Double-wing two-engine embedded ocean surface sonar dragging unmanned aerial vehicle

Abstract

The invention discloses a double-wing two-engine embedded ocean surface sonar dragging unmanned aerial vehicle based on an injection molding / or 3D printing process as a main part. The unmanned aerial vehicle comprises a box body group, a main wing group, an auxiliary wing group, an empennage group, a camera and the like, wherein the main wing group comprises a main embedded two-engine drive; through an injection molding / 3D printing process, the problems of tedious production process, high manufacturing cost and the like are solved; through attitude conversion during cruising flight, namely buoyancy / lift force generated by wings including empennages in a cruising flight mode, energy saving during cruising is achieved like aircraft flight. The unmanned aerial vehicle is shaped like a box body in a static state, lifts off like a helicopter during takeoff, and flies like the aircraft with buoyancy / lift during cruising flight. In short, through the injection molding / or 3D printing process, the production cost is reduced; the air holding capacity and the cruising ability of cruising flight are brought through the conversion of the flight attitude when the main wings are unfolded; therefore, the method is suitable for sonar system grid ocean surface implantation operation and the like.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of injection molding / or 3D printing manufacturing technology, in particular to a double-wing two-engine embedded ocean surface sonar towed unmanned aerial vehicle. BACKGROUND

[0003] It is a good choice to use unmanned aerial vehicles to complete ocean surface grid implantation, underwater detection by ocean surface towing method, and sonar towed net operation. After all, it is more convenient and fast to use a work platform such as a ship and a fishing boat, vertically lift the aerial vehicle, and then use the ocean surface implantation and towing method. That is, the platform is lifted like a helicopter, and then converted into a wing span, which is similar to flying like an airplane. The efficiency can be doubled, the flight distance and hovering time are guaranteed, and the reliability, stability, installation, and maintenance of the physical indicators are improved. SUMMARY

[0004] In view of the above, the purpose of the present application is to provide a double-wing two-engine embedded ocean surface sonar towed unmanned aerial vehicle. The flight attitude of the unmanned aerial vehicle is converted, that is, the air buoyancy or lift in the forward direction obtained by expanding the main and auxiliary wing projection area is used to realize the time-efficient cruising capability. Further, the flight attitude conversion electromechanical reality is based on the injection molding / 3D printing manufacturing technology to meet the characteristics of innovation and optimization, that is, in the case of having certain structural strength, performance, and appearance, the purpose of lightweight is realized in the maximum case. Further, one-piece forming by injection molding / or 3D printing process significantly reduces the production process and processing difficulty, and the production cost is controlled. Further, in order to reduce the headwind resistance, the box body is organically integrated with the attitude conversion mechanism and the motor, so that the unmanned aerial vehicle body structure is compact. Further, the main and auxiliary wing expansion method, the wing projection area expansion (including the tail wing), that is, after realizing the conversion of the flight attitude, the efficiency is higher and simple and reliable. Further, there are photovoltaic cell groups on the main wing for charging lithium batteries, especially when implanted in the ocean surface static state. Further, that is, the physical indicators such as reliability, stability, installation, and maintenance are well solved.

[0005] To achieve the above purpose, the present application provides a double-wing two-engine ocean surface sonar towed unmanned aerial vehicle, characterized in that it comprises: ​The box group, as a basic part, is used for embedding the flight attitude conversion motor to realize the flight attitude conversion after taking off, and is also used for the zooming operation of the sonar sphere to realize the ocean surface implantation of the sphere and the water surface drag. The main and auxiliary wing group, hinged with the hinge seat on the box side stand, is used for the conversion of the flight attitude, including the expansion of the projection area when the main and auxiliary wing group is unfolded, so as to realize the wind floating force / lift force lifting like the airplane wings.

