1485 results about "Tailplane" patented technology

The present disclosure relates to an aircraft including two or more propulsive devices, and a fuselage integrated with a pair of wings to create a Blended Wing Body (BWB) structure, wherein an orientation of the fuselage and the pair of wings change based on a transition of the aircraft from a vertical position to a horizontal position. Further, each wing of the pair of wings includes a lower winglet and an upper winglet that are identical and coupled to each other at a wing tip. The aircraft further includes a plurality of elevons controlled by two or more propellers associated with the two or more propulsive devices.

The utility model discloses an aircraft, and relates to the field of aircrafts, the aircraft comprises a fuselage, wings are symmetrically arranged on two sides of the fuselage, and an empennage is arranged at the tail part of the fuselage; the plurality of first mounting seats are arranged on the wings and / or the empennages; the plurality of first-class motor systems and the plurality of second-class motor systems are arranged on the plurality of first mounting seats in a one-to-one correspondence manner; and the plurality of battery units are respectively and correspondingly connected with the plurality of first-type motor systems and the plurality of second-type motor systems. According to the technical scheme, the balance of the batteries of the aircraft is improved.

The invention provides an aircraft, and relates to the technical field of aircrafts. The aircraft comprises a fuselage, tilting rotors and fixed rotors. Wings are arranged on two sides of the fuselage, and an empennage is arranged at the tail of the The tilting rotors are symmetrically arranged on at least one of the empennage, the wings and the fuselage, each tilting rotor comprises a first propeller and a first electric engine, the first electric engines are in transmission connection with the first propellers, and the first electric engines are integrated electric engines. The fixed rotors are symmetrically installed on the wings on the two sides of the fuselage, each fixed rotor comprises a second propeller and a second electric engine, the second electric engines are in transmission connection with the second propellers, and the second electric engines are distributed electric engines. The aircraft can solve the problems that the size, weight and heat dissipation efficiency of an existing electric engine are difficult to consider, and efficient flight of the aircraft is difficult to achieve.

The invention belongs to the related technical field of bionic flapping-wing robots, and discloses a water-air amphibious bionic flapping-wing robot with chordwise bimodal flapping wings, which comprises a main body, the chordwise bimodal flapping wings, an empennage, a cross-medium mechanism, a control unit and a flexible skin, the main machine body is a main supporting component of the robot, and the chordwise bimodal flapping wings are installed on the left side and the right side of the main machine body and oscillate up and down in a reciprocating mode to drive the flexible skin covering the chordwise bimodal flapping wings to generate power. The empennage is fixed to the rear end of the main fuselage to assist the robot in posture adjustment. The cross-medium mechanism is installed at the front end of the main machine body and used for providing impulsive force for cross-medium movement of the robot. And the control unit is connected with each component through a signal line. The bionic flapping-wing robot has an overwater motion mode and an underwater motion mode in the chordwise direction of the flapping wing, the overwater motion mode is beneficial to generation of lift force in the air, the underwater motion mode is beneficial to reduction of power consumption in water and concentration of power in the thrust direction, and the use environment and scene of the bionic flapping-wing robot are expanded.

The invention discloses a distributed electric propulsion box type wing ground effect aircraft which comprises a main fuselage, the two sides of the main fuselage are connected with one ends of sweepback wing main wings, one ends of two empennages above the tail of the main fuselage are connected with the main fuselage through vertical tails, and the other ends of the two empennages are connected with the other ends of the two main wings through end plates respectively. The empennage is connected with a plurality of high ducted fans directly driven by a motor, an elevator and an aileron are arranged at the rear part of the empennage, a rudder is arranged at the rear part of the vertical fin, and the elevator, the aileron and the rudder are controlled by a flight control system and are mutually independent. The ground-effect aircraft provided by the invention adopts a box-type wing structure formed by combining the sweepback main wing and the sweepforward empennage, has better aerodynamic performance in a take-off and climbing low-speed flight state, and can provide larger lift force and better maneuvering characteristics.

