, thereby forming two types of resonators. This arrangement makes it possible to increase the frequency range of the processed acoustic waves. Another subject of the invention is an aircraft comprising at least one such sound absorbing structure.

An acoustic absorption structure including a cellular structure which comprises tubular cells, closed at each of their ends by an acoustically resistive layer and a reflective layer, and at least one individual partitioning system, placed in a single cell and including a partition configured to separate the cell into first and second compartments, at least one opening passing through the partition, several feet independent of the conduit, having a first end connected to the partition and a second end in contact against the reflective layer, and at least one conduit which has a first end rigidly secured to the partition surrounding the opening and a second end spaced apart from the reflective layer.

A thermal insulation system for an aerospace duct through which high temperature fluid, greater than 500 F, passes. The thermal insulation system can experience pressures less than 80 kilopascals and can be included in a turbine engine. The thermal insulation system includes at least a first foil layer confronting the duct, an insulation layer confronting the first foil layer, a second foil layer confronting the insulation layer, and at least one coating applied to any one of the layers.

Provided is a double-side fixing assembly which can hold heat insulation and sound insulation materials and the like on the two sides of a frame and the like of an aircraft respectively, can reduce assembling and disassembling resistance and can restrain damage during disassembling. The fixing nail is provided with a positioning blocking piece, a clamping tongue piece, a first conical tooth and a second conical tooth, the first conical tooth is located on one side of the positioning blocking piece, the outer diameter is smaller when the first conical tooth is closer to one side, the clamping tongue piece is located on the other side of the positioning blocking piece and can elastically deform in the radial direction, and the clamping tongue piece is located between the first conical tooth and the second conical tooth from the other side to one side; the second conical tooth is located on the other side of the clamping tongue piece, and the outer diameter of the second conical tooth is smaller when the second conical tooth is closer to the other side of the clamping tongue piece; the first gasket is provided with a first pawl part which is provided with a first pawl and can elastically deform in the radial direction to enable the first pawl to be clamped with or separated from the axial end face of the first bevel gear; and the second gasket is provided with a second pawl part which is provided with a second pawl and can elastically deform in the radial direction to enable the second pawl to be clamped with or separated from the axial end face of the second bevel gear.

A swirl recovery vane with acoustic treatment including a leading edge and a trailing edge opposite chordwise from the leading edge; an attachment region opposite spanwise from a tip region; a span dimension extending between the attachment region and the tip region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the swirl recovery vane; an acoustic zone integrally formed within the swirl recovery vane. A gas turbine engine includes the swirl recovery vane with acoustic treatment. A process forms the swirl recovery vane with acoustic treatment.

A combined support comprises a mounting base which is provided with a seat part and a rod body protruding from the seat part; the gasket is detachably arranged on the rod body in a sleeving manner, so that the gasket and the seat part can clamp a plate-shaped piece; and a wire harness support which is detachably provided on a side of the rod body opposite to the seat portion with respect to the gasket, and in which a through portion through which a wire harness passes is formed. Therefore, the plate-shaped member and the wire harness can be installed at the same time.

The application provides a flexible sweating cooling composite material and a preparation method and application thereof, and belongs to the technical field of active thermal protection. The flexible sweating cooling composite material comprises, from outside to inside, a sweating function layer, a working medium conveying layer and an elastic substrate layer. The sweating function layer is a composite material comprising a flexible porous material and a hydrogel. The flexible sweating cooling composite material can realize macroscopic and microscopic double precise controllable distribution of the cooling working medium, improve the uniformity of the cooling working medium, has higher cooling efficiency, and meanwhile, each function layer is a flexible material, can be stretched and deformed, and has a thin thickness, good covering effect, can be attached to the surface of each part of an aircraft, good sealing performance, and can adapt to the complex surface requirements of different aircraft surface parts.

The invention provides a heat prevention and insulation structure of an aircraft base body and the aircraft base body, and belongs to the technical field of aircraft heat prevention and insulation. The heat insulation structure comprises a flexible connecting layer covering the surface of the aircraft base body; the heat insulation units are located on the flexible connecting layer, the first ends of the heat insulation units are connected with the flexible connecting layer, and the heat insulation units are arranged at intervals; the plurality of armor flakes are positioned on the heat insulation units and are in one-to-one correspondence with the plurality of heat insulation units, and the second ends of the heat insulation units are connected with the armor flakes; the reflecting coating covers the upper surfaces and the side surfaces of the armor flakes; the armor flakes on the adjacent heat insulation units are partially overlapped in a one-by-one pressing mode, and the tail portion of the front armor flake in every two adjacent armor flakes is in lap joint with the head portion of the rear armor flake, so that a stacked structure of the flakes is formed. According to the heat prevention and insulation structure, a labyrinth type heat flow transfer path is constructed, heat resistance is increased, and heat insulation efficiency is improved.

The invention relates to an acoustic absorption structure comprising a honeycomb structure (62), interposed between an acoustically resistive layer (64) and a reflective layer (66), which includes walls (68) delimiting cells (70) and, for at least one cell (70),: - at least one and at most three L-shaped partitions (72, 72'), impermeable and spaced apart, which delimit a straight compartment (70.1) and at least one L-shaped compartment (70.2, 70.3), - in each L-shaped compartment (70.2, 70.3), an inclined acoustically resistive porous partition (80, 80') which has an openness ratio less than or equal to 15% and divides the L-shaped compartment (70.2, 70.3) into first and second zones (80.1, 80.2, 80.1', 80.2'). forming two types of resonators. This arrangement makes it possible to increase the frequency range of the processed acoustic waves. The invention also relates to an aircraft comprising at least one such acoustic absorption structure.

