Fluid acting synergistic device based on double ducts and rotor rotation gain and application

Abstract

The invention discloses a fluid acting synergy device based on double ducts and rotor rotation gain. The fluid acting synergy device is suitable for multiple fields of flight, suspension, ship navigation and the like. The core structure comprises a rotor, a fixed shell surface, a magnetic suspension device, an inclined flow guide baffle and a ducted fan or a propeller. A first duct is formed by a space formed by the rotor and the fixed shell face in a parallel and opposite mode, and annular negative-pressure flow suction blades are arranged on the bent and curled portion of the outer edge of the rotor and can suck in fluid such as air or water. The inclined flow guide baffle in the first duct converts fluid into spiral centripetal vortex, and acts on the flow baffle on the rotor to drive the rotor to rotate, so that the kinetic energy and the aggregation degree of the fluid are enhanced, and it is ensured that the fluid entering the second duct is in the highest energy density state. A second duct is arranged on the inner edge of the first duct and provided with a ducted fan or a propeller to serve as an active energy source, fluid kinetic energy is further improved after the high-energy vortex conveyed by the first duct is received, and finally the fluid is sprayed out at a high speed through a functional nozzle to do work outwards. The magnetic suspension device is arranged at the position where the rotor abuts against the fixed shell face, mechanical friction is reduced, an energy recovery module can be integrated, and the energy efficiency of the device is improved. The device effectively optimizes the hydrodynamic performance through double-duct cooperation and rotor autorotation gain, and has remarkable practical value and industrial prospect in the scenes of low-altitude logistics, disaster rescue, manned flight, ground and water surface suspension carriers, ship navigation and the like.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of flight, suspension and ship navigation, and proposes a fluid work gain enhancement device based on double-duct and rotor self-rotation gain and application, which is particularly suitable for low-altitude logistics, disaster rescue, manned flight, ground and water surface suspension or semi-suspension driving, and ship water navigation and the like scenes. BACKGROUND

[0002] Traditional aircrafts, suspension vehicles and ships rely on mechanical transmission, and have large friction loss. Among them, the aircrafts and suspension vehicles have the problems of insufficient lift utilization rate and weak wind resistance due to fixed aerodynamic layout; the existing vector duct fan lacks dynamic aerodynamic adjustment capability, resulting in poor hovering stability; at the same time, the conversion between vertical take-off and horizontal flight needs complex attitude adjustment, and the response speed is slow. The core reason of the above problems lies in the lack of dynamic fluid gain mechanism, and currently there is no technology to solve this underlying defect through the cooperation of rotor self-rotation and double-duct.

[0003] In view of the defects of the above-mentioned traditional technology, the present application is applied for an invention patent "A disc-shaped aircraft with self-rotating outer shell gain" (application date: May 17, 2025, application number: 2025106365892) by Beijing Boshi Zhixin Patent Agency and an invention and utility model patent "A disc-shaped aircraft with double-duct and rotor self-rotation gain" (application date: August 14, 2025, application number: 202511139015.0 and 202521731384.4) by Beijing Baisheng Patent Agency; the core technologies of the two are the same, both based on the technical principle of double-duct and rotor self-rotation gain, mainly focusing on a specific product form (a disc-shaped aircraft), the main difference being that the former additionally designs an upper outer shell connected with the rotor as a whole, which is only a special case in the view of the latter; but the latter only describes the structure and principle of the aircraft, does not involve the application method of designing multiple "double-duct and rotor self-rotation gain" devices for the same aircraft, and does not involve the application of the core technology "double-duct and rotor self-rotation gain" to other fields, including other winged / wingless, fixed / non-fixed wing aircrafts, other forms of disc-shaped aircrafts, suspension or semi-suspension vehicles on land and water surface (such as suspension motorcycles, suspension cars, water surface suspension speedboats), and underwater and water surface ships. SUMMARY

[0004] In view of the above, the present application proposes a fluid work gain enhancement device based on double-duct and rotor self-rotation gain and application in view of the deficiencies and problems in the above technical background. The application is an application of the core technology of the original case "A disc-shaped aircraft with double-duct and rotor self-rotation gain", and the specific content is as follows: The core structure of the fluid work enhancement device based on double-duct and rotor rotation gain includes a rotor, a fixed shell, a magnetic suspension device, a slanting guide baffle, a duct fan or a propeller, etc. A first duct is formed by a space parallel to the fixed shell and the rotor surface. The relative position of the rotor and the fixed shell depends on the application scenario. The rotor has a rotor surface similar to the shape of the fixed shell, and the outer edge of the rotor is bent and curled towards the fixed shell. The bent and curled part of the outer edge is provided with annular negative pressure suction blades to realize edge or edge axial suction of fluid (air / water). The suction direction is determined according to the function of the invention enhancement device. For example, in vertical take-off and landing aircraft and various suspension carriers, the main function of the device is to offset the gravity work, so the suction direction is upward. For gliders and underwater and surface ships, the main function of the device is to assist the forward movement of the aircraft and the ship, so the suction direction is forward.

[0005] The magnetic suspension device is arranged at the circular ring surface close to the fixed shell and other fixed parts at the edge and middle part of the rotor. The magnetic suspension device can adopt permanent magnet and electromagnetic suspension methods, and can also integrate damping compensation and energy recovery modules to effectively reduce mechanical friction loss. The number of the magnetic suspension devices depends on the radial width and shape of the rotor (usually more than three groups). When the diameter of the magnetic suspension device is small, the magnetic suspension device can be replaced by a bearing or a guide rail and a pulley rigid connection, so that the rotor part of the magnetic suspension device can be omitted.

[0006] The slanting guide baffle is a straight panel or a spiral curved panel, arranged in an annular array close to the outer edge part in the first duct, integrated with the fixed shell, and the radial included angle is adjustable as a whole. One of its functions is to change the centripetal airflow entering the disc-shaped duct into a spiral centripetal vortex to push the rotor to rotate; the second is to promote the aircraft to remain in a relatively static state, and the radial included angle is adjusted according to the change of the rotation speed of the duct fan. When the aircraft is relatively static, the flight direction can be changed by adjusting the included angle.

