Unmanned aerial vehicle cooperates with jet flow variable inlet duct, propeller and unmanned aerial vehicle

Abstract

The application provides a variable inlet duct, a propeller and a UAV cooperating with a jet flow, the variable inlet duct comprising: an inner duct sidewall; an outer duct sidewall sleeved outside the inner duct sidewall and provided with a mounting chamber, a plurality of split lips are arranged on the front end ring of the outer duct sidewall, and a duct trailing edge is arranged at the rear end of the outer duct sidewall; the outer duct sidewall, the inner duct sidewall and the duct trailing edge jointly form an annular channel, the front end of the inner duct sidewall and the front end of the outer duct sidewall form a blowing port, and the inner duct sidewall and the duct trailing edge form an air inlet; the cooperating jet flow device comprises: a plurality of partitions arranged along the axial direction of the annular channel and forming a plurality of air ducts connected with the blowing port and the air inlet; a compression pump arranged in the air duct; and a variable air inlet device comprising: a driving assembly arranged in the mounting chamber and in transmission connection with the split lips, so as to drive the split lips to deform forward and downward along the contour of the inner duct sidewall and the outer duct sidewall, so as to change the airfoil of the lips.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and in particular to a variable intake duct, propeller and UAV for UAV cooperative jet in a wide range of operating conditions. It can improve the gas flow on the inner and outer surfaces of the shafted duct, improve the operating efficiency of the UAV propulsion system and ensure the flight stability of the UAV in a wide range of operating conditions. Background Technology

[0002] In the modern aviation industry, the research and application of unmanned aerial vehicles (UAVs) are becoming increasingly widespread. In particular, the design of the propulsion system is a key factor in ensuring the power and safe flight of UAVs. Propeller-driven UAVs typically operate under complex flight conditions. Especially for UAVs intended for near-space applications, they experience wide ranges of altitude and speed changes during climb, cruise, and descent. These flight conditions negatively impact the efficiency of propeller propulsion systems, and traditional propeller propulsion system designs are insufficient to meet the requirements of UAV applications under such wide flight conditions. To alleviate these problems, in recent years, variable camber technology has been gradually introduced into the design and application of lift-enhancing and efficiency-enhancing propeller and wing airfoils.

[0003] The concept of active flow control is introduced by combining airfoil camber technology. Active flow control is based on the Coanda effect in fluid mechanics, also known as the wall-attachment effect, which causes airflow to deviate from its original flow direction and flow along a convex surface. In aircraft design, this involves introducing additional airflow onto the upper or lower surface of the airfoil to improve airflow over the airfoil surface. The pressure difference between the upper and lower surfaces can be adjusted according to operating conditions, achieving a lift-adjusting effect similar to that of a continuously variable camber airfoil. Because active flow control introduces additional airflow, also called a jet, it will couple and mix with the mainstream airflow, hence the term cooperative jet. Since the 2010s, researchers in this field have made significant progress in cooperative jet research, including UAV design. Extensive analysis of influencing factors in the application of cooperative jets in airfoil design has been conducted, such as the airflow patterns at the inlet and outlet, the inlet and outlet angles, the relative chord length positions of the inlet and outlet, and their impact on adjusting the pressure difference between the upper and lower surfaces of the airfoil, as well as their delaying effect on airflow separation on the airfoil surface.

[0004] Meanwhile, in recent years, from the perspective of improving efficiency and reducing energy consumption, ducted propellers have been researched, developed, and applied in propeller propulsion systems. Compared with traditional propeller systems, the duct structure itself generates additional thrust, significantly improving the propulsion efficiency of propellers with the same disk diameter. However, the structural limitations of ducted propellers bring additional problems. Due to the relative rotation between the propeller and the duct wall, the design inevitably creates a gap between the propeller tip and the inner wall of the duct. This gap will cause tip vortices, resulting in energy and even aerodynamic efficiency losses in the propulsion system. Summary of the Invention

[0005] In view of this, the present invention provides a variable intake duct, propeller and UAV with UAV-coordinated jet, which can optimize the mixing effect of the ducted propeller mainstream and the jet, improve the propulsion efficiency of the ducted propeller under a wide range of operating conditions, and broaden the application range and flexibility of UAV in different flight altitudes and flight speeds.

