A ducted fan power plant for an aircraft and an aircraft

Abstract

The application relates to the technical field of aircraft design, and discloses an aircraft duct power device and an aircraft, which comprise a main body and a connecting mechanism installed in the interior of the main body and used for swinging when the main body moves. After air flow enters the interior of the fixed ring, the air flow is continuously pushed to be sprayed to the gap between the rotating shaft and the inner wall of the duct through the connecting groove near one side of the triangular block, in the process of spraying the air flow, force is applied to the vortex at the rotating shaft and the inner wall of the duct, so that the vortex is changed into a chaotic state, the strong tip vortex at the gap between the rotating shaft and the duct caused by the high-speed rotation of the rotating shaft when part of the air flow is separated from the inner wall of the duct during the lifting of the duct is reduced, the influence of the tip vortex on the rotating shaft is reduced, and the overall quality of the device during operation is improved.

Description

Technical Field

[0001] This invention relates to the field of aircraft design technology, specifically to a ducted propulsion system and an aircraft. Background Technology

[0002] An aircraft ducted propulsion system employs an aerodynamically optimized annular duct that integrates a high-power-density motor and specially designed low-noise fan blades. The aircraft uses this as its core propulsion unit and adopts a distributed layout of multiple devices, combined with an intelligent flight control system to achieve precise control of vertical take-off and landing, hovering, and smooth transition flight.

[0003] During the operation of this power unit, the fan blades are driven to rotate through the duct and internal motor. When the fan blades rotate in the duct, they constrain and accelerate the airflow, thus enabling the unit to operate stably. However, when the ducted power unit of the aircraft is at a high angle of attack, the airflow cannot "attach" well to the leading edge of the duct. This can easily lead to separation due to poor airflow "attachment," preventing the fan from effectively "capturing" the air. As a result, the gas on the high-pressure side can leak through this gap to the low-pressure side, forming strong tip vortices. This reduces the intake efficiency and causes the fan blades to vibrate during rotation, thereby affecting the overall quality of the unit during operation. Summary of the Invention

[0004] To solve the above-mentioned technical problems, the present invention provides a ducted propulsion system and an aircraft, comprising a main body and further comprising:

[0005] The connecting mechanism is installed inside the main body and is used to swing when the main body moves;

[0006] A rotating mechanism is installed inside the connecting mechanism and is used to rotate when the connecting mechanism moves.

[0007] Furthermore, the main body includes:

[0008] A rotating assembly is installed at the bottom of the main body and is used to rotate the main body when it moves.

[0009] The guide component is installed inside the rotating component to assist in its operation.

[0010] Furthermore, the connecting mechanism includes:

[0011] An auxiliary component, which is installed inside the rotating component via a connector, is used to guide the movement of gas;

[0012] The connector includes two fixing rings fixedly disposed on the inner wall of the rotating assembly, and the fixing rings have placement grooves inside;

[0013] The oscillating assembly is installed on the inner wall of the placement slot and is used to open and close when the gas flows.

[0014] Furthermore, the rotating mechanism includes:

[0015] The flow divider assembly is installed inside the auxiliary assembly and is used to rotate during gas flow.

[0016] Furthermore, the rotating assembly includes a duct fixedly connected to the bottom of the wing, a rotating shaft fixedly connected inside the duct, and several fan blades fixedly connected to the outer surface of the rotating shaft.

[0017] Furthermore, the guiding component includes two fixed plates fixedly connected to the inner wall of the duct, and an arc-shaped plate fixedly connected to the inner wall of the fixed plates, with an air intake groove opened on the inner wall of the arc-shaped plate.

[0018] Furthermore, the auxiliary components include several connecting slots formed on the side wall of the placement slot, and several blocking blocks are fixedly connected inside a portion of the connecting slots;

[0019] The side wall of the fixing ring is fixedly connected with several triangular blocks;

[0020] The outer surfaces of the two fixing rings are fixedly connected to the inner wall of the duct, and the inner wall of the fixing rings is fixedly connected to the outer surface of the arc plate.

[0021] Furthermore, the swing assembly includes two fixed blocks fixedly connected to the inner wall of the placement groove, and a closing plate rotatably connected between the two fixed blocks.

[0022] Furthermore, the diversion assembly includes a fixed shaft fixedly connected inside several connecting slots, a rotating block rotatably connected to the outer surface of the fixed shaft, and a diversion plate provided on the inner wall of the several rotating blocks;

[0023] The side of the drainage plate closest to the fixed shaft is fixedly connected to the outer surface of the fixed shaft.

