CN220701361U - Vertical take-off and landing type circulating military unmanned aerial vehicle - Google Patents
Vertical take-off and landing type circulating military unmanned aerial vehicle Download PDFInfo
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- CN220701361U CN220701361U CN202322489639.8U CN202322489639U CN220701361U CN 220701361 U CN220701361 U CN 220701361U CN 202322489639 U CN202322489639 U CN 202322489639U CN 220701361 U CN220701361 U CN 220701361U
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Abstract
The utility model belongs to the technical field of military unmanned aerial vehicles, and particularly relates to a vertical take-off and landing type circulating military unmanned aerial vehicle, which comprises a military unmanned aerial vehicle and a vertical lifting mechanism, wherein the military unmanned aerial vehicle comprises a machine body, two brackets, a propelling blade and a landing gear; the two brackets are respectively and fixedly arranged on the front side and the rear side of the machine body, the propelling blade bearing is arranged on the right side of the machine body, a driving mechanism is arranged in the machine body, and the propelling blade is fixedly connected with the output end of the driving mechanism; the landing gear is fixedly arranged below the machine body; the vertical lifting mechanism comprises a lifting part and a detaching part, wherein the lifting part comprises a spiral blade, a motor, a magnet and a magnetic block; the inside of support is the cavity form, and two notches have been seted up to the top, the motor is embedded in notch inside, magnet fixed mounting is in the bottom both sides of motor, and the device has solved the structure of the vertical lift part of the present unable quick dismantlement military unmanned aerial vehicle to just trade the problem.
Description
Technical Field
The utility model belongs to the technical field of military unmanned aerial vehicles, and particularly relates to a vertical take-off and landing type circulating military unmanned aerial vehicle.
Background
The military drone is an unmanned aircraft that is controlled and maneuvered by a remote control device or a self-contained program. According to the control mode, the method is mainly divided into three types of radio remote control, automatic program control and comprehensive control.
The vertical lifting part of the military unmanned aerial vehicle cannot be detached, so that the military unmanned aerial vehicle cannot be replaced and maintained when damaged, and the using effect of the military unmanned aerial vehicle is affected. This phenomenon is a problem to be solved by those skilled in the art.
Disclosure of Invention
The utility model aims to provide a vertical lifting type circulating military unmanned aerial vehicle so as to solve the problems in the background technology.
In order to solve the technical problems, the utility model provides the following technical scheme: the vertical take-off and landing type circulating military unmanned aerial vehicle comprises a military unmanned aerial vehicle and a vertical lifting mechanism, wherein the military unmanned aerial vehicle comprises a machine body, two brackets, a propelling blade and a landing gear;
the two brackets are respectively and fixedly arranged on the front side and the rear side of the machine body, the propelling blade bearing is arranged on the right side of the machine body, a driving mechanism is arranged in the machine body, and the propelling blade is fixedly connected with the output end of the driving mechanism;
the landing gear is fixedly arranged below the machine body;
the vertical lifting mechanism comprises a lifting part and a detaching part.
The utility model further discloses that the lifting part comprises a spiral blade, a motor, a magnet and a magnetic block;
the inside of the bracket is hollow, two notches are formed in the upper part of the bracket, the motor is embedded in the notches, the magnets are fixedly arranged on two sides of the bottom end of the motor, and the magnetic blocks are fixedly arranged on the inner wall of the bracket and are mutually attached to the magnets;
the spiral blade is fixedly connected with the output end of the motor.
The utility model further discloses that the dismounting part comprises a pressing block, a balance plate, a top block and a sleeve;
the upper middle of the bracket is provided with a through hole, the pressing block is in sliding connection with the inner wall of the through hole, the balance plate is in bearing connection with the bottom of the inner wall of the bracket, and the inner end of the balance plate is fixedly connected with the bottom of the pressing block;
the sleeve is fixedly arranged at the bottom of the inner wall of the bracket and is positioned right below the motor, and the top block is in sliding connection with the inner wall of the sleeve;
the bottom of the top block is fixed with the outer end of the balance plate.
