385results about How to "The overall structure is light in weight" patented technology

The invention discloses a bionic gradient knee femoral prosthesis structure and a production method thereof. The prosthesis structure comprises a smooth curved-surface shell, a post-osteotomy completely-covering joint face, a gradient porous structure and a fixing device. The curved-surface shell is based on the shape of the distal end of a connate femur. The post-osteotomy completely-covering joint face reversely spreads to the distal-end curved surface of the connate femur. A solid more than 5mm distant from the curved surface is replaced by the gradient porous structure, and the fixing device is formed on the distal-end plane on the inner side of a femoral prosthesis. Compared with conventional standard prostheses, the prosthesis structure has the advantages that matching degree is high, and the prosthesis highly fits the bone shape of a connate knee and is adaptable to motions of a patient. The bionic gradient knee femoral prosthesis structure is easy to produce, and conventional production methods for conventional bionic gradient prostheses are complex; by the 3D (three-dimensional)-printing production method, prostheses can be customized according to individual differences of patients, production period is short, cost is low, and a possibility for application and development of individualized therapy is provided.

The invention discloses a single drive linkage type lower limb power assisting exoskeleton, relates to a lower limb exoskeleton used for power assisting and walking, and aims to solve the problem that conventional exoskeleton design basically adopts a motor or hydraulic pressure to conduct independent control on a hip-joint and knee joints. The lower limb power assisting exoskeleton comprises a back module, two waist modules, two thighs and two cruses; the two waist modules are arranged at the two ends of the back module; thigh drive sprockets and a third crank shaft on the waist module are mounted on the output shaft of a universal coupling on the back module sequentially from inside to outside; each waist module corresponds to a thigh and a crus; front ends of adjusting outer side plates and adjusting inner side plates on the thighs are hinged to the central shafts of double-row chain wheels on the waist module; two lifting lugs on the cruses are hinged to the connecting shafts on the thighs. The lower limb power assisting exoskeleton is used for assisting the old and disabled, medical rehabilitation, and the like.

The invention provides a space capturing and locking device. The space capturing and locking device comprises a driving structure and a driven structure. The driving structure comprises a shell assembly, a driving assembly, a transmission assembly, an upper plate auxiliary assembly and three sets of finger assemblies. The shell assembly is used for supporting and being connected with the driving assembly, the transmission assembly, the upper plate auxiliary assembly and the finger assemblies. The upper plate auxiliary assembly comprises rollers. The finger assemblies comprise four-bar mechanisms. The driving assembly drives the transmission assembly, the transmission assembly converts rotational motion into linear motion, the transmission assembly controls the finger assemblies to move upwards and downwards, the three sets of finger assemblies are closed due to compression of the rollers when moving downwards, and then the driven structure matched with the driving structure is clamped. The four-bar mechanism is in linkage when the finger assemblies move upwards, the finger assemblies are driven to be opened, and then the driven structure is released. The space capturing and locking device can be used for capturing and locking of a space mechanical arm on a small aircraft, and the advantages of being low in weight, small in size, large in tolerance and diverse in capture object are achieved.

The invention relates to an expansion type environment-friendly halogen-free high-flame retardant and fire-resistant cable and a method thereof. The cable is characterized in that: each core sequentially consists of conductors, a silicon rubber insulating layer, a filler, a flame retardant oxygen separation layer, an aluminum-plastic composite tape insulation layer and an expansion type fire-resistant outer protective layer made of low-smoke halogen-free flame retardant polyolefin from inside to outside, and adopts a fire-resistant cable structure formed by combining the expansion type fire-resistant outer protective layer made of the low-smoke halogen-free flame retardant polyolefin, the aluminum-plastic composite tape insulation layer and the silicon rubber insulating layer; and a flame retardant oxygen separation layer structure is formed by a halogen-free high-flame retardant material coated with metal hydrates. The preparation method comprises the following steps of: drawing single lines, performing annealing, twisting the conductors, insulating silicon rubber, cabling, and preparing the flame retardant oxygen separation layer, the aluminum-plastic composite tape insulation layer and the expansion type refractory outer protective layer made of the low-smoke halogen-free flame retardant polyolefin. The cable provided by the invention is easy to process, the external diameter of the cable is smaller than that of the traditional cable by 2 to 4 millimeters, and the structure can be obviously lightened.