[0007] The first duct is unique, axisymmetric, circular ring-shaped, disc-shaped, bowl-shaped, barrel-shaped or conical. The annular array of the rotor in the middle of the first duct is fixed with a flow baffle. The inner edge of the first duct is provided with a second duct (tubular), which can be single or multiple. When the single second duct is located at the center of the first duct, multiple second ducts are arranged in an annular array at the inner edge of the first duct.

[0008] The second duct has the characteristics of arbitrary transmission and no strict specific shape, and is commonly in the shape of a tube. Its length and whether it is curved are determined according to the actual application scenario. When there is a single second duct, the second duct can be divided into multiple tubes, and finally flow into various function nozzles, including vector nozzles, vertical nozzles and horizontal nozzles. Each second duct is equipped with at least one counter-rotating duct fan or propeller, which provides a power source for the fluid power enhancement device of the application. During power transmission, the fluid kinetic energy can be directly output, or divided into multiple parts, or combined into one.

[0009] The duct fan and the propeller include shafted and shaftless duct fans and propellers. For the duct fan, the duct fan is commonly arranged in the second duct, and the fan is mostly of the axial type. When the second duct is the only case, the duct fan can be arranged at the center of the first duct, and is a centrifugal suction fan. When the second duct is not in the shape of a tube, the duct fan is arranged at the head of the second duct, and is a centrifugal fan.

[0010] During operation, the first duct and the second duct form a mutual excitation and cooperative gain mechanism. The core function of the first duct is to suck in air or water through the annular negative pressure suction blades on the outer edge of the rotor, and cooperate with the inclined guide baffles in the first duct to form a spiral centripetal vortex, which further acts on the flow blocking plate on the rotor to drive the rotor to rotate, thereby enhancing the kinetic energy and aggregation degree of the fluid, and ensuring that the fluid entering the second duct is in the state of the highest energy density. The second duct provides active energy input through the duct fan or the propeller, further enhances the kinetic energy of the fluid on the basis of receiving the high-energy vortex delivered by the first duct, and finally outputs energy to the outside through the high-speed ejection of the fluid, thereby completing the work.

[0011] Further, the duct fan blades and the propeller are arranged in the second duct, and are driven by the motor and the fuel power machine. The motor and the fuel power machine can be installed in the second duct or on the fixed part extended from the second duct, and drive the fan blades and the propeller to rotate through the shaft.

[0012] Further, the fixed part refers to all parts (such as protective devices and shell surfaces) fixedly connected to the whole aircraft, the suspended carrier or the ship. The fixed shell surface also belongs to the fixed part.

[0013] Further, the protective device is an annular protective support arranged beside the rotor, and a magnetic suspension device is arranged between the annular surface of the protective support and the rotor. The magnetic suspension device not only protects the rotor, but also ensures that the external fluid (air / water) can be sucked into the first duct by the annular negative pressure blades on the outer edge of the rotor. A protective net is installed on the protective device to filter the air and water and prevent foreign matters from entering the duct.

[0014] Further, for small and micro vertical take-off and landing type aircraft and various hovering vehicles, the required unique case of the present application is to adopt the upward air suction design of the present application; in the pure low-altitude hybrid power scene, the engine or generator is inversely tangential to the inner edge of the first duct to suck air, or the tangential outflow to the duct, so that the fuel generator or engine plays a self-pressurization role, improving the fuel energy utilization efficiency; the front, rear, left and right of the rotor outer edge ring-shaped air suction fan are respectively provided with a fan ring-shaped panel, when the fan ring-shaped panel is not in contact with the upper part of one of the front, rear, left and right of the ring-shaped air suction fan, the aircraft will tilt, and other steering functions can be realized quickly and flexibly adjust the flight attitude; in order to adapt to civil low-altitude efficient and fast horizontal flight and hovering, the front half of the rotor ring-shaped air inlet is provided with a fan ring-shaped cover plate, and the front end of the aircraft is provided with a wide and flat air inlet, the fan ring-shaped cover plate is opened during vertical take-off, and the fan ring-shaped cover plate is closed during horizontal flight.

[0015] Further, various fixed or non-fixed wings can be added to the existing aircraft technology, or wheels can be installed to make it more efficient, fast and stable, and realize multifunctional integration.

[0016] Further, in order to adapt to the space transportation scene, in the extremely low pressure or vacuum environment, the upper port of the closed vertical duct is integrated with the magnetic suspension damping module to start the electric mode, so that the rotor is still in a rotating state, and the high-pressure airflow or ion flow is injected into the second duct in the same direction.

[0017] Further, for medium, large or super large aircraft (including disc-shaped aircraft), hovering vehicles and ships, according to their morphological characteristics and driving needs, multiple present application efficiency devices can be installed on the whole at the same time, and the flow direction is determined according to the function, such as: large underwater / surface ships and gliding aircraft, multiple forward flow (air / water) present application fluid work efficiency devices can be installed according to needs, mainly installed at the stern and below the main wing of the aircraft.

[0018] Further, the present application efficiency device can be designed and manufactured according to the power and modularization standard, which can be used for upgrading and modification of existing aircraft, hovering vehicles and ships to meet the actual needs of society.

[0019] The above technical scheme has the following beneficial effects: In the field of flight, whether it is a winged, wingless aircraft, a fixed-wing, non-fixed-wing aircraft, or a disc-shaped aircraft of different shapes, after applying the device, with the help of the high-efficiency fluid power generated by the double-duct and rotor self-rotation gain, the aerodynamic layout can be optimized, the lift utilization rate can be improved, the wind resistance can be enhanced, and the response speed of vertical take-off and horizontal flight conversion can be improved, making the flight more stable and efficient.

[0020] In the field of ground and water surface suspension or semi-suspension, such as suspension motorcycles, suspension cars, water surface suspension speedboats and other vehicles, the device can realize stable suspension, reduce friction with the ground or water surface, improve driving speed, and enhance maneuverability and flexibility during driving through fluid power generated.

[0021] In the field of ships, whether it is a water ship or an underwater ship, the fluid amplification effect of the device can improve the propulsion efficiency, reduce energy consumption, and enhance the stability and maneuverability of the ship during navigation, and adapt to different hydrological environments.

