CN213649899U - Collapsible VTOL unmanned aerial vehicle - Google Patents
Collapsible VTOL unmanned aerial vehicle Download PDFInfo
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- CN213649899U CN213649899U CN202021217423.6U CN202021217423U CN213649899U CN 213649899 U CN213649899 U CN 213649899U CN 202021217423 U CN202021217423 U CN 202021217423U CN 213649899 U CN213649899 U CN 213649899U
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 17
- 210000001015 abdomen Anatomy 0.000 claims description 3
- 238000005096 rolling process Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 abstract description 5
- 230000008901 benefit Effects 0.000 description 5
- 150000001875 compounds Chemical class 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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Abstract
The utility model relates to a general aviation field, concretely relates to collapsible VTOL unmanned aerial vehicle. Comprises a fuselage, an outer wing of the wing, an empennage, an inner wing of the wing, a stay bar folding piece, an empennage quick-dismantling piece, a rotor wing power device and a propulsion power device. The utility model discloses a vaulting pole passes through the vaulting pole folded piece and divide into the triplex with the vaulting pole, and the vaulting pole passes through the vaulting pole folded piece and connects well vaulting pole around, and well vaulting pole and wing inner wing integrated into one piece around, the vaulting pole can be to wing inner wing direction folding, and complete machine vanning space demand is less, and the installation is more convenient. Meanwhile, the inner wing of the wing is quickly connected with the fuselage in a quick splicing mode, the outer wing of the wing is quickly connected with the inner wing of the wing in a quick splicing mode, and the tail wing is quickly connected with the support rod through the tail wing quick-detaching piece, so that the dismounting and the mounting can be quickly finished.
Description
Technical Field
The utility model relates to a general aviation field, concretely relates to collapsible VTOL unmanned aerial vehicle.
Background
Science and technology is constantly advancing, unmanned aerial vehicle popularizes gradually, take photo by plane, the survey and drawing, patrol, trades such as transportation all have unmanned aerial vehicle's shadow to appear, compare many rotors and fixed wing unmanned aerial vehicle, compound wing unmanned aerial vehicle advantage is more, the advantage of fixed wing and many rotors has been taken into account, can cruise fast, can hover in the air again in VTOL, but partial compound wing unmanned aerial vehicle vanning space is great, the installation needs use tools, it is not very convenient, the installation time is also longer, it is not too friendly to the quick responsiveness of incident.
SUMMERY OF THE UTILITY MODEL
The utility model provides a technical problem provide a collapsible, but the VTOL unmanned aerial vehicle of quick installation.
The utility model provides a technical scheme that its technical problem adopted is:
a foldable vertical take-off and landing unmanned aerial vehicle comprises a fuselage, an outer wing of a wing, an empennage, an inner wing of the wing, a stay bar folding piece, an empennage quick-dismantling piece, a rotor wing power device and a propulsion power device; the aircraft body is internally integrated with a flight control system, an electromechanical system and an aeronautical system, the propulsion power device is arranged at the tail part of the aircraft body, the inner wing of the wing is connected with the aircraft body in a rapid plug-in mode and is symmetrically arranged at the rear section of the belly of the aircraft body in a left-right mode, the outer wing of the wing is connected with the inner wing of the wing in a rapid plug-in mode and is symmetrically arranged at the left side and the right side of the aircraft body, and the outer wing of the wing and the inner wing of the wing form a lower; the strut is divided into a front part, a middle part and a rear part by the strut folding piece to form a front strut, a middle strut and a rear strut respectively, the middle strut and the wing inner wing are integrally formed, the front strut is connected with the front part of the middle strut through the strut folding piece, the front part of the rear strut is connected with the rear part of the middle strut through the strut folding piece, and the rear part of the rear strut is connected with the tail wing through the tail wing quick-release piece; the support rods are symmetrically arranged on the left side and the right side of the machine body to form a left front support rod, a right front support rod, a left middle support rod, a right middle support rod and a left rear support rod respectively; control preceding vaulting pole with all install rotor power device on the vaulting pole of controlling the back in the right side, control preceding vaulting pole with control back vaulting pole accessible the vaulting pole folded piece to the wing inner wing is folding to be accomodate.
Furthermore, an aileron is arranged at the rear edge of the outer wing of the wing, the aileron is mechanically connected with a steering engine through a pull rod, a signal line of the steering engine is connected with the flight control system, and the flight control system sends an instruction to control the deflection of the aileron so as to realize the rolling operation of the unmanned aerial vehicle.
Furthermore, a control surface is arranged on the rear edge of the empennage and is mechanically connected with a steering engine through a pull rod, a signal line of the steering engine is connected with the flight control system, and the flight control system sends an instruction to control the deflection of the control surface so as to realize the pitching and yawing operations of the unmanned aerial vehicle.
Preferably, the fuselage is a streamlined fuselage.
Preferably, the connecting position of the inner wing of the wing and the fuselage is rectified and modified to ensure that the aerodynamic characteristics are intact.
Further, the front end of the machine body is provided with an airspeed head.
Further, a photoelectric pod is arranged at the lower end of the machine body.
