CN213768958U - Vertical take-off and landing fixed wing unmanned aerial vehicle - Google Patents
Vertical take-off and landing fixed wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN213768958U CN213768958U CN202021163880.1U CN202021163880U CN213768958U CN 213768958 U CN213768958 U CN 213768958U CN 202021163880 U CN202021163880 U CN 202021163880U CN 213768958 U CN213768958 U CN 213768958U
- Authority
- CN
- China
- Prior art keywords
- aerial vehicle
- unmanned aerial
- wing
- suspension arm
- fixed wing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000000725 suspension Substances 0.000 claims abstract description 36
- 238000000034 method Methods 0.000 claims abstract description 4
- 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 18
- 230000001276 controlling effect Effects 0.000 claims description 12
- 230000035939 shock Effects 0.000 claims description 8
- 230000001105 regulatory effect Effects 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 5
- 239000002131 composite material Substances 0.000 claims description 3
- 230000005611 electricity Effects 0.000 claims description 3
- 238000006243 chemical reaction Methods 0.000 abstract description 2
- 238000012876 topography Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 229920000271 Kevlar® Polymers 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000004761 kevlar Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 230000003245 working effect Effects 0.000 description 1
Images
Abstract
The utility model discloses a vertical take-off and landing fixed wing unmanned aerial vehicle, which comprises a body, a main wing, a tail wing and a suspension arm; the tail part of the machine body 1 is provided with a main propeller for providing power for navigation, and the bottom of the machine body is connected with an aerial survey device for aerial photography of the unmanned aerial vehicle in the flying process; the main wing is detachably mounted on the machine body; the suspension arm is detachably mounted on the wing, and the suspension arm is provided with a propeller providing vertical take-off and landing acting force. The utility model discloses a mode that many rotors and two tail prop fixed wings combined together has the characteristics of fixed wing unmanned aerial vehicle range big and the convenient take off and land of many rotor unmanned aerial vehicle concurrently, need not with the help of runway and launching cradle, and it is little to take off and land the place requirement, can be in the smooth operation in complicated topography areas such as mountain area, hills, plateau. The whole course independently flies, and flight stages such as data acquisition, flight state conversion, vertical lifting and descending can be automatically completed only by planning a flight line at a ground station, so that the unmanned aerial vehicle flight platform is specially designed for large-area aerial survey.
Description
Technical Field
The utility model relates to an unmanned detection equipment technical field, especially a VTOL fixed wing unmanned aerial vehicle.
Background
The unmanned aerial vehicle low-altitude aerial photography technology is used as an important means for acquiring spatial data, has the advantages of relatively long endurance time, real-time image storage and transmission, low cost, high resolution, flexibility and the like, is particularly suitable for emergency reconnaissance and high-risk area surveying, is powerful supplement for manned aerial photogrammetry and satellite remote sensing, and is widely applied abroad.
In recent years, with the continuous promotion of informatization construction and scientific technology of China, the aerial survey research of the unmanned aerial vehicle is rapidly promoted and developed, the production, manufacture and practical application capabilities are greatly improved, and the unmanned aerial vehicle aerial survey equipment is basically equipped by the national survey and drawing geographic information bureau, the survey and drawing geographic information bureau of various provinces and other practical surveying and drawing units at the present stage, so that the low-altitude aerial survey of the unmanned aerial vehicle plays an increasingly important role in the aspects of national geographic information, basic surveying and drawing, urban planning, emergency rescue, key engineering projects and the like.
Disclosure of Invention
The utility model provides an above-mentioned problem provides a VTOL fixed wing unmanned aerial vehicle. The technical scheme of the utility model is that:
a vertical take-off and landing fixed wing unmanned aerial vehicle comprises a body, a main wing, a tail wing and a suspension arm; the tail part of the machine body is provided with a main propeller for providing power for navigation, and the bottom of the machine body is connected with an aerial survey device for aerial photography of the unmanned aerial vehicle in the flying process; the main wing is detachably mounted on the machine body; the suspension arm is detachably mounted on the wing, and the suspension arm is provided with a propeller providing vertical take-off and landing acting force.
