233results about How to "Reduce aerodynamic drag" patented technology

The invention relates to a linked landing gear cabin door folding and unfolding device and belongs to the technical field of aircraft manufacturing. The linked landing gear cabin door folding and unfolding device comprises a landing gear, a rotation shaft I, a rotation shaft II, a rotation shaft III, a rotation shaft IV, an upper supporting rod, a rocker arm I, a rocker arm II, a rocker arm III, a lower supporting rod, a folding and unfolding actuation cylinder, a connection rod I, a connection rod II, a connection rod III, a goose-shaped rocker arm, a support column protection plate and an airplane wheel protection plate. By virtue of the linked landing gear cabin door folding and unfolding device, the cabin door folding and unfolding actuation system is simplified, so that the occupying space of the device in an airplane is reduced and the structure weight is reduced; by virtue of the design of a linked mechanism, the order of folding and unfolding the landing gear, the airplane wheel protection plate and the support column protection plate is ensured, the control logic is simplified and the reliability is improved; the airplane protection plate is closed when the landing gear is unfolded, the pneumatic resistance can be reduced; the takeoff and landing performances of the airplane are improved; the damage to the airplane, caused by entrance of foreign materials in a landing gear cabin, can be avoided.

Systems, methods and media for reducing the aerodynamic drag of vehicles are disclosed. More particularly, embodiments may include at least one fan for directing air into a lower pressure region behind a vehicle in motion in order to reduce pressure drag. Embodiments may also include one or more internal air ducts for directing air from other parts of the vehicle to the at least one fan. In one embodiment, the operation of the at least one fan may be controlled based on sensed conditions, user control, or other means.

A design method of an aeroelastic model for a long-span transmission tower-line system is disclosed. On the basis of boundary layer wind tunnel test data of a rigid model, a finite element model is utilized to calculate that relaxed Froude number similarity criterion of transmission towers, the influence of the elastic stiffness of a transmission line and two kinds of variable proportion transmission line models upon wind-induced response is changed, an aeroelastic model with long span is designed. The influence of material nonlinearity and gradient wind height of concrete filled steel tube onwind-induced response is further analyzed by the finite element model. The method has the advantages that the aeroelastic model of long span can be reasonably designed by increasing the elastic stiffness of the transmission line and adopting an accurate line length similarity ratio; consideration of the material nonlinearity of concrete-filled steel tubes has little effect on wind-induced response at design wind speed, and the wind-induced response decreases when considering the gradient wind height.

The invention relates to a water-circulating-type thermal energy comprehensive utilization thermal management system for an electric vehicle, the vehicle comprising the thermal management system and an operation method of the thermal management system. The water-circulating-type thermal energy comprehensive utilization thermal management system for the electric vehicle comprises a refrigerant circulating loop and further comprises a water circulating loop. The refrigerant circulating loop comprises a refrigerant circulating primary road and two refrigerant circulating branches; an electronic compressor and a water-cooled condenser are arranged on the refrigerant circulating primary road; the first refrigerant circulating branch is provided with an evaporator electronic expansion valve andan air conditioning evaporator; and the second refrigerant circulating branch is provided with a water-cooled heat exchanger electronic expansion valve and a water-cooled heat exchanger. The water circulating loop comprises a water circulating primary road and at least two water circulating branches; the first water circulating branch conducts heat exchange with the water-cooled heat exchanger forcooling a battery pack; and the second water circulating branch conducts heat exchange with the water-cooled condenser for heating a passenger compartment. The water circulating loop is additionallyarranged in the thermal management system, the two branches of the water circulating loop conduct heat exchange with a refrigerant of an air conditioning system, thus the advantage of the high air conditioning refrigeration efficiency can be given into full play, thermal energy generated by other parts of the vehicle is fully utilized, and energy is saved.

The invention discloses a cross bionic blade combining a carangidae fish body and a pinion and a preparation method of the cross bionic blade, and the cross bionic blade is used for a multi-blade centrifugal fan. The cross bionic blade comprises a blade body. The cross section of the blade body has a carangidae-fish-cross-section-contour-imitation appearance, the mean camber line of the blade bodycross section is in a single arc shape, and the circle center position, the circular arc radius and the circular arc central angle of the mean camber line of the blade body cross section are determined according to a forward-bent blade profile design method of the multi-blade centrifugal fan. The end face, facing the impeller sucking-in side, of the blade body is of a wave-shaped structure, and the end face, facing the impelling blowing-out side, of the blade body is of a saw-tooth-shaped structure. The blade can improve the flowing of airflow in the impeller on the premise of increasing theair volume, the pressure fluctuation on the surface of the blade is lowered, and the aerodynamic noise is lowered.

