1080 results about "Tailplane" patented technology

The invention discloses an unmanned aerial vehicle suitable for microwave reconnaissance interference equipment and an equipment antenna arrangement method, and belongs to the field of unmanned aerial vehicles. The unmanned aerial vehicle comprises a fuselage, wings and an empennage. The fuselage comprises a fuselage head, a fuselage body and a fuselage tail. The wings adopt upper single wings and are mounted at the top of the fuselage; the empennage is installed at the tail of the fuselage. The head of the fuselage adopts a nose cover made of wave-transparent materials, a plurality of forward interference antennas are mounted in the nose cover, lateral interference antennas and reconnaissance antenna arrays are mounted on fuselage skins on two sides of a fuselage main body, a plurality of backward interference antennas are mounted in an engine cover made of wave-transparent materials at the tail of the fuselage, and propellers at the tail end of the unmanned aerial vehicle are made of wave-transparent materials. Through the conformal design of the unmanned aerial vehicle and the antenna, the influence of the antenna on the aerodynamic performance of the unmanned aerial vehicle is reduced to the maximum extent, the aerodynamic layout of the unmanned aerial vehicle is optimized by combining the antenna arrangement, and the task antenna is not shielded.

The invention relates to an empennage structure of a flapping-wing robot, which comprises a yawing mechanism, a pitching mechanism and a connecting mechanism, the yawing mechanism comprises a yawing steering engine, a yawing steering engine rocker arm, a yawing rocker arm and a yawing control surface; the pitching mechanism comprises a pitching steering engine, a pitching steering engine rocker arm and a pitching surface; the connecting mechanism comprises a pitching steering engine fixing plate, an empennage surface plate and a fuselage. The pitching motion function of the empennage is achieved through the knuckle bearing and the connecting rod structure, the yawing motion function of the empennage is achieved through the flexible material, the steering engine rocker arm and the yawing rocker arm, the yawing structure and the pitching structure are combined through the empennage plane plate, and the whole empennage mechanism is formed. The yawing motion cannot be affected during pitching motion, decoupling of the pitching motion and the yawing motion is achieved, meanwhile, the yawing control steering engine and the pitching control steering engine are both installed on the fuselage, empennage structural parts are reduced, the loading capacity during empennage motion is reduced, and the beneficial effects of being compact in structure and high in adjusting capacity are achieved.

The invention belongs to the field of electric vertical take-off and landing aircrafts, and discloses a novel vertical take-off and landing remote high-speed manned electric tilt-rotor aircraft structure which comprises an aircraft body, wings, a V-shaped empennage, six supporting arms, six tilt-rotor units, an energy system, an avionics system and an undercarriage. The six tilting rotor wing units are symmetrically installed on the wings and the V-shaped empennage through the six supporting arms. The aircraft is mainly characterized in that the design of six tilting rotor units is adopted, so that the aircraft has the advantages of vertical take-off and landing, high-speed forward flight, no structural'dead weight 'and useless power consumption; the design that the supporting arms extend out of the wings and the empennage to exceed the radius length of the rotors is adopted, and the downward projection of a rotor disc is not overlapped with the wings and the empennage in the vertical flight state, so that downward washing flow of the rotors cannot generate downward loads on the wings and the empennage, and power consumption for overcoming the downward loads is avoided; the design of the wings with high aspect ratio and winglets is adopted, so that the forward flying lift-drag ratio and the cruising efficiency are improved, and the aircraft has high-speed forward flying and remote flying capabilities; and the six tilting rotor units adopt the same tilting mechanism, so that the complexity of design and manufacturing is reduced.

The invention discloses a bionic robot with walking, jumping and taking-off functions and a movement method, and belongs to the technical field of robots. The robot comprises a control system, a flapping wing mechanism and two leg mechanisms. Each leg mechanism comprises a driving device I, an execution connecting rod mechanism and a buffer foot part, the buffer foot part is connected with the execution connecting rod mechanism, and the execution connecting rod mechanism is driven by the driving device I; the flapping wing mechanism comprises a driving device II, a transmission mechanism, wings and an empennage; the execution link mechanism is connected with the transmission mechanism, the wings and the empennage are respectively connected with the transmission mechanism, the transmission mechanism is driven by the driving device II, the control system is used for controlling the driving device I and the driving device II, and the motion modes comprise walking, jumping and flying. The multi-mode bird-simulating robot has a multi-mode bird-simulating motion function, can autonomously realize mode switching from land motion to air flight, and remarkably improves the motion performance of the robot.

