Flap assembly manufacturing method, flap assembly and vertical take-off and landing aircraft

Abstract

The invention relates to the technical field of aviation aircrafts, and provides a manufacturing method of a flap assembly, the flap assembly and a vertical take-off and landing aircraft, the method comprises the following steps: rotationally connecting a wing box section with a flap section, and arranging a ducted fan propulsion mechanism on the flap section; a driving mechanism with a harmonic reducer is in driving connection with the flap section, so that the driving mechanism drives the flap section to rotate through the harmonic reducer; a locking mechanism with a pneumatic spring is connected with the flap section, so that the locking mechanism locks the flap section through the pneumatic spring. According to the manufacturing method of the flap assembly, the harmonic reducer is used for driving the flap section to rotate, so that the torque of the driving mechanism is amplified, and the flap section is driven to rotate more easily; and the pneumatic spring is connected with the flap section to lock the flap section, so that the flap section is better prevented from rotating, the rotation angle between the flap section and the wing box section is ensured to be unchanged, the influence on the flight state of the vertical take-off and landing aircraft is avoided, and the safety is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation aircraft, and in particular to a method for manufacturing a flap assembly, a flap assembly and a vertical take-off and landing aircraft. Background Art

[0002] Low-altitude vertical take-off and landing aircraft, also known as eVTOL (Electric Vertical Takeoff and Landing), generally refers to aircraft used for carrying people or large-load logistics.

[0003] eVTOL does not rely on runways and can take off and land vertically. It can carry out aerial manned and cargo operations within limited space within cities and between cities. Its application scenarios mainly include low-altitude tourism, daily commuting, aerial logistics, fire rescue, medical assistance and other medium- and short-distance (20-300km) and low-altitude (<300m) applications.

[0004] Low-altitude vertical take-off and landing aircraft usually have a novel and technically difficult distributed vector propulsion mechanism, which usually includes a ducted fan propulsion mechanism, a wing box section and a flap section.

[0005] Among them, ducted fan propulsion mechanisms are increasingly being used in electric vertical take-off and landing aircraft due to their advantages such as high cruising efficiency and low ducted noise. Ducted fans are integrated into the aircraft's control surfaces, such as flaps, as a power system, to achieve compact structure, beautiful appearance, and high safety redundancy.

[0006] The complete transition of the aircraft of this configuration from the hovering mode to the cruising mode requires the ducted fan propulsion mechanism and the flap section to be integrated with the wing box section to achieve rotation. Of course, the ducted fan propulsion mechanism can be arranged on the flap section, and the flap section and the wing box section can be rotatably connected.

[0007] The wing box section is the main structure that generates lift when the vertical take-off and landing aircraft is cruising; the flap section is located behind the wing section and can control the lift of the vertical take-off and landing aircraft when cruising; the ducted fan propulsion mechanism is the power system of the aircraft and can be integrated in the upper part of the flap section.

[0008] When the flap section rotates relative to the wing box section, the ducted fan propulsion mechanism also rotates, thereby changing the direction of the power vector of the aircraft, allowing the aircraft to complete the transition from hovering mode to cruise mode, and complete pitch and other actions during cruise.

[0009] However, in the related flap assembly technology, the torque driving the flap section and the wing box section to rotate is relatively small, and it is difficult to drive the flap section and the wing box section to rotate and adjust between any angles from 0° to 90°. Moreover, after the flap section and the wing box section rotate, it is difficult to keep the rotation angle between the two unchanged, which can easily affect the flight state of the vertical take-off and landing aircraft and is dangerous. Summary of the invention

[0010] In view of the above-mentioned defects of the prior art, the present invention provides a method for manufacturing a flap assembly to solve at least one of the above-mentioned technical defects in the prior art, so that the torque driving the flap section and the wing box section to rotate is larger, and it is easier to drive the flap section and the wing box section to rotate and adjust at any angle between 0° and 90°; and after the flap section and the wing box section are rotated, the rotation angle between the two can also be better kept unchanged, thereby avoiding affecting the flight state of the vertical take-off and landing aircraft and improving the safety of flight.

[0011] A second aspect of the present invention provides a flap assembly.

[0012] The third aspect of the present invention also provides a vertical take-off and landing aircraft.

