CN214690166U - Fixed wing unmanned aerial vehicle focus adjusting device can take off and land perpendicularly - Google Patents
Fixed wing unmanned aerial vehicle focus adjusting device can take off and land perpendicularly Download PDFInfo
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- CN214690166U CN214690166U CN202120440500.2U CN202120440500U CN214690166U CN 214690166 U CN214690166 U CN 214690166U CN 202120440500 U CN202120440500 U CN 202120440500U CN 214690166 U CN214690166 U CN 214690166U
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- fuselage
- unmanned aerial
- adjusting device
- aerial vehicle
- rotor subassembly
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Abstract
The utility model discloses a fixed wing unmanned aerial vehicle focus adjusting device can take off and land perpendicularly, including wing, fuselage and setting up flight controller and level sensor in the fuselage, flight controller with level sensor connects, be provided with the rotor subassembly on the fuselage, rotor subassembly with flight controller electric connection, the rotor subassembly includes the detachable connecting rod, the connecting rod both ends are provided with detachable tilting mechanism, the fuselage lower extreme is provided with the spout base, be provided with the guide rail on the spout base, be provided with the slider on the guide rail, be provided with the installation that supplies the connecting rod to pass on the slider; the utility model discloses an adjustment rotor subassembly's position forms the new arm of force and reaches the purpose of adjusting focus, has simple structure, simple to operate, and the practicality is high, advantages such as low in manufacturing cost.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field especially relates to a but fixed wing unmanned aerial vehicle focus adjusting device of VTOL.
Background
Unmanned aerial vehicles are widely applied to various fields of life and production at present, but multi-rotor aircrafts can only perform some 'relaxed' tasks such as detection and shooting, and cannot bear larger task loads; some heavy load's equipment can only be born by fixed wing unmanned aerial vehicle, and the quality of load equipment is big or small different under many conditions, and load equipment has the requirement of placing in special position, or load task quality flight in-process is variable, and this all can change unmanned aerial vehicle's focus position, influences the unmanned aerial vehicle performance, reduces stability, causes the accident.
The position that current fixed wing unmanned aerial vehicle changes the task load through the slider to this reaches the purpose of adjusting the focus, and this kind of focus adjusting device limitation is big, operates inconveniently, adjusts heavily, and the practicality is low.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to solve the technical problem who exists among the prior art, provide a but VTOL fixed wing unmanned aerial vehicle focus adjusting device.
In order to achieve the above purpose, the utility model provides a technical scheme is: the utility model provides a but fixed wing unmanned aerial vehicle focus adjusting device of VTOL, is in including wing, fuselage and setting flight controller and level sensor in the fuselage, flight controller with level sensor connects, be provided with the rotor subassembly on the fuselage, the rotor subassembly with flight controller electric connection, the rotor subassembly includes the detachable connecting rod, the connecting rod both ends are provided with detachable tilting mechanism, the fuselage lower extreme is provided with the spout base, be provided with the guide rail on the spout base, be provided with the slider on the guide rail, be provided with the confession on the slider the mounting hole that the connecting rod passed.
Preferably, the tilting mechanism comprises a steering engine, a mounting seat is arranged on the steering engine, a platen is arranged on the mounting seat, a motor is arranged on the platen, and blades are arranged on the motor.
Preferably, the body is further provided with a loading bin for carrying a load.
Preferably, the lower side of the fuselage is also provided with an undercarriage, and the fuselage, the wings, the undercarriage and the rotor wing assembly are all made of high-strength metal pipes.
The utility model discloses beneficial effect: the utility model discloses an adjustment rotor subassembly's position forms the new arm of force and reaches the purpose of adjusting focus, has simple structure, simple to operate, and the practicality is high, advantages such as low in manufacturing cost.
Drawings
The accompanying drawings, which are described herein, serve to provide a further understanding of the invention and constitute a part of this specification, and the exemplary embodiments and descriptions thereof are provided for explaining the invention without unduly limiting it.
FIG. 1 is a schematic diagram of the overall structure of the preferred embodiment of the present invention;
FIG. 2 is a top view of the preferred embodiment of the center of gravity adjustment apparatus of the present invention;
FIG. 3 is a side view of the preferred embodiment of the center of gravity adjustment apparatus of the present invention;
fig. 4 is a schematic view of a tilting mechanism according to a preferred embodiment of the present invention.