[0006] According to one aspect of the inventive concept of the present invention, a variable intake duct for a UAV-coordinated jet is provided, comprising:

[0007] The inner wall of the culvert is cylindrical;

[0008] The outer wall of the duct is cylindrical and has an installation chamber. The outer wall of the duct is fitted outside the inner wall of the duct. The front end of the outer wall of the duct is provided with multiple segmented lips, and the rear end is provided with a tail edge of the duct. The outer wall of the duct, the inner wall of the duct, and the tail edge of the duct together form an annular channel. The front end of the inner wall of the duct and the front end of the outer wall of the duct form an air blowing port, and the inner wall of the duct and the tail edge of the duct form an air inlet.

[0009] The coordinated jet device includes:

[0010] Multiple baffles are arranged along the axial direction of the annular channel to form multiple air ducts connecting the air inlet and the air outlet;

[0011] A compression pump is installed inside the air duct;

[0012] Variable intake device, including:

[0013] A drive assembly is disposed in the mounting cavity. The drive assembly is connected to the split lip and is used to drive the split lip to deform forward and downward along the contour of the inner wall and outer wall of the duct, so as to change the lip airfoil.

[0014] Optionally, the air duct extends in a flared shape from the area where the compressor pump is located along the axial direction to both ends.

[0015] Optionally, the upper and lower halves of the inner sidewall of the split-lip mouth are respectively provided with an upper ear plate and a lower ear plate, and the driving assembly includes:

[0016] A movable frame is movably disposed in the mounting chamber along the axis of the intake duct. The inner end of the movable frame along the radial direction of the intake duct is hinged to the lower ear plate via a lower connecting rod, and the outer end of the movable frame along the radial direction of the intake duct is hinged to the upper ear plate via an upper connecting rod.

[0017] A linear motion mechanism assembly is disposed within the mounting cavity;

[0018] The transmission rod is connected at both ends to the linear motion mechanism assembly and the moving frame, respectively.

[0019] Optionally, the driving component further includes:

[0020] One end of the spring is connected to the outer end of the movable frame, and the other end is connected to the area above the ear plate on the inner side wall of the split lip.

[0021] Optionally, the driving component further includes:

[0022] An integral propulsion frame, in the shape of a ring, is slidably disposed in the mounting chamber. The output end of the linear motion mechanism assembly is connected to the integral propulsion frame to push the integral propulsion frame to translate along the axis of the air intake duct within the mounting chamber.

[0023] A rotatable rocker arm is mounted in the mounting cavity. One end of the rocker arm is hinged to the transmission rod, and the other end is hinged to the integral propulsion frame via a connecting rod.

[0024] Optionally, the variable intake duct for the drone-coordinated jet also includes:

[0025] Multiple rectifiers are respectively disposed between two adjacent segmented lips.

[0026] Optionally, the air inlet is located at 10%~15% of the chord length of the airfoil from the leading edge; and / or

[0027] The air inlet is located at a distance of 15% to 20% of the chord length from the airfoil's trailing edge; and / or

[0028] The split lip is positioned at 5% to 10% of the chord length of the airfoil from the leading edge.

[0029] Optionally, the linear motion mechanism assembly includes any of the following: an electric cylinder, a pneumatic cylinder, an electric telescopic rod, and a servo motor.

[0030] According to another aspect of the inventive concept of the present invention, a variable intake duct propeller is also provided, comprising: the variable intake duct as described above.

[0031] According to another aspect of the inventive concept of the present invention, an unmanned aerial vehicle (UAV) is also provided, comprising: a variable intake ducted propeller as described above.

[0032] Compared with the prior art, the variable intake duct, propeller, and drone of the UAV-coordinated jet provided by the present invention have the following beneficial and significant technical effects:

[0033] (1) It is more suitable for UAVs that experience a wide range of flight altitudes and speeds. It adjusts the air intake according to the real-time flight conditions to meet the thrust requirements while reducing the power consumption of the propulsion system.

[0034] (2) The variable lip airfoil profile is achieved by driving the linear motion mechanism component with a linear servo motor. The segmented lip is designed with corresponding dimensions according to the characteristics of the annular duct structure to ensure that the airfoil profile of the duct changes continuously and smoothly during the variable flow process.

[0035] (3) It can continuously adjust the air intake of the ducted propeller and achieve continuous and controllable thrust.

[0036] (4) When applied to wide-range working conditions, the relevant parameters of the coordinating device (mass flow rate of the blowing port, mass flow rate of the air inlet, etc.) and the parameters of the variable lip mechanism (stroke of the linear motion mechanism components, etc.) can be changed. Through the synergistic effect of the two, the mixing effect of the mainstream and jet of the ducted propeller can be optimized, and the propulsion efficiency of the ducted propeller under wide-range working conditions can be further improved.