An oval single-tube two-way vacuum pipeline traffic system comprises an oval pipeline. The oval pipeline is internally provided with a two-way travelling vehicle, vehicle upward suspension magnetic poles are arranged on the two sides of the travelling vehicle and matched with an outer suspension track and an inner suspension track correspondingly, and the outer suspension track is connected to theinner wall of the oval pipeline. The inner suspension track is supported on the inner wall of the oval pipeline through a track first support. A support rod is arranged at the position of a short shaft of the oval section of the oval pipeline, a semi-oval groove-shaped support seat is arranged along the exterior of the oval pipeline, and tight-pushing clamps are arranged on the position, on the horizontal positions of the two sides of the exterior of the pipeline, of the upper portion of the groove-shaped support seat along the long axis of the section of the oval pipeline. Adjusting and fixing are conducted through adjusting bolts. As for a vehicle with the same section, the blockage ratio in two-way double pipelines is slightly decreased, and the train travelling pneumatic resistance isreduced; and pipeline manufacturing materials are reduced, the pipeline erecting work procedure is reduced, the cost is reduced, the effective clearance in the pipeline is greatly increased, and mounting, examining and maintaining are conveniently facilitated.

A diffuser is arranged at the rear of a vehicle in the region of the underbody and has a fixed front part and an adjoining, pivotable rear part. Negative and positive lift effects and aerodynamic drag effects are obtained by adjusting pivotable rear part between an upwardly pivoted position and a downwardly pivoted position.

The invention provides a lower-jaw type supersonic/hypersonic inlet integrated with a forebody of an air vehicle and a design method of the lower-jaw type supersonic/hypersonic inlet. The lower-jaw type supersonic/hypersonic inlet comprises a local waverider compression surface, a rotation-formed axially symmetric compression surface, a rotation-formed axially symmetric lip cover, backswept side plates, an annular rotating round bent expanding pipeline, a forebody head upper surface, a forebody head transition surface and an aircraft fuselage profile. The forebody head of the air vehicle is designed asymmetrically, a non-regular capture surface is designed, accordingly, the theoretical capture area of the inlet and the utilization efficiency of the windward side of the air vehicle can be increased remarkably, and the shock wave intensity and the windward area above the forebody head of the air vehicle are reduced. The forebody of the air vehicle and the shock wave system of the lower-jaw type inlet are designed integrally, so that loss of strong shock waves and local reaccelerating areas can be avoided. Accordingly, the design method has a remarkable effect on improvement of the flow capture capacity and the total-pressure recovery capacity of the inlet as well as reduction of aerodynamic resistance of the air vehicle.

The invention discloses a method and system for controlling hover, reconnaissance and strike integrated aircraft. The control system comprises aircraft, airborne weapon systems, airborne detection systems and a ground monitoring station; belly suspending plates are installed on the aircraft of all states and weapons are installed on the belly suspending plates, electro-optical pods can be installed and the lifting height of the electro-optical pods can be adjusted to prevent the firing of the weapons from being interfered, and other weapons can be suspended outside under wings or on a fuselagewhile the belly suspending plates are installed. According to the designing scheme of the method and system for controlling the hover, reconnaissance and strike integrated aircraft, the problem of limited weapon firing angle is solved, by arranging the belly suspending plates, missiles arranged on the suspending plates are capable of keeping in the same pointing direction with an observing and sighting device at any time, but synchronously alignment is not necessary, the missiles only need to be capable of keeping in the same pointing direction with the observing and sighting device at any time, or capable of pointing at the same direction along with the observing and sighting device, and therefore firing conditions can be set up at any time to overcome defects in the prior art.

