CN218617173U

CN218617173U - Swept-wing aircraft capable of taking off and landing vertically

Info

Publication number: CN218617173U
Application number: CN202222254007.9U
Authority: CN
Inventors: 马龙敏
Original assignee: Guangxi Humpback Drone Technology Co ltd
Current assignee: Guangxi Humpback Drone Technology Co ltd
Priority date: 2022-08-26
Filing date: 2022-08-26
Publication date: 2023-03-14
Anticipated expiration: 2032-08-26

Abstract

The utility model belongs to the technical field of the aircraft, a but wing aircraft is swept to change of VTOL is specifically disclosed. This aircraft includes the fuselage and locates the wing of the fuselage left and right sides, still including locating the reversible propeller on fuselage or the wing, the wing includes fixed wing, accomodate wing and activity wing, fixed wing's one end and fuselage fixed connection, the other end and activity wing rotatable coupling, fixed wing's trailing flank and the leading flank of accomodating the wing are connected integratively, the medial surface and the fuselage of accomodating the wing are connected, the groove of accomodating with the activity wing adaptation is seted up to the lateral surface of accomodating the wing, the activity wing can atress abduction to with fixed wing level or receipts to accomodating in the groove. This aircraft not only can VTOL, can realize the conversion of two kinds of flight modes of low-speed gliding and high-speed flight moreover to adapt to different flight task demands, promote flight efficiency, flight stability is high.

Description

Variable-sweep wing aircraft capable of vertically taking off and landing

[ technical field ] A method for producing a semiconductor device

The utility model relates to an aircraft field, in particular to but change of VTOL sweeps wing aircraft.

[ background of the invention ]

With the increasing complexity of the mission and the diversity of the forms of demand, more and more flight missions have a higher demand for aircraft. At present, for variable-geometry aircraft, i.e. "sweepback wing aircraft" (Schwenkfluegler), such known aircraft comprise a fuselage (Rumpf) with pairs of wings projecting laterally from both sides, each having an internal fixed wing segment arranged stationary with respect to the fuselage and an external movable wing segment coupled at the end of the fixed wing and swingable about its swing axis. The wingspan is increased by opening the movable wing sections, the flying at low speed can be realized, the range is increased, and the high-speed flying can be realized by folding the movable wing sections, namely, the conversion of two flying modes can be realized. However, the current variable-sweep-wing aircraft cannot realize vertical take-off and landing and cannot well meet various requirements under different flight conditions and different fields.

[ Utility model ] content

In order to overcome the not enough of prior art, the utility model aims to provide a but change of VTOL sweepers wing aircraft, this aircraft simple structure not only can VTOL, can realize the conversion of two kinds of flight modes of low-speed gliding and high-speed flight moreover to adapt to different flight task demands, promote flight efficiency, flight stability is high.

In order to achieve the above purpose, the utility model adopts the technical proposal that:

a swept-wing aircraft capable of taking off and landing vertically comprises an aircraft body, wings arranged on the left side and the right side of the aircraft body, and a variable-direction propeller, wherein the variable-direction propeller is arranged on the aircraft body or the wings; the wing includes fixed wing, accomodates wing and activity wing, fixed wing's one end with fuselage fixed connection, fixed wing's trailing flank with accomodate the leading flank body coupling of wing, the medial surface of accomodating the wing with the fuselage is connected, the lateral surface of accomodating the wing seted up with the groove of accomodating of activity wing adaptation, the one end of activity wing pass through runner assembly with fixed wing's other end rotatable coupling, activity wing atress abduction extremely with fixed wing level or receipts are closed extremely accomodate in the groove.

Furthermore, a connecting groove is formed in the end face of the other end of the fixed wing, the connecting groove is integrally communicated with the accommodating groove, and one end of the movable wing is inserted into the connecting groove and connected with the rotating assembly.

Further, rotating assembly includes drive gear, screens pole and installation axle, drive gear is rotatable install in on the fixed wing, the one end of screens pole with fixed wing rotatable coupling, the one end of activity wing is passed through the installation axle is rotatable install in on the fixed wing, one side of activity wing one end port be equipped with the screens groove of screens pole adaptation, just still be equipped with on the port of activity wing one end and be curved rack, the rack is followed the screens groove extends to the opposite side of activity wing one end port, the rack with the drive gear meshing under drive gear's the drive, the activity wing can abduction extremely the screens pole block in the screens groove or receive to close in receiving in the groove.

