Micro-power aircraft

Abstract

The invention provides a micro-power aircraft. The micro-power aircraft comprises a framework; the air bag is used for providing lift force and is arranged in the framework; the cab is arranged at the bottom of the framework; the helium tank is arranged in the cab, and the helium tank is connected with the air bag through an inflation and deflation system; the propelling mechanism is used for driving the aircraft to move, and the propelling mechanism is fixedly connected with the cab. The aircraft provided by the embodiment of the invention ascends through the buoyancy of the air bag filled with helium and can stay in the air for a long time, the propelling mechanism can make the aircraft move up, down, left and right in a three-dimensional mode only by providing small forward propelling force, energy consumption is low, and air pollution is avoided. The extension frames horizontally extending outwards are arranged on the two sides of the top of the framework, the solar photovoltaic panels are laid on the extension frames, solar energy is converted through the solar photovoltaic panels to charge a power source in the cab, the power source supplies power to the propelling mechanism, and the cab is more environmentally friendly and saves energy.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a micro-powered aircraft. Background Art

[0002] Based on the source of lift, aircraft used in existing technology can generally be divided into three categories: fixed-wing aircraft, rotary-wing aircraft, and aerostats. Fixed-wing aircraft derive their lift from aerodynamics; rotary-wing aircraft derive their lift from vector thrust; and aerostats derive their lift from the buoyancy generated by lightweight gases. Modern aircraft, such as airplanes and drones, mostly use fuel as a power source. Some also use batteries or solar power. These not only increase the weight of the aircraft but also consume fuel, which is not environmentally friendly. Summary of the Invention

[0003] The purpose of the present invention is to provide a micro-powered aircraft to solve the technical problems raised in the background technology.

[0004] In order to achieve the above object, the present invention provides a micro-powered aircraft, comprising:

[0005] skeleton;

[0006] an airbag for providing lift, the airbag being arranged in the frame;

[0007] A cab arranged at the bottom of the frame;

[0008] A helium tank is provided in the cab, and the helium tank is connected to the airbag via a gas filling and discharging system;

[0009] as well as,

[0010] A propulsion mechanism is used to drive the aircraft to move, and the propulsion mechanism is fixedly connected to the cab.

[0011] Furthermore, the skeleton includes a plurality of semicircular support tubes and a plurality of connecting beams, wherein the openings of the support tubes are upwardly arranged, the plurality of support tubes are spaced apart along the axial direction of the airbag, the plurality of support tubes are connected by the connecting beams, and the plurality of connecting beams are spaced apart along the circumference of the support tubes;

[0012] The airbag is arranged in the opening of the support tube, and the airbag is connected to the inner wall of the support tube.

[0013] Furthermore, both sides of the top of the frame are provided with extension frames extending horizontally outward, and solar photovoltaic panels are laid on the extension frames, and the solar photovoltaic panels are electrically connected to the power supply in the cab.

[0014] Furthermore, the skeleton and the extension frame are both formed by processing carbon fiber tubes.

[0015] Furthermore, the inflation and deflation system includes a bidirectional air pump, a solenoid valve and a controller; the bidirectional air pump and the solenoid valve are connected in series on a pipeline, and both ends of the pipeline are connected to the helium tank and the air bag respectively;

[0016] The two-way air pump and the solenoid valve are both connected to the controller.

[0017] Furthermore, the propulsion mechanism includes two propulsion modules symmetrically arranged on both sides of the cab; the propulsion module includes a power unit and a tilt adjustment unit, the tilt adjustment unit includes a fixed seat and a rotating seat rotatably mounted on one end of the fixed seat, the other end of the fixed seat is fixedly connected to the cab, and the other end of the fixed seat is internally provided with a tilt power unit, and the tilt power unit drives the rotating seat to swing up and down around the fixed seat;

[0018] The power unit includes a propeller and a drive motor. The drive motor is fixedly installed in the rotating seat, and the propeller is fixedly installed on the output shaft of the drive motor.

[0019] Furthermore, the tilt power unit includes an electric steering gear, and a rotating shaft is provided on the rotating seat, and the rotating shaft is rotatably mounted on the fixed seat through a bearing.

[0020] The other end of the rotating shaft is fixedly connected to the output shaft of the electric steering gear.

[0021] Furthermore, the driving motor is a servo motor.

[0022] Furthermore, a tail surface is provided at the tail of the airbag.

[0023] Furthermore, a landing gear is provided at the bottom of the cab, and the landing gear is equipped with moving wheels.

