Flight lift mechanism and manned aircraft

Abstract

The utility model discloses a flight lift mechanism and a manned craft, the flight lift mechanism comprises a main body, the main body is internally provided with an air passage, the inner diameter of the air passage is gradually reduced from an air inlet to an air outlet, the air outlet of the air passage is provided with an airflow direction blade adjusting group, and the air passage is internally provided with a rotating shaft; a first spiral blade set and a second spiral blade set are arranged on the rotating shaft, the inclination angle of blades of the first spiral blade set relative to the cross section of the rotating shaft is smaller than that of blades of the second spiral blade set relative to the cross section of the rotating shaft, and the inclination directions of the blades of the first spiral blade set and the blades of the second spiral blade set are the same. Compared with a traditional single-layer spiral blade lift force mechanism, the flight lift force lifting mechanism provided by the utility model has the advantages that the airflow speed is increased twice through the first spiral blade group and the second spiral blade group, so that the lift force is improved, and meanwhile, the inner wall of the air passage is arranged in a taper manner, so that the airflow flowing speed at the air outlet of the air passage is increased, and the lift force is further improved.

Description

Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to a flight lift mechanism and a manned aircraft. Background Art

[0002] Manned aircraft usually include rotorcraft, which can take off and land vertically and hover freely, and have a wide range of applications.

[0003] The patent document with announcement number CN207106079U provides a manned aircraft and its system, which includes a fuselage, a chassis, a drive device and multiple rotors; a cockpit is fixedly arranged inside the fuselage; each rotor is covered with a safety cover to prevent or reduce foreign objects from touching the rotor, so as to protect the rotor and prevent or reduce damage to the rotor, so as to improve the safety performance of the aircraft, which has certain positive significance. However, there are also certain shortcomings. For example, the rotors are usually arranged in a single layer and can only be accelerated in a single stage. The lift enhancement can only be achieved by increasing the rotation speed of the rotor, thereby increasing energy consumption and affecting endurance. Utility Model Content

[0004] The purpose of this application is to provide a flight lift mechanism and a manned aircraft to solve the above-mentioned problems.

[0005] To achieve the above purpose, the technical solution of this application is:

[0006] In the first aspect, the present application provides a flight lift mechanism, including a main body, an air duct is provided inside the main body, the inner diameter of the air duct gradually decreases from the air inlet to the air outlet, the air outlet of the air duct is provided with an airflow direction blade adjustment group, a rotating shaft is provided inside the air duct, a first spiral blade group and a second spiral blade group are provided on the rotating shaft, an inclination angle of the blades of the first spiral blade group relative to the cross-section of the rotating shaft is smaller than an inclination angle of the blades of the second spiral blade group relative to the cross-section of the rotating shaft, and the inclination directions of the two are the same, the first spiral blade group is closer to the air inlet than the second spiral blade group, a fixed blade group is provided between the first spiral blade group and the second spiral blade group, and the inclination direction of the blades of the fixed blade group relative to the cross-section of the rotating shaft is opposite to the inclination direction of the blades of the first spiral blade group relative to the cross-section of the rotating shaft.

[0007] Preferably, a double-headed brushless motor is provided inside the air duct, and the rotating shaft is correspondingly connected to the rotor of the double-headed brushless motor; the double-headed brushless motor is located between the first spiral blade group and the second spiral blade group.

[0008] Preferably, the fixed blade group is located on the outer peripheral wall of the double-headed brushless motor.

[0009] Preferably, the number of blades in the first spiral blade group and the number of blades in the second spiral blade group are both seven.

[0010] Preferably, the air inlet of the air duct is provided with a removable protective net.

[0011] Preferably, the airflow direction blade adjustment group includes an adjusting rod and a plurality of rotatably connected rotating blades, and the plurality of rotatably connected rotating blades are arranged at intervals; the plurality of rotating blades are hingedly connected to the adjusting rod, and the adjusting rod is slidably arranged perpendicular to the rotating axis of the rotating blade, and one end of the adjusting rod is connected to a driving assembly to drive the adjusting rod to drive the rotating blade to rotate.

[0012] In the second aspect, the present application also provides a manned aircraft, including the above-mentioned flight lift mechanism, and also includes a main body, and the main body as a whole has a flat triangular layout; the number of the flight lift mechanisms is five, three of which are arranged along the thickness direction of the main body, and the other two are arranged along the front and rear direction of the main body.

