Power-off water adding device for aircraft water tank

Abstract

A power-off water adding device for an aircraft water tank can accurately control the amount of water added into the water tank even in a power-off water adding mode of an aircraft. Comprises: a water tank for storing water; the overflow guide pipe assembly is inserted into the water tank and can rotate to a plurality of different openings to overflow corresponding to a plurality of different liquid levels of the water tank; the knob can rotate to select a plurality of gears; and the transmission shaft is used for transmitting the rotation of the knob to the overflow guide pipe assembly so as to drive the overflow guide pipe assembly to rotate to a plurality of different openings.

Description

Technical Field

[0001] The utility model relates to the field of aircraft drinking water systems, in particular to the technical field of adding water to aircraft water tanks. Background Art

[0002] In the prior art, two water adding modes of an aircraft drinking water system are known: first, when the aircraft is powered on, the service personnel can select the water adding mode or water adding amount through the onboard equipment, and the system controls to automatically open the water adding valve and monitor the water adding amount of the water tank, thereby achieving the filling of the water tank with a certain water adding amount (1%-100%); second, when the aircraft is powered off, the service personnel manually open the water adding valve and directly fill the water tank to overflow (the overflow conduit is fixed above the water tank, and the conduit inlet is flush with the 100% water level of the water tank). At this time, the overflow pipe is connected to the 100% water level of the water tank, and the completion of water adding is judged by the occurrence of overflow phenomenon.

[0003] That is to say, currently, when the aircraft is powered off, service personnel can only fill the water tank manually and cannot fill it to a specific amount.

[0004] However, during peak hours, in order to avoid crowded queues and save ground service time, service personnel often need to cut off the power supply and manually add water. At this time, the amount of water added to the water tank is often determined according to the flight's flight distance, so it is often not constant to 100%.

[0005] In this case, how to manually add a specific amount of water to the water tank when the aircraft is powered off becomes an urgent problem to be solved. Utility Model Content

[0006] The utility model is completed in view of the above technical problems, and its purpose is to provide a power-off water-adding device for an aircraft water tank, which can accurately control the amount of water added to the water tank in the aircraft power-off water-adding mode.

[0007] In order to achieve the above-mentioned purpose, the first aspect of the utility model provides a power-off water-filling device for an aircraft water tank, comprising: a water tank, which is used to store water; an overflow conduit assembly, which is inserted into the water tank and can be rotated to overflow to multiple different openings corresponding to multiple different liquid levels of the water tank; a knob, which can be rotated to select multiple gears; and a transmission shaft, which transmits the rotation of the knob to the overflow conduit assembly to drive the overflow conduit assembly to rotate to multiple different openings.

[0008] According to the above structure, the overflow conduit assembly is driven to rotate to a plurality of different openings via the transmission shaft by rotating the button, so that water filling is stopped when the water in the water tank overflows from different openings. Thus, the water in the water tank that is higher than the water level of the opening overflows to the outside of the aircraft via the overflow conduit assembly, and the amount of water added to the water tank can be controlled to a specific amount. Compared with the past, a specific amount of water can be added to the water tank according to the flight range of the aircraft on that day, thereby saving water and reducing the load of the aircraft.

[0009] The power-off water-filling device for an aircraft water tank according to the second aspect of the utility model is based on the power-off water-filling device for an aircraft water tank according to the first aspect, wherein the overflow conduit assembly comprises a moving tube and a static tube, wherein the moving tube can be rotatably embedded in the static tube and directly connected to the transmission shaft, and a first opening opened along a spiral line with a variable pitch is formed around the circumferential wall of the moving tube; a rectangular second opening is opened along the axial direction on the circumferential wall of the static tube, and the range of the second opening in the axial direction can cover the first opening stop.

[0010] According to the above structure, the second opening formed in the static tube can cover the first opening formed in the dynamic tube in the axial direction. Therefore, when the first opening and the second opening overlap, the water in the water tank will overflow through the hole formed by the overlap. Therefore, the water level in the water tank can only be maintained at the water level of the hole formed by the overlap. In this way, the amount of water added to the water tank can be controlled.

[0011] The power-off water-filling device for an aircraft water tank of the third aspect of the utility model is based on the power-off water-filling device for an aircraft water tank of the second aspect, wherein the first opening is formed as four circular holes, and the second opening is formed as a rectangular hole with the axial direction of the static pipe as the long side direction.

[0012] According to the above structure, since the first opening is formed as four circular holes and the second opening is formed as a rectangular hole with the axial direction of the static tube as the long side direction, when the moving tube rotates relative to the static tube, the four circular holes overlap with the rectangular holes in sequence, and the water in the water tank can overflow through the holes formed by the overlapping of the circular holes and the rectangular holes (i.e., at four water level heights). In this way, the amount of water added to the water tank can be controlled to four specific amounts.

