A hybrid vertical take-off and landing vehicle

Abstract

The present invention relates to the field of flying vehicles, in particular to a hybrid power vertical take-off and landing vehicle, comprising a circular frame, wherein the surface of the circular frame is hinged with two groups of wind-breaking wings, with the circular frame as the axis, a plurality of groups of skeletons inserted inside the circular frame, a plurality of groups of pitch-changing mechanisms arranged on the skeletons, and the inner diameters away from the two sides of the circular frame decrease successively, and the circular frame is unfolded in a spherical or elliptical shape in the storage and working state, and an airbag arranged inside the circular frame provides equal buoyancy for the device based on the overall weight of the device, and is buckled inside the sphere of the pitch-changing mechanism when stored, and valves for filling hydrogen and helium are arranged on the surface of the airbag, and the windward surface of the airbag is elliptical, and the device can vertically take off and land in a small space in the working state with higher precision, so that it is suitable for work in complex terrain, and when the device is working, the calculated volume of the airbag can be relied on to generate buoyancy balance with the device as a whole, so that the device can hover within a certain range in the working state.

Description

Technical Field

[0001] The invention relates to the field of flying vehicles, in particular to a hybrid power vertical take-off and landing vehicle. Background Art

[0002] Flying vehicles refer to vehicles that fly loaded vehicles within a certain area. They may be equipped with sensors such as lidar or cameras to quickly obtain surface information for auxiliary research in land planning, urban construction, etc., to analyze the current terrain and obtain information for three-dimensional modeling. In special cases, they may also be equipped with high-definition equipment and positioning systems, and then cruise autonomously to improve the inspection efficiency and safety of the current area. Existing aircraft, during the process of being put into use, are inconvenient to take off and land in narrow environments, such as complex terrains such as mountains, jungles, and urban buildings, and consume more energy during flight, resulting in poor endurance. Moreover, they encounter two types of resistance when flying in the air, namely pressure difference resistance and viscous resistance, which will cause the vehicle to further consume electricity during flight and reduce its own endurance. At the same time, due to the high cost of flying vehicles, collisions will further increase the cost investment. Summary of the invention

[0003] In view of the above-mentioned problems or the problems in the prior art such as excessive flight resistance, increased energy consumption and easy damage, the present invention is proposed.

[0004] Therefore, an object of the present invention is to provide a hybrid vertical take-off and landing vehicle.

[0005] In order to solve the above technical problems, the present invention provides the following technical solutions: a hybrid vertical take-off and landing vehicle, comprising a circular frame, two groups of wind-breaking wings hinged on the surface of the circular frame, a plurality of groups of skeletons inserted inside the circular frame with the circular frame as the axis, a plurality of groups of pitch-changing mechanisms arranged on the skeletons, and the inner diameters away from the two sides of the circular frame decrease successively. In the stored and working states, the airbag is unfolded in a spherical or elliptical shape. The airbag arranged inside the circular frame provides equal buoyancy for the device based on the overall weight of the device, and is buckled inwardly inside the sphere of the pitch-changing mechanism when stored. Valves for filling hydrogen and helium are arranged on the surface of the airbag, and the windward side of the airbag is elliptical and the leeward side is conical. In the working state, the ratio of the diameter to the length of the airbag is 1 to 5 or 1 to 7.

[0006] As a preferred solution of a hybrid vertical take-off and landing vehicle of the present invention, the number of the skeletons ranges from four to eight.

[0007] As a preferred solution of a hybrid vertical take-off and landing vehicle of the present invention, the wind-breaking wings are rotated to the inside of the circular frame in the stored state.

[0008] As a preferred solution of a hybrid vertical take-off and landing vehicle of the present invention, the pitch changing mechanism includes a circumferential frame arranged on the skeleton, positioning blocks with the circumferential frame as the axis and the number corresponding to the skeleton, a spring one arranged inside the positioning block, and a fixed block arranged at the end of the spring one and sliding inside the positioning block.

[0009] As a preferred solution of a hybrid vertical take-off and landing vehicle of the present invention, electric propellers are arranged on a circumferential frame away from the circular frame and on the wind-breaking wing, and a tilting servo for adjusting the angle of the electric propeller is arranged inside the wind-breaking wing.

[0010] As a preferred solution of a hybrid power vertical take-off and landing vehicle of the present invention, a winglet is connected to the surface of one of the circumferential frames through threads.

[0011] As a preferred solution of a hybrid power vertical take-off and landing vehicle of the present invention, the surface of each circular frame with decreasing inner diameter is provided with a snap-in slot for receiving.

