CN210971523U - Can realize fixed wing unmanned aerial vehicle of vertical take-off - Google Patents
Can realize fixed wing unmanned aerial vehicle of vertical take-off Download PDFInfo
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- CN210971523U CN210971523U CN201922113273.8U CN201922113273U CN210971523U CN 210971523 U CN210971523 U CN 210971523U CN 201922113273 U CN201922113273 U CN 201922113273U CN 210971523 U CN210971523 U CN 210971523U
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Abstract
The utility model relates to a fixed-wing unmanned aerial vehicle capable of realizing vertical take-off, which comprises a fixed-wing unmanned aerial vehicle body, a vertical take-off driving mechanism and an automatic disengaging traction mechanism, wherein the fixed-wing unmanned aerial vehicle body comprises a body and a pair of wings which are integrally arranged, and a first limiting groove and a second limiting groove are respectively arranged on the upper surface of the body between the wings and on the rear side of the wings; the traction mechanism capable of automatically disengaging comprises an electromagnet fixedly arranged in a first limiting groove on the machine body, and a traction rod hinged to the bottom of the square box body of the vertical takeoff driving mechanism, wherein one end, which is not hinged to the square box body, of the traction rod is hinged downwards to form an iron fixing plate. The utility model discloses can enough realize steady efficient vertical take-off, and can ensure that fixed wing unmanned aerial vehicle can not receive any hindrance and interference because of the change of self structure at conventional flight in-process to can realize the seamless linking of vertical take-off and conventional flight.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle vertical lift technical field specifically indicates a can realize fixed wing unmanned aerial vehicle of taking off perpendicularly.
Background
Many rotor unmanned aerial vehicles and fixed wing unmanned aerial vehicle have been very common in daily life, often are used for occasions such as aerial photography, ground survey and drawing, disaster relief investigation. However, in the using process, the multi-rotor unmanned aerial vehicle is found to be short in flight time, the flight speed is low, the multi-rotor unmanned aerial vehicle is not suitable for large-scale exploration and flight, and the problem of short flight duration is solved by the fixed-wing unmanned aerial vehicle. Traditional fixed wing unmanned aerial vehicle need take off with the help of the runway in the use, and some small-size fixed wing unmanned aerial vehicles that are used for taking photo by plane need carry out the hand through the manual work and throw or adopt launcher equipment to launch unmanned aerial vehicle often because there is not suitable runway when using. In the manual throwing process, even if throwing personnel have enough experience, the accident that the throwing angle is not in place to cause the crash loss of the unmanned aerial vehicle often occurs. And adopt launcher equipment to launch unmanned aerial vehicle, need add outfit launcher equipment, one comes the cost too high, and two come the bulky of launcher equipment, weight sink, and some unmanned aerial vehicle's use occasion is comparatively far away, even in mountain area, and the intensity of labour of operation personnel has undoubtedly been increased in carrying of bulky, heavy launcher equipment of weight.
For this reason, many manufacturers have begun to enter the development of fixed wing drones with vertical takeoff functionality. The existing unmanned aerial vehicle with the vertical flying function mainly has two types, one type is that a vertical lifting wing is added, a driving motor is vertically added on the body of the fixed-wing unmanned aerial vehicle, then a horizontal device screw is arranged on an output shaft of the driving motor, and the fixed-wing unmanned aerial vehicle is driven to realize vertical lifting under the driving of the screw of the horizontal device. Although vertical lift has been realized to such fixed wing unmanned aerial vehicle, when conventional flight, the driving motor of perpendicular setting and level assembly's screw can cause great weight burden for fixed wing unmanned aerial vehicle, can form great resistance moreover, and the result of use is very low, is difficult to obtain the popularization. In order to solve this problem, some producers try to make the driving motor who sets up perpendicularly and the screw that the level set up and to accomodate, but this has nevertheless promoted the complexity of product structure in the very big degree easily, leads to fixed wing unmanned aerial vehicle to lose original balanced state moreover, is difficult to realize more. The other is that the driving motor and the propeller of the fixed-wing unmanned aerial vehicle are made into a turnable folding structure, when the unmanned aerial vehicle takes off vertically, the driving motor and the propeller turn upwards, and the propeller turns upwards in a horizontal state, so that the unmanned aerial vehicle takes off vertically, and after the unmanned aerial vehicle takes off vertically, the driving motor and the propeller turn downwards through the turning mechanism, and conventional flight is realized. Such fixed wing unmanned aerial vehicle causes the fuselage unstability at the upset in-process of CD-ROM drive motor and screw easily, lead to the flight unbalance, the foremost is whole tilting mechanism and upset actuating mechanism, positioning mechanism's setting has in addition very big fixed wing unmanned aerial vehicle's that has increased structure complexity, the manufacturing cost of equipment has been increased by a wide margin, and under the condition that the structure complexity promoted by a wide margin, fixed wing unmanned aerial vehicle's flight is difficult to remain stable for a long time, life is difficult to obtain the assurance.