[0013] The power-off water-filling device for an aircraft water tank according to the fourth aspect of the utility model is based on the power-off water-filling device for an aircraft water tank according to the second aspect of the utility model, wherein the overflow conduit assembly comprises a moving tube and a static tube, wherein the moving tube can be rotatably embedded in the static tube and directly connected to the transmission shaft, and an annular hole opened along a spiral line ascendingly is formed around the circumferential wall of the moving tube as a first opening, and a second opening is opened along the axial direction on the circumferential wall of the static tube, and the second opening is formed as a rectangular hole that can cover the first opening in the axial direction.

[0014] According to the above structure, since the first opening is formed as an annular hole, that is, it covers 360 degrees in the circumferential direction, and the second opening is formed as a rectangular hole that can cover the first opening in the axial direction, when the moving tube rotates relative to the static tube, a part of the annular hole always overlaps with the rectangular hole. Therefore, no matter how many degrees the moving tube rotates, the water in the water tank can always overflow through the hole formed by the overlap of a part of the annular hole and the rectangular hole (that is, at any water level height). In this way, the amount of water added to the water tank can be controlled at any amount. In this way, the amount of water added to the water tank can be controlled with high precision.

[0015] The power-off water-filling device for an aircraft water tank of the fifth aspect of the utility model is based on the power-off water-filling device for an aircraft water tank of the first aspect of the utility model, wherein the overflow conduit assembly comprises a moving tube and a static tube, wherein the moving tube can be rotatably embedded in the static tube and directly connected to the transmission shaft, and a third opening opened ascending along a spiral line of a variable pitch is formed around the circumferential wall of the static tube; a fourth opening is opened axially on the circumferential wall of the moving tube, and the fourth opening can cover the third opening in the axial direction.

[0016] According to the above structure, the third opening formed in the static tube can cover the fourth opening formed in the dynamic tube in the axial direction. Therefore, when the third opening and the fourth opening overlap, the water in the water tank will overflow through the hole formed by the overlap. Therefore, the water level in the water tank can only be maintained at the water level of the hole formed by the overlap. In this way, the amount of water added to the water tank can be controlled.

[0017] The power-off water-filling device for an aircraft water tank of the sixth aspect of the utility model is based on the power-off water-filling device for an aircraft water tank of the fifth aspect of the utility model, wherein the third opening is formed as four circular holes, and the fourth opening is formed as a rectangular hole with the axial direction of the moving tube as the long side direction.

[0018] According to the above structure, since the third opening is formed as four circular holes and the fourth opening is formed as a rectangular hole with the axial direction of the moving tube as the long side direction, when the moving tube rotates relative to the static tube, the four circular holes of the static tube overlap with the rectangular hole of the moving tube in sequence, and the water in the water tank can overflow through the holes formed by the overlapping of the circular holes and the rectangular holes (i.e., at four water level heights). Thus, the amount of water added to the water tank can be set to four specific amounts.

[0019] The power-off water-filling device for an aircraft water tank of the seventh aspect of the utility model is based on the power-off water-filling device for an aircraft water tank of the fifth aspect of the utility model, and the overflow conduit assembly includes a moving tube and a static tube, and the moving tube can be rotatably embedded in the static tube and directly connected to the transmission shaft, and an annular hole opened along a spiral line is formed around the circumferential wall of the static tube as a third opening, and a rectangular hole with the axial direction as the long side direction is formed on the circumferential wall of the moving tube as a fourth opening.

[0020] According to the above structure, since the third opening is formed as an annular hole, that is, it covers 360 degrees in the circumferential direction, and the fourth opening is formed as a rectangular hole with the axial direction of the moving tube as the long side direction, when the moving tube rotates relative to the static tube, a part of the annular hole always overlaps with the rectangular hole. Therefore, no matter how many degrees the moving tube rotates, the water in the water tank can always overflow through the hole formed by the overlap of a part of the annular hole and the rectangular hole (that is, at any water level height). In this way, the amount of water added to the water tank can be controlled at any amount. In this way, the amount of water added to the water tank can be controlled with high precision.

[0021] The power-off water-filling device for an aircraft water tank of the eighth aspect of the utility model is based on the power-off water-filling device for an aircraft water tank of any one of the first to third, fifth to sixth aspects of the utility model, and the knob is correspondingly provided with four water levels of 25%, 50%, 75% and 100%.

[0022] According to the above structure, the four water levels of 25%, 50%, 75% and 100% are correspondingly set by the knob, so that the amount of water added to the water tank can be evenly controlled.

