Soft oil tank fixing structure for aircraft

Abstract

The utility model discloses a soft oil tank fixing structure for an aircraft, and relates to the technical field of aircrafts. A plurality of buckle belt grooves are formed in each outer wall of the soft oil tank, and each buckle belt groove is of a blind groove structure with an opening in one end; the plurality of first magnetic attraction pieces are accommodated in the corresponding buckle belt grooves in a pluggable manner; the plurality of second magnetic attraction pieces are arranged on the inner wall of the aircraft fuselage and correspond to the first magnetic attraction pieces contained in the buckle belt groove; the at least two bandage fixing mechanisms are arranged in the length direction of the top of the soft oil tank and distributed in the width direction of the top of the soft oil tank at intervals, and the two ends of each bandage fixing mechanism are detachably connected to the fuselage. The structure solves the problems that traditional thread gluing fixing is prone to loosening, a soft oil tank shifts and the oil tank is prone to deformation during installation, and too much dead oil is generated, and has the advantages of being reliable in fixing, good in oil tank size shaping effect, resistant to vibration, convenient to disassemble and assemble and convenient to maintain.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft fuel system, and particularly relates to a soft fuel tank fixing structure for aircraft. BACKGROUND

[0002] In the current situation of continuous expansion of application scenarios of aircraft technology, the performance optimization of the fuel system, as the core part of guaranteeing the continuous flight of the aircraft, is crucial. The soft fuel tank has the advantages of light weight, which can effectively reduce the overall burden of the aircraft to improve flight flexibility; good sealing, which can effectively prevent fuel leakage to ensure flight safety; low cost, which is conducive to reducing the manufacturing and maintenance cost of the aircraft, and has been widely used in the fuel system of the aircraft.

[0003] However, the traditional fixing method of the soft fuel tank is to use nylon straps in combination with nylon Velcro. This scheme has many inherent defects that cannot be ignored. The nylon Velcro is easily detached due to the influence of flight vibration and environmental factors after long-term use, which causes unstable fixing of the soft fuel tank and easy displacement and deformation of the soft fuel tank during flight, and further generates "dead oil" space, reduces the effective fuel load, and seriously restricts the endurance of the aircraft. CONTENT OF THE INVENTION

[0004] The embodiment of the present application provides a soft fuel tank fixing structure for an aircraft, which solves the problems of easy detachment of the traditional Velcro fixing, displacement of the soft fuel tank, and easy deformation of the fuel tank to generate excessive "dead oil".

[0005] The embodiment of the present application provides a soft fuel tank fixing structure for an aircraft, which includes a plurality of buckle strap grooves, a plurality of first magnetic attraction members, a plurality of second magnetic attraction members, and at least two strap fixing mechanisms. Each outer wall of the soft fuel tank is provided with a plurality of buckle strap grooves, and the buckle strap grooves are blind groove structures with one end open. A plurality of first magnetic attraction members are pluggably accommodated in the corresponding buckle strap grooves. A plurality of second magnetic attraction members are arranged on the inner wall of the aircraft fuselage, and correspond to the first magnetic attraction members accommodated in the buckle strap grooves, and are used to be magnetically attracted to the corresponding first magnetic attraction members to adsorb and fix the side surface of the soft fuel tank to the fuselage. At least two strap fixing mechanisms are arranged along the length direction of the top of the soft fuel tank and are distributed at intervals along the width direction of the top of the soft fuel tank. The two ends of each strap fixing mechanism are detachably connected to the fuselage.

[0006] In a possible implementation, when the placement space of the soft fuel tank is a cuboid structure, the plurality of buckle strap grooves are rectangular groove structures and are arranged in a matrix at intervals along the length direction and the height direction of the outer wall of the soft fuel tank. When the placement space of the soft fuel tank is a curved surface structure, the plurality of buckle strap grooves are sheet-shaped groove structures and are uniformly distributed along the circumference of the outer wall of the soft fuel tank to adapt to the curved surface installation.

[0007] In a possible implementation, the binding strap fixing mechanism comprises a nylon binding rope, a sleeve, two hooks and a plurality of fixing buckles; the plurality of fixing buckles are fixedly arranged on the top of the soft fuel tank and are arranged at intervals along the length direction of the soft fuel tank, and the fixing buckles arranged on the two sides of the top of the soft fuel tank are arranged close to the edges thereof; the sleeve passes through each fixing buckle in sequence, and the two ends of the sleeve extend out of the outermost fixing buckles; the two hooks are fixedly arranged on the opposite sides inside the fuselage; one end of the nylon binding rope is detachably connected to one of the hooks, and the other end of the nylon binding rope passes through the sleeve in sequence and is detachably connected to the other hook.