[0037] (5) The propulsion system assembly can be optimized by designing the duct structure, the cooperative jet structure and the variable lip mechanism according to the flight indicators of the UAV to meet the usage requirements. Attached Figure Description

[0038] The above and other objects, features and advantages of the present invention will become more apparent from the following description of embodiments of the invention with reference to the accompanying drawings, in which:

[0039] Figure 1 This is an isometric and perspective view of an undeformed variable intake duct of a drone-coordinated jet according to an embodiment of the present invention.

[0040] Figure 2 This is an undeformed front view of a variable intake duct for a drone-coordinated jet according to an embodiment of the present invention.

[0041] Figure 3 This is an isometric view and perspective view of a variable intake duct with a deformed lip according to an embodiment of the present invention;

[0042] Figure 4 This is a front view of a variable intake duct with a deformed lip according to an embodiment of the present invention;

[0043] Figure 5 for Figure 1 A cross-sectional view of the variable intake bypass shown in Figure AA;

[0044] Figure 6 A schematic diagram of the lip deformation mechanism of the variable intake duct;

[0045] Figure 7 for Figure 6 A magnified schematic diagram of a single-group lip deformation mechanism is shown.

[0046] Figure 8 Flow field diagrams for variable inlet ducted propellers with undeformed and deformed lips, without the application of synergistic jets;

[0047] Figure 9 Flow field diagram of variable inlet ducted propeller with synergistic jet for lip deformation configuration 1 and lip deformation configuration 2;

[0048] Figure 10 Total thrust diagram of variable inlet ducted propeller with synergistic jet for lip deformation configuration 1 and lip deformation configuration 2;

[0049] Figure 11 Power consumption diagram of variable intake duct propeller with synergistic jet for lip deformation configuration 1.

[0050] The meanings of the reference numerals in the above figures are as follows:

[0051] 1: Ducted propeller;

[0052] 1-1: Inner wall of the culvert;

[0053] 1-2: Outer wall of the culvert;

[0054] 1-3: Culvert tail edge;

[0055] 1-4: Propeller system;

[0056] 2: Coordinated jet device;

[0057] 2-1: Air inlet;

[0058] 2-2: Compression pump;

[0059] 2-3: Air intake;

[0060] 3: Variable intake device;

[0061] 3-1: Split-lip style;

[0062] 3-2: Upper connecting rod;

[0063] 3-3: Lower connecting rod;

[0064] 3-4: Spring;

[0065] 3-5: Move the box;

[0066] 3-6: Transmission rod;

[0067] 3-7: Balanced rocker arm;

[0068] 3-8: Rotary bearing;

[0069] 3-9: Fixed shaft;

[0070] 3-10: Fixed shaft flange;

[0071] 3-11: Linkage;

[0072] 3-12: Overall propulsion frame;

[0073] 3-13: Linear motion mechanism components;

[0074] 3-14: Rectifier. Detailed Implementation

[0075] To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to specific embodiments and accompanying drawings.

[0076] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the invention. The terms “comprising,” “including,” etc., as used herein indicate the presence of the stated features, steps, operations, and / or components, but do not exclude the presence or addition of one or more other features, steps, operations, or components.

[0077] All terms used herein, including technical and scientific terms, have the meanings commonly understood by those skilled in the art, unless otherwise defined. It should be noted that the terms used herein are to be interpreted in a manner consistent with the context of this specification, and not in an idealized or overly rigid way.

[0078] When using expressions such as "at least one of A, B, and C," the meaning should generally be interpreted according to the understanding of someone skilled in the art. For example, "a system having at least one of A, B, and C" should include, but is not limited to, systems having A alone, having B alone, having C alone, having A and B, having A and C, having B and C, and / or having A, B, and C. Similarly, when using expressions such as "at least one of A, B, or C," the meaning should generally be interpreted according to the understanding of someone skilled in the art. For example, "a system having at least one of A, B, or C" should include, but is not limited to, systems having A alone, having B alone, having C alone, having A and B, having A and C, having B and C, and / or having A, B, and C.

[0079] It should also be noted that the directional terms mentioned in the embodiments, such as "up," "down," "front," "back," "left," and "right," are only for reference to the directions in the accompanying drawings and are not intended to limit the scope of protection of the present invention. Throughout the accompanying drawings, the same elements are represented by the same or similar reference numerals. Conventional structures or constructions will be omitted where they may cause confusion in understanding the present invention.