Further, the width of accomodating the wing constantly reduces from front to back, just the rear end of accomodating the wing is at least the tail parallel and level of fuselage.

Furthermore, a tail wing is arranged on the top surface of the rear end of the containing wing.

Furthermore, the pair of variable direction propellers is symmetrically arranged on the top surfaces of the two fixed wings and is positioned at one end close to the movable wing.

Furthermore, the direction-variable propeller comprises a connecting rod, a direction changer, a rotation driving mechanism and a paddle mechanism, the lower end of the connecting rod is connected with the fixed wing, a mounting plate is mounted at the upper end of the connecting rod, the direction changer and the rotation driving mechanism are mounted on the mounting plate, the rotation driving mechanism is mounted at the output end of the direction changer or movably arranged in the direction changer in a penetrating manner, and the output end of the rotation driving mechanism is connected with the paddle mechanism.

Owing to used the technical scheme of the utility model, the utility model discloses following beneficial effect has:

the aircraft is provided with the movable wings which can be unfolded and folded, so that the aspect ratio of the wings can be effectively expanded during unfolding, the endurance performance of the whole aircraft is improved, the flight of the aircraft can be effectively expanded, high-speed flight can be realized during folding during flight, namely, the conversion between two flight modes of low-speed gliding and high-speed flight can be realized, different flight task requirements can be met, and the flight efficiency is improved; meanwhile, the vertical take-off and landing and the auxiliary flight of the aircraft can be realized by the turning of the propeller through the arrangement of the steerable propeller. In addition, through reasonable and scientific arrangement and combination of all parts of the wings, the stability and safety of the flying motion of the aircraft can be effectively improved.

[ description of the drawings ]

Fig. 1 is a schematic perspective view of the extended state of the sweep-variable wing aircraft capable of vertical take-off and landing of the present invention.

Fig. 2 is a top view of fig. 1.

Fig. 3 is a bottom view of fig. 1.

Fig. 4 is a bottom view of the movable wing of the aircraft in the folded state.

Fig. 5 is a front view of fig. 1.

Fig. 6 is a schematic view of the connection structure of the fixed wing and the movable wing of the present invention.

Fig. 7 is another schematic perspective view of the sweep-wing aircraft in the extended state of the present invention, which can take off and land vertically.

Description of the main elements

In the figure, 1-a fuselage, 2-a fixed wing, 21-a connecting groove, 3-a storage wing, 31-a storage groove, 4-a movable wing, 41-a clamping groove, 42-a rack, 5-a steerable propeller, 51-a connecting rod, 52-a diverter, 53-a rotation driving mechanism, 54-a blade mechanism, 55-a mounting seat, 541-a reinforced ring, 542-a blade, 543-a rotation seat, 6-an empennage, 7-a clamping rod, 8-a mounting shaft and 9-a driving gear.

The following detailed description of the invention will be further described in conjunction with the above-identified drawings.

[ detailed description ] embodiments

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When a component is referred to as being "connected" to another component, it can be directly connected to the other component or intervening components may also be present. When a component is referred to as being "disposed on" another component, it can be directly on the other component or there can be intervening components, and when a component is referred to as being "disposed in the middle," it is not just disposed in the middle, so long as it is not disposed at both ends, but rather is within the scope of the middle. The terms "vertical," "horizontal," "left," "right," and the like as used herein are for illustrative purposes only.

Referring to fig. 1 to 3 and 5, in a preferred embodiment of the present invention, a vertical take-off and landing variable sweep wing aircraft includes a fuselage 1, wings disposed on left and right sides of the fuselage 1, and a steerable propeller 5 disposed on the wings. The wing includes fixed wing 2, accomodates wing 3 and activity wing 4, fixed wing 2's one end with 1 fixed connection of fuselage, fixed wing 2's trailing flank with accomodate the leading flank body coupling of wing 3, accomodate the medial surface of wing 3 with fuselage 1 is connected, the width of accomodating wing 3 constantly reduces from the front to the back, just the rear end of accomodating wing 3 at least with fuselage 1's tail parallel and level, the lateral surface of accomodating wing 3 seted up with the groove 31 of accomodating of activity wing 4 adaptation, it is equipped with fin 6 on the top surface of wing 3 rear end, and is a pair of fin 6's fixed setting can promote the equilibrium of aircraft. Through the wing body integration design of the fixed wing 2, the storage wing 3 and the fuselage 1, the fuselage area can be increased, so that the lift force and the use effect are improved.