[0012] As a preferred solution of a hybrid vertical take-off and landing vehicle of the present invention, the maximum rotation angle of each wind-breaking wing when stored in the circular frame is ninety degrees.

[0013] The beneficial effects of a hybrid vertical take-off and landing vehicle of the present invention are as follows: through the arrangement of the circular frame, the skeleton, the pitch-changing mechanism and the airbag, the device can vertically take off and land in a narrow space when in operation, with higher precision, so that it is suitable for work on complex terrains; Furthermore, when the device is working, the calculated airbag volume and the device as a whole can generate buoyancy balance, so that the device can hover within a certain range in the working state. At the same time, the electric propeller provides power intermittently, resulting in high efficiency and long endurance, optimizing flight efficiency. Under the condition of providing the same power, it is suitable for tasks such as mapping and inspection in a larger range, and has higher energy utilization rate. Furthermore, in the working state, the pressure resistance of the high-pressure area on the windward side and the suction resistance of the low-pressure area behind are reduced, the device is lightweight and has a simple structure, which reduces the mechanical complexity, reduces the overall weight, reduces the purchase cost, and is easy to transport and maintain; Furthermore, during the storage or transportation of the device, the entire device can be stored in a sphere. The storage method is simple and non-staff can also quickly get started. At the same time, the outer surface of the merged sphere is circular, which has the characteristic of evenly distributing stress, reducing the risk of structural damage when specific parts are subjected to excessive pressure. Electric propellers, wind-breaking wings and other expensive structures are stored inside the sphere when not in use to avoid bumps. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without paying creative work.

[0015] Figure 1 A partial perspective schematic diagram of a hybrid vertical take-off and landing vehicle.

[0016] Figure 2 A first-person perspective schematic diagram of a hybrid vertical take-off and landing vehicle.

[0017] Figure 3 A schematic diagram of a hybrid vertical take-off and landing vehicle without airbags.

[0018] Figure 4 This is a schematic diagram of the partial storage and disassembly of a hybrid vertical take-off and landing vehicle.

[0019] Figure 5 It is a schematic cross-sectional diagram of a pitch-changing mechanism of a hybrid vertical take-off and landing vehicle.

[0020] In the figure: 100, circular frame; 101, wind-breaking wing; 102, electric propeller; 103, winglet; 200, skeleton; 300, pitch-changing mechanism; 301, circular frame; 302, positioning block; 303, spring 1; 304, fixed block; 400, airbag. DETAILED DESCRIPTION

[0021] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below in conjunction with the accompanying drawings.

[0022] Reference Figure 1~Figure 5A hybrid vertical take-off and landing vehicle includes a circular frame 100. Under normal conditions, a wireless communication module and a flight controller need to be installed on the circular frame 100. The wireless communication module is responsible for receiving and processing instructions from a remote control or a ground control station, and transmitting these instructions to the flight controller, and then the flight controller controls the device to set operations. Two groups of wind-breaking wings 101 are hinged on the surface of the circular frame 100. The wind-breaking wings 101 are different from conventional wings. There is no need to dig holes on the surface of the wind-breaking wings 101. When a conventional wing with holes is used in conjunction with an airbag 400, it will lose lift. With the circular frame 100 as the axis, several groups of skeletons 20 are inserted inside the circular frame 100. 0, the length of the skeleton 200 is greater than that of the airbag 400, and the skeleton 200 has a certain toughness, which can fit or limit the expansion of the airbag 400. Several sets of variable pitch mechanisms 300 are arranged on the skeleton 200, and the inner diameters away from the two sides of the circular frame 100 decrease successively. In the storage and working state, it is unfolded in a spherical or elliptical shape. The airbag 400 arranged inside the circular frame 100 provides equal buoyancy for it based on the overall weight of the device. When stored, it is buckled inside the sphere of the variable pitch mechanism 300. Valve for filling hydrogen and helium are arranged on the surface of the airbag 400, and the windward side of the airbag 400 is elliptical, and the leeward side is conical. In the working state, the ratio of the diameter to the length of the airbag 400 is 1 to 5 or 1 to 7.

[0023] During use, in the initial state, each variable pitch mechanism 300 approaches the two sides of the circular frame 100, and the variable pitch mechanism 300 is merged into a sphere, and the airbag 400 and the wind-breaking wing 101 are stored inside the circular frame 100. Its function is to prevent the core device from being damaged during non-use or transportation, and they can be stacked on each other while reducing storage space. In the working state, the variable pitch mechanism 300 is unfolded on the frame 200 and inflated into the airbag 400. After the airbag 400 expands to the set range, the wind-breaking wing 101 will be pushed out and the wind-breaking wing 101 will be restricted from kicking back.