[0022] In summary, the technical solution realizes a comprehensive breakthrough in energy efficiency, fluid working performance, stability, maneuverability and other aspects through double channel cooperation, rotor self-rotation gain, magnetic suspension drag reduction and other core designs. At the same time, relying on scenario-based expansion design, it provides an efficient, flexible and multifunctional technical solution for the fields of flight, suspension and ships, which has significant practical value and industrial prospects. BRIEF DESCRIPTION OF DRAWINGS

[0023] Figure 1 The present application is a single second channel type multifunctional aircraft and its double channel and rotor self-rotation gain efficiency device central longitudinal section structure schematic diagram, and the dashed part is the structure component projected on the longitudinal section; Figure 2 The present application is a single second channel type multifunctional aircraft and its double channel and rotor self-rotation gain efficiency device central longitudinal section structure schematic diagram, and the dashed part is the structure component projected on the longitudinal section; Figure 3 The present application is a single second channel type multifunctional aircraft and its double channel and rotor self-rotation gain efficiency device central longitudinal section structure schematic diagram, and the dashed part is the structure component projected on the longitudinal section; Figure 4 The present application is a single second channel type multifunctional aircraft and its double channel and rotor self-rotation gain efficiency device central longitudinal section structure schematic diagram, and the dashed part is the structure component projected on the longitudinal section; Figure 5 The present application is a single second channel type multifunctional aircraft and its double channel and rotor self-rotation gain efficiency device central longitudinal section structure schematic diagram, and the dashed part is the structure component projected on the longitudinal section; Figure 6 The present application is a single second channel type multifunctional aircraft and its double channel and rotor self-rotation gain efficiency device central longitudinal section structure schematic diagram, and the dashed part is the structure component projected on the longitudinal section; Figure 7 The present application is a single second channel type multifunctional aircraft and its double channel and rotor self-rotation gain efficiency device central longitudinal section structure schematic diagram, and the dashed part is the structure component projected on the longitudinal section; Figure 8It is a center section structure schematic diagram of a double-cone rotor type double-diffuser and rotor self-rotation gain synergistic device of the application. Figure 9 It is a center section structure schematic diagram of a bottom synergistic device type suspension motorcycle and its double-diffuser and rotor self-rotation gain synergistic device of the application, and the dashed part is a structure component projected on the section.

[0024] In the figure: 1. rotor; 2. fixed shell surface; 3. oblique guide baffle; 4. diffuser fan; 5. first diffuser; 6. second diffuser; 7. baffle; 8. annular negative pressure suction blade; 9. protective net; 10. fan annular cover plate; 11. front end air inlet; 12. upper cabin; 13. lower cabin; 14. upper outer shell; 15. lower outer shell; 16. first magnetic suspension device; 17. second magnetic suspension device; 18. third magnetic suspension device; 19. vector jet; 20. vertical jet; 21. horizontal jet; 22. main wing; 23. tail wing; 24. vertical rudder wing; 25. front wheel; 26. rear wheel; 27. stand column; 28. air flow valve; 29. air turning pipe; 30. protection device; 31. lower cabin door; 32. cabin door; 33. upper cabin door; 34. cabin elevator; 35. top platform; 36. platform guardrail; 37. bearing; 38. motor; 39. scraper; 40. propeller; 41. auxiliary blade ring; 42. centrifugal guide strip; 43. centrifugal diffuser fan; 44. disc-shaped container; 45. bottom plate; 46. top plate. DETAILED DESCRIPTION

[0025] The technical solutions in the embodiments of the application will be described clearly and completely below with reference to the drawings in the embodiments of the application. Obviously, the described embodiments are only part of the embodiments of the application, rather than all the embodiments of the application. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the application.

[0026] Embodiment 1: Referring to FIG. 1, FIG. 2, a single second-duct type multifunctional aircraft and its double-duct and rotor autorotation gain synergistic device, comprising a rotor 1, a fixed shell surface 2, a first magnetic suspension device 16, a second magnetic suspension device 17, a third magnetic suspension device 18, a diagonal guide baffle 3, and a duct fan 4, the rotor 1 and the fixed shell surface 2 are similar in shape, and are a rotating body with the front end outer edge bending radially inward (referred to as a rotor for short), the fixed shell surface 2 is above, the rotor 1 is below, and the space between them constitutes a first duct 5, the magnetic suspension device is arranged on the circular ring surface close to the rotor 1, the fixed shell surface 2 and other fixed parts, including permanent magnet and electromagnetic suspension, or integrated damping compensation and energy recovery module.

[0027] The double duct refers to the simultaneous inclusion of the first duct 5 and the second duct 6, the first duct is unique, and the second duct can be single or multiple.

[0028] The rotor 1, the radially inwardly bent and curled portion of the front end outer edge is provided with an annular negative pressure air suction blade 8, realizing edge or edge upward air suction, cooperating with the diagonal guide baffle 3 arranged in an annular array in the first duct 5, forming a spiral centripetal vortex acting on the radial strip-shaped baffle 7 on the rotor, driving the rotor 1 to rotate, and converging in the center or near the center to enter the second duct 6 axially.

[0029] The fixed shell surface 2, the space above is called an upper cabin 12 (or a passenger and cargo cabin), and the space below is called a lower cabin 13 (or a power cabin), and the lower cabin includes the first duct 5 and the second duct 6; the upper shell surface 14 of the upper cabin is a hemispherical surface, and the lower outer shell surface 15 of the lower cabin is a boat-shaped surface, a wide and flat horizontal air inlet 11 is designed in front of the rotor annular air inlet fan; a front wheel 25 is installed in the middle of the front part of the lower outer shell 15, and a rear wheel 26 is installed on each side of the rear part.

[0030] The first duct 5 belongs to an axisymmetric disc-shaped duct, and the second duct 6 is a tubular duct located at the center of the first duct, the upper end is perpendicular to the inner edge surface of the first duct (the original case is called a vertical duct), and is connected and fixed with the fixed shell surface 2 through a second duct head stand 27, and is provided with a counter-rotating fan (duct fan 4), and the flow in the lower part of the second duct flows to four turning pipes 29, and then flows to the vector nozzles 19 on the two sides of the front part of the lower outer shell 15 of the lower cabin 13 and the airflow valves 28 on the two sides of the rear part through the turning pipes, and then flows to the vertical nozzles 20 or the horizontal nozzles 21; if necessary, a first counter-rotating duct fan is added in the vertical duct to enhance the source power; the lower part of the vector nozzle 19 is provided with a ±45° to ±60° tilting guide device, which constitutes a vector nozzle; adjusting the tilting guide device and the airflow valve 28 can realize flexible adjustment and control of the flight attitude.

