CN210310854U - Can hang wing formula unmanned aerial vehicle that takes off perpendicularly - Google Patents
Can hang wing formula unmanned aerial vehicle that takes off perpendicularly Download PDFInfo
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- CN210310854U CN210310854U CN201920592559.6U CN201920592559U CN210310854U CN 210310854 U CN210310854 U CN 210310854U CN 201920592559 U CN201920592559 U CN 201920592559U CN 210310854 U CN210310854 U CN 210310854U
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Abstract
The utility model discloses a but wing formula unmanned aerial vehicle that takes off perpendicularly, unmanned aerial vehicle include wing, preceding screw and aileron, and the aileron setting is at unmanned aerial vehicle's rear portion, and two sections alar parts include wing outer segment, wing middle section and wing inner segment respectively about the wing. The utility model has the advantages that: the aircraft has the advantages of both flying wing type aircraft and rotary wing type aircraft, reduces the power consumption, has large carrying capacity and can use sufficient space. Have stronger equilibrium and operating stability, when unmanned aerial vehicle stall, can become gyroplane safety and compel to land, play the effect that the protection carried the thing.
Description
Technical Field
The utility model belongs to the aviation unmanned aerial vehicle field, concretely relates to wing formula unmanned aerial vehicle can take off perpendicularly.
Background
The flying wing type airplane has no empennage and fuselage, and has the advantages of small resistance, low wing load, good stealth performance, large available space in the wing and the like, so that the flying wing type airplane is widely applied to military and life except for the characteristics of high flying speed and high flexibility. However, the take-off and landing of the flying-wing aircraft must depend on the runway, and the helicopter does not have the defect that the flying-wing aircraft can ascend and descend at zero speed and hover, but cannot fly at high speed due to the limitation of the rotor wing, and has very short voyage. Since the 40 s of the 20 th century, various countries have searched for novel aviation aircrafts having the vertical take-off and landing, hovering front and rear side flight capabilities of helicopters and the characteristics of high speed and long range of fixed-wing aircrafts.
Disclosure of Invention
Based on above-mentioned background art and problem, the utility model provides a:
a vertical take-off wing type unmanned aerial vehicle comprises wings, a front propeller and an aileron, wherein the aileron is arranged at the rear part of the unmanned aerial vehicle, the left and right wing parts of the wings respectively comprise an outer wing section, an intermediate wing section and an inner wing section, the intermediate wing section is hinged with the upper part of the inner wing section, a loop bar is connected between the intermediate wing section and the inner wing section, the outer wing section is hinged with the lower part of the intermediate wing section, a first hydraulic oil cylinder is connected between the outer wing section and the inner wing section, a pulling mechanism is fixed in the inner wing section, a fixed rod is fixedly arranged in the inner wing section, a sleeve is sleeved on the fixed rod, the pulling mechanism is connected with a driving connecting rod, the driving connecting rod is hinged with a pull rod, the pull rod is hinged on a driven connecting rod, one end of the driven connecting rod is hinged with the sleeve, the other end of the driven connecting rod, be provided with the leather sheath between wing middle section and the wing inner segment, the paddle of side screw is retractable, preceding screw is connected with the transform mechanism that verts, the transform mechanism that verts is used for driving preceding screw at horizontality and vertical state transform.
Furthermore, a support sleeve is arranged inside the middle section of the wing and is sleeved on the driven connecting rod to support the driven connecting rod.
Furthermore, the leather sheath can play a role in protecting the interior of the wing when the middle section of the wing is in a vertical state.
Furthermore, the paddle is provided with a front end, a rear end and a moving sleeve, the moving sleeve is arranged between the front end and the rear end and can slide between the front end and the rear end, a second hydraulic oil cylinder is connected to the front end and the rear end inside the paddle, and the rear end is fixed on the propeller rotating shaft.
Furthermore, one end of the loop bar is hinged with the middle section of the wing, and the other end of the loop bar is hinged with the inner section of the wing.
Furthermore, one end of the first hydraulic oil cylinder is hinged with the outer section of the wing, the other end of the first hydraulic oil cylinder is hinged with the inner section of the wing, and the first hydraulic oil cylinder is located below the wing.
Furthermore, the support sleeve is fixed in the middle section of the wing, the driven connecting rod can rotate in the support sleeve, the sleeve can slide on the fixed rod, and the sleeve rod is telescopic.