The invention relates to a regenerator for a micro gas turbine, concretely is a original surface heat exchanger for increasing the heat efficiency of the gas turbine, it can increase the compactness and the service life of regenerator. The gas inlet and outlet channels are arranged on the right lower horn and the left upper horn, the high pressure air flows into the regenerator through the air inlet channel, flows out from the air outlet channel, the left and right frames of the heat exchanging board are welded and formed a air in/out aperture, the fuel gas can flow into the regenerator through the aperture, flows out form aperture on another side, the centre is heat exchanging corrugation plates, the flatten area at two sides of the plates is used to place flow guiding plate, the heat exchanging board has a side frame for welding and sealing. The flow speed at two sides has a little difference, the heat exchanging effect is the best, and it can upgrade the heat exchanging efficiency.

The invention discloses a medium span steel tube concrete girder bridge which has the light weight and is simple to install, especially proper for the mountain expressway. It includes the main girder set at the top of the pier which is made up of the lower boom tube, top boom framework and many siphonets set in space and with obliquity. The two ends of every siphoned are connected with the lower boom tube and the top framework to form the girder bridge of triangular transect. The lower boom tube connected t the pier is the steel tube concrete. The invention can improve the bridge constructing speed and decrease the cost.

The invention discloses a bionic flapping-wing aircraft based on flapping-folding-torsion coupling movement. The bionic flapping-wing aircraft is composed of a fuselage, wings on the two sides and anempennage mechanism. When a wing motor is started, a crank gear on an output shaft of the wing motor rotates to sequentially drive first front-section wing rods, second front-section wing rods and third front-section wing rods to rotate, and the flapping movement of the wings is achieved; fixed gears swing up and down along with the second front-section wing rods to transmit the torque to driven bevel gears through planet gears, so that third wing face supporting plates rotate within a small range around the third front-section wing rods, and accordingly the torsion movement of the wings is achieved; and the flapping angles of front-section wing bodies, middle-section wing bodies and tail-section wing bodies are different, and accordingly the folding movement of the wings is achieved. Steering of the aircraft is achieved jointly through an empennage and a steering engine for adjusting the empennage direction. The bionic flapping-wing aircraft based on the flapping-folding-torsion coupling movement has the characteristics that the number of driving original motive parts is small, the flapping-folding-torsion coupling movement of the flapping wings can be achieved, flying is flexible, and generated effective lift force is large.

Provided is a cross-medium aircraft with a changeable shape like a sailfish. The streamline type appearance of the sailfish is simulated by a machine body (2). A head pointed cone (1) is arranged at the head portion of the machine body (2) to divide water flow. A pair of angle-changeable water wings (3) are installed on the two sides of the front portion of the machine body (2) respectively. The aircraft is controlled to sink or float in water by adjusting the positive tapping angle and the negative tapping angle of the pair of angle-changeable water wings (3). A pair of scale-shaped rectifying covers are installed on the two sides of the middle of the machine body (2) respectively. A pair of self-adaption spiral paddles (4) capable of rotating in an inclined mode are installed on the scale-shaped rectifying covers (5) through a pair of spherical multi-freedom-degree linkage steering gears (6). An X-shaped tail wing (7) is arranged at the middle rear section of the machine body (2). An underwater-propulsion spiral paddle (8) is installed at the tail portion of the machine body (2). By means of the cross-medium aircraft, the design principles and bionics principles of the aircraft and an autonomous underwater vehicle are successfully applied, and the designed cross-medium aircraft has the good running capacity in fluid of two different types including air and water.

The invention discloses a flexible trailing edge structure and a design method thereof. The flexible trailing edge structure comprises a rear beam, a flat bent beam, a rigid triangular wingtip, a flexible skin, filling honeycombs, a first driver and a second driver, wherein the rear beam, the flexible skin and the rigid triangular wingtip define a containing space; the flat bent beam is arranged in the containing space and divides the containing space into a first space and a second space; the first driver is arranged in the first space; the second driver is arranged in the second space; and the filling honeycombs are arranged in the first space and the second space. The flexible trailing edge structure is low in weight and simple in configuration, meets the demands of continuous flexibledeformation and low mass of a trailing edge structure and therefore achieves the purpose of replacing a rigid flap and an aileron.