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 discloses a small tandem wing unmanned aerial vehicle folding mechanism which comprises a pair of front wings, a pair of rear wings, a pair of vertical empennages and a fuselage, the front wings and the rear wings are in tandem wing layout on the fuselage after being unfolded, and in a folding state, the pair of front wings rotate backwards around a front rotating shaft to coincide with the back of the fuselage, and the pair of vertical empennages rotate backwards around a rear rotating shaft to coincide with the back of the fuselage. The pair of rear wings rotate forwards around the rear rotating shaft to coincide with the bottom of the fuselage, and the pair of vertical empennages rotate downwards to coincide with the side face of the fuselage. A front spring support is installed on the back of the fuselage and located at the front end of the front rotating shaft, and the pair of front wings is connected with the front spring support through tension springs. A rear spring support is installed at the bottom of the fuselage and located at the rear end of the rear rotating shaft, and the pair of rear wings is connected with the rear spring support through tension springs. The tandem wing layout is adopted, the front wings and the rear wings serve as lift wings, the area of the wings is increased, the size of the unmanned aerial vehicle is reduced, and combat maneuverability is improved.

A vertical take-off and landing aircraft with a multi-element lifting system with integrated propulsion. The multi-element lifting system may have an upper wing element, a lower wing element, and a control wing element which is located below the upper wing element and above, and rearward of, the lower wing element. The system uses internal propulsion units, such as internal ducted fans, which flow air below the upper wing element and above the lower wing element such that the air flows through the multi-element lifting system. The control wing element may be articulated to route air vertically downward to allow for short or vertical take-off and landing. An aircraft with a multi-element wing assembly and a multi-element tail assembly raised above the wing assembly. An aircraft which resides on the ground with the wing assembly and the tail assembly pitched up.

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.

According to the modularized traffic tool with multiple take-off modes, through the innovative split modularized design, the form of the traffic tool can be flexibly changed between an automobile and an aircraft, the flight state and the land running state are switched, and more novel passenger and freight application scenes can be expanded through cooperation of the independent carrying cabin modules. By utilizing the tiltable ducted fan mechanism and by virtue of boosting of the autonomous traveling chassis, the composite wing flight module can realize vertical take-off and landing, and wing lift force can be provided for short-distance taxiing take-off and landing to reduce energy consumption, so that the purposes of large voyage and high load are finally realized. The foldable fixed wing, the horizontal tail and the telescopic tail wing structure ensure that the traffic tool is small in size when running and parking on the land, so that the requirements of existing urban and rural roads and traffic safety laws and regulations can be met, and actual popularization is more facilitated.

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 discloses an intelligent empennage control method and related equipment, relates to the field of empennage control, and mainly aims to solve the problem that an existing intelligent empennage control method is not comprehensive and intelligent enough. The method comprises the steps that empennage influence parameters of a target vehicle are obtained, the empennage influence parameters comprise active influence parameters and passive influence parameters, the active influence parameters are determined based on active behaviors of a driver, and the passive influence parameters are obtained based on objective conditions of the target vehicle and the external environment; determining empennage control data based on the empennage influence parameters; and adjusting the empennage of the target vehicle based on the empennage control data. The method is used for the empennage intelligent control process.

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 amphibious transport plane based on the ground effect comprises a plane body, a main wing and a vertical empennage, the main wing is located behind the gravity center of the plane body, a pair of forward-swept front wings are further arranged in front of the gravity center of the plane body, and the vertical empennage is arranged on the main wing; a first propeller is arranged on each of the left and right sides of the head of the fuselage; a pair of second propellers is arranged at the front end of the main wing; a fault step is arranged in the middle of the fuselage. The aircraft has the beneficial effects that the aircraft obtains a great lift-drag ratio in a ground effect area by utilizing the ground effect, the aircraft is lifted up through an airflow air cushion, and the airflow angle of the engine is accurately controlled by utilizing a popular engine tilting technology, so that the aircraft is prevented from falling off. Therefore, low-oil-consumption, large-load, short-distance take-off and low-speed landing are achieved, and the take-off and landing performance of the seaplane is greatly improved.

The invention discloses a vertical take-off and landing fixed-wing aircraft, and relates to the technical field of aircrafts. According to the invention, the conversion from a multi-rotor flight mode to a fixed-wing flight mode and from the fixed-wing flight mode to the multi-rotor flight mode can be easily realized. Due to the structural layout characteristics of the aircraft, the safety of the aircraft is guaranteed, and the aircraft can be safely and reliably landed according to the fault degree and urgency of the aircraft even if the aircraft breaks down seriously and only forced landing can be selected. Through multi-rotor-wing assisting control, the forced landing buffering function of the telescopic empennage assembly and the safety protection measure of a protection sponge lining in the manned cabin, various safety modes and measures such as an internal safety protection air bag, an external safety protection air bag and a forced landing parachute of the manned cabin can be selectively used according to the fault degree and urgency of the aircraft; and safe or low-damage forced landing of the aircraft is realized.