[0013] In order to achieve the purpose of the present invention, the present invention provides a method for manufacturing a flap assembly, comprising the following steps:

[0014] The wing box section is rotatably connected to the flap section, and the ducted fan propulsion mechanism is arranged on the flap section;

[0015] Drivingly connecting a driving mechanism having a harmonic reducer to the flap segment, so that the driving mechanism drives the flap segment to rotate through the harmonic reducer;

[0016] A locking mechanism having a pneumatic spring is connected to the flap segment, so that the locking mechanism locks the flap segment through the pneumatic spring.

[0017] Preferably, the method further comprises the following steps:

[0018] The tilt shaft is arranged on the flap section, the wing box section is rotationally hinged with the flap section, and the harmonic reducer is drivingly connected with the tilt shaft;

[0019] The pneumatic spring is connected to the tilt axis.

[0020] A second aspect of the present invention further provides a flap assembly, which is applied to the flap assembly according to the manufacturing method of the flap assembly, and the flap assembly comprises:

[0021] Wing box section,

[0022] a flap section, rotatably connected to the wing box section;

[0023] A ducted fan propulsion mechanism is provided on the flap section;

[0024] A driving mechanism, comprising a driving motor and a harmonic reducer provided in the wing box section, wherein the harmonic reducer is drivingly connected to the flap section, and the driving motor drives the flap section to rotate through the harmonic reducer;

[0025] The locking mechanism comprises a pneumatic spring, wherein the pneumatic spring is connected to the flap segment.

[0026] Preferably, the driving mechanism further comprises a tilting shaft and a driving connecting rod.

[0027] The tilt shaft is arranged on the flap section, the wing box section is provided with a supporting ear piece, and the tilt shaft is rotatably hinged with the supporting ear piece.

[0028] The harmonic reducer is drivingly connected to the first end of the driving connecting rod, and the second end of the driving connecting rod is drivingly connected to the tilting shaft.

[0029] Preferably, the driving mechanism further comprises a driving swing arm and a driving rocker arm.

[0030] The driving swing arm is arranged at the output end of the harmonic reducer, and the driving swing arm is hinged to the first end of the driving connecting rod.

[0031] The driving rocker arm is arranged on the tilting shaft, and the second end of the driving connecting rod is hinged to the driving rocker arm.

[0032] Preferably, the locking mechanism further comprises a pneumatic spring controller and a locking rocker arm.

[0033] The pneumatic spring controller controls the locking state of the pneumatic spring,

[0034] The locking rocker arm is arranged on the tilting shaft, and the pneumatic spring is hinged to the locking rocker arm.

[0035] Preferably, the wing box section comprises a wing leading edge rib, a wing front beam, a wing rear beam, a first wing reinforcement rib, a second wing reinforcement rib and a third wing reinforcement rib.

[0036] The first wing reinforcement rib, the second wing reinforcement rib and the third wing reinforcement rib are arranged at intervals along a first direction to form a wing skeleton.

[0037] The wing front beam is arranged at the first end of the wing frame along the second direction, and the wing rear beam is arranged at the second end of the wing frame along the second direction.

[0038] The wing leading edge rib is fixed to the wing front beam, and the supporting ear piece is arranged on the wing rear beam.

[0039] Preferably, the flap section includes a first flap rib, a second flap rib, a third flap rib, a first transverse box and a second transverse box.

[0040] The first flap rib, the second flap rib and the third flap rib are arranged at intervals along a first direction to form a flap skeleton, the first transverse box is arranged between the first flap rib and the second flap rib, and the second transverse box is arranged between the second flap rib and the third flap rib.

[0041] The tilt axis is arranged at the first end of the flap frame along the second direction.

[0042] Preferably, the ducted fan propulsion mechanism comprises a ducted casing and a fan, the ducted casing comprises a first ducted casing and a second ducted casing, the fan comprises a first fan and a second fan,

[0043] The first fan is rotatably connected to the first duct housing, and the second fan is rotatably connected to the second duct housing.

[0044] The first duct housing is disposed on the first transverse box, and the second duct housing is disposed on the second transverse box.

[0045] A direction of a power vector generated by the first fan and the second fan is parallel to the second direction.

[0046] A third aspect of the present invention further provides a vertical take-off and landing aircraft, the vertical take-off and landing aircraft comprising the above-mentioned flap assembly and a vertical take-off and landing aircraft body,

[0047] The flap assembly is arranged on the vertical take-off and landing aircraft body.