Further, the lower end of the machine body is also provided with an undercarriage.
The utility model has the advantages that:
1. the stay bar is divided into three parts by the stay bar folding piece, the front stay bar and the rear stay bar are connected with the middle stay bar by the stay bar folding piece, the middle stay bar and the wing inner wing are integrally formed, the front stay bar and the rear stay bar can be folded towards the wing inner wing, the whole machine boxing space requirement is small, and the machine installation is more convenient.
2. The inner wing of the wing is quickly connected with the fuselage in a quick splicing mode, the outer wing of the wing is quickly connected with the inner wing of the wing in a quick splicing mode, and the tail wing is quickly connected with the stay bar through the tail wing quick-detaching piece, so that the dismounting and the mounting can be quickly finished.
Drawings
FIG. 1 is a three-dimensional structure of the present invention;
FIG. 2 is a folding deformation diagram of a part of the structure in FIG. 1;
labeled as:
1. the airplane comprises an airplane body, 2, an outer wing of a wing, 3, an empennage, 4, an inner wing of the wing, 5, a support rod, 6, a rotor wing power device, 7, a propulsion power device, 8, an airspeed head, 9, a photoelectric pod, 21, an aileron, 31, a control surface, 51, a support rod folding piece, 52, an empennage quick-release piece, 5-1, a front support rod, 5-2, a middle support rod, 5-3 and a rear support rod.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein.
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 an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
A foldable vertical take-off and landing unmanned aerial vehicle is shown in figure 1 and comprises a fuselage 1, an outer wing 2 of a wing, an empennage 3, an inner wing 4 of the wing, a stay bar 5, a stay bar folding piece 51, an empennage quick-detaching piece 52, a rotor wing power device 6 and a propulsion power device 7. The aircraft body 1 is internally integrated with a flight control system, an electromechanical system and an aeronautical system, the tail part of the aircraft body is provided with a propulsion power device 7, the inner wing 4 of the wing is connected with the aircraft body 1 in a fast splicing mode and is symmetrically arranged at the rear section of the belly part of the aircraft body 1 in a left-right mode, the outer wing 2 of the wing is connected with the inner wing 4 of the wing in a fast splicing mode and is symmetrically arranged at the left side and the right side of the aircraft body 1, and the outer wing 2 of the wing and the inner wing.
In this embodiment, fuselage 1 adopts streamlined fuselage, and the resistance when the biggest possibility reduces the flight, and the rectification is repaiied in the place of wing inner wing 4 and fuselage 1 handing-over to guarantee that unmanned aerial vehicle's aerodynamic characteristic is intact.
The stay bar 5 is divided into a front part, a middle part and a rear part by a stay bar folding piece 51, as shown in fig. 2, the front stay bar 5-1, the middle stay bar 5-2 and the rear stay bar 5-3 are respectively formed, the middle stay bar 5-2 and the inner wing 4 of the wing are integrally formed, the front stay bar 5-1 is connected with the front part of the middle stay bar 5-2 through the stay bar folding piece 51, the front part of the rear stay bar 5-3 is connected with the rear part of the middle stay bar 5-2 through the stay bar folding piece 51, and the rear part is connected with the tail wing 3 through a tail wing quick-release piece 52. The stay bars 5 are symmetrically arranged at the left side and the right side of the machine body 1 and respectively form a left front stay bar, a right front stay bar, a left middle stay bar, a right middle stay bar and a left rear stay bar; the left front stay bar 5-1, the right front stay bar 5-1 and the left rear stay bar 5-3 are both provided with rotor wing power devices, the left front stay bar 5-1, the right rear stay bar 5-3 and the left rear stay bar 5-3 can be folded and stored towards the inner wing 4 through stay bar folding pieces 51, so that the whole machine can be conveniently boxed, the boxing space requirement is small, the loading is more convenient, and the folded inner wing 4 and the left and right stay bars 5 are shown in figure 2.
As shown in fig. 1, an aileron 21 is arranged at the rear edge of the outer wing 2 of the wing, the aileron 21 is mechanically connected with a steering engine through a pull rod, a signal line of the steering engine is connected with a flight control system, and the flight control system sends an instruction to control the aileron 21 to deflect so as to realize the rolling operation of the unmanned aerial vehicle. The control surface 31 is arranged at the rear edge of the empennage 3, the control surface 31 is mechanically connected with a steering engine through a pull rod, a signal line of the steering engine is connected with a flight control system, and the flight control system sends an instruction to control the deflection of the control surface 31 so as to realize the pitching and yawing operations of the unmanned aerial vehicle.
The rotor wing power device 6 and the propulsion power device 7 are composed of propellers, motors and electric regulators, and are respectively connected with a power supply and a flight control system through the electric regulators, the power supply provides power for the motors, and the flight control system sends control instructions to the motors.
As shown in fig. 1, the front end of the fuselage 1 may be provided with an airspeed head 8, and the lower end may be provided with a photoelectric pod 9 and landing gear (omitted from the figure) to increase the functions and safe landing of the drone.
