A UAV oil release valve and its production process

Abstract

The present invention relates to the technical field of fuel system components, in particular to an unmanned aerial vehicle oil drain valve and a production process thereof, comprising an outer protective shell, including an outer protective tube with openings at both ends and a tube cover coaxially arranged above the outer protective tube, a first inner extension ring being fixedly arranged at the lower end of the inner wall of the outer protective tube along the circumferential direction; and an oil drain mechanism, including a rotating component, a top plate, a movable column, a positioning plate and a positioning sleeve arranged in sequence from top to bottom, the top plate, the movable column, the positioning sleeve and the outer protective tube are coaxially arranged, a sealing disk is fixedly connected to the top of the movable column, a sixth sealing groove is opened on the top surface of the sealing disk along the circumferential direction, and a sixth sealing ring for abutting against the lower end of the abutment ring is arranged in the sixth sealing groove, a limiting groove is opened on the bottom surface of the sealing disk outside the movable column along the circumferential direction, and the lower end of the movable column is slidably sleeved on the positioning plate. The setting of the oil drain valve can play a precise control role when draining oil, so that it is suitable for use with light and small unmanned aerial vehicles and has good overall practicality.

Description

Technical Field

[0001] The invention relates to the technical field of fuel system components, and in particular to an unmanned aerial vehicle fuel drain valve and a production process thereof. Background Art

[0002] A drone is an unmanned aircraft that does not require a person to board. It can be remotely controlled or have a preset flight plan. The energy source of some drones is fuel. The fuel tank provides fuel for the aircraft engine in various states. The quality of aircraft fuel has a significant impact on aircraft safety. The drain valve switch is generally located at the lowest point of the fuel tank. The fuel in the fuel tank is drained through the drain valve switch to check the fuel quality. This requires the drain valve switch to be flexible and convenient to operate, easy to maintain, and strong in sealing.

[0003] The existing open document CN104494836B - A small aircraft fuel tank drain valve switch discloses a drain valve for a small aircraft. The drain valve replaces the traditional bolts with a pin. Although it can achieve rapid and effective oil draining, the operation of such draining is still relatively complicated. In addition, since the size and weight of the UAV are small, it is necessary to accurately control the amount of oil drained, and the existing drain valve is difficult to meet the above requirements. Another example is the existing open document CN214742433U - A hydraulic system drain valve, which also discloses a drain valve. Although the drain valve can reduce its own size and weight to meet the requirements of miniaturization of UAVs, the design of the valve itself still has the problem of being unable to accurately control the draining.

[0004] In addition, when the drain valve is closed, the existing valve flow passage blocking structure is always in contact with or immersed in the fuel, which causes the fuel to cause damage to the structure (including but not limited to corrosion) during long-term use, thereby reducing the service life of the drain valve;

[0005] Therefore, it is necessary to improve the prior art to solve the above-mentioned technical problems. Summary of the invention

[0006] The purpose of this section is to summarize some aspects of embodiments of the present invention and briefly introduce some preferred embodiments. Some simplifications or omissions may be made in this section and the specification abstract and the invention title of this application to avoid blurring the purpose of this section, the specification abstract and the invention title, and such simplifications or omissions cannot be used to limit the scope of the present invention.

[0007] In view of the problem that the existing oil drain valve cannot achieve precise control of oil drain, an oil drain valve for a UAV is proposed.

[0008] To solve the above technical problems, the present invention provides the following technical solutions: an unmanned aerial vehicle oil release valve, comprising an outer casing, comprising an outer casing with openings at both ends and a tube cover coaxially arranged above the outer casing, a first inner extension ring is fixedly arranged at the lower end of the inner wall of the outer casing along the circumferential direction, a second inner extension ring is fixedly arranged at the middle part of the inner wall of the outer casing along the circumferential direction, and a butt ring is extended downwardly from the inner side of the second inner extension ring, and two coaxial limiting sleeves are fixedly arranged on the side wall of the outer casing above the second inner extension ring; and an oil release mechanism, comprising a rotating assembly, a top plate, a movable column, a positioning plate and a positioning sleeve arranged in sequence from top to bottom, the top plate, the movable column, the positioning sleeve and the outer casing are coaxially arranged, a sealing disk is fixedly connected to the top of the movable column, a sixth sealing groove is opened on the top surface of the sealing disk along the circumferential direction, and a sixth sealing ring for the lower end of the butt ring to abut is arranged in the sixth sealing groove, a limiting groove is opened on the bottom surface of the sealing disk on the outer side of the movable column along the circumferential direction, the lower end of the movable column is slidably sleeved on the positioning plate, and the outer side of the movable column is slidably sleeved with a reset The cam is an angular channel that is formed on a pair of camming axes and on which the cam is mounted, wherein the two ends of the cam are engaged with each other and wherein the first and second ends of the cam are engaged with each other, and the cam is engaged with the first and second ends of the cam.

[0009] The beneficial effects of the present invention are as follows: when the oil drain valve is in use, the staff can realize the second rectangular rod driving the rectangular frame block to rotate by rotating the first connecting column, so that the final rotation of the cam can be realized. Under the rotation of the cam, the side wall of the cam will provide a downward squeezing force to the top plate. Under the action of the squeezing force, the sealing plate will move downward synchronously, so that the sixth sealing ring on the sealing plate is separated from the butt ring, and the fuel will flow through the gap between the sealing plate and the butt ring, so that the fuel can enter from the lower end of the outer casing and then be taken out from the upper end of the outer casing. This design method can realize the adjustment of the downward movement distance of the sealing plate by driving the cam to rotate through mechanical force, so that precise oil drain control can be realized. The oil drain valve can meet the requirements of miniaturization, lightweight, reliability, durability and sealing of unmanned aerial vehicles, and has good practicality.