[0048] The beneficial effects of the present invention are as follows: the manufacturing method of the flap assembly provided by the present invention connects the driving mechanism with a harmonic reducer to the flap section so that the driving mechanism can drive the flap section to rotate through the harmonic reducer, thereby amplifying the torque of the driving mechanism and making it easier to drive the flap section and the wing box section to rotate and adjust at any angle between 0° and 90°; and further connects a locking mechanism with a pneumatic spring to the flap section so that the locking mechanism can lock the flap section through the pneumatic spring, thereby better preventing the flap section from rotating, thereby ensuring that the rotation angle between the flap section and the wing box section remains unchanged, avoiding affecting the flight state of the vertical take-off and landing aircraft, and improving safety.

[0049] The flap assembly provided by the present invention, because it is manufactured according to the manufacturing method of the flap assembly described above, must have all the advantages of the method. That is, the flap assembly can also more easily drive the flap section and the wing box section to rotate and adjust at any angle between 0° and 90°; and also enable the locking mechanism to lock the flap section through the pneumatic spring, better preventing the flap section from rotating, thereby ensuring that the rotation angle between the flap section and the wing box section remains unchanged, avoiding affecting the flight state of the vertical take-off and landing aircraft, and improving safety.

[0050] The vertical take-off and landing aircraft provided by the present invention, since it includes the above-mentioned flap assembly, must have all the advantages of the flap assembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] The above and other purposes, features and advantages of the present invention will become more apparent through a more specific description of the preferred embodiments of the present invention shown in the accompanying drawings. The same reference numerals indicate the same parts in all the accompanying drawings, and the drawings are not deliberately scaled to the actual size, but the focus is on illustrating the subject matter of the present application.

[0052] Figure 1 A block diagram of a method for manufacturing a flap assembly provided by an embodiment of the present invention;

[0053] Figure 2 A schematic structural diagram of a flap assembly provided in an embodiment of the present invention;

[0054] Figure 3 for Figure 2 A partial schematic diagram of

[0055] Figure 4 A schematic structural diagram of a wing box section in a flap assembly provided in an embodiment of the present invention;

[0056] Figure 5 A schematic structural diagram of a flap section in a flap assembly provided in an embodiment of the present invention;

[0057] Figure 6 A schematic structural diagram of a ducted fan propulsion mechanism in a flap assembly provided in an embodiment of the present invention;

[0058] Figure 7 for Figure 6 Schematic diagram from another perspective;

[0059] Figure 8 A schematic diagram of the structure of the connection between the wing box section and the flap section in the flap assembly provided in an embodiment of the present invention;

[0060] Fig. 9 A schematic diagram of the overall structure of a vertical take-off and landing aircraft provided in an embodiment of the present invention.

[0061] In the figure:

[0062] 100, wing box section; 110, support ear; 120, wing leading edge rib; 130, wing front beam; 140, wing rear beam; 150, first wing reinforcement rib; 160, second wing reinforcement rib; 170, third wing reinforcement rib; 180, lightening hole; 190, strip-shaped small hole;

[0063] 200, flap section; 210, first flap rib; 220, second flap rib; 230, third flap rib; 240, first transverse box; 250, second transverse box;

[0064] 300, ducted fan propulsion mechanism; 310, duct housing; 311, first duct housing; 312, second duct housing; 320, fan; 321, first fan; 322, second fan; 330, stator blade support; 340, propeller disk;

[0065] 400, driving mechanism; 410, driving motor; 420, harmonic reducer; 430, tilting axis; 440, driving connecting rod; 450, driving swing arm; 460, driving rocker arm;

[0066] 500, locking mechanism; 510, pneumatic spring; 511, pneumatic spring mounting bracket; 520, pneumatic spring controller; 530, locking rocker arm;

[0067] 600. Vertical take-off and landing aircraft body. DETAILED DESCRIPTION

[0068] To facilitate understanding of the present invention, the present invention will be described more fully below with reference to the relevant drawings.

[0069] It should be noted that when an element is considered to be "connected" to another element, it may be directly connected to another element and integrated therewith, or there may be an intermediate element at the same time. The terms "installed", "one end", "the other end" and similar expressions used herein are for illustrative purposes only.

[0070] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art to which they pertain. The terms used in the specification herein are intended only for the purpose of describing specific embodiments and are not intended to limit the present invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0071] Combine the following Figures 1 to 9 It should be understood that the following description is only an illustrative embodiment of the present invention and does not constitute any limitation to the present invention.

[0072] In order to more clearly illustrate the directions of the components of the flap assembly provided in the embodiment of the present invention, Figures 4 to 5 , establish an XYZ three-dimensional coordinate system, with the X axis set as the first direction, the Y axis set as the second direction, and the Z axis set as the third direction.

