140results about How to "Reduce structural weight" patented technology

According to the unmanned transport plane with the separable cargo hold, rapid replacement of different aviation task cabins can be achieved, a plane body longitudinal beam serves as a structure for bearing the overall weight of the plane, a locking structure used for locking the separable cargo hold is arranged at the bottom of the plane body longitudinal beam, and the separable cargo hold is of a universal module structure. The locking structure is opened after the separated cargo hold is supported, the airplane core structure composed of the airplane body longitudinal beams, the front airplane body, the rear airplane body and the airplane wings and the separated cargo hold are respectively replaced with different cargo holds, and the cargo hold structures of the same specification for bearing different tasks are replaced, so that high freight efficiency is achieved; the fuselage longitudinal beams are adopted as main bearing beams, the front fuselage and the rear fuselage only play a role in rectification and do not participate in bearing, the structural weight of the aircraft is reduced to the maximum extent, the loading capacity of the aircraft is greatly improved, meanwhile, standardized, universal and modular accessories are adopted, and all large components have interchangeability, so that the economical efficiency of the aircraft is improved.

The invention provides an integrated mechanical arm and a mobile robot, the integrated mechanical arm comprises a base, a rotating seat is arranged on the base, and the upper end of the rotating seat is rotatably connected with a mechanical big arm; the upper end of the mechanical large arm is rotationally connected with the mechanical small arm; a first adapter shell is arranged at the front end of the mechanical small arm, and a first joint module is arranged in the first adapter shell; the two ends of the first joint module are rotationally connected with mechanical cantilevers; a second joint module is arranged on the mechanical cantilever, and a clamp adapter flange is arranged on the second joint module. The structure weight can be integrally reduced, the overall power consumption can be reduced, and the flexibility of the mechanical arm can be improved.

The invention belongs to the technical field of spaceflight, and particularly relates to a large-aperture spatial columnar deployable film light shield. According to the technical scheme, the large-caliber space columnar unfoldable thin film light shield comprises an unfoldable supporting mechanism and a thin film, the unfoldable supporting mechanism has the axial folding and unfolding functions, and the shape of the unfoldable supporting mechanism in the unfolding state is an irregular dodecagonal cylindrical surface with the upper portion beveled; the thin film is connected with the inner side of the extensible supporting structure and is folded and unfolded in the axial direction along with the extensible supporting structure. The large-aperture spatial columnar deployable film light shield provided by the invention can meet the development requirements of complex optical equipment, large field of view and wide band of an optical system, light weight of a deployable structure and high storage rate.

The invention discloses a rectangular twisted waveguide capable of being twisted at any angle, and relates to the technical field of high-power microwave and millimeter wave electronics. The rectangular twisted waveguide comprises an input rectangular waveguide, a three-circle-shaped twisted waveguide and an output rectangular waveguide which are arranged in sequence. The three-circle twisted waveguide is formed by superposing a small circular hole in the middle and two large circular holes which are symmetrically formed in the two sides and have the same size, the three circular holes have the same thickness and are perpendicular to any cross section in the electromagnetic wave transmission direction, the circle centers of the small circular hole and the two large circular holes are located on the same straight line, and the straight line is a circle center axis; the included angles between the narrow side center lines of the input rectangular waveguide and the output rectangular waveguide and the circle center axis are the same. The rectangular twisted waveguide capable of being twisted at any angle is applied to different frequency bands, the size of the twisted waveguide can be reduced, the production cost can be reduced, and the twisting angle of the twisted waveguide can be changed at any angle.

The invention discloses a rocket interstage separation guiding pneumatic push rod, and relates to the technical field of spaceflight, and the rocket interstage separation guiding pneumatic push rod comprises a first push rod assembly and a second push rod assembly; the first push rod assembly comprises a base, an outer cylinder and an inner cylinder; one end of the base is communicated with the inflation system, and the other end of the base is connected with one end of the outer cylinder; an outer cylinder inner baffle ring is arranged on the inner side of the other end of the outer cylinder; the inner cylinder comprises an inner cylinder annular plate and an inner cylinder end face, and one end of the inner cylinder annular plate is connected with the inner cylinder end face. The inner cylinder is arranged in the outer cylinder, and the outer side of the inner cylinder annular plate is in sliding connection with the inner side of the outer cylinder; the second push rod assembly comprises a guide bolt, a locking nut, a connecting device and a thrust bracket; after extending, the side, away from the inner cylinder annular plate, of the end face of the inner cylinder is separated from the other end of the base, the other end of the inner cylinder annular plate is in limiting connection with the outer cylinder inner baffle ring, and one end of the guide bolt is separated from the inner cylinder and extends out of the outer cylinder. The pneumatic push rod can be guided by itself, and it can be guaranteed that the postures of the two separated substages are stable.