[0023] The power-off water-filling device for an aircraft water tank of the ninth aspect of the utility model is based on the power-off water-filling device for an aircraft water tank of any one of the first to seventh aspects of the utility model. If the amount of water in the water tank is set to V and the rotation angle of the knob is set to θ, then the rotation angle θ is directly proportional to the amount of water V, that is, θ=k*V (wherein k is a constant).

[0024] According to the above structure, since the rotation angle of the knob is directly proportional to the amount of water V added to the water tank, the amount of water added to the water tank can be intuitively controlled by rotating the knob. In this way, the operation of adding a specific amount of water to the water tank can be made simpler.

[0025] The power-off water-adding device for an aircraft water tank according to the tenth aspect of the utility model is based on the power-off water-adding device for an aircraft water tank according to the ninth aspect of the utility model, wherein the water tank is formed into a cylindrical middle portion and hemispherical ends. If the length of the middle portion is set to L, the radius of the two ends is set to R, and the water level of the water tank is set to h, then the water volume V, L, R, h of the water tank satisfies the following relationship, that is,

[0026] According to the above structure, by making the water level h of the water tank, the water volume V of the water tank, the length L of the middle part of the water tank, and the radius R of the two ends of the water tank satisfy It can be ensured that each angle value corresponding to the rotation angle θ of the knob 1 corresponds to the position where the first opening and the second opening overlap, in other words, the overflow position where the water volume in the water tank is 25%, 50%, 75%, and 100% of the maximum water volume Vmax.

[0027] The power-off water-filling device for an aircraft water tank of the eleventh aspect of the utility model is based on the power-off water-filling device for an aircraft water tank of any one of the first to seventh aspects of the utility model, and a static sealing structure is provided at the connection between the overflow conduit assembly and the water tank.

[0028] According to the above structure, by providing a static sealing structure at the connection between the overflow conduit assembly and the water tank, it is possible to prevent the water in the water tank from leaking to the outside of the water tank through the connection.

[0029] The twelfth aspect of the utility model is a power-off water-filling device for an aircraft water tank. On the basis of the power-off water-filling device for an aircraft water tank of any one of the second to seventh aspects of the utility model, a dynamic sealing structure is arranged between the moving pipe and the static pipe, and the dynamic sealing structure includes: a static ring sleeved on the outer circumferential surface of the moving pipe and fixed to the static pipe via a first sealing ring; a dynamic ring sleeved on the moving pipe and rotating integrally with the moving pipe; and a compensation spring, wherein the compensation spring compensates for pressing the moving ring against the static ring via the second sealing ring.

[0030] According to the above structure, by forming a dynamic seal between the static pipe and the dynamic pipe, the water in the water tank can be prevented from entering between the static pipe and the dynamic pipe, and the water in the water tank can only flow into the dynamic pipe through the hole formed by the overlap of the two openings when the dynamic pipe rotates to the position where the first opening and the second opening overlap. In this way, it can be ensured that the water flowing out of the water tank must be the water flowing into the inside of the dynamic pipe from the hole formed by the overlap of the two openings. In this way, it can be reliably ensured that when the water flows out of the overflow conduit assembly, it corresponds to the specific water level height rotated by the knob 1, so that the amount of water added to the water tank can be accurately controlled by the knob 1. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the technical solution of the embodiment of the utility model, the drawings required for use in the embodiment are 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 creative work.

[0032] Figure 1 1 is a schematic diagram showing the general structure of a power-off water filling device for an aircraft water tank according to a first embodiment.

[0033] Figure 2 It is a schematic diagram showing the general structure of an overflow conduit assembly of a power-off water filling device for an aircraft water tank according to a first embodiment.

[0034] Figure 3 It is a coordinate diagram showing the relationship between the rotation angle of the knob of the power-off water filling device for an aircraft water tank and the water volume in the water tank according to the first embodiment.

[0035] Figure 4 It is a coordinate diagram showing the relationship between the water level height of the water tank and the water volume of the water tank of the power-off water filling device for aircraft water tanks according to the first embodiment.

[0036] Figure 5 It is a coordinate diagram showing the relationship between the water level height of a water tank and the water volume of the water tank in a power-off water filling device for an aircraft water tank according to Modification 1 of the first embodiment.