[0024] The beneficial effects of the present invention are embodied in:

[0025] The aircraft provided in the embodiment of the present application rises by the buoyancy of a helium-filled airbag and can stay in the air for a long time. The propulsion mechanism only needs to provide a small forward thrust to enable the aircraft to move up, down, left and right in three dimensions, with low energy consumption and no air pollution.

[0026] Furthermore, there are extension frames extending horizontally outward on both sides of the top of the frame. Solar photovoltaic panels are laid on the extension frames. The solar photovoltaic panels convert solar energy to charge the power supply in the cab, and the power supply supplies power to the propulsion mechanism, which is more environmentally friendly and energy-saving. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly describes the drawings required for the specific embodiments or the description of the prior art. Similar elements or parts are generally identified by similar reference numerals throughout the drawings. Elements or parts in the drawings are not necessarily drawn to scale.

[0028] The accompanying drawings herein are incorporated into and constitute a part of the specification, illustrate embodiments consistent with the present application, and together with the specification, are used to explain the principles of the present application. For those skilled in the art, other drawings can be derived from these drawings without inventive effort.

[0029] Figure 1 A schematic diagram of the structure of a micro-powered aircraft provided in an embodiment of the present invention Figure 1 ;

[0030] Figure 2 A schematic diagram of the structure of a micro-powered aircraft provided in an embodiment of the present invention Figure 2 ;

[0031] Figure 3 A schematic diagram of the structure of a micro-powered aircraft provided in an embodiment of the present invention Figure 3 ;

[0032] Figure 4 A schematic structural diagram of a tilt adjustment unit provided in an embodiment of the present invention;

[0033] Figure 5 A schematic diagram of the connection structure between the rotating seat and the fixed seat provided in an embodiment of the present invention;

[0034] Figure 6 A schematic structural diagram of an inflation and deflation system provided in an embodiment of the present invention.

[0035] The purpose of this application, its features, and advantages will be further described in conjunction with the embodiments and with reference to the accompanying drawings. The accompanying drawings illustrate specific embodiments of this application, which will be described in more detail below. These drawings and the accompanying text are not intended to limit the scope of the present application in any way, but rather to illustrate the concepts of this application to those skilled in the art by reference to specific embodiments. DETAILED DESCRIPTION

[0036] The following embodiments of the technical solution of the present invention will be described in detail with reference to the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present invention and are therefore only examples and are not intended to limit the scope of protection of the present invention.

[0037] It should be noted that, unless otherwise specified, the technical or scientific terms used in this application should have the common meanings understood by those skilled in the art to which the present invention belongs.

[0038] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0039] In addition, the terms "first," "second," etc. are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. In the description of the present invention, "plurality" means more than two, unless otherwise specifically defined.

[0040] In this application, unless otherwise expressly specified or limited, terms such as "mounted," "connected," "connect," and "fixed" should be understood in a broad sense. For example, they may refer to fixed or detachable connections, or integration; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in this application based on specific circumstances.

[0041] In this application, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0042] like Figure 1 、 Figure 2 and Figure 3As shown, an embodiment of the present application provides a micro-powered aircraft, which includes a skeleton 1, an airbag 2 arranged in the skeleton 1, a cab 3 arranged at the bottom of the skeleton 1, a helium tank 4 arranged in the cab 3, and a propulsion mechanism for driving the aircraft to move. The propulsion mechanism is fixedly connected to the reinforcing beam structure on the cab 3, and the reinforcing beam structure is used to enhance the structural strength of the cab 3. After the airbag 2 is filled with helium with a density lower than that of air, buoyancy is generated to make the aircraft take off, which is used to provide lift. A power supply and an operating console are provided in the cab 3. The power supply is used to power the electrical devices on the entire aircraft. The driver operates the operating console in the cab 3 to control the flight of the entire aircraft.

[0043] The helium tank 4 is connected to the airbag 2 via an inflation / deflation system. The helium tank 4 stores gas. The inflation / deflation system can inflate the airbag 2 with helium from the tank 4, increasing its volume and generating greater buoyancy, thereby causing the entire aircraft to ascend. The inflation / deflation system can also draw helium from the airbag 2 into the tank 4, shrinking it and reducing its buoyancy, thereby causing the aircraft to descend.