An acoustic absorption structure including a cellular structure that includes at least one cell delimited by at least one wall and at least one partition system. The system includes at least one subsystem positioned in the cell and adapted to divide it into at least two cavities and at least one tongue connected to the subsystem and having a hook shape straddling one of the first and second edges of the wall. The tongue facilitates installing and retaining each partition system in the cell.

The application relates to the technical field of fairings and thermal protection of hypersonic aircraft, in particular to an aircraft antenna cover connecting structure. The aircraft antenna cover connecting structure comprises an antenna cover, nuts and heat insulation screws corresponding to the nuts. The antenna cover comprises a connecting end for connecting with a rear cabin section. An inner wall of the connecting end is circumferentially spaced apart with at least three nut holes. A bolt hole in communication with the nut holes is further arranged in the connecting end. The nuts corresponding to the nut holes are arranged in the nut holes. The heat insulation screws corresponding to the nuts are arranged to pass through connecting holes on the rear cabin section and bolt holes on the connecting end to connect with the nuts, so as to connect the rear cabin section and the connecting end. The application can solve the problem that the adhesives in the prior art have the risk of falling off even if the temperature of the adhesives is improved.

To reduce a drive sound transmitted to a cabin from a drive source.SOLUTION: An aircraft 10, which comprises a cabin 24 for being boarded by a crew member and a drive source 34 for being driven by using supplied fuel FL, includes a tank unit 28 that is arranged between the cabin 24 and the drive source 34 and in which a plurality of fuel tanks 40 for storing the fuel FL are stacked.SELECTED DRAWING: Figure 2

The application belongs to the field of acoustics, and discloses a low-frequency and wide-band noise reduction acoustic structure and a design method of the acoustic structure. The acoustic structure comprises a plurality of acoustic structural members and an embedded member. At least one embedded member is arranged in the plurality of acoustic structural members. On the same embedded member, the acoustic structural members in communication with the two open ends of the embedded member are arranged in pairs and jointly form a first unit. The acoustic structural member not in communication with the embedded member is a second unit. The first unit and the second unit are arranged in parallel. Compared with the prior art, when sound waves pass through the acoustic structural members arranged in pairs, the coupling resonance generated in the acoustic structural members can widen the noise reduction frequency band at a certain resonance frequency in the low-frequency range. The added embedded member can generate a new noise reduction frequency band. The weak coupling effect between the parallel units can further widen the noise reduction frequency band. Finally, the low-frequency and wide-band noise reduction effect is achieved.

The invention relates to a sound-absorbing structure comprising a honeycomb structure (32) which includes tubular cells (40), sealed at each end by an acoustically resistive layer (34) and a reflective layer (36), and at least one individual partitioning system (42), positioned within a single cell (40) and comprising: - a partition (44) configured to separate the cell (40) into first and second compartments (40.1, 40.2), - at least one orifice (46) passing through the partition (44), - several feet (48) independent of the conduit (54), which has a first end (48.1) connected to the partition (44) and a second end (48.2) in contact with the reflective layer (36), - at least one conduit (54) which has a first end (54.1) integral with the partition (44) surrounding the orifice (46) and a second end (54.2) spaced from the reflective layer (36).

- Aircraft part comprising an access door and a fuselage part forming a cavity, configured to reduce noise generated by the cavity. - The aircraft part (1) comprising a door (2) for access to the interior of the aircraft and a fuselage part (3) is provided with a cavity (6) formed between an upstream edge (8) of the door (2) in the closed position and a downstream edge (9) of the fuselage part (3), the cavity (6) opening outwards from the aircraft part (1) and comprising a bottom (10) connected to the upstream edge (8) of the door (2) and to the downstream edge (9) of the fuselage part (3), the aircraft part (1) comprising a chamfer (17) on the external face (14B) of an external plate (14) of the door (2) to the upstream edge (8) of the door (2), as well as possibly other technical features such as a sharp edge (18) and / or an added part (25), allowing to reduce the noise generated by the cavity (6).

A swirl recovery vane with structurally capable acoustic treatment includes a leading edge and a trailing edge opposite chordwise from the leading edge; an attachment region opposite spanwise from a tip region; a span dimension extending between the attachment region and the tip region; a chord dimension extending between the leading edge and trailing edge; a pressure side opposite a suction side of the swirl recovery vane; a structural feature formed within the swirl recovery vane extending at least one of spanwise through the swirl recovery vane between the attachment region and tip region and / or chordwise between the leading edge and the trailing edge; an acoustic receiver formed within the structural feature extending at least one of spanwise through the swirl recovery vane between the attachment region and the tip region or chordwise between the leading edge and the trailing edge; and an acoustic panel inserted into the acoustic receiver. A gas turbine engine includes the swirl recovery vane with structurally capable acoustic treatment. A process forms the gas turbine engine with the swirl recovery vane with structurally capable acoustic treatment.

The application belongs to the field of protective coating, and particularly discloses a composite laser protective coating and a preparation method thereof. The protective coating comprises, in sequence, a high-temperature oxidation-resistant layer, a ceramic thermal insulation layer, a ceramic reflective layer and a metal reflective layer which are arranged on a substrate in a laminated manner. The porosity of the ceramic thermal insulation layer is not less than 10%. The material of the high-temperature oxidation-resistant layer comprises at least one of NiCrAlY, CoCrAlY and NiCoCrAlY. The material of the ceramic thermal insulation layer comprises zirconium oxide and an oxide doped in the zirconium oxide. The material of the ceramic reflective layer comprises zirconium oxide and a rare earth element doped in the zirconium oxide. The protective coating has a low thermal conductivity, and the average temperature on the side of the substrate away from the protective coating is lower than 150 DEG C after the substrate is continuously irradiated by a laser with a power density of 8050 W·cm ‑2 -2 for 300 s, and the bonding strength of the coating is 35-50 MPa.