The attached drawings are marked as follows:
the aircraft comprises a 1-flight controller 2-wings 3-a fuselage 4-a rotor assembly 5-a chute base 6-a guide rail 7-a connecting rod 8-an undercarriage 9-a level sensor 10-a sliding block 11-a steering engine 12-a tilting mechanism 13-a mounting hole 14-a mounting seat 15-a screw 16-a platen 17-a motor 18-a blade 19-a loading bin.
Detailed Description
This section will describe in detail the embodiments of the present invention, preferred embodiments of the present invention are shown in the attached drawings, which are used to supplement the description of the text part of the specification with figures, so that one can intuitively and vividly understand each technical feature and the whole technical solution of the present invention, but they cannot be understood as the limitation of the protection scope of the present invention.
In the description of the present invention, it should be understood that the orientation or positional relationship indicated with respect to the orientation description, such as up, down, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
In the description of the present invention, a plurality of means are one or more, a plurality of means are two or more, and the terms greater than, less than, exceeding, etc. are understood as not including the number, and the terms greater than, less than, within, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.
In the description of the present invention, unless there is an explicit limitation, the words such as setting, installation, connection, etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above words in combination with the specific contents of the technical solution.
Referring to fig. 1-4, the preferred embodiment of the present invention is a gravity center adjusting device for a vertical take-off and landing fixed-wing unmanned aerial vehicle, comprising a wing 2, a body 3, and a flight controller 1 and a level sensor 9 disposed in the body 3, wherein the flight controller 1 is connected to the level sensor 9, the body 3 is provided with a rotor assembly 4, the rotor assembly 4 is electrically connected to the flight controller 1, the rotor assembly 4 comprises a detachable connecting rod 7, two ends of the connecting rod 7 are provided with detachable tilting mechanisms 12, the lower end of the body 3 is provided with a chute base 5, the chute base 5 is fixedly connected to the body 3 through screws, the chute base 5 is provided with a guide rail 6, the guide rail 6 is fixedly connected to the chute base 5, the guide rail 6 is provided with a slider 10, the guide rail 6 is provided with two sliders 10, the sliding block 10 can slide freely on the guide rail 6, the sliding block 10 is provided with a mounting hole 13 for the connecting rod 7 to pass through, and the connecting rod 7 is fixedly connected in the mounting hole 13 through a bolt.
The utility model can calculate the optimal proportioning position according to the flight controller 1 to control the relative position of the rotor wing assembly 4, so as to adjust the gravity center by changing the length of the force arm, so that the rotor wing assembly 4 provides lift force for the unmanned aerial vehicle during taking off, and provides a small part of power for the unmanned aerial vehicle after taking off and being stable; specifically, when the size of the unmanned aerial vehicle is larger, the length adjustment range of the force arm is also enlarged, the adjustment effect is more obvious, after the unmanned aerial vehicle flies to a certain height, when the gravity center changes due to different loading equipment and external conditions, the horizontal sensor 9 can sense the change of the gravity center, so that physical signals are converted into digital signals and transmitted to the flight controller 1, an instruction is sent to the power source to provide power to adjust the transmission teeth on the guide rail 6 to move, and the position of the sliding block 10 on the guide rail 6 is adjusted through the transmission teeth to enable the unmanned aerial vehicle to return to a stable state again; the utility model discloses an adjustment rotor subassembly 4's position forms the new arm of force and reaches the purpose of adjusting focus, has simple structure, simple to operate, and the practicality is high, advantages such as low in manufacturing cost.
As a preferred embodiment of the present invention, it may also have the following additional technical features:
in this embodiment, the tilting mechanism 12 includes a steering engine 11, an installation base 14 is arranged on the steering engine 11, a platen 16 is arranged on the installation base 14, a motor 17 is arranged on the platen 16, a paddle 18 is arranged on the motor 17, preferably, when the paddle 18 is perpendicular to the ground, the position is defined as a first position, and when the paddle 18 is parallel to the ground, the position is defined as a second position, when the unmanned aerial vehicle is in a takeoff stage, the tilting mechanism 12 controls the paddle 18 to be in the first position, that is, the tilting mechanism 12 controls the motor 17 to rotate, the motor 17 drives the paddle 18 to rotate, so as to provide an upward lift force for the unmanned aerial vehicle, and in a flat flight stage, the tilting mechanism 12 controls the paddle 18 to be in the second position, so as to provide a small amount of power and a flat flight power for the unmanned aerial vehicle; can make unmanned aerial vehicle's mobility can be higher, more nimble, operating performance is better.
