CN216636805U - Contraction type fixed wing unmanned aerial vehicle of laser guidance - Google Patents
Contraction type fixed wing unmanned aerial vehicle of laser guidance Download PDFInfo
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- CN216636805U CN216636805U CN202122595054.5U CN202122595054U CN216636805U CN 216636805 U CN216636805 U CN 216636805U CN 202122595054 U CN202122595054 U CN 202122595054U CN 216636805 U CN216636805 U CN 216636805U
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a laser-guided retractable fixed-wing unmanned aerial vehicle, which comprises: the device comprises a machine body, a control system and a control system, wherein the machine body comprises a front body and a rear body, the front body of the machine body is in a missile shape, and a guidance system is arranged in the front body of the machine body; the rear body of the machine body is in a cuboid shape, and a control system is arranged in the rear body of the machine body; the upper end of the front body of the fuselage is provided with a front rotor wing, and the front rotor wings are symmetrically distributed on the surface of the upper end of the front body of the fuselage; the lower end of the back body of the fuselage is provided with a back rotor, and the back rotors are symmetrically distributed at the lower end of the back body of the fuselage; the upper end of the front body of the machine body and the lower end of the rear body of the machine body are both provided with a transmission box; the retractable fixed wing unmanned aerial vehicle of laser guidance is through stretching and contracting the wing design, also can realize launching a plurality of unmanned aerial vehicles fast when can be convenient for concentrate on launching mechanism inside in a large number, improves wholly the retractable fixed wing unmanned aerial vehicle's of laser guidance combat the effect.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a laser-guided retractable fixed-wing unmanned aerial vehicle.
Background
The unmanned plane is called unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. Unmanned aerial vehicles are in fact a general term for unmanned aerial vehicles, and can be defined from a technical perspective as follows: unmanned helicopters, unmanned fixed wing aircraft, unmanned multi-rotor aircraft, unmanned airships, and unmanned paravane aircraft.
Most wings of the unmanned aerial vehicle in the prior art are fixed wings, so that the unmanned aerial vehicle is inconvenient to shrink, occupies a large space and volume, and is generally taken off by a single unmanned aerial vehicle; although a plurality of unmanned aerial vehicles can be simultaneously taken off through a set program, most of the unmanned aerial vehicles take off and land vertically, so that the taking-off speed is slow.
In view of the above problems in the background art, the present invention is directed to a laser guided retractable fixed wing drone.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a laser-guided retractable fixed-wing unmanned aerial vehicle, which aims to solve the problems in the background technology.
In order to achieve the purpose, the utility model provides the following technical scheme:
a laser-guided retractable fixed wing drone, the laser-guided retractable fixed wing drone comprising:
the device comprises a machine body, a control system and a control system, wherein the machine body comprises a front body and a rear body, the front body of the machine body is in a missile shape, and a guidance system is arranged in the front body of the machine body; the rear body of the machine body is in a cuboid shape, and a control system is arranged in the rear body of the machine body;
the upper end of the front body of the airframe is provided with front rotary wings which are symmetrically distributed on the surface of the upper end of the front body of the airframe; the lower end of the back body of the airframe is provided with back rotor wings which are symmetrically distributed at the lower end of the back body of the airframe; the upper end of the front body of the machine body and the lower end of the rear body of the machine body are both provided with a transmission box;
the upper side surface of the tail end of the rear body of the machine body is provided with a balance frame, the left side and the right side of the lower end of the balance frame are fixedly arranged at the upper end of the rear body of the machine body through connecting shafts, and the balance frame is in a door shape; the rear tail end of the machine body is provided with a paddle, the paddle is driven by a motor arranged in the machine body, and the paddle is in a double-blade shape.
As a further scheme of the utility model: a driving wheel, a driving wheel and a driving wheel are arranged in the transmission box, a driving shaft is arranged in the driving wheel, and one side of the driving wheel is meshed with the driving wheel; the number of the driving wheels is two, the two driving wheels are distributed on two sides in the transmission case, one end of one driving wheel is meshed with one side of the driving wheel, and one side of the other driving wheel is meshed with one side of the driving wheel; the middle of the two driving wheels is provided with a rotating shaft which passes through the transmission case and then is connected with one end of the rear rotor wing.