Consequently, a research and development section can enough realize steady efficient vertical take-off, and can ensure to accomplish the fixed wing unmanned aerial vehicle after the vertical take-off can not receive any hindrance and interference because of the change of self structure at conventional flight in-process, and the structure is simple and easy, can ensure flight effect and life to can realize the fixed wing unmanned aerial vehicle that can realize vertical take-off and the seamless linking of conventional flight is the utility model discloses a research and development purpose.
Disclosure of Invention
To the problem that above-mentioned prior art exists, the utility model provides a can realize the fixed wing unmanned aerial vehicle of taking off perpendicularly, this can realize the fixed wing unmanned aerial vehicle of taking off perpendicularly can effectively solve the problem that above-mentioned prior art exists.
The technical scheme of the utility model is that:
a fixed-wing unmanned aerial vehicle capable of achieving vertical takeoff comprises a fixed-wing unmanned aerial vehicle body, a vertical takeoff driving mechanism and an automatic disengaging traction mechanism, wherein the fixed-wing unmanned aerial vehicle body comprises a body and a pair of wings, the body is integrally arranged, the wings are arranged on the left side and the right side of the body, the front sides of the wings and the front part of the body are respectively provided with a horizontal driving motor in a horizontal fixing mode, an output shaft of each horizontal driving motor is respectively provided with a longitudinal propeller in a fixing mode, a first limiting groove and a second limiting groove are respectively formed in the upper surface of the body between the wings and the rear side of the wing, a corresponding fixed-wing unmanned aerial vehicle storage battery is arranged in the second limiting groove, and the horizontal driving motors are respectively connected to the fixed-wing unmanned aerial vehicle storage battery through corresponding fixed-wing unmanned aerial vehicle electric controllers; the vertical take-off driving mechanism comprises a square box body, the tops of four corners of the square box body are respectively and obliquely and fixedly connected with corresponding machine arms outwards, one ends of the machine arms, which are not fixedly connected to the square box body, are respectively and fixedly provided with corresponding vertical driving motors, output shafts of the vertical driving motors are respectively and fixedly connected with corresponding horizontal propellers, corresponding storage batteries for the unmanned rotor wing are fixedly arranged in the square box body, and the vertical driving motors are respectively connected to the storage batteries for the unmanned rotor wing through corresponding electric controllers for the unmanned rotor wing; but automatically, break away from drive mechanism contains fixing device in the electro-magnet of first spacing inslot, the electro-magnet passes through the power consumption controller of fixed wing unmanned aerial vehicle is connected to on the battery for the fixed wing unmanned aerial vehicle, but automatically, break away from drive mechanism still include and articulate to the pull rod of square box body bottom, the one end that the pull rod is not articulated downwards to have a shape with electro-magnet matched with iron fixed plate.
The upper surface of fuselage in the device has a corresponding photoelectric sensing ware between first spacing groove and the second spacing groove, be provided with a corresponding sign coating on the bottom intermediate position of square box body, photoelectric sensing ware is connected to stationary vane unmanned aerial vehicle power consumption controller.
The horizontal propellers are all positioned above a space formed by the fuselage and the wings.
And an upturning angle of 3-10 degrees is formed between the lower plane of the wing and the horizontal plane.
The opening direction of the second limiting groove is provided with a corresponding cover plate in a screw connection mode.