The invention provides a fuselage box section structure provided with a strut type undercarriage. The fuselage box section structure comprises a front frame, a rear frame, a left beam, a right beam, an upper platform and a lower platform. Wherein the front frame, the rear frame, the left beam, the right beam, the upper platform and the lower platform are riveted to form a closed box body; the directions of the front frame and the rear frame are perpendicular to the course of the aircraft and serve as bearing frames at the bottom of the aircraft; the directions of the left beam and the right beam are parallel to the course of the aircraft and serve as bearing beams at the bottom of the aircraft; the upper platform is a floor of the aircraft, and the lower platform is an external skin of the aircraft; mounting holes are formed in the upper platform and the lower platform and serve as undercarriage connectors, and the undercarriage connectors are in clearance fit with undercarriage supporting columns; and a flange plate mounting surface is arranged at the mounting hole of the lower platform and is connected with a flange plate of the undercarriage through a bolt.

The invention discloses a tilting type electric vertical take-off and landing aircraft with foldable airfoils and an operation method. Comprising a fuselage, a fixed section wing arranged on the fuselage, a folding section wing connected to the fixed section wing through a wing folding assembly, a vertical fin arranged at the tail of the fuselage, a fixed section horizontal tail arranged on the vertical fin and a folding section horizontal tail connected to the fixed section horizontal tail through a horizontal tail folding assembly. The conversion of the aircraft among a folding mode, a helicopter mode and a fixed-wing aircraft mode can be realized under the action of the wing folding assembly and the horizontal tail folding assembly, a front-end rotor wing is arranged on the fixed-section wing, a middle-end rotor wing is arranged on the folding-section wing, and a rear-end rotor wing is arranged on the folding-section horizontal tail. When the aircraft is parked on the ground, the folding section wings and the folding section horizontal tail can be folded, so that the parking space needed by the aircraft is reduced, the requirement for special infrastructures is lowered, the cost is saved, the aircraft can be more easily integrated into the current limited space of a city, and the operation flexibility is enhanced.

The invention discloses a single-seat electric multi-rotor ultra-light aircraft, and belongs to the field of ultra-light aircraft design. The fuselage is formed by welding a fuselage main structure with light high-strength hard aluminum alloy pipe beams and taking a large-range hollow light fuselage shell as a main body, the four sets of foldable coaxial double-paddle power supporting arms are arranged on the horizontal plane in the middle of the fuselage and symmetrically arranged front and back, and the skid type undercarriage is arranged at the bottom of the fuselage. The weight of an empty aircraft meets the weight requirement of an ultra-light aircraft, meanwhile, the main body adopts an aluminum alloy pipe beam welding structure, the cost is reduced, most drivers are located in a pipe frame structure, the gravity center of the whole aircraft is close to a rotor plane, and the driving experience is better.

The application provides a kind of integrated node flexible variable mechanism of rope drive active deformation topology structure, it is related to flexible deformation device technical field, control is realized to large-span deformable structure by using rope drive, structural weight is reduced, and the operating performance of flexible deformation body mechanism is improved.The shortening of first winding makes the radius of annular framework larger;The shortening of second winding makes the length of annular framework longer;Between the first annular framework and the second annular framework, the first winding on the first annular framework is arranged on the first node on the second annular framework, and the second winding on the first annular framework is arranged on the first node on the second annular framework to realize active turning, which can reduce the stress applied to the mechanism by the outside when the pipeline moves, help protect the flexible structure, improve the system use time, and better adapt to complex terrain space scenarios, actively adjust the travel speed and direction to select the optimal path to improve work efficiency.

