CN213323643U - Large-load-capacity fixed-wing unmanned aerial vehicle - Google Patents
Large-load-capacity fixed-wing unmanned aerial vehicle Download PDFInfo
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- CN213323643U CN213323643U CN202022217162.4U CN202022217162U CN213323643U CN 213323643 U CN213323643 U CN 213323643U CN 202022217162 U CN202022217162 U CN 202022217162U CN 213323643 U CN213323643 U CN 213323643U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a large-load-capacity fixed wing unmanned aerial vehicle, which comprises a horizontally-mounted carrying mechanism and supporting mechanisms vertically and fixedly mounted at the two ends of the carrying mechanism, wherein the peripheral sides of the carrying mechanism and the supporting mechanisms are fixedly connected with the inner wall of a machine body to form a plurality of load bins; the loading bin sequentially comprises the following parts from the head part to the tail part of the machine body: the device comprises an electricity storage bin for mounting a storage battery, an aerial camera bin for carrying aerial camera equipment or a nacelle, an oil storage bin for mounting an oil tank, and a control bin for mounting transmission equipment, wherein the oil storage bin is arranged at the gravity center position of a machine body; the multiple load bins have sufficient space and can carry various devices and instruments; in addition, the oil-electricity hybrid power and the carrying mechanisms and carrying mechanisms made of various materials also reduce the weight of the airplane body and prolong the endurance time; in addition, the loading mechanism which is horizontally arranged and the supporting mechanisms which are vertically and fixedly arranged at the two ends of the loading mechanism are fixedly connected with the inner wall of the machine body, so that the loading bin is firm in structure.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field especially relates to a big load capacity fixed wing unmanned aerial vehicle.
Background
Unmanned aerial vehicles originate from military use, but with the development of power, power supply, electronics and control technology and the development of electromechanical technology, gyros, brushless motors and oil-driven unmanned aerial vehicles are mature day by day, and small and medium-sized light unmanned aerial vehicles develop like bamboo shoots in spring after rain, are applied to various fields of the national civilians, and are prosperous.
However, most of the existing aerial survey unmanned aerial vehicles are medium and small light unmanned aerial vehicles, the task load weight is small, the endurance time is short, and the application of the unmanned aerial vehicles in the fields of large-scale aerial survey and emergency mapping is limited. The performances of the mission load weight, the duration and the like are important factors related to the aerial photogrammetry operation efficiency and the cost of the unmanned aerial vehicle, and in order to further improve the performance and the operation efficiency of the unmanned aerial vehicle, the unmanned aerial vehicle with larger mission load weight and longer duration is necessary to be designed.
SUMMERY OF THE UTILITY MODEL
Not enough to prior art exists, the utility model aims to provide a big load capacity fixed wing unmanned aerial vehicle solves above-mentioned problem.
A large-load-capacity fixed wing unmanned aerial vehicle comprises a carrying mechanism and supporting mechanisms, wherein the carrying mechanism is horizontally installed, the supporting mechanisms are vertically and fixedly installed at two ends of the carrying mechanism, and the peripheral sides of the carrying mechanism and the supporting mechanisms are fixedly connected with the inner wall of a machine body to form a plurality of load bins;
the loading bin sequentially comprises the following parts from the head part to the tail part of the machine body: the device comprises an electric storage bin for mounting a storage battery, an aerial shooting bin for carrying aerial equipment or a nacelle, an oil storage bin for mounting an oil tank, and a control bin for mounting transmission equipment, wherein the oil storage bin is arranged at the gravity center position of the machine body.
The carrying mechanism comprises a carrying frame and a carrying plate;
aerial photography storehouse and the carrying mechanism in control storehouse adopt the carrier of loop configuration, hold electrical storage storehouse, oil storage storehouse with the carrying mechanism in storage electrical storage storehouse adopts flaky carrier plate.
The supporting mechanism is a reinforcing support, a first surface of the reinforcing support is fixedly connected with the end part of the carrying frame, and a second surface of the reinforcing support is fixedly connected with the carrying plate.
The carrying plate of the electricity storage bin is made of light wood materials.
The surface of the carrying frame is provided with a plurality of threaded holes for connecting equipment in a surrounding manner.
The fuselage below aerial photography storehouse and the control cabin is equipped with the opening.
The aircraft is characterized in that a plurality of flight rotors are uniformly distributed on the left aileron and the right aileron on two sides of the aircraft body, and the oil storage bin is arranged at the gravity center position of the aircraft body between the left aileron and the right aileron.
And a jet engine is installed at the tail part of the machine body.