[0010] As a preferred solution of an oil drain valve for an unmanned aerial vehicle of the present invention, a connecting tube is coaxially fixed on the bottom surface of the tube cover, a second internal thread spirally matched with the first external thread on the outer side wall of the connecting tube is provided on the inner wall of the upper end of the outer protective tube, a hexagonal block is fixed in the middle of the top surface of the tube cover, and a second matching hole penetrating through two adjacent side surfaces is provided on the hexagonal block.

[0011] As a preferred solution of an oil drain valve for an unmanned aerial vehicle of the present invention, a first connecting plate is fixedly provided on the outer side wall of an outer casing below a limiting sleeve, a plurality of first mounting holes and first matching holes are respectively provided on the first connecting plate, and one of the first matching holes and the second matching hole are locked in series by a locking wire; a second connecting plate is fixedly provided on the outer side wall of the lower end of the outer casing, and second mounting holes are provided at four corner positions of the second connecting plate.

[0012] As a preferred solution of an unmanned aerial vehicle oil release valve of the present invention, wherein: a first sealing groove is opened on the bottom surface of the outer casing along the circumferential direction, and a first sealing ring is arranged in the first sealing groove; a fifth sealing groove is opened on the bottom surface of the top plate along the circumferential direction, and a fifth sealing ring is arranged in the fifth sealing groove; a third sealing groove is opened on the bottom surface of the tube cover on the outer side of the connecting tube along the circumferential direction, and a third sealing ring is arranged in the third sealing groove; a fourth sealing groove is opened on the outer side wall of the first connecting column along the circumferential direction, and a fourth sealing ring is arranged in the fourth sealing groove; a second sealing groove is opened on the inner wall of the limit sleeve at the position of the second connecting column along the circumferential direction, and a second sealing ring is arranged in the second sealing groove; a plug sleeve is fixedly provided on the top surface of the positioning plate on the outer side of the movable column.

[0013] As a preferred solution of an unmanned aerial vehicle oil release valve of the present invention, a second positioning hole is provided on the side wall at one end of the second connecting column, a first positioning hole is provided on the side wall of the limiting sleeve located on the outside of the outer casing coaxially with the second positioning hole, and the first positioning hole and the second positioning hole are fixed by an inserted pin; a slot is provided on the free end of the rod portion of the pin, an elastic pin is inserted in the slot, one end of the elastic pin is fixed on the outer side wall of the limiting sleeve, and the annular portion of the pin is connected in series and locked with one of the first matching holes by a locking wire.

[0014] As a preferred solution of an oil drain valve for an unmanned aerial vehicle of the present invention, a first connecting column is provided with a rotating handle at one end extending to the outside of an outer casing, a locking bolt is spirally sleeved on the rotating handle on one side of the first connecting column, and one end of the locking bolt is inserted into a recessed hole on the outside of the outer casing.

[0015] As a preferred solution of an oil release valve for an unmanned aerial vehicle of the present invention, the first connecting column is extended to the end outside the outer casing and is fixedly provided with an epitaxial column, and the connector of the first connecting column, the epitaxial column and the first rectangular rod is provided with a receiving groove with an opening at one end of the epitaxial column for sliding and inserting the rotating rod along the axial direction, a groove connected to the receiving groove is provided on the side wall of the epitaxial column, a rotating column is fixedly provided in the receiving groove at the position of the epitaxial column along the radial direction, a sliding groove is provided on the side wall of the rotating rod along the axial direction, and the rotating column is gap-fitted in the sliding groove; a second external thread for spirally sleeved sealing cover is provided on the outer side wall of the epitaxial column.

[0016] As a preferred solution of the oil release valve of a UAV of the present invention, wherein: on the same horizontal plane, the positioning plate is a plate body that partially covers the inner area of ​​the outer casing, and one side of the positioning plate is in contact with the inner wall of the outer casing.

[0017] In view of the fact that the existing oil drain valve has a short service life and the fuel is easy to cause damage to the internal structure, the oil drain valve of an unmanned aerial vehicle of the present invention is further optimized and improved, wherein: the horizontal cross-section of the positioning plate is disc-shaped, and the side wall of the positioning plate is in contact with the inner wall of the outer casing, and a plurality of convex grooves are provided on the end face of the positioning plate in a circumferential array, and a blocking block is provided in the gap at the lower end of the convex groove, and an internal threaded hole is provided on the top surface of the blocking block, which is spirally sleeved with a second threaded column fixed to the lower end of the linkage column, and the upper end of the linkage column is fixedly connected to the bottom surface of the sealing disk outside the limit groove.

[0018] Another beneficial effect of the present invention is that when the oil drain valve is in use, when the sealing disk drives the movable column to move downward, the linkage column will also synchronously drive the blocking block to move downward, so that the blocking block is disengaged from the convex groove, and the fuel flows from the convex groove to realize the oil drain operation. When the cam is disengaged from the top plate, under the action of the reset spring, the sealing disk synchronously drives the blocking block to move upward, and the blocking block fits in the convex groove to achieve the blocking effect. In this way, the positioning plate can isolate the sealing disk and the fuel, which plays a certain protective role on the oil drain mechanism itself, thereby increasing the service life of the device and having good practicality.