This utility model discloses a plastic sheet vehicle body protection structure based on adhesive bonding and serrated edge wrapping, including a wrapping layer, an adhesive layer, and an edge structure. The wrapping layer is made of one or more plastic sheets such as PVC, PC, ABS, PMMA, and PP, and is manufactured through processes such as bending and shaping, vacuum forming, and 3D printing. Its shape matches the vehicle's exterior parts and tightly wraps at least one painted surface and all sides. The adhesive layer is an adhesive layer that is applied to the area around the vehicle. After curing, it is transparent and colorless and is used to seal and bond the wrapping layer to the vehicle's exterior parts. The edge structure is a continuous serrated structure processed on the side wrapping part of the wrapping layer. It is embedded in the adhesive layer to form a mechanical interlock. The depth, density, and shape of the serrations can be adjusted as needed. The forming method is one or more of CNC machining, laser cutting, vacuum forming, or mold hot pressing.

The utility model discloses a watering device for vegetable planting, which comprises a water tank and a sprayer communicated with the top of the water tank, a supporting structure is arranged on the surface of the water tank, the supporting structure comprises swing rods which are movably connected to the front side and the back side of the water tank through pin shafts, and one side, far away from the water tank, of each swing rod is movably connected with a roller through a pin shaft. The swing rod is grabbed by two hands, the water tank is supported and moved through the rollers, the transmission structure can carry the rollers to move synchronously, when the rollers move downwards, the left side of the water tank can be lifted through supporting force, liquid in the water tank flows towards the right side, the liquid level in the water tank is increased, and the sprayer can conveniently extract the liquid; according to the watering device, the water pumping mode of an existing watering device can be improved, residual liquid in the watering device can be effectively pumped, the phenomenon that the liquid is corrupted due to bacteria after being stored for a long time is avoided, and the growth effect of vegetables is guaranteed.

The invention discloses a microgravity pressure accumulation type normal temperature storage tank, and belongs to the technical field of aerospace craft storage tanks, the microgravity pressure accumulation type normal temperature storage tank comprises a tank body and a working medium bag, the working medium bag is installed in the tank body, the tank body is provided with a working medium pipe communicated with the interior of the working medium bag, and the tank body is further provided with a pressurizing pipe communicated with the interior of the tank body. The small-capacity self-pressurization liquid working medium storage tank meets the use requirement for the small-capacity self-pressurization liquid working medium storage tank in the microgravity environment, the storage tank is provided with the pressurization cavity, a pressurization gas cylinder does not need to be additionally arranged, stable conveying of a working medium can be completed only by unlocking the working medium outflow valve, and the storage tank can be used under different working conditions such as microgravity and low gravity.

This utility model discloses a support system for an integrated sloping roof and courtyard, and a residential photovoltaic power station. The system includes a roof support and a courtyard support. The roof support comprises several horizontally spaced inclined beams on a first sloping roof, several horizontally spaced back braces on a second sloping roof, and short column support assemblies installed on both the first and second sloping roofs to support the inclined beams and back braces. The back braces are correspondingly positioned to the inclined beams, with their upward-sloping ends connected to the beams. The inclined beams extend downwards along the first sloping roof to above the courtyard. The courtyard support includes columns installed within the courtyard, with their upper ends connected to the inclined beams. A reinforcement structure is provided between the columns and the inclined beams, and / or between the columns themselves. The roof support and courtyard support can be designed as a single unit, forming a unified slope above the first sloping roof and courtyard for installing photovoltaic modules, increasing the number of photovoltaic modules installed and expanding the power generation area.

The invention relates to the technical field of constructional engineering, in particular to a modular building floor slab system which comprises a first module and a second module. The first module is arranged above the second module, and the lower end of the first module is connected with the upper end of the second module. The first module comprises a bottom plate beam, a transverse bottom frame beam, a longitudinal bottom frame beam and a first column body; the second module comprises a top plate beam, a transverse top frame beam, a longitudinal top frame beam and a second column body. By arranging the grouting cylinders and the stud structures, the top plate beams and the bottom plate beams can work together to form an open-web truss, the rigidity of the top plate beams and the rigidity of the bottom plate beams can be fully utilized, and the integrity of the modular structure is enhanced.

The invention relates to a self-deploying structure for an extended nozzle of a rocket engine, belonging to the technical field of rocket engine performance; the structure comprises an extended nozzle, an upper sub-stage, an interstage section, a lower sub-stage and a ball lock; wherein the upper sub-stage, the interstage section and the lower sub-stage are all barrel section structures; the upper sub-stage, the interstage section and the lower sub-stage are coaxially butted in sequence along the axial direction; the extended nozzle is coaxially arranged in the inner cavity of the interstage section; one axial end of the extended nozzle is fixedly connected to the upper sub-stage; the other axial end of the extended nozzle is connected to the lower sub-stage through a ball lock; the extended nozzle is deployed along the axial direction; the invention further reduces the structural mass of the extended nozzle and improves the overall performance advantage of the extended nozzle technology.