The invention provides a distributed communication-in-motion light shaped antenna which is composed of a plurality of distributed front ends (9), a distributed optical fiber signal network (6), a distributed low-frequency signal network (7) and a distributed grating sensor network (8). Each of the distributed front ends comprises a distributed antenna sub-array (1), an electro-optical/photoelectric conversion chip (3), a sub-array wave beam control system (4) and a grating sensor (5), which are electrically connected around a silicon-based integrated transceiver chip (2). Under command control of a centralized processing terminal (10), each distributed front end (9) can implement beam scanning and satellite signal alignment; and then the plurality of distributed front ends (9) implement beam forming and real-time satellite communication under command control of the centralized processing terminal (10). The technical problem that the existing communication-in-motion antenna is designed in an integrated mode in an aperture, is large in size and heavy, and is hard to match a flexible wing structure in stiffness is solved.

The invention belongs to the field of spatial sampling robot engineering and particularly relates to a planet surface mechanical arm sampling device. The planet surface mechanical arm sampling device comprises a sample saving box, a sampling mechanical arm system and a sample saving system, one end of the sampling mechanical arm system is connected onto the sample saving box through a joint, and the other end of the sampling mechanical arm system is connected with an opening-and-closing type bucket through an opening-and-closing type shoveling mechanism, the sample saving system is installed in the sample saving box, an opening is formed on the sample saving box, and samples collected by the bucket are placed in a sample receiving area of the sample saving system through the opening for saving. The planet surface mechanical arm sampling device is light in structure weight and flexible in operation, can resist to the spatial electromagnetic environment and extreme high-and-low temperature conditions on a planet surface in an application process and can adapt to wide engineering application environment and a big scope. The planet surface mechanical arm sampling device can be used for conveniently colleting objects at any position of a sphere with a mechanical arm installation base to serve as an original point and the overall length of the sampling mechanical arm system to serve as the centre of a circle, and the planet surface mechanical arm sampling device has a plurality of superiorities on sample collection work under serious conditions.

The invention discloses a three-axis simulation flight simulator executing mechanism. The mechanism includes a roll platform, a pitch platform, a yaw platform, and a base platform. The roll platform includes a front cabin, a rear cabin, a roll motor, a roll reducer, a roll sprocket pair minor sprocket, a roll cylindrical bore self-aligning roller bearing, and a large-diameter rubber roller pivotalbearing inner ring. The pitch platform includes a pivotal bearing outer ring, a U-shaped frame, a roll sprocket pair large sprocket, a roll bearing seat, a pitch sprocket pair large sprocket, a pitchright shaft, a pitch cylindrical bore self-aligning roller bearing, and a pitch left shaft. The yaw platform includes a U-shaped bracket, a pitch bearing seat, a pitch motor, a pitch reducer, a pitchsprocket pair minor sprocket and a yaw bearing seat. The base platform includes a base, a base bracket, a large-diameter pivotal bearing, a yaw motor, a yaw reducer, an open internal gear meshing pair small gear, and support feet. The mechanism of the invention can simulate that a single person operates an aircraft to perform three degrees of freedom of roll, pitch and yaw movements to realize asimulated flight function.

The invention discloses an enclosed cylinder structure catapult, mainly consisting of an ejection cylinder, a piston, a cylinder head, a telescopic sealing device, a high-strength steel cable and a reciprocating vehicle. Wherein, the ejection cylinder is in enclosed pipe-shaped structure consisting of a plurality of cylinder sections which are connected with flanges; a cylinder head is arranged at the starting end of the ejection cylinder where an air inlet valve and a steel cable hole is arranged; the telescopic sealing device consists of sleeves telescopically sleeved together from small internal diameter to large internal diameter; the head end of the most-inner sleeve is arranged on the piston and the tail of the most-outer sleeve extends out of the cylinder through the steel cable hole on the cylinder head. One end of the high strength steel cable passes through the telescopic sealing device and is connected with the piston in the cylinder by the steel cable hole in the cylinder head; the other end of the high strength steel cable is connected with the reciprocating vehicle; the invention adopts the enclosed cylinder, the high strength steel cable and the telescopic sealing device, etc., therefore, the invention has the advantages of high strength, light structural weight, simple sealing, high reliability and low production cost.

