Aircraft nozzle system and aircraft

Abstract

The utility model relates to an aircraft nozzle system and an aircraft, relates to the technical field of aircrafts, and aims to solve the problem that a nozzle of an aircraft is difficult to adjust in the prior art. The aircraft spray pipe system comprises a spray pipe, a pull rod, an upper connecting piece, a front connecting assembly and a rear connecting unit. One end of the pull rod is connected with the spray pipe through the front connecting assembly, the other end of the pull rod is connected with the upper connecting piece, the spray pipe is connected with the rear connecting unit, and the front connecting assembly and the rear connecting unit are used for supporting and adjusting the spray pipe. The direction and the pitching angle of the spray pipe can be controlled, the spray pipe is prevented from rolling, the structure is stable, and operation is easy and convenient.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to an aircraft nozzle system and an aircraft. Background Technology

[0002] With the development of drone and other aircraft technologies, aircraft are being used more and more widely in fields such as urban fire fighting and material transportation.

[0003] Taking the application of aircraft in urban fire fighting as an example, when using aircraft to spray water for fire extinguishing, in order to reduce the impact of downwash airflow on water flow, the water spray pipe needs to extend out of the rotor downwash airflow influence area. When the water spray pipe is connected to different aircraft, installation errors will cause the water spray pipe to deviate to varying degrees. Since the distance of the water spray pipe is relatively long, if the water spray pipe is not adjusted, the sprayed liquid will have a large deviation. Utility Model Content

[0004] Based on the above analysis, the present invention aims to provide an aircraft nozzle system and an aircraft to solve the problem of difficulty in adjusting the nozzle of an aircraft in the prior art.

[0005] The objective of this utility model is mainly achieved through the following technical solutions:

[0006] On the one hand, this utility model provides an aircraft nozzle system, including a nozzle, a pull rod, an upper connector, a front connection assembly, and a rear connection unit;

[0007] One end of the pull rod is connected to the nozzle via the front connecting assembly, and the other end is connected to the upper connecting member. The nozzle is connected to the rear connecting unit. The front connecting assembly and the rear connecting unit cooperate to support and adjust the position of the nozzle.

[0008] Furthermore, the front connection assembly includes a first front connector, which includes a semi-ring and a shaft. The shaft is disposed on the semi-ring, and the two semi-rings are connected to form a ring structure that is connected to the nozzle.

[0009] Furthermore, the front connection assembly also includes a second front connector and a push bolt; the first front connector further includes a top plate; the second front connector includes a ring sleeve.

[0010] The jacking bolt passes through the ring and contacts the top plate, and is used to push the top plate to move.

[0011] Furthermore, the second front connector also includes a locking tongue that inserts into the gap between the two semi-rings to prevent the nozzle from rotating.

[0012] Furthermore, a pin is provided on the nozzle, and the pin is used to connect the rear connection unit;

[0013] The rear connection unit includes a mounting plate, a lower adjusting block, and an upper adjusting block. The lower adjusting block is connected to the mounting plate, and the upper adjusting block is disposed on both sides of the nozzle. The upper adjusting block and the lower adjusting block are connected to form a pin hole, and the pin is disposed in the pin hole.

[0014] Furthermore, the rear connection unit also includes an adjustment component and a pin component. The lower adjustment block is connected to the mounting plate via the pin component, and the adjustment component is connected to the mounting plate to adjust the position of the lower adjustment block.

[0015] Furthermore, the mounting plate is provided with a movable groove, a counter-protrusion, and a positioning hole. There are two counter-protrusions, and the movable groove is disposed between the counter-protrusions. The pin assembly includes a movable pin and a fixed pin.

[0016] The movable pin is threadedly connected to the lower adjusting block and passes through the lower adjusting block into the movable groove; the fixed pin is connected to the lower adjusting block and passes through the lower adjusting block into the positioning hole.

[0017] Furthermore, the adjustment assembly includes a first push bolt and a second push bolt, the first push bolt and the second push bolt being respectively connected to the push bosses on both sides of the moving groove;

[0018] The first push bolt and the second push bolt are used to push the movable pin to move along the movable groove.