[0037] (Explanation of symbols)

[0038] 1 knob;

[0039] 2 transmission shaft;

[0040] 3 gears;

[0041] 4 overflow conduit assembly;

[0042] 41 motion tube;

[0043] 411 Trail Division;

[0044] 412 large diameter part;

[0045] 4121 first opening;

[0046] 42 static tube;

[0047] 421 head;

[0048] 422 tube body;

[0049] 4221 second opening;

[0050] 43 overflow conduit gear;

[0051] 44 static ring;

[0052] 45 moving ring;

[0053] 46 compensation spring;

[0054] 47 first sealing ring;

[0055] 48 bolts;

[0056] 49 second sealing ring;

[0057] 5 water tank;

[0058] 6. Discharge hose;

[0059] 7 Outside the aircraft;

[0060] 8 base;

[0061] 9 sealing ring;

[0062] R is the radius of the two ends of the hemispherical shape of the water tank;

[0063] L is the length of the cylindrical middle part of the water tank. DETAILED DESCRIPTION

[0064] Below, refer to Figures 1 to 5 Various embodiments of a power-off water-filling device for an aircraft water tank are described. This embodiment is a power-off water-filling device for an aircraft water tank that can fill a specific amount of water into the water tank even when the aircraft is in a power-off mode.

[0065] For the sake of convenience, in the following Figure 1 and Figure 2 In the description, the axial direction in the moving pipe 41 and the static pipe 42 of the overflow conduit assembly 4 is referred to as the Z direction, and the direction orthogonal to the Z direction is referred to as the X direction.

[0066] (First Embodiment)

[0067] In this embodiment, if Figure 1As shown, the power-off water-adding device for an aircraft water tank mainly comprises: a knob 1, which is arranged on a water system service panel and can select water levels of 25%, 50%, 75% and 100%; a transmission shaft 2, which is connected to the knob 1 and can transmit the rotation of the knob 1; a gear 3, which is connected to the transmission shaft 2; an overflow conduit assembly 4, which is sealedly inserted into a base 8 via a sealing ring 9 and fixed to the base 8 via bolts 48; a water tank 5, which is cylindrical in the middle and hemispherical at both ends, and stores water therein, and the overflow conduit assembly 4 is inserted into the bottom of the water tank 5 via the base 8; and a discharge hose 6, which can discharge water overflowing into the overflow conduit assembly 4 to the outside 7 of the aircraft.

[0068] In this embodiment, when the service personnel turn the knob 1 to the positions of 25%, 50%, 75% and 100% respectively, the overflow conduit assembly 4 opens the opening to overflow at the water levels of 25%, 50%, 75% and 100% of the maximum water volume Vmax of the water tank 5, and discharges the overflowing water to the outside 7 of the aircraft through the discharge hose 6.

[0069] Once the water in the water tank 5 begins to overflow to the outside of the aircraft 7 through the overflow conduit assembly 4, the water addition can be stopped. Thus, a specific amount of water can be added to the water tank 5 as needed. Regarding the "specific amount", four amounts of 25%, 50%, 75% and 100% of the volume of the water tank are set in this embodiment.

[0070] Correspondingly, the knob 1 of this embodiment is also provided with four gears of 25%, 50%, 75% and 100% corresponding to the above four specific amounts. By setting these four gears, the service personnel can set the water addition amount at four gears.

[0071] like Figure 2As shown, the overflow conduit assembly 4 includes: a static tube 42, which is formed into a roughly T-shaped hollow tube, and its head 421 has a relatively large diameter and is fixed to the base 8 via bolts 48. The tube body 422 extends from the head 421 to the X2 side to the bottom of the water tank 5, and a sealing ring 9 is sandwiched between the connection corner of the head 421 and the tube body 422 and the base 8 to statically seal the static tube 42 and the base 8; a moving tube 41, which can be rotatably inserted into the static tube 42, including a small diameter portion 411 that partially extends from the static tube 42 and a large diameter portion 412 that is completely inserted into the static tube 42, and the small diameter portion 411 extends from Z 1 side is inserted into the overflow duct gear 43 and the head 421 of the static tube 42 in sequence from the Z2 side to the Z2 side; and a dynamic sealing structure, which is arranged between the static tube 42 and the dynamic tube 41, and includes a static ring 44 which is sleeved on the small diameter portion 411 and fixed to the inner side of the tube body portion 422 via a first sealing ring 47, a dynamic ring 45 which is sleeved on the X2 side of the small diameter portion 411 relative to the static ring 44 and fixed to the small diameter portion 411 as a whole, and a compensation spring 46 whose Z2 side end abuts against the stepped connection between the small diameter portion 411 and the large diameter portion 412 and whose Z1 side end abuts against the Z2 side end surface of the dynamic ring 45 via a second sealing ring 49.