[0013] Preferably, a first slope is provided on both sides of the bottom of the main body, and the first slope gradually slopes downward along the direction approaching the middle of the bottom of the main body; a second slope is provided on the front side of the bottom of the main body, and the second slope gradually slopes downward along the direction approaching the middle of the bottom of the main body; a battery pack is provided at the bottom of the main body, and a cockpit is provided on the main body, and the cockpit is located above the battery pack.

[0014] Preferably, a joystick is provided in the cockpit, a conical spring is connected to the bottom of the joystick, a pressure sensor is provided at the bottom of the conical spring, and the number of the pressure sensors is four, and the four pressure sensors are arranged in a square with intervals in front, back, left and right directions.

[0015] A manned aircraft disclosed in the present application, compared with a traditional single-layer spiral blade lift mechanism, the flight lift enhancement mechanism provided by the present application increases the airflow velocity secondary through a first spiral blade group and a second spiral blade group, thereby enhancing lift. At the same time, the inner wall of the airway is set in a tapered shape to increase the airflow velocity at the airway outlet, further enhancing lift, thereby having better power with the same energy consumption. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the overall structure of the subject in this application;

[0017] Figure 2 This is a cross-sectional view of the main body in this application;

[0018] Figure 3 This is a schematic diagram of the structure of the joystick of this application;

[0019] Figure 4 This is a schematic diagram of the main body of the present application from a top view angle;

[0020] Figure 5 This is a schematic diagram of the main body of the present application from an upward angle;

[0021] Figure 6 This is a schematic diagram of the side view of the main body of this application;

[0022] Figure 7 This is a schematic diagram of the rear view angle of the main body of this application.

[0023] In the figure:

[0024] 1. Main body; 10. Protective net; 11. Air inlet; 12. Air outlet; 13. Air flow direction blade adjustment group; 130. Adjustment rod; 14. First spiral blade group; 140. Rotating shaft; 141. Fixed frame; 15. Second spiral blade group; 16. Double-headed brushless motor; 17. Fixed blade group; 2. Joystick; 20. Conical spring; 21. Pressure sensor; 3. Main body; 30. First position; 31. Second position; 32. Third position. DETAILED DESCRIPTION

[0025] The present application will now be described in further detail in conjunction with the accompanying drawings. The accompanying drawings are simplified schematic diagrams, which only illustrate the basic structure of the present application in a schematic manner, and therefore only show the components related to the present application.

[0026] like Figure 1-3 As shown, in the first aspect, the present application provides a flight lift mechanism, including a main body 1, an air duct is provided inside the main body 1, the inner diameter of the air duct gradually decreases from the air inlet 11 to the air outlet 12, the air outlet 12 of the air duct is provided with an airflow direction blade adjustment group 13, a rotating shaft 140 is provided inside the air duct, a first spiral blade group 14 and a second spiral blade group 15 are provided on the rotating shaft 140, an inclination angle of the blades of the first spiral blade group 14 relative to the cross-section of the rotating shaft 140 is smaller than an inclination angle of the blades of the second spiral blade group 15 relative to the cross-section of the rotating shaft 140, and the inclination directions of the two are the same, the first spiral blade group 14 is closer to the air inlet 11 than the second spiral blade group 15, a fixed blade group 17 is provided between the first spiral blade group 14 and the second spiral blade group 15, and the inclination direction of the blades of the fixed blade group 17 relative to the cross-section of the rotating shaft 140 is opposite to the inclination direction of the blades of the first spiral blade group 14 relative to the cross-section of the rotating shaft 140.

[0027] The outer contour of the main body 1 is a columnar structure. The airway is located inside the main body 1. The airway is a columnar structure, specifically a cone, that is, the inner diameter of the airway gradually decreases from the air inlet 11 to the air outlet 12.

[0028] The rotating shaft 140 inside the airway can rotate, and when rotating, it will drive the first spiral blade group 14 and the second spiral blade group 15 arranged thereon to rotate synchronously.

[0029] Since the interior of the entire airway is conical and the diameter of the air outlet 12 is small, during operation, the airflow enters from the air inlet 11 of the airway, flows through the interior of the airway, and then flows out from the air outlet 12 of the airway. Due to the variable diameter setting inside the airway, the airflow is faster when it is closer to the air outlet 12 of the airway. At the same time, since the inclination angle of the blades of the first spiral blade group 14 relative to the cross-section of the rotating shaft 140 is smaller than the inclination angle of the blades of the second spiral blade group 15 relative to the cross-section of the rotating shaft 140 and the inclination directions of the two are the same, the second spiral blade with a larger inclination angle further drives the airflow to circulate rapidly, thereby further increasing the airflow flowing out of the airway outlet 12 to enhance the lift of the entire lifting mechanism.