[0006] The tail wing group, hinged with the hinge seat on the box rear crossbar, is used for the flight attitude stabilization and adjustment, like the airplane tail wing, to complete the horizontal and turning control, and also includes the expansion of the projection area, which is beneficial to the floating force / lift force lifting. The two engines embedded in the main wing complete the natural attitude conversion from vertical take-off to cruising flight under the action of gravity.

[0007] Preferably, the flight attitude conversion unmanned aerial vehicle has the following characteristics: The box has four flange interval cutting in the side stand, and the end face hole is inserted with the up and down main and auxiliary wing attitude control motor, which is used for synchronously or asynchronously driving the main and auxiliary wing to transform between the horizontal and vertical, so as to realize the transformation of the flight attitude from taking off to flying; and the rear crossbar has a built-in tail wing attitude control motor, which is used for driving each tail wing to transform between the super horizontal and vertical, so as to realize the height and direction adjustment of the aerial position during the transformation of the flight attitude from taking off to flying, and also includes the adjustment of the center of mass during the vertical take-off.

[0008] Preferably, the flight attitude conversion unmanned aerial vehicle has the following characteristics: The box group has a center motor, which is used for winding the drum sonar sphere to complete the grid ocean surface implantation of the ocean sonar system, underwater detection of the sonar drag, and underwater fish detection to form the purse seine operation.

[0009] Preferably, the flight attitude conversion unmanned aerial vehicle has the following characteristics: The main wing and tail wing group are pasted with photovoltaic cell groups, which are used for supplementing the charging of the lithium battery.

[0010] The application provides a double-wing two-engine embedded ocean surface sonar towed unmanned aerial vehicle, through optimization of each component of the device, including modular design, especially main piece injection molding / 3D printing process, lightweight is realized. Further, the unmanned aerial vehicle attitude conversion motor is embedded in the box, which fully shows the simple structure, reduces the process difficulty and manufacturing cost, and is easy to check and maintain. Obviously, the unmanned aerial vehicle has the characteristics of low cost, guaranteed structural strength, simple process and easy to realize, and can be mass produced. Most importantly, it has good adaptability and practicability, which is convenient for popularization and application of the unmanned aerial vehicle. BRIEF DESCRIPTION OF DRAWINGS

[0011] The above and other objects, features and advantages of the present application will become more apparent from the following description of embodiments of the present application taken in conjunction with the accompanying drawings, in which: Fig. 1 is a schematic diagram of the equipment of the flight attitude conversion unmanned aerial vehicle of the embodiment of the application during cruising; Fig. 2 is a schematic diagram of the equipment of the flight attitude conversion unmanned aerial vehicle of the embodiment of the application during vertical take-off; Fig. 4 is a schematic diagram of the sonar ball winch mechanism structure of the flight attitude conversion unmanned aerial vehicle of the embodiment of the application; Fig. 6 is a schematic diagram of the tail wing equipment of the flight attitude conversion unmanned aerial vehicle of the embodiment of the application; Fig. 7 is a schematic diagram of the equipment of the flight attitude conversion unmanned aerial vehicle of the second embodiment of the application during cruising; Fig. 9 is a schematic diagram of the equipment of the flight attitude conversion unmanned aerial vehicle of the third embodiment of the application during cruising; Fig. 10 is a schematic diagram of the equipment of the flight attitude conversion unmanned aerial vehicle of the third embodiment of the application during take-off. DETAILED DESCRIPTION

[0012] Various embodiments of the present application will be described in detail with reference to the drawings. In each of the drawings, the same elements are denoted by the same or similar reference numerals. For the sake of clarity, each part in the drawings is drawn as much as possible in proportion, for example, in proportion to the width and height direction dimensions of the box. In addition, some well-known parts can not be shown in the drawings.

[0013] The specific embodiments of the present application will be further described in detail below with reference to the accompanying drawings and examples. In the following, many specific details of the present application are described, such as the structure, material, size, processing process and technology of components, so as to make the present application more clearly understood. But as the skilled in the art can understand, the present application can be implemented without these specific details.