[0019] In addition, the present invention also provides the following technical solution: a production process of a UAV oil drain valve, wherein the UAV oil drain valve is produced according to the following steps;

[0020] S1: forming the components of the outer casing and the oil discharge mechanism by at least one of casting, forging, turning, milling, planing, grinding, hot pressing and stamping;

[0021] S2: performing surface treatment on each produced component by at least one of grinding, polishing and paint spraying;

[0022] S3: After the surface treatment, the top plate is first screwed onto the top surface of the sealing plate, and then the return spring and the positioning plate are sequentially sleeved onto the movable column to form a matching part;

[0023] S4: Put the fitting into the outer casing from the lower end of the outer casing, and after ensuring that the sixth sealing ring is in contact with the bottom of the retaining ring, screw the positioning sleeve into the outer casing to achieve the fitting and fixing between the fitting and the outer casing;

[0024] S5: insert the connector of the first rectangular rod and the second rectangular rod into the limiting sleeve on one side of the outer casing. When the second connecting column is located inside the outer casing, the staff inserts the rectangular frame block from the upper port of the outer casing and fixes the rectangular frame block on the second rectangular rod, and then continues to insert the second connecting column into the limiting sleeve on the other side of the outer casing.

[0025] S6: inserting the latch into the first matching hole and the second matching hole, and engaging the elastic bayonet into the slot, so as to achieve preliminary matching and fixing of the rotating assembly with the outer casing;

[0026] S7: Screw the cylinder cover on the upper end of the outer casing to achieve the matching and fixing between the cylinder cover and the outer casing;

[0027] S8: The first matching hole and the second matching hole are connected in series through a locking wire to achieve locking between the outer casing and the casing cover, and the annular portion of the plug and the first matching hole are connected in series through a locking wire to achieve locking between the plug and the outer casing. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for describing the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative labor. Among them:

[0029] Figure 1 The figure is a schematic diagram of the overall structure of an oil drain valve of a UAV in Example 1 of the present invention.

[0030] Figure 2 For the present invention Figure 1 Bottom view of the structure.

[0031] Figure 3 For the present invention Figure 1 Vertical cross-sectional view of the structure in the axial direction of the first connecting column.

[0032] Figure 4 For the present invention Figure 1 A vertical cross-sectional view of the structure in the radial direction of the first connecting column.

[0033] Figure 5 For the present invention Figure 1 Exploded view of the structure.

[0034] Figure 6 For the present invention Figure 5 Bottom view of the structure.

[0035] Figure 7 This is a diagram of the top plate, movable column and positioning plate to be matched in Example 1 of the present invention.

[0036] Figure 8 This is an exploded view of the rotating assembly in Example 1 of the present invention.

[0037] Fig. 9 This is a schematic diagram of the overall structure of an oil drain valve for a UAV in Example 2 of the present invention.

[0038] Fig.10 It is an exploded view of the rotating assembly in Example 2 of the present invention.

[0039] Fig.11 This is a vertical cross-sectional view of an oil drain valve of a UAV in Example 3 of the present invention in the direction of the axis of the first connecting column.

[0040] Fig.12 This is a diagram of the top plate, movable column and positioning plate to be matched in Example 3 of the present invention. DETAILED DESCRIPTION

[0041] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below in conjunction with the accompanying drawings.

[0042] In the following description, many specific details are set forth to facilitate a full understanding of the present invention, but the present invention may also be implemented in other ways different from those described herein, and those skilled in the art may make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0043] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The term "in one embodiment" that appears in different places in this specification does not necessarily refer to the same embodiment, nor does it refer to a separate or selective embodiment that is mutually exclusive with other embodiments.

[0044] Secondly, the present invention is described in detail with reference to the schematic diagram. When describing the embodiments of the present invention in detail, for the sake of convenience, the cross-sectional diagrams showing the device structure will not be partially enlarged according to the general scale, and the schematic diagrams are only examples, which should not limit the scope of protection of the present invention. In addition, in actual production, the three-dimensional dimensions of length, width and depth should be included. Example 1

[0045] Reference Figure 1 , Figure 2 , Figure 3 and Figure 4 , which is the first embodiment of the present invention, and this embodiment provides a UAV oil drain valve, which is integrally installed on the bottom surface of the fuel tank when in use. When draining oil through the oil drain mechanism 200, the fuel enters from the lower end of the outer casing 100 and is discharged from the upper end of the outer casing 100 through transportation.

[0046] Specifically, it includes an outer casing 100, including an outer casing 101 with openings at both ends and a casing cover 102 coaxially arranged above the outer casing 101; and an oil discharge mechanism 200, including a rotating assembly 201, a top plate 202, a movable column 203, a positioning plate 204 and a positioning sleeve 205 arranged in sequence from top to bottom, and the top plate 202, the movable column 203, the positioning sleeve 205 and the outer casing 101 are coaxially arranged;

[0047] A connecting tube 102b is coaxially fixed on the bottom surface of the cylinder cover 102, and a second internal thread 101h is provided on the inner wall of the upper end of the outer casing 101 to be spirally matched with the first external thread 102b-1 on the outer wall of the connecting tube 102b. This arrangement facilitates the detachable connection between the outer casing 101 and the cylinder cover 102, thereby enabling the staff to discharge the fuel by opening the cylinder cover 102. A third sealing groove 102c is provided on the bottom surface of the cylinder cover 102 outside the connecting tube 102b along the circumferential direction, and a third sealing ring 102c-1 is provided in the third sealing groove 102c, thereby improving the sealing performance of the matching between the cylinder cover 102 and the outer casing 101;

[0048] A second connecting plate 101c is fixedly provided on the outer side wall of the lower end of the outer casing 101, and second mounting holes 101c-1 are provided at four corners of the second connecting plate 101c. The second mounting holes 101c-1 are provided to facilitate the outer casing 101 to be installed on the bottom surface of the oil tank, and the oil drain cover of the oil tank is closed inside the outer casing 101. A first sealing groove 101d is provided on the bottom surface of the outer casing 101 along the circumferential direction, and a first sealing ring 101d-1 is provided in the first sealing groove 101d. This arrangement can improve the sealing performance between the outer casing 101 and the oil tank.