The invention discloses a wingspan-changeable inflatable floating and rising integrated stratospheric airship. The wingspan-changeable inflatable floating and rising integrated stratospheric airship comprises a central cabin and two wingtip cabins. Four propeller propelling devices are mounted on the central cabin, and two propeller propelling devices are mounted on each wingtip cabin. Double-row wings are adopted, and the interior of a front wing body and the interior of a rear wing body of each wing are both provided with three air chambers distributed in the extension direction. All the air chambers are separated from one another through supporting ribs. The inner surfaces of all the wing bodies adhere to the outer profiles of the supporting ribs. Telescopic rod sets are arranged in the air chambers respectively, the diameters of telescopic rods of the telescopic rod sets in the air chambers are different, and thus the telescopic rods in the air chambers can stretch and retract in a nested mode. The wingspan-changeable inflatable floating and rising integrated stratospheric airship has the advantages that the aerodynamic efficiency is high, and generated dynamic lifting force is large; both control and manipulation are quite convenient, and adjustment of different air-staying heights is achieved by adjusting the extension lengths of the wings.

A method of reducing aerodynamic drag on a moving blunt-edged body, the method comprising actively generating a flow of air at a blunt edge of a body and using the generated flow of air to control an external flow of air moving relative to an edge of a moving blunt-body.

The invention discloses an inflatable type outer windscreen of a motor train unit. The inflatable type outer windscreen of the motor train unit is characterized in that the periphery of the end face of a front car (1) is fixedly connected with an inflatable integral-ring-shaped rubber air bag (3), the periphery of the end face of a rear car (2) is also fixedly connected with an inflatable integral-ring-shaped rubber air bag (3), and the opposite surfaces of the two inflatable rubber air bags (3) are tightly attached to each other. The inflatable type outer windscreen of the motor train unit has good air tightness, heat-shielding performance, sound insulation performance and rainproof performance, small aerodynamic resistance and good curve passage capacity, and can provide a safer and more comfortable walking-through environment for passengers, and provide more effective protection for car flexible connection devices.

The invention provides an electric automobile driving charging system based on a cable system, a lifting system, an energy switching interface, an automobile-mounted terminal and a central regulation and control system. When an electric automobile needs to be charged and is driven into a charging circuit, the lifting system rises and enables the cable system to be connected, and the energy switching interface is switched to be powered by the cable system; the automobile-mounted terminal monitors automobile state parameters and electricity consumption and communicates with the central regulation and control system; the electric automobile has two driving states, namely manual driving and automatic driving, during charging driving; and the central regulation and control system monitors the states of charging-driving automobiles on the whole circuit, regulates the power supply amount and regulates and controls the automatic/manual driving automobile speed. According to the electric automobile driving charging system, the charging waiting time can be thoroughly eliminated, the cruising power can be improved, the dependence on fossil energy can be avoided, and zero pollutant emission is achieved; and automatic driving can also guarantee the safety speed and automobile distance of the electric automobile during charging driving, and the long-distance driving fatigue of a user is relieved.

The invention discloses a diving aircraft. The wings of the diving aircraft can rotate between two orientations perpendicular to the longitudinal axis of the fuselage and parallel to the longitudinal axis of the fuselage through the rotating shaft, and the canards can rotate in the horizontal state and dihedral through the rotating shaft. Rotate between two orientations, the butterfly tail can rotate between the two orientations of large dihedral and large dihedral through the rotating shaft, so that the diving plane can switch between the three states of seaplane, ship and underwater plane. Gliding takes off and lands on the water surface and flies in the air, can sail on the water surface, and can also dive into the water and fly underwater, which has more comprehensive functions and more freedom.

The invention provides a high-flow-rate ultra-large-diameter semi-milling and semi-welding closed ternary impeller and a manufacturing method. The closed ternary impeller mainly comprises a wheel cover, a wheel disc and a blade, wherein the blade is uniformly divided into two halves, one half of blade is integrally milled and formed with the wheel cover, the other half of blade is integrally milled and formed with the wheel disc, in addition, the two halves of blades are welded at a butt joint part for forming an integral blade, a groove is formed in the butt joint part of the two halves of blades, and in addition, a welding seam is formed in the middle of the whole blade after the welding. The manufacturing method comprises the following steps that the blade of the ternary impeller is uniformly divided into two parts, one half of blade is integrally milled into the wheel disc, one half of blade is integrally milled into the wheel cover, the groove is formed in the butt joint part of the two halves of the blades, in addition, the whole blade is welded after the fixation by a tooling, and the welding seam is formed in the middle of the whole blade; after the welding of the wheel cover and the wheel disc of the impeller is completed, the stress is eliminated, and the outer contour of the impeller is finely turned in the turning processing center of a numerical control machine tool after the re-installing and re-clamping; finally, the welding part of the blade is manually ground to be smooth. The ternary impeller and the manufacturing method have the characteristics that better pneumatic performance and pneumatic efficiency are realized, the processing quality is good, the impeller intensity is high, and the like.

