CN116119015B

CN116119015B - Fuel tank for adapting overturning flight for aircraft

Info

Publication number: CN116119015B
Application number: CN202310406280.5A
Authority: CN
Inventors: 黄厚龙
Original assignee: Jiangsu Suguang Auto Parts Co ltd
Current assignee: Jiangsu Suguang Auto Parts Co ltd
Priority date: 2023-04-17
Filing date: 2023-04-17
Publication date: 2023-07-14
Anticipated expiration: 2043-04-17
Also published as: CN116119015A

Abstract

The invention discloses a fuel tank for an aircraft, which is suitable for overturning and flying, and relates to the technical field of aircraft movement. According to the invention, when the aircraft turns over, the conical rod is enabled to be inert and not to move, the ratchet wheel component formed by the pole and the toothed ring follows the turn over, the toothed ring in the ratchet wheel component is just supported by one corner of the v-shaped frame when the toothed ring turns over anticlockwise, the toothed ring drives the pole and the central shaft to rotate along with the increase of the turn over angle, the conical rod swings back and forth, torsional force is periodically applied to the air inlet component, the relative movement when the aircraft turns over is utilized, air is injected into the air bag expansion component, the air bag expansion component is inflated and exhausted, and the problem of 'surge' caused by insufficient fuel quantity feeding when the aircraft turns over is solved.

Description

Fuel tank for adapting overturning flight for aircraft

Technical Field

The invention relates to the technical field of aircraft movement, in particular to a fuel tank for an aircraft, which is suitable for overturning and flying.

Background

An aircraft is an instrument that flies in an intra-atmosphere or an extra-atmosphere space. Aircraft fall into three categories: aircraft, spacecraft, rockets, and missiles. Aircraft, such as balloons, airships, aircraft, etc., flying in the atmosphere, while existing aircraft, such as fighter aircraft and helicopters, require fuel as a source of power and therefore fuel tanks, which are used by different types and sizes of aircraft.

As disclosed in chinese patent CN104210355a, a flame-retardant and explosion-proof fuel tank for a fuel-fired aircraft comprises a tank body, wherein a partition board is arranged in a cavity inside the tank body for dividing the cavity into a first cavity and a second cavity which are mutually communicated, and an explosion-proof grille is arranged in the first cavity for dividing the first cavity into a plurality of mutually communicated subchambers; a fuel pump is arranged in the second cavity and used for conveying oil to the engine; the box body is provided with an oil inlet communicated with the first cavity and an oil outlet communicated with an oil pump in the second cavity; and a through hole penetrating through the explosion-proof grille is formed right below the oil inlet, a metal chain is arranged in the through hole, and one end of the metal chain is connected with the oil tank cover of the oil inlet so as to be electrically communicated with the tank body.

However, in the prior art, when the flying is in high-difficulty actions such as head lifting and overturning, the flow field changes, and the air quantity entering the engine is unstable. At this time, the engine will generate a surge phenomenon, as is commonly understood, like the asthma patient, the engine will generate strong mechanical vibration and overtemperature, causing equipment damage, while the surge method, such as adding a jet pipe and an additional control mechanism to jet and stabilize the flow field in time, or reducing the fuel adaptation flow field change, etc., wherein the surge phenomenon is caused by not sucking enough air in time by the turbine engine, but the fuel tank is in a state of mixing the fuel and the air, the fuel is overturned in the fuel tank in the process of overturning the aircraft, causing the fuel and the air in the fuel outlet pipe to be in a mixed state, and not enough fuel enters the engine, so that the power cannot meet the expected requirement.