[0049] A first connecting plate 101b is fixedly provided on the outer wall of the outer casing 101 below the limiting sleeve 101a. A plurality of first mounting holes 101b-1 are opened on the first connecting plate 101b. The connection and cooperation between the first mounting holes 101b-1 and the UAV can further improve the stability of the cooperation between the device and the UAV.

[0050] Furthermore, a hexagonal block 102a is fixedly provided in the middle of the top surface of the cylinder cover 102, and a second matching hole 102a-1 penetrating two adjacent side surfaces is opened on the hexagonal block 102a; a plurality of first matching holes 101b-2 are opened on the first connecting plate 101b, and one of the first matching holes 101b-2 and the second matching hole 102a-1 are locked in series by a locking wire. This arrangement can improve the firmness of the fit between the cylinder cover 102 and the outer casing 101, and the arrangement of the hexagonal block 102a itself makes it convenient for the staff to remove the cylinder cover 102 by tools.

[0051] See Figure 4 , Figure 5 , Figure 6 and Figure 7 As shown, a limiting groove 203a-1 is circumferentially provided on the bottom surface of the sealing disk 203a outside the movable column 203, the lower end of the movable column 203 is slidably sleeved on the positioning plate 204, and a plug sleeve 204a is fixedly provided on the top surface of the positioning plate 204 outside the movable column 203. A return spring 203b is slidably sleeved on the outer side of the movable column 203, and the two ends of the return spring 203b are respectively abutted on the limiting groove 203a-1 and the positioning plate 204 to limit the two ends of the return spring 203b. A first threaded column 202b is fixedly provided in the middle of the bottom surface of the top plate 202 A slot 203c extending into the movable column 203 is provided in the middle of the top surface of the sealing disk 203a, and a third internal thread 203c-1 spirally matched with the first threaded column 202b is provided on the upper end of the slot 203c. This arrangement can realize a detachable connection between the top disk 202 and the sealing disk 203a; a fifth sealing groove 202a is provided along the circumferential direction on the bottom surface of the top disk 202, and a fifth sealing ring 202a-1 is provided in the fifth sealing groove 202a. This arrangement can realize the sealing performance of the top disk 202 and the sealing disk 203a;

[0052] When the above arrangement is in use, when the top plate 202 is squeezed downward, the connecting body between the top plate 202 and the movable column 203 will move downward relative to the positioning plate 204. After the squeezing force on the top plate 202 is lost, the connecting body between the top plate 202 and the movable column 203 will be reset under the reset action of the reset spring 203b.

[0053] See Figure 3As shown, a second inner extension ring 101f is fixedly provided along the circumferential direction at the middle part of the inner wall of the outer casing 101, and a butt ring 101f-1 is extended downwardly from the inner side of the second inner extension ring 101f, a sealing disk 203a is fixedly connected to the top of the movable column 203, a sixth sealing groove 203a-2 is opened on the top surface of the sealing disk 203a along the circumferential direction, and a sixth sealing ring 203a-3 for abutting the lower end of the butt ring 101f-1 is provided in the sixth sealing groove 203a-2, and when the connector between the top plate 202 and the movable column 203 is reset under the reset action of the reset spring 203b, the butt ring 101f-1 and the sixth sealing ring 203a-3 are in abutment state, so that the sealing performance of the butt ring 101f-1 and the sealing disk 203a can be achieved.

[0054] See Figure 3 and Figure 5 As shown, a first inner extension ring 101e is fixedly provided at the lower end of the inner wall of the outer casing 101 along the circumferential direction, and the upper and lower surfaces of the positioning plate 204 respectively abut against the first inner extension ring 101e and one side of the positioning sleeve 205. A first internal thread 101g is also provided on the inner wall of the outer casing 101 for spirally engaging with the third external thread 205a on the outer wall of the positioning sleeve 205. When the positioning sleeve 205 is spirally engaged and moves upward, the positioning plate 204 will be clamped between the first inner extension ring 101e and the positioning sleeve 205, thereby realizing the limited fixation of the positioning plate 204.