The invention relates to a vectored thrust ducted propeller. The vectored thrust ducted propeller comprises a screw propeller and a duct cylinder body, wherein the screw propeller can rotate to generate air currents and the duct cylinder body surrounds the screw propeller; a first rotating piece, a second rotating piece and a blocking piece which are arranged in an air current deflection mechanism are respectively and directly derived from a part of a duct body; a complete duct is jointly formed by the first rotating piece, the second rotating piece, the blocking piece and the duct cylinder body part. Under the driving of a speed reducing motor, a rotation driving shaft is rotated, so that the first rotating piece and the second rotating piece are driven to rotate to expected positions; the blocking piece moves forward and backward along a sliding groove formed in the duct cylinder body to prevent the air currents from flowing out of the right side of the duct, and the blocking piece is matched with the first rotating piece and the second rotating piece so that the air currents can flow out of the remained empty part formed after the first rotating piece is rotated; therefore, the whole system bears lateral force which is reversed to the air currents. According to the vectored thrust ducted propeller disclosed by the invention, the thrust direction of a ducted fan is substantially changed, large enough lateral force is provided for an aircraft to balance the reaction torque of a main rotor, so that the residual thrust in the axial direction of the aircraft is as small as possible, and more suitable for the aircraft of the type to ascend and descend perpendicularly and hang in the air.

HYPERDRIVE receives continuous air breathing assistance from compressed atmospheric air through a high speed magnetically core driven turbine accelerator which resolves around a common flow path tunnel. The tunnel runs from the front to the back of the engine. It is assisted by a series of radial geometric ramjet engines that share the common flow path tunnel for hypersonic exhaust but has separate inlet air from a linear aerospike which governs mass flow of air, velocity of inlet air and pressure to the turbine and/or ramjets, as well as the positioning of the shock wave at the inlet to reduce aerodynamic drag. The ramjet is of hybrid engine design where it can also function as a scramjet, thus a ram-scramjet structure for combustion in a radial configuration about the engine (aft of an electrical compressor), where the common flow path tunnel also serves as a compression tunnel to compress air through a the constantly occurring series of compression shocks entering from and around the aerospike.

The invention relates to a vertical lifting aerodyne employing tiltable ducted wheels. A fuselage adopts the streamline design, two sides of the fuselage are provided with large strake wing body-fused horizontal fixed stub wings, tilting systems are designed at the tail ends of the stub wings and connected with the earth-space dual purpose ducted wheels, the ducted wheels are overturned towards the inner side of the fuselage through the tilting systems, and thus the vertical lifting aerodyne can run on the ground, take off and land vertically and fly in the air with any attitude. Six stub wings are designed at both sides of the fuselage in total, so that six ducted wheels are required in total. The vertical lifting aerodyne has the advantages that the technology of fusing the streamline fuselage and wing bodies is adopted, and thus the structure weight is light, the internal capacity is large, the air resistance is small; control over the flight attitudes is realized through controlling power differentials of the six wheels, the design of control rules is simple, and the control is convenient.

Methods and systems are provided for estimating a cooling demand of a vehicle powertrain component and selecting a mode of operation of a vehicle cooling system based on the estimated cooling demands of the vehicle powertrain component and the energy usage of the cooling system components. Based on the selected operating mode, each of a radiator fan speed, a coolant system pump output, a vehicle grille shutter opening, and an opening of vents coupled to a powertrain component insulating enclosure may be concurrently adjusted to minimize the cooling parasitic losses while satisfying the cooling requirements of the vehicle.

The invention relates to a water circulation type thermal management and air conditioning system for an electric vehicle, a vehicle including the thermal management and air conditioning system and anoperation method of the thermal management and air conditioning system. The water circulation type thermal management and air conditioning system for the electric vehicle comprises a refrigerant circulation loop and a water circulation loop. The water circulation type thermal management and air conditioning system for the electric vehicle is characterized in that the refrigerant circulation loop comprises an electronic compressor, a water-cooled condenser, a water-cooled heat exchanger electronic expansion valve and a water-cooled heat exchange; the water circulation loop comprises a water circulation trunk road and at least two water circulation branches, wherein the circulating water of one water circulation branch is heat exchanged with the water-cooled heat exchanger for cooling a passenger compartment and/or a battery pack, and the circulating water of the other water circulation branch is heat exchanged with the water-cooled condenser for heating the passenger compartment; and apart which cools the passenger compartment is a refrigerator, a part which heats the passenger compartment is a heater, and the refrigerator and the heater form a water-cooled air conditioning system.Different from a traditional vehicle air conditioner, the water circulation type thermal management and air conditioning system for the electric vehicle adopts the water-cooled air conditioning system and utilizes the refrigerator and the heater which are arranged in series to refrigerate and/or heat the passenger compartment, the advantage of high refrigeration efficiency of an air conditioner is fully achieved, the heat energy generated by other parts of the vehicle is fully utilized, and energy is saved.