The utility model aims at: a vertical take-off wing type unmanned aerial vehicle capable of realizing interconversion between a flying wing type unmanned aerial vehicle and a propeller type unmanned aerial vehicle by enabling wings to deform is designed. The characteristics of high speed, high flexibility, long range and the like of the flying wing type airplane are kept, and meanwhile, the airplane can have vertical take-off and landing and hovering functions like a rotary wing type airplane.
The technical solution of the utility model is as follows: the flying wing type airplane is taken as a prototype, the aspect ratio of the wings is increased, the wings are divided into three sections, the tail ends of the wings can be deformed and unfolded into propellers, the middle sections of the wings can be rotated to be vertical, a steering engine/pulling mechanism is arranged in the wings, the propellers at the nose of the airplane can be rotated to be vertical, the three-shaft propeller type unmanned aerial vehicle can be used for vertical take-off and landing. And after the unmanned aerial vehicle is lifted off, the unmanned aerial vehicle is changed back to the flying wing type unmanned aerial vehicle.
The utility model has the advantages that: the aircraft has the advantages of both flying wing type aircraft and rotary wing type aircraft, reduces the power consumption, has large carrying capacity and can use sufficient space. Have stronger equilibrium and operating stability, when unmanned aerial vehicle stall, can become gyroplane safety and compel to land, play the effect that the protection carried the thing.
Drawings
FIG. 1 shows the overall structure of the unmanned aerial vehicle;
FIG. 2 is a process diagram of the unmanned aerial vehicle wing of the present invention when the wing is transformed from a flight attitude to a take-off and landing attitude;
FIG. 3 is a view showing the wing take-off and landing attitude of the unmanned aerial vehicle;
FIG. 4 is a development view of the wing of the unmanned aerial vehicle of the present invention during taking off and landing;
FIG. 5 is a development view of the propeller blades of the present invention;
in the figure, a wing 1, a front propeller 2, an aileron 3, a wing outer section 4, a wing middle section 5, a wing inner section 6, a loop bar 7, a first hydraulic oil cylinder 8, a pulling mechanism 9, a fixed rod 10, a sleeve 11, a driving connecting rod 12, a pull rod 13, a driven connecting rod 14, a motor support 15, a motor 16, a side propeller 17, a leather sheath 18, a support sleeve 19, a front end 20, a rear end 21, a movable sleeve 22 and a second hydraulic oil cylinder 23 are shown.
Detailed Description
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.
In the present invention, unless otherwise expressly stated or limited, the terms "disposed," "mounted," "connected," and "fixed" are to be construed broadly, e.g., as meaning either a fixed connection or a removable connection; may be a mechanical connection; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
As shown in fig. 1-5, the utility model discloses a: a vertical take-off wing type unmanned aerial vehicle comprises a wing 1, a front propeller 2 and an aileron 3, wherein the aileron 3 is arranged at the rear part of the unmanned aerial vehicle, the left and right wing parts of the wing 1 respectively comprise an outer wing section 4, an intermediate wing section 5 and an inner wing section 6, the intermediate wing section 5 is hinged with the upper part of the inner wing section 6, a loop bar 7 is connected between the intermediate wing section 5 and the inner wing section 6, the outer wing section 4 is hinged with the lower part of the intermediate wing section 5, a first hydraulic oil cylinder 8 is connected between the outer wing section 4 and the inner wing section 6, a pulling mechanism 9 is fixed in the inner wing section 6, a fixed rod 10 is fixedly arranged in the inner wing section 6, a sleeve 11 is sleeved on the fixed rod 10, the pulling mechanism 9 is connected with a driving connecting rod 12, the driving connecting rod 12 is hinged with a pull rod 13, the pull rod 13 is hinged on a driven connecting rod 14, one, the other end is provided with motor support 15, fixed motor 16 on the motor support 15, motor 16's output shaft side screw 17, be provided with leather sheath 18 between wing middle section 5 and the wing inner segment 6, the paddle of side screw 17 is the retractable, preceding screw 2 is connected with the transform mechanism that verts, the transform mechanism that verts is used for driving preceding screw 2 and changes at horizontality and vertical state.
A support sleeve 19 is arranged in the middle section 5 of the wing, and the support sleeve 19 is sleeved on the driven connecting rod 14 and used for supporting the driven connecting rod 14.