[0055] See Figure 3 , Figure 4 and Figure 8 As shown, two coaxial limiting sleeves 101a are fixedly arranged on the side wall of the outer casing 101 above the second inner extension ring 101f, and the rotating assembly 201 includes a first rectangular rod 201a, a second rectangular rod 201b and a rectangular frame block 201d. The ends of the first rectangular rod 201a and the second rectangular rod 201b are fixedly connected, and the other end of the first rectangular rod 201a is fixedly provided with a first connecting column 201a-1, and the other end of the second rectangular rod 201b is fixedly provided with a second connecting column 201b-1. The first connecting column 201a-1 and the second connecting column 201b-1 are respectively slidably sleeved in the two limiting sleeves 101a, and the second rectangular rod 201b-1 is respectively slidably sleeved in the two limiting sleeves 101a. A rectangular frame block 201d is slidably sleeved on one end of the rod 201b close to the first rectangular rod 201a, and the rectangular frame block 201d is fixed with the second rectangular rod 201b by fixing bolts. A cam 201d-1 is fixed on one side of the rectangular frame block 201d. When the staff rotates the first connecting column 201a-1 to drive the second rectangular rod 201b to rotate, and then the cam 201d-1 rotates with the axis of the first connecting column 201a-1, the cam 201d-1 will provide a downward squeezing force to the top plate 202, so that the top plate 202 can drive the movable column 203 to move downward;

[0056] A fourth sealing groove 201a-2 is circumferentially opened on the outer wall of the first connecting column 201a-1, and a fourth sealing ring is arranged in the fourth sealing groove 201a-2, which can achieve the sealing between the first connecting column 201a-1 and the limiting sleeve 101a; a second sealing groove 101a-1 is circumferentially opened on the inner wall of the limiting sleeve 101a at the position of the second connecting column 201b-1, and a second sealing ring 101a-2 is arranged in the second sealing groove 101a-1, which can achieve the sealing between the second connecting column 201b-1 and the limiting sleeve 101a.

[0057] For further details, see Figure 5 and Figure 8 As shown, a second positioning hole 201b-2 is formed on the side wall of one end of the second connecting column 201b-1, and a first positioning hole 101a-3 is formed on the side wall of the limiting sleeve 101a located outside the outer casing 101 coaxially with the second positioning hole 201b-2, and the first positioning hole 101a-3 and the second positioning hole 201b-2 are fixed by an inserted latch 101a-5. This arrangement can realize the connection between the second connecting column 201b-1 and the limiting sleeve 101a The two ends of the two connecting rods 101a-5 are fixedly matched, thereby preventing the second connecting rod 201b-1 from rotating when the oil is not discharged; a slot 101a-6 is provided on the free end of the rod of the latch 101a-5, and an elastic latch 101a-4 is inserted into the slot 101a-6, and one end of the elastic latch 101a-4 is fixedly arranged on the outer wall of the limiting sleeve 101a, and this arrangement can further limit the latch 101a-5 to prevent the latch 101a-5 from rotating;

[0058] The annular portion of the latch pin 101a-5 is connected in series with one of the first matching holes 101b-2 through a locking wire, and this arrangement can achieve a more secure fit between the latch pin 101a-5 and the outer casing 101;

[0059] A rotating handle 201c is fixedly provided at one end of the first connecting column 201a-1 extending to the outside of the outer casing 101. The setting of the rotating handle 201c can facilitate the staff to rotate the first connecting column 201a-1. A locking bolt 201c-1 is spirally sleeved on the rotating handle 201c on one side of the first connecting column 201a-1, and one end of the locking bolt 201c-1 is inserted into the recessed hole on the outside of the outer casing 101. This setting can limit the rotating handle 201c.

[0060] For further details, see Figure 2 , Figure 3 , Figure 4 and Figure 7 As shown, on the same horizontal plane, the positioning plate 204 is a plate body that partially covers the inner area of ​​the outer casing 101 , and one side of the positioning plate 204 is in contact with the inner wall of the outer casing 101 .

[0061] In addition, it should be noted that the sealing rings used for sealing in this device are designed according to HB4-57 and HB7520-97, and the materials used are nitrile rubber and polytetrafluoroethylene. Both can work for a long time at a temperature of -55℃ to +90℃. Austenitic stainless steel is used for parts that are often worn, and aluminum alloy is required in other positions. Aluminum alloy materials meet the strength requirements while also reducing weight. Example 2

[0062] Reference Fig. 9 and Fig.10 , which is the second embodiment of the present invention, is based on the previous embodiment, except that the structure for driving the first connecting column 201a-1 to rotate is deformed to facilitate the staff to better implement the device, so this embodiment is proposed.

[0063] Specifically, the first connecting column 201a-1 extends to one end of the outer casing 101 and is fixed with an epitaxial column 201e. The connecting body of the first connecting column 201a-1, the epitaxial column 201e and the first rectangular rod 201a is provided with a receiving groove 201e-3 for slidingly inserting the rotating rod 201e-6, and the side wall of the epitaxial column 201e is provided with a The groove 201e-4 and the receiving groove 201e-3 at the position of the epitaxial column 201e are fixedly provided with a rotating column 201e-5 along the radial direction, and a sliding groove 201e-7 is provided on the side wall of the rotating rod 201e-6 along the axial direction, and the rotating column 201e-5 is fitted with a gap in the sliding groove 201e-7; a second external thread 201e-2 for spirally sleeved sealing cover 201e-1 is provided on the outer side wall of the epitaxial column 201e;

[0064] When the above-mentioned arrangement is in use, one end of the rotating rod 201e-6 extends from the groove 201e-4. At this time, the staff can realize the rotation of the first connecting column 201a-1 by pulling the rotating rod 201e-6. In the daily non-oil-draining state, the staff can rotate the rotating rod 201e-6 to make the rotating rod 201e-6 rotate around the rotating column 201e-5. Under the action of rotation and the sliding groove 201e-7 sliding on the rotating column 201e-5, the entire rotating rod 201e-6 can be inserted into the storage groove 201e-3, and then the sealing cover 201e-1 is spirally engaged on the extension column 201e, so as to realize the storage of the rotating rod 201e-6, thereby improving the overall convenience of the device and facilitating the use of the drone. Example 3

[0065] Reference Fig.11 and Fig.12, which is the third embodiment of the present invention, is based on any of the above embodiments, except that the shape of the positioning plate 204 is deformed. Such deformation can protect the oil drain mechanism 200 itself, preventing the oil drain mechanism 200 from being immersed in fuel for a long time, causing damage, thereby reducing the service life of the device.