As a further description of the present invention, the present invention further includes a remote controller for controlling the flight of the unmanned aerial vehicle, a flight control system is provided in the fuselage, the main propeller and the propeller are respectively connected to an independent motor, the flight control system includes a power supply module and a signal receiver, the remote controller is provided with a signal transmitter capable of being connected to the signal receiver in a wireless communication manner, a main switch for controlling the operation of the motor, and a speed control switch for adjusting the rotation speed of the motor; the power supply module is electrically connected with the motor, the motor is electrically connected with the flight control system, and the flight control system comprises an electronic speed regulator for regulating the rotating speed of the motor.
Furthermore, the wings and the empennage comprise ailerons and servo components for controlling the ailerons to move, each servo component comprises a steering engine and a connecting rod for controlling the movement of the ailerons of the unmanned aerial vehicle, and the steering engines are electrically connected with a flight control system.
Furthermore, the empennage is connected with the suspension arm through a thread dismounting structure, the thread dismounting structure comprises a first screwing part, a second screwing part and a turnbuckle, the first screwing part is rigidly fixed with the suspension arm, the second screwing part is rigidly fixed with the empennage, and the first screwing part and the second screwing part are screwed and fastened through the turnbuckle.
Furthermore, the thread dismounting structure further comprises an anti-loosening buckle, and the anti-loosening buckle is buckled on the outer side of the screw buckle and locks the screw buckle.
Furthermore, the aerial survey device comprises a camera, a camera cabin for placing the camera and a camera shock pad, wherein the camera shock pad is arranged between the camera and the camera cabin, the camera is provided with a shutter, and the shutter is electrically connected with the flight control system through a shutter control line.
Furthermore, the power supply module is a high-density power battery.
Furthermore, the machine body and the suspension arm are both made of composite materials.
Furthermore, the detachable connection mode of the wing and the fuselage is bolt connection.
Furthermore, the suspension arm is of a hollow structure.
The utility model discloses a mode that many rotors and two tail prop fixed wings combined together has the characteristics of fixed wing unmanned aerial vehicle range big and the convenient take off and land of many rotor unmanned aerial vehicle concurrently, need not with the help of runway and launching cradle, and it is little to take off and land the place requirement, can be in the smooth operation in complicated topography areas such as mountain area, hills, plateau. The whole course independently flies, and flight stages such as data acquisition, flight state conversion, vertical lifting and descending can be automatically completed only by planning a flight line at a ground station, so that the unmanned aerial vehicle flight platform is specially designed for large-area aerial survey.
Drawings
Fig. 1 is a schematic top view of an embodiment of the present invention;
FIG. 2 is a schematic front view of the embodiment of the present invention;
FIG. 3 is a schematic view of a boom structure according to an embodiment of the present invention;
FIG. 4 is a schematic cross-sectional view of a wing according to an embodiment of the present invention;
FIG. 5 is a schematic side view of the body of the embodiment of the present invention;
fig. 6 is a schematic structural diagram of a remote controller according to an embodiment of the present invention;
fig. 7 is a schematic structural diagram of an aerial survey device according to an embodiment of the present invention.
Fig. 8 is a schematic structural diagram of the wing and boom installation of the present invention.
Fig. 9 is a schematic structural view of the installation of the boom and the tail wing of the present invention.
Fig. 10 is a schematic view of the structural anti-loosening member for installing the suspension arm and the tail wing of the present invention.
Detailed Description
Example (b):
the embodiments of the present invention will be described in detail below with reference to the accompanying drawings, and it is to be understood that the described embodiments are merely illustrative of some, but not all embodiments of the invention.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
Referring to the attached drawings, the vertical take-off and landing fixed wing unmanned aerial vehicle comprises a body 1, a main wing 2, a tail wing 3 and a suspension arm 4; the tail part of the machine body 1 is provided with a main propeller 20 for providing power for navigation, and the bottom of the machine body is connected with an aerial survey device 5 for aerial photography of the unmanned aerial vehicle in the flying process; the main wing 2 is detachably mounted on the machine body 1; the suspension arm 4 is detachably mounted on the wing, and a propeller 41 for providing vertical take-off and landing acting force is arranged on the suspension arm 4.
In this embodiment, main screw 20 quantity is one, sets up at fuselage 1 afterbody, makes wing 2 and fin 3 can effectively avoid the screw air current, can improve main screw 20's propulsive efficiency, increases the time of endurance of this unmanned aerial vehicle scheme.
