Oiling device for shock strut of aircraft landing gear

Abstract

The utility model belongs to the field of refueling devices, and particularly relates to a refueling device for a shock strut of an aircraft landing gear, which is characterized in that an oil supply port is arranged at the upper part of a red oil tank, an oil pipe is inserted into the oil supply port, a miniature electric pump is inserted into the end part of the oil pipe, and a liquid outlet of the miniature electric pump is inserted into one end of a contraction hose; a liquid inlet pipe is inserted into the other end of the shrinkage hose, the end of the liquid inlet pipe is sleeved with an extension frame, the end of the extension frame is sleeved with an extension frame, the end of the extension frame is movably connected with a sliding frame, the end of the sliding frame is fixedly connected with a deposition piece, and the extension frame and the sliding frame are matched to ensure that the liquid inlet pipe cannot be bent; and a deposition piece and a balancing weight which are installed on the lower end face of the sliding frame can drive the liquid inlet pipe to sink into the bottom of the inner barrel, so that the liquid level of oil is higher than a liquid outlet of the liquid inlet pipe in the oil filling process, it is ensured that the tail end of the liquid pipe is always soaked in liquid, and air is prevented from entering the liquid pipe.

Description

Technical Field

[0001] The utility model relates to the field of refueling devices, in particular to a refueling device for a shock absorbing strut of an aircraft landing gear. Background Art

[0002] The landing gear shock absorber strut of the Airbus A320 aircraft uses an oil-gas shock absorber strut that uses red oil and nitrogen. The oil-gas ratio of the shock absorber strut must be coordinated. If the oil-gas ratio is incorrect, the working efficiency of the shock absorber strut will be reduced. For example, more oil and less gas will cause the shock absorber strut to be too hard, resulting in obvious bumps during landing and taxiing and even damage to the landing gear structure. If there is more gas and less oil, the shock absorber strut may be too soft, resulting in excessive compression of the landing gear and damage to the internal structure of the shock absorber strut. The compression of the landing gear on both sides may also be inconsistent. The correct refueling process should be: when the shock absorber strut is fully extended, fill the cavity with red oil, wait until the oil and gas are completely separated, and then slowly compress the shock absorber strut to a fully compressed state, so that the air in the cavity and excess red oil are completely discharged through the opened upper inflation port. At this time, the remaining oil in the cavity is the correct oil amount, and then nitrogen service is performed according to the ambient temperature at that time, thereby completing the entire oil and gas service process.

[0003] The traditional refueling method is to add red oil to the refueling truck and then connect the high-pressure air pipe through a hand pump, pass through a three-way valve, and directly connect to the upper inflation joint of the shock absorber strut to refuel. On the one hand, this refueling method cannot naturally overflow the original air in the inner cylinder during the refueling process. After a period of time, the air must be released through the three-way valve before refueling can continue, that is, refueling and deflation are performed alternately. On the other hand, due to the high pressure of the hand pump, the red oil entering the cylinder through the upper inflation port is almost in a mist form, which is fully mixed with the air in the cylinder to form a large amount of oil-gas mixture; therefore, in view of the above problems, a refueling device for aircraft landing gear shock absorber struts is proposed. Utility Model Content

[0004] In order to make up for the deficiencies of the prior art, the utility model provides a refueling device for a shock absorbing strut of an aircraft landing gear.

[0005] The utility model solves the technical problem by adopting the following technical solution: a refueling device for a shock absorber strut of an aircraft landing gear, comprising a red oil tank, an oil supply port is provided on the upper part of the red oil tank, an oil pipe is plugged into the oil supply port, a micro electric pump is plugged into the end of the oil pipe, a liquid outlet of the micro electric pump is plugged into one end of a shrink hose, a liquid inlet pipe is plugged into the other end of the shrink hose, an extension frame is sleeved at the end of the liquid inlet pipe, an extension frame is sleeved at the end of the extension frame, a sliding frame is movably connected to the end of the extension frame, and a deposition member is fixedly connected to the end of the sliding frame;

[0006] Preferably, the extension frame comprises: a fixed column and a limiting ring, the end surface of the extension frame is fixedly connected to one end of the fixed column, and the other end of the fixed column is fixedly connected to the end surface of the limiting ring;

[0007] Preferably, the limiting ring further comprises: an arc-shaped groove and an engaging claw, the ring body of the limiting ring is provided with an arc-shaped groove, the inner wall of the arc-shaped groove is fixedly connected with an engaging claw, and the arc-shaped groove is slidably connected to the rod body of the sliding frame;

[0008] Preferably, the sliding frame comprises: an engaging plug and a sliding column, the end surface of the sliding frame is fixedly connected to the end of the sliding column, the middle part of the sliding frame is fixedly connected to the end of the engaging plug, and the groove opened on the end surface of the sliding frame is engaged with the end of the deposition member;

[0009] Preferably, the sliding column further comprises: a circular block and a tooth block, the column body of the sliding column is fixedly connected with a plurality of tooth blocks at equal intervals, and the end of the sliding column is fixedly connected to the end of the circular block;

[0010] Preferably, the deposition member comprises: a counterweight block and a connecting column, wherein the end surface of the deposition member is fixedly connected to one end of the connecting column, and the other end of the connecting column is fixedly connected to the end surface of the counterweight block;

[0011] Preferably, the red oil tank further comprises a scale, and the front portion of the red oil tank is fixedly connected with the scale.