The utility model discloses a cylindrical launch folding wing unmanned aerial vehicle which comprises an unmanned aerial vehicle body, the unmanned aerial vehicle body comprises a square fuselage and a conical nose cover, a concave platform is arranged below the middle rear section of the fuselage, foldable wings are arranged in the concave platform, foldable empennages are arranged on the two side faces, close to the tail, of the fuselage, and the tail of the fuselage is connected with the tail of the fuselage. A foldable propeller is arranged at the tail of the fuselage, two blades of the propeller can be folded and retracted into an upper arc-shaped groove and a lower arc-shaped groove, close to the tail, of the fuselage respectively, a pod, a parachute cabin and a GPS antenna cabin are integrated in the nose cover, and a load cabin, a battery cabin and an equipment cabin are sequentially arranged at the front section, the middle section and the rear section of the fuselage. According to the cylindrical launching folding wing unmanned aerial vehicle, the design of the conical nose cover, the square fuselage, the lower single wing and the V-shaped empennage is adopted, launching is carried out through the square launching cylinder during launching, a plurality of cabin sections are designed in the square fuselage, each cabin section is fully utilized under the condition that the gravity center of the unmanned aerial vehicle is proper, and the assembly efficiency is greatly improved.

The invention belongs to the technical field of airplane structure design, and discloses a horizontal tail wing beam connecting structure, an airplane and an assembling method, and the horizontal tail wing beam connecting structure comprises a central rib plate, an upper T-shaped connector, a lower T-shaped connector, a left connecting plate, a right connecting plate and an outer side connecting plate. The upper T-shaped joint comprises a lower edge strip, a first left edge strip and a first right edge strip, the lower T-shaped joint comprises an upper edge strip, a second left edge strip and a second right edge strip, the central rib plate is arranged between the left beam and the right beam, and the left connecting plate, the right connecting plate and the outer side connecting plate are combined for use, so that the bearing capacity of a left beam web plate and a right beam web plate is improved; the first left edge strip and the first right edge strip can increase the contact area between the upper T-shaped connector and the left wing and the contact area between the upper T-shaped connector and the right wing, the second left edge strip and the second right edge strip can increase the contact area between the lower T-shaped connector and the left wing and the contact area between the lower T-shaped connector and the right wing, the connecting strength of the left beam and the right beam in the vertical direction is improved, and the lower edge strip, the upper edge strip and the central rib plate are matched with one another. And the connection strength of the left beam and the right beam in the horizontal direction is improved.

The invention belongs to the technical field of flight mechanics, and particularly relates to a V-shaped empennage control surface course control extension control method which comprises the steps that a left control surface deflection angle reaches an upper limit, a right control surface deflection angle continues to deflect leftwards, and a right empennage generates right lower lift increment perpendicular to the incoming flow direction; the right empennage can simultaneously generate a vertically downward force and a head-up torque relative to the gravity center of the whole aircraft; a downward head lowering moment is generated through the longitudinal periodic pitch change of the rotor wings and the tilt angle of the rotor wings, so that the pitching moment is balanced; the vertical force balance of the whole aircraft is achieved by adjusting the attack angle of the aircraft body.

The invention belongs to the technical field of aerodynamic wind tunnel tests, and discloses a test device and method for a dynamic derivative wind tunnel test, and the device comprises an aircraft model which is formed by assembling a nose, a middle fuselage, a rear fuselage, a balance, wings and an empennage; the oscillation mechanism is provided with an adapter, and the adapter is connected with the balance; and one end of the wind tunnel strut is connected with the wind tunnel attitude control system and the other end is connected with the oscillation mechanism. The problem that an existing dynamic derivative wind tunnel test model and a test device are low in efficiency is solved, heaving, sidesway, yawing, pitching and rolling oscillation of the model are achieved by replacing the adapters, and the test efficiency of a dynamic derivative wind tunnel test can be effectively improved.

