335results about How to "Lightweight structure" patented technology

A multi-operating mode frame type portable landslide testing device for a geomechanical model belongs to the field of geological hazard model test. The testing device comprises a frame-beam-type testing bed, a rainfall simulator, a water level regulator and a self-weight horizontal loading mechanism, wherein the frame-beam-type testing bed mainly comprises a cuboid framework, a front panel, a rear panel and a base plate; the rainfall simulator is arranged at the top of the frame-beam-type testing bed and comprises a plurality of spraying pipes and nozzles on the spraying pipes and is used for simulating rainfall in the frame-beam-type testing bed; the water level regulator comprises a left-side trough and a right-side trough respectively formed on the left and the right sides of the frame-beam-type testing bed, and a plurality of drainage holes are respectively formed on the right panel of the left-side trough and the left panel of the right-side trough and used for changing the water levels of water level simulation libraries in the left-side trough and the right-side trough; and the self-weight horizontal loading mechanism is arranged above the right-side trough and used for bearing weights, so as to exert horizontal load to the landslide model in the frame-beam-type testing bed.

The invention discloses a device that can stretch the reflection plane in space, which includes a foldable ring pole, a foldable rib pole and a plurality of connection joints, wherein, every two foldable ring poles (1) are connected by a ring pole connection joint (2) to form a furling and stretching ring structure; every two foldable rib poles (3) form a furling and stretching rib structure by a rib pole connection joint (4); one end of the rib structure is connected with the ring structure by a ring rib connection joint (5) and the other end is connected with a central ribbed tube connection joint (6) to form a whole rigid body; the ring pole connection joint and the rib pole connection joint drives, locks and controls the foldable ring pole to stretch from the vertical furled state to the horizontal stretched state and controls the foldable rib pole to stretch from the vertical furled state to the expected curve proximity state. The invention has low area density, high structural precision and large holding rate and can be used for the ground or space as a reflector or a collector.

The invention belongs to the technical field of building engineering and particularly relates to an integral assembling type building system and an installing method. The integral assembling type building system is characterized by comprising prefabricated steel reinforced concrete combination columns, prefabricated steel reinforced concrete combination beams, prefabricated reinforced concrete slabs, a prefabricated light integral inner wall and a prefabricated concrete heat preservation outer wall which are assembled together. The building system has the beneficial effects that all the members are prefabricated in a factory, quality is controlled conveniently, and the construction difficulty caused by outdoor weather changes can be reduced. Moreover, splicing is carried out on site, and installing is safe, fast and convenient. The recycle rate of formworks is high, work for the formworks and frame pipes on site is avoided, the number of times of use and consumption of the formworks and frame pipes are reduced, on-site labor is saved, the on-site dust raise phenomenon is improved substantially, the influence on the environment is small, and environmental pollution is reduced.

The invention relates to a ship-based net collision recovery unmanned aerial vehicle, comprising an airframe, an airfoil, ailerons, a horizontal tail, an elevating rudder, vertical tails, rudders, an engine and a propeller, wherein the airfoil is mounted on the airframe and adopts an upper single-airfoil layout; the left side and the right side of the airfoil are respectively provided with one aileron; the horizontal tail is mounted at the upper end of the tail part of the airframe and adopts double vertical fin layout; the left and right vertical tails are connected with the wing ends of the horizontal tail respectively; the horizontal tail has a 1.5-degree mounting angle; the front edge of the horizontal tail is higher than the rear edge of the horizontal tail; the elevating rudder is arranged on the rear edge of the horizontal tail; the rudders are arranged on the rear edges of the vertical tails; the engine is mounted at the tail end of the airframe and is used for driving the propeller to rotate. The unmanned aerial vehicle has the characteristics that the endurance time is long, so a flight mission with high requirement on endurance is convenient to carry out during navigation; the wind-resistant ability is strong and the stability is high, so the unmanned aerial vehicle is applicable to the flight emission under a complicated sea condition; catapult-assisted take-off and high-precision net collision zero-distance recovery are adopted, so the unmanned aerial vehicle is applicable to emission and recovery on a narrow space on naval vessels; the whole machine adopts modular design, so containerized transportation is facilitated and the occupied space on the naval vessel is reduced.