The invention relates to the technical field of car body-in-white hallstands, in particular to a supporting rod structure capable of improving torsional rigidity of a car body, which comprises a V-shaped main body and two inclined struts symmetrically arranged on two sides of the V-shaped main body, the inclined struts face downwards, and the V-shaped main body and the two inclined struts are integrally formed. According to the supporting rod structure, efficient utilization of materials is achieved through the topological optimization technology, the torsional rigidity of the whole vehicle is improved by more than 11%, and meanwhile the manufacturing process is simplified. According to the structure, the innovative layout of the V-shaped main body and the inclined struts is adopted, a plurality of triangular and inverted W-shaped structures are formed, and the stability and the bearing capacity are enhanced. Due to the collinear arrangement of the inclined struts and the V-shaped main body and the design of the trapezoidal bottom, the contact area with an automobile cross beam is increased, and the firmness of connection is ensured. In addition, according to the design, the attractiveness and functionality are balanced, the performance of the vehicle is improved, and wide applicability and market application potential are achieved.

The invention relates to a double-propellant configuration barrel rocket gun, in particular to a smoothbore barrel rocket gun using a double-propellant configuration rocket projectile, and aims to solve the problem that a large-power weapon is long in barrel and large in dead weight due to the fact that killing power of a traditional light weapon and a medium and small caliber gun is limited by barrel bore pressure at present. And the practical requirements that the weapon hit precision is superior to or at least not lower than that of an existing traditional barrel gun and the weapon and ammunition cost does not exceed that of the existing traditional barrel gun can be met. The main technical advantages of the invention are concentrated in the field of medium-and-small-caliber and limited-range direct aiming gun and gun weapons, and can be applied to infantry light weapons, such as pistols (individual self-defense weapons), submachine guns, automatic rifles, sniper rifles and light and heavy machine guns, and medium-and-small-caliber direct aiming artillery, such as tank cannons, antitank cannons, air defense cannons and aviation machine cannons.

The invention discloses a flexible bracket for an angle sensor of a tilting mechanism and an assembly method. The flexible bracket is characterized in that a fixed end bearing seat is fixedly connected with a main shaft; the tilting end bearing seat is fixedly connected with the main shaft and is spaced from the fixed end bearing seat; an inner ring of the bearing is fixedly connected with the fixed end bearing seat, and an outer ring of the bearing is clamped and fixed with the sensor stator bracket through the tilting end bearing seat; the sensor stator bracket is used for fixing an angle sensor stator; the sensor rotor bracket is used for fixing an angle sensor rotor, and the sensor rotor bracket and the sensor stator bracket are coaxially arranged in a relatively rotating manner; the flexible decoupling assembly is arranged between the sensor rotor support and the fixed end bearing seat and is used for generating elastic deformation when the main shaft deforms or vibrates. According to the invention, the fixed end bearing seat, the tilting end bearing seat and the mounting bracket of the angle sensor are integrated into a whole, the structure is simplified, and the reduction of the mounting coaxiality caused by the bending deformation of the main shaft under load can be automatically compensated through the flexible decoupling assembly.

This invention belongs to the field of underwater launch technology, specifically relating to an underwater projectile configuration design. It mainly consists of a projectile body and a pusher block. The projectile body adopts a hollow thin-shell structure, with a stepped structure at the front end and four (or more) evenly distributed 90° inclined slots at the rear. The pusher block is a short cylindrical structure with a through hole in the center, sealed by a sealing membrane. This device is small in size, with a diameter of 8-10 mm, making it suitable for underwater launch.

The invention discloses a steel structure house and a construction method thereof.The steel structure house comprises four stand column beams, and the four stand column beams are arranged at the four corners of the same rectangle respectively; the two horizontal beams and the two vertical beams are arranged on the four sides of the rectangle respectively. The invention discloses a construction method of a steel structure house. The construction method comprises the following steps: S1, fixing a foundation structure and a beam body; s2, damp-proof plate installation; s3, the snakelike liquid storage pipe and a floor are installed; s4, the steel plate with the door and the honeycomb structure wall body are installed; and S5, ceiling and energy supply. By arranging the stand column beams, the horizontal beams, the vertical beams, the honeycomb structure wall bodies and the like and by referring to a honeycomb structure, the strength and stability of the structure are greatly improved while the weight of the structure is reduced, light weight and high efficiency of the building structure are achieved, meanwhile, intelligent adjustment of the indoor temperature is achieved, and the living comfort is effectively improved; meanwhile, natural resources are fully utilized, energy consumption is reduced, and the energy-saving and environment-friendly concept is met.