The intelligent bionic ornithopter with the body and the self-adaptive attack angle adjusting joints comprises an ornithopter body, wings and an empennage, the wings and the empennage are arranged on the ornithopter body, driving motors are symmetrically arranged on the flapping portions of the wings, and each driving motor is provided with a limiting joint; the limiting joint comprises an outer ring, an inner ring and an elastic cushion block, the outer ring is composed of a plane end and first protruding parts, the plane end and the driving motor are connected and rotate synchronously, the first protruding parts are located on the two sides of the plane end and provided with penetrating holes, the inner ring is a cylinder, and the inner ring is arranged between the first protruding parts and swings with the middle of the plane end as the center. The inner ring and the penetrating hole are matched and jointly sleeved and fixedly connected with the edge of the wing, a second protruding part is arranged on the inner ring, and elastic cushion blocks are arranged at the upper end and the lower end of the second protruding part. The invention aims to provide the bionic ornithopter which can fully simulate flapping wing flapping actions of flying organisms and can adaptively adjust the attack angle in the flapping process so as to improve the flapping lift force and reduce the resistance.

The utility model discloses a flapping wing aircraft adopting bionic feathers as flapping wings. The flapping wing aircraft comprises a main beam assembly, a power assembly, a wing assembly and an empennage assembly, the power assembly is connected with one end of the main beam assembly, the empennage assembly is connected with the other end of the main beam assembly, and the wing assemblies are connected with the two sides of the power assembly in a mirror image mode and are in spherical hinge joint with the main beam assembly. The wing assembly comprises a wing main rod, a plurality of feather shafts and a plurality of feather pieces, one end of the wing main rod is connected with the power assembly, the feather shafts are connected to the wing main rod at intervals, and the feather pieces are rotationally connected to the feather shafts respectively; with the feather pieces and the rotating point of the feather shaft as a boundary, the feather pieces on the two sides of the rotating point are bent towards the two sides in opposite directions, and the adjacent feather pieces are in lap joint. The utility model has the beneficial effects that the flapping resistance of the wings is small, and the wings have the capability of flying in rainy days.

The invention provides a wing type biological hybrid flapping wing aircraft with deformable wings. The wing type biological hybrid flapping wing aircraft comprises a flapping mechanism, a wing deformation mechanism, bird feather type wings, an aircraft body, an empennage deformation mechanism and a bird feather type empennage, the flapping mechanism and the empennage deformation mechanism are mounted on the fuselage; the flapping mechanism drives the wing deformation mechanism to do wing flapping motion; the bird feather type wings are arranged on the wing deformation mechanism; the empennage deformation mechanism comprises an empennage joint and a plurality of steering engines, the steering engines drive the empennage joint to do four-degree-of-freedom motion, and the bird feather type empennage is installed on the empennage joint. The multi-degree-of-freedom cooperative connecting rod transmission mechanism is adopted, high-fidelity reproduction of bird flapping wing motion is efficiently achieved, and independent and accurate regulation and control of the torsion angle, the torsion rate and the torsion direction of the empennage are achieved based on hierarchical steering engine control and the decoupling characteristic of the double-layer motion frame.

The invention discloses a novel bird-imitating empennage multi-degree-of-freedom platform, and relates to the technical field of flying robots, the novel bird-imitating empennage multi-degree-of-freedom platform comprises a first driving structure, a support, a second driving structure, an empennage driving structure and an empennage assembly, the second driving structure and the empennage driving structure are both arranged on the support, the first driving structure can drive the empennage assembly to rotate in the heading direction, and the second driving structure can drive the empennage assembly to rotate in the pitching direction and the rolling direction. And the empennage driving structure can control the area change of the empennage assembly. According to the novel bird-imitating empennage multi-degree-of-freedom platform, control over the heading direction, the rolling direction and the pitching direction can be achieved, and the area of the empennage assembly can be changed.