[0073] Combination Figures 1 to 8 An embodiment of the present invention provides a method for manufacturing a flap assembly, the method comprising the following steps:

[0074] Step 1: Rotate and connect the wing box section 100 and the flap section 200, and set the ducted fan propulsion mechanism 300 on the flap section 200; the ducted fan propulsion mechanism 300 can rotate relative to the wing box section 100 through the flap section 200 (for example, an angle between 0° and 90°) to form propulsion power at different angles, thereby realizing the transition of the vertical take-off and landing aircraft between the hovering mode and the cruising mode, as well as the pitch action during cruising.

[0075] Step 2: Drive and connect the driving mechanism 400 having the harmonic reducer 420 to the flap section 200, so that the driving mechanism 400 can drive the flap section 200 to rotate through the harmonic reducer 420; the harmonic reducer 420 can amplify the torque of the driving mechanism 400, so that the driving mechanism 400 can more easily drive the flap section 200 to rotate.

[0076] Step three: Connect the locking mechanism 500 having the pneumatic spring 510 to the flap section 200, so that the locking mechanism 500 can lock the flap section 200 through the pneumatic spring 510; when the specific rotation angle between the flap section 200 and the wing box section 100 is adjusted to be determined (for example: 90°), the pneumatic spring 510 can immediately lock the flap section 200 to prevent the flap section 200 from rotating, thereby ensuring that the rotation angle between the flap section 200 and the wing box section 100 remains unchanged, that is, the direction of the power vector formed by the ducted fan propulsion mechanism 300 can be maintained unchanged, thereby avoiding affecting the flight state of the vertical take-off and landing aircraft and improving safety.

[0077] Furthermore, in step one, the tilt axis 430 is also arranged on the flap segment 200 so that the wing box segment 100 and the flap segment 200 are rotationally hinged.

[0078] Moreover, in step 2, the harmonic reducer 420 is also driven and connected to the tilt shaft 430, and the flap section 200 is rotated by driving the tilt shaft 430 to rotate, thereby simplifying the structure of the flap assembly.

[0079] In step three, the pneumatic spring 510 is connected to the tilt shaft 430 , and the flap section 200 is prevented from rotating by locking the tilt shaft 430 , which has a better locking effect.

[0080] It can be understood that the manufacturing method of the flap assembly provided by the embodiment of the present invention drives and connects the driving mechanism 400 having the harmonic reducer 420 with the flap segment 200, so that the driving mechanism 400 can drive the flap segment 200 to rotate through the harmonic reducer 420, thereby amplifying the torque of the driving mechanism 400, and more easily driving the flap segment 200 and the wing box segment 100 to rotate and adjust at any angle between 0° and 90°; and also connects the locking mechanism 500 having the pneumatic spring 510 with the flap segment 200, so that the locking mechanism 500 can lock the flap segment 200 through the pneumatic spring 510, and better prevent the flap segment 200 from rotating, thereby ensuring that the rotation angle between the flap segment 200 and the wing box segment 100 remains unchanged, avoiding affecting the flight state of the vertical take-off and landing aircraft, and improving safety.

[0081] Combination Figures 1 to 8 According to the above-mentioned method for manufacturing a flap assembly, an embodiment of the present invention further provides a flap assembly, which includes a wing box section 100, a flap section 200, a ducted fan propulsion mechanism 300, a driving mechanism 400 and a locking mechanism 500.

[0082] The flap section 200 is rotationally connected to the wing box section 100, and the ducted fan propulsion mechanism 300 is arranged on the flap section 200 to realize the rotation adjustment of the ducted fan propulsion mechanism 300 relative to the flap section 200 at any angle between 0° and 90°, thereby adjusting the cruise mode of the vertical take-off and landing aircraft. For example: after the ducted fan propulsion mechanism 300 is arranged on the flap section 200 to form a flap ducted fusion structure, the ducted fan propulsion mechanism 300 can stop at any angle of 0° to 90°, where 0° corresponds to the cruise mode of the distributed vector propulsion vertical take-off and landing aircraft, 90° corresponds to the hovering mode, and the intermediate angle is a transition state.

