A helium-filled split plug-in aircraft and its manufacturing method

Abstract

The present invention discloses a helium-filled split plug-in type aircraft and its manufacturing method. The present invention includes a support frame and a cargo compartment. The cargo compartment is detachably arranged below the support frame. An independent helium-filled split plug-in unit with an adjustable inclination angle is provided on the support frame. An engine is provided outside the support frame, and a rotor is provided at the output end of the engine. The independent helium-filled split plug-in unit and the engine are connected to a controller arranged in the cargo compartment. The present invention adopts a split plug-in helium-filled airbag, and each plug-in is an independent safety unit, which is convenient for adjusting the number and arrangement form of the helium-filled airbags. Therefore, the design of this split aircraft can not only conveniently adjust the load capacity and flight state of the aircraft, but also maximize the safety of the aircraft during flight. By dividing the whole into parts, it is more flexible in use, maximally ensuring the safe flight of the aircraft and preventing catastrophic consequences caused by aircraft failures, thus having high safety performance.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and particularly to a helium-filled plug-in split aircraft and a manufacturing method thereof. Background Art

[0002] Currently, there are various types of aircraft, including: (1) Hot air balloon, which is a balloon using hot air as the lifting gas. There is a large opening at the bottom of the airbag for heating cold air and a gondola. Equipment such as simple flight instruments, fuel tanks, and blowtorches are installed in the gondola. When taking off from the ground, the blowtorch is lit, and the air is heated and then filled into the airbag through the opening at the bottom of the airbag. After taking off and flying, the fuel injection volume of the blowtorch is controlled to manipulate the ascent or descent of the balloon. In addition to the troublesome flight operation, the biggest problem with hot air balloons is safety. Once problems occur with the airbag, blowtorch, etc., the consequences are often catastrophic. (2) Paraglider, which is a paraglider that takes off and soars using the lift of the air. A paraglider usually mainly consists of four major parts: an airfoil canopy, suspension lines, a harness system, and a control system. When the canopy moves relative to the air, the air enters the air chamber through the inlet. Since the trailing edge of the canopy is closed and cannot be discharged, under the action of the air impact pressure, a certain pressure is generated inside the canopy cavity, enabling this flexible canopy to maintain a certain rigidity and shape. In order to facilitate the inflow of air into the inlet, a plastic reinforcement piece with a certain hardness, smoothness, and stiffness is sewn at the inlet part of each rib. At different parts of the rib, round holes with different sizes and numbers are also opened. The purpose is to enable the air between the air chambers to flow along the wingspan direction to balance the pressure inside the entire canopy and facilitate maintaining the shape of the entire canopy, avoiding the collapse of the canopy due to uneven stress during inflation. The biggest problem with paragliders is the complex operation. Without long-term professional training, it is impossible to operate.

[0003] The serious defects common to the above two types of aircraft are that if a local failure occurs during the flight of the aircraft, it is very likely to lead to a catastrophic flight tragedy as a whole, and the consequences are unimaginable. Moreover, the existing aircraft have a single flight mode and cannot be changed according to the flight environment during the flight, with poor flexibility and low safety factor. Therefore, it is necessary to develop an adjustable aircraft. Summary of the Invention

[0004] In view of the deficiencies in the above background art, the present invention proposes a helium-filled plug-in split aircraft and a manufacturing method thereof to solve the above technical problems.

[0005] The technical solution of the present invention is realized as follows: A helium-filled plug-in split aircraft includes a support frame and a cargo compartment. The cargo compartment is detachably arranged below the support frame. An independent helium-filled plug-in unit with an adjustable tilt angle is provided on the support frame. An engine is provided outside the support frame, and a rotor is provided at the output end of the engine. The independent helium-filled plug-in unit and the engine are connected to a controller arranged in the cargo compartment.

[0006] The independent helium - filling socket unit includes a solar panel and a number of helium - filling socket components arranged in parallel. The solar panel is arranged on one side of the helium - filling socket components and is connected to the controller. The helium - filling socket components are connected to the support frame through a swing - adjusting mechanism.

[0007] The helium - filling socket component includes a fixed - plate seat. Both ends of the fixed - plate seat are hinged to the support frame through a central pin shaft, and an air - filled bag is arranged on the fixed - plate seat.