The leather sheath 18 can protect the inside of the wing when the wing middle section 5 is in a vertical state.
The blade is provided with a front end 20, a rear end 21 and a moving sleeve 22, the moving sleeve 22 is arranged between the front end 20 and the rear end 21 and can slide between the front end 20 and the rear end 21, a second hydraulic oil cylinder 23 is connected to the front end 20 and the rear end 21 inside the blade, the rear end 21 is fixed on a propeller rotating shaft, and the moving sleeve 22 is provided with a plurality of parts.
One end of the loop bar 7 is hinged with the middle section 5 of the wing, and the other end is hinged with the inner section of the wing.
One end of a first hydraulic oil cylinder 8 is hinged with the outer wing section 4, the other end of the first hydraulic oil cylinder is hinged with the inner wing section 6, and the first hydraulic oil cylinder 8 is positioned below the wing 1.
The supporting sleeve 19 is fixed in the middle section of the wing, the driven connecting rod 14 can rotate in the supporting sleeve 19, the sleeve 11 can slide on the fixing rod 10, and the loop bar 7 is telescopic.
The flying and cruising postures are shown in figure 1, and the flying wing type airplane is high in speed, long in voyage and high in flexibility.
The cruise attitude is changed into a take-off and landing attitude shown in fig. 2, the middle section 5 of the wing is bent, the outer section 4 of the wing is opened, the internal steering engine/pulling mechanism 9 rotates clockwise to drive the driving connecting rod 12, the driving connecting rod 12 pulls the driven connecting rod 14, and meanwhile, the sleeve 11 is pulled out along with inertia, so that the driven connecting rod 14 is changed into a vertical state.
The taking-off and landing postures are shown in fig. 3, the wings are in a sectional type, the inner sections and the middle sections of the wings are connected through metal shafts on the upper surfaces of the wings, the lower surfaces of the wings are connected through special protective materials (leather sleeves), and the middle sections and the outer ends of the wings are connected through the metal shafts on the lower surfaces of the wings, so that the airplane is changed into a three-shaft propeller airplane, can take off and land stably, and has a hovering function.
When the taking-off and landing posture is changed into a flying posture, the side propellers shrink and are folded with the motor, the steering engine/pulling mechanism 9 drives the driving connecting rod 12 to rotate so that the wings turn back to be horizontal, the motor is horizontally arranged, the sleeve 11 retracts the motor, meanwhile, the outer sections 4 of the wings and the middle sections 5 of the wings are horizontally arranged, and the front propellers turn back to be in a horizontally arranged state and return to the flying posture.
The sleeve 8 can freely extend and retract on the rod, and the steering engine/pulling mechanism 9 can rotate to drive the main male connecting rod 12 to control the rotation of the driven connecting rod 14.
The airplane generated by the application combines the advantages of the morphing airplane and the flying wing type airplane, realizes the optimal lift force, maneuvering characteristics and drag reduction effect during high-speed and low-speed flight, and can effectively complete flight tasks, thereby improving the overall performance of the airplane.
The utility model aims at: a vertical take-off wing type unmanned aerial vehicle capable of realizing interconversion between a flying wing type unmanned aerial vehicle and a propeller type unmanned aerial vehicle by enabling wings to deform is designed. The characteristics of high speed, high flexibility, long range and the like of the flying wing type airplane are kept, and meanwhile, the airplane can have vertical take-off and landing and hovering functions like a rotary wing type airplane.
The technical solution of the utility model is as follows: the flying wing type airplane is taken as a prototype, the aspect ratio of the wings is increased, the wings are divided into three sections, the tail ends of the wings can be deformed and unfolded into propellers, the middle sections of the wings can be rotated to be vertical, a steering engine/pulling mechanism is arranged in the wings, the propellers at the nose of the airplane can be rotated to be vertical, the three-shaft propeller type unmanned aerial vehicle can be used for vertical take-off and landing. And after the unmanned aerial vehicle is lifted off, the unmanned aerial vehicle is changed back to the flying wing type unmanned aerial vehicle.
The utility model has the advantages that: the aircraft has the advantages of both flying wing type aircraft and rotary wing type aircraft, reduces the power consumption, has large carrying capacity and can use sufficient space. Have stronger equilibrium and operating stability, when unmanned aerial vehicle stall, can become gyroplane safety and compel to land, play the effect that the protection carried the thing.