[0072] According to the overflow conduit assembly 4 constructed in the above manner, by providing the sealing ring 9 between the static tube 42 and the base 8, the static tube 42 can be fixed to the base 8 in a static sealing manner. In addition, by providing the dynamic sealing structure constructed as described above between the dynamic tube 41 and the static tube 42, since the first sealing ring 47 is provided between the Z1 side corner of the Z1 side inner circumference of the static tube 42 and the outer circumference of the static ring 44, the second sealing ring 49 is provided between the Z1 side corner of the inner circumference of the dynamic ring 45 and the outer circumference of the small diameter portion 411 of the dynamic tube 41, and the compensation spring 46 applies force to the dynamic ring 45 to press it against the Z2 side surface of the static ring 44, when the overflow conduit gear 43 drives the dynamic tube 41 to rotate, the dynamic tube 41 drives the dynamic ring 45 to rotate, and the compensation spring 46 pushes the Z1 side end surface of the dynamic ring 45 and the Z2 side end surface of the static ring 44 to always be in close contact. Therefore, when the service personnel turns the knob 1 to drive the moving tube 41 to rotate relative to the static tube 42, the end faces of the two are always sealed, so that the water in the water tank 5 can be prevented from leaking through the moving tube 41 and the static tube 42, thereby ensuring that the water in the water tank 5 can only overflow into the inside of the moving tube 41 through the specific opening and be discharged to the discharge hose 6. In this way, it can be ensured with high accuracy that the amount of water V added to the water tank 5 is the specific amount set by the knob 1.

[0073] Furthermore, in order to achieve 25%, 50%, 75% and 100% of the maximum water volume Vmax of the water tank set above, as Figure 4As shown, four first openings 4121 are provided on the peripheral wall of the large diameter portion 412 of the moving tube 41 along a spiral line S with different pitches. The four first openings 4121 are all formed as circular holes and rotate around the large diameter portion 412 once.

[0074] The water level height h corresponding to 25% of the maximum water volume Vmax of the water tank is h1, that is, the water level height of the first first opening 4121 from the left in the figure is h1; the water level height h corresponding to 50% of the maximum water volume Vmax of the water tank is h2, that is, the water level height of the second first opening 4121 from the left in the figure is h2, the water level height h corresponding to 75% of the maximum water volume Vmax of the water tank is h3, that is, the water level height of the third first opening 4121 from the left in the figure is h3, and the water level height h corresponding to 100% of the maximum water volume Vmax of the water tank is h4.

[0075] Correspondingly, Figure 4 As shown, corresponding to the axial range of the above-mentioned four first openings 4121, a rectangular second opening 4221 is formed along the axial direction on the peripheral wall of the static tube 21, and the second opening 4221 covers the above-mentioned four first openings 4121 in the axial direction.

[0076] By arranging four first openings 4121 on the peripheral wall of the moving tube 41 and correspondingly arranging second openings 4221 on the peripheral wall of the static tube 42 as described above, when the moving tube 41 rotates to a position where the first openings 4121 overlap with the second openings 4221, the water in the water tank 5 will enter the moving tube 41 through the hole formed by the overlap of the second openings 4221 and the first openings 4121 and be discharged to the discharge hose 6 through the moving tube 41, and thereby be discharged to the outside 7 of the aircraft.

[0077] Thus, when Knob 1 is turned to Figure 4 When the first opening 4121 and the second opening 4221 from the left overlap (i.e. rotated 90 degrees), the water level of the water tank 5 reaches h1, and the water volume V reaches 25% of the maximum capacity Vmax of the water tank; when the knob 1 is rotated to Figure 4 When the second opening 4121 from the left overlaps with the second opening 4221 (i.e., rotated 180 degrees), the water level of the water tank 5 reaches h2, and the water volume V reaches 50% of the maximum capacity Vmax of the water tank; when the knob 1 is rotated to Figure 4 When the third second opening 4121 from the left overlaps with the second opening 4221 (i.e., rotated 270 degrees), the water level of the water tank 5 reaches h3, and the water volume V reaches 75% of the maximum capacity Vmax of the water tank; when the knob 1 is rotated to Figure 4When the fourth second opening 4121 counting from the left overlaps with the second opening 4221 (i.e. rotated 360 degrees), the water level of the water tank 5 reaches h4, and the water volume V reaches 100% of the maximum capacity Vmax of the water tank.

[0078] Thus, the rotation angle θ of the knob 1 and the water volume V of the water tank 5 are as follows: Figure 3 As shown, it is in direct proportion, specifically θ=k*V (wherein k is a constant).

[0079] As described above, a positive proportional relationship is formed between the rotation angle θ of the knob 1 and the water volume V in the water tank 5, so that the service personnel can intuitively observe the water volume V added to the water tank 5 through the rotation angle of the knob 1, thereby making the operation of controlling the water volume added to the water tank 5 through the knob 1 easier.

[0080] In order to achieve the above-mentioned positive proportional relationship between the rotation angle θ of the knob 1 and the water volume V of the water tank 5, it is required through experiments and calculations that the water level height h of the water tank and the water volume V of the water tank meet Figure 4 The relationship shown by the spiral line S is:

[0081]

[0082] Where "L" is Figure 1 The length of the cylindrical middle portion of the water tank 5 shown is "R", and the radius of the two side ends of the hemispherical shape.