[0014] The specific embodiments of the present application will be further described in detail below with reference to the accompanying drawings and examples. In the following, many specific details of the present application are described, such as the structure, material, size, processing process and technology of components, so as to make the present application more clearly understood. But as the skilled in the art can understand, the present application can be implemented without these specific details.

[0015] Figure 1 is a schematic diagram of the equipment of the flight attitude conversion unmanned aerial vehicle in cruising. The unmanned aerial vehicle includes: a box body group 1, a main wing group 2, an auxiliary wing group 3, a tail wing group 4, an attitude control motor 5 (including the main wing group, the auxiliary wing group, and the tail wing group), a sonar ball winch group 6 (including a reel, a reel motor, and a sonar ball), two engine groups 7, and a video head 8 (not shown in the figure, see Figure 2).

[0016] The box body 1 is made of injection molding or 3D printing process and is placed in the center position as a main part. From the front, the four corners of the vertical plates on both sides of the box body group form longitudinal barrel-shaped column dividing flanges, which are used to form a hinge seat structure to realize the articulation of the main wing 2 and the auxiliary wing 3 to complete the deployment conversion in flight, that is, to realize low-power flight like an airplane. From the front, the four corners of the vertical plates on both sides of the box body group form longitudinal barrel-shaped column dividing flanges, which are used to form a hinge seat structure to realize the articulation of the main wing 2 and the auxiliary wing 3 made of injection molding or 3D printing to complete the deployment conversion in flight, that is, to realize low-power flight like an airplane. In the holes of the front flanges on both sides, the speed reduction control motor 5 (collectively referred to as 5 in the figure) with a flat surface is inserted into the main wing and the auxiliary wing attitude long shaft and is used to complete the linkage and support of the main wing and the auxiliary wing (including the platform connection in the flange hole of the main wing and the auxiliary wing) to realize the attitude control of the main wing and the auxiliary wing from drooping to deployment in flight when taking off. In the horizontal bar on the back upper part, there is also a horizontal barrel-shaped column dividing flange, which is used to form a hinge seat structure to realize the articulation of the tail wing 4 to complete the deployment conversion in flight, that is, to realize low-power flight like an airplane. The flange holes in the rear end are glued and inserted into the tail wing posture long shaft with a plane deceleration control motor 5 (the posture control motor is collectively referred to as 5 in the figure) for completing the tail wing linkage (including the connection of the square shaft surface in the tail wing flange hole, see FIG. 5) to realize the posture control of the tail wing from drooping in take-off to unfolding in flight. It can be seen that the tail wing is added to expand the projection area, which is also very helpful to the buoyancy / lift of the unmanned aerial vehicle in low-speed flight in the case of wind channel; there are float boxes on the front and rear sides of the box body, which have space for implanting the floating of the ocean surface; at the same time, the internal space of the float box also includes the installation of the circuit system, including the integration of lithium batteries, flight control circuits, posture sensing circuits including height and direction, 5G or Beidou positioning circuits, camera control circuits, etc., that is, to form a lower plane seal; there is a winch mechanism of a sonar ball body between the two float boxes, which is used for lowering at a point to form an underwater floating state; photovoltaic cells are attached on the upper planes of the main wing and the tail wing, which are used for charging the lithium batteries of the power equipment for communication, ocean positioning, etc.

[0017] According to the box body group structure provided by the above-mentioned embodiment of the present application, as a basic component, it is one-time formed by injection molding / 3D printing process, the process is simple, and the structural strength is guaranteed; at the same time, the posture control motor is glued and embedded in the flange hole, which is an integrated structure, and also makes the structure simple and reliable; and the two engines embedded in the main wing are naturally converted to a flat state under the action of gravity when unfolded.

