Fuel tank anti-slosh assembly and gyroplane

Abstract

The utility model discloses a kind of fuel tank anti-shaking assembly and gyroplane, including tank seat, two groups of baffle are fixed in the inner wall of oil tank two sides respectively, fixed connection is realized between the two through connecting plate, and still several groups of reinforcing ribs are fixed between baffle and connecting plate, these reinforcing ribs, baffle and connecting plate form stable triangle structure together, triangle structure itself has excellent mechanical stability, can greatly enhance the structural strength and anti-deformation ability of reinforcing baffle assembly whole, effectively solve the problem that baffle is separately connected in prior art and is deformed by fuel impact, simultaneously, several groups of through slot, which are opened on connecting plate, can play certain buffer and flow guiding effect on fuel shaking under the premise of not affecting normal fuel flow, reduce the direct impact degree of fuel shaking on baffle, further improve anti-shaking effect, ensure the stable operation of fuel tank in gyroplane flight process.

Description

Technical Field

[0001] This utility model relates to the field of aircraft component technology, specifically a fuel tank anti-sway component and a rotorcraft. Background Technology

[0002] In aircraft, especially in aircraft like gyroplanes where flight stability and safety are extremely important, the design of the fuel tank directly affects the overall performance of the aircraft. Gyroplanes, with their vertical take-off and landing capabilities and low-altitude, low-speed flight characteristics, are widely used in emergency rescue, aerial patrol, agricultural operations and other scenarios. During the flight of a gyroplane, the fuel in the fuel tank will shake violently due to airflow disturbances, maneuvering (such as turning, pitching and tilting) and attitude changes during take-off and landing.

[0003] In the prior art, fuel tanks are usually equipped with baffles to suppress fuel sloshing. The baffles are usually individually connected to the inner wall of the fuel tank. During long-term use, the baffles are prone to deformation due to fuel impact. Therefore, we need to propose a fuel tank anti-sloshing component and a rotorcraft. Utility Model Content

[0004] The purpose of this utility model is to provide a fuel tank anti-sway component and a rotorcraft. By setting two sets of partitions, connecting plates and several sets of reinforcing ribs to form a stable triangular structure, and opening through grooves on the connecting plates, the structural strength and deformation resistance of the reinforced partition component are enhanced, the fuel is buffered and guided to reduce impact, the anti-sway effect is improved and the stable operation of the fuel tank is ensured, thereby solving the problems mentioned in the background art.

[0005] To achieve the above objectives, this utility model provides the following technical solution: A fuel tank anti-sway assembly includes: a fuel tank base, in which a fuel tank is fixedly embedded, and a reinforcing baffle assembly is provided inside the fuel tank; the reinforcing baffle assembly includes two sets of baffles, which are respectively fixedly connected to the inner walls of the two sides of the fuel tank, and a connecting plate is fixedly connected between the two sets of baffles, and a plurality of reinforcing ribs are fixedly connected between the two sets of baffles and the connecting plate, forming a stable triangular structure between the reinforcing ribs, baffles and connecting plate, and a plurality of through grooves are provided on the connecting plate.

[0006] Preferably, both sets of partitions have oil-absorbing grooves, and the inside of the oil-absorbing grooves is provided with special sponge blocks.

[0007] Preferably, a double-layer isolation net is fixedly embedded inside the oil passage, and the special sponge block is disposed between the double-layer isolation net.

[0008] Preferably, the tank also includes a level gauge, which is fixedly installed on the top of the tank, and the probe of the level gauge is located inside the tank.

[0009] Preferably, an oil injection pipe is fixedly connected to one side wall of the oil tank, and an oil outlet pipe is fixedly connected to the bottom of the oil tank.

[0010] Preferably, the oil outlet pipe includes an oil collecting hopper, which is fixedly connected to the bottom of the oil tank. A connecting pipe is fixedly connected to the bottom of the oil collecting hopper, and a filter screen is fixedly connected to the top opening of the oil collecting hopper.

[0011] Preferably, it also includes an active heating component for preheating the oil inside the tank, the active heating component being disposed on one side of the tank base.