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.

According to the rotary folding empennage of the aircraft and the using method, two or more empennages are arranged at the tail of a fuselage of the aircraft, each empennage is connected with a steering engine, each empennage is divided into a first empennage section and a second empennage section, the two empennage sections are connected through a folding and unfolding mechanism, and folding and unfolding of the empennages can be achieved. The first empennage is provided with a rotating shaft which penetrates through the fuselage tail skin to be connected with the steering engine, a gap is formed between the empennage and the fuselage tail, and when the empennage is in a folded state, the second empennage is close to the fuselage tail; when the empennage is in an unfolded state, the second empennage body rotates around the hinge to be flush with the first empennage body, after the empennage is unfolded, the empennage can rotate along with the rotating shaft under driving of the steering engine, and control over the flight attitude of the aircraft is achieved.

The invention discloses a bionic flexible flapping wing underwater robot which comprises a shell, two side wing flapping mechanisms located on the two sides of the shell, an empennage flapping mechanism located at the tail of the shell, a camera cabin located at the front end of the shell, a steering engine control cabin located at the front end of the interior of the shell and a gravity adjusting cabin located at the rear end of the interior of the shell. The side wing flapping mechanism comprises a side wing steering engine, a flapping assembly and a flexible side wing fin surface, the flapping assembly comprises a flapping transmission assembly, a fixing rod and a plurality of fin rays, one end of each fin ray is connected with the flapping transmission assembly, the middle of each fin ray is penetrated by the fixing rod, the other end of each fin ray is connected with the side wing fin surface, and the side wing steering engine is connected with and drives the flapping transmission assembly to drive one end of each fin ray to swing; all the fin rays are not in the same plane, and when the fin rays swing, the fin surfaces of the side wings swing in a wave shape. The device simulates the structural form, the motion characteristic and the driving mechanism of the natural aquatic organism manta ray, and has the characteristics of low noise, high maneuverability, small size, portability and high concealment.

The invention provides a supersonic-speed jet adopting supersonic-speed double wings and variant design, and belongs to the field of novel supersonic-speed civil aircrafts, a large-area truncated delta wing with edgings on the inner side is adopted, an engine nacelle is arranged on the upper portion of the outer end of the large-area truncated delta wing, and the supersonic-speed double wings are installed on the outer side of the nacelle; the front edges and the rear edges of the upper wing and the lower wing of the supersonic double-wing adopt intelligent materials to realize a variant function; the empennage can rotate around a mounting shaft in the longitudinal direction of the airplane to change the inclination angle; the front edge and the rear edge of the supersonic double-wing are deformed, and the inclination angle of the empennage is changed to jointly form a supersonic state and a subsonic state. The problem that the conventional double-wing non-design-point performance is poor is solved, high aerodynamic performance can be achieved within the flight envelope range, and it is guaranteed that an aircraft achieves ideal supersonic speed environment-friendly performance such as acoustic explosion and noise and aerodynamic efficiency.

The invention discloses a bimorphic high-speed unmanned aerial vehicle capable of taking off and landing on the water surface and flying in ground effect and a control method, and belongs to the technical field of unmanned aerial vehicles, the bimorphic high-speed unmanned aerial vehicle comprises a vehicle body and a control device, the vehicle body is provided with an adjustable turbine jet driving mechanism and telescopic folding wings, and the tail of the vehicle body is provided with an empennage and a tail turbine jet driving mechanism. Meanwhile, the invention discloses a control method based on the two-form aircraft capable of taking off and landing on the water surface and flying in the ground effect, and the two-form high-speed unmanned aerial vehicle capable of taking off and landing on the water surface and flying in the ground effect and the control method are adopted. By adjusting the inclination angle, the distance and the height of the two front turbojet engines, operation and conversion of various forms of water sailing, ground running, ground effect flight and height flight are achieved, the use scenes of the unmanned aerial vehicle are greatly enriched, and the requirement for high-speed flight is met by adopting the telescopic folding wings.

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.