The utility model further discloses that the bottom of the pressing block is connected with the bottom spring of the inner wall of the bracket.
Compared with the prior art, the utility model has the following beneficial effects: according to the utility model, an operator drives the military unmanned aerial vehicle to run, the motor is started to drive the spiral blade to rotate at a high speed to generate downward air flow, so that the military unmanned aerial vehicle is driven to ascend, the landing gear is separated from contact with the ground, the magnet and the magnetic block generate magnetic attraction force which attracts each other, the motor is firmly embedded in the bracket to prevent the motor from falling off from the bracket, and then the driving mechanism drives the propulsion blade to rotate at a high speed, so that the military unmanned aerial vehicle flies back and forth and left and right.
Drawings
The accompanying drawings are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate the utility model and together with the embodiments of the utility model, serve to explain the utility model. In the drawings:
FIG. 1 is a schematic view of the overall structure of the present utility model;
FIG. 2 is a schematic view of the motor and screw blade of the present utility model disassembled;
FIG. 3 is a schematic plan view of the internal structure of the bracket of the present utility model;
FIG. 4 is a schematic plan view of the lifting and lowering portions of the present utility model;
in the figure: 1. a body; 2. a bracket; 3. propelling the leaves; 4. landing gear; 5. spiral leaves; 6. a motor; 7. a magnet; 8. a magnetic block; 9. pressing the blocks; 10. a balance plate; 11. a top block; 12. a sleeve.
Detailed Description
The technical scheme of the present utility model is further described in non-limiting detail below with reference to the preferred embodiments and the accompanying drawings. It will be apparent that the described embodiments are only some, but not all, embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Referring to fig. 1-4, the present utility model provides the following technical solutions: the vertical take-off and landing type circulating military unmanned aerial vehicle comprises a military unmanned aerial vehicle and a vertical lifting mechanism, wherein the military unmanned aerial vehicle comprises a machine body 1, two brackets 2, a propelling blade 3 and a landing gear 4;
the two brackets 2 are respectively and fixedly arranged on the front side and the rear side of the machine body 1, the propelling blade 3 is arranged on the right side of the machine body 1 in a bearing way, a driving mechanism is arranged in the machine body 1, and the propelling blade 3 is fixedly connected with the output end of the driving mechanism;
the landing gear 4 is fixedly arranged below the machine body 1;
the vertical lifting mechanism comprises a lifting part and a detaching part.
The lifting part comprises a spiral blade 5, a motor 6, a magnet 7 and a magnetic block 8;
the inside of the bracket 2 is hollow, two notches are formed in the upper part of the bracket, the motor 6 is embedded in the notches, the magnet 7 is fixedly arranged on two sides of the bottom end of the motor 6, and the magnet 8 is fixedly arranged on the inner wall of the bracket 2 and is mutually attached to the magnet 7;
the spiral blade 5 is fixedly connected with the output end of the motor 6;
operating personnel drive for military use unmanned aerial vehicle operation, motor 6 starts, drive spiral leaf 5 high-speed rotation, produce decurrent air current, thereby drive for military use unmanned aerial vehicle and rise, undercarriage 4 breaks away from the contact with ground, magnet 7 and magnet 8 produce the magnetic attraction of mutual attraction, make motor 6 firmly imbed in support 2, prevent motor 6 and support 2 to drop, afterwards actuating mechanism drives and impels leaf 3 high-speed rotation, make for military use unmanned aerial vehicle fly around, through setting up magnet 7 and magnet 8, can pull down motor 6 when needs change motor 6, and can pull down spiral leaf 5, easy dismounting is swift.
The disassembly part comprises a pressing block 9, a balance plate 10, a top block 11 and a sleeve 12;
a through hole is formed in the middle upper part of the bracket 2, the pressing block 9 is in sliding connection with the inner wall of the through hole, the balance plate 10 is in bearing connection with the bottom of the inner wall of the bracket 2, and the inner end of the balance plate 10 is fixedly connected with the bottom of the pressing block 9;
the sleeve 12 is fixedly arranged at the bottom of the inner wall of the bracket 2 and is positioned right below the motor 6, and the top block 11 is in sliding connection with the inner wall of the sleeve 12;
the bottom of the top block 11 is fixed with the outer end of the balance plate 10.