[0008] In a possible implementation, the binding strap fixing mechanism further comprises a tensioning and locking mechanism; the tensioning and locking mechanism is arranged on the top of the soft fuel tank; the sleeve is provided with a breakage at a position corresponding to the tensioning and locking mechanism; the middle section of the nylon binding rope passes through the breakage of the sleeve and is fixedly connected to the tensioning and locking mechanism, and the nylon binding rope can be quickly tensioned or released and locked by operating the tensioning and locking mechanism.

[0009] In a possible implementation, the tensioning and locking mechanism comprises a knob, a rotating disc, a base, a guide tube, a support, an elastic member, a screw rod, two limiting members, two elastic clamping plates, two threading plates and a plurality of connecting pins; the base is installed on the top of the soft oil tank; the middle part of the base is provided with the support; the two elastic clamping plates are oppositely arranged on the top of the support; the two ends of the elastic member are respectively connected to the inner walls of the two elastic clamping plates opposite to each other, for providing elastic force for moving the two elastic clamping plates close to each other; the two limiting members are respectively arranged on the top of the two elastic clamping plates, and the side surfaces opposite to each other of the two limiting members are provided with clamping grooves; the rotating disc is fixedly connected to the bottom of the knob, and the outer wall of the rotating disc is symmetrically fixed with the two threading plates; the threading plates are provided with wire holes for the nylon binding rope to pass through and be fixed; the top of the base is circumferentially provided with the plurality of connecting pins; the rotating disc is circumferentially provided with a plurality of limiting holes matched with the connecting pins; the guide tube penetrates through and is fixed to the center of the rotating disc; the middle part of the knob is provided with a threaded hole; the screw rod is threadedly matched with the threaded hole, and the bottom of the screw rod is provided with a conical structure; the inner diameter of the guide tube is greater than or equal to the maximum span of the two limiting members in the radial direction of the guide tube when the two limiting members are close to each other; wherein the tensioning and locking mechanism has a locking state and an unlocking state: in the unlocking state, the screw rod is driven to move upward, the conical structure is separated from the clamping groove, the two elastic clamping plates are close to each other under the elastic force of the elastic member, the two limiting members are close to each other, and the projection of the limiting member in the direction perpendicular to the axis of the guide tube is located within the projection range of the inner wall of the guide tube; at this time, the knob is lifted upward to drive the rotating disc and the guide tube to move upward, so that the limiting member is at least partially accommodated in the guide tube, and the limiting hole of the rotating disc is separated from the connecting pin on the base, and the knob is rotated to drive the threading plate to rotate, so as to wind up or release the nylon binding rope; in the locking state, the knob is moved downward to drive the rotating disc to move downward until the bottom of the rotating disc abuts against the top of the base, and then the screw rod is driven to move downward, and the conical structure at the bottom of the screw rod abuts against and is pressed into the clamping groove of the two limiting members, so as to force the two limiting members to be far away from each other against the elastic force of the elastic member, until the projection area of the limiting member in the direction perpendicular to the axis of the guide tube at least partially overlaps with the projection area of the guide tube, and the bottom wall of the limiting member abuts against the top wall of the guide tube, to achieve locking.

[0010] In a possible implementation, the tensioning and locking mechanism further comprises two accommodating grooves; the two accommodating grooves are arranged on the outer wall of the threading plate, for placing the wound nylon binding rope.

[0011] In a possible implementation, the aircraft soft fuel tank fixing structure further comprises a measuring unit support supported between the top of the soft fuel tank and the inner wall of the fuselage, and an oil quantity measuring unit for monitoring the oil quantity in the soft fuel tank is installed on the measuring unit support.