Compared with the prior art, the utility model discloses the beneficial effect of equipment is:
the utility model discloses the prelude of equipment edge fuselage to afterbody do in proper order: the aerial photography device comprises an electric storage bin for mounting a storage battery, an aerial photography bin for carrying aerial photography equipment or a nacelle, an oil storage bin for mounting an oil tank and a control bin for mounting transmission equipment, wherein the space is sufficient, and various equipment and instruments can be carried; in addition, the oil-electricity hybrid power and the carrying mechanisms and carrying mechanisms made of various materials also reduce the weight of the airplane body and prolong the endurance time.
The device of the utility model is fixedly connected with the inner wall of the body through a horizontally installed carrying mechanism and a vertical supporting mechanism fixedly installed at the two ends of the carrying mechanism to form a plurality of load bins; load storehouse sound construction reduces because of the load mass is great, causes unmanned aerial vehicle fracture or damaged.
Drawings
Fig. 1 is a schematic structural diagram I of a large-load fixed-wing drone in this embodiment.
Fig. 2 is a schematic structural diagram II of a large-load fixed-wing drone in this embodiment.
Fig. 3 is a schematic structural diagram of a connection relationship between a carrying mechanism and a supporting mechanism in a large-load fixed-wing drone in the embodiment.
Fig. 4 is a schematic structural diagram III of a large-load fixed-wing drone in this embodiment.
In the drawings: the aircraft comprises an aircraft body 1, a left aileron 1-1, a right aileron 1-2, a flight rotor 1-3, a lifting support I1-4, a lifting support II 1-5, a lifting support III 1-6, a power storage bin 2, a aerial photography bin 3, a fuel storage bin 4, a control bin 5, a fuel tank 6, a carrying frame 7, a threaded hole 7-1, a carrying plate 8, a reinforcing support 9, a wind-power generator, a wind,
Detailed Description
In the following, the technical solutions in the embodiments of the present invention will be clearly and completely described with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
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 a component is referred to as being "connected" to another component, it can be directly connected to the other component or intervening components may also be present. When a component is referred to as being "disposed on" another component, it can be directly on the other component or intervening components may also be present. The terms "vertical," "horizontal," "left," "right," and the like as used herein are for illustrative purposes only.
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 large-load-capacity fixed wing unmanned aerial vehicle comprises a carrying mechanism and supporting mechanisms, wherein the carrying mechanism is horizontally installed, the supporting mechanisms are vertically and fixedly installed at two ends of the carrying mechanism, and the peripheral sides of the carrying mechanism and the supporting mechanisms are fixedly connected with the inner wall of a machine body 1 to form a plurality of load bins;
because most of the existing aerial survey unmanned aerial vehicles are medium and small light unmanned aerial vehicles, the mission load weight is small, the endurance time is short, and the application of the aerial survey unmanned aerial vehicles in the fields of large-scale aerial survey and emergency surveying and mapping is limited. The performances of the mission load weight, the duration time and the like are important factors related to the aerial photogrammetry operation efficiency and the cost of the unmanned aerial vehicle, and in order to further improve the performance and the operation efficiency of the unmanned aerial vehicle, the unmanned aerial vehicle with larger mission load weight and longer duration is necessary to be designed;
so this equipment utilizes horizontal installation's the supporting mechanism of carrying on mechanism and vertical fixed mounting at its both ends to and 1 inner wall of fuselage forms a plurality of load storehouses, the load storehouse is followed fuselage 1's prelude to afterbody and is in proper order: an electric storage bin 2 for mounting a storage battery, an aerial camera bin 3 for carrying aerial equipment or a pod, an oil storage bin 4 for mounting an oil tank 6, and a control bin 5 for mounting transmission equipment;
furthermore, a jet engine is installed at the tail part of the machine body 1, and an oil tank 6 in the oil storage bin 4 supplies fuel for the jet engine, so that the power endurance of the fuel oil is longer than that of most of the existing small and medium-sized rechargeable unmanned aerial vehicles; considering that the oil in the oil tank 6 is gradually reduced due to consumption in the flight process of the unmanned aerial vehicle; the oil storage bin 4 is arranged at the gravity center of the unmanned aerial vehicle body 1, and the stable state of the unmanned aerial vehicle cannot be influenced no matter the amount of oil in the oil tank 6 is increased or reduced;
furthermore, a plurality of flight rotors 1-3 are uniformly distributed on the left aileron 1-1 and the right aileron 1-2 on two sides of the fuselage 1 and can be vertically lifted, so that the lifting of the airplane is not influenced by the terrain, and considering that the flight rotors 1-3 of the airplane are not main driving devices, the flight rotors 1-3 adopt electrically-driven flight rotors, the self weight of the electrically-driven flight rotors is smaller than that of the fuel-driven flight rotors, so that the loss of fuel in the fuel tank 6 is reduced, and in addition, the flight rotors 1-3 are powered by a storage battery in the power storage bin 2; in the oil-electricity hybrid power system, if one of a jet engine or a flying rotor wing 1-3 on the airplane is damaged, the airplane can also continue flying, so that the airplane cannot crash; the oil storage bin 4 is arranged on the gravity center position of the fuselage 1 between the left aileron 1-1 and the right aileron 1-2.