[0019] Furthermore, a rod end bearing is provided on the pull rod, the rod end bearing is connected to the pull rod and can move along the pull rod, and the shaft is connected to the rod end bearing.

[0020] On the other hand, the present invention also provides an aircraft, including a frame and the aforementioned aircraft nozzle system, wherein the upper connector and the rear connector are connected to the frame.

[0021] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0022] (1) The aircraft nozzle system of this utility model supports and adjusts the nozzle through the front connecting component and the rear connecting unit, thereby controlling the direction and pitch angle of the nozzle, making the spray direction of the nozzle more accurate, improving the adaptability and accuracy of the nozzle to different aircraft models, and meeting diverse usage needs.

[0023] (2) The aircraft nozzle system of this utility model can fix the tumbling of the nozzle by inserting the locking tongue into the gap between the two half rings, thereby preventing the nozzle from rotating and improving the stability of the structure.

[0024] (3) The aircraft of this utility model improves the stability and adaptability of the connection between the nozzle and the frame by adopting the aircraft nozzle system. By adjusting the direction and pitch angle of the nozzle, the spray direction of the nozzle can be better controlled, which improves the applicability of the aircraft in fire fighting and other scenarios. The structure is stable and the operation is simple.

[0025] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages will become apparent from the description or be learned by practicing this invention. The objectives and other advantages of this invention can be realized and obtained from the details specifically pointed out in the text and accompanying drawings. Attached Figure Description

[0026] The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0027] Figure 1 This is a schematic diagram of the overall structure of the aircraft nozzle system according to Embodiment 1 of this utility model;

[0028] Figure 2 This is a partial structural diagram of the connection between the pull rod and the front connecting assembly in Embodiment 1 of this utility model;

[0029] Figure 3 This is a partial structural schematic diagram of the front connection component of Embodiment 1 of this utility model;

[0030] Figure 4 This is a partial structural schematic diagram of the second front connector of Embodiment 1 of this utility model;

[0031] Figure 5 This is a partial structural diagram of the nozzle and shaft pin connection in Embodiment 1 of this utility model;

[0032] Figure 6 This is a partial structural diagram of the connection between the nozzle and the rear connection unit in Embodiment 1 of this utility model;

[0033] Figure 7 This is a schematic diagram of the structure of the rear connection unit in Embodiment 1 of this utility model;

[0034] Figure 8 This is a schematic diagram of the mounting plate of Embodiment 1 of this utility model.

[0035] 1- Nozzle; 11- Pin; 2- Tie rod; 21- Rod end bearing; 211- Locking nut; 3- Upper connector; 4- Front connector assembly; 41- First front connector; 411- Half ring; 412- Top plate; 413- Shaft; 414- Rod end fixing piece; 42- Second front connector; 421- Ring sleeve; 422- Locking tongue; 43- Push bolt; 5- Rear connector unit; 51- Mounting plate; 511- Moving groove; 512- Push boss; 513- Positioning hole; 52- Lower adjusting block; 53- Upper adjusting block; 54- Adjusting assembly; 541- First push bolt; 542- Second push bolt; 55- Pin assembly; 551- Moving pin; 552- Fixing pin. Detailed Implementation

[0036] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of this application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0037] Example 1

[0038] A specific embodiment of this utility model discloses an aircraft nozzle system, such as... Figure 1 As shown, the assembly includes a nozzle 1, a pull rod 2, an upper connector 3, a front connecting assembly 4, and a rear connecting unit 5. One end of the pull rod 2 is connected to the nozzle 1 via the front connecting assembly 4, and the other end is connected to the frame via the upper connector 3. The nozzle 1 is connected to the frame via the rear connecting unit 5. The position of the nozzle 1 can be adjusted by adjusting the front connecting assembly 4 and the rear connecting unit 5.

[0039] There are two pull rods 2 and two upper connectors 3. One end of the upper connector 3 is fixed to the frame, and the other end is connected to the pull rod 2. The pull rod 2 connects the nozzle 1 to the frame, thereby supporting and fixing the nozzle 1.

