64 results about "V-tail" patented technology

The invention is directed to an actuation system in an aircraft comprising a fuselage and a hinged tail section with at least one interlock component that engages a tail support, wherein the engagement of the tail support to the tail section enables the actuation system to operate. The actuation system pulls in, latches, and locks the tail section during closing of the tail section, and the actuation system unlocks, unlatches, and releases the tail section during opening of the tail section.

A method for preventing the loops from not containing the steel tail features that the load head signal of down stream rolling mill is used as the loop lifting command, the load tail signal of upstream rolling mill is used as the loop lowering command, and the load signal of the first rolling mill is directly used as the control signal of the loop lifters for the next three rolling mills.

Aircraft, such as tri-body aircraft, and associated methods of manufacture. In one embodiment, a tri-body aircraft has a fuselage with a forward portion extending at least partially forward of an aft-mounted main wing and first and second aft portions extending at least partially aft of the main wing. The forward fuselage portion and the first and second aft fuselage portions can include passenger cabins that are connected, allowing passengers to travel between the cabins during flight. In another embodiment, the aircraft includes a propulsion system having a first engine nacelle positioned at least proximate to the first aft fuselage portion, a second engine nacelle positioned at least proximate to the second aft fuselage portion, and a third engine nacelle positioned atop an inverted V-tail extending upwardly from the first and second engine nacelles.

The invention relates to a positioning drive mechanism for an aircraft full-movement V tail. The positioning drive mechanism comprises a rudder shaft, an upper bearing sleeve, an upper joint bearing, a cylindrical positioning sleeve, a connection key, a semi rocker arm, a cone positioning sleeve, a lower bearing sleeve, a lower joint bearing, a shaft end cover, an upper bearing base, a lower bearing base, a servo actuator and a servo actuator bracket, wherein the upper bearing base and the lower bearing base are connected with an aircraft body frame to form a box-shaped structure so as to increase bending resistance and torsion resistance of the support structure, the upper joint bearing and the lower joint bearing provide rotation support for the rudder shaft, the semi rocker arm is connected with the rudder shaft through the connection key so as to change a load output by the servo actuator into a torque for driving the rudder shaft to deflect, the cone surfaces of the lower bearing sleeve and the lower bearing base are matched to perform centering, and the cylindrical surface matching position of the lower bearing sleeve and the lower bearing base is provided with threaded half holes to auxiliarily load and unload the full-movement V tail. According to the present invention, reliable positioning drive and convenient loading and unloading of the rudder surface of the aircraft with characteristics of large size, inclined angle and dual pivot point cantilever support are concurrently achieved.

The invention discloses a novel trans-domain multiphibious carrier, which includes a fuselage, a tail, a V-tail, a landing gear, first to second wings, first to second buoys, first to fourth hydrofoils, first to fourth angle adjustment modules, first to second deflection motors, first to second power motors, first to second built-in propellers, and first to second auxiliary flight modules. The invention adopts unique shark-like shape design, has excellent aerodynamic and hydrodynamic performance, and can realize rapid motion under water and in the air. The use of hydrofoils enables the vehicleto move quickly and flexibly on the water surface, and the use of tilting ducts and tilting propellers enables the vehicle to move vertically and flexibly. The carrier of the invention has the characteristics of a tilting aircraft, a hydrofoil boat and a submarine.

The invention relates to a horizontal taking-off and landing two stage to orbit (TSTO) reuse aerospace plane layout. A first-stage aircraft and a second-stage aircraft are included, and the second-stage aircraft and the first-stage aircraft are in up-down horizontal parallel layout; the second-stage aircraft is in wing body combination body layout with a wedge-shaped head, a fusion edge strip, a small-span-chord-ratio sweepback thin wing and a central vertical fin; and the first-stage aircraft is in wing body combination body layout of a cathedral sweepback wing with the waverider characteristic, a downwards-folding wing tip and a V tail. The horizontal taking-off and landing TSTO reuse aerospace plane layout meets the TSTO flight principle based on the turbine based combined cycle (TBCC),the design demands of the whole speed domain, the whole airspace lift-drag matching, push-resistance matching, operation-stability matching, volume-weight matching and the like are reached, and the closure of the TSTO technical scheme in the conceptual design stage is achieved.