[0080] To address the technical issues mentioned in the background section, we integrate synergistic jet technology into the ducted propeller propulsion system to improve gas flow on the inner and outer surfaces of the duct, thereby increasing the pressure difference between the inner and outer surfaces and effectively leveraging the additional thrust effect of the duct structure on the propeller.

[0081] To further maximize the combined efficiency of the "cooperative jet + ducted propeller" system and to support UAV applications operating in a wider range of conditions (wide speed range, wide airspace), this invention integrates a variable-flow variable-lip mechanism into the aforementioned combined propulsion system. This mechanism adjusts the air intake according to real-time flight conditions, meeting thrust requirements while reducing the power consumption of the propulsion system. A wide speed range refers to the broad range between the minimum and maximum speeds that the aircraft can cover. This requires the aircraft to maintain stable flight performance at both low and high speeds. A wide airspace refers to the aircraft's ability to fly in various airspaces (such as low altitude, medium altitude, high altitude, and near space).

[0082] In use, by changing the relevant parameters of the coordinating device (e.g., the mass flow rate of the blowing port and the mass flow rate of the inlet) and the parameters of the variable lip mechanism (e.g., the stroke of the linear motion mechanism components), the two work synergistically to achieve an optimized mixing effect between the ducted propeller's main stream and the jet, further improving the propulsion efficiency of the ducted propeller under wide operating conditions. Based on this, the above propulsion system can be applied to UAVs flying under wide operating conditions to broaden their application range and flexibility in scenarios with different flight altitudes and speeds.

[0083] Figure 1 This is an isometric and perspective view of an undeformed variable intake duct of a drone-coordinated jet according to an embodiment of the present invention. Figure 2 This is an undeformed front view of a variable intake duct for a drone-coordinated jet according to an embodiment of the present invention. Figure 3 This is an isometric view and perspective view of a variable intake duct with a deformed lip according to an embodiment of the present invention; Figure 4 This is a front view of a variable intake duct with a deformed lip according to an embodiment of the present invention; Figure 5 for Figure 1 The diagram shows a cross-sectional view of the variable intake bypass duct AA.

[0084] According to one aspect of the inventive concept of the present invention, a variable intake duct for a UAV-coordinated jet is provided, such as... Figures 1 to 5 As shown, it includes: an inner duct wall 1-1, an outer duct wall 1-2, a coordinating jet device 2, and a variable intake device 3. The inner duct wall 1-1 is cylindrical. The outer duct wall 1-2 is cylindrical and has an internal installation chamber. The outer duct wall 1-2 is fitted over the inner duct wall 1-1. The front end of the outer duct wall 1-2 (with...) Figure 1 In the coordinate system, the direction indicated by x is rear, and the opposite direction is front. Multiple segmented lips 3-1 are arranged in a ring, and a duct trailing edge 1-3 is provided at the rear end. The outer wall 1-2, inner wall 1-1, multiple segmented lips 3-1, and duct trailing edge 1-3 together form an annular channel. The front end of the inner wall 1-1 and the front end of the outer wall 1-2 form an air inlet 2-1, and the inner wall 1-1 and duct trailing edge 1-3 form an air inlet 2-3. The coordinating jet device 2 includes: baffles and a compressor pump 2-2. Multiple baffles are arranged along the axial direction of the annular channel, forming multiple air ducts connecting the air inlets 2-1 and the air inlets 2-3. The compressor pump 2-2 is located within the air ducts. The variable intake device 3 includes a drive assembly disposed in the mounting chamber. The drive assembly is connected to the split lip 3-1 for driving the split lip 3-1 to deform forward and downward along the contour of the inner wall 1-1 and the outer wall 1-2 of the duct, so as to change the lip airfoil.

[0085] In this embodiment, relevant parameters, such as the mass flow rate of the blowing port 2-1 and the mass flow rate of the air inlet 2-3, can be adjusted by the drive component. At the same time, the parameters of the lip mechanism, such as the output stroke of the drive component, can be changed. Through the synergistic effect of the two, the mixing effect of the mainstream and jet of the ducted propeller can be optimized, thereby improving the propulsion efficiency of the ducted propeller under wide operating conditions.

[0086] According to some embodiments of the present invention, the variable intake duct of the UAV cooperative jet is generally annular, and its cross-section is a high-lift airfoil (multi-element airfoil).