[0040] Preferably, the pull rod 2 is symmetrically arranged about the nozzle 1, so that the nozzle 1 is kept in a balanced state.

[0041] Furthermore, such as Figures 2-3 As shown, a rod end bearing 21 is provided on the pull rod 2. The rod end bearing 21 is connected to the pull rod 2 and can move along the pull rod 2. A locking nut 211 is provided on the rod end bearing 21. Tightening the locking nut 211 can prevent the rod end bearing 21 from moving. Figure 3 As shown, the front connecting assembly 4 includes a first front connecting member 41, which includes a semi-ring 411 and a shaft 413. The shaft 413 is provided on the semi-ring 411. The two semi-rings 411 are connected to form a ring structure and are connected to the nozzle 1. The shaft 413 is connected to the rod end bearing 21, so that the pull rod 2 is connected to the nozzle 1 through the first front connecting member 41.

[0042] Preferred, such as Figure 2 As shown, the first front connector 41 also includes a rod end fixing member 414, which can fix the connection between the shaft 413 and the rod end bearing 21, thereby improving the stability of the connection between the shaft 413 and the rod end bearing 21. For example, the rod end fixing member 414 is a snap-fit.

[0043] Preferably, a rigid rubber plate is provided inside the ring structure formed by the connection of two semi-rings 411 to increase the friction between the semi-rings 411 and the nozzle 1 and prevent the semi-rings 411 from actively sliding along the nozzle 1.

[0044] Furthermore, such as Figures 3-4 As shown, the first front connector 41 also includes a top plate 412, and the front connector assembly 4 also includes a second front connector 42 and a push bolt 43. The second front connector 42 includes a ring 421 and a locking tongue 422. The ring 421 is fixedly connected to the nozzle 1, and the locking tongue 422 is inserted into the gap between the two half rings 411 to prevent the nozzle 1 from rotating. The push bolt 43 passes through the ring 421 and contacts the top plate 412. The push bolt 43 is threadedly connected to the ring 421. By adjusting the length of the ring 421 when the push bolt 43 is tightened, the push bolt 43 can push the top plate 412 to move, thereby causing the rod end bearing 21 to move along the pull rod 2 with the movement of the first front connector 41, driving the nozzle 1 to move with the pull rod 2, adjusting the pitch angle of the nozzle 1, and fixing the position of the nozzle 1 by tightening the locking nut 211.

[0045] Furthermore, such as Figure 5 As shown, a pin 11 is also provided on the nozzle 1. The pin 11 is connected to the outer wall of the nozzle 1 and is used to connect to the rear connection unit 5, so that the nozzle 1 is connected to the frame through the rear connection unit 5.

[0046] Preferably, the connection point between the upper connector 3 and the frame and the connection point between the rear connector 5 and the frame can form an isosceles triangle, thereby increasing the stability of the connection between the nozzle 1 and the frame.

[0047] Furthermore, such as Figures 6-7 As shown, the rear connection unit 5 includes a mounting plate 51, a lower adjusting block 52, and an upper adjusting block 53. The mounting plate 51 is fixed on the frame, the lower adjusting block 52 is connected to the mounting plate 51, and the upper adjusting block 53 is detachably connected to the lower adjusting block 52. When the upper adjusting block 53 is connected to the lower adjusting block 52, the upper adjusting block 53 and the lower adjusting block 52 cooperate to form a pin hole, and the pin shaft 11 is placed in the pin hole. The upper adjusting block 53 is located on both sides of the nozzle 1, thereby connecting the nozzle 1 to the frame through the rear connection unit 5.

[0048] For example, the upper adjusting block 53 and the lower adjusting block 52 are connected by bolts.

[0049] Preferably, boss structures are provided on both sides of the pin 11 to confine the pin 11 within the pin hole.

[0050] Furthermore, such as Figures 7-8 As shown, the rear connection unit 5 also includes an adjustment component 54 and a pin component 55. The lower adjustment block 52 is connected to the mounting plate 51 through the pin component 55, and the adjustment component 54 is connected to the mounting plate 51 to adjust the position of the lower adjustment block 52.