This invention discloses a vibration damper for an afterburner with an insertion tube, belonging to the design field of afterburners. It includes a vibration damper, a flame stabilizer, and a central cone. The vibration damper is located at the downstream end of the outer bypass channel, closely attached to the inner wall of the afterburner shell, forming a double-wall structure. Cold air from the outer bypass flows through it, cooling the wall surface and absorbing oscillation energy, thus suppressing high-frequency vibrations in the combustion chamber. The flame stabilizer is located in the inner bypass channel, its inner end connected to the central cone. The inner bypass and part of the outer bypass airflow meet here, forming a low-speed recirculation zone, achieving fuel-air mixing and stable ignition. The vibration damper has openings, employing a deep-hole structure with an insertion tube. The insertion tube is placed within a hole in the vibration damper's base, significantly increasing the equivalent neck length of the vibration damper while maintaining the same main plate thickness. This shifts the peak sound absorption frequency towards lower frequencies, improving the vibration damper's absorption capacity for low-frequency oscillation modes in the afterburner.

The invention discloses a bulk carrier hatch deck structure, which comprises a hatch deck, a topside tank vertical plate is fixedly arranged at the bottom of the hatch deck, a transverse stiffener and a plurality of supporting brackets are also fixedly arranged at the bottom of the hatch deck; a longitudinal bone is arranged between the supporting bracket closest to the topside tank vertical plate and the topside tank vertical plate, the longitudinal bone is fixedly connected to the bottom of the hatch deck, and the end of the transverse stiffener is fixedly connected to the longitudinal bone; no brackets are arranged on the end faces of the topside tank vertical plate. The invention can save steel, reduce structural weight, and reduce costs; it can also reduce the number of components, simplify construction technology, and make construction easier.

The invention discloses an intelligent follow-up rotating cockpit system for port mobile machinery, and relates to the technical field of port mobile machinery cockpits, and the intelligent follow-up rotating cockpit system comprises a middle annular sliding rail mechanism and a flexible suspension frame mechanism which are fixed in a cockpit. The flexible suspension frame mechanism is in sliding connection with the annular sliding rail through an arc-shaped sliding plate, and a seat chassis and a seat are installed on the flexible suspension frame mechanism through a spring damping assembly. The annular sliding rail is further rotationally connected with a display screen, the main operation table and the auxiliary operation table are installed on a seat chassis, and the display screen and the seat achieve synchronous follow-up rotation through magnetic coupling. According to the system, a traditional ground rotating base is replaced with the middle annular sliding rail, and the structure is more compact; the flexible suspension frame provides multi-direction vibration reduction, and comfort is improved. According to the invention, the real-time consistency of the operation visual field and the control direction is realized, and the harbor machinery operation efficiency, the man-machine work efficiency adaptability and the long-term driving comfort are obviously improved.

This application relates to the technical field of clamping devices for loading platforms, and discloses a clamping device for a stacker crane loading platform, which includes a mounting frame, a first clamping frame, and a second clamping frame. The mounting frame is mounted on the loading platform, forming a loading area between it and the platform. Both the first and second clamping frames are mounted on the mounting frame and move towards or away from each other synchronously via a power unit. A clamping area is formed between the first and second clamping frames, and this clamping area is located within the loading area. This application improves the stability when conveying filter rod boxes.

The application discloses a high-temperature curing ablation-resistant and heat-insulating two-component coating and a preparation process. The coating is composed of A component and B component. The A component comprises modified epoxy resin, liquid butyronitrile rubber, aluminum hydroxide powder, chromium trioxide, high-silica fiber powder, hollow glass microbead and toluene; the B component is a curing agent and a curing accelerator. In the preparation, the aluminum hydroxide powder, the chromium trioxide, the high-silica fiber powder and the hollow glass microbead are made into a filler dispersion liquid; then the epoxy resin and the liquid butyronitrile rubber are made into a resin-rubber mixture; then the filler dispersion liquid is slowly and uniformly added into the resin-rubber mixture under stirring, and the A component is obtained by soaking in a static magnetic field at room temperature and grinding; the curing agent and the curing accelerator are the B component. By optimizing the coating composition, the ablation resistance and the heat-insulating performance of the coating can be obviously improved by coating a single layer, the construction process is simplified, the coating thickness is reduced, and the high-temperature resistance of the coating is improved.