[0087] According to some optional embodiments of the present invention, the inner wall 1-1 of the culvert is a hollow structure to reduce the weight of the structure. Furthermore, the inner wall 1-1 of the culvert has multiple independent spaces to reduce weight without significantly reducing the overall strength of the structure.

[0088] According to some embodiments of the present invention, the cross-section of the split lip 3-1 is arc-shaped and the longitudinal section is U-shaped. The front end of the outer wall 1-2 of the duct (that is, the front end of the mounting chamber) is open. The split lip 3-1 is slidably embedded in the above-mentioned opening. By rotating the split lip 3-1, the airfoil of the lip can be changed, the pressure difference between the inner and outer contour surfaces of the duct can be adjusted, thereby adjusting the lift-drag ratio of the airfoil to change the overall thrust of the duct propeller.

[0089] According to some optional embodiments of the present invention, the number of segmented lip openings 3-1 is multiple. Further optionally, the number of segmented lip openings 3-1 is 5 to 12, for example, 5, 6, 7, 8, 9, 10, 11, or 12.

[0090] According to some optional embodiments of the present invention, the inner wall of the front end of the outer wall 1-2 of the duct extends and bends along an arc, forming an annular air inlet 2-1 together with the front end of the inner wall 1-1 of the duct. The rear end of the trailing edge 1-3 of the duct extends and bends along an arc, forming an annular air inlet 2-3 together with the rear end of the inner wall 1-1 of the duct.

[0091] According to some optional embodiments of the present invention, the inner sidewall 1-1 and the outer sidewall 1-2 of the duct are spaced apart to form a cylindrical channel. Multiple baffles are provided in the cylindrical channel. The baffles are arranged along the axis of the variable intake duct (or approximately / entirely along the axis of the variable intake duct), thereby dividing the cylindrical channel into multiple air ducts. Each air duct is provided with a compressor pump 2-2.

[0092] According to some embodiments of the present invention, in each air duct, with the compressor pump 2-2 as the boundary, the air duct located in front of the compressor pump 2-2 is the blowing air duct, and the air duct located behind the compressor pump 2-2 is the inlet air duct.

[0093] According to some optional embodiments of the present invention, the compression pump 2-2 is located in the middle region of the air duct.

[0094] According to some optional embodiments of the present invention, 5 to 12 sets of discrete cooperative jet devices 2 are arranged circumferentially in the above-mentioned cylindrical channel, for example, 5 sets, 6 sets, 7 sets, 8 sets, 9 sets, 10 sets, 11 sets, and 12 sets.

[0095] Further optionally, each segmented lip 3-1 corresponds to a set of discrete cooperative jet devices 2.

[0096] According to some embodiments of the present invention, the air duct extends in a flared shape from the area where the compression pump 2-2 is located along the axial direction to both ends, so as to facilitate air collection, compression and injection.

[0097] In this embodiment, the co-jet device 2 generates compressed airflow through the compressor pump 2-2, which is then directed to the air inlet 2-1 via the airflow channel. Simultaneously, under the suction of the air inlet 2-3, the compressed airflow enters the air inlet 2-3 along the boundary layer of the inner sidewall 1-1 of the duct through the air inlet 2-1, and returns to the compressor pump 2-2 through the airflow channel, forming a jet. This jet mixes with the mainstream of the ducted propeller, adjusting the system thrust of the ducted propeller. The jet is adjusted by regulating various parameters of the co-jet device 2. Its structural design parameters include the size, relative size ratio, angle, relative angle, relative position of the air inlet 2-1 and the air inlet 2-3, as well as the relative position between each co-jet cavity. Its jet flow design parameters include the power control of the compressor pump 2-2.

[0098] Figure 6 A schematic diagram of the lip deformation mechanism of the variable intake duct; Figure 7 for Figure 6 The diagram shows an enlarged schematic of a single-group lip deformation mechanism.

[0099] According to some embodiments of the present invention, such as Figures 5 to 7 As shown, the upper and lower halves of the inner wall of the split-type lip 3-1 are respectively provided with an upper ear plate and a lower ear plate. The driving assembly includes: a movable frame 3-5, a linear motion mechanism assembly 3-13, and a transmission rod 3-6. The movable frame 3-5 is movably disposed in the mounting chamber along the axis of the intake duct. The inner end of the movable frame 3-5 along the radial direction of the intake duct is hinged to the lower ear plate via a lower connecting rod 3-3, and the outer end of the movable frame 3-5 along the radial direction of the intake duct is hinged to the upper ear plate via an upper connecting rod 3-2. The linear motion mechanism assembly 3-13 is disposed in the mounting chamber. The transmission rod 3-6 is connected at both ends to the linear motion mechanism assembly 3-13 and the movable frame 3-5, respectively.