[0012] Preferably, the active heating component includes a mounting shell, which is fixedly connected to one side wall of the oil tank base. Two sets of fans are fixedly installed inside the mounting shell. An electric heating box is fixedly connected to one side wall of the mounting shell. Conveying pipes are fixedly connected to the air outlets on both sides of the mounting shell. An air outlet cover is fixedly connected to one end of each of the two sets of conveying pipes.

[0013] Preferably, the two side walls of the fuel tank seat are respectively provided with mounting grooves that are adapted to the air outlet cover, and the air outlet cover is fixedly embedded in the mounting groove.

[0014] A gyroplane includes a fuel tank anti-sway assembly and a gyroplane body. The top of the gyroplane body is provided with a rotor support beam, the top of the rotor support beam is equipped with a rotor head, the rotor head is provided with a rotor, and the bottom of the gyroplane body is provided with landing gear.

[0015] Compared with the prior art, the beneficial effects of this utility model are: The design of this reinforced baffle assembly is particularly crucial. Two sets of baffles are fixed to the inner walls of both sides of the fuel tank, and the two are fixedly connected by a connecting plate. Several sets of reinforcing ribs are also fixed between the baffles and the connecting plate. These reinforcing ribs, baffles, and connecting plates together form a stable triangular structure. The triangular structure itself has excellent mechanical stability, which can greatly enhance the overall structural strength and deformation resistance of the reinforced baffle assembly. This effectively solves the problem that baffles connected alone in the prior art are easily deformed by fuel impact. At the same time, several sets of through grooves opened on the connecting plate can buffer and guide the fuel sloshing without affecting the normal flow of fuel, reducing the direct impact of fuel sloshing on the baffle, further improving the anti-sloshing effect, and ensuring the stable operation of the fuel tank during rotorcraft flight. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the structure of the fuel tank and fuel tank base of this utility model; Figure 2This is a schematic diagram of the active heating component of this utility model; Figure 3 This is a schematic diagram of the internal structure of the fuel tank of this utility model; Figure 4 This is a schematic diagram of the structure of the reinforced partition assembly of this utility model; Figure 5 This is a schematic diagram of the oil outlet pipe of this utility model; Figure 6 This is a schematic diagram of the rotorcraft of this utility model.

[0017] In the diagram: 1. Fuel tank base; 2. Fuel tank; 3. Reinforced partition assembly; 301. Partition; 302. Connecting plate; 303. Reinforcing rib; 304. Through groove; 4. Oil passage groove; 5. Double-layer isolation net; 6. Liquid level gauge; 7. Oil injection pipe; 8. Oil outlet pipe; 801. Oil collection hopper; 802. Connecting pipe; 803. Filter screen; 9. Active heating assembly; 901. Mounting shell; 902. Fan; 903. Electric heating box; 904. Conveying pipe; 905. Air outlet cover; 10. Rotor body; 11. Rotor support beam; 12. Rotor head; 13. Rotor; 14. Landing gear. Detailed Implementation

[0018] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0019] Please see Figure 1-6This utility model provides a fuel tank anti-sway component, comprising: a fuel tank base 1, in which a fuel tank 2 is fixedly embedded; a reinforcing baffle assembly 3 is provided inside the fuel tank 2; the reinforcing baffle assembly 3 includes two sets of baffles 301, which are respectively fixedly connected to the inner walls of both sides of the fuel tank 2; a connecting plate 302 is fixedly connected between the two sets of baffles 301; and several sets of reinforcing ribs 303 are fixedly connected between the two sets of baffles 301 and the connecting plate 302. The reinforcing ribs 303, baffles 301, and connecting plate 302 form a stable triangular structure; and several sets of through grooves 304 are provided on the connecting plate 302. By setting the fuel tank base 1 to fix the fuel tank 2, the triangular structure of the baffles 301, connecting plate 302, reinforcing ribs 303, and through grooves 304 on the connecting plate 302, the internal structural stability of the fuel tank 2 is enhanced, the resistance to fuel impact deformation is improved, and the effect of buffering and guiding fuel swaying is achieved. The triangular structure design makes full use of mechanical properties. Compared with the traditional single baffle, it can distribute the force generated by fuel impact more evenly to the entire reinforced baffle assembly 3. The size and distribution of the through groove 304 can be adapted and adjusted according to the actual volume of the fuel tank 2 and the common intensity of fuel sloshing.