The invention relates to a mobile device communication method and device, a mobile device, a readable storage medium and a program product. The mobile device comprises an empennage which is provided with an antenna array and is adjustable in pitching angle; the method comprises the following steps: determining a target pitch angle of an empennage required by the mobile device for satellite communication; according to the moving information of the moving device in the moving process, the acting moment borne by the empennage in the moving process is determined; adjusting the pitch angle of the empennage to a target pitch angle according to the acting moment; and under the condition that the empennage is at the target pitch angle, adjusting the phase difference between communication signals of each antenna unit in the antenna array so as to perform satellite communication for the mobile device through the antenna array. The method can improve the communication efficiency of the mobile device.

The invention relates to an electric spoiler of an automobile, which comprises a lower base assembly fixed on a tail door metal plate; the upper base assembly is connected with the lower base assembly through a section of lifting mechanism assembly; the main spoiler assembly is fixed on the upper base assembly; and the outward opening spoiler assembly is connected with the upper base assembly through a two-section lifting mechanism assembly. Through the cooperation of the first-section lifting mechanism assembly and the second-section lifting mechanism assembly, the purpose of multi-section opening of the automobile spoiler is achieved, the high lifting height and the large overturning angle of the automobile spoiler are achieved, the function of a high-performance vehicle on the spoiler is achieved, meanwhile, when the automobile spoiler is closed, the whole mechanism can be compactly folded, occupied space is reduced, and the cost is reduced. The aesthetics and the space utilization efficiency of the vehicle are improved, and the manufacturing cost and the maintenance difficulty are reduced.

The invention discloses a mechanical linkage posture stabilizing pull-type submersible. The pull-type submersible comprises a cabin, an empennage assembly, an inertia assembly and at least one pair of side wings. The side wings are rotatably arranged on the side walls of the cabin body through second rods; the inertia assembly comprises a balance weight part, a main shaft and a gear structure, the balance weight part rotatably sleeves the main shaft, the tail end of the main shaft is connected with the empennage assembly, the gear structure is rotatably arranged on the inner side wall of the cabin body, and the balance weight part is connected with the gear structure; the counter weight part deviates from the central axis of the cabin body, relative rotation between the counter weight part and the cabin body can drive the paired side wings to rotate in the opposite directions through the gear structure, and movement of the counter weight part and the main shaft relative to the cabin body can drive the empennage assembly to be opened and closed. The pull-type submersible is provided with the inertia assembly, the inertia assembly achieves passive posture stabilization of the pull-type submersible through relative movement of the balance weight piece and the cabin body, and the pull-type submersible can be widely applied to the technical field of ocean exploration.

The invention belongs to the field of vertical take-off and landing aircrafts, and relates to a distributed contra-rotating rotor hybrid tilting rotorcraft. Comprising a front tilting electric contra-rotating rotor nacelle, a front cabin body, a wing end tilting electric contra-rotating rotor nacelle, a V-shaped empennage, a V-shaped empennage aileron, a vertical empennage, a retractable undercarriage, a green hybrid power energy system and an empennage tilting electric contra-rotating rotor nacelle, the front tilting electric contra-rotating rotor nacelle is hinged with the other end of the front cabin body; an empennage tilting electric contra-rotating rotor nacelle is arranged at the end part of the V-shaped empennage; wing end tilting electric contra-rotating rotor wing nacelles are arranged at the ends of the wings; and rotor wing units are arranged in the rotor wing nacelles, the six rotor wing units all adopt a coaxial reverse upper and lower two-paddle structure, and the rotating directions of the rotor wings in the six rotor wing units are that the adjacent rotating directions and the opposite rotating directions are opposite.

Provided in the present application are a vertical take-off and landing aircraft and a control method therefor. The vertical take-off and landing aircraft comprises a fuselage and 2N tilt-rotors. Wings are provided on two sides of the fuselage, and an empennage is provided at the tail of the fuselage, an elevator rudder being provided on the empennage. The 2N tilt-rotors are symmetrically mounted on two sides of the fuselage, and some of the 2N tilt-rotors are located on the empennage, where N is a natural number greater than or equal to 2. In a vertical take-off and landing state, the projections of propellers of the 2N tilt-rotors on the horizontal plane are centrally symmetrical about point B, both the point B and the center of gravity G of the vertical take-off and landing aircraft are located in the symmetrical plane of the fuselage, and the point B is located on the side of the point G close to the empennage. During the transition of the vertical take-off and landing aircraft from the vertical take-off and landing state to a cruising state, both the point G and the point B move along the symmetrical plane towards the side close to the nose, and the point B is always located on the side of the point G close to the empennage. Such a layout enables the vertical take-off and landing aircraft to have a better pitch trim capability.