The invention relates to the field of carrier rocket posture control systems, in particular to a hydrogen peroxide posture control system applied to a solid-liquid hybrid power carrier rocket. The system includes four pitching rolling posture control engines and two yawing posture control engines; the two yawing posture control engines are arranged in the positive and negative directions of a Z axis of the outer side of a rocket three-sublevel main engine separately; the first pitching rolling posture control engine is installed on the surface of the main engine, and a 40-degree included angleis formed between the first pitching rolling posture control engine and the negative direction of the Z axis; the fourth pitching rolling posture control engine is installed on the surface of the main engine, and a 40-degree included angle is formed between the fourth pitching rolling posture control engine and the positive direction of the Z axis; the other two pitching rolling posture control engines are installed symmetrically on the surface of the main engine relatively to an XZ plane. According to the scheme, six posture control engines are adopted as propelling force, the number of thrusters is small, invalid loads can be reduced to a great extent, and the conveying capability of the whole carrier rocket is improved. Meanwhile, the failure rate of the posture control system is decreased, and the stability and safety of the system are improved.

The invention discloses an orbit and attitude control integrated space marching system based on an electric pump. The orbit and attitude control integrated space marching system comprises a high-pressure air bottle, an oxidizing agent storage tank, a fuel storage tank, an electric pump system, an oxidizing agent pressure accumulator, a fuel pressure accumulator, an orbit-control engine and attitude-control engines; the high-pressure air bottle is connected with the oxidizing agent storage tank and the fuel storage tank through a pipeline I, the oxidizing agent storage tank and the fuel storagetank are connected with the electric pump system through a pipeline II and a pipeline III correspondingly, the electric pump system is connected with the orbit-control engine and the oxidizing agentpressure accumulator and the fuel pressure accumulator through a pipeline V and a pipeline VI correspondingly, and the oxidizing agent pressure accumulator and the fuel pressure accumulator are connected with the attitude-control engines through a pipeline VII and a pipeline VIII correspondingly. The electric pump system controls the rotating speed and the lift of a motor pump through an actuator,the pressure and flow of an oxidizing agent and fuel supplied for the engines are controlled, the adjustment is convenient, and the supplying requirements for a propellant of large-range thrust adjustment and multi-time starting and stopping of the orbit-control engine can be met.

The invention relates to a roller tappet (1) for a high pressure fuel pump, having a housing (2) in which a friction bearing mounted roll (4) serving as a run-up of a cam is immanent in the drive-side face (3) thereof, wherein the housing (2) has a bridge piece (5) underneath the roll (4) when viewed in the direction of the housing which has an attachment (8) for a tappet follower part on the one end face (7) thereof facing a drive-side face (6) of the housing (2) and wherein a shell part (11) separate from a rolling ring, such as a half or third-shell, sits in a cylindrical molding (9) of another drive-side end face (10) of the bridge part (5), in which the friction bearing mounted roll (4) runs directly.

The invention provides an electric pump pressure type liquid oxygen methane space propelling system. The electric pump pressure type liquid oxygen methane space propelling system comprises a high-pressure gas cylinder, a liquid oxygen storage tank, a methane storage tank, an electric pump system, an oxygen heat exchange injection rod, a methane heat exchange injection rod and a track control engine; the high-pressure gas cylinder is connected with the liquid oxygen storage tank and the methane storage tank through a first pipeline; the liquid oxygen storage tank and the methane storage tank are connected with an electric pump system through a second pipeline and a third pipeline; the oxygen heat exchange injection rod is arranged in the liquid oxygen storage tank; the methane heat exchangeinjection rod is arranged in the methane storage tank; the electric pump system is connected with the oxygen heat exchange injection rod and the track control engine through a fourth pipeline; and the electric pump system is connected with the methane heat exchange injection rod and the track control engine through a fifth pipeline. The electric pump pressure type liquid oxygen methane space propelling system is suitable for a space aircraft propulsion system, and particularly has obvious application advantages on a space propelling system which has large propellant filling amount and whose track control engine needs to be started for a plurality of times..

