237results 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.

The invention relates to a coaxial double-rotor-wing system of an aircraft. The coaxial double-rotor-wing system comprises a speed reducer, a lower rotor wing shaft, a lower rotor wing hub, a lower rotor wing, an upper rotor wing, an upper rotor wing shaft, an upper rotor wing hub, an upper rotor wing and a control link or controlling the upper rotor wing and the lower rotor wing and is characterized in that the upper rotor wing and the lower rotor wing are rigid coaxial rotor wings only provided with an axial hinge, a pull rod direct-connection structure between the upper automatic inclinator and the lower automatic inclinator of the control link is omitted, and the control link further comprises a cyclic pitch control mechanism and a differential cyclic pitch control mechanism. The coaxial double-rotor-wing system has the advantages that lift force compensation of the rotor wings is omitted by utilizing the rigid coaxial rotor wings; further aerodynamic limiting caused by air flow separation and air supersonic turbulent flows is avoided under the situation that the condition of lift force compensation is not met; a retreating propeller pitch is decreased by adding the differential cyclic pitch control mechanism, accordingly the aerodynamic resistance of the retreating positions of rotor wing blades can be reduced, ineffective consumption is reduced, and the flat flight speed is improved based on the same output power.

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 relates to a machining method of a closed three-elemental impeller with a small flow. The machining method comprises the following steps of: 1. mounting an impeller forging on a lathe machining center of a numerically-controlled machine tool, thereby carrying out semi-finishing treatment on the impeller forging; 2. machining a circular groove in an impeller cover and completing the machining of the whole flow channel of an impeller; and 3. welding a circular impeller cover shielding plate on the impeller cover and completing the contour finishing of the impeller cover and an impeller hub, wherein the semi-finishing treatment is performed by clamping the impeller forging on the lathe machining center of the numerically-controlled machine tool and carrying out the lathe machining on the impeller forging; the lathe machining in an axial feeding manner is performed until reaching an air inlet of an impeller blade; the outer contour of the impeller cover is formed by performing the lathe machining in a radial feeding manner; and the allowance of 4 to 6mm is left between the impeller cover and the impeller hub. The method has the characteristics of weldless flow channel forming surface, smooth flow channel, effective reduction in aerodynamic resistance, good aerodynamic performance and aerodynamic efficiency, good machining quality, high impeller strength, good corrosion resistance and the like.

The invention discloses a vertical take-off and landing fixed wing long-endurance air vehicle. The vertical take-off and landing fixed wing long-endurance air vehicle comprises a fuselage in horizontal position in flight; the head part of the fuselage is provided with a pair of canard type wings; the tail part of the fuselage is provided with a pair of wings; a vertical empennage is arranged below the tail part of the fuselage; the lower parts of the wings are provided with at least two pairs of distributed power plants, wherein the number of the power plants is even, and the revolving shafts of the power plants are arranged along the axis of the fuselage; the head part of the fuselage is provided with a vertically distributed through hole; and an elevating control power plant is arranged in the through hole, and the revolving shaft of the elevating control power plant is arranged in vertical. According to the vertical take-off and landing fixed wing long-endurance air vehicle, the elevating control power plant is used for changing rotating aped of variable pitch propellers and elevating control moment force needed by screw pitch output in the whole flight envelope; the number of fixed pitch propellers is larger, and rotating speed of each propeller can be controlled individually, so that rolling and yaw control adjustable minimum pulse-width is smaller, and control accuracy is higher.

The invention relates to a twin-screw compressor rotor profile, wherein a two-side asymmetric profile is adopted, six sections of profiles are combined to form end face profiles of a female rotor and a male rotor, and the female rotor and the male rotor which are identical in central distance A and different in size are combined to a form a female / male rotor profile series of a screw compressor. An arc f2g2 with a certain radius and an arc envelope d2e2 at the addendum circle on the passive side of the female rotor end face profile are in smooth connection through taking a straight line e2f2 as a common tangent. The elliptic arc b1c1 on the male rotor end face profile is different from the ordinary arc pin tooth curve or the envelope and can enable the engagement and releasing of the male and female rotors to be more stable through properly adjusting the length ratio of the major and minor axes of the ellipse, so as to reduce noise and vibration. The included angle of the addendum arc c1d1 on the male rotor end face profile can be adjusted, and the addendum arc c1d1 is in tangent and smooth connection with both the elliptic arc b1c1 and an arc d1e1. The invention endows the rotors with the advantages of short contact line, small disclosed triangle, big flow passage area, streamlined rotor profile, reduced aerodynamic resistance and the like.

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.