The flight process is as follows:
unmanned aerial vehicle starts, controls preceding vaulting pole and controls the rotor power device 6 high-speed rotation on the back vaulting pole, keeps the stable rising of unmanned aerial vehicle, reachs appointed high back, starts propulsion power device 7 to reduce four rotor power device 6's power gradually until the stall, realize unmanned aerial vehicle take off to patrol the conversion of flying. When descending, the propulsion power device 7 is closed, and the rotor power device 6 is started, so that the unmanned aerial vehicle vertically descends.
The above-mentioned embodiments, further detailed description of the objects, technical solutions and advantages of the present invention, it should be understood that the above-mentioned embodiments are only specific embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (8)
1. The utility model provides a collapsible VTOL unmanned aerial vehicle which characterized in that: the aircraft comprises an aircraft body (1), an outer wing (2) of the aircraft wing, an empennage (3), an inner wing (4) of the aircraft wing, a stay bar (5), a stay bar folding piece (51), an empennage quick-dismantling piece (52), a rotor wing power device (6) and a propulsion power device (7); the aircraft body (1) is internally integrated with a flight control system, an electromechanical system and an avionic system, the tail part of the aircraft body (1) is provided with the propulsion power device (7), the inner wing (4) of the wing is connected with the aircraft body (1) in a rapid plug-in mode and is symmetrically arranged at the rear section of the belly part of the aircraft body (1), the outer wing (2) of the wing is connected with the inner wing (4) of the wing in a rapid plug-in mode and is symmetrically arranged at the left side and the right side of the aircraft body (1), and the outer wing (2) of the wing and the inner wing (4) of the wing form a lower single wing layout; the stay bar (5) is divided into a front part, a middle part and a rear part by the stay bar folding piece (51) to form a front stay bar (5-1), a middle stay bar (5-2) and a rear stay bar (5-3), the middle stay bar (5-2) and the inner wing (4) of the wing are integrally formed, the front stay bar (5-1) is connected with the front part of the middle stay bar (5-2) through the stay bar folding piece (51), the front part of the rear stay bar (5-3) is connected with the rear part of the middle stay bar (5-2) through the stay bar folding piece (51), and the rear part of the rear stay bar (5-3) is connected with the tail wing (3) through the tail wing quick-detaching piece (52); the support rods (5) are symmetrically arranged on the left side and the right side of the machine body (1) to form a left front support rod, a right middle support rod, a left rear support rod and a right rear support rod respectively; control preceding vaulting pole (5-1) and all install rotor power device (6) on controlling back vaulting pole (5-3), left right side preceding vaulting pole (5-1) with control back vaulting pole (5-3) accessible vaulting pole folded piece (51) to wing inner wing (4) are folded and are accomodate.
2. The foldable VTOL UAV of claim 1, wherein: ailerons (21) are arranged at the rear edge of the outer wing (2) of the wing, the ailerons (21) are mechanically connected with a steering engine through a pull rod, a signal line of the steering engine is connected with a flight control system, and the flight control system sends out an instruction to control the deflection of the ailerons (21) so as to realize the rolling operation of the unmanned aerial vehicle.
3. The foldable VTOL UAV of claim 1, wherein: the unmanned aerial vehicle is characterized in that a control surface (31) is arranged on the rear edge of the empennage (3), the control surface (31) is mechanically connected with a steering engine through a pull rod, a signal line of the steering engine is connected with a flight control system, and the flight control system sends an instruction to control the deflection of the control surface (31) so as to realize the pitching and yawing operations of the unmanned aerial vehicle.
4. A foldable VTOL UAV according to any of claims 1-3, characterized in that: the fuselage (1) is a streamlined fuselage.
5. The foldable VTOL UAV of claim 4, wherein: and the connecting part of the inner wing (4) of the wing and the fuselage (1) is rectified and modified to ensure that the aerodynamic characteristics are intact.
6. The foldable VTOL UAV of claim 5, wherein: the front end of the machine body (1) is provided with an airspeed head (8).
7. The foldable VTOL UAV of claim 5, wherein: the lower end of the machine body (1) is provided with a photoelectric pod (9).
8. The foldable VTOL UAV of claim 7, wherein: the lower end of the machine body (1) is also provided with an undercarriage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021217423.6U CN213649899U (en) | 2020-06-28 | 2020-06-28 | Collapsible VTOL unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021217423.6U CN213649899U (en) | 2020-06-28 | 2020-06-28 | Collapsible VTOL unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN213649899U true CN213649899U (en) | 2021-07-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202021217423.6U Active CN213649899U (en) | 2020-06-28 | 2020-06-28 | Collapsible VTOL unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023001157A1 (en) * | 2021-07-22 | 2023-01-26 | 田丰年 | Wing-and-rotary-wing mixed folding and unfolding system of flying vehicle, and flying vehicle |
-
2020
- 2020-06-28 CN CN202021217423.6U patent/CN213649899U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023001157A1 (en) * | 2021-07-22 | 2023-01-26 | 田丰年 | Wing-and-rotary-wing mixed folding and unfolding system of flying vehicle, and flying vehicle |
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