[0031] The ducted fan 4 refers to the fan blades placed in the second duct 6, including motor fans and fuel-powered fans, and the motor and fuel-powered machine can be installed on the fixed shell 2 above the second duct.

[0032] The protective net 9 is in the shape of a circular ring or a sector ring, located on the upper part of the annular air intake fan of the rotor 1, and is fixedly connected with the outer shell of the aircraft to filter the air and prevent foreign matter from being sucked into the duct.

[0033] To adapt to civil low-altitude efficient and rapid horizontal flight and hovering driving, a sector-shaped cover plate 10 is designed in the front half of the annular air intake of the rotor 1. When the aircraft is vertically taking off and landing, the sector-shaped cover plate 10 is opened, and when the aircraft is horizontally flying, the sector-shaped cover plate 10 is closed to suck air from the horizontal air intake 11 at the front end of the aircraft. Secondly, main wings 22 with tilting and telescoping functions are arranged on both sides of the aircraft, and a naturally shaped tail wing 23 is arranged at the tail of the aircraft, and a vertical rudder wing 24 is designed on the upper part of the tail wing.

[0034] The aircraft in Example 1 fully utilizes the "double-duct and rotor self-rotation gain technology", and at the same time, absorbs the advantages of existing fixed-wing aircraft and hovering carriers. The power coordination mode can realize efficient operation in different flight states. When vertically taking off and landing, the sector-shaped cover plate 10 is opened, and the annular air intake fan blades 8 of the rotor 1 suck air through the edge in cooperation with the inclined guide baffle 3 in the first duct 5, forming a powerful spiral centripetal vortex to drive the rotor 1 to rotate and generate lift. The ducted fan 4 in the second duct 6 operates at full capacity, and the airflow is divided into the vector nozzle 19 and the vertical nozzle 20 through the diversion pipeline 29, which cooperates with the rotor self-rotation lift to ensure stable and reliable vertical take-off and landing, and precise control of height and attitude.

[0035] When horizontally flying, the sector-shaped cover plate 10 is closed, and the aircraft sucks air from the front horizontal air intake 11 to reduce air resistance; the main wings 22 on both sides are tilted to the horizontal state and extended, and the tail wing 23 and the vertical rudder wing 24 at the tail work cooperatively, combined with the forward thrust generated by the airflow through the horizontal nozzle 21 of the second duct 6, to have the high-speed horizontal flight capability similar to that of a fixed-wing aircraft. The tilting and telescoping functions of the main wings 22 can be adjusted according to the flight speed and load to optimize the aerodynamic layout and improve the low-altitude efficient and rapid horizontal flight performance, meeting the demand for rapid transportation in the civil low-altitude field.

[0036] The innovation of the aircraft power system has significant functional advantages: the magnetic suspension device (16, 17, 18) reduces the mechanical friction of the rotor 1 and the fixed shell surface 2 and other components, reduces energy loss and noise, and the integrated damping compensation and energy recovery module improves energy utilization efficiency and prolongs the endurance time; the protective net 9 provides safety protection for the power system and ensures stable operation in complex environments.

[0037] In practical applications, the multifunctional aircraft has wide applicability: in the field of urban low-altitude logistics, it can vertically take off and land into narrow streets or rooftop platforms to deliver goods, and also can quickly fly horizontally to realize long-distance transportation and improve logistics efficiency; in emergency rescue, the flexible take-off and landing capability can reach disaster sites that conventional transportation tools cannot reach, and quickly transport rescue personnel and materials; in short-distance intercity transportation, low-altitude routes are used to avoid ground congestion, providing an efficient and convenient travel method.

[0038] In addition, the boat-shaped design of the lower cabin 13 and the lower shell surface 15 provides water floating capability in emergency situations, increasing operational safety; the front wheels 25 and rear wheels 26 make ground movement as convenient as a vehicle, realizing seamless switching from the ground to the low altitude, and truly achieving "land-air integration".

[0039] In summary, the aircraft of Example 1, with the "double-duct and rotor self-rotation gain technology", combines the high speed of fixed-wing aircraft and the flexibility of suspended vehicles, and has an irreplaceable advantage in the field of civil low-altitude, providing a new solution for low-altitude transportation, logistics, rescue and other industries, and is expected to become an important part of future low-altitude three-dimensional transportation network.

[0040] Following the design of this embodiment, the main wing 22, tail wing 23, vertical rudder wing 24 of the tail, front wheels 25 and rear wheels 26 can be removed, and a water-suspended speedboat can be designed. By simplifying the aerodynamic components, the core technology of double-duct and rotor self-rotation gain is retained, realizing low-cost and fast driving of the water-suspended speedboat.

[0041] Embodiment 2: Referring to FIG. 3, FIG. 4, a single second-duct type hovercar and its dual-duct and rotor self-rotation gain synergizing device are introduced, which has obvious differences in structure compared with Embodiment 1: the tiltable telescopic main wings 22, tail wings 23 and vertical rudder wings 24 on the tail of the aircraft are cancelled; in the dual-duct and rotor self-rotation gain synergizing device, the rotor 1 is located above the first duct 5, the fixed shell surface 2 is below the duct, and the rotor 1 is a rotating body with radially outward bending and curling outer edge; the electric motor 38 is installed on the fixed part of the upper outer shell 14 of the upper cabin 12, the shaft drives the duct fan 4 to rotate in the opposite direction, the inner edge of the rotor 1 is rigidly connected through the bearing 37 on the motor shaft, and the outer edge second magnetic suspension device 17 is retained; the lower cabin 13 is set as a passenger and cargo cabin, the second duct 6 is relatively long and penetrates the lower cabin 13 from top to bottom, and at the lower outer shell 15, it is divided into two through four turning pipes 29 to the front and rear two sides of the lower outer shell 15, and then to the vertical jet 20 or the horizontal jet 21 through the airflow valve 28; at the same time, two front wheels 25 and two rear wheels 26 are provided.

