41results about How to "Improve rudder efficiency" patented technology

The invention relates to a split type booster efficient rudder, which divides a rudder blade into an upper part and a lower part by taking the propeller axis as a boundary, wherein the two parts are independent from each other and are in steering control respectively; the shapes and the sizes of the upper rudder blade and the lower blade can be different; the cross sections of the upper rudder blade and the lower blade can be asymmetrical wing sections with cambers; the balance position (maintaining direct route of a ship at the moment of out of steering or being called as amidship) of the upper rudder blade and the lower rudder blade is arranged by deflecting a certain degree toward the rotation direction in a staggered manner to form an X-shaped structure in a horizontal plane according to the rotation direction of a propeller; the upper rudder blade and the lower rudder blade are respectively provided with an upper rudder blade tiller and a lower rudder blade tiller; and the upper rudder blade tiller of the upper rudder blade is a hollow shaft, the lower rudder blade tiller of the lower rudder blade is a solid shaft, and the upper rudder blade tiller is sheathed on the lower rudder blade tiller to form a coaxial mode. When at the balance position, the biggest fluid power can be obtained, and manipulation can be completed by breaking the balance of side force. The invention has the advantages of improving steerability by making full use of the wake flow characteristics of the propeller and having the capability of self boosting, thus being suitable for manipulation of various ships.

The invention relates to a flapped rudder transmission device. The device comprises a main rudder and an auxiliary rudder, wherein the main rudder and the auxiliary rudder are rotatably hinged together in parallel. The upper end of the main rudder is provided with a rudderstock, and the lower end of the rudderstock is fixedly connected with the main rudder. A sleeve barrel is arranged outside andis moveably matched with the rudderstock. The device is characterized in that the space between the upper end of the auxiliary rudder and the sleeve barrel is provided with a guide rod, the guide rodis horizontally arranged, the external end of the guide rod is fixed on the upper end of the auxiliary rudder, and the internal end points to the sleeve barrel. A sliding sleeve is arranged on the guide rod, and an upper connecting shaft and a lower connecting shaft are respectively fixed on the upper lateral face and the lower lateral face of the sliding sleeve. The upper connecting shaft and thelower connecting shaft are respectively provided with a bearing seat and a bearing, and the two bearing seats are respectively connected together with the sleeve barrel by an upper connecting plate and a lower connecting plate. The flapped rudder transmission device has long service life and higher rudder effect under small rudder angle, and is applicable to ships.

The invention relates to the field of thrusters and discloses a universal thruster. The universal thruster comprises a shell (2) and a propeller (1). A joint bearing (3) is installed in the shell (2), the propeller (1) is installed on a spherical inner ring (31) of the joint bearing (3), a pushing guide rod (4) is installed on the spherical inner ring (31) and connected with a pushing motor (5), and the joint bearing (3) drives the propeller (1) to swing under the pushing function of the pushing guide rod (4). Steering of the universal thruster does not depend on steerage generated when water flow flows past a control surface but depends on vector thrust force which is more direct, so the steering radius is very small, and high steering torque can be generated even under a dead slow condition. The universal thruster has the advantage of being high in steerage and is particularly suitable for military unmanned underwater vehicles.

The invention provides a triangular-section power draft-increase ballast-free semi-submersible conveying ship. The ship comprises a main ship body, a power draft-increase system and a control system. The main ship body comprises an upright rounded-triangular-cross-section parallel body, a flow inflow section and a flow removal section, the upright rounded-triangular-cross-section parallel body is designed in an optimized mode to adapt to underwater near-surface sailing, the flow inflow section and the flow removal section downward incline to a blunt bow and a conical stern respectively. The power draft-increase system is a multi-wing combined system, comprises board side fixed negative lift horizontal wings, a controllable main lift adjusting wing combined appendage and stern lift adjusting horizontal wings, and is used for adjusting vertical force of the ship body under various loading conditions to achieve the optimal semi-submersible draft. The control system comprises a variable wing type section forward-leaning upright column, an inward-leaning light invisible upper construction part, shallowly submerged piercing hydrofoils and a stern controllable vertical wing, and is used for controlling the course and stability of the ship body. The ship is novel in type and high in subsequent expansion performance, is a tool for navy land battle force hiding, quick delivery and emergency transport of special civil materials in a route, and has certain research and application value in military and civil fields.