The utility model has the advantages that:
1) the utility model discloses on the basis of traditional fixed wing unmanned aerial vehicle body, increased the actuating mechanism that takes off perpendicularly to through the intervention that can break away from drive mechanism automatically, effectively realize that fixed wing unmanned aerial vehicle body and the perpendicular break off between the actuating mechanism can break away from and be connected. Before vertical takeoff, the electromagnet which can automatically separate from the traction mechanism is controlled by an electric controller for the fixed wing unmanned aerial vehicle to be communicated with a storage battery for the fixed wing unmanned aerial vehicle, and then an iron fixing plate which can automatically separate from the traction mechanism is assembled on the electromagnet in an adsorption manner; in the vertical takeoff process, the vertical driving motor is controlled to start by the electric controller of the rotor unmanned aerial vehicle, and the vertical takeoff driving mechanism is driven to fly upwards by the rotation of the horizontal propeller at the output shaft end of the vertical driving motor, as in the existing rotor unmanned aerial vehicle; in the process of flying upwards by the vertical takeoff driving mechanism, the fixed-wing unmanned aerial vehicle body is pulled and driven to take off upwards, and after the fixed-wing unmanned aerial vehicle body takes off upwards passively to a certain height, the horizontal driving motor is controlled to be started by the electric controller of the fixed-wing unmanned aerial vehicle, and the conventional horizontal flying of the fixed-wing unmanned aerial vehicle body is realized by the rotation of the longitudinal propeller at the output end of the horizontal driving motor; and when the conventional horizontal flight of fixed wing unmanned aerial vehicle body was to certain speed, through the outage of fixed wing unmanned aerial vehicle for the controller control electro-magnet, make fixed wing unmanned aerial vehicle body and the driving mechanism formation separation of taking off perpendicularly, ensure that fixed wing unmanned aerial vehicle body is under the prerequisite that has possessed sufficient flying height and flying speed, directly get into conventional flight. Can reach and realize steady efficient vertical take-off, and can ensure that the fixed wing unmanned aerial vehicle after accomplishing vertical take-off can not receive any hindrance and interference because of the change of self structure at conventional flight in-process, and the structure is simple and easy, can ensure flight effect and life.
2) The utility model discloses a fuselage upper surface has a corresponding photoelectric sensing ware between first spacing groove and second spacing groove, is provided with a corresponding sign coating on the bottom intermediate position of square box body, and the photoelectric sensing ware is connected to fixed wing unmanned aerial vehicle power consumption controller. When the conventional horizontal flight of fixed wing unmanned aerial vehicle body sensed the sign coating to photoelectric sensing ware, photoelectric sensing ware was with signal of telecommunication to fixed wing unmanned aerial vehicle power consumption controller, fixed wing unmanned aerial vehicle power consumption controller is receiving the signal of telecommunication that photoelectric sensing ware transmission was come back, the outage of control electro-magnet, ensure that fixed wing unmanned aerial vehicle body possesses sufficient flying speed when breaking away from the actuating mechanism that takes off perpendicularly, realize practically taking off perpendicularly and the seamless linking of conventional flight, fuselage when effectively ensuring fixed wing unmanned aerial vehicle body to get into conventional flight is stable.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a usage state diagram of the present invention.