[0083] The driving mechanism 400 includes a driving motor 410 and a harmonic reducer 420, both of which are arranged on the wing box section 100. The harmonic reducer 420 is connected to the flap section 200 by driving, and the driving motor 410 can drive the flap section 200 to rotate through the harmonic reducer 420. The harmonic reducer 420 has a small structure size, high precision and high bearing capacity, and can amplify the torque of the driving mechanism 400, so that the driving mechanism 400 can more easily drive the flap section 200 to rotate and adjust at any angle between 0° and 90°. Among them, the driving motor 410 can be a driving steering gear, and the driving steering gear can be connected to the harmonic reducer 420 by driving through a keyway.

[0084] The locking mechanism 500 includes a pneumatic spring 510, which is connected to the flap section 200. The pneumatic spring 510 can lock the flap section 200 at any position to prevent the flap section 200 from rotating, thereby ensuring that the rotation angle between the flap section 200 and the wing box section 100 remains unchanged, that is, the power vector direction formed by the ducted fan propulsion mechanism 300 remains unchanged, avoiding affecting the flight state of the vertical take-off and landing aircraft, and improving safety.

[0085] In addition, the flap assembly is arranged on a vertical take-off and landing aircraft. When the aircraft is flying, after the flap assembly receives the control instruction from the flight control module, the flap section 200 is driven to rotate (i.e., the ducted fan propulsion mechanism 300 rotates) to a specific angle through the harmonic reducer 420, and the locking mechanism 500 locks the flap section 200 rotation (the ducted fan propulsion mechanism 300 stops rotating) through the pneumatic spring 510. Thus, the resultant force and the resultant torque formed by the aerodynamic lift generated by the vertical take-off and landing aircraft and the thrust generated by the ducted fan propulsion mechanism 300 are borne by the pneumatic spring 510, which greatly protects the aircraft and the harmonic reducer 420.

[0086] It is understandable that the flap assembly provided by the embodiment of the present invention, because it is manufactured according to the manufacturing method of the flap assembly described above, must have all the advantages of the method. That is, the flap assembly can also more easily drive the flap section 200 and the wing box section 100 to rotate and adjust at any angle between 0° and 90°; and also enable the locking mechanism 500 to lock the flap section 200 through the pneumatic spring 510, so as to better prevent the flap section 200 from rotating, thereby ensuring that the rotation angle between the flap section 200 and the wing box section 100 remains unchanged, avoiding affecting the flight state of the vertical take-off and landing aircraft, and improving safety.

[0087] Specifically, combined Figures 2 to 8 In order to make it easier to drive the flap segment 200 to rotate, in some embodiments of the present invention, the driving mechanism 400 also includes a tilt axis 430 and a driving link 440.

[0088] The tilt shaft 430 is provided at the flap section 200, and the wing box section 100 is provided with a support ear piece 110, and the tilt shaft 430 is rotatably hinged with the support ear piece 110. The tilt shaft 430 can be fixedly connected to the flap section 200 through a joint, and when the tilt shaft 430 rotates, the entire flap section 200 also rotates based on the axis of the tilt shaft 430, thereby driving the ducted fan propulsion mechanism 300 to rotate, and the rotation angle is within the range of 0° to 90°.

[0089] The harmonic reducer 420 is drivingly connected to the first end of the driving link 440, and the second end of the driving link 440 is drivingly connected to the tilt shaft 430. The driving link 440 greatly improves the bearing capacity of the driving mechanism 400, thereby effectively driving the flap section 200 to rotate.

[0090] The driving connecting rod 440 may be a buffer connecting rod, which can reduce the vibration and impact on the driving motor 410 (ie, the driving servo) and the harmonic reducer 420, thereby improving the stability and safety of the flap assembly.

[0091] Furthermore, combined with Figures 2 to 8 In order to simplify the structure of the flap assembly and save manufacturing costs, in some embodiments of the present invention, the driving mechanism 400 also includes a driving swing arm 450 and a driving rocker arm 460.

[0092] Among them, the driving motor 410 has a driving output shaft, the harmonic reducer 420 has an input shaft and an output shaft, the input shaft of the harmonic reducer 420 is connected to the driving output shaft of the driving motor 410, the driving swing arm 450 is arranged on the output end (i.e., the output shaft) of the harmonic reducer 420, and the driving swing arm 450 is hinged to the first end of the driving connecting rod 440.

[0093] The driving rocker arm 460 is disposed on the tilting shaft 430 , and the second end of the driving link 440 is hinged to the driving rocker arm 460 .