The invention discloses a miniature double-flapping-wing aircraft capable of autonomous stability augmentation control and a three-degree-of-freedom control moment generation method thereof. The miniature double-flapping-wing aircraft specifically comprises two identical driving systems, a lifting force system and a control system, the two driving systems are connected through a middle connectingstructure, and the driving systems drive the lifting force system to generate a lifting force; the control system changes the lift system to generate control torque. The aircraft can efficiently generate pitching, rolling and yawing three-axis control torque, estimates aircraft state information through a complementary filtering and Kalman filtering algorithm, and performs autonomous stability augmentation control. The aircraft has the autonomous stability augmentation flight capacity, the yawing performance is improved emphatically, rolling and yawing are controlled only by changing the tension degree of the wing films, gravity center changes unfavorable for control are avoided, and lift force losses in the stability augmentation control process are reduced.

The invention relates to a folding double-face rudder and an underwater vehicle with the double-face rudder. The double-face rudder comprises two rudder faces arranged oppositely and a base connectedbetween the two rudder faces. The folding double-face rudder has the beneficial effects that the double-face rudder has the high rudder effect relative to a single rudder face, and under the conditionof the same aspect ratio, the double-face rudder has larger control force and control torque; the double-face rudder can be folded to the tail of the vehicle, the mounting size is reduced, and when acarrying platform suffers from size limiting, the vehicle with the folding rudder faces has high adaptability; according to the vehicle controlled by the double-face rudder, the posture of the vehicle can be effectively adjusted under the conditions of a low speed and a high speed; and relative to other underwater vehicles, the underwater vehicle has the advantages of being simple in structure and flexible in control form and has the characteristics of energy saving, high efficiency and stability especially for the underwater high-speed navigational status.

The invention discloses a dismountable tilting-power flying wing-type hybrid lift airship, and solves the problems existing in the aerodynamic optimization design of wings and a floating body, the design of a stabilizing surface and a control surface, and the connection mode of a nacelle, the wings and an airship body. The overall aerodynamic layout is determined through numerical analysis, and a fixed wing and a rotor wing are combined. In the respect of connection of the nacelle and the wings, the airship body is fabricated in three sections for allowing a carbon rod space to be reserved, and then the nacelle and wing motors are connected to the airship body by using carbon rods. The control mode adopts vertical tailless control, the direction of the airship is controlled through the differential motion between the two motors, and pitch control can be achieved by matching with a tilting angle. The dismountable tilting-power flying wing-type hybrid lift airship disclosed by the invention has the advantages of a fixed wing aircraft and a rotor wing aircraft, overcomes the disadvantages of conventional airships, and can be widely applied to military and civil fields.

The invention discloses a tail rudder of an underwater vehicle, which comprises a housing, a steering gear, a steering gear mounting plate, a tail wing plate, a steering gear plate shaft, a steering gear plate, a bevel gear and a steering gear shaft. Three steering gear lug plates and three rudder shaft lug plates are uniformly arranged at equal distances in the housing; three rudder platforms arearranged on the outside, and rudder shaft lug plates are arranged on the inside of the rudder platforms; the steering mounting plate is screwed on the steering gear lug plate, and three groups of steering gears are arranged on the steering gear mounting plate; at that out end of the rudder platform and the steering gear plate bevel gear, a flap rudder is arranged; and at the outer end of the rudder platform and the rudder plate bevel gear, a flap rudder is arranged. The steering gear bevel gear and the rudder plate bevel gear are mutually meshed and driven. The invention adopts a three-axis rudder tail rudder arrangement mode, which saves cost and improves system reliability. The control model is simplified and the control difficulty is reduced; it has compact structure and high stability. The rudder plate adopts the flap structure to improve the rudder efficiency and the attitude control ability of the underwater vehicle. The electromagnetic interference is reduced, the stress structure of the rudder shaft is improved, the damage probability of the rudder shaft caused by the trailer is reduced, and the safety of the rudder shaft is improved.

The invention relates to a flap-type rudder. The flap-type rudder comprises a rudder blade component, a sleeve component and a transmission mechanism, wherein the rudder blade component comprises a main rudder blade and a flap; the flap is hinged on the main rudder blade and arranged at the rear part of the main rudder blade; the flap is controlled through the transmission mechanism; the transmission mechanism comprises a transmission guide rod, a guide rod bushing and a pin shaft; the flap is connected with the sleeve component; upper ends of the main rudder blade and the flap are provided with an upper rudder bearing; and an upper rudder bearing supporting plate and a lower rudder bearing supporting plate are arranged on the upper rudder bearing. After the structure is adopted, a rudder of a sub rudder blade controlled by a follow-up mechanism is attached to the rear part of the main rudder blade is a sub rudder; and the sub rudder is the flap; and the flap-type rudder is suitable for ships sailing in multi-turn channels so that the maneuverability of the ship is improved.

