Pressure balancing device for opening cover of aircraft fuel tank
By designing a pressure balancing device for aircraft fuel tank caps that includes a cover, a vent plate, a fixing rod, an annular plate, a circular plate, a spring, and an adjustment mechanism, the problem of insufficient pressure balance in traditional designs is solved. This achieves automatic adjustment and sealing of the air pressure inside and outside the fuel tank, thereby improving aircraft safety and fuel supply efficiency.
Patent Information
- Application Number
- CN202520643409.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-07
- Publication Date
- 2026-01-16
- Estimated Expiration
- 2035-04-07
AI Technical Summary
Traditional aircraft fuel tank cap designs neglect pressure balance, leading to pressure fluctuations inside the fuel tank, which affects fuel supply and safety.
A pressure balancing device was designed, comprising a cover, a vent plate, a fixing rod, an annular plate, a circular plate, a spring, and an adjusting mechanism. This device can automatically adjust the air pressure and achieve pressure balance inside and outside the oil tank through the cooperation of the vent plate and the adjusting mechanism.
It achieves automatic pressure balance inside and outside the fuel tank, improving the aircraft's flight safety and the fuel tank's sealing performance, and reducing safety hazards and environmental pollution risks.
Smart Images
Figure CN223803793U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model belongs to the technical field of aircraft fuel tank, specifically is a kind of aircraft fuel tank mouth cover pressure balancing device. BACKGROUND
[0002] With the continuous development of aviation technology, the stability and safety of aircraft fuel tank system are increasingly improved. As an important part of fuel tank system, the sealing and pressure balancing ability of fuel tank mouth cover is directly related to the stability of internal pressure of fuel tank and the supply efficiency of fuel.
[0003] Traditional aircraft fuel tank mouth cover design often focuses on sealing and ignores the importance of pressure balancing. In the flight process, due to the consumption of fuel inside the tank and the change of external environment temperature, the internal pressure of the tank will fluctuate, and if the fuel tank mouth cover cannot effectively balance these pressure changes, it may lead to excessive internal pressure of the tank, and thus affect the normal supply of fuel, and even cause safety hazards. INVENTION CONTENTS
[0004] To solve the problems in the background art, the utility model provides a kind of aircraft fuel tank mouth cover pressure balancing device.
[0005] To achieve the above purpose, the utility model takes the following technical scheme: a kind of aircraft fuel tank mouth cover pressure balancing device, including cover, gas-permeable plate, fixed rod, annular plate, round plate, spring one and multiple adjusting mechanisms;
[0006] The outer wall of the cover is provided with threads, and the inner wall of the cover is fixedly connected with the gas-permeable plate. The gas-permeable plate is fixedly connected with the fixed rod. The fixed rod is fixedly connected with the inner top end of the cover. Multiple through holes one are uniformly distributed on the gas-permeable plate. Each through hole one is provided with an adjusting mechanism at the upper end. An annular plate is arranged above the gas-permeable plate. The peripheral wall of the annular plate is fixedly connected with the inner wall of the cover. Multiple through holes two are uniformly distributed on the annular plate. The inner wall of the annular plate is sealingly and slidably connected with the outer wall of the round plate. The round plate is sealingly and slidably sleeved on the fixed rod. Multiple air grooves one are formed in the lower end of the round plate. Multiple air grooves two are formed in the side wall of the round plate and communicated with the corresponding air grooves one. The upper end of the round plate is fixedly connected with one end of the spring one. The spring one is sleeved on the fixed rod. The other end of the spring one is fixedly connected with the inner top end of the cover. Multiple through holes three are formed in the side wall of the cover, and the through holes three are located above the annular plate.
[0007] Each adjusting mechanism comprises an exhaust bucket, a slide rod, a sealing ball and a spring two.
[0008] The open end of the exhaust barrel is fixedly connected with the upper end of the corresponding through hole, the side wall of the exhaust barrel is meshed, the closed end of the exhaust barrel is provided with a through hole four, the through hole four is slidably connected with a sliding rod, the lower end of the sliding rod is fixedly connected with a closed ball, the closed ball blocks the corresponding through hole one, a spring two is sleeved on the sliding rod, one end of the spring two is fixedly connected with the closed ball, and the other end of the spring two is fixedly connected with the closed end of the exhaust barrel.
[0009] Compared with the prior art, the beneficial effects of the utility model are:
[0010] 1. Automatic adjustment of air pressure balance: the utility model can automatically sense the change of air pressure in the oil tank and timely adjust the exhaust volume, ensuring that the air pressure inside and outside the oil tank remains balanced; this automatic adjustment function effectively avoids potential safety hazards caused by excessive air pressure, improving the flight safety of the aircraft.