The utility model discloses an ornithopter with wings and an empennage capable of actively deforming. The ornithopter comprises a fuselage, a driving mechanism, the empennage and a wing folding mechanism, the driving mechanism is mounted on the machine body; the wing folding mechanisms are symmetrically installed on the two sides of the fuselage, and vertical flapping and folding movement of wings are achieved through steering engines and crank and rocker mechanisms in the driving mechanisms. The empennage is installed at the tail of the fuselage, deflection of the empennage in the horizontal direction and the vertical direction is achieved through the two small steering engines, and empennage attitude adjustment in the flying process is achieved. According to the ornithopter with the wings and the empennage capable of being actively transformed, the wings can be actively unfolded and folded in the flying process, the aerodynamic characteristics of the wings can be changed, efficient flying is achieved, and the wings and the empennage can be adjusted by adjusting the empennage. The flapping-wing air vehicle is more stable in flight attitude under the working conditions of taking off, landing, turning, gliding, hovering and the like, and the defects that an existing flapping-wing air vehicle is few in foldable wings, uncontrollable in folding, unstable in flight and the like are overcome.

The invention provides an ornithopter with multi-degree-of-freedom empennage collaborative movement and a control method.The ornithopter comprises a rack, empennage bodies and an empennage driving mechanism, each empennage body comprises an empennage support, a plurality of tail feather bodies, a traction rope guide wheel and a tail feather elastic rope, and one end of each tail feather body is sequentially hinged to one end of the empennage support; the number of the traction rope guide wheels is two, the traction rope guide wheels are arranged in the middle of the empennage support side by side, the tail feather elastic rope is sequentially connected to the multiple tail feather bodies, and the two tail feather bodies on the outermost side are each provided with a connecting part extending towards the other side of the hinged end. The empennage driving mechanism comprises an empennage connecting pipe assembly, a traction steering engine, a winding roll, a traction rope, an empennage torsion steering engine, an empennage deflection steering engine and an empennage pitching steering engine. According to the empennage structure, independent control or combined control of torsion, pitching, deflection and opening and closing actions can be achieved, and the problems that an existing ornithopter empennage mechanism is insufficient in motion freedom degree and lacks an efficient wing-empennage cooperative motion system are solved.

The invention relates to the technical field of unmanned aerial vehicles, in particular to a passive tilting wing unmanned aerial vehicle which comprises a vehicle body, wings, a locking mechanism, a vertical empennage, a thrust power assembly, a posture regulation and control power assembly and a controller, and the thrust power assembly, the posture regulation and control power assembly and the locking mechanism are all electrically connected with the controller. The locking mechanism is responsible for locking angles of the wings in a vertical take-off and landing state and a cruising flight state, the thrust power assembly is arranged on the wings, the wings are rotationally connected with the fuselage, and the thrust power assembly is responsible for generating lift force for vertical take-off and landing and thrust force for cruising flight. The device can also be used for providing underwater thrust during water surface navigation; the passive tilting wing unmanned aerial vehicle can solve the technical problems that an existing tilting wing aircraft is heavy in tilting mechanism, poor in loading capacity, complex in aerodynamic characteristic in the tilting process, large in robustness control difficulty, poor in stability and the like.

An aircraft comprising a fuselage with a nose and a tail arranged on opposite parts to each other along a first longitudinal axis is described; a pair of half-wings arranged on respective mutually opposite sides of the fuselage; a first and a second rotor carried by respective half-wings, respectively rotatable around a second and third axis inclinable with respect to said fuselage, and independently operable from each other; the aircraft is switchable between a first hovering flight or take-off / landing configuration wherein the fourth and fifth axis are arranged orthogonal to said first axis; and a second forward flight configuration wherein the fourth and fifth axis are arranged parallel or inclined with respect to said first axis; the aircraft further comprising a tail portion comprising a first aerodynamic surface, and a third and a fourth rotor rotatable around a fixed fourth and a fifth axis; and support means of the third and fourth rotor connected to a corresponding said half-wing and to a corresponding said fin.