Disclosure of Invention

The invention aims to provide a fuel tank for an aircraft, which is suitable for overturning and flying, so as to solve the problem that when the aircraft makes high-difficulty actions such as head lifting and overturning, the flow field changes, and the air quantity entering an engine is unstable. At this time, the engine will generate a surge phenomenon, as is commonly understood, like the asthma patient, the engine will generate strong mechanical vibration and overtemperature, causing equipment damage, and the surge method, such as adding a jet pipe and an additional control mechanism to jet and stabilize a flow field in time, or reducing the variation of fuel adaptive flow field, etc., wherein the surge phenomenon is caused by not sucking enough air in time by the turbine engine, but the fuel tank is in a state of mixing the fuel and the air, and the fuel is overturned in the fuel tank in the process of overturning the aircraft, so that the fuel and the air are mixed in the fuel outlet pipe, and the fuel does not enter the engine in a sufficient quantity, so that the power cannot meet the expected requirement.

In order to achieve the above purpose, the present invention provides the following technical solutions: the fuel tank comprises a fuel filling pipe, a first exhaust pipe, a second exhaust pipe, a first filter flask, an oil outlet pipe and a fuel tank body, wherein the upper side of the fuel tank body is fixedly connected with the lower end of the fuel filling pipe, the lower end of the first exhaust pipe and the lower end of the second exhaust pipe, and valves are respectively arranged at the lower ends of the fuel filling pipe, the first exhaust pipe and the second exhaust pipe; one end of the fuel tank body is fixedly connected with one end of the oil outlet pipe, the other end of the inside of the fuel tank body is fixedly connected with an air injection internal support mechanism, the air injection internal support mechanism comprises an air bag expansion assembly, the air bag expansion assembly comprises a fixed plate, one side of the fixed plate is fixedly connected with a folding air bag, the other side of the folding air bag is fixedly connected with a movable plate, the outer side of the movable plate is fixedly connected with a sealing ring, the outer side of the fixed plate is fixedly connected with the inner wall of the fuel tank body, and the outer side of the sealing ring is in sliding clamping connection with the inner wall of the fuel tank body; the middle part fixedly connected with subassembly that admits air of fixed plate, the one end fixedly connected with of subassembly that admits air is from the pendulum subassembly, it includes the toper stick to certainly pendulum the subassembly, the upside fixedly connected with shape frame of toper stick, shape frame's inner chamber bottom fixedly connected with frustum, shape frame's middle part activity joint has v shape frame, v shape frame's lower extreme one side with frustum's outside overlap joint, shape frame's upper end inside rotation is connected with the pole, the outside fixed joint of pole has the ring gear, the ring gear is located shape frame's upper end middle part, the other end fixed joint of pole has square post.

Preferably, the other end of the square column is fixedly clamped with a central shaft, and the other end of the central shaft is movably clamped with a branch column shell.

Preferably, a plurality of cylindrical grooves are formed in the branch column casing, and piston columns are slidably clamped on the inner walls of the cylindrical grooves.

Preferably, the other end of each piston column is movably connected with a connecting sleeve, and the other ends of the connecting sleeves are fixedly connected with hemispherical blocks.

Preferably, the other end of the hemispherical block is movably connected with a movable column, and the middle part of the outer surface of the central shaft is rotationally connected with a mounting cover.

Preferably, two groups of special-shaped holes are formed in the mounting cover, an inner cavity shell is fixedly connected to the other side of the mounting cover through bolts, and the upper side of the outer surface of the inner cavity shell is fixedly connected with the top surface of the inner cavity of the fuel tank body.

Preferably, one end of the inner cavity shell is rotationally connected with one end of the branch column shell, and a roller bearing is fixedly arranged at the other end of the branch column shell.

Preferably, the outside of roller bearing with the inner chamber other end fixed mounting of inner chamber shell, the other end inner chamber of inner chamber shell with the surface slip joint of removal post, the lower extreme threaded connection of removal post has the adjusting knob, the upper end of adjusting knob with the surface downside of inner chamber shell rotates and is connected.

Preferably, the inner wall threaded connection in one of the dysmorphism hole has the second solenoid valve, the other end fixedly connected with second filter flask of second solenoid valve, the other end of second filter flask with fuel tank body through connection.

Preferably, the inner wall thread of the other special-shaped hole is connected with a first electromagnetic valve, the other end of the first electromagnetic valve is fixedly connected with a gas output pipe, and the other end of the gas output pipe is connected with the middle part of the fixing plate in a penetrating way.