[0030] Compared with the traditional single-layer spiral blade lift mechanism, the flight lift enhancement mechanism provided by the present application increases the airflow velocity secondarily through the first spiral blade group 14 and the second spiral blade group 15, thereby enhancing the lift. At the same time, the inner wall of the airway is set in a tapered shape to increase the airflow velocity at the airway outlet 12, further enhancing the lift, thereby having better power with the same energy consumption.

[0031] In some further embodiments, a double-headed brushless motor 16 is provided inside the air duct, and the rotating shaft 140 is correspondingly connected to the rotor of the double-headed brushless motor 16 ; the double-headed brushless motor 16 is located between the first spiral blade group 14 and the second spiral blade group 15 .

[0032] The rotation of the first spiral blade group 14 and the second spiral blade group 15 is realized by a double-headed brushless motor 16, and the double-headed brushless motor 16 is specifically arranged between the first spiral blade group 14 and the second spiral blade group 15; illustratively, the number of the rotating shafts 140 can be two corresponding to the two spiral blade groups.

[0033] In some further embodiments, the fixed blade assembly 17 is located on the outer peripheral wall of the double-headed brushless motor 16 .

[0034] The fixed blade group 17 is arranged on the outer peripheral wall of the double-headed brushless motor 16, and the inclination direction of the cross-section of the blades of the fixed blade group 17 relative to the rotating shaft 140 is opposite to the inclination direction of the cross-section of the blades of the first spiral blade group 14 relative to the rotating shaft 140, so as to avoid the airflow flowing through the first spiral blade group 14 having the same rotation tendency as the second spiral blade group 15, thereby weakening the lift brought by the second spiral blade group 15. Therefore, under the action of the fixed spiral blade group, the airflow passing through the first spiral blade group 14 is corrected to a certain extent or restored to the state before entering the air inlet 11, so as to ensure that the second spiral blade group 15 can effectively drive the airflow to generate lift, and avoid the second spiral blade group 15 obtaining the "wind-breaking" effect similar to the first spiral blade group 14 and reducing the lifting effect of the second spiral blade group 15.

[0035] In some further embodiments, the number of blades of the first spiral blade set 14 and the second spiral blade set 15 are both seven.

[0036] In some other embodiments, the number of blades of the first spiral blade set 14 and the second spiral blade set 15 may also be five.

[0037] In some further embodiments, a mounting frame is provided inside the air duct, a double-headed brushless motor 16 is arranged on the mounting frame, a mounting arm is provided on the outer peripheral wall of the mounting frame, one end of the mounting arm is connected to the mounting frame, and the other end is connected to the inner wall of the air duct; a fixing frame 141 is provided inside the air duct, a bearing for supporting the rotation of the rotating shaft 140 is provided on the fixing frame 141, and the fixing frame 141 is connected to the inner wall of the air duct.

[0038] The mounting frame is mainly used to fix the double-headed brushless motor 16 . Exemplarily, the mounting frame is fixed to the outer peripheral wall of the double-headed brushless motor 16 , thereby fixing the double-headed brushless motor 16 .

[0039] Exemplarily, there are two fixing frames 141 , and the two fixing frames 141 are respectively close to the air inlet 11 and the air outlet 12 of the airway to ensure coaxial rotation.

[0040] In some other embodiments, a corresponding brake disc can be provided on the rotating shaft 140. When an unexpected power failure of the aircraft occurs, the first spiral blade group 14 and the second spiral blade group 15 will reverse during the landing of the aircraft. When the aircraft approaches the ground, the brake disc can be clamped by a caliper to instantly stop the rotation of the first spiral blade group 14 and the second spiral blade group 15, thereby reducing the landing speed of the aircraft to a certain extent.

[0041] In some further embodiments, the air inlet 11 of the air duct is provided with a detachable protective net 10 .

[0042] The protection net 10 is used to prevent debris from entering the interior of the airway and affecting the rotation of the first spiral blade group 14 and the second spiral blade group 15 .