[0024] Furthermore, an aircraft includes wings fixedly connected to the left and right sides of the main body, with connecting frames fixedly connected to the bottom of the wings.

[0025] The present invention has the following beneficial effects:

[0026] 1. In this invention, when the air enters the interior of the fixed ring through the air inlet groove under the guidance of the arc plate, the fixed ring collects the strong airflow during the flight of the aircraft. After the airflow enters the interior of the fixed ring, it will be ejected through the connecting groove near the triangular block to the gap between the rotating shaft and the inner wall of the duct under the continuous push of the subsequent airflow. During the ejection of the airflow, it will exert a force on the vortex at the rotating shaft and the inner wall of the duct, thereby making the vortex into a chaotic state. This reduces the occurrence of strong tip vortices at the gap between the rotating shaft and the duct when the rotating shaft rotates at high speed after some airflow separates from the inner wall of the duct during the lifting of the duct. This reduces the impact of tip vortices on the rotating shaft and improves the overall quality of the device during operation.

[0027] 2. In this invention, the rotating block rotates after being pushed. When the rotating block rotates, its recessed part will detach from the inner wall of the fixed ring and rotate towards the fan blade side, thus exposing a gap. Then, it will spray out through the gap between the rotating block and the fixed ring towards the side wall of the fan blade. When the airflow is sprayed out, it will contact the side wall of the fan blade, thereby applying a force to the other side when pressure is generated on the rotating side of the fan blade. By applying two forces to the same fan blade, the fan blade remains stable when rotating, reducing the vibration of the blade tip due to the pressure generated by the fan blade rotation during rapid rotation. This keeps the fan blade stable during operation and improves the efficiency of the device during operation.

[0028] 3. In this invention, after the closed plate rotates, the airflow enters the interior of the fixed ring. At this time, under the guidance of the guide plate, most of the airflow contacts the flat surface of the rotating block. Then, with the continuous flow of airflow, the flat surface of the rotating block is pushed to rotate the rotating block. After the rotating block rotates, the airflow will be in a horizontal state and contact the side wall of the rotating shaft. This allows the airflow to better fit with the inner wall of the duct when the main body is in horizontal flight, reducing the situation where the airflow is dispersed due to the effect of the arc plate when the duct changes from an inclined state to a horizontal state, thus reducing the airflow separation effect when the duct is flying, and further improving the overall quality of the device during operation.

[0029] 4. In this invention, the airflow propelling the rotating block will spray out to both sides along the concave part of the rotating block. When the airflow is sprayed out to both sides through the concave part of the rotating block, it will be guided by the inclined surface of the triangular block to flow at an angle towards the side wall of the rotating shaft, while applying a thrust to the side wall of the rotating shaft. This makes the force on the rotating shaft more stable during rotation and reduces the situation where the rotating shaft shakes due to uneven force caused by distance when the airflow is sprayed out from the concave part of the rotating block towards the side wall of the rotating shaft. Attached Figure Description

[0030] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0031] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0032] Figure 2 This is a partial cross-sectional view of the structure of the present invention;

[0033] Figure 3 This is a schematic diagram of the guide component of the present invention;

[0034] Figure 4 This is a schematic diagram of the auxiliary components of the present invention;

[0035] Figure 5 This is a schematic diagram of the swing component of the present invention;

[0036] Figure 6 For the present invention Figure 5 Enlarged view of point A in the middle;

[0037] Figure 7 This is a partial planar schematic diagram of the present invention;

[0038] Figure 8 For the present invention Figure 7 Enlarged view of point B in the middle;

[0039] Figure 9 This is a diagram showing the connection relationships of some components of the present invention.

[0040] The attached diagram lists the components represented by each number as follows:

[0041] In the diagram: 1. Main body; 101. Wing; 102. Connecting frame; 11. Rotating assembly; 111. Duct; 112. Rotating shaft; 113. Fan blade; 12. Guiding assembly; 121. Fixing plate; 122. Arc plate; 123. Air intake slot; 2. Connecting mechanism; 21. Auxiliary assembly; 211. Fixing ring; 212. Placement slot; 213. Connecting slot; 214. Blocking block; 215. Triangular block; 22. Swinging assembly; 221. Fixing block; 222. Closing plate; 3. Rotating mechanism; 31. Diverting assembly; 311. Fixing shaft; 312. Rotating block; 313. Drain plate. Detailed Implementation

[0042] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0043] Please see Figure 1 - Figure 9 As shown, the present invention is a ducted propulsion system and an aircraft, comprising a main body 1, and further comprising:

[0044] The connecting mechanism 2 is installed inside the main body 1 and is used to swing when the main body 1 moves;

[0045] Rotating mechanism 3 is installed inside connecting mechanism 2 and is used to rotate when connecting mechanism 2 moves.