Compared with the prior art, the invention has the beneficial effects that:

1. according to the invention, the self-swinging assembly is arranged, particularly when an aircraft turns over, fuel oil and air in the fuel tank body and the fuel oil and air in the fuel tank body are turned over, the -shaped frame is not integrally connected with the post rod all the time, the conical rod is inertially and fixedly connected with the post rod, the ratchet wheel component formed by the post rod and the toothed ring follows the turn over, so that a fan-shaped turn over motion with a certain angle is formed between the ratchet wheel component and the conical rod, the ratchet wheel component turns over anticlockwise, the v-shaped frame is arranged under the side top of the frustum, only can rotate clockwise in the -shaped frame, the toothed ring in the ratchet wheel component is just supported by one corner of the v-shaped frame when the toothed ring turns anticlockwise, the tangential force of the toothed ring becomes larger along with the turn over angle, the toothed ring drives the post rod to rotate in the mounting cover along with the back and forth swinging of the conical rod, the torsional force is periodically applied to the central shaft, and the relative motion during the aircraft turn over is utilized, the air is injected into the air for the air bag expansion assembly, and the problem of insufficient fuel oil feeding during turn over is solved.

2. According to the invention, the air bag expansion assembly is arranged, and as the air is continuously injected into the folding air bag, the folding air bag expands according to the preset folding trace, after the air is expanded, the moving plate is pushed, the moving plate is forced to drive the sealing ring at the outer side to be attached to the inner wall of the fuel tank body to move, at the moment, the valve at the lower end of the second exhaust pipe is opened, the sealing ring and the moving plate push the fuel in the fuel tank body to compress the space in the fuel tank body at the moment, the air in the fuel tank body is compressed and discharged from the second exhaust pipe, the space occupied by the fuel is also reduced, at the moment, the fuel also sequentially enters the engine from the oil outlet pipe and the first filter flask, and when the fuel is overturned, the air quantity entering the oil outlet pipe is sharply reduced, the fuel quantity is increased compared with the former fuel quantity, the phenomenon of 'surging' of the engine caused by insufficient fuel quantity feeding when the aircraft overturns is reduced, and the overturned stability is improved.

3. According to the invention, through arranging the air inlet component, the central shaft drives the branch column shell to rotate in the inner cavity shell under the assistance of the roller bearing, the branch column shell drives the piston columns to rotate, and the adjusting knob is rotated, meshing force is generated in the moving column by the adjusting knob, so that the moving column slides up and down in the inner cavity shell, the angle of the hemispherical block is adjusted, the inclination angles of the hemispherical block are different, under the ball hinge connection mode of the connecting sleeves, the compression depths of the piston columns in the cylindrical grooves are different, at the moment, the first electromagnetic valve and the second electromagnetic valve are in an open state, after one special-shaped hole and one of the cylindrical grooves form a passage, at the moment, the piston columns in the cylindrical grooves move outwards to form suction force, so that external air is filtered by the second electromagnetic valve and then directly enters one special-shaped hole from the second electromagnetic valve, the air is temporarily stored in the inner cavity of the cylindrical groove, along with the rotation of the branch column shell, the cylindrical groove for storing the air and the other special-shaped hole form a passage, at the moment, the piston columns are influenced by the inclination angles of the hemispherical block, the piston columns move inwards in the cylindrical groove to form a thrust force, the stored special-shaped air is temporarily pushed into the other cylindrical groove, the other special-shaped air is temporarily pushed into the cylindrical groove to form a passage, the other special-shaped air hole, the piston is temporarily stored in the cylinder, and the other special-shaped air is cyclically expanded into the air bag through the cylindrical groove, and the air bag is cyclically expanded, and the air bag is filled into the air bag, and the air bag is cyclically, and the air is expanded.