The invention provides a tilting mechanism with a control surface. A horizontal control surface is mounted on a long side of a horizontal control surface frame; and two vertical control surfaces are correspondingly mounted on one long side of a vertical control surface frame. The horizontal control surface and the vertical control surfaces are all positioned on the same side of a control surface mounting frame. A motor is fixed at a cross-shaped center formed by the horizontal control surface frame and the vertical control surface frame. Two ends of a tilting shaft are correspondingly fixed between an upper connecting piece and a lower connecting piece. A horizontal control surface steering engine is mounted at one end of the horizontal control surface frame of the control surface mountingframe; and vertical control surface steering engines are correspondingly mounted at the two ends of the vertical control surface frame of the control surface mounting frame. According to the tiltingmechanism with the control surface, by using the attached control surface, the tilting mechanism can self-balance moment, the resisting ability to outside airflow interference is higher, and the desired mounting accuracy is lower; the attitude can be more easily controlled in a vertical take-off and landing state or a lower flying speed state; the tension of a rotor is 10.13 N under conditions ofno aircraft body shielding and 9000 revolutions per minute; and the aerodynamic efficiency is enhanced.

The invention relates to a controllable pitch propeller capable of improving a rudder effect. The invention provides the controllable pitch propeller capable of improving the rudder effect. The controllable pitch propeller capable of improving the rudder effect comprises a propeller shaft and propeller hubs; the two ends of the propeller shaft are main engines connected with the propeller hubs; atotal separate type pitch control mechanism is arranged at the tail end of the propeller shaft; the total separate type pitch control mechanism comprises blade root bearing discs, slide blocks, push-pull rods and connecting keys; the push-pull rods are transitional from the propeller shaft, are divided into four parts and adopt dovetail joint structures; and each two push-pull rods are connected with each other. The slide blocks and the blade root bearing discs are arranged on the push-pull rods; the slide blocks are connected with the blade root bearing discs through the connecting keys; andthe slide blocks are in non-tight connections with both the push-pull rods and the blade root bearing discs. The controllable pitch propeller capable of improving the rudder effect has the advantagesthat the rudder effect in the ship sailing process can be effectively improved, the structure is simple, convenient and flexible, the layout is compact and the controllable pitch propeller is especially suitable for medium and large ships.

The invention discloses an amphibious unmanned vehicle with front-mounted double bodies on inclined sides and three bodies on water surface. Second sheet bodies and side bodies are arranged on the left side and the right side of a boat bow of a middle boat body, the side bodies are fixedly connected with the middle boat body through the horizontal second sheets, a front propeller and a rear propeller are arranged on each second sheet body, the middle of a stern part of the middle boat body is connected with a water entry boat body through a perpendicular first sheet body, each propeller is connected with a brushless motor which is connected with an electronic speed governor, and the electronic speed governor is connected with a battery pack and a controlling system through cables; the two front-mounted propellers are fixed on the sheet bodies, outer ends of two rear-mounted propellers in the boat width direction are connected with the sheet bodies through bearings, inner ends are connected to two ends of a first transmission shaft, a pair of driving rudders are connected with two ends of a second transmission shaft, and the middle parts of the first transmission shaft and the second transmission shaft are connected with a transmission system. The amphibious unmanned vehicle has high steerability and good manipulation effect, and can guarantee stability of voyage and operation.

The invention discloses a small high-speed loitering munition based on visual image precision guidance. A duct motor is arranged at the tail of a high-speed loitering platform, a visual navigation system is arranged at the front lower part of the high-speed loitering platform, and a high-specific-energy lithium battery, a link, a flight control system and a combat part are arranged in the high-speed loitering platform. The small high-speed loitering munition achieves the technical effects that the weight and the size meet the requirements of individual soldier carrying and use; the combat efficiency is high; the lift-drag ratio is increased through a wingtip end plate, the transverse direction stability is enhanced, and the rudder effect is enhanced through the duct fan wake flow; wings serve as a force bearing structure and a battery shell at the same time, structural weight is saved, the wings and a vehicle body are designed separately, independent charging and storage are facilitated, and safety is high; a duct fan motor is used for providing thrust, the flight speed is high, and the cost is low; multi-node two-way information transmission is adopted, single-shot use can be achieved, and cluster battle is also facilitated; and the loitering height is low, the self target is small, the flying speed is high, and the survivability is high.