[0024] It should be noted that when the volume is too large, the friction resistance of the air will be greater than the pressure difference resistance. For example, the projected area of ​​a 500-gram small fixed-wing drone is about 0.155 square meters. The projected area of ​​an airship that needs to support a weight of 500 grams is about 2 square meters. The calculation formula for air resistance is generally Fw=0.5× Cd×A×ρ×v², where Cd is the drag coefficient, A is the cross-sectional area, ρ is the air density, and v is the speed. At 70 kilometers per hour, the airship is subject to a friction resistance of 13.9 Newtons. It is approximately equal to 1 kilogram. A fixed-wing aircraft has only 1 Newton of force, which is approximately equal to 0.1 kilogram. Therefore, the windward surface of the airbag 400 is elliptical and the leeward surface is conical. The diameter and length ratio of the airbag 400 is 1 to 5 or 1 to 7. Such setting parameters can effectively reduce the pressure difference. Assuming that the overall weight of the device is 1KG, when the airbag 400 is filled with helium, 1m³ of gas needs to be filled into the airbag 400. At this time, the overall weight of the device and the buoyancy generated by the airbag 400 are balanced, and the buoyancy ≥ the overall weight of the device. When installing or transporting objects on the device, it is necessary to inflate the inside of the airbag 400 according to this setting. According to actual tests, this range is the maximum energy-saving benefit of the device, and when the airbag 400 is in the forward working state, the pressure gradient in front of the windward surface will be slowed down, and the cone of the airbag 400 will extend the laminar flow area. Thereby, the pressure difference resistance is greatly reduced, the load capacity is increased as much as possible, the range is increased, and the overall safety of the device when it is unpowered is increased, and a direct fall that would cause serious damage to the device is avoided. In addition, the designed airbag 400 can reduce the working time of the electric propeller 102 and excessive energy consumption. The conical part of the airbag 400 can also better fill the low-pressure space and reduce the pressure difference resistance.

[0025] Reference Figure 2~Figure 3 The number of the skeletons 200 ranges from four to eight, and the number of the skeletons 200 shall not be less than four. If the number of the skeletons 200 is less than four, the structure of the device will be unstable during operation. If the number of the skeletons 200 is too large, the overall weight of the device will increase, reducing the aerial working time of the device.

[0026] The wind-breaking wings 101 are rotated to the inside of the circular frame 100 in the stored state.

[0027] Reference Figure 5 The pitch changing mechanism 300 includes a circumferential frame 301 arranged on the skeleton 200, a positioning block 302 with the circumferential frame 301 as the axis and the number of which corresponds to the skeleton 200, a spring 303 arranged inside the positioning block 302, and a fixed block 304 arranged at the end of the spring 303 and sliding inside the positioning block 302, and the fixed block 304 is provided with an anti-slip groove close to the contact surface of the skeleton 200.

[0028] Reference Figure 3An electric propeller 102 is disposed on a circumferential frame 301 away from the circular frame 100 and on the wind-breaking wing 101 , and a tilting servo for adjusting the angle of the electric propeller 102 is disposed inside the wind-breaking wing 101 .

[0029] A winglet 103 is connected to the surface of one of the circumferential frames 301 through a thread. When the current environment is disturbed by airflow, the winglet 103 is installed on the circumferential frame 301. When the device is not in use, the winglet 103 can be stored in the sphere formed by the circumferential frame 301 to avoid damage caused by external collision when not in use. The winglet 103 can resist crosswind interference when in use, and the lateral aerodynamic force is generated by the winglet 103 to balance the crosswind and ensure that the device flies along a predetermined trajectory. When landing in a strong crosswind, the winglet 103 can effectively offset the influence of the lateral airflow. When the device as a whole yaws due to airflow disturbance, the winglet 103 automatically generates a reverse torque to correct the posture, similar to the tail feathers of an arrow to stabilize the flight trajectory. When making a sharp turn or roll, the damping torque is used to slow down the yaw oscillation to prevent loss of control.

[0030] The surface of each circular frame 301 with decreasing inner diameter is provided with a snap-in groove for storage. The snap-in groove on the surface of the circular frame 301 ensures that each circular frame 301 can be stably combined into a sphere when it is close to the circular frame 100 for storage, thereby preventing the wind-breaking wings 101 stored toward the inside of the circular frame 100 from being damaged during transportation or accidents when not in use.