The invention provides a high-fuel-efficiency double-fuselage layout passenger plane and a design method. The high-fuel-efficiency double-fuselage layout passenger plane comprises fuselages, wings, empennages and a power device. The machine body comprises a first machine body and a second machine body which are arranged in parallel in bilateral symmetry; the wings are fixedly arranged above the middle parts of the first fuselage and the second fuselage, and the empennage is fixedly arranged above the tail parts of the first fuselage and the second fuselage; the power devices are symmetrically arranged at the front edges of the left side and the right side of the wing in a wing-hung double-sheet bureau mode. The high-fuel-efficiency double-fuselage layout passenger plane and the design method have the characteristics of energy conservation and emission reduction, the design method and the internal layout design method of the corresponding double-fuselage layout passenger plane are provided, and energy conservation and environmental protection are achieved by minimizing the weight of the fuselage structure and fully utilizing the internal space of the fuselage. And the method has the potential of bringing more operating profits to airlines.

The present disclosure relates to an autonomous, electric, vertical takeoff and landing (VTOL) aircraft that is low-noise, safe, and efficient to operate for cargo transportation over relatively long ranges. A VTOL aircraft includes a fuselage, a plurality of arms, a tail, and a plurality of propulsion systems mounted on the arms and the tail. The plurality of arms have parts that are rotatable and the tail has a part that is rotatable for transitioning the VTOL aircraft between a forward-flight configuration and a hover configuration.

The utility model relates to the technical field of storage and transportation equipment of empennages of unmanned aerial vehicles, in particular to a loading structure of an empennage of an unmanned aerial vehicle, which comprises two frame bodies arranged at an interval, and the interval between the two frame bodies forms an accommodating space of an empennage body; each frame body comprises an upper cross beam and a lower cross beam which are vertically arranged at an interval, and an oblique beam is jointly welded at the front ends of the upper cross beam and the lower cross beam; a plurality of supporting plates are welded between the lower cross beams of the two frame bodies; a plurality of empennage fixing plates are mounted between the oblique beams of the two frame bodies through screws; and a trailing edge mounting plate and a trailing edge middle supporting plate are mounted between the upper cross beams of the two frame bodies through screws. The loading structure provided by the utility model is simple in structure, can load the empennage body and the tail edge of the wing at the same time, and effectively improves the loading efficiency. The loading structure is used for loading the empennage body and the tail edge of the wing, so that the whole can be conveniently put into a container for transportation.

The invention relates to the technical field of aircrafts, in particular to a variable-attack-angle double-section flapping-wing aircraft which comprises an aircraft body, a power source and driving system, a double-section-wing flapping system left wing, a double-section-wing flapping system right wing, an attack angle adjusting driving system and an empennage adjusting driving system. Wherein the fuselage serves as a main body structure of the aircraft and is used for supporting and fixing other functional modules; the power source and the driving system are mounted on the fuselage and are used for providing power for the flapping wing to move; a left wing and a right wing of the double-section wing flapping system are mounted on the power source and the driving system.According to the variable-attack-angle double-section flapping-wing aircraft, in the flapping-wing flight process, by adjusting the attack angles of the wings in real time, the lift force and resistance distribution of the aircraft in different flight states can be optimized, and therefore the flight efficiency and stability are improved; the variable attack angle design enables the aircraft to better cope with a complex airflow environment.

The utility model discloses a solar unmanned aerial vehicle, and particularly relates to the technical field of unmanned aerial vehicle equipment, the solar unmanned aerial vehicle comprises a fuselage, wings, an empennage and a power system, the fuselage is internally provided with a cabin for placing a control system and an effective load, and the upper surfaces of the wings are provided with solar cell panels electrically connected with the power system. The control system is connected with the solar cell panel and stores electric energy collected by the solar cell panel, the control system is in signal connection with the power system and controls the power system to provide power, and the two sides of a middle-section horizontal wing of the wings are fixedly connected with two outer-section wings with dihedral angles of the wings respectively. The middle-section horizontal wing is fixedly connected to the top of the fuselage, a plane formed by the symmetry axis of the fuselage and the symmetry axis of the middle-section horizontal wing is perpendicular to the middle-section horizontal wing, one end of the fuselage is fixedly connected with the empennage through a connecting piece, and the power system is installed on the wing. The unmanned aerial vehicle can carry loads, has long endurance time, and can enable the flight process to be more stable and safer.