Drawings

FIG. 1 is a schematic view of a fuel tank adapted for roll-over flight for an aircraft in accordance with the present invention;

FIG. 2 is a schematic view of a second view of a fuel tank adapted for flip-flop flight for an aircraft in accordance with the present invention;

FIG. 3 is a schematic view of the structure of the inside of a fuel tank body in a fuel tank adapted for overturn flight for an aircraft according to the present invention;

FIG. 4 is a schematic view of the structure of an airbag module in a fuel tank adapted for roll-over flight for an aircraft in accordance with the present invention;

FIG. 5 is a schematic view of the structure of an intake assembly in a fuel tank adapted for turndown flight for an aircraft in accordance with the present invention;

FIG. 6 is a schematic view of a partial cross-section of an air intake assembly in a fuel tank adapted for turndown flight for an aircraft in accordance with the present invention;

FIG. 7 is a schematic view of a partial cross-section of a mounting cap in a fuel tank adapted for flip-flop flight for an aircraft in accordance with the present invention;

FIG. 8 is a schematic view of the interior of the inner chamber housing of the fuel tank adapted for roll-over flight for an aircraft in accordance with the present invention;

FIG. 9 is a schematic exploded view of a self-swinging assembly in a fuel tank adapted for turndown flight for an aircraft in accordance with the present invention.

In the figure:

1. a filler tube; 2. a first exhaust pipe; 3. a second exhaust pipe; 4. a first filter flask; 5. an oil outlet pipe; 6. a fuel tank body; 7. an air injection internal support mechanism; 71. a balloon dilation assembly; 711. a fixing plate; 712. folding the air bag; 713. a seal ring; 714. a moving plate; 72. an air intake assembly; 721. a gas outlet pipe; 722. a first electromagnetic valve; 723. a second electromagnetic valve; 724. a second filter flask; 725. a mounting cover; 726. an inner chamber shell; 727. a roller bearing; 728. a moving column; 729. a central shaft; 730. a special-shaped hole; 731. an adjusting knob; 732. a branched column shell; 733. a cylindrical groove; 734. a piston column; 735. connecting sleeves; 736. hemispherical blocks; 74. a self-swinging assembly; 741. square columns; 742. a post; 743. a toothed ring; 744. shaped shelves; 745. a V-shaped frame; 746. a frustum; 747. a conical rod.

Detailed Description

The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

Example 1

Referring to fig. 1-9: the utility model provides an adaptation upset flight's fuel tank for aircraft, including oil filler pipe 1, first blast pipe 2, second blast pipe 3, first filter flask 4, go out oil pipe 5 and fuel tank body 6, the upside of fuel tank body 6 and the lower extreme fixed connection of oil filler pipe 1, the lower extreme of first blast pipe 2 and second blast pipe 3, the valve is installed respectively to the lower extreme of oil filler pipe 1, first blast pipe 2 and second blast pipe 3, the one end of fuel tank body 6 and the one end fixed connection of go out oil pipe 5, the inside other end fixedly connected with gas injection internal stay mechanism 7 of fuel tank body 6, gas injection internal stay mechanism 7 includes gasbag expansion subassembly 71, gasbag expansion subassembly 71 includes fixed plate 711, one side fixedly connected with folding gasbag 712 of fixed plate 711, the opposite side fixedly connected with movable plate 714 of folding gasbag 712, the outside fixedly connected with sealing ring 713 of movable plate 714, the outside and the inner wall fixed connection of fuel tank body 6 of fixed plate 711, the outside and the inner wall slip joint of fuel tank body 6 of sealing ring 713, the middle part fixedly connected with subassembly 72 that admits air of fixed plate 711, the one end fixedly connected with from pendulum subassembly 74 of subassembly 72 admits air, from pendulum subassembly 74 includes toper stick 747, the upside fixedly connected with shape frame 744 of toper stick 747, the inner chamber bottom fixedly connected with frustum 746 of shape frame 744, the middle part movable joint of shape frame 744 has v shape frame 745, the lower extreme one side of v shape frame 745 overlaps with the outside of frustum 746, the inside rotation of upper end of shape frame 744 is connected with pole 742, the outside fixed joint of pole 742 has toothed ring 743, toothed ring 743 is located shape frame 744's upper end middle part, the other end fixed joint of pole 742 has square post 741.