Detailed Description
To facilitate understanding of those skilled in the art, the structure of the present invention will now be described in further detail with reference to the following examples:
referring to fig. 1-2, a fixed wing unmanned aerial vehicle capable of realizing vertical takeoff comprises a fixed wing unmanned aerial vehicle body 1, a vertical takeoff driving mechanism 2 and an automatic disengaging traction mechanism 3, the fixed wing unmanned aerial vehicle body 1 comprises a body 101 and a pair of wings 102, wherein the body 101 is integrally arranged, the wings 102 are arranged on the left side and the right side of the body 101, the front sides of the wings 102 and the front part of the fuselage 101 are respectively horizontally fixed with corresponding horizontal drive motors 4, the output shafts of the horizontal driving motors 4 are respectively provided with a longitudinal propeller 5, the upper surface of the fuselage 101 is respectively provided with a first limit groove and a second limit groove between the wings 102 and at the rear side of the wings 102, the second limit groove is internally provided with a corresponding fixed wing unmanned aerial vehicle storage battery 6, and the horizontal driving motors 4 are respectively connected to the fixed wing unmanned aerial vehicle storage battery 6 through corresponding fixed wing unmanned aerial vehicle electric controllers 7; the vertical takeoff driving mechanism 2 comprises a square box body 201, the tops of four corners of the square box body 201 are respectively and obliquely and fixedly connected with corresponding arms 202 outwards, one ends, which are not fixedly connected to the square box body 201, of the arms 202 are respectively and fixedly provided with corresponding vertical driving motors 8, output shafts of the vertical driving motors 8 are respectively and fixedly connected with corresponding horizontal propellers 9, corresponding storage batteries 10 for the unmanned rotor wing are fixedly arranged in the square box body 201, and the vertical driving motors 8 are respectively connected to the storage batteries 10 for the unmanned rotor wing through corresponding electric controllers 11 for the unmanned rotor wing; the traction mechanism 3 capable of automatically disengaging comprises an electromagnet 301 which is fixedly arranged in a first limiting groove, the electromagnet 301 is connected to the storage battery 6 for the fixed-wing unmanned aerial vehicle through an electric controller 7 for the fixed-wing unmanned aerial vehicle, the traction mechanism 3 capable of automatically disengaging further comprises a traction rod 302 hinged to the bottom of the square box body 201, and one end, which is not hinged to the square box body 201, of the traction rod 302 is hinged downwards to an iron fixing plate 303, wherein the shape of the iron fixing plate is matched with that of the electromagnet 301.
A corresponding photoelectric sensor 12 is arranged on the upper surface of the body 101 between the first limiting groove and the second limiting groove, a corresponding identification coating 13 is arranged at the middle position of the bottom of the square box body 201, and the photoelectric sensor 12 is connected to the fixed-wing unmanned aerial vehicle power consumption controller 7.
The horizontal propellers 9 are all positioned above the space formed by the fuselage 101 and the wings 102.
An upturned angle of 8 degrees is formed between the lower plane of the wing 102 and the horizontal plane.
The opening of the second limiting groove is covered with a corresponding cover plate 14 in a screw connection mode.
The utility model discloses a take-off control process as follows:
1) before vertical takeoff, the electromagnet 301 which can automatically separate from the traction mechanism 3 is controlled by the electric controller 7 for the fixed wing unmanned aerial vehicle to be communicated with the storage battery 6 for the fixed wing unmanned aerial vehicle, and then the iron fixing plate 303 which can automatically separate from the traction mechanism 3 is assembled on the electromagnet 301 in an adsorption manner;
2) in the vertical takeoff process, the vertical driving motor 8 is controlled to start through the electric controller 11 of the rotor unmanned aerial vehicle, and the vertical takeoff driving mechanism 3 is driven to fly upwards through the rotation of a horizontal propeller 9 at the output shaft end of the vertical driving motor 8, as the existing rotor unmanned aerial vehicle does;
3) in the upward flying process of the vertical takeoff driving mechanism 3, the fixed-wing unmanned aerial vehicle body 1 is pulled and driven to take off upwards, after the fixed-wing unmanned aerial vehicle body 1 takes off upwards passively to a certain height, the horizontal driving motor 4 is controlled to be started through the electric controller 7 of the fixed-wing unmanned aerial vehicle, and the conventional horizontal flying of the fixed-wing unmanned aerial vehicle body 1 is realized through the rotation of the longitudinal propeller 5 at the output end of the horizontal driving motor 4;