[0012] The one or more technical solutions provided in the embodiments of the present application have at least the following technical effects:

[0013] The aircraft soft fuel tank fixing structure provided by the embodiments of the present application comprises a plurality of buckle grooves, a plurality of first magnetic attraction members, a plurality of second magnetic attraction members, and at least two binding belt fixing mechanisms. The installation process of the aircraft soft fuel tank fixing structure is as follows: first, the soft fuel tank is placed in the fuselage of the aircraft after being crumpled; when in use, the front, rear, left and right outer walls of the soft fuel tank are expanded, and each first magnetic attraction member is sequentially embedded in the corresponding buckle groove; then, the soft fuel tank wall surface with the embedded first magnetic attraction member is attached to the inner wall of the fuselage, and the first magnetic attraction member and the second magnetic attraction member are automatically aligned and attracted by magnetic force, thereby realizing reliable fixation of the side surface of the soft fuel tank; finally, the two ends of the at least two binding belt fixing mechanisms are connected with the fuselage, so that the top of the soft fuel tank is flattened and compressed, and the top fixation is completed. Through the synergistic effect of the first magnetic attraction member, the second magnetic attraction member and the binding belt fixing mechanism, a three-dimensional fixing system is constructed: the first magnetic attraction member and the second magnetic attraction member provide uniform attraction force in multiple directions, effectively inhibiting the displacement and deformation of the soft fuel tank caused by flight vibration; the binding belt fixing mechanism further strengthens the stability of the top structure of the soft fuel tank, avoids the generation of “dead oil” space, and guarantees the effective utilization rate of fuel. Therefore, the magnetic attraction connection method of the present application has excellent anti-vibration performance and no risk of loosening in long-term use; the modular design facilitates quick disassembly and assembly, improves maintenance efficiency; the overall structure is lightweight, meets the requirements of the aircraft for the economy of the fuel system, and provides a reliable, stable and easy-to-maintain fixing solution for the soft fuel tank. BRIEF DESCRIPTION OF DRAWINGS

[0014] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed in the description of the embodiments of the present application will be briefly introduced. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor.

[0015] Figure 1 The structural schematic diagram of the aircraft soft fuel tank fixing structure provided by the embodiments of the present application is shown in the figure;

[0016] Figure 2 The structural schematic diagram of the first magnetic attraction member and the second magnetic attraction member provided by the embodiments of the present application is shown in the figure;

[0017] Figure 3This is a schematic diagram of the tensioning and locking mechanism provided in the embodiments of this application;

[0018] Figure 4 This is a schematic diagram of the structure of the rotating disk provided in an embodiment of this application;

[0019] Figure 5 This is a schematic diagram of the structure of the base provided in an embodiment of this application;

[0020] Figure 6 This is a schematic diagram of the screw structure provided in an embodiment of this application;

[0021] Figure 7 This is a schematic diagram of the structure of the limiting member provided in the embodiments of this application;

[0022] Figure 8 This is a schematic diagram of the tensioning locking mechanism provided in the embodiments of this application during unlocking;

[0023] Figure 9 This is a schematic diagram of the tensioning and locking mechanism provided in the embodiments of this application when locked.

[0024] Icons: 1-Soft oil tank; 2-Fastening groove; 3-First magnetic chuck; 4-Second magnetic chuck; 5-Binding strap fixing mechanism; 51-Nylon binding rope; 52-Sleeve; 53-Break; 54-Fixing buckle; 55-Tension locking mechanism; 551-Knob; 552-Rotating disc; 5521-Limiting hole; 553-Base; 554-Guide tube; 555-Support component; 556-Limiting component; 5561-Card slot; 557-Elastic card plate; 558-Wire threading plate; 5581-Wire hole; 559-Connecting pin; 5590-Receiving groove; 5591-Elastic component; 5592-Screw; 55921-Conical structure; 6-Measuring unit bracket; 7-Oil quantity measuring unit. Detailed Implementation

[0025] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0026] In the description of the embodiments of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the embodiments of this application and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. The terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this application according to the specific circumstances.

[0027] This application provides a flexible fuel tank fixing structure for aircraft, such as... Figures 1 to 9 As shown. The aircraft's flexible fuel tank fixing structure includes multiple strap slots 2, multiple first magnetic attractors 3, multiple second magnetic attractors 4, and at least two strap fixing mechanisms 5. Each outer wall of the flexible fuel tank 1 is provided with multiple strap slots 2, and the strap slots 2 are blind slot structures with one open end. Multiple first magnetic attractors 3 are detachably accommodated in the corresponding strap slots 2. Multiple second magnetic attractors 4 are provided on the inner wall of the aircraft fuselage, and they correspond to the first magnetic attractors 3 accommodated in the strap slots 2, and are used to magnetically attract the corresponding first magnetic attractors 3 to magnetically fix the side of the flexible fuel tank 1 to the fuselage. At least two strap fixing mechanisms 5 are arranged along the length direction of the top of the flexible fuel tank 1 and are spaced apart along the width direction of the top of the flexible fuel tank 1. The two ends of each strap fixing mechanism 5 are detachably connected to the fuselage.