[0100] In this embodiment, the output end of the linear motion mechanism component 3-13 can move forward or backward along the axis of the variable intake duct, thereby driving the transmission rod 3-6 to extend or retract, so as to change the posture of the split lip 3-1.

[0101] According to some embodiments of the present invention, the movable frame 3-5 is an annular frame structure, slidably disposed within the mounting chamber, and the movable frame 3-5 as a whole translates along the axis of the variable intake duct. Furthermore, a limiting or guiding structure is provided between the movable frame 3-5 and the side wall of the mounting chamber, such as a guide groove combined with a slider; this type of structure is quite common and will not be described in detail here.

[0102] According to some optional embodiments of the present invention, the linear motion mechanism assembly 3-13 includes an electric cylinder, a pneumatic cylinder, an electric telescopic rod, a servo motor, etc.

[0103] According to some embodiments of the present invention, the drive assembly further includes a spring 3-4, one end of which is connected to the outer end of the movable frame 3-5, and the other end is connected to the area above the ear plate on the inner sidewall of the split lip 3-1.

[0104] According to some embodiments of the present invention, the drive assembly further includes an integral propulsion frame 3-12, which is annular and slidably disposed within the mounting chamber. The output end of the linear motion mechanism assembly 3-13 is connected to the integral propulsion frame 3-12 to push the integral propulsion frame 3-12 to translate along the intake duct axis within the mounting chamber. A balance rocker arm 3-7 is rotatably disposed within the mounting chamber. One end of the balance rocker arm 3-7 is hinged to the transmission rod 3-6, and the other end is hinged to the integral propulsion frame 3-12 via a connecting rod 3-11.

[0105] In this embodiment, the overall propulsion frame 3-12 has a ring frame structure, which is similar to the structure of the movable frame 3-5. It also moves as a whole along the axis of the variable intake duct, which will not be described in detail here.

[0106] According to some embodiments of the present invention, the balance rocker arm 3-7 is a long strip structure with a through hole in the middle. A rotary bearing 3-8 is embedded in the through hole. A fixed shaft 3-9 is provided on the inner ring of the rotary bearing 3-8. The upper and lower ends of the fixed shaft 3-9 are connected to the upper and lower side walls of the mounting chamber through a fixed shaft flange 3-10.

[0107] According to some embodiments of the present invention, the variable intake duct of the UAV cooperative jet further includes a plurality of rectifiers 3-14, which are respectively disposed between two adjacent split lips 3-1 to ensure that the lip airfoil is smooth and continuous.

[0108] According to some embodiments of the present invention, the air inlet 2-1 is located at 10%~15% chord length of the airfoil from the leading edge; and / or, the air inlet 2-3 is located at 15%~20% chord length of the airfoil from the trailing edge; and / or, the split lip 3-1 is located at 5%~10% chord length of the airfoil from the leading edge.

[0109] According to some optional embodiments of the present invention, the air inlet 2-1 is located at 13% of the chord length of the airfoil from the leading edge.

[0110] According to some optional embodiments of the present invention, the air inlet 2-3 is located at 18% chord length of the airfoil from the trailing edge.

[0111] According to some optional embodiments of the present invention, the split lip 3-1 is provided at 8% of the chord length of the airfoil from the leading edge.

[0112] According to another aspect of the inventive concept of the present invention, a variable intake ducted propeller is also provided, including the variable intake duct of the UAV cooperative jet as described above.

[0113] According to some embodiments of the present invention, a propeller system 1-4 is provided in the variable intake duct of the UAV cooperative jet.

[0114] According to some embodiments of the present invention, the variable intake ducted propeller is a shafted ducted propeller structure.

[0115] According to another aspect of the inventive concept of the present invention, an unmanned aerial vehicle (UAV) is also provided, comprising a variable-intake ducted propeller as described above.

[0116] The technical solution of the present invention will be further described below with reference to specific embodiments. It should be understood that the specific embodiments are only for the purpose of enabling those skilled in the art to better understand the present invention, and should not be construed as an inappropriate limitation on the scope of protection of the present invention.