[0051] The mounting plate 51 is provided with a movable groove 511, a counter-protrusion 512, and a positioning hole 513. There are two counter-protrusions 512. The movable groove 511 is located between the counter-protrusions 512. The pin assembly 55 includes a movable pin 551 and a fixed pin 552. The movable pin 551 is threadedly connected to the lower adjusting block 52 and passes through the lower adjusting block 52 into the movable groove 511. The fixed pin 552 is connected to the lower adjusting block 52 and passes through the lower adjusting block 52 into the positioning hole 513, so that the lower adjusting block 52 is kept fixed.

[0052] When the movable pin 551 is loosened, the movable pin 551 can move along the movable groove 511, thereby driving the nozzle 1 to move through the lower adjusting block 52. When the movable pin 551 is tightened, the movable pin 551 can be fixed in the movable groove 511, thereby fixing the position of the nozzle 1.

[0053] The adjustment assembly 54 includes a first push bolt 541 and a second push bolt 542. The first push bolt 541 and the second push bolt 542 are respectively connected to the push bosses 512 on both sides of the moving groove 511. By controlling the length of the first push bolt 541 and the second push bolt 542 screwed into the push bosses 512, the first push bolt 541 or the second push bolt 542 can push the moving pin 551 to move along the moving groove 511, thereby adjusting the direction of the nozzle 1.

[0054] The first push bolt 541 includes a first rotating head and a first threaded section. The first rotating head is connected to the first threaded section, and the first threaded section is threadedly connected to the push boss 512 on one side of the moving groove 511. The position of the first threaded section corresponds to the position of the moving pin 551. By rotating the first rotating head, the length of the first threaded section screwed into the push boss 512 can be adjusted, so that the first threaded section pushes the moving pin 551 along the moving groove 511 towards the direction closer to the second push bolt 542. The second push bolt 542 includes a second rotating head and a second threaded section. The second rotating head is connected to the second threaded section, and the second threaded section is threadedly connected to the push boss 512 on the other side of the moving groove 511. The position of the second threaded section corresponds to the position of the moving pin 551. By rotating the second rotating head, the length of the second threaded section screwed into the push boss 512 can be adjusted, so that the second threaded section pushes the moving pin 551 along the moving groove 511 towards the direction closer to the first push bolt 541. By setting the first push bolt 541 and the second push bolt 542, the mobility of the moving pin 551 along the moving groove 511 is increased, thereby increasing the flexibility of adjusting the position of the nozzle 1.

[0055] Example 2

[0056] A specific embodiment of this utility model discloses an aircraft, including a frame and the aircraft nozzle system described in Embodiment 1, wherein the aircraft nozzle system is connected to the frame. An upper connector 3 and a rear connector 5 are connected to the frame, thereby fixing the nozzle 1 to the frame.

[0057] When it is necessary to adjust the direction of the nozzle 1, loosen the locking nut 211, the moving pin 551 and the fixing pin 552, and adjust the position of the adjusting block 52 by controlling the length of the first push bolt 541 and / or the second push bolt 542 screwed into the push boss 512, thereby adjusting the direction of the nozzle 1 so that the nozzle 1 is in the center position relative to the frame. Tighten the locking nut 211, the moving pin 551 and the fixing pin 552 to fix the position of the nozzle 1.

[0058] When it is necessary to adjust the pitch angle of the nozzle 1, loosen the locking nut 211, and push the top plate 412 to move by rotating the adjusting push bolt 43. This causes the rod end bearing 21 to move along the pull rod 2 along with the first front connecting piece 41, thereby adjusting the tilt of the nozzle 1 and making the nozzle 1 horizontal.

[0059] Compared with the prior art, the aircraft nozzle system of this utility model supports and adjusts the nozzle 1 through the front connecting component 4 and the rear connecting unit 5, thereby controlling the direction and pitch angle of the nozzle 1, making the spray direction of the nozzle 1 more accurate, and improving the adaptability and accuracy of the nozzle 1 in combination with different aircraft models; the locking tongue 422 can be inserted into the gap between the two semi-rings 411 to fix the tumbling of the nozzle 1, thereby preventing the nozzle 1 from rotating and improving the stability of the structure.