The carrying mechanism comprises a carrying frame 7 and a carrying plate 8; the carrying mechanisms of the aerial photography cabin 3 and the control cabin 5 adopt a carrying frame 7 with an annular structure, and the carrying mechanisms of the power storage cabin 2, the oil storage cabin 4 and the power storage cabin 2 adopt sheet-shaped carrying plates 8; the fuselage 1 below aerial photography storehouse 3 and control cabin 5 is equipped with the opening.
The purpose of this design is; the aerial photographing device or the pod is carried in the aerial photographing cabin 3, the aerial photographing device can be mounted on the upper surface of the carrying frame 7 with the annular structure by adopting the carrying frame 7 with the annular structure, the image head of the aerial photographing device can penetrate through the carrying frame 7 with the annular structure at the moment, the ground is photographed, the visual field of the aerial photographing device cannot be blocked, when the pod is mounted, the connecting frame of the pod can be connected with the upper surface of the carrying frame 7 and also can be connected with the lower surface of the carrying frame 7, the aerial photographing cabin is suitable for connection of different pods, and the aerial photographing cabin 3 and the opening formed in the fuselage 1 below the control cabin 5 cannot block the visual field of the image head of the aerial photographing device and the mounting of the pod; similarly, the transmission device, such as a data transmitter, a graphic transmitter, an engine controller, etc., which can be installed in the control cabin 5, because the data transmitter and the graphic transmitter transmit with the receiving station on the ground through the wireless antenna, the body 1 below the control cabin 5 is also provided with an opening, so that the antennas of the data transmitter and the graphic transmitter can be extended;
because the oil tank 6 is loaded in the oil storage bin 4, the oil tank 6 has larger mass, and external force factors are required to be prevented from touching the oil tank 6, the sheet-shaped carrying plate 8 is adopted, compared with a carrying frame, the force bearing area of the carrying plate 8 and the oil tank 6 can be increased, the carrying device for carrying the oil tank 6 is prevented from being broken, and the external force factors are prevented from touching the oil tank 6 to a certain extent; the storage battery carried in the storage bin 2 has no mass larger than that of the oil tank 6, and the carrying plate made of metal is easy to generate a short circuit phenomenon with the battery, so the carrying plate 8 of the storage bin 2 is made of light wood materials.
Of course, in the airplane with large load capacity, the transported instruments and equipment have larger mass, so that the connection between the supporting mechanism and the carrying mechanism which form the load cabin needs to be firm, and the problem of breakage and even disintegration in the flying process is avoided;
therefore, the carrying frame 7 and the carrying plate 8 are horizontally installed, the first surface of the reinforcing bracket 9 is vertically and fixedly installed on the end surface of the carrying frame 7, the second surface of the reinforcing bracket 9 is vertically and fixedly installed on the end surface of the carrying plate 8, the reinforcing bracket 9 and the carrying frame 7 are fixedly connected with each other and then fixedly connected with the inner wall of the airframe 1, in such a connection way, even if the carrying plate 8 and one of the reinforcing brackets 9 are broken, one end of the carrying plate is fixedly connected with the other reinforcing bracket 9, and the other reinforcing bracket 9 is fixedly connected with the end surface of the carrying plate 8, even if part of the carrying plate 8 or the carrying frame 7 is damaged, the unmanned aerial vehicle cannot be easily broken, and further, the reinforcing bracket 9 is made of light composite material;
the surface of the carrying frame 7 is provided with a plurality of threaded holes 7-1 for connecting equipment in a surrounding manner; the purpose of this design is that the aerial camera 3 for carrying aerial camera or pod and the aerial camera and transport device carried in the control cabin 5 for mounting transport device are many, so the screw hole 7-1 is arranged around the surface of the carrying frame 7 for connecting and fixing with different kinds of devices.
The aircraft tail is provided with a lifting support III 1-6 which is arranged on the same horizontal line with the symmetric centers of the lifting support I1-4 and the lifting support II 1-5.
