A variable-sweep wing aircraft capable of vertical take-off and landing

Abstract

The present invention belongs to the technical field of aircraft, and specifically discloses a variable-sweep wing aircraft capable of vertical take-off and landing. The aircraft includes a fuselage and wings arranged on the left and right sides of the fuselage, and also includes a directional-adjustable propeller arranged on the fuselage or the wing. The wing includes a fixed wing, a stowed wing and a movable wing. One end of the fixed wing is fixedly connected to the fuselage, and the other end is rotatably connected to the movable wing. The rear side of the fixed wing is integrally connected to the front side of the stowed wing, the inner side of the stowed wing is connected to the fuselage, and the outer side of the stowed wing is provided with a stowage groove adapted to the movable wing. The movable wing can be extended outward to the level of the fixed wing or retracted into the stowage groove under force. The aircraft can not only take off and land vertically, but also realize the conversion of two flight modes, low-speed gliding and high-speed flight, to meet the requirements of different flight missions, improve flight efficiency, and have high flight stability.

Description

[Technical field]

[0001] The invention relates to the field of aircraft, and in particular to a variable-sweep-wing aircraft capable of vertical take-off and landing. [Background technology]

[0002] With the increase of mission complexity and the diversity of demand forms, more and more flight missions have higher requirements for aircraft. At present, for aircraft with variable geometry, i.e. "variable sweep wing aircraft (Schwenkfluegler)", this known aircraft includes a fuselage (Rumpf), the fuselage has a pair of wings extending laterally from both sides, and the wings respectively have an internal fixed wing section statically arranged with respect to the fuselage and an external movable wing section connected to the end of the fixed wing and swingable around its swing axis. By opening the movable wing section to increase the wingspan, low-speed gliding can be achieved to increase the range, and by folding the movable wing section, high-speed flight can be achieved, that is, the conversion of two flight modes can be achieved. However, the structure of the current variable sweep wing aircraft cannot achieve vertical take-off and landing, and cannot well meet the various requirements under different flight conditions and different fields. [Summary of the invention]

[0003] In view of the above, it is necessary to provide a variable-sweep wing aircraft that can take off and land vertically. The aircraft has a simple structure and can not only take off and land vertically, but also can realize the conversion between low-speed gliding and high-speed flight modes to adapt to different flight mission requirements, improve flight efficiency, and have high flight stability.

[0004] In order to achieve the above object, the technical solution adopted by the present invention is:

[0005] A variable-sweep wing aircraft capable of vertical take-off and landing comprises a fuselage and wings arranged on left and right sides of the fuselage, and also comprises variable-direction propellers, wherein the variable-direction propellers are arranged on the fuselage or the wings; the wings comprise fixed wings, stowed wings and movable wings, one end of the fixed wing is fixedly connected to the fuselage, the rear side surface of the fixed wing is integrally connected to the front side surface of the stowed wing, the inner side surface of the stowed wing is connected to the fuselage, and a stowage groove adapted to the movable wing is provided on the outer side surface of the stowed wing, one end of the movable wing is rotatably connected to the other end of the fixed wing via a rotating assembly, and the movable wing can be extended outward by force to be level with the fixed wing or stowed in the stowage groove.

[0006] Furthermore, a connecting groove is provided on the end surface of the other end of the fixed wing, the connecting groove and the receiving groove are connected as one body, and one end of the movable wing is inserted into the connecting groove and connected to the rotating assembly.

[0007] Furthermore, the rotating assembly includes a driving gear, a locking rod and a mounting shaft, the driving gear can be rotatably mounted on the fixed wing, one end of the locking rod is rotatably connected to the fixed wing, one end of the movable wing can be rotatably mounted on the fixed wing through the mounting shaft, one side of the port at one end of the movable wing is provided with a locking groove adapted to the locking rod, and the port at one end of the movable wing is also provided with an arc-shaped rack, the rack extends from the locking groove to the other side of the port at one end of the movable wing, the rack is meshed with the driving gear, and under the drive of the driving gear, the movable wing can be extended outward until the locking rod is engaged in the locking groove or retracted in the storage groove.

[0008] Furthermore, a filling airbag is provided on the inner side of the storage groove, and the filling airbag can just fill the storage groove when it is filled with gas.

[0009] Furthermore, the width of the stowed wing decreases continuously from front to back, and the rear end of the stowed wing is at least flush with the tail of the fuselage.

[0010] Furthermore, a tail wing is provided on the top surface of the rear end of the storage wing.

[0011] Furthermore, the variable-direction propellers are a pair, and the pair of variable-direction propellers are symmetrically arranged on the top surfaces of the two fixed wings and located near one end of the movable wing.