The invention discloses a selective catalytic reduction (SCR) tail-gas after-treatment system fault diagnosis instrument, which comprises a controller network (CAN) communication module, a microcontrol unit, a storage device, a display screen, a keyboard and a power supply. The CAN communication module is electrically connected with an SCR tail-gas after-treatment system and an engine. The microcontrol unit is electrically connected with the CAN communication module and the display screen. The storage device is electrically connected with the microcontrol unit, and the keyboard is electrically connected with the microcontrol unit. The power supply is electrically connected with the microcontrol unit. Due to the adoption of the SCR tail-gas after-treatment system fault diagnosis instrument, the fault of the SCR tail-gas after-treatment system can be accurately judged, the fault finding time can be shortened, and convenience in use and carrying also can be realized.

The invention relates to a V-tail unmanned aerial vehicle with an oil tank embedded into a blended wing body. The unmanned aerial vehicle can be used to execute flight missions such as scientific experiments, remote sensing, aerial photographing and the like. The unmanned aerial vehicle is characterized in that: 1) the duration of flight is long and flight missions with high requirements can be conducted conveniently; 2) the use is simple and the operation is convenient; 3) the stability is good and devices such as autopilots, aerial photographing cameras, video cameras and the like can be carried; and 4) the requirement on taking-off and landing conditions is low. According to one aspect of the invention, the small unmanned aerial vehicle comprises a body (1), wings (3), an empennage (7), a left front oil tank (16), a left rear oil tank (15), a right front oil tank (13) and a right rear oil tank (14), wherein the wings (3) are connected on the body (1); and the left front oil tank (16) is arranged at the left front of the internal part of the body (1), the left rear oil tank (15) is arranged at the left rear of the internal part of the body (1), the right front oil tank (13) is arranged at the right front of the internal part of the body (1) and the right rear oil tank (14) is arranged at the right rear of the internal part of the body (1). According to the further aspect of the invention, the left front oil tank, the right front oil tank, the left rear oil tank and the right rear oil tank are respectively provided with shapes adaptive to the wing profile of the body and balanced oil consumption sequences.

The invention provides a method for qualitatively and quantitatively analyzing long straight side chain cyclane and alkylbenzene of hydrocracking tail oil, and belongs to the technical field of qualitative and quantitative analysis of detailed physical properties of the hydrocracking tail oil. The GC-MS is adopted for qualitatively analyzing compositions in raw materials and quantitatively analyzing the detailed compositions of the long straight side chain cyclane and alkylbenzene. The analytical method comprises the following steps: preparing samples; dissolving a sample HVGO5 by normal hexane; performing the qualitative analysis; and adopting an SIM method to draw an external standard curve to quantitatively analyze the detailed compositions of the long straight side chain cyclane and alkylbenzene. By comparing with different analytic methods, the method suitable for qualitatively analyzing the long straight side chain cyclane and alkylbenzene of the hydrocracking tail oil is established; moreover, the method for considering the influence of a response factor is adopted in the quantitative analysis, so that the problem of the quantitative calculation for materials without master standards is solved.

The invention discloses a redundancy architecture method for a flight control system for a large-scale medium-high-altitude reconnaissance and attack integrated unmanned aerial vehicle. The flight control system comprises three parts, namely a flight sensor, a redundancy flight control computer and an execution mechanism. According to the redundancy architecture method for the flight control system, corresponding redundancy design is carried out on each part; the flight control computer part adopts a three-redundancy hardware architecture based on FlexRay and Can buses; and the execution mechanism part comprises an aileron steering engine, a V-tail steering engine, a front wheel steering engine, an air door steering engine, an accelerator steering engine and a propeller speed regulation steering engine. The method has the advantages that the corresponding redundancy design is carried out on all the components of the flight control system, the three-redundancy flight control computer and the distributed architecture design based on the FlexRay and Can buses enable the system to eliminate the Byzantine General's fault, and therefore the reliability is improved, meanwhile, the expansibility is high, the structure is simple and flexible, and the maintenance cost is low, and the like; and the system can simultaneously meet the requirements of high reliability, low cost and high costperformance of the unmanned aerial vehicle.