The invention provides a high-performance subsonic speed air inlet duct integrated with an inner auxiliary air inlet duct. The high-performance subsonic speed air inlet duct integrated with the inner auxiliary air inlet duct comprises a main air inlet duct and the auxiliary air inlet duct. The main air inlet duct can be an S-shaped bent air inlet duct or an embedded type air inlet duct. The bottom edge of an inlet of the S-shaped bent air inlet duct is attached to the surface of a machine body. An inlet of the embedded type air inlet duct is fully integrated with the surface of the machine body. An inner channel of the auxiliary air inlet duct is communicated with an aircraft environment control system or a cabin air guiding channel. The auxiliary air inlet duct is arranged in an inner channel of the main air inlet duct in an integrated mode. By the adoption of the high-performance subsonic speed air inlet duct integrated with the inner auxiliary air inlet duct, the independently arranged auxiliary air inlet duct and a boundary layer partition channel on the machine body can be eliminated, so that the aerodynamic resistance of an aircraft is reduced, and the stealth performance of a radar of the aircraft is improved; in addition, through mutual cooperation between a plurality of groups of miniature eddy generators and auxiliary inlets in the inner channel, low-energy air flow in the main air inlet duct can be gathered and supplied to the auxiliary air inlet duct to be used, as a result, the total pressure recovery coefficient of the main air inlet duct is remarkably increased, and the flow distortion performance of the main air inlet duct is remarkably improved.

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 belongs to the field of aviation technology, in particular to a trailing edge and wing tip continuously variable camber structure and a decentralized driving control method thereof, theaircraft continuous camber structure of the present invention comprises SMA wires, for connecting the edges of two adjacent pterygoid joints on the same side of the hinge, and the SMA wire is connected with a heating power source and sealed with a plastic tube, A plastic tube is connected to the cooling compressor, An angle sensor is mounted on each hinge, SMA wires have shape memory function, Atlow temperature, that SMA wires can be elongate and deformed under the external force, and the shape of the fixed length can be kept. The SMA wire on one side is heated, and the SMA wires on the other side are cooled by the cool gas living in the house through a plastic tube, so that the whole wing-rib joint can be deflected to one side.

The invention provides a bionic stratospheric airship, and belongs to the technical field of aircraft design. The shape of a hull of the stratospheric airship is obtained according to the shape setting out of a portuguese man-of-war. The hull is internally provided with more than one main airbag, more than one auxiliary airbag and a heat-regulating airbag. The main airbags are filled with gas withthe density lower than air, the main airbags are disposed on an upper layer in the hull, and first gas valves are arranged on the upper parts of the main airbags. The auxiliary airbags are filled with the air, the auxiliary airbags are disposed on a lower layer in the hull, and second gas valves and blowers are arranged at the bottoms of the auxiliary airbags. The heat-adjusting airbag is arranged in a middle layer in the hull, and the heat-regulating airbag is internally provided with a thermal cycle device. The heat-regulating airbag is filled with a gas-liquid reversible control working medium. Under the working conditions of super-thermal and over-pressure, the working medium is converted from a gaseous state to a liquid state by the thermal cycle device, and the working medium is converted from the liquid state to the gaseous state by the thermal cycle device under the ultra-cold working condition.

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 provides a high-speed train abdomen rectifying device, which relates to high-speed train manufacturing technology. A bogie of the train abdomen is provided with a streamline bogie fairing which covers the bogie and most part of a wheel on the bogie; and the bogie fairing is overlooked as a fusiform shape. The train abdomen rectifying device can significantly reduce the pneumatic resistance at the train abdomen, raise the running safety of a train and also greatly reduce the energy consumption, and has great practical value.

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.

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.

A wing (2) for an aircraft comprises a leading edge (4) and a wing tip extension (8) extending from an end of a main wing region to a wing tip (26). The wing tip extension (8) comprises an arrangement of openings (22) at least from the end of a main wing region to the wing tip (26) along the leading edge (8), which openings (22) are connected to an air conveying device for conveying air through the openings (22).Thereby in flight states with a low flight velocity the flow around a wing tip extension can be harmonized such that the drag is decreased and the lift of the wing is increased. The invention further relates to a method for reducing the aerodynamic drag and improving the maximum lift, and an aircraft.

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 relates to a grille airflow shutter system with discrete shutter control. A method of controlling airflow through a grille on a front end of a vehicle comprising the steps of: detecting vehicle operating conditions; determining a desired percentage of airflow through the grille based on the desired operating conditions; actuating grille airflow shutters to an open position for the determined desired percentage of a predetermined time interval; and actuating the grille airflow shutter to a closed position for a remaining percentage of the predetermined time interval.