[0012] The utility model is beneficial in that:

[0013] 1. The utility model can ensure that the liquid inlet pipe will not be bent through the cooperation of the extension frame and the sliding frame, so as to avoid the accumulation of bubbles at the bends and affect the flow of the fluid. The sedimentation piece and the counterweight block installed on the lower end surface of the sliding frame will drive the liquid inlet pipe to sink to the bottom of the inner cylinder, so that during the refueling process, the oil level is higher than the liquid outlet of the liquid inlet pipe, ensuring that the end of the liquid pipe is always immersed in the liquid, and preventing air from entering the liquid pipe;

[0014] 2. The utility model delivers the oil in the red oil tank into the inner cylinder of the shock absorber column through a micro electric pump, and the micro electric pump uses a 100V DC motor with moderate power, which can ensure a certain flow rate without forming high-pressure oil mist, thus saving the trouble of multiple people taking turns to pump. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0016] Figure 1 This is a schematic diagram of the front structure of the utility model;

[0017] Figure 2 This is a schematic diagram of the structure of the extension frame, the sliding frame and the deposition member of the utility model;

[0018] Figure 3 for Figure 2 A schematic diagram of the enlarged structure of part A;

[0019] Figure 4 It is a structural schematic diagram of the sliding frame and the deposition member of the utility model;

[0020] Figure 5 It is a structural schematic diagram of the extension frame of the utility model.

[0021] In the figure:

[0022] 1. Red oil tank; 11. Scale; 2. Oil supply port; 3. Oil pipe; 4. Micro electric pump; 5. Contraction hose; 6. Liquid inlet pipe; 7. Extension frame; 71. Fixed column; 72. Limiting ring; 721. Arc groove; 722. Engaging claw; 9. Sliding frame; 91. Engaging plug; 92. Sliding column; 921. Round block; 922. Tooth block; 10. Sedimentation piece; 101. Counterweight block; 102. Connecting column. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0024] The following is combined with Figure 1-5 To further explain this application in detail,

[0025] The embodiment of the present application discloses a refueling device for a shock absorber strut of an aircraft landing gear, comprising a red oil tank 1, an oil supply port 2 is provided at the upper portion of the red oil tank 1, an oil supply port 2 is plugged with an oil pipe 3, an end of the oil pipe 3 is plugged with a micro electric pump 4, a liquid outlet of the micro electric pump 4 is plugged with one end of a shrink hose 5, the other end of the shrink hose 5 is plugged with a liquid inlet pipe 6, an end of the liquid inlet pipe 6 is sleeved with an extension frame 7, an end of the extension frame 7 is sleeved with an extension frame 7, an end of the extension frame 7 is movably connected to a sliding frame 9, and an end of the sliding frame 9 is fixedly connected to a deposition member 10;

[0026] The extension frame 7 includes: a fixed column 71 and a limiting ring 72. The end surface of the extension frame 7 is fixedly connected to one end of the fixed column 71, and the other end of the fixed column 71 is fixedly connected to the end surface of the limiting ring 72.

[0027] The limiting ring 72 further includes: an arc groove 721 and an engaging claw 722. The ring body of the limiting ring 72 is provided with an arc groove 721. The inner wall of the arc groove 721 is fixedly connected with the engaging claw 722. The arc groove 721 is slidably connected to the rod body of the sliding frame 9.

[0028] The sliding frame 9 includes: an interlocking plug 91 and a sliding column 92. The end surface of the sliding frame 9 is fixedly connected to the end of the sliding column 92. The middle part of the sliding frame 9 is fixedly connected to the end of the interlocking plug 91. The groove opened on the end surface of the sliding frame 9 is interlocked and connected to the end of the deposition member 10.

[0029] The sliding column 92 further includes: a circular block 921 and a tooth block 922. The column body of the sliding column 92 is fixedly connected with a plurality of tooth blocks 922 at equal intervals. The end of the sliding column 92 is fixedly connected to the end of the circular block 921.

[0030] The deposition member 10 comprises: a counterweight block 101 and a connecting column 102, wherein the end surface of the deposition member 10 is fixedly connected to one end of the connecting column 102, and the other end of the connecting column 102 is fixedly connected to the end surface of the counterweight block 101;

[0031] The red oil tank 1 further includes a scale 11 , and the front portion of the red oil tank 1 is fixedly connected with the scale 11 .