[0012] Furthermore, the variable-direction propeller includes a connecting rod, a direction changer, a rotation drive mechanism and a blade mechanism. The lower end of the connecting rod is connected to the fixed wing, and the upper end of the connecting rod is equipped with a mounting plate, and the direction changer and the rotation drive mechanism are mounted on the mounting plate. The rotation drive mechanism is installed on the output end of the direction changer or movably arranged in the direction changer, and the output end of the rotation drive mechanism is connected to the blade mechanism.

[0013] Furthermore, there is one variable-direction propeller, and one variable-direction propeller is arranged at the nose of the aircraft.

[0014] Furthermore, the variable-direction propeller includes a mounting seat, a direction changer, a rotation drive mechanism and a blade mechanism. The rear side of the mounting seat is connected to the nose of the machine, the direction changer is installed on the mounting seat, the rotation drive mechanism is installed on the output end of the direction changer or is installed on the fuselage and movably passes through the direction changer, and the output end of the rotation drive mechanism is connected to the blade mechanism.

[0015] The present invention has the following beneficial effects:

[0016] The aircraft is equipped with movable wings that can be extended and retracted. When extended, the aspect ratio of the wings can be effectively expanded, the endurance performance of the whole aircraft can be improved, and the flight time of the aircraft can be effectively extended. When retracted, it can achieve high-speed flight, that is, it can realize the conversion of low-speed gliding and high-speed flight modes to meet the needs of different flight missions and improve flight efficiency. At the same time, by setting up variable-direction propellers, the aircraft can achieve vertical take-off and landing and assisted flight through the change of propeller direction. In addition, through the reasonable and scientific setting and combination of various wing components, the stability and safety of the aircraft's flight movement can be effectively improved.

Brief Description of the Drawings

[0017] Figure 1 The present invention is a three-dimensional structural schematic diagram of a variable-sweep wing aircraft capable of vertical take-off and landing in an extended state.

[0018] Figure 2 yes Figure 1 Top view of the .

[0019] Figure 3 yes Figure 1 Bottom view of .

[0020] Figure 4 It is a bottom view of the movable wings of the aircraft of the present invention in a folded state.

[0021] Figure 5 yes Figure 1 Front view of .

[0022] Figure 6 It is a schematic diagram of the connection structure of the fixed wing and the movable wing of the present invention.

[0023] Figure 7 It is another three-dimensional structural schematic diagram of a variable-sweep wing aircraft capable of vertical take-off and landing in an extended state according to the present invention.

[0024] Main component symbols

[0025] In the figure, 1-fuselage, 2-fixed wing, 21-connecting slot, 3-storage wing, 31-storage slot, 4-movable wing, 41-locking slot, 42-rack, 5-variable propeller, 51-connecting rod, 52-direction changer, 53-rotation drive mechanism, 54-blade mechanism, 55-mounting seat, 541-reinforcement ring, 542-blade, 543-rotating seat, 6-tail, 7-locking rod, 8-mounting shaft, 9-driving gear.

[0026] The following specific implementation manner will further illustrate the present invention in conjunction with the above-mentioned drawings. [Specific implementation method]

[0027] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0028] It should be noted that when a component is referred to as being "fixed to" another component, it may be directly on the other component or there may be a central component. When a component is considered to be "connected to" another component, it may be directly connected to the other component or there may be a central component at the same time. When a component is considered to be "set on" another component, it may be directly set on the other component or there may be a central component at the same time. When a component is referred to as being "set in the middle", it does not only mean being set in the middle, as long as it is not set at both ends within the range defined by the middle. The terms "vertical", "horizontal", "left", "right" and similar expressions used herein are for illustrative purposes only.

[0029] See also Figures 1 to 3 and Figure 5 In a preferred embodiment of the present invention, a variable-sweep wing aircraft capable of vertical take-off and landing comprises a fuselage 1, wings arranged on the left and right sides of the fuselage 1, and variable-direction propellers 5 arranged on the wings. The wings comprise fixed wings 2, stowed wings 3, and movable wings 4. One end of the fixed wing 2 is fixedly connected to the fuselage 1, the rear side of the fixed wing 2 is integrally connected to the front side of the stowed wing 3, the inner side of the stowed wing 3 is connected to the fuselage 1, the width of the stowed wing 3 decreases continuously from front to back, and the rear end of the stowed wing 3 is at least flush with the tail of the fuselage 1, the outer side of the stowed wing 3 is provided with a stowage slot 31 adapted to the movable wing 4, and a tail 6 is provided on the top surface of the rear end of the stowed wing 3. The fixed arrangement of a pair of tails 6 can improve the balance of the aircraft. By integrating the fixed wing 2 and the retractable wing 3 with the fuselage 1, the fuselage area can be increased, thereby improving the lift and the use effect.