[0083] By setting the relationship between the water level h of the water tank and the water volume V of the water tank and the relationship between the water volume V of the water tank and the rotation angle θ of the knob 1 as described above, the amount of water added to the water tank 5 can be simply adjusted by the knob 1. Compared with the past, in the aircraft power-off mode, not only can the knob 1 be manually rotated to add water to the water tank 5, but also a specific amount of water can be added to the water tank 5 according to the flight of the day. In this way, compared with the case of filling up every time, not only water can be saved, but also the load of the aircraft can be reduced.

[0084] (Variation 1 of the First Embodiment)

[0085] Above, refer to Figures 1 to 4 The power-off water-adding device of the first embodiment and its working principle of adding a specific amount of water to the water tank 5 are described. In the above embodiment, the knob 1 is set to four gears of 25%, 50%, 75% and 100%, corresponding to 25%, 50%, 75% and 100% of the maximum water volume Vmax of the water tank 5, but the utility model is not limited to this, and the knob 1 can also be set to three gears, five gears or other number of gears, for example Figure 5 The knob 1 shown is a variation 1 in which N gears (any number between 1% and 100%) are set.

[0086] like Figure 5 As shown, the four first openings 4121 in the large diameter portion 412 of the moving tube 41 in the first embodiment are replaced with annular holes 4121A. Except for the different arrangement of the first openings 4121, the rest are the same as the first embodiment.

[0087] In this variation, if Figure 5 As shown, a spirally ascending annular hole 4121A is formed all around the circumference of the large diameter portion 412 of the moving tube 41 as a first opening. Correspondingly, a second opening 4221 of a rectangular hole with the axial direction as the long side direction is formed on the tube wall of the tube body portion 422 of the static tube 42 in the same manner as in the first embodiment described above, and the second opening 4221 can cover the annular hole 4121A in the axial direction (i.e., the Z direction).

[0088] In this way, the annular hole 4121A surrounds the entire circumference of the large diameter portion 412 of the moving tube 41 along the spiral line. Therefore, no matter how much the moving tube 41 rotates relative to the static tube 42, a portion of the annular hole 4121A always overlaps with the second opening 4221 of the static tube 42, and the height of the hole formed by the overlap of the two changes continuously with the rotation of the moving tube 41. Figure 5 In the figure, for the sake of convenience, only the portions of the annular holes near 25%, 50%, 75%, and 100% are shown. In the figure, the first large diameter portion 412 from the left shows a portion of the annular hole 4121A near the water level height corresponding to when the water tank V is 25% of the maximum capacity Vmax of the water tank, the second large diameter portion 412 from the left shows a portion of the annular hole 4121A near the water level height corresponding to when the water tank V is 50% of the maximum capacity Vmax of the water tank, the third large diameter portion 412 from the left shows a portion of the annular hole 4121A near the water level height corresponding to when the water tank V is 75% of the maximum capacity Vmax of the water tank, and the fourth large diameter portion 412 from the left shows a portion of the annular hole 4121A near the water level height corresponding to when the water tank V is 100% of the maximum capacity Vmax of the water tank. Portions of these four annular holes 4121A are located on the same curve in the figure, and the water levels are all within the water level height range of the second opening 4221 of the tube body 422 of the static tube 42 (i.e., the axial direction of the static tube 42).

[0089] Moreover, the relationship between the rotation angle θ of the knob 1 and the water volume V of the water tank 5 is also as follows: Figure 3 As shown, a direct proportional relationship is satisfied, that is, θ=k*V (where k is a constant). In this way, the service personnel can intuitively judge the amount of water added to the water tank 5 by rotating.

[0090] Moreover, in order to realize the above-mentioned positive proportional relationship between the rotation angle θ of the knob 1 and the water volume V of the water tank 5, it is required through experiments and calculations that the water level height h of the water tank and the water volume V of the water tank meet Figure 4 The relationship shown by the spiral line S is:

[0091]

[0092] Where "L" is Figure 1 The length of the cylindrical middle part of the water tank 5 shown in the figure, "R" is the radius of the two ends of the hemispherical shape. In this way, by setting the relationship between the water level h of the water tank and the water volume V of the water tank, and the relationship between the water volume V of the water tank and the rotation angle θ of the knob 1 as described above, the amount of water added to the water tank 5 can be simply adjusted by rotating the knob 1.

[0093] Similar to the first embodiment, the power-off water filling device of this modified example can also limit the amount of water added to the water tank 5 to a certain specific amount by overlapping the second opening 4221 of the moving pipe 41 with the annular hole 4121A and the static pipe 42 in the aircraft power-off mode. Compared with the previous situation of filling the water tank 5 with water every time, it can not only save water but also reduce the load of the aircraft.