The working principle of the embodiment is as follows: through setting up from pendulum subassembly 74, when the aircraft overturns, fuel and air in fuel tank body 6 and inside also can overturn, and because gravity direction is down all the time, shape frame 744 is not an organic whole with pole 742, conical rod 747 receives inertia and motionless, ratchet part that pole 742 and ring gear 743 constitute follows the upset, from this, form the fan-shaped upset motion of certain angle between ratchet part and the conical rod 747, ratchet part anticlockwise upset, and V shape frame 745 can only rotate clockwise in shape frame 744 under the side top of frustum 746, just by the bight of V shape frame 745 when the ring gear 743 anticlockwise upset in the ratchet part, along with the back and forth of upset angle grow, make the ring gear 743 drive pole 742 and rotate, under the connection of square post 741, drive center pin 729 rotates in installation lid 725, along with conical rod 747 makes up the periodic application torsional force to center pin 729 and realizes utilizing the relative motion when overturning, for aircraft expansion subassembly 71 is filled with air, the sufficient power of inflation after the gasbag expansion subassembly 71, the insufficient power of fuel when the upset "surge problem" is caused.

Example two

Referring to fig. 1-4: one end of the fuel tank body 6 is fixedly connected with one end of the oil outlet pipe 5, the other end of the inside of the fuel tank body 6 is fixedly connected with an air injection internal stay mechanism 7, the air injection internal stay mechanism 7 comprises an air bag expansion assembly 71, the air bag expansion assembly 71 comprises a fixing plate 711, one side of the fixing plate 711 is fixedly connected with a folding air bag 712, the other side of the folding air bag 712 is fixedly connected with a movable plate 714, the outer side of the movable plate 714 is fixedly connected with a sealing ring 713, the outer side of the fixing plate 711 is fixedly connected with the inner wall of the fuel tank body 6, and the outer side of the sealing ring 713 is in sliding clamping connection with the inner wall of the fuel tank body 6.

The working principle of the embodiment is as follows: through setting up gasbag expansion assembly 71, along with being continuously injected with the air in the folding gasbag 712, folding gasbag 712 expands according to the folding trace of advance, after the gas struts, promote movable plate 714, movable plate 714 atress drives the laminating of the sealing ring 713 in outside at the inner wall of fuel tank body 6 and removes, the valve of second blast pipe 3 lower extreme is opened this moment, sealing ring 713 and movable plate 714 promote the inside fuel of fuel tank body 6, the inside space of fuel tank body 6 at this moment is compressed, the air in the fuel tank body 6 is discharged from second blast pipe 3, the space that the fuel occupies also diminishes, the fuel also gets into the engine from delivery pipe 5 and first filter flask 4 in proper order this moment, and when overturning, the air volume that gets into delivery pipe 5 reduces sharply, the fuel volume increases than before, compensate the power shortage that the fuel volume feeding is insufficient and leads to when overturning, the engine "surging" phenomenon when alleviating the aircraft upset, improve the upset stability.