[0030] The other end of the fixed wing 2 is rotatably connected to one end of the movable wing 4 via a rotating assembly. Driven by the rotating assembly, the movable wing 4 can be forced to extend outward to be level with the fixed wing 2 or to be retracted into the storage slot 31 .

[0031] Continue reading Figure 6In this embodiment, the specific relationship between the fixed wing 2 and the movable wing 4 is connected through the rotating assembly as follows: the rotating assembly includes a driving gear 9, a locking rod 7 and a mounting shaft 8, a connecting groove 21 is provided on the end surface of the other end of the fixed wing 2, the connecting groove 21 and the receiving groove 31 are connected as a whole, one end of the movable wing 4 is inserted into the connecting groove 21, the locking rod 7 is located in the connecting groove 21 and one end of the movable wing 2 is rotatably connected, one end of the movable wing 4 is rotatably installed on the fixed wing 2 through the mounting shaft 8, one side of the port at one end of the movable wing 4 is provided with a locking groove 41 adapted to the locking rod 7, and the movable An arc-shaped rack 42 is also provided on the port at one end of the wing 4, and the rack 42 extends from the locking groove 41 to the other side of the port at one end of the movable wing 4. The driving gear 9 is rotatably installed in the connecting groove 21 and is located behind the locking rod 7. The rack 42 is meshed with the driving gear 9. Under the positive drive of the driving gear 9, the movable wing 4 can be gradually rotated outward from the folded state until the locking rod 7 is engaged and fixed in the locking groove 41. At this time, the movable wing 4 and the fixed wing 2 are stably located on the same horizontal line, and under the reverse drive of the driving gear 9, the movable wing rotates in the reverse direction from the outstretched state to the storage groove 31 (such as Figure 4 As shown in the figure, during the folding process, the locking rod 7 is pushed out of the locking groove 41 by the rack. By extending the wings, the aspect ratio of the wings can be effectively extended, the endurance performance of the whole aircraft can be improved, and the flight time of the aircraft can be effectively extended. When the wings are folded, high-speed flight can be achieved, that is, the conversion between low-speed gliding and high-speed flight modes can be achieved to meet the requirements of different flight missions and improve flight efficiency.

[0032] The directional-changeable propellers 5 are a pair, and the pair of directional-changeable propellers 5 are symmetrically arranged on the top surfaces of the left and right fixed wings 2 and located at one end close to the movable wing 4, for providing power and steering, and include a connecting rod 51, a direction changer 52, a rotation drive mechanism 53 and a blade mechanism 54, the lower end of the connecting rod 51 is connected to the fixed wing 2, the upper end of the connecting rod 51 is installed with a mounting plate, the mounting plate is installed with the direction changer 52, the output end of the direction changer 52 is connected to the rotation drive mechanism 53, and the output end of the rotation drive mechanism 53 is connected to the blade mechanism 54 (or the rotation drive mechanism 53 is installed on the mounting plate, and the output end of the rotation drive mechanism 53 is movably arranged through the body of the direction changer 52 and connected to the blade structure 54). The direction changer 52 can realize spatial swing and maintain the changed spatial swing angle, thereby changing the angle of the blade mechanism 54 to adapt to a variety of application occasions and facilitate later control, and the rotation drive mechanism 53 is used to provide rotational force to rotate the blade mechanism 54. The blade mechanism 54 specifically includes a rotating seat 543, a plurality of blades 542 and a reinforcement ring 541. All the blades 542 are evenly arranged on the outer periphery of the rotating seat 543 along the circumferential direction of the rotating seat 543. The rotating seat 543 is connected to the output end of the rotating drive mechanism 53. The inner side of the reinforcement ring 541 is connected to the outward end of the blade 542. The outward end of the blade 542 is connected by the reinforcement ring 541, which can effectively improve the strength of the outward end of the blade 542. When the blade mechanism 54 changes the direction of the rotation center, the reinforcement ring 541 can reduce the deformation resistance of the outward end of the blade 542, thereby improving the rotation stability of the entire blade mechanism 54 and reducing vibration.

[0033] In this embodiment, the connecting rod 51 is inclined toward the front and the outside. The inclined setting of the connecting rod 51 combined with the changing direction of the blade mechanism 54 can improve the safety performance of the aircraft and ensure that in the event that one of the variable-direction propellers fails, the aircraft can still land smoothly by relying on the other variable-direction propeller.

[0034] In this embodiment, the structures of the deflector 52 and the rotation drive mechanism 53 and the connection structures therebetween are all prior art, and may adopt deflectors and rotation drive mechanisms (i.e., power mechanisms) and corresponding connection structures as described in the rotor device and aircraft with strong anti-interference performance in Chinese utility model patent CN 216232961 U, or other deflectors and rotation drive mechanisms in the prior art, as long as the spatial swinging, changing direction and rotation of the blade mechanism 54 can be realized.