The invention discloses a two-dimensional supersonic air inlet passage with a variable structure. The air inlet passage and an aircraft body are of an integrated structure, a fixing plate is positioned in the air inlet passage and is arranged parallel to an upper supporting plate, a piston barrel and a piston rod are fixedly connected with an upper fixed support and a lower fixed support respectively, the piston barrel and the piston rod are synchronously matched and are positioned between the fixing plate and the upper supporting plate, a front compression plate is articulated with a movable compression plate by a first rotating rod, the movable compression plate is articulated with the upper supporting plate by a second rotating rod, the upper supporting plate and the air inlet passage are articulated by a third rotating rod, and two ends of each of the second rotating rod and the third rotating rod are positioned in a front sliding groove and a rear sliding groove on the two side walls inside the air inlet passage respectively for movement. The air inlet passage has simple structure and has strong realizability in engineering application, the compression angle of the air inlet passage is changed to directly adjust the quality of air flows entering into a combustion chamber, the aerodynamic performance and the working state of the air inlet passage operating in a wide range of mach number are ensured, and the working efficiency and the aerodynamic performance of the air inlet passage are greatly improved.

An aircraft double-layer air-liquid skin heat exchange method belongs to the technical field of environmental control, is a new technology for reducing aircraft ram air volume and improving air-liquid heat exchange efficiency, and is a heat exchange method for single-layer air-liquid skin. improvement of. A double-layer air-liquid skin heat exchanger is installed on the outer surface of the fuselage skin, the air-liquid skin heat exchanger includes an outer surface (1), an inner surface (2), a liquid inlet conduit (3), a liquid outlet The conduit (4), the sealing ends (5), (6), the fuselage connecting part (10), leave a gap (11) between the inner surface (2) and the outer surface of the skin, and the outer surface (1) and Double-layer heat dissipation fins are installed between the inner surfaces (2), and the double-layer heat dissipation fins include inner-layer heat-dissipating fins (7), outer-layer heat-dissipating fins (8), and partitions (9) for the inner-layer heat-dissipating fins . Compared with the air-air skin heat exchanger, the method has higher heat transfer coefficient, larger heat exchange and better cooling effect; compared with the air-liquid heat exchanger, the air-liquid skin heat exchanger Using the surface layer heat dissipation technology integrated with the aircraft skin, the traditional ram air intake air cooling method is cancelled, the fuel compensation loss of the system to the aircraft is greatly reduced, and the flight time of the aircraft is improved; at the same time, it can meet the needs of the aircraft Stealth performance requirements.

The invention discloses a novel efficient tilt rotor unmanned aerial vehicle. Unmanned aerial vehicle layout has higher aerodynamic efficiency and better level-flight longitudinal direction and coursecontrol performance, and high-speed and high-efficiency flight can be achieved on the premise of vertical take-off and landing. The unmanned aerial vehicle comprises tilt rotors, vertical flight mechanisms, fixed wings, a fixed vertical fin, a stabilator, a body structure and a landing gear. The unmanned aerial vehicle needs to experience a vertical flight state, a transition flight state and a level flight state from take-off to level flight. The tilt rotors and the vertical flight mechanisms can rotate through an actuation mechanism, so that the unmanned aerial vehicle can vertically take off and horizontally fly at high speed, the tilt rotors can change a distance, take account of rotating efficiency in the vertical flight state and the level flight state and drive the unmanned aerialvehicle to fly at high speed, the vertical flight mechanisms and the tilt rotors collectively provide lift force and control force of vertical take-off and landing in the vertical flight state, the vertical flight mechanisms are stored on two sides of a body in the level flight state, and a good aerodynamic shape of the unmanned aerial vehicle is kept.