[0066] Specifically, the horizontal cross-section of the positioning plate 204 is disc-shaped, and the side wall of the positioning plate 204 is in contact with the inner wall of the outer casing 101. A plurality of convex grooves 204c are provided on the end surface of the positioning plate 204 along a circumferential array, and a blocking block 204b is provided in the gap at the lower end of the convex groove 204c. An internal threaded hole 204b-1 is provided on the top surface of the blocking block 204b, which is spirally sleeved with a second threaded column 203a-5 fixed at the lower end of the linkage column 203a-4. The upper end of the linkage column 203a-4 is fixedly connected to the bottom surface of the sealing disk 203a outside the limiting groove 203a-1. This arrangement can realize a detachable connection between the blocking block 204b and the linkage column 203a-4.

[0067] When the above arrangement is in use, when the sealing disk 203a moves downward, the linkage column 203a-4 will drive the blocking block 204b to move downward synchronously, so that the blocking block 204b can be separated from the convex groove 204c, and the fuel will enter from the convex groove 204c to achieve oil discharge, and when the sealing disk 203a moves upward, the blocking block 204b is matched in the convex groove 204c to play a partition role, thereby preventing the fuel from entering the upper end of the outer casing 101 and soaking the structure in the non-oil discharge state (in actual use, because the lower end of the outer casing 101 is installed on the bottom surface of the fuel tank, the whole device is in an inverted state. When the partition is performed, the fuel above the positioning plate 204 can be discharged due to the action of gravity, so there is no problem of residual fuel). Example 4

[0068] This embodiment is the fourth embodiment of the present invention, and this embodiment provides a production process of a UAV oil release valve. Specifically, the production is carried out according to the following steps:

[0069] S1: forming the components of the outer casing 100 and the oil discharge mechanism 200 by at least one of casting, forging, turning, milling, planing, grinding, hot pressing and stamping;

[0070] S2: performing surface treatment on each produced component by at least one of grinding, polishing and coating;

[0071] S3: After the surface treatment, the top plate 202 is first screwed onto the top surface of the sealing plate 203a, and then the return spring 203b and the positioning plate 204 are sequentially sleeved onto the movable column 203 to form a matching piece;

[0072] S4: Put the fitting into the outer casing 101 from the lower end of the outer casing 101, and after ensuring that the sixth sealing ring 203a-3 is in contact with the bottom of the annular ring 101f-1, screw the positioning sleeve 205 into the outer casing 101 to achieve the fitting and fixing between the fitting and the outer casing 101;

[0073] S5: insert the connecting body of the first rectangular rod 201a and the second rectangular rod 201b into the limiting sleeve 101a on one side of the outer casing 101. When the second connecting column 201b-1 is located inside the outer casing 101, the staff inserts the rectangular frame block 201d from the upper port of the outer casing 101 and fixes the rectangular frame block 201d on the second rectangular rod 201b, and then continues to insert the second connecting column 201b-1 into the limiting sleeve 101a on the other side of the outer casing 101.

[0074] S6: Insert the latch pin 101a-5 into the first matching hole 101b-2 and the second matching hole 102a-1, and engage the elastic latch pin 101a-4 into the slot 101a-6, so as to achieve preliminary matching and fixing of the rotating assembly 201 with the outer casing 101;

[0075] S7: Screw the cylinder cover 102 onto the upper end of the outer casing 101 to achieve the fit and fixation between the cylinder cover 102 and the outer casing 101;

[0076] S8: Connect the first matching hole 101b-2 and the second matching hole 102a-1 in series via a locking wire to achieve locking between the outer casing 101 and the tube cover 102; connect the annular portion of the latch 101a-5 and the first matching hole 101b-2 in series via a locking wire to achieve locking between the latch 101a-5 and the outer casing 101.

[0077] In addition, it should be noted that the components not described in detail in this article are prior art.

[0078] Importantly, it should be noted that the construction and arrangement of the present application shown in a plurality of different exemplary embodiments are only exemplary. Although only a few embodiments are described in detail in this disclosure, it should be readily understood by those who refer to this disclosure that many modifications are possible (e.g., the size, scale, structure, shape and ratio of various elements, and parameter values ​​(e.g., temperature, pressure, etc.), installation arrangements, use of materials, color, directional changes, etc.) without substantially departing from the novel teachings and advantages of the subject matter described in the application. For example, the element shown as integrally formed can be composed of a plurality of parts or elements, the position of the element can be inverted or otherwise changed, and the nature or number or position of the discrete element can be changed or changed. Without departing from the scope of the present invention, other replacements, modifications, changes and omissions can be made in the design, operating conditions and arrangement of the exemplary embodiments. Therefore, the present invention is not limited to a specific embodiment, but extends to a variety of modifications that still fall within the scope of the appended claims.

[0079] Additionally, in order to provide a concise description of exemplary embodiments, all features of an actual embodiment may not be described (ie, those features that are not relevant to the best mode presently contemplated for carrying out the invention or those features that are not relevant to implementing the invention).

[0080] It will be appreciated that in the development of any actual implementation, as in any engineering or design project, numerous implementation-specific decisions may be made. Such a development effort may be complex and time-consuming, but will be a routine task of design, fabrication, and production for those of ordinary skill having the benefit of this disclosure without undue experimentation.

