Auxiliary tool for oil spilling of ventilation oil tank of Boeing B737NG aircraft

Abstract

An auxiliary tool for oil spilling of a ventilation oil tank of a Boeing B737NG aircraft relates to the technical field of regular maintenance of airplanes, and is characterized in that the whole auxiliary tool is moved below a cover plate of the ventilation oil tank of a large wing of the aircraft, a sleeve is fixed on a floating disc through a locking mechanism, and an oil receiving pipe is moved upwards relative to the sleeve; due to the fact that the area, where the ventilation oil tank cover plate is located, of the lower end of the large wing of the airplane is a non-horizontal plane, the sleeve can freely deflect through flexible connection between the floating disc and the fixing ring, the large wing of the airplane can be conveniently matched, and the oil receiving pipe is locked and fixed relative to the sleeve through the fixing mechanism. When fuel oil overflows from the ventilation oil tank, the fuel oil falls into the oil collecting barrel through the oil receiving nozzle and the oil receiving pipe, and collection of the fuel oil is achieved. Fuel oil is prevented from overflowing to corrode a paint layer structure on the surface of an airplane and injure a human body.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft scheduled inspection and maintenance, in particular to an auxiliary tool for oil overflow in a ventilation tank of a Boeing B737NG aircraft. Background Art

[0002] The vent tanks on Boeing B737NG aircraft are located at the outer ends of each wing. Their primary purpose is to connect the wing structural fuel tanks to the external environment, balance the pressure differential between the internal and external tanks, protect the wing structure, and smoothly supply fuel to the engines. Under normal circumstances, no fuel is stored within them. However, if there is a malfunction in the aircraft's refueling system, or during scheduled aircraft inspections to check for leaks near the vent cover, a certain amount of fuel may be stored in the vent tanks. In such cases, the slightest operator error or failure of internal tank components could result in a dangerous large amount of fuel spilling from the vent opening. Fuel is flammable and explosive, corrosive to the aircraft's surface finish, and harmful to personnel. Summary of the Invention

[0003] In order to overcome the deficiencies of the above technologies, the present invention provides an auxiliary tool for conveniently collecting fuel overflowed from a ventilated fuel tank.

[0004] The technical solution adopted by the utility model to overcome the technical problems is:

[0005] An auxiliary tooling for oil overflow in the ventilation tank of a Boeing B737NG aircraft, comprising:

[0006] The chassis has a fixing ring at its upper end, and the lower end of the fixing ring is connected and fixed to the chassis via a support rod;

[0007] Oil collecting barrel, placed on the chassis;

[0008] A floating plate is located in the fixed ring and is flexibly connected to the fixed ring via a floating mechanism. A through hole is provided in the floating plate in a vertical direction.

[0009] The sleeve is inserted into the through hole and is locked and fixed relative to the floating plate through a locking mechanism;

[0010] The oil receiving pipe is inserted into the casing and coaxially fixed in the casing through a fixing mechanism. The lower end of the oil receiving pipe is located directly above the oil collecting barrel. An oil receiving nozzle is connected to the top of the oil receiving pipe. The outer diameter of the oil receiving nozzle matches the inner diameter of the vent at the vent tank cover at the lower end of the aircraft's wing. The oil receiving nozzle is inserted into the vent.

[0011] In order to facilitate movement, N universal wheels are provided at intervals along the circumferential direction at the lower end of the chassis.

[0012] The value of N is 3.

[0013] For easy operation, handle grooves are provided on the left and right ends of the oil collecting barrel.

[0014] Furthermore, the floating mechanism is M tension springs, each of which is evenly distributed along the circumferential direction, one end of the tension spring is connected to the fixed ring, and the other end is connected to the floating plate.