[0028] It should be noted that each outer wall of the flexible fuel tank 1 is provided with multiple fastening grooves 2. These fastening grooves 2 are integrally formed with the outer wall of the flexible fuel tank 1 using a heat-sealing process, ensuring connection strength and sealing. The fastening groove 2 is a blind groove structure with a single-end opening. Its inner cavity size is perfectly matched with the first magnetic suction member 3. The interference fit achieves circumferential limiting of the first magnetic suction member 3, preventing displacement of the first magnetic suction member 3 under vibration. The end face of the first magnetic suction member 3 is designed to be flush with the open end face of the fastening groove 2, which ensures the magnetic contact area and avoids interference during installation.

[0029] Multiple second magnetic chucks 4 are bonded to internal structures such as ribs of the aircraft fuselage using high-strength structural adhesive. Their installation positions should maintain a safe distance from the magnetic compass of the flight control system. This distance needs to be calibrated experimentally to ensure that the residual strength of the magnetic field generated by the second magnetic chucks 4 at the magnetic compass is below the allowable threshold of the flight control system, thereby avoiding the impact of magnetic interference on flight attitude control. The first magnetic chuck 3 and the second magnetic chuck 4 are made of weak magnetic materials to further reduce the potential impact of the magnetic field on surrounding electronic equipment while ensuring sufficient attraction force.

[0030] The installation process of the soft fuel tank fixing structure for this aircraft is as follows: First, the soft fuel tank 1 is folded up and placed inside the aircraft fuselage; when in use, the front, rear, left, and right outer walls of the soft fuel tank 1 are opened, and each first magnetic suction piece 3 is sequentially embedded into the corresponding buckle groove 2; then, the wall of the soft fuel tank 1 with the first magnetic suction piece 3 embedded is brought close to the inner wall of the fuselage, and the first magnetic suction piece 3 and the second magnetic suction piece 4 are automatically aligned and attracted by magnetic force, thereby achieving reliable fixation of the side of the soft fuel tank 1; finally, the two ends of at least two strap fixing mechanisms 5 are connected to the fuselage, so that the top of the soft fuel tank 1 is flattened and pressed, completing the top fixation. This design constructs a three-dimensional fixing system through the synergistic action of the first magnetic suction component 3, the second magnetic suction component 4, and the strap fixing mechanism 5. The first magnetic suction component 3 and the second magnetic suction component 4 provide multi-directional uniform adsorption force, effectively suppressing the displacement and deformation of the soft fuel tank 1 caused by flight vibration. The strap fixing mechanism 5 further enhances the stability of the top structure of the soft fuel tank 1, avoids the generation of "dead fuel" space, and ensures efficient fuel utilization. Therefore, the magnetic connection method of this application has excellent vibration resistance and no risk of loosening during long-term use; the modular design facilitates quick assembly and disassembly, improving maintenance efficiency; the overall structure is lightweight, meeting the aircraft's requirements for fuel system economy, and providing a reliable, stable, and easy-to-maintain fixing solution for the soft fuel tank 1.

[0031] In this embodiment, when the placement space of the flexible fuel tank 1 is a cuboid structure, the multiple fastening slots 2 are rectangular slot structures and are arranged in a matrix at intervals along the length and height directions of the outer wall of the flexible fuel tank 1. When the placement space of the flexible fuel tank 1 is a curved structure, the multiple fastening slots 2 are sheet-like groove structures and are evenly distributed along the circumference of the outer wall of the flexible fuel tank 1 to adapt to curved surface installation.

[0032] It should be noted that both schemes utilize the synergistic effect of the fastening groove 2, the first magnetic chuck 3, and the second magnetic chuck 4 to form a fully covered fixing network on the outer wall of the soft fuel tank 1. This ensures that all areas of the soft fuel tank 1 receive balanced and reliable restraint under flight vibration conditions, thereby eliminating fuel retention areas caused by deformation of the soft fuel tank 1 and maximizing fuel space utilization to its theoretical maximum. This design significantly expands the aircraft adaptability of the fixed structure of the soft fuel tank 1, providing a standardized solution for fuel system integration of aircraft with different configurations.