[0042] The core advantage of the hovercar is remarkable. The lower cabin 13 as a passenger and cargo cabin facilitates the entry and exit of passengers and goods, realizes the combination of ground driving and low-altitude hovering, and can well adapt to urban road environment. When driving at low speed, the rotor 1 reduces the speed, uses part of the lift to offset the weight of the car body, reduces the ground pressure of the front wheels 25 and the rear wheels 26, and cooperates with the low friction characteristics of the magnetic suspension device to significantly reduce the driving energy consumption. When it is necessary to cross obstacles or move in low altitude for a short distance, the fan ring cover plate 10 is opened, the lift generated by the cooperation of the dual-duct can make the car body lift 0.5-5 meters, and the horizontal thrust can be adjusted through the vector jet 19 and the airflow valve 28 to realize flexible steering and rapid movement, effectively avoiding ground traffic congestion.

[0043] Further, if the hovercar shape is relatively long and the load is relatively large, two or more invention synergizing devices can be provided on the top of the hovercar to increase its load capacity.

[0044] Embodiment 3: Referring to FIG. 5, FIG. 6, a multi-second-duct large disc-shaped aircraft and its dual-duct and rotor self-rotation gain synergizing device are introduced. Compared with other embodiments, it has distinct structural characteristics: The aircraft is a central axis symmetrical disc without any visible wings. To embody strong transport capacity and versatility, in addition to the overall size scale-up, in the invention efficiency device, the second duct 6 is designed as multiple (more than 3), arranged in a ring array on the inner edge of the first duct, each second duct is equipped with an anti-rotation duct fan 4 and an electric motor 38, and the lower part directly passes through the respective vector nozzle 19.

[0045] The upper cabin 12 and the lower cabin 13 have large spaces, and the upper shell 14 includes a top platform 35 with platform guardrails 36 on the edges of the platform, which is mainly used for launching and landing small unmanned aerial vehicles and disc-shaped aircrafts. In addition, the upper hatch 33, the lower hatch 31 and the partition hatch 32 are respectively arranged at the center of the upper shell 14, the lower shell 15 and the intermediate fixed shell 2, and a vertical lift cabin elevator 34 is arranged to connect the upper and lower cabins and the top platform, realizing cargo transposition.

[0046] This unique design makes the aircraft of embodiment 3 exhibit significant implementation effects: In terms of transport capacity, due to the overall size scale-up and the large space of the upper cabin 12 and the lower cabin 13, a large amount of goods or passengers can be accommodated, greatly improving the transport capacity and meeting the medium and large transport demand.

[0047] In terms of functional versatility, the top platform 35 of the upper shell 14 can be used for launching and landing small unmanned aerial vehicles and disc-shaped aircrafts, expanding the application scenarios of the aircraft, so that it not only completes its own transport task, but also provides support for other small aircrafts.

[0048] In terms of operation and use convenience, the upper hatch 33, the lower hatch 31, the partition hatch 32 and the vertical lift cabin elevator 34 are arranged to facilitate personnel access, cargo loading and unloading and transposition, and improve the overall operation efficiency.

[0049] At the same time, the ring array layout of multiple second ducts 6, together with the respective anti-rotation duct fans 4, electric motors 38 and vector nozzles 19, makes the power output of the aircraft more stable and balanced, and can better control the attitude and adjust the direction during flight, enhancing the safety and reliability of flight.

[0050] Embodiment 4: Referring to Figure 7, a double-duct and rotor self-rotation gain synergistic device for underwater and surface ship sterns is introduced. The ship stern is designed as a conical fixed shell 2, and a conical funnel with a similar shape to the fixed shell is designed as a rotor 1. Negative pressure suction blades 8 are arranged in an annular array and welded on the outer edge of the rotor head. Flow baffles 7 are arranged in an annular array and welded on the middle part of the rotor. Adjustable inclined guide baffles 3 are arranged between the flow baffles and the suction blades. The guide baffles are attached to the fixed shell as a whole. The rotor and the conical fixed shell form a conical first duct 5, and the rear circular tube part of the rotor forms a second duct 6. Boosting blade rings 41 are arranged in an annular array on the inside of the tail, and are rigidly connected to the power shaft through bearings 37. Magnetic suspension devices 17 are designed between the annular surface of the rotor head edge and the protective net 9 on the fixed shell. An electric motor 38 is installed inside the ship stern, which drives the counter-rotating propeller 40 through the shaft. The water flow is directly sprayed from the tail of the rotor. To prevent debris in the water from blocking the protective net 9, a scraper 39 can be welded on the edge of the rotor head.

[0051] This embodiment is wrapped in a smooth rotor on the whole, and is a fluid work synergistic device designed for underwater and surface ship sterns. The double-duct design optimizes the water flow path, and the negative pressure suction + boosting blades improve the power utilization efficiency, achieving "high energy efficiency and large thrust". The magnetic suspension device reduces mechanical friction, and cooperates with the smooth rotor shell to greatly reduce the operating noise, which is suitable for military concealment requirements.

[0052] The existing ship sterns are mostly conical, which matches the shape of the device fixed shell, facilitating modification and upgrading, especially suitable for military ships and submarines with strict requirements on concealment (low noise) and power performance (high thrust), while also having the convenience of modifying existing ships.

[0053] This device realizes the three core values of "synergistic effect, noise reduction, and easy modification" through structural innovation (double-duct, magnetic suspension) and functional synergy (suction + guide + boosting), which is of great significance for upgrading the ship power system.

[0054] Example 5: Referring to Figure 8, a dual-cone rotor type dual-duct and rotor rotation gain synergistic device is introduced. The device is mainly composed of a funnel-shaped outer shell containing a conical fixed shell surface 2 and a conical surface of a double-cone rotor 1 forming a first duct 5, the rear circular tube part of the outer shell forms a second duct 6, a ring array of negative pressure suction blades 8 is arranged at the outer edge of the rotor, a ring array of fixed flow barriers 7 is arranged in the middle of the rotor, adjustable inclined guide baffles 3 are arranged on the fixed shell surface between the flow barriers and the suction blades, the front conical surface of the rotor is either smooth or provided with centrifugal guide strips 42, two bearings 37 (including magnetic suspension bearings) are used to rigidly connect the head protection net 9 of the invention, the second duct 6 and the rotating shaft of the duct fan 4 or propeller 40, the duct fan or propeller is driven by the motor 38 fixed to the outer shell, and the air flow or water flow is directly ejected from the tail of the outer shell.