[0015] Furthermore, the above-mentioned locking mechanism includes an open groove I arranged at the front end of the fixing ring, an open groove II arranged at the front end of the floating plate, a sliding groove arranged at the bottom of the floating plate and respectively located on the left and right sides of the opening groove II, and an external thread arranged at the upper end of the floating plate. The nut is screwed on the external thread, and the nut and the through hole are coaxially arranged. The front end of the nut is provided with an open groove III. The widths of the opening groove I, the opening groove II and the opening groove III are all greater than the outer diameter of the sleeve. A flange is provided on the sleeve. When the sleeve is located in the through hole, the two ends of the flange are inserted into the corresponding sliding grooves on the same side.

[0016] Furthermore, the fixing mechanism is a hand-tightening bolt screwed onto the casing, and the head end of the hand-tightening bolt contacts the outer wall of the oil receiving pipe.

[0017] The beneficial effects of the present invention are as follows: the entire auxiliary tooling is moved below the vent tank cover of the aircraft's wing, the sleeve is fixed to the floating plate via a locking mechanism, and the oil connection pipe is moved upward relative to the sleeve until the oil connection nozzle is inserted into the vent opening of the vent tank cover. Since the area where the vent tank cover is located at the lower end of the aircraft's wing is not horizontal, the sleeve can be freely deflected by the flexible connection between the floating plate and the fixing ring, facilitating matching with the aircraft's wing. The oil connection pipe is locked and fixed relative to the sleeve via the fixing mechanism. When fuel overflows from the vent tank, the fuel falls into the oil collection barrel through the oil connection nozzle and the oil connection pipe, thereby achieving fuel collection. This prevents fuel overflow from corroding the aircraft's surface paint structure and causing harm to the human body. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a structural diagram of the aircraft's oil spill port;

[0019] Figure 2 It is a schematic diagram of the three-dimensional structure of the utility model;

[0020] Figure 3 for Figure 2 The enlarged structural diagram of part B in FIG;

[0021] Figure 4 This is a structural diagram of the floating plate portion of the present utility model;

[0022] Figure 5 for Figure 2 A magnified structural diagram of part A;

[0023] Figure 6 This is a structural diagram of the hand-tightened bolt portion of the utility model;

[0024] In the figure, 1. Vent tank cover, 2. Vent, 3. Support rod, 4. Retaining ring, 5. Oil collecting barrel, 6. Handle groove, 7. Floating plate, 8. Sleeve, 9. Oil connecting pipe, 10. Thumb bolt, 11. Chassis, 12. Universal wheel, 13. Oil connecting nozzle, 14. Tension spring, 15. Through hole, 16. Nut, 17. Opening groove I, 18. Opening groove II, 19. Opening groove III, 20. Slide groove, 21. Flange. DETAILED DESCRIPTION

[0025] The following is combined with Figure 1 To the attached Figure 6 The utility model is further described.

[0026] An auxiliary tooling for oil overflow in the ventilation tank of a Boeing B737NG aircraft comprises: a chassis 11, a fixing ring 4 being provided at the upper end thereof, the lower end of the fixing ring 4 being connected and fixed to the chassis 11 by a support rod 3; an oil collecting barrel 5 being placed on the chassis 11; a floating plate 7 being located in the fixing ring 4, the floating plate 7 being flexibly connected to the fixing ring 4 by a floating mechanism, a through hole 15 being provided in the floating plate 7 along the vertical direction; a sleeve 8 being inserted into the through hole 15 and being locked and fixed relative to the floating plate 7 by a locking mechanism; an oil receiving pipe 9 being inserted into the sleeve 8 and coaxially fixed in the sleeve 8 by a fixing mechanism, the lower end of the oil receiving pipe 9 being located directly above the oil collecting barrel 5, an oil receiving nozzle 13 being connected above the oil receiving pipe 9, the outer diameter of the oil receiving nozzle 13 matching the inner diameter of the vent 2 at the ventilation tank cover 1 at the lower end of the aircraft's wing, the oil receiving nozzle 13 being inserted into the vent 2. During use, the entire auxiliary tooling is moved to the bottom of the aircraft's wing vent tank cover 1. The sleeve 8 is secured to the floating plate 7 via a locking mechanism. The oil receiving pipe 9 is moved upward relative to the sleeve 8 until the oil receiving nozzle 13 is inserted into the vent opening 2 of the vent tank cover 1. Because the area where the vent tank cover 1 is located at the lower end of the aircraft's wing is not horizontal, the sleeve 8 can freely deflect due to the flexible connection between the floating plate 7 and the fixing ring 4, making it easier to match the aircraft's wing. The oil receiving pipe 9 is locked relative to the sleeve 8 via the fixing mechanism. When fuel overflows from the vent tank, the fuel falls through the oil receiving nozzle 13 and the oil receiving pipe 9 into the oil collection drum 5, thereby achieving fuel collection. This prevents fuel overflow from corroding the aircraft's surface paint structure and causing harm to the human body. The B737 aircraft landing gear is an oil and gas device. The heavier it is, the lower the aircraft's ground clearance is, and the lower the vent opening 2 on the vent tank cover 1 is. Therefore, the ground clearance of the vent opening 2 of the fuel tank varies depending on the aircraft size or the load capacity of the same aircraft. To address this issue, the oil receiving pipe 9 is axially movable within the sleeve 8. A fixing mechanism allows the oil receiving pipe 9 to be moved up and down within the sleeve 8 and fixed, thereby adapting the vent opening 2 to different ground clearances.