[0020] Both sets of baffles 301 have oil passage grooves 4, and special sponge blocks are installed inside the oil passage grooves 4. By setting up the oil passage grooves 4 and special sponge blocks, the flow of fuel between the two sets of baffles 301 is ensured, while the elasticity of the special sponge blocks buffers the fuel impact, further reducing the sloshing energy. The special sponge blocks are made of oil-resistant and aging-resistant materials with optimized porosity. They allow fuel to pass smoothly while absorbing a large amount of sloshing energy through their own compression deformation during fuel impact, and maintain good elasticity even after long-term use.

[0021] A double-layered isolation mesh 5 is fixedly embedded inside the oil passage 4, with a special sponge block positioned between the two layers of isolation mesh 5. By using the double-layered isolation mesh 5, the position of the special sponge block is firmly restrained, preventing it from shifting or deforming due to long-term fuel sloshing, thus ensuring a continuous and effective cushioning effect. The double-layered isolation mesh 5 is made of high-strength metal, with a reasonably sized mesh that neither obstructs fuel flow through the oil passage 4 nor fails to reliably limit the movement of the special sponge block. The upper isolation mesh prevents the sponge block from moving upwards, while the lower isolation mesh prevents it from sinking to the bottom of the oil passage 4 under fuel impact.

[0022] It also includes a level gauge 6, which is fixedly installed on the top of the fuel tank 2, with its probe located inside the fuel tank 2. By setting up the level gauge 6 and its probe extending into the fuel tank 2, the fuel level in the fuel tank 2 can be monitored in real time, providing accurate data support for the rotorcraft's fuel management. The level gauge 6 can be a high-precision electronic level gauge, and its probe is made of corrosion-resistant material, which can adapt to the fuel environment inside the fuel tank 2. The monitored level data can be transmitted to the rotorcraft's cockpit instrument panel in real time, allowing the pilot to easily monitor the remaining fuel level.

[0023] A fuel filler pipe 7 is fixedly connected to one side wall of fuel tank 2, and a fuel outlet pipe 8 is fixedly connected to the bottom of fuel tank 2. By setting up the fuel filler pipe 7 and the fuel outlet pipe 8, it is possible to conveniently add fuel to fuel tank 2 while ensuring a stable fuel output to the engine fuel supply system. The end of the fuel filler pipe 7 can be equipped with a suitable sealing cap to prevent fuel from overflowing due to shaking during flight. The connection between the fuel outlet pipe 8 and fuel tank 2 adopts a sealed structure to prevent fuel leakage and ensure the safety and reliability of fuel delivery.

[0024] The fuel outlet pipe 8 includes a fuel collection hopper 801, which is fixedly connected to the bottom of the fuel tank 2. A connecting pipe 802 is fixedly connected to the bottom of the fuel collection hopper 801, and a filter screen 803 is fixedly connected to the top opening of the fuel collection hopper 801. By setting up the fuel collection hopper 801, connecting pipe 802, and filter screen 803, the fuel at the bottom of the fuel tank 2 is efficiently collected to reduce residue, while impurities in the fuel are filtered to prevent them from entering the engine and affecting its normal operation. The fuel collection hopper 801 is funnel-shaped, which can maximize the collection of fuel in the fuel tank 2 to the fuel outlet pipe 8, reducing the amount of fuel residue at the bottom of the fuel tank 2. The filter screen 803 can be disassembled for cleaning or replacement periodically to ensure its long-term stable filtration effect.