The invention discloses a flap type rudder structure. One side of the tail part of a main rudder blade is arc-shaped and sunken inwards, and a flap is arranged at the arc-shaped sunken part of the main rudder blade; a telescopic rod and a rudder blade cover with a guide rail are installed at the top and the bottom of the main rudder blade respectively, the tail end of the telescopic rod is connected with the two ends of a flap rudder stock through bearings, a driving rod is installed on a supporting rod connected to the flap rudder stock, and the end of the driving rod is connected with the guide rail through a sliding block. When the main rudder blade is located in the middle of a ship, the flap contracts to the arc-shaped sunken part on one side of the tail portion of the main rudder blade, and the whole flap rudder is in a symmetrical wing shape. When the flap type rudder needs to be adjusted, the telescopic rod drives the flap to extend out to a set distance, and then the driving rod drives the flap to steer, so that the total area of the flap type rudder is changed, and the camber required by sailing is obtained. Through the arrangement of the flap type rudder structure, the total area of the rudder blade of the flap type rudder can be conveniently and quickly changed, so that the requirements of different navigational speeds on the rudder effect are met, the rudder effectin a low-speed state is effectively improved, or the ship resistance in a high-speed state is reduced.

The invention discloses a marine fishtail rudder which comprises a rudder blade, a first tail plate and a second tail plate; the rudder blade comprises a first rudder surface and a second rudder surface, the first tail plate is hinged to the first rudder surface, and the second tail plate is hinged to the second rudder surface; a motor is arranged in the rudder blade and used for driving the first tail plate and the second tail plate to rotate, so that the tail edge of the first tail plate and the tail edge of the second tail plate are close to or away from the tail edge of the rudder blade. According to the marine fishtail rudder disclosed by the invention, tail plates are respectively arranged on two rudder surfaces at the tail part of the rudder, and the tail plates are rotated through a motor; and during steering, the tail plate is opened to form a rudder shape of a fishtail rudder, so that a relatively high rudder effect is obtained. During direct navigation or backing, the tail plate is closed to form a rudder shape of a streamline rudder, so that the resistance of the rudder is reduced.

The invention relates to a semi-spade rudder cavitation probability reducing device. The semi-spade rudder cavitation probability reducing device comprises at least two upper flow guiding devices fixed on upper part positions of a spade rudder arm and at least two lower flow guiding devices fixed on lower part positions of a rudder blade, wherein an upper rubber flow guiding piece of a luffing side board rotates to a certain angle around a fixing shaft under the effect of the rudder blade and is close to the rudder blade during luffing a semi-spade rudder, the upper rubber flow guiding piece on the other side is close to the rudder blade under the effect of incoming flow, the surfaces of the flow guiding pieces and the rudder blade are in smooth transition, so that turbulent flow and cavitation phenomena are avoided, and the upper rubber flow guiding pieces of a left board and a right board are automatically close to the rudder blade under the effect of the incoming flow when a rudder angle is recovered to 0 degree; upper spring devices and lower spring devices are arranged between shaft sleeves corresponding to the lower flow guiding devices and lining sleeves corresponding to the lower flow guiding devices, the upper spring devices are used for limiting the clockwise rotation of lower rubber flow guiding pieces, the lower spring devices are used for limiting the anticlockwise rotation of the lower rubber flow guiding pieces, and under the effects of the upper spring devices and the lower spring devices, the lower rubber flow guiding pieces invariably have trends of recovering to initial positions and are close to the spade rudder arm.

The invention discloses an efficient leading edge distributed propeller aircraft power layout, and particularly relates to the technical field of aircrafts. The efficient leading edge distributed propeller aircraft power layout comprises a plurality of electric propellers distributed on fixed wings on the two sides of an aircraft, the multiple electric propellers are symmetrically arranged in front of the fixed wings, and each electric propeller is provided with a nacelle connected with the corresponding fixed wing, the electric propellers at the wing tips of the fixed wings are located rightin front of the front edge points of the fixed wings, and the centers of the other propellers are all located above the front edge points of the fixed wings. By the adoption of the technical scheme, the problem that all distributed propellers of an existing aircraft are distributed right in front of the leading edge points of the wings, and consequently the aerodynamic performance of the aircraftis affected is solved, and the layout can be used for aircraft design.