[0008] An air - pressure sensor is arranged in the air - filled bag, and the air - pressure sensor is connected to the controller.

[0009] The swing - adjusting mechanism includes a transverse shaft. The transverse shaft is rotatably arranged on one side of the support frame, and a small motor is connected to one end of the transverse shaft. A longitudinal rod is arranged at the bottom of the fixed - plate seat, and the longitudinal rod is connected to the transverse shaft through a bevel - gear pair.

[0010] The bevel - gear pair includes a driving bevel gear arranged on the transverse shaft and a driven bevel gear arranged on the longitudinal rod. The driven bevel gear meshes with the driving bevel gear.

[0011] The swing - adjusting mechanism includes an electric push - rod. The electric push - rod is fixed on one side of the support frame, and the telescopic end of the electric push - rod is connected to a sliding transverse rod. The sliding transverse rod is connected to the fixed - plate seat through a linkage mechanism.

[0012] The linkage mechanism includes a chute seat fixed on the sliding transverse rod and a swing rod fixed on the central pin shaft. A slider is arranged at the lower end of the swing rod, and the slider is located in the chute seat and is slidably connected to the chute seat.

[0013] At least two engines are evenly distributed on the outer side ends of the support frame, and the engines are drive motors.

[0014] A flight method of a helium - filling socket split - type aircraft is as follows:

[0015] S1: Engines with rotors are arranged around the support frame, and an appropriate number of independent helium - filling socket units filled with helium are selected and installed on the support frame according to the load.

[0016] S2: Start the engines, and the aircraft moves upward. During the flight, adjust the tilt angle of the independent helium - filling socket units according to the wind speed and wind direction to make the aircraft fly smoothly.

[0017] S3: During the descent of the aircraft, adjust the tilt angle of the independent helium - filling socket units to make the aircraft descend slowly.

[0018] S4: During the processes of step S2 and step S3, the controller controls the engine and the independent helium-filled plug unit to form an aircraft control system with coupled plug control and engine control, ensuring the safe flight of the aircraft.

[0019] In view of problems such as the relationship between the buoyancy force on an object in a fluid, air resistance and the force-bearing area, the present invention applies fluid mechanics principles such as Archimedes' law and Bernoulli's equation to design a helium-filled plug split-type aircraft. By freely adjusting the angle of the plug, the air force-bearing area of the aircraft can be changed, and through the change of the force-bearing area, the air resistance during the ascent, descent and forward movement of the aircraft can be changed, thereby providing a user with an aircraft with safe flight, convenient operation and energy conservation. The split-type plug helium-filled airbag, with each plug being an independent safety unit, realizes the adjustment of the number and arrangement form of the helium-filled airbags, maximally ensuring the safe flight of the aircraft and preventing catastrophic consequences caused by aircraft failures, and has high safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present invention, and those of ordinary skill in the art can obtain other drawings based on these drawings without creative efforts.

[0021] Figure 1 It is a schematic diagram of the overall structure of the present invention.

[0022] Figure 2 It is a top view schematic diagram of the overall structure of the present invention.

[0023] Figure 3 It is a front view schematic diagram of a single helium-filled plug component of the present invention.

[0024] Figure 4 It is a schematic diagram of the structure of the swing adjustment mechanism in Embodiment 2.

[0025] Figure 5 It is a schematic diagram of the structure of the swing adjustment mechanism in Embodiment 3. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0026] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, rather than all, embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art without creative efforts based on the embodiments of the present invention belong to the scope of protection of the present invention.