[0117] Example 1

[0118] like Figure 1 and Figure 2 As shown, the ducted propeller 1 has an airfoil chord length of 320mm, a maximum airfoil thickness of 45mm, and a duct radius of 300mm. A coordinating jet device 2 and a variable intake device 3 are sequentially arranged between the inner wall 1-1 and the outer wall 1-2 of the duct.

[0119] In the co-jet device 2, the air inlet 2-1 is located at 13% chord length of the airfoil from the leading edge, and the air inlet 2-3 is located at 18% chord length of the airfoil from the trailing edge. A total of eight discrete co-jet devices 2 are arranged circumferentially. In application, the co-jet device 2 generates compressed airflow through the compressor pump 2-2, which is then directed to the air inlet 2-1 via the airflow channel. Simultaneously, under the suction of the air inlet 2-3, the compressed airflow enters the air inlet 2-3 along the boundary layer of the inner wall 1-1 of the duct, and returns to the compressor pump 2-2 through the air inlet channel, forming a jet. This jet mixes with the mainstream of the ducted propeller, adjusting the system thrust of the ducted propeller. The jet is adjusted by regulating various parameters of the co-jet device 2. Its structural design parameters include the dimensions, relative size ratio, angle, relative angle, and relative position of the air inlet 2-1 and air inlet 2-3, as well as the relative positions between the co-jet cavities. Its jet flow design parameters include the power control of the compressor pump.

[0120] In the variable intake device 3, the segmented lip 3-1 is located at 8% of the chord length of the airfoil leading edge, and a total of 8 segments of segmented lips 3-1 are arranged along the circumference, with a set of rectifier vanes 3-14 arranged between each adjacent segmented lip 3-1. Figures 3-4 This diagram illustrates a variable-intake ducted propeller structure with a deformed lip and a coordinated jet flow. Driven by a servo motor, the linkage mechanism of the variable-intake device 3 deforms each structure of the segmented lip 3-1 forward and downward along the contours of the inner duct wall 1-1 and the outer duct wall 1-2, altering the lip airfoil and adjusting the pressure difference between the inner and outer contour surfaces of the duct. This, in turn, adjusts the airfoil lift-to-drag ratio, thereby changing the overall thrust of the ducted propeller. A fairing 3-14 is positioned between each pair of segmented lips 3-1 to ensure a smooth and continuous lip airfoil.

[0121] Figures 5-7 The diagram illustrates the position, dimensions, and structural details of the ducted propeller, the coordinating jet device 2, and the variable intake device 3. The servo motor drives the 360° annular moving frame 3-5 and the integral propulsion frame 3-12 via telescopic linkages. These linkages work in conjunction with the connecting rods to uniformly and synchronously adjust the forward and downward deformation of each segmented lip 3-1, altering the airfoil profile. This design utilizes an integral frame drive concept, reducing the number of connecting rods, lowering the weight of the variable intake device 3, and ultimately improving the thrust-to-weight ratio of the ducted propeller.

[0122] Figure 8The flow field diagrams are shown for variable inlet ducted propellers with undeformed and deformed lips and without the application of synergistic jets.

[0123] Flow field simulation analysis was performed on variable inlet ducted propeller airfoils with undeformed and deformed lips, without the application of cooperative jet, such as... Figure 8 As shown, the results indicate that after the lip is deformed, the airfoil profile of the duct changes, which improves the movement of the airflow stagnation point and increases the thrust in the x-direction.

[0124] Example 2

[0125] Figure 9 Flow field diagram of variable inlet ducted propeller with synergistic jet for lip deformation configuration 1 and lip deformation configuration 2; Figure 10 Total thrust diagram of variable inlet ducted propeller with synergistic jet for lip deformation configuration 1 and lip deformation configuration 2; Figure 11 Power consumption diagram of variable intake duct propeller with synergistic jet for lip deformation configuration 1.

[0126] Simulation calculations were performed on a deformed variable-inlet ducted propeller with a coordinated jet, including lip deformation configurations 1 and lip deformation configuration 2. The calculation results are as follows: Figure 9 and Figure 10 As shown, both configurations employ the same cooperative jet device 2 structural design. The dimensions, relative size ratio, angle, relative angle, relative position of the air inlet 2-1 and air inlet 2-3, as well as the relative positions between each cooperative jet cavity, are consistent. The power of the compression pump 2-2 is also consistent. Comparative results show that in the lip deformation configuration 2, the profile is relatively deformed outward, and the stagnation point moves. Under the same cooperative jet device 2 design, the mass flow rate of the ducted propeller increases with the increase of the cooperative jet aerodynamic force.