The marine elastic rudder comprises a rudder stock, a rigid frame and an elastic rudder body, the rudder stock is fixedly connected with the rigid frame, the rigid frame comprises a head sealing body, a middle body and a tail sealing body which are sequentially connected in the chordwise direction, the elastic rudder body comprises a shell and a filling body, the shell is connected with the head sealing body and the tail sealing body, and the filling body is connected with the shell. A containing cavity is defined by the outer shell and the middle body, and the filling body is arranged in the containing cavity; and when the rudder is in a steering state, the elastic rudder body on one side of the incident flow surface of the rudder is stressed to contract, and the elastic rudder body on one side of the back flow surface of the rudder is stressed to expand. During direct navigation, the section of the rudder blade is in a symmetrical airfoil shape, and resistance is small; during steering, the section of the rudder is in an asymmetric airfoil shape, larger lift force can be generated, and therefore the steering effect is effectively improved.

The invention discloses a variable-area rotatable bionic horizontal tail wing, and belongs to the technical field of aircraft. The tail wing comprises a flat tail rotating mechanism, a flat tail deflection control mechanism and variable area mechanisms, wherein one end of the flat tail rotating mechanism is fixed to the center position of the tail part of a machine body, the other end of the flattail rotating mechanism is connected with the flat tail deflection control mechanism, the two groups of variable area mechanisms are symmetrically arranged on the two sides of the flat tail deflectioncontrol mechanism correspondingly, the flat tail rotating mechanism comprises a motor, a motor base and a first rotating shaft, the flat tail deflection control mechanism comprises a first steering engine, a first connecting rod, a second rotating shaft and a tail wing supporting frame, the first steering engine is fixedly mounted at the output end of the first rotating shaft, and the variable area mechanisms comprise second steering engines, second connecting rods, fixing plates, first long rods, second long rods and a plurality of feathers. The tail wing has the heading operation capacity and can integrally rotate around the axis of symmetry, after rotating at a certain angle, the lateral area is increased, and it means that the tail wing can bring a heading moment.

The invention relates to a ship device with excellent slewing maneuverability, which is composed of a rudder blade assembly, a sleeve assembly and a transmission mechanism. The rudder blade assembly is composed of a main rudder blade and flaps, and the flaps are on the rudder blade and arranged at the rear of the main rudder blade, the flap is controlled by a transmission mechanism, the transmission mechanism is composed of a transmission guide rod, a guide rod bushing and a pin shaft, the flap is connected with the sleeve assembly, The upper ends of the main rudder blades and flaps are provided with an upper rudder bearing, the upper rudder bearing is provided with an upper rudder bearing support plate and a lower rudder bearing support member, and the front end of the upper rudder bearing support plate is provided with a fan-shaped baffle; after adopting the above structure , a rudder of an auxiliary rudder blade controlled by a servo mechanism is attached to the rear of the main rudder blade. manipulative.

The invention discloses a ship line with a stern transom plate and a balanced rudder blade designing method. The ship bottom at the mounting position of a ship body rudder blade takes the shape of a combined ship body cyclogenesis plane; the combined ship body cyclogenesis plane comprises a ship body cyclogenesis curved plane, a ship body cyclogenesis horizontal sector plane, a ship body cyclogenesis column plane and a ship body cyclogenesis column plane lower end surface; for a streamline rudder blade, the upper end surface of the rudder blade is a curved plane parallel to the ship body cyclogenesis curved plane; and for a flat-plate rudder blade, the upper end line of the rudder blade is a curved line parallel to the ship body cyclogenesis curved plane. According to the invention, within all rotation angle ranges of the rudder blade, the shape of the upper edge of the rudder blade and the shape of a ship bottom plate are always kept parallel, so that the clearance can be minimized and an optimal space is always kept; therefore, the rudder effect is effectively enhanced, the operability of the ship is improved and energy is saved.

The invention discloses a device for controlling the gap flow of a combined control surface of an aircraft, which comprises a front section of a rudder and a rear section of a rudder, and a gap is provided between the front section of the rudder and the rear section of the rudder; it is characterized in that: a flow blocking surface is provided between the gaps , the choke surface is made of flexible water-proof material, and the choke surface is at the same height as the rear section of the rudder; the two opposite sides of the choke surface are detachably connected to the front section of the rudder and the rear section of the rudder respectively, and the connection is located at the rudder Mid-section of the fore and aft rudder sections; the spoiler is fully deployed when the maximum rudder angle is reached. The invention can effectively control the flow in the gap of the combined control surface, improve the flow field around the control surface, slow down the occurrence of flow separation, significantly improve the rudder effect when the rudder angle is large, and improve the maneuverability of the aircraft; it can make the control surface stall Angle increases, which effectively shortens the turning radius of the aircraft and improves the safety of the aircraft's navigation; it is easy to refit the existing control surfaces without redesigning the control surfaces.