[0011] 2. Improve the sealing of the oil tank: under normal conditions, the closed ball in the adjusting mechanism can tightly block the through hole, effectively preventing external air pressure from entering the oil tank and maintaining the sealing of the oil tank; this helps to prevent the evaporation and leakage of fuel in the oil tank, reducing environmental pollution and safety hazards.
[0012] 3. Enhance exhaust efficiency: when the air pressure in the oil tank continues to rise, the round plate will slide up to expose the air groove two, forming a new exhaust passage and increasing the exhaust volume; this design allows the air pressure to balance more quickly, reducing the risk of damage to the oil tank due to excessive air pressure.
[0013] In summary, the utility model provides strong protection for the flight safety of the aircraft through automatic adjustment of air pressure balance, improvement of oil tank sealing, and enhancement of exhaust efficiency. BRIEF DESCRIPTION OF DRAWINGS
[0014] Figure 1 is a front view of the utility model;
[0015] Figure 2 is Figure 1 A local enlarged schematic view of the A place. DETAILED DESCRIPTION
[0016] The technical solutions in the utility model will be described clearly and completely below in combination with the drawings in the embodiments of the utility model, obviously, the described embodiments are only a part of the embodiments of the utility model, not all the embodiments, based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor belong to the protection scope of the utility model.
[0017] This embodiment describes an aircraft oil tank cover pressure balancing device, which comprises a cover body 1, a breathable plate 2, a fixed rod 3, an annular plate 4, a round plate 5, a spring one 6 and multiple adjusting mechanisms.
[0018] The outer wall of the cover 1 is provided with threads, the inner wall of the cover 1 is fixedly connected with the air permeable plate 2, the air permeable plate 2 is fixedly connected with the fixed rod 3, the fixed rod 3 is fixedly connected with the inner top end of the cover 1, a plurality of through holes one are uniformly arranged on the air permeable plate 2, the upper end of each through hole one is provided with an adjusting mechanism, an annular plate 4 is arranged above the air permeable plate 2, the peripheral wall of the annular plate 4 is fixedly connected with the inner wall of the cover 1, a plurality of through holes two are uniformly arranged on the annular plate 4, the inner wall of the annular plate 4 is sealingly and slidably connected with the outer wall of the circular plate 5, the circular plate 5 is sealingly and slidably sleeved on the fixed rod 3, a plurality of air grooves one are arranged on the lower end of the circular plate 5, a plurality of air grooves two are arranged on the side wall of the circular plate 5 and communicated with the corresponding air grooves one, one end of the spring one 6 is fixedly connected with the upper end of the circular plate 5, the spring one 6 is sleeved on the fixed rod 3, the other end of the spring one 6 is fixedly connected with the inner top end of the cover 1, a plurality of through holes three are arranged on the side wall of the cover 1 and located above the annular plate 4.
[0019] Each adjusting mechanism comprises an exhaust barrel 7, a sliding rod 8, a sealing ball 9 and a spring two 10.
[0020] The open end of the exhaust barrel 7 is fixedly connected with the upper end of the corresponding through hole one, the side wall of the exhaust barrel 7 is meshed, a through hole four is arranged on the closed end of the exhaust barrel 7 and slidably connected with the sliding rod 8, the lower end of the sliding rod 8 is fixedly connected with the sealing ball 9, the sealing ball 9 blocks the corresponding through hole one, the spring two 10 is sleeved on the sliding rod 8, one end of the spring two 10 is fixedly connected with the sealing ball 9, and the other end of the spring two 10 is fixedly connected with the closed end of the exhaust barrel 7.