[0018] FIG. 2 is an equipment schematic diagram of the flight posture conversion unmanned aerial vehicle in vertical take-off according to the embodiment of the present application; in the vertical take-off posture, it is composed of: a box body 1, a main wing group 2, an auxiliary wing group 3, a tail wing group 4, a posture conversion motor 5 (the posture control motor is collectively referred to as 5), a sonar ball winch mechanism 6, a double-engine group 7, and a video head 8. As can be seen from the figure, before take-off, the main wing, the auxiliary wing, and the tail wing are in a drooping and compact posture, and the body is like a box, which reduces the projection area and reduces the resistance and energy consumption of vertical take-off. Compared with FIG. 1, when the main wing 2 and the auxiliary wing 3 are unfolded, the projection area is expanded (including the tail wing group 4), which is convenient for forming a larger buoyancy / lift to meet the wind, greatly reducing the engine driving energy consumption, and ensuring the long-distance flight capability and longer hovering capability.

[0019] Figure 3 is a schematic diagram of the box group structure of the flight attitude conversion unmanned aerial vehicle according to the embodiment of the application; as shown in the figure, the box group can be divided into two parts, which is completed by injection molding / 3D printing; in the upper part, the two side vertical plates of the box group form four corner longitudinal barrel column segmentation flanges, which are used to form a hinge seat structure to realize the hinge connection of the main and auxiliary wings, so as to complete the unfolding transformation during take-off to cruising flight, that is, to generate buoyancy / or lift in the case of wind, that is, to form a low-power flight; its In the middle, the glue-coated insertion main and auxiliary wing state conversion long shaft is inserted into the flange hole, and the flat reduction motor 5 (attitude control motor is collectively referred to as 5) and the flange are inserted into the grease-filled sleeve to form support, which is used to form the linkage of the main and auxiliary wings (including the plane connection of the main and auxiliary wing flange hole, see Figure 5) to realize the attitude control of the drooping of the main and auxiliary wings during take-off to the unfolding during flight. Above the back, there is a transverse barrel column segmentation flange to form a hinge seat structure for the hinge connection of the tail wing group to complete the timely adjustment of the horizontal and steering after the state attitude conversion; wherein, the glue-coated tail wing attitude long shaft is provided with a flat control motor 5 (all state control motors are collectively referred to as 5), and a grease-filled sleeve is inserted into the box flange hole, which is used to complete the linkage of the tail wing (including the plane connection of the tail wing flange hole) to realize the attitude control of the drooping of the tail wing during take-off to the upward during flight; at the same time, the tail wing is added to expand the projection area, which is a good help to the buoyancy / or lift of the unmanned aerial vehicle during cruising flight in the case of wind channel; in the box front and rear sealed cavities, lithium batteries and control circuits are installed; and between the two sealed cavity floats, there is a sonar ball launching winch mechanism 62 and a sonar ball 61 rolled up; the front part is inserted into a square hole, and the rear part has a wire plug inserted including a center motor to form a glued center stepping motor to realize the synchronous work of the winch barrel; a video head is installed on the lower front sealed cavity plate for video transmission to realize accurate positioning.

[0020] According to the box group structure provided by the above embodiment of the application, as a basic component, it is one-time formed by injection molding / 3D printing process, the process is simple, and the structural strength is guaranteed; at the same time, the attitude control motor is glued and embedded in the flange hole, which is an integrated structure, and also makes the structure simple and reliable.

[0021] Figure 4 is a schematic diagram of the sonar ball winch mechanism structure of the flight attitude conversion unmanned aerial vehicle according to the embodiment of the application; it is composed of a center stepping motor 61, a winding drum 62, a sonar ball 63 and an end cap 64; when the center position is glued and inserted, the center stepping motor is fixed due to the existence of the square joint; That is, the synchronous work of the stepping motor shell-winding drum is completed to complete the winding work. The end cap is used to complete the normal installation of the stepping motor.