[0027] As Figure 1As shown in the figure, Embodiment 1 provides a helium-filled split plugboard aircraft, which includes a support frame 1 and a cargo compartment 2. The cargo compartment 2 is detachably arranged below the support frame 1. The cargo compartment can be connected to the support frame through ropes or connecting rods. The support frame is a frame grid structure, and the air-force-bearing part is a plugboard combination, which is the main support structure of the aircraft. An independent helium-filled plugboard unit 3 with an adjustable inclination angle is provided on the support frame 1. The independent helium-filled plugboard unit 3 uses plugboard-type helium-filled airbags to realize the adjustment of the number and arrangement form of the helium-filled airbags, breaking the whole into parts and making it more flexible to use. An engine 4 is provided on the outer side of the support frame 1, and a rotor 5 is provided at the output end of the engine 4 to provide power for the aircraft to lift. The support frame 1 is a rectangular frame, and a transmitter is provided at each of the four corners of the rectangular frame, with a total of 4 engines 4. The engine 4 is a drive motor, and the drive motor drives the rotor to rotate. The independent helium-filled plugboard unit 3 and the engine 4 are connected to a controller arranged in the cargo compartment 2. The plugboard control and the engine control are coupled into a complete aircraft control system to control the flight state of the aircraft.

[0028] Further, as Figure 2 shown, the independent helium-filled plugboard unit 3 includes a solar panel 302 and a plurality of helium-filled plugboard components 301 arranged in parallel. The solar panel 302 is arranged on one side of the helium-filled plugboard components 301 and is connected to the controller. The solar panel can also be arranged at other positions of the support frame as long as it does not interfere with the independent helium-filled plugboard unit. The setting of the solar panel provides electrical energy for the aircraft. The helium-filled plugboard component 301 is connected to the support frame 1 through a swing adjustment mechanism 303. Under the action of the swing adjustment mechanism, the helium-filled plugboard component 301 can freely adjust the angle relative to the support frame, changing the air-force-bearing area of the aircraft. By changing the force-bearing area, the air resistance during the ascent, descent, and forward movement of the aircraft is changed, so as to provide a user with an aircraft with safe flight, convenient operation, and energy saving. The swing adjustment mechanism can adopt a connecting rod mechanism or a cam mechanism or other mechanical control structures to realize the adjustment of the swing angle of the helium-filled plugboard component.

[0029] Further, as Figure 3As shown in the figure, the helium-filled plug-in row assembly 301 includes a fixed plate seat 301-1. The fixed plate seat is a grid plate, which is used to support the air-filled balloon while not affecting the air buoyancy provided to the aircraft when the air-filled balloon is filled with helium. Both ends of the fixed plate seat 301-1 are hinged to the support frame 1 through a central pin shaft 301-3. By pushing the fixed plate seat, it can rotate left and right around the central pin shaft for angle adjustment. An air-filled balloon 301-2 is provided on the fixed plate seat 301-1. After the air-filled balloon 301-2 is filled with helium, the overall independent helium-filled plug-in row unit is an airbag body in the shape of a paraglider with a convex upper part and a flat lower part. When flying horizontally, in such a shape, an upward lift force can be generated due to the air flow velocity difference between the upper and lower parts. The air-filled balloon is made of a thin, tough, non-permeable flexible fabric, which is used to hold helium and provide better lift force for the horizontal flight of the aircraft. A pressure sensor is provided inside the air-filled balloon 301-2, and the pressure sensor is connected to the controller. The pressure sensor is used to detect the helium gas pressure in the air-filled balloon and monitor the helium gas volume in real time.

[0030] As Figure 4 shown in the figure, in Embodiment 2, a helium-filled plug-in row split-type aircraft, the swing adjustment mechanism 303 includes a transverse shaft 303-1. The helium-filled plug-in row assembly is arranged longitudinally, and the transverse shaft 303-1 is arranged horizontally and is located on one side of the helium-filled plug-in row assembly. The transverse shaft 303-1 is rotatably arranged on one side of the support frame 1, that is, the transverse shaft is arranged on the support frame through a bearing, and one end of the transverse shaft 303-1 is connected with a small motor 303-2, and the small motor drives the transverse shaft to rotate. A longitudinal rod 303-3 is fixedly provided at the bottom of the fixed plate seat 301-1, and the longitudinal rod 303-3 is connected to the transverse shaft 303-1 through a bevel gear pair 303-4. The small motor drives the transverse shaft to rotate, and the transverse shaft drives the longitudinal rod to rotate through the bevel gear pair 303-4, thereby realizing the rotation of the fixed plate seat for adjusting the angle of the helium-filled plug-in row assembly.