[0033] In this embodiment, the strap fixing mechanism 5 includes a nylon strap 51, a sleeve 52, two hooks, and multiple fixing buckles 54. The multiple fixing buckles 54 are fixedly disposed on the top of the soft fuel tank 1 and spaced apart along its length, with the fixing buckles 54 located on both sides of the top of the soft fuel tank 1 near its edge. The sleeve 52 passes through each fixing buckle 54 in sequence, with both ends extending beyond the outermost fixing buckle 54. The two hooks are fixedly disposed on opposite sides inside the body. One end of the nylon strap 51 is detachably connected to one of the hooks, and the other end passes through the sleeve 52 in sequence and is detachably connected to the other hook.

[0034] It should be noted that when the two ends of the nylon binding rope 51 are detachably connected to the hooks on both sides of the machine body and tension is applied, the tension is evenly transmitted through the sleeve 52 to each of the fixing buckles 54 distributed along the line, thereby forming a continuous and balanced linear pressure distribution band on the top of the soft fuel tank 1. This structure effectively disperses local stress, avoids the stress concentration and surface deformation problems that are easily caused by traditional point fixing, significantly improves the flattening effect and overall fixing tightness of the top of the soft fuel tank 1, and enhances the stability and reliability of the soft fuel tank 1 in a vibration environment.

[0035] Specifically, the nylon lanyard 51 has hooks at both ends. The hooks are closed-loop structures made of spring steel, with elastic locking plates at their openings. When the hooks are engaged with the hooks on the fuselage side, the elastic locking plates automatically reset under the action of the spring force, forming a fully enclosed connecting ring, effectively preventing the risk of disengagement caused by flight vibration.

[0036] In this embodiment, the strap fixing mechanism 5 further includes a tension locking mechanism 55. The tension locking mechanism 55 is disposed on the top of the soft oil tank 1. The sleeve 52 has a break 53 at the position corresponding to the tension locking mechanism 55. The middle section of the nylon strap 51 passes through the break 53, is fixedly connected to the tension locking mechanism 55, and after tension adjustment, is re-entered into the sleeve 52 after the break 53, and finally connected to the hook on the other side.

[0037] In the embodiments of this application, such as Figures 3 to 9As shown. The tensioning and locking mechanism 55 includes a knob 551, a rotating disk 552, a base 553, a guide tube 554, a support member 555, an elastic member 5591, a screw 5592, two limiting members 556, two elastic locking plates 557, two threading plates 558, and multiple connecting pins 559. The base 553 is mounted on the top of the soft oil tank 1. The support member 555 is located in the middle of the base 553. The two elastic locking plates 557 are disposed opposite each other on the top of the support member 555. The two ends of the elastic member 5591 are respectively connected to the inner walls of the two elastic locking plates 557 facing each other, for providing an elastic force to bring the two elastic locking plates 557 closer together. The two limiting members 556 are respectively disposed on the top of the two elastic locking plates 557, and the two limiting members 556 have slots 5561 on their opposite sides. A rotating disk 552 is fixedly connected to the bottom of a knob 551. Two threading plates 558 are symmetrically fixed to the outer wall of the rotating disk 552. Each threading plate 558 has a thread hole 5581 for a nylon binding cord 51 to pass through and be secured. Multiple connecting pins 559 are circumferentially arranged on the top of the base 553. Multiple limiting holes 5521, which mate with the connecting pins 559, are circumferentially arranged on the rotating disk 552. A guide tube 554 passes through and is fixed to the center of the rotating disk 552. A threaded hole is provided in the middle of the knob 551. A screw 5592 is threaded into the threaded hole, and a tapered structure 55921 is provided at the bottom of the screw 5592. The inner diameter of the guide tube 554 is greater than or equal to the maximum span in the radial direction of the guide tube 554 when the two limiting members 556 are close to each other. The tensioning and locking mechanism 55 has a locked state and an unlocked state. In the unlocked state, the operator rotates the screw 5592 to move it upward, causing the cone structure 55921 to disengage from the slot 5561. The two elastic plates 557 move closer to each other under the elastic force of the elastic element 5591, causing the two limiting elements 556 to move closer to each other, so that the projection of the limiting element 556 in the direction perpendicular to the axis of the guide tube 554 is within the projection range of the inner wall of the guide tube 554. At this time, lifting the knob 551 can drive the rotating disk 552 and the guide tube 554 to move upward, so that the limiting element 556 is at least partially accommodated in the guide tube 554. At the same time, the limiting hole 5521 of the rotating disk 552 disengages from the connecting pin 559 on the base 553. Rotating the knob 551 can drive the threading plate 558 to rotate, so as to gather or release the nylon binding rope 51. In the locked state, moving the knob 551 downwards causes the rotating disk 552 to move down until its bottom abuts against the top of the base 553. Then, rotating the screw 5592 in the opposite direction causes it to move downwards. The conical structure 55921 at its bottom abuts against and presses into the slots 5561 of the two limiting members 556, forcing the two limiting members 556 to overcome the elastic force of the elastic member 5591 and open away from each other until the projected area of ​​the limiting member 556 in the direction perpendicular to the axis of the guide tube 554 at least partially coincides with the projected area of ​​the guide tube 554, and the bottom wall of the limiting member 556 abuts against the top wall of the guide tube 554 to achieve locking.