[0127] Calculate the power consumption of variable inlet ducted propellers with different cooperative jet aerodynamic forces for lip deformation configuration 1, such as... Figure 11 As shown in the figure. The results show that after changing the lip angle, the ducted propeller profile approaches a higher lift-to-drag ratio airfoil, significantly reducing the power consumption of the ducted propeller.

[0128] The embodiments of the present invention have been described above. However, these embodiments are merely illustrative and not intended to limit the scope of the invention. Although various embodiments have been described above, this does not mean that the measures in the various embodiments cannot be used advantageously in combination. The scope of the invention is defined by the appended claims and their equivalents. Various substitutions and modifications can be made by those skilled in the art without departing from the scope of the invention, and all such substitutions and modifications should fall within the scope of the invention.

Claims

1. A variable intake duct for UAV-coordinated jet propulsion, characterized in that, include: The inner wall of the culvert is cylindrical; The outer wall of the duct is cylindrical and has an installation chamber. The outer wall of the duct is fitted outside the inner wall of the duct. The front end of the outer wall of the duct is provided with multiple segmented lips, and the rear end is provided with a tail edge of the duct. The outer wall of the duct, the inner wall of the duct, and the tail edge of the duct together form an annular channel. The front end of the inner wall of the duct and the front end of the outer wall of the duct form an air blowing port, and the inner wall of the duct and the tail edge of the duct form an air inlet. The coordinated jet device includes: Multiple baffles are arranged along the axial direction of the annular channel to form multiple air ducts connecting the air inlet and the air outlet; A compression pump is installed inside the air duct; Variable intake device, including: A drive assembly is disposed in the mounting cavity. The drive assembly is connected to the split lip and is used to drive the split lip to deform forward and downward along the contour of the inner wall of the duct and the outer wall of the duct, so as to change the lip airfoil. The upper and lower halves of the inner sidewall of the split-lip type are respectively provided with an upper ear plate and a lower ear plate, and the driving assembly includes: A movable frame is movably disposed in the mounting chamber along the axis of the intake duct. The inner end of the movable frame along the radial direction of the intake duct is hinged to the lower ear plate via a lower connecting rod, and the outer end of the movable frame along the radial direction of the intake duct is hinged to the upper ear plate via an upper connecting rod. A linear motion mechanism assembly is disposed within the mounting cavity; The transmission rod is connected at both ends to the linear motion mechanism assembly and the movable frame, respectively. An integral propulsion frame, in the shape of a ring, is slidably disposed in the mounting chamber. The output end of the linear motion mechanism assembly is connected to the integral propulsion frame to push the integral propulsion frame to translate along the axis of the air intake duct within the mounting chamber. A rotatable rocker arm is mounted in the mounting cavity. One end of the rocker arm is hinged to the transmission rod, and the other end is hinged to the integral propulsion frame via a connecting rod.

2. The variable intake duct for UAV-coordinated jet as described in claim 1, characterized in that, The air duct extends in a flared shape from the area where the compressor pump is located along the axial direction to both ends.

3. The variable intake duct for UAV-coordinated jet as described in claim 1, characterized in that, The driving component also includes: One end of the spring is connected to the outer end of the movable frame, and the other end is connected to the area above the ear plate on the inner side wall of the split lip.

4. The variable intake duct for UAV-coordinated jet as described in claim 1, characterized in that, Also includes: Multiple rectifiers are respectively disposed between two adjacent segmented lips.

5. The variable intake duct for UAV-coordinated jet as described in claim 1, characterized in that, The air inlet is located at a distance of 10% to 15% of the chord length from the leading edge of the airfoil; and / or The air inlet is located at a distance of 15% to 20% of the chord length from the airfoil's trailing edge; and / or The split lip is positioned at 5% to 10% of the chord length of the airfoil from the leading edge.

6. The variable intake duct for UAV-coordinated jet as described in claim 1, characterized in that, The linear motion mechanism assembly includes any of the following: an electric cylinder, a pneumatic cylinder, an electric telescopic rod, and a servo motor.

7. A variable intake ducted propeller, characterized in that, include: The variable intake duct for unmanned aerial vehicle (UAV) cooperative jets as described in any one of claims 1 to 6.

8. A drone, characterized in that, include: The variable intake ducted propeller as described in claim 7.

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