[0046] Entity 1 includes:

[0047] Rotating assembly 11 is installed at the bottom of the main body 1 and is used to rotate when the main body 1 moves;

[0048] The guide component 12 is installed inside the rotating component 11 to assist the operation of the rotating component 11.

[0049] The connecting mechanism 2 includes:

[0050] Auxiliary component 21 is installed inside the rotating component 11 via a connector and is used to guide the movement of gas;

[0051] The connector includes two fixing rings 211 fixedly disposed on the inner wall of the rotating assembly 11, and the fixing rings 211 have placement grooves 212 inside;

[0052] The swing assembly 22 is installed on the inner wall of the placement groove 212 and is used to open and close when the gas flows.

[0053] Rotating mechanism 3 includes:

[0054] The flow splitter assembly 31 is installed inside the auxiliary assembly 21 and is used to rotate during gas flow.

[0055] The rotating assembly 11 includes a duct 111 fixedly connected to the bottom of the wing 101. A rotating shaft 112 is fixedly connected inside the duct 111. Several fan blades 113 are fixedly connected to the outer surface of the rotating shaft 112. After the rotating block 312 rotates, the airflow will be in a horizontal state and contact the side wall of the rotating shaft 112, so that the airflow can better fit the inner wall of the duct 111 when the main body 1 is in horizontal flight.

[0056] The guiding component 12 includes two fixed plates 121 fixedly connected to the inner wall of the duct 111. An arc-shaped plate 122 is fixedly connected to the inner wall of the fixed plate 121. An air inlet groove 123 is opened on the inner wall of the arc-shaped plate 122. When the main body 1 drives the duct 111 to continuously climb, the airflow that is separated from the inner wall of the duct 111 will directly contact the arc-shaped plate 122 fixed to the inner wall of the duct 111 by the fixed plate 121 under the action of the tilt angle. Then, under the guidance of the arc-shaped plate 122, it enters the interior of the fixed ring 211 through the air inlet groove 123.

[0057] The auxiliary component 21 includes a number of connecting slots 213 formed on the side wall of the placement slot 212, wherein a number of blocking blocks 214 are fixedly connected inside a portion of the connecting slots 213;

[0058] The side wall of the fixing ring 211 is fixedly connected with several triangular blocks 215;

[0059] The outer surfaces of the two fixed rings 211 are fixedly connected to the inner wall of the duct 111, and the inner wall of the fixed rings 211 is fixedly connected to the outer surface of the arc plate 122. The fixed rings 211 collect the strong airflow during the flight of the aircraft. After the airflow enters the interior of the fixed rings 211, it will be ejected through the connecting groove 213 near the side of the triangular block 215 into the gap between the rotating shaft 112 and the inner wall of the duct 111 under the continuous push of the subsequent airflow.

[0060] The swing assembly 22 includes two fixed blocks 221 fixedly connected to the inner wall of the placement groove 212. A closing plate 222 is rotatably connected between the two fixed blocks 221. When the airflow passes through the connecting groove 213, it will apply a thrust to the closing plate 222 to make it rotate around the fixed block 221. After the closing plate 222 rotates, the airflow will enter the interior of the fixed ring 211.

[0061] The diversion assembly 31 includes a fixed shaft 311 fixedly connected inside several connecting slots 213. A rotating block 312 is rotatably connected to the outer surface of the fixed shaft 311, and a diversion plate 313 is provided on the inner wall of the several rotating blocks 312.

[0062] The side of the guide plate 313 near the fixed shaft 311 is fixedly connected to the outer surface of the fixed shaft 311. When the airflow enters the interior of the fixed ring 211 in the inclined state of the duct 111, most of the airflow will be subjected to the action of the guide plate 313 to exert force on the recess of the rotating block 312, causing the rotating block 312 to rotate around the fixed shaft 311. The airflow pushing the rotating block 312 will be ejected to both sides along the recess of the rotating block 312.