[0035] In this embodiment, a filling airbag (not shown in the figure) is provided on the inner side of the storage groove 31. When the filling airbag is filled with gas, it can just fill the storage groove 31. When the movable wing 4 is in an extended state, the filling airbag is inflated to fill the storage groove 31 to further improve the stability of the aircraft movement.

[0036] By combining the expandable wing structure and a pair of directional-adjustable propellers 5, the carrying capacity of the aircraft is greatly improved, and the aircraft can be used for both unmanned aerial vehicles and manned aircraft.

[0037] See also Figure 7 In another embodiment of the present invention, there is only one variable-direction propeller 5, which is arranged on the nose of the fuselage 1. The variable-direction propeller 5 includes a mounting seat 55, a direction changer 52, a rotation drive mechanism (not shown) and a blade mechanism 54. The rear side of the mounting seat 55 is connected to the nose of the fuselage 1. The direction changer 52 is mounted on the mounting seat 55. The rotation drive mechanism is mounted on the output end of the direction changer or is mounted on the fuselage 1 and movably penetrates the direction changer 52 (which can reduce the weight outside the fuselage). The output end of the rotation drive mechanism is connected to the blade mechanism 54. The design of a model with one variable-direction propeller 5 arranged on the nose makes the aircraft lightweight and has a wider range of applications.

[0038] In another embodiment of the present invention, the rotating assembly may adopt other structures in the prior art as long as the stable extension and retraction of the movable wing can be achieved.

[0039] The above description is a detailed description of the preferred feasible embodiments of the present invention, but the embodiments are not intended to limit the scope of the patent application of the present invention. All equivalent changes or modified changes completed under the technical spirit suggested by the present invention should fall within the patent scope covered by the present invention.

Claims

1. A variable-sweep wing aircraft capable of vertical take-off and landing, comprising a fuselage and wings arranged on the left and right sides of the fuselage, characterized in that: It also includes a variable-direction propeller, which is arranged on the fuselage or the wing; the wing includes a fixed wing, a stowed wing and a movable wing, one end of the fixed wing is fixedly connected to the fuselage, the rear side of the fixed wing is integrally connected to the front side of the stowed wing, the inner side of the stowed wing is connected to the fuselage, and the outer side of the stowed wing is provided with a stowage groove adapted to the movable wing, one end of the movable wing is rotatably connected to the other end of the fixed wing through a rotating assembly, and the movable wing can be extended outward to be level with the fixed wing or stowed in the stowage groove under force; There is a pair of adjustable propellers, which are symmetrically arranged on the top surfaces of the two fixed wings and located at one end close to the movable wing; the adjustable propeller includes a connecting rod, a direction changer, a rotation drive mechanism and a blade mechanism, the lower end of the connecting rod is connected to the fixed wing, the upper end of the connecting rod is equipped with a mounting plate, the direction changer and the rotation drive mechanism are installed on the mounting plate, the rotation drive mechanism is installed on the output end of the direction changer or movably inserted in the direction changer, and the output end of the rotation drive mechanism is connected to the blade mechanism; the connecting rod is inclined toward the front and the outside.

2. A variable-sweep wing aircraft capable of vertical take-off and landing according to claim 1, characterized in that: A connecting groove is formed on the end surface of the other end of the fixed wing, and the connecting groove is connected to the receiving groove as a whole. One end of the movable wing is inserted into the connecting groove and connected to the rotating assembly.

3. A variable-sweep wing aircraft capable of vertical take-off and landing according to claim 1 or 2, characterized in that: The rotating assembly includes a driving gear, a locking rod and a mounting shaft, the driving gear can be rotatably mounted on the fixed wing, one end of the locking rod is rotatably connected to the fixed wing, one end of the movable wing is rotatably mounted on the fixed wing through the mounting shaft, one side of the port at one end of the movable wing is provided with a locking groove adapted to the locking rod, and the port at one end of the movable wing is also provided with an arc-shaped rack, the rack extends from the locking groove to the other side of the port at one end of the movable wing, the rack is meshed with the driving gear, and under the drive of the driving gear, the movable wing can be extended outward until the locking rod is engaged in the locking groove or retracted in the receiving groove.

4. The variable-sweep wing aircraft capable of vertical take-off and landing according to claim 1, characterized in that: A filling air bag is arranged on the inner side of the storage groove, and the filling air bag can just fill the storage groove when it is filled with gas.

5. The variable-sweep wing aircraft capable of vertical take-off and landing according to claim 1, characterized in that: The width of the stowed wing decreases continuously from front to back, and the rear end of the stowed wing is at least flush with the tail of the fuselage.

6. The variable-sweep wing aircraft capable of vertical take-off and landing according to claim 1, characterized in that: A tail wing is arranged on the top surface of the rear end of the storage wing.

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