[0043] In some further embodiments, the airflow direction blade adjustment group 13 includes an adjusting rod 130 and a plurality of rotatably connected rotating blades, and the plurality of rotatably connected rotating blades are arranged at intervals; the plurality of rotating blades are hingedly connected to the adjusting rod 130, and the adjusting rod 130 is slidably arranged vertically to the rotating axis of the rotating blade, and one end of the adjusting rod 130 is connected to a driving assembly to drive the adjusting rod 130 to drive the rotating blade to rotate.

[0044] Exemplarily, the airflow direction adjusting blade is similar to a shutter structure, wherein the rotating blade can swing under the adjustment of the adjusting rod 130. Specifically, one side wall of the rotating blade is hinged to the outer peripheral wall of the adjusting rod 130. When the adjusting rod 130 slides along its axial direction, it will synchronously drive the rotating blade to rotate, thereby changing the outlet direction of the airflow in the airway.

[0045] The driving component that drives the adjusting rod 130 to move may be a hydraulic rod.

[0046] like Figure 4-7 As shown, in the second aspect, the present application also provides a manned aircraft, including the above-mentioned flight lift mechanism, and also includes a main body 3, and the main body as a whole is in a flat triangular layout; the number of flight lift mechanisms is five, three of which are arranged along the thickness direction of the main body 3, and the other two are arranged along the front and rear direction of the main body 3, that is, the horizontal direction.

[0047] The main body 3 is a triangular flat structure, and the thickness direction of the main body 3 is the up-and-down direction of the main body 3 when flying horizontally.

[0048] Among the three flight lift mechanisms arranged along the thickness direction of the main body 3, two of them are relatively located at the rear of the main body 3 and are arranged at intervals on the left and right, and the remaining one is relatively located at the front of the main body 3 and is located on the perpendicular bisector of the line connecting the two rear flight lift mechanisms. By way of example, the specifications, dimensions and power of the flight lift mechanism located at the front are greater than those of the two rear flight lift mechanisms.

[0049] The two flight lift mechanisms arranged along the front-rear direction are mainly used to provide power for forward flight, and the three flight lift mechanisms arranged along the thickness direction of the body 3 are mainly used to provide lift.

[0050] The three flight lift mechanisms along the thickness direction are respectively arranged at a first position 30 and a second position 31 , and the two flight lift mechanisms arranged along the front-rear direction of the body 3 are arranged at a third position 32 .

[0051] In some other embodiments, the rotation axis of a rotating blade in a flight lift mechanism located relatively to the left rear is perpendicular to a line connecting the left rear of the aircraft and the center of the aircraft, the rotation axis of a rotating blade in a flight lift mechanism located relatively to the right rear is perpendicular to a line connecting the right rear of the aircraft and the center of the aircraft, and the length direction of the rotation axis of a rotating blade in a flight lift mechanism located relatively to the front is consistent with the front-to-back direction; the length directions of the rotation axes in the two flight lift mechanisms arranged along the front-to-back direction are consistent with the up-and-down direction, so as to meet the direction adjustment of the entire aircraft during flight while taking into account the flight stability performance of the aircraft.

[0052] In some other embodiments, the inner contour of the airway of the two flight lift mechanisms along the front-to-back direction gradually changes, that is, the closer to the air outlet 12 of the airway, the inner diameter contour of the airway gradually changes into a vertical flat rectangular structure, thereby increasing the compression of the airflow. At the same time, the air outlet 12 with the flat rectangular structure can also better control the left and right direction of the aircraft.

[0053] In some further embodiments, a first slope is provided on both sides of the bottom of the main body 3, and the first slope gradually slopes downward along the direction approaching the middle of the bottom of the main body 3; a second slope is provided on the front side of the bottom of the main body 3, and the second slope gradually slopes downward along the direction approaching the middle of the bottom of the main body 3; a battery pack is provided at the bottom of the main body 3, and a cockpit is provided on the main body 3, and the cockpit is located above the battery pack.

[0054] The middle of the bottom of the entire body 3 is lower than the surroundings, so that the bottom of the entire body 3 presents a bowl-shaped outer wall structure, thereby ensuring stability during flight, and preventing serious overturning even when the aircraft has an unexpected power failure.

[0055] In some further embodiments, a joystick 2 is provided in the cockpit, a conical spring 20 is connected to the bottom of the joystick 2, a pressure sensor 21 is provided at the bottom of the conical spring 20, and the number of the pressure sensors 21 is four, and the four pressure sensors 21 are arranged in a square with intervals in the front, back, left and right directions.