[0063] An aircraft includes wings 101 fixedly connected to the left and right sides of a main body 1. A connecting frame 102 is fixedly connected to the bottom of the wings 101. When the wings 101 and the rotating component 11 are adjusted to lift, the main body 1 will drive the wings 101 and the connecting frame 102 to climb to a specified height. Then, under the operation of the staff, the wings 101 and the connecting frame 102 will keep the main body 1 stable.

[0064] In use, the operator starts the power unit inside the main body 1. After the unit is started, the landing gear at the bottom of the main body 1 will begin to move. The main body 1 moves to the outside of the takeoff runway via the landing gear. After the operator completes the inspection, the main body 1 accelerates within the takeoff runway via the landing gear. During the acceleration of the main body 1, the rotating shaft 112 inside the duct 111 will start to rotate. When the rotating shaft 112 rotates, it will drive the fan blades 113 on the outer surface to start rotating. At the same time, under the action of the wing 101 and the rotating assembly 11, the main body 1 will drive the wing 101 and the connecting frame 102 to climb to the designated height. Then, under the operation of the operator, the wing 101 and the connecting frame 102 will keep the main body 1 stable, thus facilitating subsequent long-duration flights.

[0065] During the ascent of the main body 1 and the wing 101, the main body 1 is tilted, causing some airflow to detach from the inner wall of the duct 111. As the main body 1 continues to climb, this detached airflow, due to the tilt angle, directly contacts the arc-shaped plate 122 fixed to the inner wall of the duct 111 by the fixing plate 121. Guided by the arc-shaped plate 122, the airflow then enters the interior of the fixing ring 211 through the air intake slot 123. At this time, the fixing ring 211 collects the strong airflow during the flight. Afterwards, under the continuous push of the subsequent airflow, it will be ejected through the connecting groove 213 near the side of the triangular block 215 into the gap between the rotating shaft 112 and the inner wall of the duct 111. During the ejection of the airflow, it will exert a force on the vortex at the inner wall of the rotating shaft 112 and the duct 111, thereby making the vortex into a chaotic state. This reduces the situation where strong tip vortices appear at the gap between the rotating shaft 112 and the duct 111 when the duct 111 is lifted and some airflow separates from the inner wall of the duct 111. This reduces the impact of tip vortices on the rotating shaft 112 and improves the overall quality of the device during operation.

[0066] After the airflow enters the fixed ring 211 through the inlet slot 123, most of the airflow will flow towards the recessed side of the rotating block 312 under the action of the guide plate 313. During the continuous flow of the gas, it will contact the inner wall of the recessed part of the rotating block 312 and thus apply a thrust to the rotating block 312. After being thrust, the rotating block 312 will rotate. When the rotating block 312 rotates, its recessed part will detach from the inner wall of the fixed ring 211 and rotate towards the fan blade 113 side, thus exposing the gap. Then, the airflow will pass through the rotating block 312 and the fixed ring 211. The airflow is ejected through the gap between 11 and the side wall of the blade 113. When the airflow is ejected, it will come into contact with the side wall of the blade 113. Thus, when pressure is generated on one side of the blade 113 during rotation, a force is applied to the other side. By applying two forces to the same blade 113, the blade 113 remains stable during rotation. This reduces the vibration that occurs when the blade tip is subjected to pressure generated during the rotation of the blade 113 during rapid rotation. This keeps the blade 113 stable during operation and improves the efficiency of the device during operation.

[0067] After the main body 1 climbs and enters horizontal flight, the airflow will be parallel to the inner wall of the duct 111. After entering the interior of the duct 111, the airflow will adhere to the inner wall of the duct 111. As the airflow continues to move, it will enter the interior of the connecting groove 213 near the side of the closing plate 222. Then, as the airflow passes through the connecting groove 213, it will exert a thrust on the closing plate 222, causing it to rotate around the fixed block 221. After the closing plate 222 rotates, the airflow will enter the interior of the fixed ring 211. At this time, under the guidance of the guide plate 313, most of the airflow will interact with the rotating block 312. The flat surface makes contact, and then the continuous flow of air will push the flat surface of the rotating block 312 to rotate. After the rotating block 312 rotates, the airflow will be in a horizontal state and contact the side wall of the rotating shaft 112. This allows the airflow of the main body 1 to better fit with the inner wall of the duct 111 when it is in horizontal flight. This reduces the situation where the airflow is dispersed due to the action of the arc plate 122 when the duct 111 changes from an inclined state to a horizontal state, thus reducing the airflow separation effect when the duct 111 is in flight and further improving the overall quality of the device during operation.