[0044] In this embodiment, Figure 6 As shown, the inflation and deflation system includes a two-way air pump 9, a solenoid valve 10 and a controller 11. The two-way air pump 9 and the solenoid valve 10 are connected in series on a pipeline, and the two ends of the pipeline are respectively connected to the helium tank 4 and the airbag 2. The two-way air pump 9 and the solenoid valve 10 are both connected to the controller 11, and the controller 11 can be set on the operating table in the cab 3. Under normal circumstances, the solenoid valve 10 is in a closed state. When it is necessary to fill the airbag 2 with helium to increase the volume of the airbag 2, the driver inputs a first control instruction to the controller 11. After receiving the first control instruction, the controller 11 controls the solenoid valve 10 to open, and controls the two-way air pump 9 to discharge the helium in the helium tank 4 outward and fill it into the airbag 2. After the inflation is completed, the solenoid valve 10 and the two-way air pump 9 are closed at the same time. When the volume of the airbag 2 needs to be reduced, the driver inputs a second control instruction to the controller 11. After receiving the second control instruction, the controller 11 controls the solenoid valve 10 to open and controls the two-way air pump 9 to reversely fill the helium in the airbag 2 into the helium tank 4. After the adjustment is completed, the solenoid valve 10 and the two-way air pump 9 can be closed at the same time.

[0045] In this embodiment, the frame 1 is used to provide support for the airbag 2 and bear the weight of the cab 3, thereby improving the structural strength of the aircraft. Figure 1As shown, the skeleton 1 includes multiple semicircular support tubes 5 and multiple connecting beams 6. The support tubes 5 are arranged with their openings facing upward. The multiple support tubes 5 are spaced axially along the airbag 2. The multiple support tubes 5 are connected by the connecting beams 6. The multiple connecting beams 6 are spaced circumferentially along the support tubes 5. The airbag 2 is positioned within the openings of the support tubes 5 and connected to the inner wall of the support tubes 5.

[0046] like Figure 1 and Figure 2 As shown, the top of the frame 1 has extension frames 7 extending horizontally outward on both sides, and the extension frames 7 are covered with solar photovoltaic panels 8. The solar photovoltaic panels 8 are electrically connected to the power supply in the cab 3 for charging the power supply. In an exemplary embodiment, the power supply can be a battery.

[0047] The frame 1 and the extension frame 7 are both made of carbon fiber tubes. Carbon fiber tubes have high structural strength, low density, corrosion resistance, and strong fatigue resistance. Under the same volume, they can significantly reduce the weight of the aircraft itself, thereby improving the aircraft's load capacity.

[0048] like Figure 3 As shown, the propulsion mechanism includes two propulsion modules symmetrically arranged on both sides of the cab 3. The propulsion module includes a power unit and a tilt adjustment unit, as shown in FIG. Figure 4 As shown, the inclination adjustment unit includes a fixed seat 12 and a rotating seat 13 rotatably mounted on one end of the fixed seat 12, the other end of the fixed seat 12 is fixedly connected to the cab 3, and a inclination power unit is arranged inside the other end of the fixed seat 12, and the inclination power unit drives the rotating seat 13 to swing up and down around the fixed seat 12.

[0049] The power unit includes a propeller 14 and a drive motor 15. The drive motor 15 is fixedly mounted in the rotating seat 13, and the propeller 14 is fixedly mounted on the output shaft of the drive motor 15. When the drive motor 15 drives the propeller 14 to rotate, the rotation of the propeller 14 disturbs the air, causing the air to flow backward at an accelerated rate, thereby providing forward thrust to the aircraft and causing the aircraft to move forward. The pilot can control the flight speed of the aircraft by controlling the speed of the propeller 14. In order to facilitate accurate control of the speed of the drive motor 15, in this embodiment, the drive motor 15 can be a servo motor.

[0050] like Figure 5As shown, the pitch power unit includes an electric servo 16. A rotating shaft 17 is provided on the rotating base 13. The rotating shaft 17 is rotatably mounted on the fixed base 12 via a bearing 18. The other end of the rotating shaft 17 is fixedly connected to the output shaft of the electric servo 16. The electric servo 16 rotates the rotating base 13 by a preset angle to adjust the pitch angle of the propeller 14 and thus the flight state of the aircraft. In the event of unstable airflow, the pilot can maintain stability by adjusting the pitch angle of the propeller 14.

[0051] like Figure 2 As shown, to control the flight direction of the airship and maintain stability, a tail surface 19 is provided at the tail of the airbag 2. The tail surface 19 of the airship is primarily used to control and maintain the stability of the heading and pitch. It typically includes a rudder and elevator, which help the airship maneuver and adjust during flight, ensuring stability in the air.

[0052] like Figure 1 、 Figure 2 and Figure 3 As shown, a landing gear 20 is provided at the bottom of the cab 3, and the landing gear 20 is equipped with moving wheels 21. The landing gear 20 has a shock-absorbing function, and the landing gear 20 facilitates the aircraft to land directly on the ground, and the moving wheels 21 facilitate the aircraft to move on the ground.