[0055] The core advantages of this synergistic device are: dual-duct synergistic effect: the first duct enhances the kinetic energy of the fluid through negative pressure suction, flow guide optimization and other designs, and the second duct directly drives the fluid with the help of power components, both of which work together to significantly improve fluid utilization and power output efficiency compared to single-duct structure; strong adjustability: adjustable inclined guide baffles 3 can be flexibly adjusted according to different working conditions (such as fluid density and flow rate requirements), allowing the device to maintain optimal working conditions in a variety of environments and have greater adaptability; compact structure: the components are integrated through bearings and rigid connections, with a reasonable layout that effectively controls the overall size of the device while ensuring synergistic effect, making it easy to install and apply to various equipment (such as aircraft, ship propulsion systems, or various water pumps, etc.); multi-functional adaptation with strong versatility.

[0056] With its efficient fluid power utilization capability and wide adaptability, this device can be applied in multiple fields: in the field of aviation, it can be used as an auxiliary propulsion device for unmanned aerial vehicles and small aircraft to improve endurance and thrust; in shipbuilding engineering, it can be used as an auxiliary power system for ships to enhance navigation speed and fuel economy; in underwater exploration equipment, it can provide stable and efficient propulsion for underwater robots to ensure their workability in complex underwater environments, as well as water pumping or sewage treatment, etc.

[0057] Embodiment 6: Referring to FIG. 9, a bottom booster device type hover motorcycle is introduced, the structure and working principle of the self-rotation gain booster device of its double ducts and rotor are basically the same as those of other embodiments, except that: only the second duct port is circular, not a pipeline, and the disc-shaped container 44 composed of the fixed shell surface 2 and the booster device bottom plate 45 is used to transport fluid to the vector jet 19 fixed under the bottom plate; second duct fan adopts centrifugal fan 43, and the space above the booster device top plate 46 carries people and objects. The structure of the booster device of the invention designed in this way is simpler and more compact. If a duct fan is added to each vector jet, a reasonable algorithm is adopted, the rotation speed of each duct fan is adjusted, the booster device is kept stable, the safety and stability of the flight process are ensured, the vector jet 19 is turned by the handle, and the flexible turning experience similar to a motorcycle can be realized, greatly improving the control and interest of driving. In terms of application scenarios, the bottom booster device type hover motorcycle has a short distance low altitude flight capability of 5-10 kilometers, is very suitable for urban short distance commuting, can effectively avoid ground traffic congestion, and improve travel efficiency; at the same time, it can also be used as a scenic area walking tool, so that tourists can more easily and conveniently tour the scenic area, and improve the tour experience.

[0058] In summary: the invention focuses on the core technology of "double ducts and rotor self-rotation gain", and realizes the expansion application of multi-field flight, hovering carrier and ship on the basis of the original disc-shaped aircraft, providing an innovative and efficient technical solution for the field of flight and suspension.

[0059] In terms of core technology, the rotor, fixed shell surface, magnetic suspension device, inclined guide baffle and duct fan are the key structures, the first duct is formed by the rotor and the fixed shell surface, and the second duct is distributed in the center or in the ring shape, and the double duct cooperation system is constructed. The ring-shaped suction blade at the front end of the rotor sucks in air / water, which forms a spiral centripetal vortex under the action of the inclined guide baffle of the spiral curved surface plate or the straight surface plate (the spiral curved surface plate can form a double spiral centripetal vortex), drives the rotor to rotate to generate gain lift and thrust, and at the same time, the fluid is gathered to the second duct, and the attitude control is realized through the vector jet and other devices. The magnetic suspension device reduces friction loss and integrates energy recovery function, further improving energy efficiency.

[0060] The embodiment design embodies the flexibility and adaptability of the technology. The low-altitude type multifunctional aircraft of embodiment 1 retains the tiltable retractable main wing and vertical rudder wing, combines the characteristics of fixed wing and suspended carrier, is equipped with tiltable retractable main wing, tail wing and land-air integrated moving parts (front wheel, rear wheel), the lower shell is boat-shaped and has water floating capacity. When taking off and landing vertically, the rotor rotates and the double channel cooperates to generate lift; when flying horizontally, the fan-shaped cover plate is closed, high-speed cruising is realized by using the main wing and horizontal nozzle, and it is suitable for city low-altitude logistics, emergency rescue and short-distance intercity transportation; embodiment 2: single second channel type suspended vehicle, canceling the wing, taking ground driving and low-altitude suspension as the core, the lower cabin is a passenger and cargo cabin, the second channel penetrates the cabin, the direction is adjusted through the vector nozzle, the lift is used to reduce the ground pressure at low speed, and the energy consumption is reduced; short-distance can be lifted 0.5-5 meters to avoid congestion, the derived suspended motorcycle is more portable, and is suitable for city commuting and scenic area walking. Embodiment 3: multi-second channel medium / large disc-shaped aircraft, disc-shaped design, no exposed wing, more than 4 second channels are arranged in annular array, equipped with a top platform (landing small aircraft) and a vertical elevator, the cabin space is large, the power is balanced and stable, the transportation capacity is strong, and a large number of personnel or goods can be carried, and the "mother machine" role (supporting small aircraft landing) is considered, suitable for medium / large transportation and multi-task cooperation scene; embodiment 4: ship stern double channel efficiency device, the conical fixed shell surface cooperates with the rotor to form a double channel, the tail is provided with a booster blade ring and a reverse propeller, and is equipped with a scraper cleaning protective net. The double channel optimizes the water flow path, the magnetic suspension device reduces noise, the thrust is large and the concealment is strong, which is suitable for existing ship modification and is suitable for military ships and submarines; embodiment 5: the device has high efficient fluid power utilization capacity and wide adaptability, and can be applied to multiple fields: in the field of aviation, it can be used as an auxiliary propulsion device of unmanned aerial vehicle and small aircraft to improve the endurance capacity and thrust; in the field of ship engineering, it can be used as an auxiliary power system of ship to enhance the navigation speed and fuel economy; in underwater detection equipment, it can provide stable and efficient propulsion for underwater robots to guarantee the operation capacity of the robots in complex underwater environment and water pumping or sewage treatment.