[0032] Working principle: when refueling the oil and gas shock absorber column, first put the liquid inlet pipe 6 into the extension frame 7, then adjust the sliding of the sliding column 92, so that the chimeric plug 91 is stuck in the liquid outlet of the liquid inlet pipe 6, and then the extension frame 7 is supported against the connection part of the liquid inlet pipe 6 and the shrink hose 5, and then the extension frame 7 is rotated so that the extension frame 7 drives the limit ring 72 to rotate through the fixed column 71, and the arc groove 721 drives the chimeric claw 722 to move. At this time, the chimeric claw 722 will be stuck between the two tooth blocks 922, so that the limit ring 72 and the sliding column 92 are fixed. In this way, when the liquid inlet pipe 6 is inserted into the inner cylinder of the shock absorber column, the specific method is to remove the refueling and inflation port on the upper part of the shock absorber column, there will be a hole at the installation position, and the liquid inlet pipe 6 will be directly inserted into the small hole until it is near the bottom of the inner cylinder, and the cooperation of the extension frame 7 and the sliding frame 9 can ensure that the liquid inlet pipe 6 will not be bent, so as to avoid the accumulation of bubbles at the bending point and affect the flow of the fluid, and the lower end surface of the sliding frame 9 is installed The depositing piece 10 and the counterweight 101 installed will drive the liquid inlet pipe 6 to sink to the bottom of the inner tube, so that during the refueling process, the oil level is higher than the liquid outlet of the liquid inlet pipe 6, ensuring that the end of the liquid pipe 6 is always immersed in the liquid to prevent air from entering the liquid pipe 6; the oil in the red oil tank 1 is sent to the inner tube of the shock absorber column through the micro electric pump 4, and the micro electric pump 4 uses a 24-volt DC motor with moderate power, which can not only ensure a certain flow rate, but also will not form high-pressure oil mist, saving the trouble of multiple people taking turns to pump, and the whole refueling process only takes 30 minutes, and then it can be done after 30 minutes of rest. The next step of inflation can be carried out. The biggest advantage of this method is that as the red oil level slowly rises, the air in the cylinder naturally overflows, refueling does not stop and there is very little air mixed in the oil, and a small amount of air can also be completely discharged when the inner tube is compressed once after resting. Through this method, the normal refueling and inflation time of a single landing gear is 1.5-2 hours, which can save 2-3 hours compared with the original.

[0033] The above shows and describes the basic principle, main features and advantages of the utility model. Those skilled in the art should understand that the utility model is not limited by the above embodiments, and the above embodiments and descriptions are only for explaining the principle of the utility model. Without departing from the spirit and scope of the utility model, the utility model may have various changes and improvements, and these changes and improvements fall within the scope of the utility model to be protected.

Claims

1. A refueling device for a shock absorber strut of an aircraft landing gear, comprising a red oil tank (1), characterized in that: The upper part of the red oil tank (1) is provided with an oil supply port (2), the oil supply port (2) is plugged with an oil pipe (3), the end of the oil pipe (3) is plugged with a micro electric pump (4), the liquid outlet of the micro electric pump (4) is plugged with one end of a shrink hose (5), the other end of the shrink hose (5) is plugged with a liquid inlet pipe (6), the end of the liquid inlet pipe (6) is sleeved with an extension frame (7), the end of the extension frame (7) is sleeved with an extension frame (7), the end of the extension frame (7) is movably connected to a sliding frame (9), and the end of the sliding frame (9) is fixedly connected to a deposition member (10).

2. A refueling device for an aircraft landing gear shock strut according to claim 1, characterized in that: The extension frame (7) comprises: a fixing column (71) and a limiting ring (72); the end surface of the extension frame (7) is fixedly connected to one end of the fixing column (71), and the other end of the fixing column (71) is fixedly connected to the end surface of the limiting ring (72).

3. A refueling device for an aircraft landing gear shock strut according to claim 2, characterized in that: The limiting ring (72) further comprises: an arcuate groove (721) and an engaging claw (722); the ring body of the limiting ring (72) is provided with an arcuate groove (721); the inner wall of the arcuate groove (721) is fixedly connected with the engaging claw (722); and the arcuate groove (721) is slidably connected to the rod body of the sliding frame (9).

4. A refueling device for an aircraft landing gear shock strut according to claim 3, characterized in that: The sliding frame (9) comprises: an interlocking plug (91) and a sliding column (92); the end face of the sliding frame (9) is fixedly connected to the end of the sliding column (92); the middle part of the sliding frame (9) is fixedly connected to the end of the interlocking plug (91); and the groove opened on the end face of the sliding frame (9) is interlockedly connected to the end of the deposition member (10).

5. A refueling device for an aircraft landing gear shock strut according to claim 4, characterized in that: The sliding column (92) further comprises: a circular block (921) and a tooth block (922); the column body of the sliding column (92) is fixedly connected with a plurality of tooth blocks (922) at equal intervals; and the end of the sliding column (92) is fixedly connected to the end of the circular block (921).

6. A refueling device for an aircraft landing gear shock strut according to claim 1, characterized in that: The deposition element (10) comprises: a counterweight (101) and a connecting column (102); the end surface of the deposition element (10) is fixedly connected to one end of the connecting column (102); and the other end of the connecting column (102) is fixedly connected to the end surface of the counterweight (101).

7. A refueling device for an aircraft landing gear shock strut according to claim 1, characterized in that: The red oil tank (1) further comprises a scale (11), and the front part of the red oil tank (1) is fixedly connected with the scale (11).

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