In this embodiment, still be provided with the loading storehouse 19 that is used for carrying on load on the fuselage 3, loading storehouse 19 can carry the load of different weight, and unmanned aerial vehicle can carry out more nimble chooseing for use to the weight and the density of detachable connecting rod 7 through the load that carries on to it is more convenient when making unmanned aerial vehicle adjustment rotor subassembly 4's focus position.
In this embodiment, 3 downside of fuselage still is provided with undercarriage 8, the material of fuselage 3, wing 2, undercarriage 8 and rotor subassembly 4 is high strength metal tubular product for in order to satisfy the requirement of unmanned aerial vehicle to aspects such as the intensity of material, rigidity, guarantee unmanned aerial vehicle's stability.
The above additional technical features can be freely combined and used in superposition by those skilled in the art without conflict.
The above is only the preferred embodiment of the present invention, as long as the technical solution of the purpose of the present invention is realized by the substantially same means, all belong to the protection scope of the present invention.
Claims (4)
1. The utility model provides a but fixed wing unmanned aerial vehicle focus adjusting device of VTOL, is in including wing (2), fuselage (3) and setting flight controller (1) and level sensor (9) in fuselage (3), flight controller (1) with level sensor (9) are connected, its characterized in that: be provided with rotor subassembly (4) on fuselage (3), rotor subassembly (4) with flight controller (1) electric connection, rotor subassembly (4) are including detachable connecting rod (7), connecting rod (7) both ends are provided with detachable tilting mechanism (12), fuselage (3) lower extreme is provided with spout base (5), be provided with guide rail (6) on spout base (5), be provided with slider (10) on guide rail (6), be provided with the confession on slider (10) mounting hole (13) that connecting rod (7) passed.
2. The device of claim 1, wherein the gravity center adjusting device comprises: the tilting mechanism (12) comprises a steering engine (11), a mounting seat (14) is arranged on the steering engine (11), a table plate (16) is arranged on the mounting seat (14), a motor (17) is arranged on the table plate (16), and blades (18) are arranged on the motor (17).
3. The device of claim 1, wherein the gravity center adjusting device comprises: the machine body (3) is also provided with a loading bin (19) for carrying a load.
4. The device of claim 1, wherein the gravity center adjusting device comprises: fuselage (3) downside still is provided with undercarriage (8), the material of fuselage (3), wing (2), undercarriage (8) and rotor subassembly (4) is high strength metal tubular product.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120440500.2U CN214690166U (en) | 2021-03-01 | 2021-03-01 | Fixed wing unmanned aerial vehicle focus adjusting device can take off and land perpendicularly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120440500.2U CN214690166U (en) | 2021-03-01 | 2021-03-01 | Fixed wing unmanned aerial vehicle focus adjusting device can take off and land perpendicularly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214690166U true CN214690166U (en) | 2021-11-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120440500.2U Expired - Fee Related CN214690166U (en) | 2021-03-01 | 2021-03-01 | Fixed wing unmanned aerial vehicle focus adjusting device can take off and land perpendicularly |
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| CN (1) | CN214690166U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115503943A (en) * | 2022-08-30 | 2022-12-23 | 南京壮大智能科技研究院有限公司 | Working method of anti-crash rotor guide rail device of tandem type double-rotor unmanned aerial vehicle |
| WO2024045724A1 (en) * | 2022-08-30 | 2024-03-07 | 南京壮大智能科技研究院有限公司 | Anti-crash rotor wing guide rail device for tandem dual-rotor wing unmanned aerial vehicle |
-
2021
- 2021-03-01 CN CN202120440500.2U patent/CN214690166U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115503943A (en) * | 2022-08-30 | 2022-12-23 | 南京壮大智能科技研究院有限公司 | Working method of anti-crash rotor guide rail device of tandem type double-rotor unmanned aerial vehicle |
| WO2024045724A1 (en) * | 2022-08-30 | 2024-03-07 | 南京壮大智能科技研究院有限公司 | Anti-crash rotor wing guide rail device for tandem dual-rotor wing unmanned aerial vehicle |
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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: 20211112 |