[0061] All embodiments include a first channel and a second channel. The first channel is an annular space (such as a disc, a bowl, a cone, etc.), which is formed by the rotor and the fixed shell surface, and is responsible for inhaling and preliminarily guiding the fluid (air or water); the second channel is a central or annular array of tubular channels, which receives the fluid from the first channel and further accelerates, and generates power through the vector nozzle or direct injection.

[0062] Rotor rotation gain: the rotor is the core rotating part, the annular negative pressure flow blade at the head of the rotor generates negative pressure by rotation, actively inhales fluid; the middle flow barrier and the inclined flow guide barrier cooperate to stabilize the flow, drive the rotor to rotate and form a spiral centripetal vortex, improve the fluid utilization rate, and realize the "rotation gain" effect.

[0063] Auxiliary system: universally equipped with magnetic suspension devices (reducing mechanical friction and noise), protective nets (filtering debris), adjustable guide / nozzle components (controlling attitude and direction), some designs include energy recovery modules to improve energy efficiency and safety.

[0064] Cross-field applicability: core technology can be transferred to aviation, ground transportation, and marine fields by adjusting the duct shape, fluid type (air / water), and auxiliary components to meet the power needs of different vehicles.

[0065] Performance breakthrough: dual-duct and rotor self-rotation synergy improves energy efficiency by more than 30%; magnetic suspension devices and smooth hulls significantly reduce noise, improving concealment in military scenarios; vector nozzles and adjustable components enhance attitude control accuracy.

[0066] Practicality and economy: structural design adapts to existing vehicles (such as ship sterns), with low modification difficulty; some designs (such as land-air integration, water surface floating) expand emergency capabilities and improve operational safety.

[0067] Through the innovative architecture of "dual-duct + rotor self-rotation gain", this invention breaks through the limitations of traditional vehicle power systems, achieving the comprehensive advantages of "high efficiency, low noise, multi-function, and easy modification". From civilian low-altitude logistics, urban commuting to military ships, and medium-to-large transportation, its application scenarios cover land, sea, and air, providing core solutions for future three-dimensional transportation networks and vehicle power upgrades, with important technical breakthrough value and industrial application prospects.

Claims

1. A fluid work enhancement device based on dual-ducted and rotor spin gain, characterized by, The double duct structure and auxiliary system are composed of a rotor (1), a fixed shell surface (2), a diagonal guide baffle (3), a magnetic suspension device (16-18), a duct fan (4) or a propeller (40); The rotor (1) is a rotating body with a rotor surface similar to the fixed shell surface, an outer edge bent and curled towards the fixed shell surface, a head bent and curled part provided with annular negative pressure suction blades (8), and a middle part provided with a flow baffle (7), which can be driven to rotate by a spiral centripetal vortex to realize energy gain; The fixed shell surface (2) is parallel to the rotor (1) to form a first duct (5), the diagonal guide baffle (3) is annularly arranged in the first duct (5) close to the outer edge and connected with the fixed shell surface (2), and the radial included angle can be adjusted as a whole to convert centripetal fluid into spiral centripetal vortex to drive the rotor (1) to rotate; The double duct structure further includes a second duct (6) which is characterized by random transmission and no strict specific shape, commonly in the shape of a tube, and the length and whether it is curved need to be determined according to the actual application scene, and it can be single (located in the center of the first duct) or multiple (annularly arranged in the inner edge of the first duct), which can receive the fluid in the first duct (5) and accelerate the ejection through the counter-rotating duct fan (4) or propeller (40) to the vector jet (19), vertical jet (20) or horizontal jet (21) to output power, and the fluid power can be directly output, divided into multiple parts or combined into one part during power transmission; The magnetic suspension device (16, 17, 18) is at least three groups, arranged on the edge and middle part of the rotor (1) and the circular surface close to the fixed shell surface (2) or other fixed parts, used to reduce mechanical friction, adopts permanent magnet suspension, electromagnetic suspension or combination of the two, can integrate damping compensation module and energy recovery module, when the diameter of the magnetic suspension device is small, the magnetic suspension device can be replaced by a bearing; The duct fan (4) and propeller (40) include shaft or shaftless duct fan (4) and propeller (40); as for the duct fan (4), it is usually placed in the second duct, and the fan is mostly axial type, when the second duct is unique, the duct fan can be placed in the center of the first duct, and it is a centripetal suction fan, when the second duct is not in the shape of a tube, the duct fan is placed at the head of the second duct, and it is a centrifugal fan.

2. The apparatus of claim 1, wherein, The auxiliary system includes a protection assembly and a control component; The protection assembly includes a protection net (9) and a protection device (30), the protection net (9) is arranged at the inlet of the fluid entering the first duct (5) and connected and fixed with the fixed shell surface (2) to filter foreign matters in the fluid, and the protection device (30) is used to prevent the rotor from colliding with the outside world; The control component includes a vector jet (19) and an air flow valve (28) in addition to the diagonal guide baffle (3), the vector jet (19) can realize extension, rotation and tilting in the range of ±45° to ±60°.

3. The apparatus of claim 1, wherein, The oblique guide baffle (3) is a straight panel or a spiral curved panel, which can convert the fluid entering the first duct (5) into a spiral centripetal vortex, and the vortex acts on the baffle (7) of the rotor (1) to drive the rotor (1) to rotate; the radial angle of the oblique guide baffle (3) is adjusted according to the change of the rotating speed of the power component in the second duct (6), and when the device is relatively static, the aircraft and the suspended vehicle can be turned by changing the angle.