The invention provides a spacecraft engine support and a design method thereof, and belongs to the technical field of spacecraft structure design. The spacecraft engine support is a combined support and comprises a plurality of thin-shell polyhedral carbon fiber composite material single supports which are independent of one another, and a first single support for installing a main engine serves as a main body support. And the other second to sixth monomer brackets are mounted on the main body bracket and are combined and connected in a manner of mutually gluing and screwing inclined surfaces of the polyhedrons to form the thin-shell polyhedral carbon fiber composite material combined bracket in a complex shape. The combined bracket provides a connecting interface with a spacecraft cabin through a main body bracket for mounting a main engine, and also provides mounting interfaces for a plurality of space layout engines and a large air cylinder outside the cabin. The invention has the advantages of strong adaptability to complex interfaces and large temperature difference environment, good pointing stability and light weight, and provides installation interfaces of multiple groups of main engines and attitude control engines which are intensively installed on the outer side for a light-weight lander cabin.

The utility model discloses a battery pack for an electric aircraft, which comprises a shell integrally arranged in a hollow rectangular shape; the battery cells are arranged in the shell side by side; the fixing plate is arranged in a C shape and is provided with an opening, and the battery cell is embedded into the fixing plate; the cooling fins are integrally formed and vertically arranged at the opening positions of the two sides of the fixing plate. Compared with the prior art, the battery pack has the following advantages and effects: by arranging the mounting structure integrating the fixing plate and the radiating fins, the battery cell can be fixed, the radiating of the battery cell can be ensured, the battery pack is fixed, the structure number and the structure weight are reduced, and meanwhile, the heat transfer efficiency is high and the radiating efficiency is improved due to the integral forming arrangement.

This invention discloses a high lift-to-drag ratio, long-endurance, low-speed airfoil, revealing its maximum relative camber, maximum relative thickness, and the curve equations satisfied by its upper and lower edges. The origin of the coordinate system containing the airfoil is defined as the leading edge of the chord. The X-axis coincides with the chord line, pointing from the leading edge to the trailing edge of the airfoil. The Y-axis is perpendicular to the X-axis, pointing in the direction of the airfoil's curvature. The chord length is defined as C; therefore, the maximum relative camber is 6%C, and the maximum relative thickness is 4.5%C. The airfoil of this invention exhibits a higher lift-to-drag ratio and a higher lift coefficient while maintaining a lower drag coefficient. It reduces the weight of the wing structure, and its thin, curved shape results in a smaller internal wing cavity, optimizing aircraft weight while concentrating stress on the structure.

The application discloses a kind of machine arm joint loosening and folding structure, including center disc cantilever assembly, machine arm folding assembly and threaded sleeve assembly.The application is tightly matched with center disc inner part by threaded sleeve kit, and threaded sleeve kit is pressed tightly machine arm inner part, so that machine arm folding assembly and center disc cantilever assembly are realized stable connection, simultaneously, the threaded sleeve loosening assembly designed can be loosened to threaded sleeve assembly, so as to increase the safety and reliability of unmanned aerial vehicle flight.The first pivot pin and the second pivot pin of the first pivot pin and the second pivot pin connected by machine arm folding assembly and folding adapter are rotated twice around the shaft, so that machine arm folding assembly can be folded to the smallest storage size space without increasing structural weight and complexity when folding without interfering with other components of unmanned aerial vehicle.

A metal composite material mixed type fuselage structure comprises a metal framework structure and a composite material appearance structure embedded in the metal framework structure, based on the stress characteristics of the fuselage structure of a novel basic training plane, a main force bearing structure adopts the metal framework structure, a non-main force bearing fuselage appearance adopts a full composite material structure, and according to the stress magnitude and function difference of all parts, the main force bearing structure and the non-main force bearing fuselage appearance are combined. Different composite material structures are adopted, so that the weight of the fuselage structure is reduced, riveting assembly is reduced, and the surface quality of the fuselage is improved; on the basis of meeting the lightweight requirement of the aircraft structure, the structural strength and safety of the composite fuselage are effectively improved.