[0031] Preferably, the bevel gear pair 303-4 includes a driving bevel gear arranged on the transverse shaft 303-1 and a driven bevel gear arranged on the longitudinal rod 303-3. The driven bevel gear meshes with the driving bevel gear. The number of driving bevel gears corresponds to the longitudinal rods one by one. One longitudinal rod is arranged at the bottom of one fixed plate seat. When the transverse shaft rotates, it drives multiple longitudinal rods to rotate simultaneously for adjusting the overall angle of the helium-filled plug-in row assembly.

[0032] Other structures are the same as those in Embodiment 1.

[0033] As Figure 5As shown in the figure, Embodiment 3 is a helium-filled pluggable split aircraft. The swing adjustment mechanism 303 includes an electric push rod 303-1a. The electric push rod 303-1a is horizontally fixed on one side of the support frame 1, and the telescopic end of the electric push rod 303-1a is connected to a sliding horizontal rod 303-2a. A horizontal slide rail 303-3a is provided on the support frame. The sliding horizontal rod 303-2a is slidably arranged on the horizontal slide rail, and drives the sliding horizontal rod to move left and right under the telescopic action of the electric push rod. The sliding horizontal rod 303-2a is connected to the fixed plate seat 301-1 through a linkage mechanism. During the left and right movement of the sliding horizontal rod, the fixed plate seat is driven to swing through the linkage mechanism, realizing the adjustment of the overall angle of the helium-filled pluggable component.

[0034] Preferably, the linkage mechanism includes a chute seat 303-4a fixed on the sliding horizontal rod 303-2a and a swing rod 303-5a fixed on the central pin 301-3. The swing of the swing rod drives the swing of the fixed plate seat through the central pin. A slider 303-6a is provided at the lower end of the swing rod 303-5a. The slider 303-6a is located in the chute seat 303-4a and is slidably connected to the chute seat 303-4a. That is, a vertical chute is provided on the chute seat, and the slider is located in the vertical chute. The sliding horizontal rod moves under the action of the electric push rod, drives the swing rod to swing through the chute seat, and then drives the swing of the fixed plate seat through the central pin. One swing rod is provided on one central pin, and the number of chute seats corresponds to the number of swing rods one by one. The movement of the sliding horizontal rod drives the simultaneous rotation of multiple longitudinal rods at the same time, for the adjustment of the overall angle of the helium-filled pluggable component.

[0035] Other structures are the same as those in Embodiment 1.

[0036] Embodiment 4: A flight method of a helium-filled pluggable split aircraft, the steps are as follows:

[0037] S1: Install engines 4 with rotors around the support frame 1, and select and install an appropriate number of independent helium-filled pluggable units 3 filled with helium on the support frame 1 according to the load. The main body structure of the aircraft is a frame grid structure, and the air-force-bearing part is the pluggable combination. Since each plug and the buoyancy it provides are relatively independent, this maximally ensures the safe flight of the aircraft and will not cause catastrophic consequences due to aircraft failures.

[0038] S2: Start the engine 4, and the aircraft moves upward. During the flight, adjust the inclination angle of the independent helium-filled pluggable unit 3 according to the wind speed and direction. By changing the force-bearing area, change the air resistance when the aircraft rises, descends, and moves forward, so that the aircraft flies smoothly;

[0039] S3: During the descent of the aircraft, adjust the tilt angle of the independent helium-filled insert unit 3. By changing the force-bearing area, change the air resistance of the aircraft during ascent, descent, and forward movement, so that the aircraft descends slowly;

[0040] S4: During steps S2 and S3, the controller controls the engine 4 and the independent helium-filled insert unit 3 to form an aircraft control system that couples insert control and engine control, ensuring the safe flight of the aircraft.

[0041] Other structures are the same as those in Embodiment 2 or 3.