The other end of the fixed wing 2 is rotatably connected with one end of the movable wing 4 through a rotating component, and the movable wing 4 can be forced to extend out to be horizontal to the fixed wing 2 or be folded into the accommodating groove 31 under the driving of the rotating component.

With continued reference to fig. 6, in the present embodiment, the fixed wing 2 and the movable wing 4 are connected by the rotating assembly in the following specific relationship: the rotating assembly comprises a driving gear 9, a clamping rod 7 and an installation shaft 8, the end face of the other end of the fixed wing 2 is provided with a connecting groove 21, the connecting groove 21 is integrally communicated with the accommodating groove 31, one end of the movable wing 4 is inserted into the connecting groove 21, the clamping rod 7 is positioned in the connecting groove 21, one end of the clamping rod is rotatably connected with the fixed wing 2, one end of the movable wing 4 is rotatably installed on the fixed wing 2 through the installation shaft 8, one side of a port at one end of the movable wing 4 is provided with a clamping groove 41 matched with the clamping rod 7, a port at one end of the movable wing 4 is also provided with an arc-shaped rack 42, and the rack 42 extends from the clamping groove 41 to the other side of the port at one end of the movable wing 4, the drive gear 9 is rotatably installed in the connecting groove 21 and located behind the position clamping rod 7, the rack 42 is engaged with the drive gear 9, under the forward drive of the drive gear 9, the movable wing 4 can be gradually rotated from the folding state to be unfolded to the position clamping rod 7 to be clamped in the position clamping groove 41 for fixation, at the moment, the movable wing 4 and the fixed wing 2 are stably located on the same horizontal line, under the reverse drive of the drive gear 9, the movable wing reversely rotates to be folded from the unfolding state to be located in the accommodating groove 31 (as shown in fig. 4), and in the folding process, the position clamping rod 7 is ejected by the rack and is disengaged from the position clamping groove 41. Through wing abduction, can expand the aspect ratio of wing effectively, promote complete machine continuation of the journey performance, the flight time of effectual expansion aircraft, and the wing can realize high-speed flight when closing, can realize the conversion of two kinds of flight modes of low-speed gliding and high-speed flight promptly to adapt to different flight task demands, promote flight efficiency.

The variable direction propeller 5 is a pair of variable direction propellers 5 symmetrically arranged on the top surfaces of the left fixed wing 2 and the right fixed wing 2 and positioned at one end close to the movable wing 4, and is used for providing power and steering, and the variable direction propeller 5 comprises a connecting rod 51, a direction changer 52, a rotation driving mechanism 53 and a blade mechanism 54, wherein the lower end of the connecting rod 51 is connected with the fixed wings 2, the upper end of the connecting rod 51 is provided with a mounting plate, the direction changer 52 is mounted on the mounting plate, the output end of the direction changer 52 is connected with the rotation driving mechanism 53, and the output end of the rotation driving mechanism 53 is connected with the blade mechanism 54 (or the rotation driving mechanism 53 is mounted on the mounting plate, and the output end of the rotation driving mechanism 53 movably penetrates through the body of the direction changer 52 and is connected with the blade mechanism 54). The direction changer 52 can swing spatially and maintain a changed spatial swing angle, so as to change the angle of the paddle mechanism 54 to adapt to various application occasions and facilitate later control, and the rotation driving mechanism 53 is used for providing a rotating force to rotate the paddle mechanism 54. Paddle mechanism 54 specifically includes rotates seat 543, a plurality of paddle 542 and reinforces ring 541, and all paddle 542 follows the circumferential direction that rotates seat 543 evenly sets up on the periphery that rotates seat 543, rotate seat 543 with the output that rotates actuating mechanism 53 is connected, reinforce ring 541's inboard with the outside one end of paddle 542 is connected, connects through strengthening ring 541 at the outside one end of paddle 542, can effectively improve the intensity of the outside one end of paddle 542, makes paddle mechanism 54 when the rotation center direction changes, strengthens ring 541 can reduce the anti deformability who makes the outside one end of paddle 542, improves the rotational stability of whole paddle mechanism 54, reduces the vibration.