[0060] The aircraft of this utility model, by adopting the aircraft nozzle system, improves the stability and adaptability of the connection between the nozzle 1 and the frame. By adjusting the direction and pitch angle of the nozzle 1, the spray direction of the nozzle 1 can be better controlled, which improves the applicability of the aircraft in scenarios such as fire fighting. It has a stable structure and is easy to operate.

[0061] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present utility model should be included within the protection scope of the present utility model.

Claims

1. An aircraft nozzle system, characterized in that, It includes a nozzle (1), a pull rod (2), an upper connector (3), a front connecting assembly (4), and a rear connecting unit (5); One end of the pull rod (2) is connected to the nozzle (1) through the front connecting assembly (4), and the other end is connected to the upper connecting piece (3). The nozzle (1) is connected to the rear connecting unit (5). The front connecting assembly (4) and the rear connecting unit (5) cooperate to support and adjust the position of the nozzle (1).

2. The aircraft nozzle system according to claim 1, characterized in that, The front connection assembly (4) includes a first front connector (41), which includes a semi-ring (411) and a shaft (413). The shaft (413) is disposed on the semi-ring (411), and the two semi-rings (411) are connected to form a ring structure that is connected to the nozzle (1).

3. The aircraft nozzle system according to claim 2, characterized in that, The front connecting assembly (4) further includes a second front connecting member (42) and a push bolt (43), the first front connecting member (41) further includes a top plate (412); the second front connecting member (42) includes a ring sleeve (421); The push bolt (43) passes through the ring (421) and contacts the top plate (412) to push the top plate (412) to move.

4. The aircraft nozzle system according to claim 3, characterized in that, The second front connector (42) also includes a locking tongue (422) which is inserted into the gap between the two semi-rings (411) to prevent the nozzle (1) from rotating.

5. The aircraft nozzle system according to claim 1, characterized in that, A pin (11) is provided on the nozzle (1), and the pin (11) is used to connect the rear connecting unit (5); The rear connection unit (5) includes a mounting plate (51), a lower adjusting block (52) and an upper adjusting block (53). The lower adjusting block (52) is connected to the mounting plate (51). The upper adjusting block (53) is disposed on both sides of the nozzle (1). The upper adjusting block (53) and the lower adjusting block (52) are connected to form a pin hole. The pin shaft (11) is disposed in the pin hole.

6. The aircraft nozzle system according to claim 5, characterized in that, The rear connection unit (5) further includes an adjustment component (54) and a pin component (55). The lower adjustment block (52) is connected to the mounting plate (51) through the pin component (55). The adjustment component (54) is connected to the mounting plate (51) and is used to adjust the position of the lower adjustment block (52).

7. The aircraft nozzle system according to claim 6, characterized in that, The mounting plate (51) is provided with a moving groove (511), a counter-pushing boss (512) and a positioning hole (513). The moving groove (511) is disposed between the counter-pushing bosses (512). The pin assembly (55) includes a moving pin (551) and a fixing pin (552). The movable pin (551) is threadedly connected to the lower adjusting block (52) and passes through the lower adjusting block (52) into the movable groove (511). The fixed pin (552) is connected to the lower adjusting block (52) and passes through the lower adjusting block (52) into the positioning hole (513).

8. The aircraft nozzle system according to claim 7, characterized in that, The adjustment assembly (54) includes a first push bolt (541) and a second push bolt (542), the first push bolt (541) and the second push bolt (542) being connected to the push bosses (512) on both sides of the moving groove (511), respectively. The first push bolt (541) and the second push bolt (542) are used to push the movable pin (551) to move along the movable groove (511).

9. The aircraft nozzle system according to claim 2, characterized in that, A rod end bearing (21) is provided on the pull rod (2). The rod end bearing (21) is connected to the pull rod (2) and can move along the pull rod (2). The shaft (413) is connected to the rod end bearing (21).

10. An aircraft, characterized in that, Includes a frame and an aircraft nozzle system as described in any one of claims 1-9, wherein the upper connector (3) and the rear connector (5) are connected to the frame.

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