In the embodiment, the tail fin 3 is directly connected with the suspension arm 4, so that the length of the machine body 1 can be shortened, and the overall flight efficiency and the tail fin steering effect are ensured while the overall weight is reduced. Specifically, referring to the attached drawings, the tail wing 3 and the suspension arm 4 are connected by a thread dismounting structure without tool dismounting. The thread dismounting structure comprises a first screwing part 47 and a second screwing part 48, the first screwing part 47 is rigidly fixed with the suspension arm 4, the second screwing part 48 is rigidly fixed with the tail wing 3, the first screwing part 47 and the second screwing part 48 are buckled together through a turnbuckle 49, the turnbuckle 49 adjusts the buckling degree in a screwing mode, and the tail wing 3 and the suspension arm 4 are mounted and dismounted. In this embodiment, an anti-loosening buckle 54 is additionally provided, and after the screw buckle 49 is tightened, the anti-loosening buckle 54 is buckled on the outer side of the screw buckle 49 again, so as to achieve the purpose of loosening prevention.
The detachable connection mode of the suspension arm 4 and the wing 2 is bolt connection, referring to the attached drawing, in the embodiment, the suspension arm 4 is an arc-shaped suspension arm, the number of the suspension arm 4 is two, the two suspension arms are respectively installed on the left main wing 2 and the right main wing 2, two ends of each suspension arm 4 are respectively provided with a propeller 41, and when the suspension arm works, the four propellers 41 arranged on the suspension arm 4 and the wing 2 form power for vertical take-off and landing, so that an unmanned aerial vehicle can be driven to vertically take off and land; the middle section of the suspension arm 4 is provided with a first through hole 44, the wing 2 is provided with a first bolt hole 45 matched with the first through hole 44, a bolt sleeve 46 can be fastened and connected with the first spiral hole 45 through the first through hole 44, and meanwhile, the bolt sleeve 46 can be quickly loosened manually to disassemble the suspension arm 4 and separate the suspension arm from the wing 2.
In this embodiment, as preferred, the unmanned aerial vehicle still includes the remote controller 6 of control unmanned aerial vehicle flight, fuselage 1 in be equipped with flight control system, independent motor is connected respectively to main screw 20 and screw 41, and every main screw 20 and every screw 41 all are connected with independent motor promptly, and every motor provides power for main screw 20 and screw 41 alone. Flight control system includes power module 13 and signal receiver 11, and power module 13 is used for supplying power for all modules of unmanned aerial vehicle, refers to the attached drawing, remote controller 6 be equipped with can with signal receiver 11 wireless communication connection's signal transmitter 60, be used for controlling the master switch 61 of motor work and be used for adjusting motor speed's speed governing switch 62, power module 13 is connected with the motor electricity, the motor is connected with flight control system electricity, and signal transmitter 60 carries out wireless communication connection with signal receiver 11, preferably can adopt wireless spread spectrum communication connection, can realize accurate control flight control system work through anti-jamming, can control all motors simultaneous workings or do not work simultaneously through master switch 61 on remote controller 6 to control flight state. As a further explanation, the motor of the present embodiment is controlled in rotation speed by an electronic speed regulator, and the rotation speed of the motor can be controlled by a speed regulating switch 62 of the remote controller 6 to control the flying speed and the landing speed.
In this embodiment, preferably, the wings 2 and the tail wing 3 both include ailerons and a servo assembly for controlling the movement of the ailerons, and the servo assembly includes a steering engine 21 and a connecting rod for controlling the movement of the ailerons of the drone. The servo assembly adjusts the rotation angle of the left and right ailerons of the unmanned aerial vehicle according to the command output by the flight control, so that the flight attitude of the unmanned aerial vehicle is controlled.
In the present embodiment, preferably, referring to the drawings, the aerial survey device 5 includes a camera 51, a camera chamber 50 for placing the camera 51, and a camera shock pad 53, the camera shock pad 53 is disposed between the camera 51 and the camera chamber 50, the camera shock pad 53 is used for eliminating the influence of high-frequency vibration of the unmanned aerial vehicle casing on the camera 51, the camera shock pad 53 may be made of a shock-absorbing sponge or the like, the camera 51 is provided with a shutter 52, and the shutter 52 is electrically connected to a flight control system through a shutter control line for controlling the camera 51 to capture images.