[0068] When the airflow enters the fixed ring 211 under the inclined state of the duct 111, most of the airflow will exert a force on the recess of the rotating block 312 under the action of the guide plate 313, causing the rotating block 312 to rotate around the fixed shaft 311. The airflow pushing the rotating block 312 will spray out to both sides along the recess of the rotating block 312. When the airflow is sprayed out to both sides through the recess of the rotating block 312, it will be guided by the inclined surface of the triangular block 215 to flow obliquely towards the side wall of the rotating shaft 112, while exerting a thrust on the side wall of the rotating shaft 112. This makes the force on the rotating shaft 112 more stable when it rotates, and reduces the situation where the rotating shaft 112 shakes due to uneven force caused by distance when the airflow is sprayed out from the recess of the rotating block 312 towards the side wall of the rotating shaft 112.

[0069] The preferred embodiments of the present invention disclosed above are merely illustrative of the invention. These preferred embodiments do not exhaustively describe all details, nor do they limit the invention to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the invention, thereby enabling those skilled in the art to better understand and utilize the invention. The invention is limited only by the claims and their full scope and equivalents.

Claims

1. A ducted power plant for an aircraft comprising a main body (1), characterized in that, Also includes: Connecting mechanism (2) is mounted in the inside of the main body (1), for swing when the main body (1) movement; Rotary mechanism (3) is mounted in the inside of the connecting mechanism (2), for rotation when the connecting mechanism (2) movement; The main body (1) includes: Rotary assembly (11) is mounted in the bottom of the main body (1), for rotation when the main body (1) moves; Guide assembly (12) is mounted in the inside of the rotary assembly (11), for assisting the operation of the rotary assembly (11); The connecting mechanism (2) includes: Auxiliary assembly (21) is mounted in the inside of the rotary assembly (11) through the connecting piece, for guiding gas movement; The connecting piece includes two fixed rings (211) fixedly arranged in the inner wall of the rotary assembly (11), and a placing groove (212) is formed in the inside of the fixed ring (211); Swing assembly (22) is mounted in the inner wall of the placing groove (212), for opening and closing when the gas flows; The rotary mechanism (3) includes: Flow dividing assembly (31) is mounted in the inside of the auxiliary assembly (21), for rotating when the gas flows; The rotary assembly (11) includes a duct (111) fixedly connected to the bottom of the wing (101), a rotating shaft (112) fixedly connected to the inside of the duct (111), and a plurality of fan blades (113) fixedly connected to the outer surface of the rotating shaft (112); The guide assembly (12) includes two fixed plates (121) fixedly connected to the inner wall of the duct (111), an arc-shaped plate (122) fixedly connected to the inner wall of the fixed plate (121), and an air inlet groove (123) formed in the inner wall of the arc-shaped plate (122); The auxiliary assembly (21) includes a plurality of connecting grooves (213) formed in the side wall of the placing groove (212), and a plurality of blocking blocks (214) fixedly connected to the inside of part of the connecting grooves (213); The side wall of the fixed ring (211) is fixedly connected with a plurality of triangular blocks (215); The outer surface of the two fixed rings (211) is fixedly connected with the inner wall of the duct (111), and the inner wall of the fixed ring (211) is fixedly connected with the outer surface of the arc-shaped plate (122); The flow dividing assembly (31) includes a fixed shaft (311) fixedly connected to the inside of the plurality of connecting grooves (213), a rotating block (312) rotatably connected to the outer surface of the fixed shaft (311), and a plurality of drainage plates (313) arranged on the inner wall of the rotating block (312); The side of the drainage plate (313) close to the fixed shaft (311) is fixedly connected with the outer surface of the fixed shaft (311).

2. A ducted fan powerplant for a flying vehicle as claimed in claim 1 wherein: The swing assembly (22) includes two fixed blocks (221) fixedly connected to the inner wall of the placing groove (212), and a closing plate (222) rotatably connected between the two fixed blocks (221).

3. An aircraft employing a ducted fan power plant as claimed in claim 1, characterised in that, The wing (101) is fixedly connected to the left side and the right side of the main body (1), and the bottom of the wing (101) is fixedly connected with a connecting frame (102).

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