[0038] Specifically, the slot 5561 can be set as an inclined surface corresponding to the conical structure 55921 to facilitate the insertion of the conical structure 55921.

[0039] In this embodiment, the tensioning locking mechanism 55 further includes two receiving slots 5590. The two receiving slots 5590 are disposed on the outer wall of the threading plate 558 and are used to hold the wound nylon binding rope 51. After the nylon binding rope 51 is stored, the overall structure becomes more compact.

[0040] In this embodiment of the application, the aircraft soft fuel tank fixing structure further includes a measuring unit bracket 6 supported between the top of the soft fuel tank 1 and the inner wall of the fuselage, and a fuel quantity measuring unit 7 for monitoring the fuel quantity in the soft fuel tank 1 is installed on the measuring unit bracket 6.

[0041] It should be noted that the key components such as the soft oil tank 1, the buckle groove 2, and the fixing buckle 54 in the embodiments of this application are all made of thermoplastic polyurethane elastomer (TPU).

[0042] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, please refer to each other. Each embodiment focuses on describing the differences from other embodiments.

[0043] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of this application.

Claims

1. A flexible fuel tank fixing structure for aircraft, characterized in that, It includes multiple buckle slots (2), multiple first magnetic attractors (3), multiple second magnetic attractors (4), and at least two strap fixing mechanisms (5); Each outer wall of the soft oil tank (1) is provided with a plurality of the buckle grooves (2), and the buckle grooves (2) are blind groove structures with one end open; Multiple first magnetic elements (3) are detachably accommodated in the corresponding buckle slots (2); Multiple second magnetic components (4) are disposed on the inner wall of the aircraft fuselage and correspond to the first magnetic component (3) housed in the buckle groove (2) for magnetic attraction with the corresponding first magnetic component (3) to adsorb and fix the side of the soft fuel tank (1) to the fuselage. At least two of the strap fixing mechanisms (5) are arranged along the length direction of the top of the soft oil tank (1) and are spaced apart along the width direction of the top of the soft oil tank (1). The two ends of each strap fixing mechanism (5) are detachably connected to the body.

2. The aircraft soft fuel tank fixing structure according to claim 1, characterized in that, When the placement space of the soft oil tank (1) is a cuboid structure, the multiple buckle slots (2) are rectangular slot structures and are arranged in a matrix at intervals along the length and height directions of the outer wall of the soft oil tank (1). When the placement space of the soft oil tank (1) is a curved structure, the multiple buckle grooves (2) are sheet-like groove structures and are evenly distributed along the circumference of the outer wall of the soft oil tank (1) to adapt to curved installation.

3. The aircraft soft fuel tank fixing structure according to claim 1, characterized in that, The strap fixing mechanism (5) includes a nylon strap (51), a sleeve (52), two hooks and multiple fixing buckles (54); Multiple fixing buckles (54) are fixedly disposed on the top of the soft oil tank (1) and spaced apart along its length. The fixing buckles (54) located on both sides of the top of the soft oil tank (1) are arranged close to its edge. The sleeve (52) passes through each of the fixing buckles (54) in sequence, and its two ends extend beyond the outermost fixing buckle (54); The two hooks are fixedly installed on opposite sides inside the body; One end of the nylon cord (51) is detachably connected to one of the hooks, and the other end passes through the sleeve (52) and is detachably connected to the other hook.