[0031] The maximum rotation angle of each wind-breaking wing 101 when stored in the circular frame 100 is ninety degrees. After the wind-breaking wing 101 is unfolded outward, the airbag 400 is inflated in the circular frame 100, and then the inward movement angle of the wind-breaking wing 101 is limited. When the airbag 400 is inflated to a set range, the wind-breaking wing 101 will move inward only when the gas inside the airbag 400 is released. After the gas in the airbag 400 is released, the two do not contact each other above the wind-breaking wing 101 in the initial state inside the circular frame 100 when the airbag 400 is not inflated. Specific implementation method: The device is transported to the place of use, and then the circumferential frames 301 on both sides of the circular frame 100 are unfolded away from the circular frame 100, and then the frame 200 is bent to a certain extent by each circumferential frame 301 with different inner diameters, and then the spring 1 303 generates a force inside the positioning block 302 to push the positioning block 304 toward the frame 200, and then the frame 200 is pressed against the inside of the circumferential frame 301 for secondary fixation. In the case where the device needs to perform a topographic analysis of the current terrain, a high-definition device and a positioning system are installed on the surface of the circular frame 100, close to the ground, but The overall weight of the device is kept within the set range, that is, assuming that the load is 1KG, the airbag 400 is filled with 1m³ of helium gas. When the airbag 400 is filled with helium, the airbag 400 expands inside the circumferential frame 301, and then the airbag 400 pushes out the wind-breaking wing 101. The rounder end ensures a smaller wetted area under the same volume to reduce friction resistance. The tapered cone can minimize the curvature to avoid boundary layer separation, thereby generating pressure difference resistance and minimizing the wind resistance coefficient. In the case of strong wind, a small wing 103 is installed on the surface of the circumferential frame 301. When the preparation work is completed, the personnel control the wireless communication module and the flight controller on the circular frame 100 through the remote control, and the flight controller controls the device to set the operation. When turning is required, the angle of the electric propeller 102 is controlled by controlling the tilt servo inside the wind-breaking wing 101, and the operation is completed.

[0033] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solutions of the present invention may be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the present invention, which should all be included in the scope of the claims of the present invention.

Claims

1. A hybrid vertical take-off and landing vehicle, characterized in that: include; A circular frame (100), wherein two sets of wind-breaking wings (101) are hingedly connected on the surface of the circular frame (100); A plurality of groups of skeletons (200) are inserted into the circular frame (100) with the circular frame (100) as the axis; A plurality of sets of pitch-changing mechanisms (300) are arranged on the frame (200), and the inner diameters of the two sides away from the circular frame (100) decrease in sequence, and in the storage and working states, they are unfolded in a spherical or elliptical shape; The airbag (400) is arranged inside the circular frame (100) to provide equal buoyancy to the device based on the overall weight thereof, and is inwardly buckled inside the sphere of the pitch-changing mechanism (300) when stored. Valve for filling hydrogen and helium are arranged on the surface of the airbag (400), and the windward side of the airbag (400) is elliptical and the leeward side is conical. In the working state, the ratio of the diameter to the length of the airbag (400) is 1:5 or 1:

7.

2. A hybrid vertical take-off and landing vehicle according to claim 1, characterized in that: The number of the skeletons (200) ranges from four to eight.

3. A hybrid vertical take-off and landing vehicle according to claim 2, characterized in that: The wind-breaking wings (101) are rotated to the inside of the circular frame (100) in the stored state.

4. A hybrid vertical take-off and landing vehicle according to claim 3, characterized in that: The pitch-changing mechanism (300) comprises a circumferential frame (301) arranged on the frame (200), positioning blocks (302) with the circumferential frame (301) as the axis and the number of which corresponds to the frame (200), a spring (303) arranged inside the positioning block (302), and a fixed block (304) arranged at the end of the spring (303) and sliding inside the positioning block (302).

5. A hybrid vertical take-off and landing vehicle according to claim 4, characterized in that: An electric propeller (102) is disposed on one of the circumferential frames (301) away from the circular frame (100) and the wind-breaking wing (101), and a tilting servo for adjusting the angle of the electric propeller (102) is disposed inside the wind-breaking wing (101).

6. A hybrid vertical take-off and landing vehicle according to claim 5, characterized in that: A small wing (103) is connected to the surface of one of the circumferential frames (301) via threads.

7. A hybrid vertical take-off and landing vehicle according to claim 6, characterized in that: A clamping notch for receiving is provided on the surface of each circular frame (301) with decreasing inner diameter.

8. A hybrid vertical take-off and landing vehicle according to claim 7, characterized in that: The maximum rotation angle of each wind-breaking wing (101) when stored in the circular frame (100) is ninety degrees.

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