[0025] It also includes an active heating component 9 for preheating the fuel inside the fuel tank 2, which is located on one side of the fuel tank base 1. By installing the active heating component 9, preheating of the fuel inside the fuel tank 2 is achieved in low-temperature environments, reducing fuel viscosity, ensuring fuel flowability, and preventing fuel supply problems caused by low temperatures. The active heating component 9 can automatically start and stop according to the temperature of the fuel inside the fuel tank 2. It starts heating when the fuel temperature is lower than a set value and stops heating when a suitable temperature is reached, ensuring both effective preheating and avoiding energy waste.

[0026] The active heating component 9 includes a mounting housing 901, which is fixedly connected to one side wall of the fuel tank 1. Two sets of fans 902 are fixedly installed inside the mounting housing 901. An electric heating box 903 is fixedly connected to one side wall of the mounting housing 901. Delivery pipes 904 are fixedly connected to the air outlets on both sides of the mounting housing 901, and one end of each delivery pipe 904 is fixedly connected to an air outlet hood 905. By configuring the mounting housing 901, fans 902, electric heating box 903, delivery pipes 904, and air outlet hoods 905, a hot airflow is generated and directionally delivered to the area around the fuel tank 2, achieving uniform heating of the fuel. Simultaneous operation of the two sets of fans 902 improves the efficiency of hot airflow delivery. The heating power of the electric heating box 903 can be adjusted according to actual preheating requirements. The delivery pipes 904 are made of heat-insulating material to reduce heat loss during delivery.

[0027] The oil tank base 1 has mounting grooves on both side walls that fit the air outlet shroud 905, which is then fixedly embedded inside the mounting grooves. By setting the mounting grooves that fit the air outlet shroud 905 and fixing the air outlet shroud 905, the hot airflow is precisely applied to the side wall of the oil tank 2, improving heating efficiency and reducing heat loss. The air outlet shroud 905 and the mounting grooves are sealed to prevent hot airflow from escaping through gaps. At the same time, the air outlet of the air outlet shroud 905 faces the side wall of the oil tank 2, allowing the hot airflow to exchange heat more directly with the oil tank 2.

[0028] This utility model also provides a gyroplane, including a fuel tank anti-sloshing component, and further comprising: a gyroplane body 10, a rotor support beam 11 on the top of the gyroplane body 10, a rotor head 12 mounted on the top of the rotor support beam 11, a rotor 13 mounted on the rotor head 12, and a landing gear 14 mounted on the bottom of the gyroplane body 10. By integrating the fuel tank anti-sloshing component, rotor 13, landing gear 14, and other structures onto the gyroplane, the stability of the fuel system of the gyroplane under various flight attitudes is improved, the impact of fuel sloshing on the center of gravity of the entire aircraft is reduced, and flight safety is ensured. The installation position of the fuel tank anti-sloshing component on the gyroplane body 10 is optimized to be compatible with the overall structure of the gyroplane, will not adversely affect the aerodynamic performance of the gyroplane, and its weight is controlled within a reasonable range, meeting the load requirements of the gyroplane.

[0029] Working Principle: When the fuel tank anti-sloshing component is working, the fuel tank seat 1 provides stable support and fixation for the fuel tank 2, preventing displacement of the fuel tank 2 due to airframe swaying during rotorcraft flight. In the reinforced baffle assembly 3 inside the fuel tank 2, the triangular structure formed by the baffle 301, connecting plate 302, and reinforcing rib 303 constitutes a rigid frame that can directly withstand and disperse the impact force generated by fuel sloshing, effectively resisting deformation. The through-slot 304 on the connecting plate 302 allows fuel to flow between different areas, while also guiding and buffering the fuel flow. The oil passage groove 4 on the baffle 301, in conjunction with the internal special sponge block, further absorbs the fuel sloshing energy through the elastic deformation of the sponge block, weakening the sloshing intensity. The double-layer isolation net 5 confines the special sponge block to a fixed position within the oil passage groove 4, ensuring its continuous buffering function.

[0030] The fuel level gauge 6 detects the fuel level in real time via a probe inserted into the fuel tank 2 and feeds the data back to the relevant control system for real-time monitoring of fuel quantity. The fuel filling pipe 7 is used to add fuel to the fuel tank 2, while the fuel outlet pipe 8 delivers the fuel from the fuel tank 2 to the engine. The fuel collection hopper 801 collects fuel from the bottom of the fuel tank 2 to reduce residue, and the filter screen 803 filters impurities in the fuel to ensure that the fuel delivered to the engine is clean.