Claims (7)
1. The utility model provides a but wing formula unmanned aerial vehicle that takes off perpendicularly, unmanned aerial vehicle includes wing (1), preceding screw (2) and aileron (3), aileron (3) set up at unmanned aerial vehicle's rear portion, its characterized in that: the wing comprises a wing (1) and a left wing part and a right wing part, wherein the wing (1) and the left wing part respectively comprise a wing outer section (4), a wing middle section (5) and a wing inner section (6), the wing middle section (5) is hinged with the upper part of the wing inner section (6), a loop bar (7) is connected between the wing middle section (5) and the wing inner section (6), the wing outer section (4) is hinged with the lower part of the wing middle section (5), a first hydraulic oil cylinder (8) is connected between the wing outer section (4) and the wing inner section (6), a pulling mechanism (9) is fixed in the wing inner section (6), a fixed rod (10) is fixedly arranged in the wing inner section (6), a sleeve (11) is sleeved on the fixed rod (10), the pulling mechanism (9) is connected with a driving connecting rod (12), the driving connecting rod (12) is hinged with a pull rod (13), the pull rod (13) is hinged on a driven connecting rod (14), and one end, the other end is provided with motor support (15), fixed motor (16) on motor support (15), output shaft side screw (17) of motor (16), be provided with leather sheath (18) between wing middle section (5) and wing inner segment (6), the paddle of side screw (17) is retractable, preceding screw (2) are connected with the transform mechanism that verts, the transform mechanism that verts is used for driving preceding screw (2) and alternate at horizontality and vertical state.
2. The vertical takeoff wing type unmanned aerial vehicle as claimed in claim 1, wherein: the wing middle section (5) is internally provided with a support sleeve (19), and the support sleeve (19) is sleeved on the driven connecting rod (14) and used for supporting the driven connecting rod (14).
3. The vertical takeoff wing type unmanned aerial vehicle as claimed in claim 2, wherein: the leather sheath (18) can play a role in protecting the interior of the wing when the middle wing section (5) is in a vertical state.
4. The vertical takeoff wing type unmanned aerial vehicle as claimed in claim 2, wherein: the paddle has front end (20), rear end (21) and removes cover (22), remove cover (22) and set up between front end (20) and rear end (21) to can slide between, the inside of paddle, be connected with second hydraulic cylinder (23) at front end (20) and rear end (21), on the fixed screw rotation axis of rear end (21), it is provided with a plurality ofly to remove cover (22).
5. The vertical takeoff wing type unmanned aerial vehicle as claimed in claim 2, wherein: one end of the loop bar (7) is hinged with the middle wing section (5), and the other end is hinged with the inner wing section (6).
6. The vertical takeoff wing type unmanned aerial vehicle as claimed in claim 2, wherein: one end of the first hydraulic oil cylinder (8) is hinged with the outer wing section (4), the other end of the first hydraulic oil cylinder is hinged with the inner wing section (6), and the first hydraulic oil cylinder (8) is positioned below the wing (1).
7. The vertical takeoff wing type unmanned aerial vehicle as claimed in claim 2, wherein: the supporting sleeve (19) is fixed in the middle section of the wing, the driven connecting rod (14) can rotate in the supporting sleeve (19), the sleeve (11) can slide on the fixing rod (10), and the loop bar (7) is telescopic.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920592559.6U CN210310854U (en) | 2019-04-28 | 2019-04-28 | Can hang wing formula unmanned aerial vehicle that takes off perpendicularly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920592559.6U CN210310854U (en) | 2019-04-28 | 2019-04-28 | Can hang wing formula unmanned aerial vehicle that takes off perpendicularly |
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| Publication Number | Publication Date |
|---|---|
| CN210310854U true CN210310854U (en) | 2020-04-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920592559.6U Expired - Fee Related CN210310854U (en) | 2019-04-28 | 2019-04-28 | Can hang wing formula unmanned aerial vehicle that takes off perpendicularly |
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| Country | Link |
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| CN (1) | CN210310854U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110104163A (en) * | 2019-04-28 | 2019-08-09 | 厦门大学 | One kind can hang down flying wing type unmanned plane |
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2019
- 2019-04-28 CN CN201920592559.6U patent/CN210310854U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110104163A (en) * | 2019-04-28 | 2019-08-09 | 厦门大学 | One kind can hang down flying wing type unmanned plane |
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200414 Termination date: 20210428 |