The working principle is as follows:
the carrying mechanism comprises a carrying frame 7 and a carrying plate 8; the carrying mechanisms of the aerial camera cabin 3 and the control cabin 5 adopt a carrying frame 7 with an annular structure, an image head of aerial camera equipment can penetrate through the middle of the carrying frame 7 with the annular structure to shoot the ground, the view field of the aerial camera equipment cannot be blocked, and when the pod is installed, the connecting frame of the pod can be connected with the upper surface of the carrying frame 7 and also can be connected with the lower surface of the carrying frame 7, so that the aerial camera cabin is suitable for connecting different pods; compared with the carrying frame, the sheet-shaped carrying plate 8 can increase the stress area of the carrying plate and the oil tank 6, avoid the breakage of a carrying device for carrying the oil tank 6 and prevent external force factors from touching the oil tank 6 to a certain extent; the storage battery carried in the storage bin 2 has no mass larger than that of the oil tank 6, and the carrying plate made of metal is easy to generate a short circuit phenomenon with the battery, so the carrying plate 8 of the storage bin 2 is made of light wood materials.
Therefore, the carrying frame 7 and the carrying plate 8 are horizontally arranged, the first surface of the reinforcing support 9 is vertically and fixedly arranged on the end surface of the carrying frame 7, the second surface of the reinforcing support 9 is vertically and fixedly arranged on the end surface of the carrying plate 8, the reinforcing support 9 and the carrying frame 7 are fixedly connected with each other and then fixedly connected with the inner wall of the airframe 1, and in such a connection mode, even if the carrying plate 8 and one of the reinforcing supports 9 are broken, one end of the carrying plate is fixedly connected with the other reinforcing support 9, and the other reinforcing support 9 is fixedly connected with the end surface of the carrying plate 8, even if part of the carrying plate 8 or the carrying frame 7 is damaged, the unmanned aerial vehicle cannot be easily broken.
The above description is for the detailed description of the preferred possible embodiments of the present invention, but the embodiments are not intended to limit the scope of the present invention, and all equivalent changes or modifications accomplished under the technical spirit suggested by the present invention should fall within the scope of the present invention.
Claims (8)
1. A large-load fixed wing unmanned aerial vehicle is characterized in that; the device comprises a carrying mechanism which is horizontally arranged and supporting mechanisms which are vertically and fixedly arranged at the two ends of the carrying mechanism, wherein the peripheral sides of the carrying mechanism and the supporting mechanisms are fixedly connected with the inner wall of a machine body (1) to form a plurality of load bins;
the load bin sequentially comprises the following parts from the head part to the tail part of the machine body (1): the device comprises an electric storage bin (2) for mounting a storage battery, an aerial camera bin (3) for carrying aerial camera equipment or a nacelle, an oil storage bin (4) for mounting an oil tank (6), and a control bin (5) for mounting transmission equipment, wherein the oil storage bin (4) is arranged at the gravity center position of a machine body (1).
2. The high load fixed wing drone of claim 1, wherein: the carrying mechanism comprises a carrying frame (7) and a carrying plate (8);
the aerial photography cabin (3) and the carrying mechanism of the control cabin (5) adopt a carrying frame (7) with an annular structure, and the power storage cabin (2), the oil storage cabin (4) and the carrying mechanism of the power storage cabin (2) adopt a sheet-shaped carrying plate (8).
3. A high load capacity fixed wing drone according to claim 2, characterized in that: the supporting mechanism is a reinforcing support (9), a first surface of the reinforcing support (9) is fixedly connected with the end part of the carrying frame (7), and a second surface of the reinforcing support (9) is fixedly connected with the carrying plate (8).
4. A high load capacity fixed wing drone according to claim 2, characterized in that: the carrying plate (8) of the electricity storage bin (2) is made of light wood materials.
5. A high load capacity fixed wing drone according to claim 2, characterized in that: the surface of the carrying frame (7) is provided with a plurality of threaded holes (7-1) for connecting equipment in a surrounding way.
6. A high load capacity fixed wing drone according to claim 2, characterized in that: the aerial photography cabin (3) and the machine body (1) below the control cabin (5) are provided with openings.
7. The high load fixed wing drone of claim 1, wherein: a plurality of flying rotors (1-3) are uniformly distributed on the left aileron (1-1) and the right aileron (1-2) on two sides of the fuselage (1), and the oil storage bin (4) is arranged on the gravity center position of the fuselage (1) between the left aileron (1-1) and the right aileron (1-2).
8. The high load fixed wing drone of claim 1, wherein: the tail part of the machine body (1) is provided with a jet engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022217162.4U CN213323643U (en) | 2020-09-30 | 2020-09-30 | Large-load-capacity fixed-wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022217162.4U CN213323643U (en) | 2020-09-30 | 2020-09-30 | Large-load-capacity fixed-wing unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN213323643U true CN213323643U (en) | 2021-06-01 |
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| CN202022217162.4U Active CN213323643U (en) | 2020-09-30 | 2020-09-30 | Large-load-capacity fixed-wing unmanned aerial vehicle |
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| CN (1) | CN213323643U (en) |
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- 2020-09-30 CN CN202022217162.4U patent/CN213323643U/en active Active
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