4. The aircraft soft fuel tank fixing structure according to claim 3, characterized in that, The strap fixing mechanism (5) also includes a tensioning locking mechanism (55); The tensioning locking mechanism (55) is located on the top of the soft oil tank (1); The sleeve (52) has a break (53) at a position corresponding to the tensioning locking mechanism (55); The middle section of the nylon binding rope (51) passes through the break (53) of the sleeve (52) and is fixedly connected to the tensioning and locking mechanism (55). By operating the tensioning and locking mechanism (55), the nylon binding rope (51) can be quickly tensioned or released and locked.

5. The aircraft soft fuel tank fixing structure according to claim 4, characterized in that, The tensioning and locking mechanism (55) includes a knob (551), a rotating disk (552), a base (553), a guide tube (554), a support (555), an elastic element (5591), a screw (5592), two limiting elements (556), two elastic locking plates (557), two threading plates (558), and multiple connecting pins (559). The base (553) is mounted on top of the soft oil tank (1); The support member (555) is provided in the middle of the base (553); The two elastic plates (557) are disposed opposite to each other on the top of the support (555); The two ends of the elastic element (5591) are respectively connected to the inner walls of the two elastic plates (557) facing each other, and are used to provide an elastic force that brings the two elastic plates (557) closer to each other. The two limiting members (556) are respectively disposed on the top of the two elastic plates (557), and the two limiting members (556) are provided with slots (5561) on their opposite sides. The rotating disk (552) is fixedly connected to the bottom of the knob (551), and two threading plates (558) are symmetrically fixed on the outer wall of the rotating disk (552); the threading plate (558) is provided with a thread hole (5581) for the nylon binding rope (51) to pass through and be fixed. The base (553) is provided with the plurality of connecting pins (559) around its top circumference. The rotating disk (552) is provided with a plurality of limiting holes (5521) in the circumferential direction that are adapted to the connecting pin (559). The guide tube (554) passes through and is fixed at the center of the rotating disk (552); The knob (551) has a threaded hole in the middle; the screw (5592) is threaded into the threaded hole, and the bottom of the screw (5592) has a conical structure (55921). The inner diameter of the guide tube (554) is greater than or equal to the maximum span in the radial direction of the guide tube (554) when the two limiting members (556) are close to each other; The tensioning locking mechanism (55) has a locked state and an unlocked state: In the unlocked state, the drive screw (5592) moves upward, the cone structure (55921) disengages from the slot (5561), and the two elastic plates (557) move closer to each other under the elastic force of the elastic member (5591), causing the two limiting members (556) to move closer to each other, so that the projection of the limiting member (556) in the direction perpendicular to the axis of the guide tube (554) is located within the projection range of the inner wall of the guide tube (554). At this time, lifting the knob (551) upwards can drive the rotating disk (552) and the guide tube (554) to move upwards, so that the limiting member (556) is at least partially accommodated in the guide tube (554). At the same time, the limiting hole (5521) of the rotating disk (552) is disengaged from the connecting pin (559) on the base (553). Rotating the knob (551) can drive the threading plate (558) to rotate, so as to gather or release the nylon binding rope (51). In the locked state, moving the knob (551) downward causes the rotating disk (552) to move down until its bottom abuts against the top of the base (553). Then, the screw (5592) is driven to move downward, and the cone structure (55921) at its bottom abuts against and presses into the slots (5561) of the two limiting members (556), forcing the two limiting members (556) to overcome the elastic force of the elastic member (5591) and open away from each other until the projected area of ​​the limiting member (556) in the direction perpendicular to the axis of the guide tube (554) at least partially coincides with the projected area of ​​the guide tube (554), and the bottom wall of the limiting member (556) abuts against the top wall of the guide tube (554) to achieve locking.

6. The aircraft soft fuel tank fixing structure according to claim 5, characterized in that, The tensioning locking mechanism (55) also includes two receiving grooves (5590); Two receiving slots (5590) are provided on the outer wall of the threading plate (558) for placing the wound nylon binding rope (51).

7. The aircraft soft fuel tank fixing structure according to claim 1, characterized in that, It also includes a measuring unit bracket (6) supported between the top of the soft oil tank (1) and the inner wall of the fuselage, and an oil quantity measuring unit (7) for monitoring the oil quantity in the soft oil tank (1) is installed on the measuring unit bracket (6).

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