[0081] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solutions of the present invention may be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the present invention, which should all be included in the scope of the claims of the present invention.

Claims

1. An unmanned aerial vehicle oil drain valve, characterized in that: include, An outer protective shell (100) comprises an outer protective tube (101) with openings at both ends and a tube cover (102) coaxially arranged above the outer protective tube (101); a first inner extension ring (101e) is fixedly arranged at the lower end of the inner wall of the outer protective tube (101) along the circumferential direction; a second inner extension ring (101f) is fixedly arranged at the middle of the inner wall of the outer protective tube (101) along the circumferential direction; a stop ring (101f-1) is extended downwardly from the inner side of the second inner extension ring (101f); and two coaxial limiting sleeves (101a) are fixedly arranged on the side wall of the outer protective tube (101) above the second inner extension ring (101f); and, The oil discharge mechanism (200) comprises a rotating assembly (201), a top plate (202), a movable column (203), a positioning plate (204) and a positioning sleeve (205) which are arranged in sequence from top to bottom. The top plate (202), the movable column (203), the positioning sleeve (205) and the outer casing (101) are arranged coaxially. The top of the movable column (203) is fixedly connected to a sealing plate (203a). A sixth sealing groove (203a-2) is provided on the top surface of the sealing plate (203a) along the circumferential direction. A sixth sealing ring (203a-3) for abutting against the lower end of the abutment ring (101f-1) is provided in the sixth sealing groove (203a-2). A limiting groove (203a-1) is provided on the bottom surface of the sealing disk (203a) outside the movable column (203) along the circumferential direction; the lower end of the movable column (203) is slidably sleeved on the positioning plate (204); a return spring (203b) is slidably sleeved on the outer side of the movable column (203); and the two ends of the return spring (203b) are respectively abutted on the limiting groove (203a-1) and the positioning plate (204); the upper and lower surfaces of the positioning plate (204) are respectively abutted on the first inner extension ring (101e) and one side of the positioning sleeve (205); and a third external thread (201e) for contacting with the outer wall of the positioning sleeve (205) is also provided on the inner wall of the outer casing (101). 5a) a first internal thread (101g) that is spirally matched, a first threaded column (202b) is fixedly provided in the middle of the bottom surface of the top plate (202), a slot (203c) that extends into the movable column (203) is provided in the middle of the top surface of the sealing plate (203a), and a third internal thread (203c-1) that is spirally matched with the first threaded column (202b) is provided on the upper end of the slot (203c); the rotating assembly (201) comprises a first rectangular rod (201a), a second rectangular rod (201b) and a rectangular frame block (201d), the first rectangular rod (201a) and the second rectangular rod (201b) are fixedly connected at their ends, and the first A first connecting column (201a-1) is fixedly provided at the other end of the rectangular rod (201a), and a second connecting column (201b-1) is fixedly provided at the other end of the second rectangular rod (201b); the first connecting column (201a-1) and the second connecting column (201b-1) are respectively slidably sleeved in two limit sleeves (101a); a rectangular frame block (201d) is slidably sleeved at one end of the second rectangular rod (201b) close to the first rectangular rod (201a); the rectangular frame block (201d) is fixedly provided with the second rectangular rod (201b) by means of fixing bolts; a cam (201d-1) is fixedly provided on one side surface of the rectangular frame block (201d); A connecting tube (102b) is coaxially fixedly disposed on the bottom surface of the tube cover (102); a second internal thread (101h) is provided on the inner wall of the upper end of the outer protective tube (101) and is screw-matched with a first external thread (102b-1) on the outer wall of the connecting tube (102b); a hexagonal block (102a) is fixedly disposed in the middle of the top surface of the tube cover (102); and a second matching hole (102a-1) is provided on the hexagonal block (102a) and passes through two adjacent side surfaces; A first connecting plate (101b) is fixedly provided on the outer side wall of the outer protective tube (101) below the limiting sleeve (101a), and a plurality of first mounting holes (101b-1) and first matching holes (101b-2) are respectively provided on the first connecting plate (101b), and one of the first matching holes (101b-2) and the second matching hole (102a-1) are connected in series and locked by a locking wire; A second connecting plate (101c) is fixedly provided on the outer side wall of the lower end of the outer casing (101), and second mounting holes (101c-1) are provided at four corner positions of the second connecting plate (101c); A first sealing groove (101d) is provided on the bottom surface of the outer casing (101) along the circumferential direction, and a first sealing ring (101d-1) is provided in the first sealing groove (101d); A fifth sealing groove (202a) is provided on the bottom surface of the top plate (202) along the circumferential direction, and a fifth sealing ring (202a-1) is provided in the fifth sealing groove (202a); A third sealing groove (102c) is provided on the bottom surface of the cylinder cover (102) outside the connecting cylinder (102b) along the circumferential direction, and a third sealing ring (102c-1) is provided in the third sealing groove (102c); A fourth sealing groove (201a-2) is provided on the outer side wall of the first connecting column (201a-1) along the circumferential direction, and a fourth sealing ring is provided in the fourth sealing groove (201a-2); A second sealing groove (101a-1) is provided on the inner wall of the limiting sleeve (101a) at the position of the second connecting column (201b-1) along the circumferential direction, and a second sealing ring (101a-2) is provided in the second sealing groove (101a-1); A plug sleeve (204a) is fixedly provided on the top surface of the positioning plate (204) outside the movable column (203).