Example III

Referring to fig. 4-8: the other end fixed joint of square post 741 has center pin 729, the other end movable joint of center pin 729 has branch post shell 732, a plurality of post grooves 733 have been seted up to the inside of branch post shell 732, the inner wall slip joint of every post groove 733 has piston post 734, the other end swing joint of every piston post 734 has adapter sleeve 735, the other end fixedly connected with hemisphere piece 736 of a plurality of adapter sleeves 735, the other end movable connection of hemisphere piece 736 has movable post 728, the surface middle part rotation of center pin 729 is connected with installation lid 725, two sets of special-shaped holes 730 are seted up to the inside of installation lid 725, the opposite side of installation lid 725 is through bolt fixed connection there being inner chamber shell 726, the surface upside of inner chamber shell 726 and the inner chamber top surface fixed connection of fuel tank body 6, the one end of inner chamber shell 726 and the one end rotation of branch post shell 732 are connected, the other end fixed mounting of branch post shell 734 has roller bearing 727, the outside of roller bearing 727 and the inner chamber other end fixed mounting of inner chamber shell 726, the other end inner chamber of inner chamber 728 and the surface slip joint of movable post 728, the lower extreme swing joint of movable post piece 736 has adjusting knob 731, the upper end screw thread is connected with the second special-shaped hole 722 of the second electromagnetic valve body 724 of which is connected with the second electromagnetic valve body, the other end of the special-shaped hole 722 is connected with the second electromagnetic valve body 722, the other end of the second electromagnetic valve body is connected with the second electromagnetic valve 722 of the other end of the special-shaped hole, the other end of the electromagnetic valve is connected with the second electromagnetic valve 722, the other end of the electromagnetic valve is connected with the other end of the electromagnetic valve, the other end of the filter plate is connected with the other end of the electromagnetic valve, and the filter plate is connected with the other end of the filter, and the filter plate is connected with the filter, and the filter.

The working principle of the embodiment is as follows: by arranging the air inlet assembly 72, the center shaft 729 drives the branch column casing 732 to rotate in the inner cavity casing 726 under the assistance of the roller bearing 727, the branch column casing 732 drives the plurality of piston columns 734 to rotate, and the adjusting knob 731 is rotated, the adjusting knob 731 generates engaging force in the inner cavity casing 726, so that the moving column 728 slides up and down in the inner cavity casing 726, the angle of the hemispherical block 736 is adjusted, the inclination angles of the hemispherical block 736 are different, under the ball hinge connection mode of the plurality of connecting sleeves 735, the compression depths of the plurality of piston columns 734 in the cylindrical slots 733 are different, at this time, the first electromagnetic valve 722 and the second electromagnetic valve 723 are in an open state, after one of the special-shaped holes 730 and one of the cylindrical slots 733 form a passage, at this time, the piston column 734 in the cylindrical slot 733 moves outwards to form suction force, so that outside air is filtered by the second electromagnetic valve 723, the outside air is directly fed into one of the special-shaped holes 730, the air is temporarily stored in the inner cavity of the cylindrical slots 733, along with the rotation of the branch column casing 732, the cylindrical slots 733 and the other special-shaped holes 730 form a passage, the compression depth of the piston blocks 734 in the cylindrical slots 734 is temporarily influenced by the inclination angle of the cylindrical blocks, the piston columns 734 is injected into the other air bag 712, and the air bag is temporarily expanded, and the cycle is completely expanded, and the air is injected into the other air bag module is completely, and the air bag is completely expanded, and the cycle is completely by the piston assembly is compressed, and is compressed and is expanded.

The application method and the working principle of the device are as follows: when the fuel tank for adapting to overturning flight is used, the fuel gun is inserted into the fuel filling pipe 1, the valve below the fuel filling pipe 1 and the first exhaust pipe 2 is opened, the air pressure in the fuel tank body 6 is balanced, the fuel is filled into the fuel tank body 6, the valve of the fuel filling pipe 1 and the valve of the first exhaust pipe 2 are closed after the fuel filling is finished, when an aircraft stably flies, fuel enters the first filter flask 4 from the fuel outlet pipe 5, and after the first filter flask 4 filters certain impurities, the fuel enters the engine to participate in operation.

Firstly, when the aircraft turns over, the fuel tank body 6 and the fuel and air in the fuel tank body can also turn over, the rack 744 is not integrally connected with the post 742 because the gravity direction is always downward, the conical rod 747 is inertially fixed, the ratchet component formed by the post 742 and the toothed ring 743 follows the turn over, a fan-shaped turn over motion with a certain angle is formed between the ratchet component and the conical rod 747, the ratchet component turns over anticlockwise, the v-shaped rack 745 can only rotate clockwise in the rack 744 under the side top of the conical table 746, the toothed ring 743 in the ratchet component is just supported by one corner of the v-shaped rack 745 when the toothed ring 743 turns over anticlockwise, the tangential force of the outer edge of the toothed ring 743 becomes larger as the turning angle becomes larger, the toothed ring 743 drives the post 742 to rotate, the central shaft 729 is driven to rotate in the mounting cover 725 under the connection of the square post 741, and the torsional force is periodically applied to the central shaft 729 as the conical rod 747 swings back and forth.