[0094] When the driving motor 410 rotates to output driving force, the output shaft of the harmonic reducer 420 drives the driving swing arm 450 to rotate, and the driving swing arm 450 drives the driving connecting rod 440 to swing, so that the driving swing arm 460 also swings, thereby driving the tilting shaft 430 to rotate.

[0095] Combination Figures 2 to 8 In order to ensure that the pneumatic spring 510 can lock the tilt axis 430 in time, in some embodiments of the present invention, the locking mechanism 500 also includes a pneumatic spring controller 520 and a locking rocker arm 530.

[0096] The pneumatic spring controller 520 can control the locking state of the pneumatic spring 510 . The locking rocker arm 530 is disposed on the tilt shaft 430 . The pneumatic spring 510 is hinged to the locking rocker arm 530 .

[0097] When the pneumatic spring controller 520 receives the aircraft locking control instruction, the pneumatic spring controller 520 controls the pneumatic spring 510 to be in a locked state to lock the swing of the locking rocker arm 530 , thereby locking the tilt axis 430 .

[0098] Combination Figures 2 to 8In a specific embodiment of the present invention, the wing box section 100 includes a wing leading edge rib 120, a wing front beam 130, a wing rear beam 140, a first wing reinforcement rib 150, a second wing reinforcement rib 160 and a third wing reinforcement rib 170.

[0099] The first wing reinforcement rib 150, the second wing reinforcement rib 160 and the third wing reinforcement rib 170 are arranged along a first direction (reference Figure 4 In other words, the first wing reinforcement rib 150, the second wing reinforcement rib 160 and the third wing reinforcement rib 170 can be arranged in their own width direction (reference Figure 4 The wing box section 100 is arranged at equal intervals in the second direction (in the Y-axis direction) to form a wing skeleton, so that the structure of the wing box section 100 is more stable and the safety is ensured.

[0100] The wing front beam 130 is along the second direction (reference Figure 4 The wing rear beam 140 is arranged at the second end of the wing frame along the second direction.

[0101] The wing leading edge rib 120 is fixed to the wing front spar 130 , and the supporting ear piece 110 is arranged at the wing rear spar 140 .

[0102] Specifically, the wing leading edge rib 120 can be made of glass fiber fabric or epoxy resin, and connected to the wing front beam 130 made of carbon fiber fabric or epoxy resin by gluing. Figure 4 The ribs are designed with a depression in the first direction where the X-axis is located, and are assembled into the first wing reinforcement rib 150 and the third wing reinforcement rib 170 made of aluminum alloy, and are connected by rivets at the overlap.

[0103] Of course, the outside of the wing frame is also covered with a skin, which is connected to the wing leading edge rib 120 and the wing frame by countersunk rivets.

[0104] The structure of the wing rear beam 140 is similar to that of the wing front beam 130. The wing rear beam 140 is also made of carbon fiber fabric or epoxy resin. Figure 4 The ribs are designed with a depression in the first direction where the X-axis is located, and are assembled into the first wing reinforcement rib 150 and the third wing reinforcement rib 170 made of aluminum alloy, and are connected by rivets at the overlap.

[0105] In addition, the support ear piece 110 is machined from aluminum alloy, and the support ear piece 110 is connected to the wing rear beam 140 by bolts. Three support ear pieces 110 may be provided, and bolts are respectively used to pass through the wing rear beam 140 and fixedly connected to the first wing reinforcement rib 150, the second wing reinforcement rib 160 and the third wing reinforcement rib 170.

[0106] In some other embodiments, the support ear piece 110 fixed on the first wing reinforcement rib 150 and the third wing reinforcement rib 170 can be respectively integrally processed with the first wing reinforcement rib 150 and the third wing reinforcement rib 170, and the other support ear piece 110 is fixed to the second wing reinforcement rib 160 by bolts.

[0107] The wing rear beam 140 is also provided with a pneumatic spring mounting bracket 511 made of glass fiber fabric or epoxy resin connected by bolts.

[0108] The first wing reinforcement rib 150 , the second wing reinforcement rib 160 , the third wing reinforcement rib 170 and the wing leading edge rib 120 are all designed with lightening holes 180 , which can effectively reduce the weight and provide a channel for the cables of the flap assembly. A strip-shaped small hole 190 is opened on the wing rear beam 140 to provide a channel for the driving connecting rod 440 of the driving mechanism 400 .

[0109] Combination Figures 2 to 8 In a specific embodiment of the present invention, the flap section 200 includes a first flap rib 210 , a second flap rib 220 , a third flap rib 230 , a first transverse box 240 and a second transverse box 250 .