2. The UAV oil drain valve according to claim 1, characterized in that: A second positioning hole (201b-2) is provided on a side wall at one end of the second connecting column (201b-1), a first positioning hole (101a-3) is provided on a side wall of a limiting sleeve (101a) located outside the outer casing (101) coaxially with the second positioning hole (201b-2), and the first positioning hole (101a-3) and the second positioning hole (201b-2) are fixed by means of an engaged latch (101a-5); A slot (101a-6) is provided on the free end of the rod of the latch pin (101a-5), an elastic latch pin (101a-4) is inserted into the slot (101a-6), and one end of the elastic latch pin (101a-4) is fixedly arranged on the outer side wall of the limiting sleeve (101a), and the annular portion of the latch pin (101a-5) is connected in series and locked with one of the first matching holes (101b-2) via a locking wire.

3. The UAV oil drain valve as claimed in claim 2, characterized in that: A rotating handle (201c) is fixedly provided at one end of the first connecting column (201a-1) extending to the outside of the outer casing (101), a locking bolt (201c-1) is spirally sleeved on the rotating handle (201c) on one side of the first connecting column (201a-1), and one end of the locking bolt (201c-1) is inserted into a concave hole on the outside of the outer casing (101).

4. The UAV oil drain valve as claimed in claim 2, characterized in that: An end of the first connecting column (201a-1) extending to the outside of the outer casing (101) is fixedly provided with an epitaxial column (201e); a connecting body of the first connecting column (201a-1), the epitaxial column (201e) and the first rectangular rod (201a) is provided with a receiving groove (201e-3) for slidingly inserting a rotating rod (201e-6) and having an opening at one end of the epitaxial column (201e); a groove (201e-4) communicating with the receiving groove (201e-3) is provided on a side wall of the epitaxial column (201e); a rotating column (201e-5) is fixedly provided in the receiving groove (201e-3) at the position of the epitaxial column (201e) along a radial direction; a sliding groove (201e-7) is provided on the side wall of the rotating rod (201e-6) along an axial direction, and the rotating column (201e-5) is gap-fitted in the sliding groove (201e-7); The outer side wall of the epitaxial column (201e) is provided with a second external thread (201e-2) for spirally sleeved engagement of the sealing cover (201e-1).

5. The UAV oil drain valve as claimed in claim 3 or 4, characterized in that: On the same horizontal plane, the positioning plate (204) is a plate body that partially covers the inner area of ​​the outer casing (101), and one side surface of the positioning plate (204) is in contact with the inner wall of the outer casing (101).

6. The UAV oil drain valve as claimed in claim 3 or 4, characterized in that: The horizontal cross-section of the positioning plate (204) is disc-shaped, and the side wall of the positioning plate (204) is fitted with the inner wall of the outer casing (101); a plurality of convex grooves (204c) are arranged in a circumferential array on the end surface of the positioning plate (204); a blocking block (204b) is provided in a gap at the lower end of the convex groove (204c); an internal threaded hole (204b-1) is provided on the top surface of the blocking block (204b) and is spirally sleeved with a second threaded column (203a-5) fixed to the lower end of the linkage column (203a-4); and the upper end of the linkage column (203a-4) is fixedly connected to the bottom surface of the sealing disk (203a) outside the limiting groove (203a-1).

7. A production process for an unmanned aerial vehicle oil drain valve, characterized in that: The UAV oil drain valve according to any one of claims 3 to 6 is produced according to the following steps; S1: forming the components of the outer casing (100) and the oil discharge mechanism (200) by at least one of casting, forging, turning, milling, planing, grinding, hot pressing and stamping; S2: performing surface treatment on each produced component by at least one of grinding, polishing and paint spraying; S3: After the surface treatment, the top plate (202) is first screwed onto the top surface of the sealing plate (203a), and then the return spring (203b) and the positioning plate (204) are sequentially sleeved onto the movable column (203) to form a matching part; S4: inserting the fitting into the outer casing (101) from the lower end of the outer casing (101), and after ensuring that the sixth sealing ring (203a-3) is in contact with the bottom of the retaining ring (101f-1), screwing the positioning sleeve (205) into the outer casing (101) to achieve the fitting and fixing between the fitting and the outer casing (101); S5: inserting the connecting body of the first rectangular rod (201a) and the second rectangular rod (201b) into the limiting sleeve (101a) on one side of the outer casing (101), and when the second connecting column (201b-1) is located inside the outer casing (101), the staff inserts the rectangular frame block (201d) from the upper port of the outer casing (101) and fixes the rectangular frame block (201d) on the second rectangular rod (201b), and then continues to insert the second connecting column (201b-1) into the limiting sleeve (101a) on the other side of the outer casing (101); S6: inserting the latch pin (101a-5) into the first matching hole (101b-2) and the second matching hole (102a-1), and engaging the elastic latch pin (101a-4) into the latch groove (101a-6), thereby achieving preliminary matching and fixing of the rotating assembly (201) with the outer casing (101); S7: Screw the tube cover (102) onto the upper end of the outer casing (101) to achieve a fixed fit between the tube cover (102) and the outer casing (101); S8: The first matching hole (101b-2) and the second matching hole (102a-1) are connected in series via a locking wire to achieve locking between the outer casing (101) and the casing cover (102); the annular portion of the latch pin (101a-5) and the first matching hole (101b-2) are connected in series via a locking wire to achieve locking between the latch pin (101a-5) and the outer casing (101).

Images