Then, the central shaft 729 drives the branch column casing 732 to rotate inside the inner cavity casing 726 under the assistance of the roller bearing 727, the branch column casing 732 drives the plurality of piston columns 734 to rotate, and the adjusting knob 731 is rotated, the adjusting knob 731 generates meshing force inside the moving column 728, so that the moving column 728 slides up and down in the inner cavity casing 726, thereby adjusting the angle of the hemispherical block 736, the inclination angles of the hemispherical block 736 are different, under the ball hinge connection mode of the plurality of connecting sleeves 735, the compression depths of the plurality of piston columns 734 in the cylindrical slots 733 are different, at this time, the first electromagnetic valve 722 and the second electromagnetic valve 723 are in an open state, after one special-shaped hole 730 and one of the cylindrical slots 733 form a passage, at this time, the piston column 734 in the cylindrical slot 733 moves outwards to form suction force, so that external air is filtered by the second filter bottle 724 and then directly enters into one special-shaped hole 723, the air is temporarily stored in the inner cavity of the cylindrical slot 733, along with the rotation of the branch column casing 732, the cylindrical slot 733 and the other special-shaped hole 730 form a passage, the piston column 734 is temporarily pushed into the other cylinder slot 734 by the piston rod 734, and the other special-shaped hole 730 is periodically pushed into the cylindrical slot 734, and the other air is periodically pushed into the other cylinder slot 734 by the piston 734 after the piston rod 734.

Then, as the air is periodically injected into the folded airbag 712, the folded airbag 712 expands according to the pre-folded trace, after the air is opened, the moving plate 714 is pushed, the moving plate 714 is forced to drive the sealing ring 713 on the outer side to be attached to the inner wall of the fuel tank body 6 and move, at the moment, the valve at the lower end of the second exhaust pipe 3 is opened, the sealing ring 713 and the moving plate 714 push the fuel in the fuel tank body 6 to compress the space in the fuel tank body 6 at the moment, the air in the fuel tank body 6 is compressed and discharged from the second exhaust pipe 3, the space occupied by the fuel is also reduced, at the moment, the fuel also sequentially enters the engine from the oil outlet pipe 5 and the first filter flask 4, and when the aircraft is overturned, the air quantity entering the oil outlet pipe 5 is sharply reduced, the fuel quantity is increased compared with the prior art, the power shortage caused by the shortage of fuel quantity feeding when the aircraft is made up, the phenomenon of engine surging when the aircraft is overturned is lightened, and the overturning stability is improved.

Although the present invention has been described with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described, or equivalents may be substituted for elements thereof, and any modifications, equivalents, improvements and changes may be made without departing from the spirit and principles of the present invention.

Claims

1. The utility model provides a fuel tank that adaptation upset was flown for aircraft, includes oil filler pipe (1), first blast pipe (2), second blast pipe (3), first filter flask (4), goes out oil pipe (5) and fuel tank body (6), its characterized in that: the upper side of the fuel tank body (6) is fixedly connected with the lower end of the oil filling pipe (1), the lower end of the first exhaust pipe (2) and the lower end of the second exhaust pipe (3), and valves are respectively arranged at the lower ends of the oil filling pipe (1), the first exhaust pipe (2) and the second exhaust pipe (3);