[0110] The first flap rib 210, the second flap rib 220 and the third flap rib 230 are arranged along the first direction (i.e., the adjacent Figure 5 The flaps are arranged in a first direction (in a first direction where the X-axis is located) to form a flap skeleton.

[0111] The first transverse box 240 is disposed between the first flap rib 210 and the second flap rib 220 , and the second transverse box 250 is disposed between the second flap rib 220 and the third flap rib 230 .

[0112] The tilt axis 430 is along the second direction (i.e. Figure 5 The second direction where the Y-axis is located) is arranged at the first end of the flap frame.

[0113] The flap section 200 is installed at the rear of the wing box section 100. When the aircraft is cruising, the flap section 200 mainly bears the interaction of the aerodynamic lift generated by the aircraft, the support reaction force of the tilt axis 430 of the wing box section 100 and the pulling force of the ducted fan propulsion mechanism 300.

[0114] The flap leading edge skin made of fiberglass fabric / epoxy resin is mounted on the first flap rib 210 , the second flap rib 220 , and the third flap rib 230 made of aluminum alloy by countersunk rivets.

[0115] The tilt axis 430 is along the first direction (i.e. Figure 5The first flap rib 210 (the first direction where the X-axis is located) passes through the first flap rib 210, the second flap rib 220, and the third flap rib 230, and is connected to the three flap ribs through a rotating shaft connecting joint. The joint and the rib, the joint and the tilt axis 430 are all connected by bolts, and the rotating shaft connecting joint is an aluminum alloy structure.

[0116] In addition, the first transverse box 240 and the second transverse box 250 are symmetrically arranged. The first transverse box 240 and the second transverse box 250 can be made of aluminum alloy. The four corners of each transverse box are designed with depressions so that it can be installed in three flap ribs. The depressions, flap ribs and flap lower skin are three-layer structures. The overlapping parts are connected with countersunk rivets. The left and right sides of each transverse corner box are connected to the flap ribs by bolts. The flap lower skin made of fiberglass fabric / epoxy resin is connected to the left, right and middle reinforcement ribs of the flap and the lower edge strip of the transverse corner box by countersunk rivets. The upper side of the transverse corner box is a curved surface, which is completely in line with the outer surface of the lower part of the ducted shell of the ducted fan electric propulsion system and is bolted.

[0117] Combination Figures 2 to 8 In a specific embodiment of the present invention, the ducted fan propulsion mechanism 300 includes a ducted housing 310 and a fan 320 , the ducted housing 310 includes a first ducted housing 311 and a second ducted housing 312 , and the fan 320 includes a first fan 321 and a second fan 322 .

[0118] The first fan 321 is rotatably connected to the first duct housing 311 , and the second fan 322 is rotatably connected to the second duct housing 312 .

[0119] The first duct housing 311 is disposed in the first transverse box 240, and the second duct housing 312 is disposed in the second transverse box 250. The power vector direction generated by the first fan 321 and the second fan 322 is parallel to the second direction, thereby ensuring the navigation power of the aircraft.

[0120] In addition, the ducted fan propulsion mechanism 300 is the power source of the vertical take-off and landing aircraft, the ducted shell 310 wraps the internal structure and is connected to the flap section 200. The ducted shell 310 is a fiberglass fabric or epoxy resin structure. The stator blade support 330 inside the ducted shell 310 is the main supporting structure of the duct and is made of aluminum alloy.

[0121] The blades of the ducted fan 320 and the propeller disk 340 are integrally processed from aluminum alloy. The propeller disk 340 is bolted to the stator blade support 330, which is also made of aluminum alloy. The leading edge fairing of the ducted fan is connected to the propeller disk through countersunk rivets, and the trailing edge fairing is connected to the stator blade support through countersunk rivets. Both fairings are made of glass fiber fabric / epoxy resin.

[0122] Combination Fig. 9 An embodiment of the present invention further provides a vertical take-off and landing aircraft, which includes the above-mentioned flap assembly and a vertical take-off and landing aircraft body 600.

[0123] The flap assembly is disposed on the vertical take-off and landing aircraft body 600 .

[0124] It can be understood that the vertical take-off and landing aircraft provided in the embodiment of the present invention, since it includes the above-mentioned flap assembly, must have all the advantages of the flap assembly.