[0021] When the device is used, the device is threadedly connected with the corresponding aircraft fuel tank, when the air pressure in the aircraft fuel tank is in a normal range, the device keeps a static balance state, the closed ball 9 in the adjusting mechanism is tightly sealed against the corresponding through hole I under the action of the spring II 10, external air pressure is prevented from entering the fuel tank, and meanwhile the stability of the air pressure inside the fuel tank is kept, the circular plate 5 is in a low position under the action of the spring I 6, and the air groove I and the air groove II thereon are not communicated with the space above the annular plate 4, so air pressure exchange is not carried out through these paths; when the air pressure in the fuel tank starts to rise due to some reasons and exceeds a set threshold, the air pressure will act on the closed ball 9 of the adjusting mechanism, if the air pressure is large enough, the spring force of the spring II 10 will be overcome, the sliding rod 8 is pushed to slide upwards, and then the closed ball 9 is separated from the through hole I, the exhaust passage is opened, the air pressure in the fuel tank enters the exhaust bucket 7 through the opened through hole I, since the side wall is designed in a meshed manner, the air pressure can smoothly pass through and continue to flow upwards, the air pressure then enters the space above the annular plate 4 through the through hole II on the air permeable plate 2, finally, the air pressure is discharged to the outside of the fuel tank through the through hole III of the side wall of the cover body 1, the balance of the air pressure is realized; if the air pressure in the fuel tank continues to rise and reaches a higher threshold, at this time, the adjusting mechanism can not balance the air pressure rapidly and sufficiently, the increased air pressure will act on the circular plate 5, the spring force of the spring I 6 is overcome, the circular plate 5 is pushed to slide upwards, after the circular plate 5 slides upwards, the air groove II of the side wall thereof is exposed to the space above the annular plate 4, a new exhaust passage is formed, the air pressure in the fuel tank can now enter the air groove II through the air groove I, and then is discharged through the through hole III, the exhaust amount is increased, and the air pressure is balanced more quickly; when the air pressure in the fuel tank decreases to a safety range, the spring II 10 and the spring I 6 will respectively push the closed ball 9 and the circular plate 5 to return to the initial positions, the closed ball 9 again seals the through hole I, external air pressure is prevented from entering, the circular plate 5 slides downwards, the air groove II is shielded, the device returns to the normal state, and is prepared to cope with the next air pressure change. Through the above working principle, the device can automatically respond to the change of the air pressure in the fuel tank, timely adjusts the exhaust amount, keeps the balance of the air pressure inside and outside the fuel tank, and ensures the safe operation of the aircraft fuel tank.
[0022] It is obvious for those skilled in the art that the utility model is not limited to the details of the above exemplary embodiments, and the utility model can be realized in other assembly forms without departing from the spirit or basic characteristics of the utility model. Therefore, no matter from which point, the embodiments should be regarded as exemplary and non-limiting, the scope of the utility model is defined by the appended claims instead of the above description, and therefore all changes falling within the meaning and scope of the equivalent conditions of the claims are intended to be included in the utility model. Any reference signs in the claims should not be regarded as limiting the involved claims.
Claims
1. An aircraft fuel tank access door pressure equalization device, characterized by: Including cover (1), air permeable plate (2), fixed rod (3), ring plate (4), round plate (5), spring one (6) and multiple adjusting mechanisms; The outer wall of the cover (1) is provided with threads, the inner wall of the cover (1) is fixedly connected with the air permeable plate (2), the air permeable plate (2) is fixedly connected with the fixed rod (3), the fixed rod (3) is fixedly connected with the inner top end of the cover (1), a plurality of through holes one are uniformly arranged on the air permeable plate (2), an adjusting mechanism is arranged on the upper end of each through hole one, an annular plate (4) is arranged above the air permeable plate (2), the peripheral wall of the annular plate (4) is fixedly connected with the inner wall of the cover (1), a plurality of through holes two are uniformly arranged on the annular plate (4), the inner wall of the annular plate (4) is sealingly and slidably connected with the outer wall of the round plate (5), the round plate (5) is sealingly and slidably sleeved on the fixed rod (3), a plurality of air grooves one are formed in the lower end of the round plate (5), a plurality of air grooves two are formed in the side wall of the round plate (5) and communicate with the corresponding air grooves one, the upper end of the round plate (5) is fixedly connected with one end of the spring one (6), the spring one (6) is sleeved on the fixed rod (3), the other end of the spring one (6) is fixedly connected with the inner top end of the cover (1), a plurality of through holes three are formed in the side wall of the cover (1) and are located above the annular plate (4).
2. A pressure equalizing device for an aircraft fuel tank access door as defined in claim 1 wherein: Each adjusting mechanism comprises an exhaust barrel (7), a sliding rod (8), a sealing ball (9) and a spring two (10); The open end of the exhaust barrel (7) is fixedly connected with the upper end of the corresponding through hole one, the side wall of the exhaust barrel (7) is meshed, a through hole four is formed in the closed end of the exhaust barrel (7) and is slidably connected with the sliding rod (8), the lower end of the sliding rod (8) is fixedly connected with the sealing ball (9), the sealing ball (9) blocks the corresponding through hole one, the spring two (10) is sleeved on the sliding rod (8), one end of the spring two (10) is fixedly connected with the sealing ball (9), and the other end of the spring two (10) is fixedly connected with the closed end of the exhaust barrel (7).