[0031] When in a low-temperature environment, the active heating component 9 is activated, and the fan 902 inside the mounting housing 901 works to draw in the heat generated by the electric heating box 903. Then, the hot airflow is delivered to the air outlet hood 905 through the delivery pipe 904. The air outlet hood 905 is embedded in the mounting groove of the fuel tank seat 1 and blows the hot airflow in a direction toward the side wall of the fuel tank 2 to heat the fuel in the fuel tank 2, reduce the fuel viscosity, and ensure its fluidity.

[0032] When this component is applied to a rotorcraft, the above-mentioned structural parts work together to effectively suppress the violent sloshing of fuel in the fuel tank 2 when the rotorcraft is performing maneuvers such as turning and pitching or encountering airflow disturbances. This reduces the impact of fuel sloshing on the structure of the fuel tank 2 and the interference with the overall center of gravity of the rotorcraft. Together with the lift provided by the rotor 13 and the takeoff and landing stability ensured by the landing gear 14, they jointly ensure that the rotorcraft can operate stably and safely.

[0033] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A fuel tank anti-sway component, characterized in that, include: The fuel tank holder has a fuel tank fixedly installed inside, and the fuel tank is equipped with a reinforcing baffle assembly inside. The reinforced baffle assembly includes two sets of baffles, which are fixedly connected to the inner walls of both sides of the oil tank. A connecting plate is fixedly connected between the two sets of baffles, and several sets of reinforcing ribs are fixedly connected between the two sets of baffles and the connecting plate. The reinforcing ribs, baffles and connecting plate form a stable triangular structure. Several sets of through grooves are provided on the connecting plate.

2. The fuel tank anti-sway assembly according to claim 1, characterized in that: Both sets of partitions have oil passage grooves, and the inside of the oil passage grooves is equipped with special sponge blocks.

3. The fuel tank anti-sway assembly according to claim 2, characterized in that: The inside of the oil trough is fixedly fitted with a double-layer isolation net, and a special sponge block is placed between the double-layer isolation net.

4. The fuel tank anti-sway assembly according to claim 1, characterized in that: It also includes a level gauge, which is fixedly installed on the top of the tank, with the probe of the level gauge located inside the tank.

5. A fuel tank anti-sway assembly according to claim 1, characterized in that: An oil filling pipe is fixedly connected to one side wall of the oil tank, and an oil outlet pipe is fixedly connected to the bottom of the oil tank.

6. A fuel tank anti-sway assembly according to claim 5, characterized in that: The oil outlet pipe includes an oil collection hopper, which is fixedly connected to the bottom of the oil tank. A connecting pipe is fixedly connected to the bottom of the oil collection hopper, and a filter screen is fixedly connected to the top opening of the oil collection hopper.

7. A fuel tank anti-sway assembly according to claim 1, characterized in that: It also includes an active heating component for preheating the oil inside the tank, which is located on one side of the tank base.

8. A fuel tank anti-sway assembly according to claim 7, characterized in that: The active heating component includes a mounting housing, which is fixedly connected to one side wall of the oil tank base. Two sets of fans are fixedly installed inside the mounting housing. An electric heating box is fixedly connected to one side wall of the mounting housing. Delivery pipes are fixedly connected to the air outlets on both sides of the mounting housing. An air outlet cover is fixedly connected to one end of each of the two delivery pipes.

9. A fuel tank anti-sway assembly according to claim 8, characterized in that: The two side walls of the fuel tank are respectively provided with mounting grooves that are compatible with the air outlet cover, and the air outlet cover is fixedly embedded in the mounting groove.

10. A rotorcraft comprising the fuel tank anti-sway assembly as described in any one of claims 1-9, characterized in that, Also includes: The gyroplane body has a rotor support beam on top, a rotor head mounted on top of the rotor support beam, a rotor on the rotor head, and landing gear at the bottom of the gyroplane body.

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