The bottom of the pressing block 9 is connected with the bottom spring of the inner wall of the bracket 2;
through the steps, when the motor 6 is disassembled, an operator presses the pressing block 9, the pressing block 9 is stressed to press the balance plate 10 to rotate around the axis, meanwhile, the spring is stressed to deform, then the outer end of the balance plate 10 is lifted upwards, the top block 11 is driven to slide upwards along the inner wall of the sleeve 12, the upper end of the top block 11 is contacted with the lower surface of the motor 6, the motor 6 is extruded, the motor 6 is ejected out of the notch, and therefore the motor 6 is convenient to replace quickly, and the disassembly efficiency is faster.
In the description of the present utility model, it should be understood that the directions or positional relationships indicated by the terms "upper", "lower", "front", "rear", "left", "right", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present utility model, and do not indicate or imply that the apparatus or elements 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 utility model.
Finally, it should be pointed out that: the above embodiments are only for illustrating the technical solution of the present utility model, and are not limiting. Although the utility model has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may be modified or some technical features may be equivalently replaced, and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present utility model.
Claims (4)
1. The utility model provides a take off and land formula circulation perpendicularly and use military unmanned aerial vehicle, includes for military use unmanned aerial vehicle and vertical lifting mechanism, its characterized in that: the military unmanned aerial vehicle comprises a machine body (1), two brackets (2), a propelling blade (3) and a landing gear (4);
the two brackets (2) are respectively and fixedly arranged on the front side and the rear side of the machine body (1), the propelling blade (3) is arranged on the right side of the machine body (1) in a bearing manner, a driving mechanism is arranged in the machine body (1), and the propelling blade (3) is fixedly connected with the output end of the driving mechanism;
the landing gear (4) is fixedly arranged below the machine body (1);
the vertical lifting mechanism comprises a lifting part and a detaching part.
2. The vertical lift circulation military drone of claim 1, wherein: the lifting part comprises a spiral blade (5), a motor (6), a magnet (7) and a magnetic block (8);
the inside of the bracket (2) is hollow, two notches are formed in the upper part of the bracket, the motor (6) is embedded into the notches, the magnet (7) is fixedly arranged on two sides of the bottom end of the motor (6), and the magnet block (8) is fixedly arranged on the inner wall of the bracket (2) and is mutually attached to the magnet (7);
the spiral blade (5) is fixedly connected with the output end of the motor (6).
3. The vertical lift circulation military drone of claim 2, wherein: the disassembly part comprises a pressing block (9), a balance plate (10), a top block (11) and a sleeve (12);
a through hole is formed in the middle upper part of the support (2), the pressing block (9) is in sliding connection with the inner wall of the through hole, the balance plate (10) is connected with the bottom bearing of the inner wall of the support (2), and the inner end of the balance plate (10) is fixedly connected with the bottom of the pressing block (9);
the sleeve (12) is fixedly arranged at the bottom of the inner wall of the bracket (2) and is positioned right below the motor (6), and the ejector block (11) is in sliding connection with the inner wall of the sleeve (12);
the bottom of the top block (11) is fixed with the outer end of the balance plate (10).
4. The vertical lift circulation military drone of claim 3, wherein: the bottom of the pressing block (9) is connected with the bottom spring of the inner wall of the bracket (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322489639.8U CN220701361U (en) | 2023-09-14 | 2023-09-14 | Vertical take-off and landing type circulating military unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322489639.8U CN220701361U (en) | 2023-09-14 | 2023-09-14 | Vertical take-off and landing type circulating military unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220701361U true CN220701361U (en) | 2024-04-02 |
Family
ID=90450015
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322489639.8U Active CN220701361U (en) | 2023-09-14 | 2023-09-14 | Vertical take-off and landing type circulating military unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220701361U (en) |
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2023
- 2023-09-14 CN CN202322489639.8U patent/CN220701361U/en active Active
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