4. A multi-functional aircraft using the device of any one of claims 1-3, characterized in that: It has an upper cabin (12) and a lower cabin (13), and the fluid working efficiency device is built in the lower cabin (13), the lower outer shell (15) of the lower cabin (13) is boat-shaped, and is provided with front wheels (25), rear wheels (26) and a front horizontal air inlet (11); It is equipped with a tiltable telescopic main wing (22), a tail wing (23) and a vertical rudder wing (24); The front part of the annular air inlet of the rotor (1) is provided with a fan-shaped cover plate (10), which is opened in the vertical take-off and landing state and closed in the horizontal flight state, and the fluid is introduced through the front horizontal air inlet (11).

5. A suspended vehicle using the device of any one of claims 1-3, characterized in that: There is no wing structure, the lower cabin (13) serves as a passenger and cargo cabin, the second duct (6) penetrates through the lower cabin (13) from top to bottom, and is connected to the vector jet (19) on the front side and the air flow valve (28) on the rear side of the lower outer shell (15) through four rotating pipes (29) respectively; The rotor (1) is located above the first duct (5), the outer edge is radially bent and curled outward, the inner edge is rigidly connected to the rotating shaft of the motor (38) through a bearing (37), and the second magnetic suspension device (17) is arranged at the outer edge; It is provided with two front wheels (25) and two rear wheels (26), which can realize ground driving and low-altitude suspension at a height of 0.5-5 meters.

6. A medium / large disc-shaped aircraft using the device of any one of claims 1-3, characterized in that: It is a whole disc-shaped structure with central axis symmetry, without external wings, the inner edge of the first duct (5) is arranged with four or more than four second ducts (6) in a ring shape, each second duct (6) is equipped with a counter-rotating duct fan (4) and a corresponding motor (38), and is connected to an independent vector jet (19) at the lower part; The upper cabin (12) and the lower cabin (13) have large space capacity, the upper outer shell (14) is provided with a top platform (35), and the edge of the top platform (35) is provided with a platform guardrail (36); The center of the upper outer shell (14), the lower outer shell (15) and the fixed shell surface (2) is respectively provided with an upper cabin door (33), a lower cabin door (31) and a partition door (32), and is connected through a vertically lifting cabin elevator (34).

7. A ship efficiency device using the device of any one of claims 1-3, characterized in that: The fixed shell surface (2) is a conical structure at the stern of a ship, the head of the rotor (1) is a conical funnel matched with the shape of the fixed shell surface (2), and a conical first duct (5) is formed between them. The tail pipe of the rotor (1) constitutes a second duct (6), and an annular array of boost blades (41) is arranged inside the tail of the second duct (6), and the second duct (6) is rigidly connected with the power shaft through a bearing (37); The annular array of negative pressure suction blades (8) is welded to the inner part of the head of the rotor (1), and the annular array of baffles (7) is welded to the middle part of the rotor (1), and the magnetic suspension device (17) is arranged between the edge of the rotor (1) and the protective net (9) on the fixed shell surface (2), and the scraper (39) for cleaning the protective net (9) is welded to the edge of the head of the rotor (1); The electric motor (38) is installed inside the stern of the ship, and the electric motor (38) drives the counter-rotating propeller (40) through the shaft, so that the water flows out from the tail of the second duct (6).

8. A device for augmenting the performance of a dual-ducted and rotor-spinning gain twin-cone-rotor, characterized by, The funnel-shaped shell, the double-cone-shaped rotor (1), the negative pressure suction blades (8), the fixed baffle (7), the adjustable oblique guide baffle (3), the bearing (37), the head protective net (9), the duct fan (4) or the propeller (40) and the motor (38) are included; The front end of the funnel-shaped shell comprises a conical fixed shell surface (2), and the rear end extends out a pipe part, one conical surface of the double-cone-shaped rotor (1) cooperates with the conical fixed shell surface (2) to form a first duct (5), and the pipe part at the rear of the funnel-shaped shell constitutes a second duct (6) by itself; The negative pressure suction blades (8) are arranged in an annular array at the outer edge of the double-cone-shaped rotor (1), the fixed baffles (7) are arranged in an annular array at the middle part of the double-cone-shaped rotor (1), and the adjustable oblique guide baffles (3) are arranged in an annular array on the conical fixed shell surface (2) and located between the fixed baffles (7) and the negative pressure suction blades (8); The front conical surface of the double-cone-shaped rotor (1) is a smooth surface or provided with centrifugal guide strips (42); The two sharp heads of the double-cone-shaped rotor (1) are respectively rigidly connected with the head protective net (9) and the rotating shaft of the duct fan (4) or the propeller (40) through the bearings (37) (including magnetic suspension bearings), the duct fan (4) or the propeller (40) is arranged in the second duct (6), the motor (38) is fixedly connected with the funnel-shaped shell and drives the duct fan (4) or the propeller (40) to operate, so that the air flow or water flow can be sprayed from the tail of the funnel-shaped shell.

9. A bottom boost device type hover motorcycle, characterized by, The efficiency increasing device comprises a fixed shell surface (2), an efficiency increasing device bottom plate (45), a disc-shaped container (44), a vector jet (19), a centrifugal fan (43) and an efficiency increasing device top plate (46); The disc-shaped container (44) is jointly constituted by the fixed shell surface (2) and the efficiency increasing device bottom plate (45) and is used for transferring fluid, and the second duct opening of the efficiency increasing device is circular and is not in the form of a pipe; The centrifugal fan (43) is arranged in the duct and is adapted to the fluid transfer requirement of the disc-shaped container (44); The vector jet (19) is fixed below the efficiency increasing device bottom plate (45) and receives the fluid transferred by the disc-shaped container (44), and the steering direction of the vector jet (19) is directly controlled by a handle; The top plate (46) of the synergistic device is used for carrying people and objects in the upper space; A ducted fan can be additionally arranged at each vector jet (19), and the rotation speed of each ducted fan and the direction of the vector jet are adjusted through a reasonable algorithm to control the synergistic device to maintain a stable state.

10. The apparatus or application of any of claims 1-9, wherein, The direction of the flow suction of the rotor (1) is determined according to the application scene: upward in vertical take-off and landing aircraft and hovering vehicles, and forward in gliding aircraft and water surface and underwater ships; for medium, large or super large aircraft (including disc-shaped aircraft), hovering vehicles and ships, according to the morphological characteristics and travel requirements, a plurality of synergistic devices can be arranged on the whole.

Images