Compared with the prior art, the utility model has the beneficial effects that:
the retractable fixed wing unmanned aerial vehicle of laser guidance is through stretching and contracting the wing design, also can realize launching a large amount of unmanned aerial vehicles fast when can be convenient for concentrate on emission mechanism inside in a large number, improves wholly the retractable fixed wing unmanned aerial vehicle's of laser guidance combat the effect.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention.
Fig. 1 is a schematic structural view of a laser-guided retractable fixed-wing drone according to an embodiment of the present invention.
Fig. 2 is a schematic diagram of a rear rotor driving principle of a laser-guided retractable fixed-wing drone according to an embodiment of the present invention.
Fig. 3 is a top view of a laser guided retractable fixed wing drone according to an embodiment of the present invention.
In the figure: 1-body, 2-front rotor, 3-balancing stand, 4-connecting shaft, 5-paddle, 6-rear rotor, 7-transmission box, 8-driving wheel, 9-driving wheel, 10-driving wheel and 11-driving shaft.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects to be solved by the present invention more clearly apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the utility model and are not intended to limit the utility model.
Examples
Referring to fig. 1 and 3, in an embodiment of the present invention, a laser-guided retractable fixed-wing drone includes:
the unmanned aerial vehicle comprises a body 1, wherein the body 1 comprises a front body and a rear body, the front body of the body 1 is in a missile shape, and the front body of the missile-shaped body 1 has a better fluid shape and conforms to the dynamics of the unmanned aerial vehicle during flying; a guidance system is arranged in the front body of the machine body 1, and is not further elaborated as the guidance system is the prior art; the rear body of the machine body 1 is in a cuboid shape, a control system is arranged in the rear body of the machine body 1, and the control system is in the prior art and is not further explained herein;
the upper end of the front body of the fuselage 1 is provided with a front rotor 2, and the front rotors 2 are symmetrically distributed on the surface of the upper end of the front body of the fuselage 1; the lower end of the back body of the fuselage 1 is provided with a back rotor wing 6, and the back rotor wings 6 are symmetrically distributed at the lower end of the back body of the fuselage 1; the upper end of the front body of the machine body 1 and the lower end of the rear body of the machine body 1 are both provided with a transmission case 7, and the arranged rear rotor wing 6 and the front rotor wing 2 can be controlled to retract and extend through the arranged transmission cases 7;
the upper side surface of the tail end of the back of the machine body 1 is provided with a balance frame 3, the left side and the right side of the lower end of the balance frame 3 are fixedly arranged at the upper end of the back of the machine body 1 through connecting shafts 4, the balance frame 3 is in a door shape, and the balance frame 3 is used for balancing the stability of the laser-guided retractable fixed-wing unmanned aerial vehicle during flying; the tail end of the back of the machine body 1 is provided with a blade 5, the blade 5 is driven by a motor arranged in the machine body 1, the blade 5 is in a double-blade shape, and the blade 5 rotates to generate power for the whole laser-guided retractable fixed-wing unmanned aerial vehicle during flying;
when the laser-guided retractable fixed-wing unmanned aerial vehicle is launched, a front rotor 2 and a rear rotor 6 of the unmanned aerial vehicle are in a retracted state, and the whole laser-guided retractable fixed-wing unmanned aerial vehicle is launched by a launching mechanism to fly at a high speed for a certain distance; starting a motor arranged in the fuselage 1 to drive the blades 5 to rotate at a high speed to generate thrust, and simultaneously unfolding the arranged rear rotor 6 and the front rotor 2 through the arranged transmission case to provide the lift force of the whole laser-guided retractable fixed-wing unmanned aerial vehicle so as to ensure that the unmanned aerial vehicle keeps continuously flying fast; unmanned aerial vehicle can be so that whole through the design of this kind of telescopic wing the collapsible fixed wing unmanned aerial vehicle of laser guidance is convenient for concentrate on inside the launching mechanism, can realize launching a large amount of a plurality of unmanned aerial vehicles fast, improves military operation effect.