The invention discloses an axial injection end combustion solid-liquid rocket engine structure which comprises an engine head cover, a solid propellant shell, a solid propellant heat insulating layer, end combustion solid propellants, a spray pipe shell and a spray pipe heat insulating layer. The engine head cover is mounted at the front end of the solid propellant shell, the spray pipe shell is mounted at the rear end of the solid propellant shell, the engine head cover is provided with an air inlet channel, the end combustion solid propellants are coaxially arranged in the solid propellant shell, a constant volume cavity is formed between the front end faces of the end combustion solid propellants and the rear end face of the engine head cover, each end combustion solid propellant is provided with a plurality of axial injection holes with small diameters, the flow rate of oxidizing agents in the injection holes is high, and combustion reaction only occurs at the end faces of the end combustion solid propellants; the joint between the solid propellant shell and the engine head cover and the joint between the solid propellant shell and the spray pipe shell are respectively provided with a sealing structure, so that air impermeability of an engine is guaranteed; the heat insulating layers are arranged in the solid propellant shell and the spray pipe shell, so that thermal protection performance of the engine during operation is guaranteed. Thus, performance of the engine is improved, meanwhile the filling fraction of the engine is improved, the slenderness ratio of the engine is reduced, and the application rage of engine is widened.

The invention aims at providing an oil-drive direct-driven multi-rotor-wing agricultural plant protection unmanned aerial vehicle which can greatly prolong the runtime, is high in structural stability and anti-shock capacity and can increase the load capacity. According to the adopted technical solution, the oil-drive direct-driven multi-rotor-wing agricultural plant protection unmanned aerial vehicle comprises a machine frame, avionics, a power mechanism and a spraying mechanism; the machine frame comprises a supporting beam, an upper central plate, a lower central plate, machine arms and pull rods; the upper central plate and the lower central plate are fixedly connected to the supporting beam; the six machine arms are fixed between the upper central plate and the lower central plate in a crossed mode in the regular hexagon diagonal direction; a reinforced umbrella-shaped structure formed by the pull rods is arranged between the machine arms and the supporting beam; each power unit comprises an engine fixed to an engine base, a steering engine fixed to the bottom of the engine, and a propeller connected to an output shaft of the engine; the power mechanism of an oil-drive direct-driven structure; and the output shafts of the engines are directly connected with the propellers.

The invention discloses a satellite-borne deployable mesh antenna. The satellite-borne deployable mesh antenna comprises an antenna reflecting surface extending arm (1), an antenna reflecting surfacedeployable supporting assembly (2) and a cable net structure (3). The antenna reflecting surface extending arm adopts a carbon fiber composite material hollow round rod design, so that the weight of the extending arm and the in-orbit thermal deformation of the extending arm are reduced, and the antenna pointing accuracy is ensured. The antenna reflecting surface deployable supporting assembly (2)is composed of module units, can be increased or decreased according to the aperture requirement of the antenna reflecting surface, and is high in expandability. The cable net structure is designed ina multi-layer cable net mode, ground adjustment of the profile precision of the reflecting surface is achieved, and the requirement of microwave antenna detection for the profile precision of the reflecting surface is met. According to the invention, factors such as antenna emission folding and in-orbit unfolding, antenna reflecting surface function and performance testing and antenna reflectingsurface profile precision adjusting are comprehensively considered for design, and the requirement of satellite in-orbit ground detection can be met.

The invention discloses an aerodynamic layout of a transatmospheric reusable aircraft, which comprises a head, a fuselage, a horizontal wing, a vertical tail, a body flap and a liquid hydrogen/liquid oxygen linear plug-type nozzle rocket engine. The invention has no booster, and adopts a single stage to vertically launch into orbit from the ground; after completing the mission, it can return to the atmosphere and glide horizontally to land, and can be completely reused after recovery. Through reasonable aerodynamic configuration and optimized design, the aircraft has a high lift-to-drag ratio and good stability and maneuverability in a wide range of altitudes and speeds. At the same time, the fuselage has a large effective volume and needs to carry propulsion Dose less. The invention has low launching cost, short launching preparation period and high reliability. It can overcome the shortcomings of current space vehicles that cannot be completely reused, expensive to launch, and cumbersome to use and maintain. It can be used not only for military space missions, but also for commercial and civil space services.