[0094] In addition, according to the power-off water filling device constructed as described above, when the knob 1 starts to rotate, the annular hole 4121A of the large diameter portion 412 of the movable tube 41 always overlaps with the second opening 4221 within the water level range of the second opening 4221. Therefore, when the knob 1 is rotated to a certain position, the annular hole 4121A of the movable tube 41 overlaps with the second opening 4221 at a certain water level, and the water in the water tank 5 exceeding the water level overflows to the discharge hose 6 until it is transferred to the outside of the aircraft 7. Compared with the first embodiment described above, the amount of water added to the water tank can be controlled to any amount of water, and the amount of water added to the water tank can be controlled with higher accuracy than the first embodiment described above.

[0095] (Variation 2 of the first embodiment)

[0096] As mentioned above, in the above Figures 1 to 4 In the first embodiment shown, four circular holes rising along a spiral line with a variable pitch are provided in the tube wall of the moving tube 41 as the first openings, and correspondingly, a rectangular hole 4221 is provided in the tube body 422 of the static tube 42 within the range of the four circular holes in the axial direction as the second opening. However, the present invention is not limited to this, and although not shown in the figure, the arrangement of the first opening of the static tube and the second opening of the moving tube can also be interchanged, that is, four circular holes (i.e., the third openings) rising along a spiral line with a variable pitch are provided in the tube body of the static tube, and the rectangular hole (i.e., the fourth opening) is provided within the range of the four circular holes in the axial direction of the moving tube.

[0097] According to the power-off water-filling device constructed as described above, similarly to the above-mentioned first embodiment, in the aircraft power-off water-filling mode, when the service personnel manually rotate the movable pipe, the water in the water tank will enter the interior of the movable pipe through the hole formed by the overlapping of the third opening and the fourth opening and be discharged to the discharge hose through the movable pipe, thereby being discharged outside the aircraft.

[0098] Thus, when the water in the water tank reaches a certain amount (for example, 25%, 50%, 75%, 100% of the maximum capacity Vmax of the water tank), the water overflows from the moving pipe of the overflow conduit assembly to the outside of the aircraft, and it can be determined to stop adding water. Thus, compared with the past, in the aircraft power-off mode, not only can the water tank be added by manually rotating the knob, but also a certain amount of water can be added to the water tank according to the flight of the day. Thus, compared with the case of filling up every time, not only water can be saved, but also the weight of the aircraft can be reduced.

[0099] (Variation 3 of the first embodiment)

[0100] In the second variation of the first embodiment described above, although not shown in the figure, the third openings provided in the body of the static tube are formed as four circular holes rising along the spiral line of the variable pitch, and the corresponding gear positions of the knob 1 are four gear positions, but the utility model is not limited to this. In this variation, the third openings may also be formed as three circular holes, five circular holes or other number of circular holes rising along the spiral line in the body of the static tube, or as Figure 5 In addition, in this embodiment, as in the first embodiment, the large diameter portion of the moving tube and the Figure 4 A rectangular hole (ie, the fourth opening) is formed with the axial direction as the long side direction. In addition, except that the arrangement of the third opening is different from that of the above-mentioned modification example 2, the rest of the parts are the same as those of the above-mentioned modification example 2.

[0101] According to the power-off water filling device constructed as described above, since the annular hole surrounds the entire circumference of the static tube along the spiral line, no matter how many degrees the dynamic tube rotates relative to the static tube, a portion of the annular hole always overlaps with the rectangular hole of the dynamic tube, and the height of the hole formed by the overlap of the two constantly changes with the rotation of the dynamic tube. When the knob is rotated to a certain position, the annular hole of the static tube overlaps with the rectangular hole of the dynamic tube at a certain water level, and the water in the water tank that exceeds the water level overflows to the outside of the aircraft. Compared with the above-mentioned modification 2, the amount of water added to the water tank can be controlled at any amount, and the amount of water added to the water tank can be controlled with higher precision.

[0102] Above, in order to make the purpose, technical solution and advantages of the preferred embodiment of the utility model clearer, the technical solution of the preferred embodiment of the utility model is clearly and completely described in conjunction with the accompanying drawings. Obviously, the described embodiment is a part of the embodiment of the utility model, not all of the embodiments. Based on the preferred embodiment of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work belong to the scope of protection of the utility model.

[0103] In the above-mentioned embodiment and its modified example, a sealing ring is used as a static sealing member between the static pipe and the water tank, but the present invention is not limited thereto, and other types of sealing members may also be used.