4) and when fixed wing unmanned aerial vehicle body 1 conventional level flies to photoelectric sensor to sense 12 should sign coating 13, photoelectric sensor 12 transmits the signal of telecommunication to fixed wing for unmanned aerial vehicle controller 7, fixed wing for unmanned aerial vehicle controller 7 is after receiving the signal of telecommunication that photoelectric sensor 12 transmitted, control electro-magnet 301 cuts off the power supply, make fixed wing unmanned aerial vehicle body 1 and take off actuating mechanism 3 formation separation perpendicularly, ensure that fixed wing unmanned aerial vehicle body 1 has possessed under the prerequisite of sufficient flying height and flying speed, directly get into conventional flight, effectively further ensure perpendicular take off and conventional flight's no trace link up.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (5)
1. The utility model provides a can realize fixed wing unmanned aerial vehicle of vertical takeoff, includes fixed wing unmanned aerial vehicle body (1), vertical takeoff actuating mechanism (2) and can break away from drive mechanism (3) automatically, its characterized in that:
the fixed-wing unmanned aerial vehicle body (1) comprises a body (101) and a pair of wings (102) which are integrally arranged, wherein the wings (102) are arranged on the left side and the right side of the body (101), the front sides of the wings (102) and the front part of the body (101) are respectively provided with a corresponding horizontal driving motor (4), an output shaft of the horizontal driving motor (4) is respectively provided with a longitudinal propeller (5), the upper surface of the body (101) between the wings (102) and the rear side of the wings (102) are respectively provided with a first limiting groove and a second limiting groove, a corresponding fixed-wing unmanned aerial vehicle storage battery (6) is arranged in the second limiting groove, and the horizontal driving motors (4) are respectively connected to the fixed-wing unmanned aerial vehicle storage battery (6) through corresponding fixed-wing unmanned aerial vehicle electric controllers (7);
the vertical takeoff driving mechanism (2) comprises a square box body (201), the tops of four corners of the square box body (201) are respectively and obliquely fixedly connected with corresponding machine arms (202), one ends, which are not fixedly connected to the square box body (201), of the machine arms (202) are respectively and fixedly provided with corresponding vertical driving motors (8), output shafts of the vertical driving motors (8) are respectively and fixedly connected with corresponding horizontal propellers (9), the internal fixing device of the square box body (201) is provided with corresponding storage batteries (10) for the unmanned rotorcraft, and the vertical driving motors (8) are respectively connected to the storage batteries (10) for the unmanned rotorcraft through corresponding unmanned rotorcraft power controllers (11);
can break away from automatically that drive mechanism (3) contain fixing device in electro-magnet (301) of first spacing inslot, electro-magnet (301) pass through for fixed wing unmanned aerial vehicle electric controller (7) are connected to on the battery (6) for the fixed wing unmanned aerial vehicle, can break away from automatically that drive mechanism (3) still contain and articulate to draw rod (302) of square box body (201) bottom, draw rod (302) do not articulate downwards to the one end of square box body (201) have a shape with electro-magnet (301) matched with iron fixed plate (303).
2. The fixed-wing drone capable of vertical takeoff of claim 1, characterized in that: the upper surface of fuselage (101) in the device has a corresponding photoelectric sensing ware (12) between first spacing groove and the second spacing groove, be provided with a corresponding sign coating (13) on the bottom intermediate position of square box body (201), photoelectric sensing ware (12) are connected to stationary vane unmanned aerial vehicle power consumption controller (7).
3. The fixed-wing drone capable of vertical takeoff of claim 1, characterized in that: the horizontal propellers (9) are all positioned above a space formed by the fuselage (101) and the wings (102).
4. The fixed-wing drone capable of vertical takeoff of claim 1, characterized in that: and an upturning angle of 3-10 degrees is formed between the lower plane of the wing (102) and the horizontal plane.
5. The fixed-wing drone capable of vertical takeoff of claim 1, characterized in that: the opening of the second limiting groove is provided with a corresponding cover plate (14) in a covering mode through a screw connection mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922113273.8U CN210971523U (en) | 2019-11-29 | 2019-11-29 | Can realize fixed wing unmanned aerial vehicle of vertical take-off |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922113273.8U CN210971523U (en) | 2019-11-29 | 2019-11-29 | Can realize fixed wing unmanned aerial vehicle of vertical take-off |
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| Publication Number | Publication Date |
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| CN210971523U true CN210971523U (en) | 2020-07-10 |
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| CN201922113273.8U Active CN210971523U (en) | 2019-11-29 | 2019-11-29 | Can realize fixed wing unmanned aerial vehicle of vertical take-off |
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