Referring to fig. 2, specifically, a driving wheel 8, a driving wheel 9 and a driving wheel 10 are arranged inside the transmission box 7, a driving shaft 11 is arranged inside the driving wheel 10, and one side of the driving wheel 10 is engaged with the driving wheel 9; the number of the driving wheels 8 is two, the two driving wheels 8 are distributed on two sides in the transmission box 7, one end of one driving wheel 8 is meshed with one side of the transmission wheel 9, and one side of the other driving wheel 8 is meshed with one side of the driving wheel 10; a rotating shaft is arranged between the two driving wheels 8, penetrates through the transmission case 7 and then is connected with one end of the rear rotor wing 6;
when the rear rotor wings 6 on the outer side of the fuselage 1 need to be retracted and extended, the driving shaft 11 is started, the driving shaft 11 drives the driving wheel 10 to rotate, and because the outer side of the driving wheel 10 is simultaneously meshed with one side of the driving wheel 8 and the outer side of the driving wheel 9, the driving wheel 10 can drive the driving wheel 8 on the right side in the transmission box 7 and the driving wheel 9 to simultaneously rotate when rotating, one end of the driving wheel 9 is meshed with the driving wheel 8 on the left side in the transmission box 7, and finally the two rear rotor wings 6 are pushed to move relatively, so that the extension and retraction of the rear rotor wings 6 arranged at the lower end of the fuselage 1 are realized;
the working principle of the embodiment of the utility model is as follows:
the retractable fixed wing unmanned aerial vehicle of laser guidance through stretch and shrink the wing design, can be convenient for concentrate on in a large number inside launching mechanism, can realize launching a large amount of a plurality of unmanned aerial vehicles fast, improve military operation effect.
In the description of the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the utility model, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (2)
1. A laser-guided retractable fixed wing drone, comprising: the airplane body (1), the airplane body (1) comprises a front body and a rear body; the method is characterized in that:
the front body of the machine body (1) is in a missile shape, and a guidance system is arranged in the front body of the machine body (1); the rear body of the machine body (1) is in a cuboid shape, and a control system is arranged in the rear body of the machine body (1);
the upper end of the front body of the fuselage (1) is provided with a front rotor (2), and the front rotors (2) are symmetrically distributed on the surface of the upper end of the front body of the fuselage (1); the lower end of the back body of the airframe (1) is provided with a back rotor (6), and the back rotor (6) is symmetrically distributed at the lower end of the back body of the airframe (1); the upper end of the front body of the machine body (1) and the lower end of the rear body of the machine body (1) are both provided with a transmission box (7);
the upper side surface of the tail end of the rear body of the machine body (1) is provided with a balance frame (3), the left side and the right side of the lower end of the balance frame (3) are fixedly arranged at the upper end of the rear body of the machine body (1) through connecting shafts (4), and the balance frame (3) is in a door shape; the rear tail end of the machine body (1) is provided with the paddle (5), the paddle (5) is driven by a motor arranged inside the machine body (1), and the paddle (5) is in a double-blade shape.
2. The laser-guided retractable fixed wing drone of claim 1, characterized in that: a driving wheel (8), a driving wheel (9) and a driving wheel (10) are arranged in the transmission box (7), a driving shaft (11) is arranged in the driving wheel (10), and one side of the driving wheel (10) is meshed with the driving wheel (9); the number of the driving wheels (8) is two, the two driving wheels (8) are distributed on two sides in the transmission case (7), one end of one driving wheel (8) is meshed with one side of the transmission wheel (9), and one side of the other driving wheel (8) is meshed with one side of the driving wheel (10); the middle of the two driving wheels (8) is provided with a rotating shaft which passes through the transmission case (7) and then is connected with one end of the rear rotor wing (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122595054.5U CN216636805U (en) | 2021-10-27 | 2021-10-27 | Contraction type fixed wing unmanned aerial vehicle of laser guidance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122595054.5U CN216636805U (en) | 2021-10-27 | 2021-10-27 | Contraction type fixed wing unmanned aerial vehicle of laser guidance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216636805U true CN216636805U (en) | 2022-05-31 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122595054.5U Active CN216636805U (en) | 2021-10-27 | 2021-10-27 | Contraction type fixed wing unmanned aerial vehicle of laser guidance |
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| Country | Link |
|---|---|
| CN (1) | CN216636805U (en) |
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2021
- 2021-10-27 CN CN202122595054.5U patent/CN216636805U/en active Active
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