[0125] In this specification, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0126] In the description of this specification, the description with reference to the terms "preferred embodiment", "further embodiment", "some embodiments", "other embodiments" or "specific example" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, unless they are contradictory.

[0127] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations on the present application. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present application.

Claims

1. A method for manufacturing a flap assembly, characterized in that: The following steps are involved: The wing box section is rotatably connected to the flap section, and the ducted fan propulsion mechanism is arranged on the flap section; Drivingly connecting a driving mechanism having a harmonic reducer to the flap segment, so that the driving mechanism drives the flap segment to rotate through the harmonic reducer; A locking mechanism having a pneumatic spring is connected to the flap segment, so that the locking mechanism locks the flap segment through the pneumatic spring.

2. The method for manufacturing a flap assembly according to claim 1, characterized in that: The following steps are also included: The tilt shaft is arranged on the flap section, the wing box section is rotationally hinged with the flap section, and the harmonic reducer is drivingly connected with the tilt shaft; The pneumatic spring is connected to the tilt axis.

3. A flap assembly, characterized in that: The method for manufacturing a flap assembly according to any one of claims 1 to 2 is applied to the flap assembly, and the flap assembly comprises: wing box section; a flap section, rotatably connected to the wing box section; A ducted fan propulsion mechanism is provided on the flap section; A driving mechanism, comprising a driving motor and a harmonic reducer provided in the wing box section, wherein the harmonic reducer is drivingly connected to the flap section, and the driving motor drives the flap section to rotate through the harmonic reducer; The locking mechanism comprises a pneumatic spring, wherein the pneumatic spring is connected to the flap segment.

4. The flap assembly according to claim 3, characterized in that: The driving mechanism also includes a tilting shaft and a driving connecting rod. The tilt shaft is arranged on the flap section, the wing box section is provided with a supporting ear piece, and the tilt shaft is rotatably hinged with the supporting ear piece. The harmonic reducer is drivingly connected to the first end of the driving connecting rod, and the second end of the driving connecting rod is drivingly connected to the tilting shaft.

5. The flap assembly according to claim 4, characterized in that: The driving mechanism also includes a driving swing arm and a driving rocker arm. The driving swing arm is arranged at the output end of the harmonic reducer, and the driving swing arm is hinged to the first end of the driving connecting rod. The driving rocker arm is arranged on the tilting shaft, and the second end of the driving connecting rod is hinged to the driving rocker arm.

6. The flap assembly according to claim 4, characterized in that: The locking mechanism also includes a pneumatic spring controller and a locking rocker arm. The pneumatic spring controller controls the locking state of the pneumatic spring, The locking rocker arm is arranged on the tilting shaft, and the pneumatic spring is hinged to the locking rocker arm.

7. The flap assembly according to claim 4, characterized in that: The wing box section includes a wing leading edge rib, a wing front beam, a wing rear beam, a first wing reinforcement rib, a second wing reinforcement rib and a third wing reinforcement rib. The first wing reinforcement rib, the second wing reinforcement rib and the third wing reinforcement rib are arranged at intervals along a first direction to form a wing skeleton. The wing front beam is arranged at the first end of the wing frame along the second direction, and the wing rear beam is arranged at the second end of the wing frame along the second direction. The wing leading edge rib is fixed to the wing front beam, and the supporting ear piece is arranged on the wing rear beam.

8. The flap assembly according to claim 4, characterized in that: The flap section includes a first flap rib, a second flap rib, a third flap rib, a first transverse box and a second transverse box, The first flap rib, the second flap rib and the third flap rib are arranged at intervals along a first direction to form a flap skeleton, the first transverse box is arranged between the first flap rib and the second flap rib, and the second transverse box is arranged between the second flap rib and the third flap rib. The tilt axis is arranged at the first end of the flap frame along the second direction.

9. The flap assembly according to claim 8, characterized in that The ducted fan propulsion mechanism includes a ducted housing and a fan, the ducted housing includes a first ducted housing and a second ducted housing, and the fan includes a first fan and a second fan. The first fan is rotatably connected to the first duct housing, and the second fan is rotatably connected to the second duct housing. The first duct housing is disposed on the first transverse box, and the second duct housing is disposed on the second transverse box. A direction of a power vector generated by the first fan and the second fan is parallel to the second direction.

10. A vertical take-off and landing aircraft, characterized in that: The invention comprises a flap assembly as claimed in any one of claims 3 to 9 and a vertical take-off and landing aircraft body, The flap assembly is arranged on the vertical take-off and landing aircraft body.

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