one end of the fuel tank body (6) is fixedly connected with one end of the oil outlet pipe (5), the other end of the inside of the fuel tank body (6) is fixedly connected with an air injection internal support mechanism (7), the air injection internal support mechanism (7) comprises an air bag expanding assembly (71), the air bag expanding assembly (71) comprises a fixing plate (711), one side of the fixing plate (711) is fixedly connected with a folding air bag (712), the other side of the folding air bag (712) is fixedly connected with a movable plate (714), the outer side of the movable plate (714) is fixedly connected with a sealing ring (713), the outer side of the fixing plate (711) is fixedly connected with the inner wall of the fuel tank body (6), and the outer side of the sealing ring (713) is in sliding clamping connection with the inner wall of the fuel tank body (6);

the middle part fixedly connected with subassembly (72) that admits air of fixed plate (711), the one end fixedly connected with of subassembly (72) that admits air is from pendulum subassembly (74), from pendulum subassembly (74) including toper stick (747), the upside fixedly connected with shape frame (744) of toper stick (747), the inner chamber bottom fixedly connected with frustum (746) of shape frame (744), the middle part activity joint of shape frame (744) has v shape frame (745), the lower extreme one side of v shape frame (745) with the outside overlap joint of frustum (746), the inside rotation of upper end of shape frame (744) is connected with pole (742), the outside fixed joint of pole (742) has ring gear (743), ring gear (743) are located the upper end middle part of shape frame (744), the other end fixed joint of pole (742) has square post (741).

2. The fuel tank for adapting a turn-over flight for an aircraft according to claim 1, wherein: the other end of the square column (741) is fixedly clamped with a central shaft (729), and the other end of the central shaft (729) is movably clamped with a branch column casing (732).

3. The fuel tank for adapting a turn-over flight for an aircraft according to claim 2, wherein: the inside of branch post shell (732) has seted up a plurality of cylindricality grooves (733), every cylindricality groove (733) inner wall slip joint has piston post (734).

4. A fuel tank for an aircraft adapted for reverse flight according to claim 3, wherein: the other end of each piston column (734) is movably connected with a connecting sleeve (735), and the other ends of a plurality of connecting sleeves (735) are fixedly connected with hemispherical blocks (736).

5. The fuel tank for adapting a turn-over flight for an aircraft according to claim 4, wherein: the other end of the hemispherical block (736) is movably connected with a movable column (728), and the middle part of the outer surface of the central shaft (729) is rotatably connected with a mounting cover (725).

6. The fuel tank for adapting a turn-over flight for an aircraft according to claim 5, wherein: two groups of special-shaped holes (730) are formed in the mounting cover (725), an inner cavity shell (726) is fixedly connected to the other side of the mounting cover (725) through bolts, and the upper side of the outer surface of the inner cavity shell (726) is fixedly connected with the top surface of the inner cavity of the fuel tank body (6).

7. The fuel tank for adapting a turn-over flight for an aircraft according to claim 6, wherein: one end of the inner cavity shell (726) is rotationally connected with one end of the branch column shell (732), and a roller bearing (727) is fixedly arranged at the other end of the branch column shell (732).

8. The fuel tank for adapting a turn-over flight for an aircraft according to claim 7, wherein: the outside of roller bearing (727) with the inner chamber other end fixed mounting of inner chamber shell (726), the other end inner chamber of inner chamber shell (726) with the surface slip joint of removal post (728), the lower extreme threaded connection of removal post (728) has adjusting knob (731), the upper end of adjusting knob (731) with the surface downside rotation of inner chamber shell (726) is connected.

9. The fuel tank for adapting a turn-over flight for an aircraft according to claim 8, wherein: the inner wall threaded connection of one of the special-shaped holes (730) has second solenoid valve (723), the other end fixedly connected with second filter flask (724) of second solenoid valve (723), the other end of second filter flask (724) with fuel tank body (6) through connection.

10. The fuel tank for adapting a turn-over flight for an aircraft according to claim 9, wherein: the inner wall of the other special-shaped hole (730) is in threaded connection with a first electromagnetic valve (722), the other end of the first electromagnetic valve (722) is fixedly connected with a gas output pipe (721), and the other end of the gas output pipe (721) is in penetrating connection with the middle part of the fixing plate (711).