The invention relates to a rapidly-controlled aeration releasing mechanism which mainly comprises an end cap, a gas generator, a guide cylinder, a thin film tube and a thread gluing and the like, wherein the gas generated by the gas generator ensures the folded thin film tube to be unfolded. The rapidly-controlled aeration releasing mechanism provided by the invention has the characteristics of light weight, small volume, rapid unfolding process and controllability, thereby providing an effective method for realizing the requirement of rapid releasing structures in the aerospace field and relative fields.

The invention relates to a piezoelectric floor device of a blocking cantilever beam structure and belongs to the field of energy collection based on piezoelectric materials. By the device, the potential energy generated when pedestrians tread on floors is converted into electric energy through piezoelectric patches. According to the piezoelectric floor device, the integrated piezoelectric floors of different shapes are composed of a plurality of hexagonal piezoelectric units. Each hexagonal piezoelectric unit is composed of a cover board, a fixing pressing board, one piezoelectric patch, a base board, a bottom board and a screw. The peripheral fixedly supporting mode of a polygonal piezoelectric structure is changed into the long cantilever beam supporting mode in a blocking mode so as to increase displacement and an output power value. The piezoelectric floor device is applied to pedestrian dense places such as railway stations, subway stations and pedestrian streets, and lighting is provided for pedestrians in the walking process in the mode that LEDs and energy storage elements are connected. The piezoelectric floor device is light, small in size and high in electric energy generating capacity and has wide application prospects.

The invention discloses a construction method of a decorative sheet dry hanging system, and a decorative sheet dry handing system. the construction method includes: A, arranging a handing member on a decorative sheet; B, arranging vertical keels; C, arranging horizontal keels; D, arranging the decorative sheet. The vertical keels and the horizontal keels are made of an aluminum material. The decorative sheet dry handing system includes the vertical keels, the horizontal keels, the hanging member, the decorative sheet, first corner connectors, second corner connectors, first waist-shaped holes, second waist-shaped holes, chemical bolts, first T-shaped bolts, first nuts, third waist-shaped holes, fourth waist-shaped holes, second T-shaped bolts, second nuts, third T-shaped bolts, and third nuts. The first waist-shaped holes and the second waist-shaped holes are formed in the first corner connectors, the third waist-shaped holes and the fourth waist-shaped holes are formed in the second corner connectors, and the vertical keels and the horizontal keels are made of the aluminum material; and the decorative sheet dry handing system is light in weight, is adjustable, is simple to operate, is low in demand for the proficiency of workers, and is easy to install and demount.

The invention relates to an active flexible telescopic truss structure, and belongs to the technical field of morphing aircraft structural design. The structure comprises a first panel and a second panel, a telescopic truss, springs and controllable alloy wires, wherein the first panel and the second panel are opposite to each other; the telescopic truss is arranged between the first panel and thesecond panel and can be stretched between the first panel and the second panel; the springs are perpendicular to the movement direction of the telescopic truss, and are respectively connected to thefirst side and the second side of the telescopic truss; the controllable alloy wires are respectively arranged on the first side and the second side of the telescopic truss; and stretching of the telescopic truss can be controlled through the control of the controllable alloy wires. The active flexible telescopic truss structure is driven through the controllable alloy wires (shape memory alloy wires), drives angles between telescopic trusses to change, and achieves the purpose of telescopic deformation.

The invention discloses a noise barrier which comprises a plurality of columns and a plurality of wall plates which are arranged between the adjacent columns and are connected up and down, wherein a curved plate is arranged on the topmost wall plate; each wall plate is formed by arranging a noise absorbing plate between two noise insulation plates. According to the noise barrier, the noise is eliminated by using a way of insulation-absorption-insulation, and the effect is more ideal than the traditional single noise insulation or absorption effect.

The invention relates to a vertical lifting aerodyne employing tiltable ducted wheels. A fuselage adopts the streamline design, two sides of the fuselage are provided with large strake wing body-fused horizontal fixed stub wings, tilting systems are designed at the tail ends of the stub wings and connected with the earth-space dual purpose ducted wheels, the ducted wheels are overturned towards the inner side of the fuselage through the tilting systems, and thus the vertical lifting aerodyne can run on the ground, take off and land vertically and fly in the air with any attitude. Six stub wings are designed at both sides of the fuselage in total, so that six ducted wheels are required in total. The vertical lifting aerodyne has the advantages that the technology of fusing the streamline fuselage and wing bodies is adopted, and thus the structure weight is light, the internal capacity is large, the air resistance is small; control over the flight attitudes is realized through controlling power differentials of the six wheels, the design of control rules is simple, and the control is convenient.