[0027] In one embodiment of the present invention, N universal wheels 12 are circumferentially spaced apart at the lower end of the chassis 11. The provision of these universal wheels 12 facilitates movement of the entire auxiliary tooling to the construction location, further enhancing operational convenience. Preferably, N is set to 3. Three or more universal wheels 12 ensure stability, allowing the entire auxiliary tooling to move smoothly.

[0028] In one embodiment of the present invention, handle grooves 6 are provided at the left and right ends of the oil collecting barrel 5. After the oil collecting barrel 5 is filled with fuel, the handle grooves 6 can be inserted into the handle grooves 6 to conveniently lift the oil collecting barrel 5 from the chassis 11, and the fuel in the oil collecting barrel 5 can be conveniently poured into the designated oil storage device, further improving the convenience of operation.

[0029] In one embodiment of the present invention, the floating mechanism comprises M tension springs 14, each uniformly distributed along the circumference. One end of each tension spring 14 is connected to the retaining ring 4, and the other end is connected to the floating plate 7. When the sleeve 8 needs to be deflected, the floating plate 7 deflects relative to the retaining ring 4, and the tension springs 14 stretch to achieve a flexible connection to the floating plate 7. Because the aircraft wing droops during refueling tests or leak inspections, the wing, after installation of the auxiliary fixture, moves downward, driving the floating plate 7 downward as a whole through the sleeve 8 via the oil nipple 13. At this point, each tension spring 14 stretches to match the change in wing position.

[0030] In one embodiment of the present utility model, the locking mechanism includes an open groove I 17 arranged at the front end of the fixing ring 4, an open groove II 18 arranged at the front end of the floating plate 7, a slide groove 20 arranged at the bottom of the floating plate 7 and located on the left and right sides of the open groove II 18, and an external thread arranged at the upper end of the floating plate 7. The nut 16 is screwed onto the external thread. The nut 16 is coaxially arranged with the through hole 15. The front end of the nut 16 is provided with an open groove III 19. The widths of the open groove I 17, the open groove II 18 and the open groove III 19 are all greater than the outer diameter of the sleeve 8. A flange 21 is provided on the sleeve 8. When the sleeve 8 is located in the through hole, the two ends of the flange 21 are inserted into the corresponding slide grooves 20 on the same side. During installation, the sleeve 8 passes through the opening groove I 17, the opening groove II 18 and the opening groove III 19 in sequence and then enters the through hole 15. The two ends of the flange 21 slide in the corresponding sliding grooves 20 on the same side. When the sleeve 8 completely enters the through hole 15 of the floating plate 7, the nut 16 is rotated so that the opening groove III 19 of the nut 16 does not overlap with the opening groove II 18. After that, the sleeve 8 is locked in the non-axial direction. The sleeve 8 is limited axially by the flange 21 inserted in the sliding groove 20.