[0053] In summary, the aircraft provided in the embodiments of the present application ascends via the buoyancy of the helium-filled airbag 2 and can remain airborne for extended periods. The propulsion mechanism only needs to provide a small forward thrust to enable the aircraft to move vertically, horizontally, and horizontally, resulting in low energy consumption and zero air pollution. Furthermore, outwardly extending horizontal extension frames 7 are provided on both sides of the top of the frame 1. These extension frames 7 are equipped with solar photovoltaic panels 8. These panels convert solar energy into electricity to charge the power supply within the cab 3, which in turn powers the propulsion mechanism, resulting in a more environmentally friendly and energy-efficient design.

[0054] Finally, it should be noted that the various technical features of the technical solution of this application can be combined arbitrarily. In order to make the description concise, not all possible combinations of the various technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this application.

[0055] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or make equivalent replacements for some or all of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present invention, and they should all be included in the scope of the claims and description of the present invention.

Claims

1. A micro-powered aircraft, characterized in that: include: Skeleton (1); an airbag (2) for providing lift, the airbag (2) being arranged in the frame (1); A cab (3) disposed at the bottom of the frame (1); a helium tank (4) disposed in the cab (3), the helium tank (4) being connected to the airbag (2) via an inflation and deflation system; as well as, A propulsion mechanism is used to drive the aircraft to move, and the propulsion mechanism is fixedly connected to the cab (3).

2. A micro-powered aircraft according to claim 1, characterized in that: The skeleton (1) comprises a plurality of semicircular support tubes (5) and a plurality of connecting beams (6), the support tubes (5) are arranged with their openings facing upward, the plurality of support tubes (5) are distributed at intervals along the axial direction of the airbag (2), the plurality of support tubes (5) are connected by the connecting beams (6), and the plurality of connecting beams (6) are distributed at intervals along the circumference of the support tubes (5); The airbag (2) is arranged in the opening of the support tube (5), and the airbag (2) is connected to the inner wall of the support tube (5).

3. A micro-powered aircraft according to claim 2, characterized in that: Both sides of the top of the frame (1) are provided with extension frames (7) extending outward horizontally, and solar photovoltaic panels (8) are laid on the extension frames (7). The solar photovoltaic panels (8) are electrically connected to the power supply in the cab (3).

4. A micro-powered aircraft according to claim 3, characterized in that: The skeleton (1) and the extension frame (7) are both formed by processing carbon fiber tubes.

5. The micro-powered aircraft according to claim 1, wherein: The inflation and deflation system comprises a bidirectional air pump (9), a solenoid valve (10) and a controller (11); the bidirectional air pump (9) and the solenoid valve (10) are connected in series on a pipeline, and the two ends of the pipeline are respectively connected to the helium tank (4) and the air bag (2); The bidirectional air pump (9) and the electromagnetic valve (10) are both connected to the controller (11).

6. The micro-powered aircraft according to claim 1, wherein: The propulsion mechanism comprises two propulsion modules symmetrically arranged on both sides of the cab (3); the propulsion module comprises a power unit and a tilt adjustment unit, the tilt adjustment unit comprises a fixed seat (12) and a rotating seat (13) rotatably mounted on one end of the fixed seat (12), the other end of the fixed seat (12) is fixedly connected to the cab (3), and a tilt power unit is arranged inside the other end of the fixed seat (12), and the tilt power unit drives the rotating seat (13) to swing up and down around the fixed seat (12); The power unit comprises a propeller (14) and a drive motor (15), wherein the drive motor (15) is fixedly mounted in the rotating seat (13), and the propeller (14) is fixedly mounted on the output shaft of the drive motor (15).

7. A micro-powered aircraft according to claim 6, characterized in that: The tilt power unit includes an electric steering gear (16). A rotating shaft (17) is provided on the rotating seat (13). The rotating shaft (17) is rotatably mounted on the fixed seat (12) through a bearing (18). The other end of the rotating shaft (17) is fixedly connected to the output shaft of the electric steering gear (16).

8. The micro-powered aircraft according to claim 6, characterized in that: The driving motor (15) is a servo motor.

9. The micro-powered aircraft according to claim 1, wherein: The tail of the airbag (2) is provided with a tail surface (19).

10. The micro-powered aircraft according to claim 1, characterized in that: A landing gear (20) is provided at the bottom of the cab (3), and the landing gear (20) is equipped with moving wheels (21).

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