[0022] Fig. 5 is a schematic diagram of the main and auxiliary wing structure of the flight attitude conversion unmanned aerial vehicle according to the embodiment of the present application; referring to Figs. 1 and 2, the main and auxiliary wings are placed on both sides of the box group, and correspond to each other, which are made by injection molding or 3D printing process. The two pieces are upper and lower pieces, and the end face has a split flange for forming a hinge body structure, which is hinged with the hinge seat in the box to form the attitude conversion in cruising. The hole in the flange is reserved for the insertion of the long shaft wing attitude control motor 5 with a reducer to form the connection, and the grease-coated sleeve is placed in the flange hole between the hinge seats on the box to provide lubrication support for the long shaft. That is, the synchronous rotation is completed. The arc-shaped notch is reserved in the flange to facilitate the barrier-free shaft rotation with the hinge seat in the box. The engine-driven motor is embedded in the main wing near the middle part to complete the driving of the aircraft; the main and auxiliary wings are designed like a cantilever beam to reduce the wind resistance caused by the cross section; the corner structure is provided at the lower end of the two pieces, like an aircraft tail, which can play a role in stabilizing the flow, which is beneficial to the flight cruising against the wind and stabilizing the flight; the photovoltaic cells are attached on the surface for charging the lithium battery to maintain sufficient supply to the electrical system.

[0023] According to the main and auxiliary wings provided by the above embodiment of the present application, as the hinge form rotating part, it is completed by injection molding or 3D printing process, which is one-time forming, simple process and easy to realize. The expanded projection area of the main and auxiliary wings when unfolded is the fundamental guarantee for forming the lift or buoyancy in cruising.

[0024] Fig. 6 is a schematic diagram of the tail wing structure of the flight attitude conversion unmanned aerial vehicle according to the embodiment of the present application; as shown in the figure, the tail wing 4 is a right and left piece, which is placed at the top rear corner of the box group, and is made by injection molding or 3D printing process. The flange is provided on the upper part for the hinge to be hinged with the hinge seat in the box to form the attitude conversion in cruising. The square hole in the flange is reserved for the insertion of the tail wing attitude control motor long shaft 5 (all state control motors are collectively referred to as 5) to form the connection, and the grease-coated sleeve is placed in the flange hole between the hinge seats on the box to provide necessary support for the long shaft to complete the synchronous rotation of the tail wing. The arc-shaped notch is reserved in the flange for barrier-free free rotation when cooperating with the hinge seat in the box. The arc-shaped edge is provided at the lower part to form the effect of increasing overflow in cruising to solve the vortex caused by the lower cross section. The corner vertical surface is designed on both sides to form the effect of stabilizing the flow and resisting the wind like an aircraft tail in cruising attitude; the photovoltaic cells are attached on the rear surface for charging the lithium battery.

[0025] The tail wing set provided by the above-mentioned embodiment of the present application is formed by injection molding or 3D printing process, which is one-time forming, simple process and convenient to realize. It is the basis of horizontal and height adjustment, further expands the projection area when unfolded, and further strengthens the lift or buoyancy during cruising.

[0026] Figure 7 is a schematic diagram of the equipment of the second embodiment of the present application when the flight attitude conversion unmanned aerial vehicle is cruising; comparison Figure 1 The third engine is led from the middle of the front crossbar, and the first and second engines are arranged on the main wing, that is, three-engine driving; other, basically consistent with the description of Figure 1, which will not be described here.

[0027] Figure 8 is a schematic diagram of the equipment of the second embodiment of the present application when the flight attitude conversion unmanned aerial vehicle takes off; comparison Figure 2 The two engines are increased to three engines; other, basically consistent with the description of Figure 2, which will not be described here.

[0028] Figure 9 is a schematic diagram of the equipment of the third embodiment of the present application when the flight attitude conversion unmanned aerial vehicle is cruising; comparison Figure 1 The two engines on both sides of the main wing are increased to two engines, and a total of four engines are driven; other, basically consistent with the description of Figure 1, which will not be described here.