A technology for manufacturing the squeezed Mg-alloy rod includes smelting Mg-alloy ingot, casting solid circular ingot, heating for 12-18 hrs, natural cooling, heating, squeezing and straightening. Its advantages are low specific weight and high rigidity.

The invention relates to a square tapered aluminum alloy automobile front carling based on an embedded carbon fiber. The square tapered aluminum alloy automobile front carling based on the embedded carbon fiber is characterized in that the section of the front carling is composed of two parts, namely the aluminum alloy outer wall and a carbon fiber reinforced plate. An aluminum alloy outer plate is little in elasticity modulus and good in deformation mode and the carbon fiber reinforced plate has the strong collision energy absorption capability. By means of the two new materials are combined and a square tapered structure, the contradiction among the high energy-absorption performance, the low-collision-acceleration peak value and the good crushing mode can be coordinated in a satisfying manner in the collision safety design process. The square tapered aluminum alloy automobile front carling based on the embedded carbon fiber has great significance in improvement of the collision performance and weight reduction.

Disclosed is a shear type unit imitation cobweb space expandable mechanism. The shear type unit imitation cobweb space expandable mechanism comprises expandable units and a machine base, wherein eachexpandable unit comprises a driving rod, a hinge, a connecting rod and a shear type unit; and the machine base is a pentagonal machine base. The five expandable units are annularly arrayed on the samemachine base; one driving rod can be shared between every two adjacent expandable units; the first hinge sleeved on the driving rod is connected with the second hinge to form a closed loop space expandable mechanism; and the space expandable mechanism has a freedom degree, the required driving is small, the control is simple, and the expandable units are connected through two hinges, so that themechanism has the advantages of being high in rigidity and strength, stable in mechanism unfolding, light in structure weight and high in folding ratio, and is suitable for the fields of space plane satellite launching antennas, space satellite parabolic antennas and the like.

The invention belongs to the technical field of ocean renewable energy utilization, and discloses offshore semi-submersible wind energy and wave energy integrated power generation equipment. The integrated power generation equipment comprises a wind energy power generation mechanism, a semi-submersible platform and a plurality of wave energy power generation mechanisms, wherein the wind power generation mechanism is used for wind power generation and arranged on the semi-submersible platform; the plurality of wave energy power generation mechanisms are separately arranged on the semi-submersible platform and used for consuming wave energy received by the integrated power generation equipment to generate power; when the integrated power generation equipment vibrates under the action of waveenergy, the wave energy power generation mechanisms consume the wave energy to generate electricity as well as elastic deformation to store energy while limiting the movement of the semi-submersibleplatform; and after energy storage is finished, the wave energy power generation mechanisms generate power through an elastic restoring force, so that the vibration amplitude of the integrated power generation equipment is reduced while power generation is carried out by consuming wave energy received by the integrated power generation equipment. According to the integrated power generation equipment, the power generation efficiency and stability are improved, and the practicability is higher.

An aircraft wing rib dynamics determination method based on the formation superposition method. The determination method includes steps: guiding into an aircraft wing rib initial geometric model and a dynamic load; transforming the geometric model of a wing rib into a finite element model; initializing pseudo density values of units of portions needed to be optimized of the finite element model, integrally substituting the wing rib finite element model attached with the pseudo density values in a solver for modal analysis; based on modal analysis results, adopting the formation superposition method for approximate analysis of wing rib dynamic response; based on dynamic analysis result, solving deformation energy of the wing rib, and adopting the Newman expansion difference method to solve the deformation energy and sensitivity of the pseudo density values of restriction; transmitting these values to an optimizer to obtain pseudo density value after updating; and if convergence criteria are met, stopping iteration, if not, returning to the finite element solving portion to generate a final dynamic design scheme for the wing rib. By the aircraft wing rib dynamics determination method based on the formation superposition method, working conditions of dynamics are taken into consideration, aircraft weight is lowered and aircraft performance is improved.