The invention belongs to the technical field of electric heating deicing, and particularly relates to a surface heating electric heating film and a preparation method thereof. Comprising an outer surface insulating layer, a heating layer, a power supply electrode and an inner surface insulating layer, the heating layer is prepared from a carbon-based conductor composite polymeric material in a printing or coating mode, and the carbon-based conductor composite polymeric material is formed by mixing polyimide resin and carbon fibers (or one or more of graphene, carbon nanotubes and the like). The surface heating electric heating film provided by the invention has the characteristics of simple and reliable structure, light weight and surface heating performance, can be applied to ice prevention and removal operation of parts such as aircraft wings, empennages, propellers and the like, and has relatively high practical application value.

The utility model discloses an empennage lifting structure with a large overturning angle and a high lifting height. The empennage lifting structure comprises a supporting base. The lower end of the main driving arm is connected with a main driving shaft and is fixed on the supporting base through a pin shaft; the auxiliary driving arm is connected with the upper end of the main driving arm through a pin shaft; the rear end of the main supporting rod is fixed to the supporting base through a pin shaft, and the upper end of the auxiliary driving arm is connected to the middle section of the main supporting rod through a pin shaft; the auxiliary connecting rod assembly comprises an auxiliary linkage rod; an auxiliary lower supporting rod; an auxiliary upper supporting rod; wherein two ends of the mounting bracket are respectively connected with the front end of the main support rod and the auxiliary upper support rod through pin shafts. According to the auxiliary connecting rod assembly, the principle that the three simple supporting rods rotate around the middle shaft, and the length of the auxiliary rod is expanded and contracted is applied, the tail wing can be contained in a small space when being closed and can be unfolded when being supported in the working process, and a high lifting height and a large overturning angle are provided for a spoiler of the tail wing.

The invention provides an aircraft overall optimization design method and device and electronic equipment, and relates to the technical field of aircraft overall design. The method comprises the following steps: calculating the weight of each part of an aircraft based on aircraft design parameters, and calculating the maximum takeoff weight and the gravity center of the whole aircraft by integrating the weight and the gravity center of each part; based on airplane design parameters and the gravity center of the whole machine, parametric modeling is conducted on all the components, pneumatic calculation is conducted, and a lift-drag analysis result is output; establishing an engine performance model according to the engine type and the engine performance parameters, and generating a power curve and an oil consumption curve based on the model; calculating a plurality of aircraft performance indexes; and performing multi-objective optimization by taking the shape parameters of the wing empennage as design variables and taking a plurality of aircraft performance indexes as optimization objectives, and generating a Pareto optimal solution set containing an optimal value combination of the shape parameters of the wing empennage. The defects of subject conflict and long research and development period caused by the adoption of a serial design process in the existing aircraft design are overcome.

The utility model relates to the technical field of automobile spoilers, in particular to an adjustable automobile spoiler metal casting which comprises a main wing plate, and sliding grooves are formed in the two end faces of the main wing plate in the length direction. Auxiliary wing plates are slidably mounted at the two sliding grooves, and a plurality of fixing grooves are formed in the bottoms of the two auxiliary wing plates in the length direction; side wing plates are fixed to the ends, away from each other, of the two auxiliary wing plates. Fixing parts are fixed at the two ends of the bottom of the main wing plate; the top end of the fixing plate penetrates through the fixing base and sequentially penetrates through the top of the fixing base and the top of the support in a sliding mode, and the top end of the fixing plate can penetrate through the bottom of the main wing plate in a sliding mode and is matched with the corresponding fixing groove in an inserted mode. The auxiliary wing plates are installed in the sliding grooves in the two ends of the main wing plate in a sliding mode, the auxiliary wing plates on the two sides can be conveniently adjusted to stretch out and draw back, and the using requirements of different vehicle types are met; and meanwhile, the fixed plate is matched with the fixed grooves in different positions in an inserted manner, so that the adjusted aileron plate can be limited, and the mounting stability of the aileron plate is ensured.