The invention relates to an automatic skiving machine for the head and tail of a shoe last, which mainly solves the problem that in the prior art, when the head and tail allowances of a last is skived, only a manual operation method can be adopted, thereby resulting in low production efficiency and poor skiving effect, so that the quality of products is influenced. The automatic skiving machine comprises a rack, the rack is provided with a positioning device, a head dresser and a tail dresser, a sliding frame formed in such a way that a hydraulic cylinder on the head dresser is connected with the sliding frame carries out a linear reciprocating motion along a sliding rail and drives a first ring tool to cooperate with the head of a shoe last, and a sliding plate formed in such as way that a hydraulic cylinder on the tail dresser is connected with the sliding plate can slide upwards and downwards along the surface of the tail end of the last so as to drive a second ring tool to cooperate with the tail end of the shoe last. Because the head and tail of a shoe last are subjected to dressing by using the fully automatic skiving machine, the production efficiency is high, and the head and tail of the shoe last are dressed smoothly and completely, and the product quality is high.

The invention discloses an aerodynamic layout of a high altitude long flight time tandem wing aircraft adopting a tail wing with high back wing support and belongs to the field of aerodynamic layout designs of aircrafts. According to the aerodynamic layout disclosed by the invention, the aircraft comprises a cylindrical section body, front wings and a rear wing with a large aspect ratio, V-shaped tail wings and a vertical fin, wherein the front wings are lower single wings and are symmetrically mounted on the front half section of the body; totally two V-shaped tail wings are symmetrically mounted on the rear half section of the body; the rear wing is mounted at the tip of the V-shaped tail wings in a V tail supporting manner; the vertical fin is mounted below the tail of the body; and an engine is mounted above the tail of the body. Large elongation can be avoided by using the tandem wing layout under the condition that the same wing area is guaranteed, the requirements on the structural strength and rigidity of the wings are further reduced, the weight of the aircraft is lightened, and the effective load is increased; and with the adoption of a reasonable aerodynamic surface fit manner, the aircraft has excellent flight stability and controllability under the condition that excellent aerodynamic characteristics are guaranteed.

A tail-wheel-free combined left-turning driven disk plow is a drive tillage implement, consisting of a drive tillage disk and a moldboard plow, and having the advantages of low oil consumption, low traction resistance, high production efficiency and high oil penetrating performance. The structure of the disk plow comprises a suspension bracket assembly, a central transmission assembly, a main beam, a side transmission box assembly, a disk tillage component assembly, a right side plate, a tail plow assembly, and on the like. With the adoption of the implement, the complex tail wheel device is eliminated and the machining cost and the raw material consumption are reduced; the lateral force is mainly balanced by a plow side plate of the moldboard plow arranged on the tail part, so the balancing property is high, the disk plow is suitable for paddy field dry tillage and dry land tillage, and capable of being developed and used in large dry farming areas, so that the novel tillage implement which saves energy, reduces emission, enhances gain and reduces cost is provided to the agricultural industry.

The invention discloses a built-in V tail vane surface driving mechanism. The built-in V tail vane surface driving mechanism comprises a machine body and a vane surface. Steering engines for providing driving power, first tumblers for being connected with the steering engines, a second tumbler for driving the vane surface, a third tumbler for being in transmission driving connection with the second tumbler, and connecting rods for being in transmission connection with the first tumbler and the third tumbler are arranged in the machine body. The first tumblers are steering engine pieces for connecting the steering engines with the connecting rods, the second tumbler is a driving stirring piece directly connected with the vane surface in a matched mode and used for driving the vane surface, and the third tumbler is a shaft seat transmission stirring piece and is in driving connection with the driving stirring piece through an arranged stirring piece connecting shaft. The built-in V tail vane surface driving mechanism is convenient to assemble, more reliable in driving and more attractive in appearance, and the internal space of the machine body can be more effectively utilized through modular installation of an overall framework.