[0056] When the joystick 2 is tilted in different directions, the pressure of the conical spring 20 at the bottom of the joystick 2 toward the tilted side increases, thereby triggering the corresponding pressure sensor 21, which further triggers the rotation speed of the first spiral blade group 14 and the second spiral blade group 15 in different flight lift mechanisms or the direction of the rotating blades therein, so as to achieve directional adjustment of the entire aircraft.

[0057] Two pressure sensors 21 are also provided on the top of the joystick 2 for controlling the adjustment of the rotating blades at the tail of the flight lift mechanism in the horizontal direction.

[0058] It should be noted that the double-headed brushless motor 16, the motion control of the rotating blades and the triggering principle of the pressure sensor 21 in the present application are relatively common in the industry and are prior art, and will not be repeated in this embodiment.

[0059] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection created by this application.

Claims

1. A flying lift mechanism, characterized in that: The invention comprises a main body (1), wherein an air passage is provided inside the main body (1), wherein the inner diameter of the air passage gradually decreases from an air inlet (11) to an air outlet (12), wherein the air outlet (12) of the air passage is provided with an airflow direction blade adjustment group (13), wherein a rotating shaft (140) is provided inside the air passage, wherein a first spiral blade group (14) and a second spiral blade group (15) are provided on the rotating shaft (140), wherein the inclination angle of the blades of the first spiral blade group (14) relative to the cross section of the rotating shaft (140) is smaller than that of the blades of the second spiral blade group (15). The first spiral blade group (14) is closer to the air inlet (11) than the second spiral blade group (15) at an inclination angle relative to the cross section of the rotating shaft (140) and the inclination directions of the two are the same; a fixed blade group (17) is provided between the first spiral blade group (14) and the second spiral blade group (15); the inclination direction of the blades of the fixed blade group (17) relative to the cross section of the rotating shaft (140) is opposite to the inclination direction of the blades of the first spiral blade group (14) relative to the cross section of the rotating shaft (140).

2. The flying lift mechanism according to claim 1, characterized in that: A double-headed brushless motor (16) is provided inside the air passage, and the rotating shaft (140) is correspondingly connected to the rotor of the double-headed brushless motor (16); the double-headed brushless motor (16) is located between the first spiral blade group (14) and the second spiral blade group (15).

3. The flying lift mechanism according to claim 2, characterized in that: The fixed blade group (17) is located on the outer peripheral wall of the double-headed brushless motor (16).

4. The flying lift mechanism according to claim 3, characterized in that: The number of blades in the first spiral blade group (14) and the second spiral blade group (15) are both seven.

5. The flying lift mechanism according to claim 4, characterized in that: The air inlet (11) of the air passage is provided with a detachable protective net (10).

6. The flying lift mechanism according to claim 5, characterized in that: The airflow direction blade adjustment group (13) comprises an adjustment rod (130) and a plurality of rotatably connected rotating blades, wherein the plurality of rotatably connected rotating blades are arranged at intervals; the plurality of rotating blades are hingedly connected to the adjustment rod (130), the adjustment rod (130) is slidably arranged perpendicular to the rotating axis of the rotating blade, and one end of the adjustment rod (130) is connected to a driving assembly to drive the adjustment rod (130) to drive the rotating blade to rotate.

7. A manned aircraft, characterized in that: It comprises the flight lift mechanism as claimed in any one of claims 1 to 6, and also comprises a body (3), wherein the body (3) is in a flat triangular layout as a whole; the number of the flight lift mechanisms is five, three of which are arranged along the thickness direction of the body (3), and the other two are arranged along the front-rear direction of the body (3).

8. The manned aircraft according to claim 7, characterized in that: A first inclined surface is provided on both sides of the bottom of the body (3), and the first inclined surface gradually slopes downward in a direction close to the middle of the bottom of the body (3); a second inclined surface is provided on the front side of the bottom of the body (3), and the second inclined surface gradually slopes downward in a direction close to the middle of the bottom of the body (3); a battery pack is provided at the bottom of the body (3), and a cockpit is provided on the body (3), and the cockpit is located above the battery pack.

9. The manned aircraft according to claim 8, characterized in that: A joystick (2) is provided in the cockpit, a conical spring (20) is connected to the bottom of the joystick (2), a pressure sensor (21) is provided at the bottom of the conical spring (20), the number of the pressure sensors (21) is four, and the four pressure sensors (21) are arranged in a square at intervals in the front, back, left and right directions.

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