In this embodiment, as preferred, the power module 13 is a high-density power battery, and the duration is long, thereby improving the one-time flight time of the unmanned aerial vehicle.
In the embodiment, the machine body 1 and the boom 4 are preferably made of a composite material, such as kevlar carbon fiber, so that the weight of the machine body is reduced while the strength and toughness of the machine body are ensured.
In this embodiment, as an optimization, referring to the drawings, the detachable connection mode between the wing 2 and the fuselage 1 is a bolt connection mode, a second bolt hole 23 is formed in one side, close to the fuselage 1, of the wing 2, a second through hole 12 used for being matched with the second bolt hole 23 is formed in one side of the fuselage 1, the bolt can be in threaded connection with the second bolt hole 23 formed in the wing 2 through the second through hole 12 formed in the fuselage 1, and the fuselage 1 and the wing 2 can also be detached and separated by loosening the bolt.
In this embodiment, the bolts used are preferably quick bolts, which can be tightened and loosened by hand to achieve quick assembly and disassembly.
In the present embodiment, the suspension arm 4 is preferably a hollow structure to reduce the weight and the lifting resistance
The foregoing is illustrative of the preferred embodiments of the present invention only, and is not to be construed as limiting the claims. The present invention is not limited to the above embodiments, and the specific structure thereof allows for variations, and in short, all variations within the scope of the independent claims of the present invention are within the scope of the present invention.
Claims (9)
1. The utility model provides a VTOL fixed wing unmanned aerial vehicle which characterized in that: comprises a machine body, a main wing, a tail wing and a suspension arm; the tail part of the machine body is provided with a main propeller for providing power for navigation, and the bottom of the machine body is connected with an aerial survey device for aerial photography of the unmanned aerial vehicle in the flying process; the main wing is detachably mounted on the machine body; the suspension arm is detachably mounted on the wing, and a propeller for providing vertical take-off and landing acting force is arranged on the suspension arm;
the utility model discloses a suspension arm, including the davit, fin, screw thread dismouting structure, first revolving part, second revolving part and back-off, fin and davit pass through screw thread dismouting structural connection, screw thread dismouting structure includes first revolving part, second revolving part and turnbuckle, first revolving part is fixed with the davit rigidity, second revolving part is fixed with the fin rigidity, first revolving part revolves with the second and connects the portion to revolve through the turnbuckle and revolve to twist the straining.
2. The vtol fixed wing drone of claim 1, wherein: the unmanned aerial vehicle is characterized by further comprising a remote controller for controlling the unmanned aerial vehicle to fly, a flight control system is arranged in the unmanned aerial vehicle body, the main propeller and the propellers are respectively connected with independent motors, the flight control system comprises a power supply module and a signal receiver, and the remote controller is provided with a signal transmitter, a main switch and a speed regulating switch, wherein the signal transmitter can be in wireless communication connection with the signal receiver, the main switch is used for controlling the motors to work, and the speed regulating switch is used for regulating the rotating speed of the motors; the power supply module is electrically connected with the motor, the motor is electrically connected with the flight control system, and the flight control system comprises an electronic speed regulator for regulating the rotating speed of the motor.
3. The vtol fixed wing drone of claim 2, wherein: the wing and the empennage comprise ailerons and servo components for controlling the ailerons to move, each servo component comprises a steering engine and a connecting rod for controlling the movement of the ailerons of the unmanned aerial vehicle, and the steering engines are electrically connected with a flight control system.
4. The vtol fixed wing drone of claim 1, wherein: the thread dismounting structure further comprises an anti-loosening buckle, and the anti-loosening buckle is buckled on the outer side of the screw buckle and locks the screw buckle.
5. The vtol fixed wing drone of claim 2, wherein: the aerial survey device include the camera, be used for placing camera storehouse and camera shock pad, the camera shock pad is established between camera and camera storehouse, the camera is equipped with the shutter, the shutter passes through the shutter control line and is connected with flight control system electricity.
6. The vtol fixed wing drone of claim 2, wherein: the power supply module is a high-density power battery.
7. The vtol fixed wing drone of claim 1, wherein: the machine body and the suspension arm are both made of composite materials.