[0042] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims

1. A helium-filled split plug-in aircraft, characterized in that: It includes a support frame (1), a cargo bin (2) and an independent helium - filling socket unit (3). The cargo bin (2) is detachably arranged below the support frame (1). An independent helium - filling socket unit (3) with an adjustable tilt angle is provided on the support frame (1). An engine (4) is provided on the support frame (1), and a rotor (5) is provided at the output end of the engine (4). The independent helium - filling socket unit (3) and the engine (4) are connected to a controller arranged in the cargo bin (2). The independent helium - filling socket unit (3) includes a solar panel (302) and a number of parallel helium - filling socket components (301). The helium - filling socket components (301) are connected to the support frame (1) through a swing adjustment mechanism (303). The helium - filling socket component (301) includes a fixed - plate seat (301 - 1). Both ends of the fixed - plate seat (301 - 1) are hinged to the support frame (1) through a central pin shaft (301 - 3), and a helium - filled airbag (301 - 2) is provided on the fixed - plate seat (301 - 1). The independent helium - filling socket unit (3) uses socket - type helium - filled airbags to realize the adjustment of the number and arrangement form of the helium - filled airbags. The socket control and the engine control are coupled into a complete aircraft control system to control the flight state of the aircraft. Under the action of the swing adjustment mechanism, the helium - filling socket component (301) can freely adjust the angle relative to the support frame, changing the air - receiving area of the aircraft. By changing the air - receiving area, the air resistance during the ascent, descent and forward movement of the aircraft is changed, so as to provide a user with an aircraft with flight safety, convenient operation and energy conservation.

2. The helium-filled plug-in split aircraft according to claim 1, wherein: The solar panel (302) is arranged on one side of the helium - filling socket component (301) and is connected to the controller.

3. The helium-filled pluggable split aircraft according to claim 1, characterized in that: A pressure sensor is provided inside the helium - filled airbag (301 - 2), and the pressure sensor is connected to the controller.

4. The helium-filled plug-in split aircraft according to claim 2 or 3, characterized in that: The swing adjustment mechanism (303) includes a transverse shaft (303 - 1). The transverse shaft (303 - 1) is rotatably arranged on one side of the support frame (1), and a small motor (303 - 2) is connected to one end of the transverse shaft (303 - 1). A longitudinal rod (303 - 3) is provided at the bottom of the fixed - plate seat (301 - 1), and the longitudinal rod (303 - 3) is connected to the transverse shaft (303 - 1) through a bevel gear pair (303 - 4).

5. The helium-filled pluggable and separable aircraft according to claim 4, characterized in that: The bevel gear pair (303 - 4) includes a driving bevel gear arranged on the transverse shaft (303 - 1) and a driven bevel gear arranged on the longitudinal rod (303 - 3). The driven bevel gear meshes with the driving bevel gear.

6. The helium-filled plug-in split aircraft according to claim 3 or 5, characterized in that: The swing adjustment mechanism (303) includes an electric push rod (303 - 1a). The electric push rod (303 - 1a) is fixed on one side of the support frame (1), and a sliding transverse rod (303 - 2a) is connected to the telescopic end of the electric push rod (303 - 1a). The sliding transverse rod (303 - 2a) is connected to the fixed - plate seat (301 - 1) through a link mechanism.

7. The helium-filled split plug-in row aircraft according to claim 6, characterized in that: The link mechanism includes a chute seat (303-4a) fixed on a sliding transverse rod (303-2a) and a swing rod (303-5a) fixed on a central pin shaft (301-3). A slider (303-6a) is provided at the lower end of the swing rod (303-5a). The slider (303-6a) is located inside the chute seat (303-4a) and is slidably connected to the chute seat (303-4a).

8. The helium-filled plug-in row split aircraft according to any one of claims 1 to 3, 5, and 7, characterized in that: At least two engines (4) are evenly distributed at the outer ends of the support frame (1). The engines (4) are drive motors.

9. A flight method of the helium-filled plug-in split aircraft according to any one of claims 1 to 8, characterized in that, The steps are as follows: S1: Engines (4) with rotors are arranged around the support frame (1), and an appropriate number of independent helium-filled plug-in row units (3) are installed on the support frame (1) according to the load capacity. S2: Start the engines (4). The aircraft moves upward. During flight, adjust the inclination angle of the independent helium-filled plug-in row unit (3) according to the wind speed and wind direction to make the aircraft fly smoothly. S3: During the descent of the aircraft, adjust the inclination angle of the independent helium-filled plug-in row unit (3) to make the aircraft descend slowly. S4: During the processes of step S2 and step S3, the controller controls the engines (4) and the independent helium-filled plug-in row unit (3) to form an aircraft control system with coupling of plug-in row control and engine control, ensuring the safe flight of the aircraft.

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