The invention relates to a trimix pressurization system applied to a liquid rocket. The trimix pressurization system comprises a helium and hydrogen bottle (1), an oxygen bottle (2), a flow control unit and a catalytic bed (5), wherein mixed helium and hydrogen are stored in the helium and hydrogen bottle (1) in advance; oxygen is stored in the oxygen bottle (2); flow of gas output in the two bottles is controlled through the flow control unit; a mixed gas of output helium, hydrogen and oxygen is subjected to catalytic reaction through the catalytic bed (5); oxygen and hydrogen react to generate water vapor and release hat; and helium, water vapor and oxygen remaining after reaction are heated and enter a storage tank to pressurize the storage tank.

The invention belongs to the related technical field of floating offshore wind power generators, and discloses a semi-submersible wind power generator platform with a vibration reduction and isolationfunction. The semi-submersible wind power generator platform comprises a supporting structure, a vibration reduction and damping assembly and a spherical hinge, wherein the supporting structure is ofan upper layer and a lower layer frame structure, and the upper layer of the supporting structure is connected with a generator assembly through the spherical hinge; the vibration reduction and damping assembly is connected with the generator assembly and the supporting structure, and is used for reducing vibration suffered by the generator assembly; the vibration reduction and damping assembly comprises a plurality of dampers and a plurality of springs, wherein the dampers are uniformly distributed around the generator assembly; and one ends of the dampers are connected to the supporting structure, and the other ends of the dampers are connected to the generator assembly through the springs. According to the semi-submersible wind power generator platform, the motion amplitude of an offshore wind power generator is can obviously reduced, so that the stability of the whole generator platform is increased, and a safe and reliable platform supporting infrastructure is provided for high-power floating offshore wind power generation equipment.

The invention discloses a quick-replacement grinding tool for automatic grinding by a robot. The quick-replacement grinding tool comprises a connection cone matched with an electric spindle tool clamping jaw and the like, wherein a clamping slot connected with a tool frame is located on one side of the connection cone matched with the electric spindle tool clamping jaw; a manual quick-disassembly wedge slot is located between the clamping slot connected with the tool frame as well as a rear backing plate; the connection cone matched with the electric spindle tool clamping jaw, the clamping slot connected with the tool frame and the manual quick-disassembly wedge slot are all located on a front and rear backing plate threaded rod; one end of the front and rear backing plate threaded rod penetrates through a grinding wheel to be in threaded connection with a flat nut; the rear backing plate and a front backing plate are located on two sides of the grinding wheel; an anti-loose washer is located between the front backing plate and the flat nut. With the adoption of the quick-replacement grinding tool, the grinding tool can be replaced quickly, accurately and automatically, the automation level of robot grinding is further improved, the overall structure is light in mass and small in size, the center of gravity is in the axis, the dynamic balance is good, and accordingly, the grinding tool cannot shake during high-speed rotation.

The invention provides a fabricated building of a pre-assembling structure of a prefabricated section steel concrete shear wall. The building is provided with a structure preformed in a factory, and the preformed structure comprises section steel concrete shear walls, prefabricated section steel concrete beams, steel bar truss concrete slabs, prefabricated reinforced concrete stairs, light masonry partition walls, and prefabricated foam-concrete outer walls. The invention further provides a mounting method of the fabricated building of the pre-assembling structure of the prefabricated section steel concrete shear wall. The fabricated building disclosed by the invention is characterized in that all components are prefabricated in the factory, so that the quality of the components is convenient to control, and construction difficulties caused by the change of outdoor weather can be reduced. The fabricated building is assembled on site, and safe, rapid and convenient to mount; the recycling rate of templates is high, work about templates and tube frames is omitted on side, the use and the consumption of the templates and the tube frames are reduced, on-site workers are saved, and the phenomenon of on-site raise dust is greatly improved, so that the influence on environment is small, and the environmental pollution is reduced. The fabricated building disclosed by the invention is suitable for various houses and buildings, such as high-rises, small high-rises, garden houses and villas.