[0031] In one embodiment of the present invention, the securing mechanism comprises a thumb bolt 10 screwed onto the sleeve 8, the head of which contacts the outer wall of the oil receiving pipe 9. After the oil receiving nipple 13 at the upper end of the oil receiving pipe 9 is inserted into the vent 2, the thumb bolt 10 is tightened to lock the oil receiving pipe 9 axially relative to the sleeve 8. This facilitates operation. To remove the oil receiving nipple 13 from the vent 2, the thumb bolt 10 is loosened to allow the oil receiving pipe 9 to move downward relative to the sleeve 8.

[0032] Finally, it should be noted that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art will be able to modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein with equivalents. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. An auxiliary tool for oil overflow in the ventilation tank of Boeing B737NG aircraft, characterized in that: include: A chassis (11) is provided with a fixing ring (4) at its upper end, and the lower end of the fixing ring (4) is connected and fixed to the chassis (11) via a support rod (3); The oil collecting barrel (5) is placed on the chassis (11); A floating plate (7) is located in the fixed ring (4), the floating plate (7) is flexibly connected to the fixed ring (4) via a floating mechanism, and a through hole (15) is provided in the floating plate (7) along the vertical direction; The sleeve (8) is inserted into the through hole (15) and is locked and fixed relative to the floating plate (7) through a locking mechanism; An oil receiving pipe (9) is inserted into the sleeve (8) and coaxially fixed in the sleeve (8) through a fixing mechanism. The lower end of the oil receiving pipe (9) is located directly above the oil collecting barrel (5). An oil receiving nozzle (13) is connected to the upper part of the oil receiving pipe (9). The outer diameter of the oil receiving nozzle (13) matches the inner diameter of the vent (2) at the vent oil tank cover (1) at the lower end of the aircraft's wing. The oil receiving nozzle (13) is inserted into the vent (2).

2. The auxiliary tooling for oil overflow of the ventilation tank of the Boeing B737NG aircraft according to claim 1 is characterized in that: The lower end of the chassis (11) is provided with N universal wheels (12) at intervals along the circumferential direction.

3. The auxiliary tooling for oil overflow of the ventilation tank of Boeing B737NG aircraft according to claim 2 is characterized in that: The value of N is 3.

4. The auxiliary tooling for oil overflow of the ventilation tank of Boeing B737NG aircraft according to claim 1 is characterized in that: The oil collecting barrel (5) is provided with handle grooves (6) at both left and right ends.

5. The auxiliary tooling for oil overflow of the ventilation tank of Boeing B737NG aircraft according to claim 1 is characterized in that: The floating mechanism comprises M tension springs (14), each tension spring (14) being evenly distributed along the circumferential direction, one end of the tension spring (14) being connected to the fixed ring (4), and the other end thereof being connected to the floating disk (7).

6. The auxiliary tooling for oil overflow of the ventilation tank of Boeing B737NG aircraft according to claim 1, characterized in that: The locking mechanism includes an open groove I (17) provided at the front end of the fixed ring (4), an open groove II (18) provided at the front end of the floating plate (7), a slide groove (20) provided at the bottom of the floating plate (7) and located on the left and right sides of the open groove II (18), and an external thread provided at the upper end of the floating plate (7). The nut (16) is screwed onto the external thread. The nut (16) and the through hole (15) are coaxially arranged. The front end of the nut (16) is provided with an open groove III (19). The widths of the open groove I (17), the open groove II (18) and the open groove III (19) are all greater than the outer diameter of the sleeve (8). The sleeve (8) is provided with a flange (21). When the sleeve (8) is located in the through hole, the two ends of the flange (21) are inserted into the corresponding slide grooves (20) on the same side.

7. The auxiliary tooling for oil overflow of the ventilation tank of Boeing B737NG aircraft according to claim 1, characterized in that: The fixing mechanism is a hand-tightening bolt (10) screwed onto the sleeve (8), and the head end of the hand-tightening bolt (10) contacts the outer wall of the oil receiving pipe (9).

Images