In this embodiment, the connection rod 51 is inclined towards the front and the outside, and the inclination of the connection rod 51 in combination with the direction change of the blade mechanism 54 can improve the safety of the aircraft in use, ensuring that in the event of failure of one of the steerable propellers, the other steerable propeller can still be used for smooth landing.

In this embodiment, the structures of the direction changer 52 and the rotation driving mechanism 53 and the connection structures therebetween are the prior art, and a rotor device with strong interference immunity and a direction changer and a rotation driving mechanism (i.e. a power mechanism) and corresponding connection structures described in an aircraft can be adopted, for example, in chinese utility model CN216232961U, or other direction changers and rotation driving mechanisms in the prior art can be adopted, as long as the space swing direction change and rotation of the blade mechanism 54 can be realized.

Through the combination of the wingable structure and the pair of the steerable propellers 5, the bearing capacity of the aircraft is greatly improved, and the unmanned aerial vehicle and the manned aircraft can be used.

In another embodiment of the present invention, the rotating assembly may adopt other structures in the prior art, as long as the stable outward expansion and the folding of the movable wing can be realized.

To sum up, the utility model discloses an aircraft simple structure not only can the VTOL, can realize the low-speed conversion of gliding and two kinds of flight modes of high-speed flight moreover to adapt to different flight task demands, promote flight efficiency, flight stability is high.

Claims

1. The utility model provides a but vertical take-off and landing's becomes and sweeps wing aircraft, includes the fuselage and locates the wing of fuselage left and right sides, its characterized in that: the variable-direction propeller is arranged on the airframe or the wing; the wing includes fixed wing, accomodate wing and activity wing, fixed wing's one end with fuselage fixed connection, fixed wing's trailing flank with accomodate the leading flank body coupling of wing, accomodate the medial surface of wing with the fuselage is connected, accomodate the lateral surface of wing seted up with the groove of accomodating of activity wing adaptation, the one end of activity wing pass through rotating assembly with fixed wing's other end rotatable coupling, the activity wing can be atress abducted to with fixed wing level or receipts are closed extremely accomodate in the groove.

2. The vtol variable-sweep aircraft according to claim 1, wherein: the end face of the other end of the fixed wing is provided with a connecting groove, the connecting groove is integrally communicated with the accommodating groove, and one end of the movable wing is inserted into the connecting groove and connected with the rotating assembly.

3. The VTOL swept wing aircraft of claim 1 or 2, wherein: the runner assembly includes drive gear, screens pole and installation axle, drive gear rotatable install in on the fixed wing, the one end of screens pole with fixed wing rotatable coupling, the one end of activity wing is passed through the installation axle is rotatable install in on the fixed wing, one side of activity wing one end port be equipped with the screens groove of screens pole adaptation, just still be equipped with on the port of activity wing one end and be curved rack, the rack is followed the screens groove extends to the opposite side of activity wing one end port, the rack with drive gear meshes under drive gear's the drive, the activity wing can abduct extremely the screens pole block close in the screens groove or receive and close in accomodate in the groove.

4. The vtol variable-sweep aircraft according to claim 1, wherein: the width of accomodating the wing constantly reduces from the front to the back, just the rear end of accomodating the wing is at least the tail parallel and level of fuselage.

5. The VTOL swept-wing aircraft of claim 1, wherein: and the top surface of the rear end of the storage wing is provided with a tail wing.

6. The vtol variable-sweep aircraft according to claim 1, wherein: the pair of the variable direction propellers is symmetrically arranged on the top surfaces of the two fixed wings and is positioned at one end close to the movable wing.

7. The VTOL sweeped wing aircraft of claim 6, wherein: the variable-direction propeller comprises a connecting rod, a direction changer, a rotary driving mechanism and a paddle mechanism, the lower end of the connecting rod is connected with the fixed wing, a mounting plate is mounted at the upper end of the connecting rod, the direction changer and the rotary driving mechanism are mounted on the mounting plate, the rotary driving mechanism is mounted at the output end of the direction changer or movably arranged in the direction changer in a penetrating mode, and the output end of the rotary driving mechanism is connected with the paddle mechanism.