8. The vtol fixed wing drone of claim 1, wherein: the detachable connection mode of the wings and the fuselage is bolt connection.
9. The vtol fixed wing drone of claim 1, wherein: the suspension arm is of a hollow structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021163880.1U CN213768958U (en) | 2020-06-22 | 2020-06-22 | Vertical take-off and landing fixed wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021163880.1U CN213768958U (en) | 2020-06-22 | 2020-06-22 | Vertical take-off and landing fixed wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213768958U true CN213768958U (en) | 2021-07-23 |
Family
ID=76867138
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021163880.1U Active CN213768958U (en) | 2020-06-22 | 2020-06-22 | Vertical take-off and landing fixed wing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213768958U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113697086A (en) * | 2021-09-26 | 2021-11-26 | 北京海利天梦科技有限公司 | Rotatable multi-functional unmanned aerial vehicle fin |
-
2020
- 2020-06-22 CN CN202021163880.1U patent/CN213768958U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113697086A (en) * | 2021-09-26 | 2021-11-26 | 北京海利天梦科技有限公司 | Rotatable multi-functional unmanned aerial vehicle fin |
| CN113697086B (en) * | 2021-09-26 | 2023-12-19 | 北京海利天梦科技有限公司 | Rotatable multifunctional unmanned aerial vehicle fin |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105620735B (en) | High-speed multi-rotor vertical take-off and landing aircraft | |
| CN203294313U (en) | Police quadrotor type unmanned aerial vehicle | |
| CN106809402B (en) | Automatic auxiliary landing system of rotor unmanned aerial vehicle and control method thereof | |
| CN105431352A (en) | Rotary wing vehicle | |
| CN203996886U (en) | A kind of four axle eight oars aircraft of taking photo by plane | |
| CN105314110A (en) | Unmanned aerial vehicle with umbrella | |
| CN105652886A (en) | Internet unmanned aerial vehicle capable of achieving continuous endurance | |
| CN111731475B (en) | Vertical take-off and landing tilting composite wing aircraft | |
| CN205168905U (en) | Stationary vane aerial survey unmanned aerial vehicle | |
| CN109896003A (en) | A kind of VTOL is verted three rotor wing unmanned aerial vehicles | |
| CN105480418A (en) | Ducted fixed-wing oil-electric hybrid unmanned aircraft | |
| CN213768958U (en) | Vertical take-off and landing fixed wing unmanned aerial vehicle | |
| US20220055736A1 (en) | Multi-Function Flap For Aerial Vehicle | |
| CN216185992U (en) | Modularized fixed wing unmanned aerial vehicle | |
| CN205608525U (en) | Last internet unmanned aerial vehicle of continuation of journey | |
| CN214824104U (en) | Unmanned aerial vehicle | |
| CN105129088A (en) | Spherical uniaxial rudder oriented intelligent aircraft | |
| CN111152921A (en) | Control system of unmanned aerial vehicle capable of taking off and landing vertically | |
| CN210526849U (en) | Fixed wing unmanned aerial vehicle of tilting-rotating force | |
| CN111152919B (en) | Control method of unmanned aerial vehicle capable of taking off and landing vertically | |
| CN114379777B (en) | Tilting rotor unmanned aerial vehicle structure and working method thereof | |
| CN209649972U (en) | A kind of land and air double-used operation type flying robot | |
| CN204433051U (en) | Can Fast Installation formula eight-rotary wing aircraft | |
| CN107757914A (en) | Double dynamical VTOL fixed-wing unmanned plane | |
| CN206954510U (en) | It is a kind of can VTOL fixed-wing unmanned plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240324 Address after: Room 805, 8th Floor, No. 39 Sicheng Road, Tianhe District, Guangzhou City, Guangdong Province, 510000 (for office purposes only) (not intended for use as a factory building) Patentee after: GUANGZHOU SOUTH HIGH-SPEED RAILWAY SURVEYING TECHNOLOGY CO.,LTD. Country or region after: China Address before: 510663 No.39 Sicheng Road, Tianhe District, Guangzhou City, Guangdong Province Patentee before: SOUTH SURVEYING & MAPPING TECHNOLOGY CO.,LTD. Country or region before: China |