The invention relates to a simplified model design method suitable for mechanism research of a complex hypersonic aircraft. The design of the complex hypersonic aircraft is simplified according to thefollowing simplified design criteria to obtain a simplified model for mechanism research; and the complex hypersonic aircraft is a two-stage parallel aircraft. The simplified model comprises a first-stage simplified model and a second-stage simplified model which meet the original parallel relation, the simplified design criterion is that the two-stage simplified model removes the appearance endof an original second-stage standard model, and other characteristics are unchanged; and the appearance of the first-stage simplified model is kept consistent with that of an original first-stage standard model in front of the position of a second-stage standard model head, and a V tail is reserved.

The invention discloses a fish-tail-imitating propulsion device suitable for a small waterplane area catamaran, and is mainly used for the field of boats and ships. The fish-tail-imitating propulsion device comprises a steering engine for supplying the dynamic effect, fish-tail-imitating hydrofoils, springs, connecting rods, rocking rods and pin nails. According to the fish-tail-imitating propulsion device disclosed by the invention, the connecting rods are driven by the steering engine to move, the rocking rods are driven by the connecting rods to move, and the fish-tail-imitating hydrofoils are driven by the rocking rods to move; because the pin nails for connecting the rocking rods and the fish-tail-imitating hydrofoils are eccentrically fixed relative to the fish-tail-imitating hydrofoils, the fish-tail-imitating hydrofoils can swing around the pin nails under the driving of the rocking rods, so that propulsion force consistent with fish tails can be generated.

The invention belongs to the field of the biological test instruments and relates to a device for preventing climbing on tail in an animal tail suspension test. The device is capable of preventing an animal from climbing on the tail in an animal tail suspension test. The device is composed of a main suspension arm, a main beam, an upper connecting shaft, a threaded rod, a tension meter, a lifting ring, a suspension arm, a spring plate, semilunar tail climbing preventing plates, a circular ring hook and the like. The height of the tension meter is adjusted by use of a screw on the threaded rod so that the root part of the tail of the animal is slightly lower than the lower parts of the semilunar tail climbing preventing plates. The circular ring hook is fixed to the 1/3 part, close to the tail end, of the tail of a mouse by use of an adhesive tape; the semilunar tail climbing preventing plates are divided and stabilized on both sides; the circular ring hook fixed on the tail of the mouse is suspended on a lifting hook. Two semilunar tail climbing preventing plates are connected by use of four connecting fasteners to form a circular structure in the center of which a hole is formed; the tail of the mouse passes through the central round hole and the root part of the tail of the mouse is basically flush with the lower part of the central round hole. The size of the central round hole is smaller than that of the head of the mouse so that the head of the mouse cannot pass through the central round hole and only can contact the root part of the tail of the mouse at top, and therefore, climbing on the tail is prevented.

The invention discloses a tail-gas treating process in the preparation process of calcined clay. The tail-gas treating process comprises the following steps: cleaning and treating acid-removing gas by traditional tail-gas treating method. The tail-gas treating process is characterized by comprising the detailed steps of: (1) collecting and treating residual heat of tail gas and cooling the tail gas; (2) introducing the tail gas into a water pool, cleaning the tail gas, precipitating dust and solid particles in the tail gas to obtain slurry, wherein residual tail gas becomes wet gas; and (3) introducing wet gas of the tail gas into NaOH solution, enabling SO2, SO3 and CO2 in the tail gas to react with NaOH to obtain and discharge sodium salt and clean tail gas. The tail-gas treating process disclosed by the invention has the advantages that the problem of tail-gas treatment in the traditional manufacturing process of the calcined clay is solved, the residual energy in the tail gas is fully utilized, and the harmful gas components of the tail gas are purified, so that the environment is protected, the tail-gas treating cost of a company is saved, and more benefit for production of the company is saved. The tail-gas treating process has the advantages of simple process, high treating efficiency and low cost.