The present invention relate to an impact-resistant lightweight density gradient composite material, a fan containment casing, a preparation method and an application thereof. The impact-resistant lightweight density gradient composite material, the structure form of the composite material fan containment casing, and material delamination are creatively designed, the designs of composite structurelayers of a carbon fiber reinforced resin matrix composite layer, a carbon fiber/aramid fiber reinforced resin matrix composite layer and an aramid fiber reinforced resin matrix composite layer are adopted, the thickness of each structural layer is optimized, and the carbon fiber reinforced resin matrix composite layer resists shear failure, the carbon fiber/aramid fiber reinforced resin matrix composite layer resists delamination failure, the aramid fiber reinforced resin matrix composite layer resists tensile fracture failure. The structural design significantly reduces the structural weight and improves the impact resistance of materials.

The invention discloses a method for determining the positions of wing spars. The method includes the first step of analyzing and calculating the flying loads of a wing, the second step of designing the flexural and torsional center line position, and the third step of determining the positions of the wing bars. According to the method, the thought that the positions of the wing spars is matched with the flexural and torsional center line and the loads, the flexural and torsional center line position can be rapidly determined according to the characteristic that the wing bears the loads in the initial stage of the design, the determination of the positions of the wing spars can then be completed, the positions of the wing spars of the wing can be matched with the flexural and torsional center line position, the flexural and torsional center line position can be matched with the loads, and therefore the aim of enabling the position of the wing spars, the flexural and torsional center line position and the loads to be matched is achieved; the method provides powerful scientific evidence for the subsequent structural design of the wing; the method for determining the positions of the wing spars is novel, clear in thought, practicable in operation, high in universality and capable of being popularized and applied to the structural design of the double-spar wing with the high span chord ratio.

The invention discloses a novel thermal insulation system for a free jet flow force measuring test model. The novel thermal insulation system includes a force measuring balance, a supporting rod, a balance protection cover, a thermal insulation assembly and a gas cooling assembly; the force measuring balance is arranged in a mould inner cavity; one end of the force measuring balance is connected with the mould inner cavity; one end of the supporting rod is connected with the other end of the force measuring balance; the balance protection cover is arranged on the force measuring balance in a covering manner so as to realize thermal insulation protection for the force measuring balance; the thermal insulation assembly includes a thermal insulation sleeve which is arranged along the circumferential direction of the supporting rod; a sealing space is defined between the thermal insulation sleeve and the outer circumferential surface of the supporting rod; labyrinth seal components are arranged on the supporting rod at intervals so as to divide the sealing space into at least three intervals; and the gas cooling assembly includes gas jetting rings which are located in the intervals and sleeve the outer circumference of the supporting rod, and a cold gas pipeline which is communicated with the gas jetting rings, wherein the cold gas pipeline is connected with a high-pressure cold gas source, and the gas jetting rings jet out a cooling gas to decrease the temperature of the mould inner cavity. According to the novel thermal insulation system of the invention, a plurality of thermal insulation and cooling means are adopted, and therefore, the novel thermal insulation system is remarkable in cooling effect and compact in structure, and can effectively control the temperature of the balance.

The invention discloses a bearing quick-release lock and belongs to the fields of quick release connection of a fairing and an access panel which are frequently released in an aviation helicopter structure. The bearing quick-release lock is characterized by comprising a lock seat assembly and a lock pin assembly, wherein the lock seat assembly comprises a sealing cap, a snap spring, a compression spring, a sliding block and a lock seat; the lock pin assembly consists of a washer, a lock pin, a bush and an ejection rod. The bearing quick-release lock disclosed by the invention has the advantages of light structural weight, attractive appearance, high reliability, sealing property and certain bearing capacity, and can be suitable for quick release connection of a fairing at a position where the vibration environment is particularly severe. According to the quick-release lock disclosed by the invention, after locking, the lock pin is clamped by a clamping groove of the sliding block, so that the lock pin cannot extend by rotating; the lock pin can be unlocked by rotating after the ejector rod is pushed by a tool and is enabled to push the sliding block to move until the lock pin cannot be clamped by the sliding block; after locking, the ejector rod ejects to be in flush with the head of the lock pin, so whether the virtual locking exists or not can be effectively judged.