[0029] Figure 10 is a schematic diagram of the equipment of the third embodiment of the present application when the flight attitude conversion unmanned aerial vehicle takes off; comparison Figure 2 The two engines on both sides of the main wing are increased to two engines, and a total of four engines are driven; other, basically consistent with the description of Figure 2, which will not be described here.

[0030] In summary, the embodiment of the present application is a two-wing two-engine embedded ocean acoustic sonar towed unmanned aerial vehicle, which has obvious structural contraction characteristics when taking off and double-wing unfolding characteristics when flying, so that the energy consumption from taking off to cruising flight is greatly reduced; especially in terms of cruising ability. The main part is prepared by injection molding or 3D printing process, which is well optimized including lightweight structure, so that the structure is simple, convenient for overall manufacturing, and the cost is well controlled.

[0031] The attitude control motor embedded in the box brings good organic cooperation to the engine, main wing, auxiliary wing and tail wing, and reduces the volume; at the same time, the separate control of the engine, main auxiliary wing and tail wing can strengthen the good control of the flight attitude. In short, the two-engine two-wing injection molding or 3D printing structure flight attitude conversion unmanned aerial vehicle is drawn from the actual size, which can be refined for production guidance; and it plays a role in promoting the popularization and application of unmanned aerial vehicle technology.​

[0032] The above description is only the preferred embodiment of the present application and is not intended to limit the present application. The present application can be variously changed and modified by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the present application.

Claims

1. A dual-wing, dual-engine, embedded ocean surface sonar-towed unmanned aerial vehicle, characterized in that, include: The housing assembly, as a basic component, is used for embedding the flight attitude conversion motor to achieve flight attitude conversion after takeoff. It also includes the scaling operation of the sonar sphere to achieve the implantation or dragging of the sphere on the ocean surface. The main and auxiliary wing assemblies are hinged to the hinge seats on the vertical plates on both sides of the box, and are used for flight attitude conversion, including the expansion of the projected area when the main and auxiliary wing assemblies are deployed, like the wings of an airplane, to achieve wind-assisted buoyancy / or lift enhancement; photovoltaic cell arrays are covered on the main wing for energy storage of lithium batteries. The tail assembly, which is hinged to the rear crossbar hinge seat on the box, is used for flight attitude stabilization and adjustment. Like the tail of an aircraft, it completes horizontal and turning control and also includes the expansion of the projected area, which is beneficial for buoyancy and / or lift enhancement. The two engines, embedded in the main wing, allow for a natural attitude transition from vertical takeoff to cruise flight under the influence of gravity.

2. The UAV according to claim 1, characterized in that, The enclosure assembly includes: The box body has four flanges cut into its side panels, with end holes into which are embedded attitude control motors for the upper and lower main and auxiliary wings. These motors are used to synchronously or asynchronously drive the main and auxiliary wings to change between horizontal and vertical, thus achieving the change in attitude from takeoff to flight. Additionally, there is a built-in tail wing attitude control motor embedded in the rear crossbar. This motor drives each tail wing to change between horizontal and vertical, thus achieving the adjustment of altitude and orientation during takeoff and flight attitude changes, including the adjustment of the center of gravity during vertical takeoff.

3. The UAV according to claim 2, characterized in that, The enclosure assembly also includes: The housing assembly contains a central motor for winching the drum sonar sphere to meet the requirements of marine sonar system grid implantation on the sea surface and sonar towed netting operations.

4. The UAV according to claim 2, characterized in that, The enclosure assembly also includes: The enclosure has sealed cavities at the front and rear for housing the circuit system, including lithium batteries, flight control drive circuits, attitude sensing circuits (including altitude and azimuth), and BeiDou navigation signal receiving circuits. The sealed cavities also serve to facilitate the buoyancy of the enclosure.

5. The UAV according to claim 2, characterized in that, The main wing and tail assembly includes: Photovoltaic cell arrays are attached to the main wing and tail fin assembly for supplemental charging of the lithium battery.

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