[0104] In the above-mentioned embodiment and its modified example, a friction pair consisting of a static ring and a dynamic ring is used as a dynamic sealing member between the dynamic pipe and the static pipe, but the present invention is not limited to this, and other dynamic sealing methods such as labyrinth seals, oil seals, etc. may also be used.

[0105] Furthermore, in the above-mentioned embodiment and its modified examples, the second opening is formed into a rectangular shape, but the present invention is not limited thereto, and may be formed into an elliptical shape, an oblong shape or other shapes as long as it can cover the first opening in the axial direction.

Claims

1. A power-off water-adding device for an aircraft water tank, characterized in that: include: A water tank, wherein the water tank is used to store water; An overflow conduit assembly, the overflow conduit assembly is inserted into the water tank and can rotate to overflow at multiple different openings corresponding to multiple different liquid levels of the water tank; A knob that can be rotated to select a plurality of gears; and A transmission shaft transmits the rotation of the knob to the overflow conduit assembly to drive the overflow conduit assembly to rotate to a plurality of different openings.

2. The power-off water-adding device for aircraft water tanks according to claim 1, characterized in that: The overflow conduit assembly includes a moving tube and a static tube, wherein the moving tube is rotatably embedded in the static tube and directly connected to the transmission shaft. A first opening is formed around the peripheral wall of the moving tube and is opened along a spiral line with a variable pitch. A second opening is formed in the peripheral wall of the static pipe along the axial direction, and the second opening is formed to cover the first opening in the axial direction.

3. The power-off water-adding device for aircraft water tanks according to claim 2, characterized in that: The first opening is formed as four circular holes, The second opening is formed as a rectangular hole with the axial direction of the static tube as the long side direction.

4. The power-off water-adding device for aircraft water tanks according to claim 1, characterized in that: The overflow conduit assembly includes a moving tube and a static tube, wherein the moving tube is rotatably embedded in the static tube and directly connected to the transmission shaft. An annular hole is formed around the peripheral wall of the moving tube and is opened along a spiral line to serve as a first opening. A second opening is formed in the peripheral wall of the static pipe along the axial direction. The second opening is formed as a rectangular hole that can cover the first opening in the axial direction.

5. The power-off water-adding device for aircraft water tanks according to claim 1, characterized in that: The overflow conduit assembly includes a moving tube and a static tube, wherein the moving tube is rotatably embedded in the static tube and directly connected to the transmission shaft. A third opening is formed around the circumferential wall of the static tube and is opened in an ascending manner along a helical line with a variable pitch; A fourth opening is formed on the peripheral wall of the moving tube along the axial direction, and the fourth opening can cover the third opening in the axial direction.

6. The power-off water-adding device for aircraft water tanks according to claim 5, characterized in that: The third opening is formed as four circular holes, The fourth opening is formed as a rectangular hole with the axial direction of the moving tube as the long side direction.

7. The power-off water-adding device for aircraft water tanks according to claim 1, characterized in that: The overflow conduit assembly includes a moving tube and a static tube, wherein the moving tube is rotatably embedded in the static tube and directly connected to the transmission shaft. An annular hole is formed around the circumferential wall of the static tube and is opened along a spiral line to serve as a third opening. A rectangular hole with the axial direction as the long side direction is formed on the peripheral wall of the moving tube as a fourth opening.

8. The power-off water-adding device for aircraft water tanks according to any one of claims 1 to 3, 5 to 6, characterized in that: The knob is correspondingly provided with four water levels of 25%, 50%, 75% and 100%.

9. The power-off water-adding device for an aircraft water tank according to any one of claims 1 to 7, characterized in that: If the amount of water in the water tank is set to V, and the rotation angle of the knob is set to θ, Then the rotation angle θ is directly proportional to the water volume V, that is, θ=k*V (where k is a constant).

10. The power-off water-adding device for aircraft water tanks according to claim 9, characterized in that: The water tank is formed into a cylindrical shape in the middle and hemispherical shapes at both ends. If the length of the middle part is set to L, the radius of the two end portions is set to R, and the water level of the water tank is set to h, Then the water volume V, L, R, h of the water tank satisfies the following relationship: Satisfaction 11. The power-off water-adding device for an aircraft water tank according to any one of claims 1 to 7, characterized in that: A static sealing structure is provided at the connection between the overflow conduit assembly and the water tank.

12. The power-off water-adding device for an aircraft water tank according to any one of claims 2 to 7, characterized in that: A dynamic sealing structure is provided between the dynamic pipe and the static pipe. The dynamic sealing structure comprises: A static ring sleeved on the outer circumference of the dynamic tube and fixed to the static tube via a first sealing ring; a moving ring sleeved on the moving tube and rotating integrally with the moving tube; and A compensation spring is used to compensate for pressing the dynamic ring against the static ring via the second sealing ring.

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