Aircraft nozzle system, aircraft and nozzle adjusting method

Abstract

The invention discloses an aircraft nozzle system, an aircraft and a nozzle adjusting method, relates to the technical field of aircrafts, and aims to solve the problem that a nozzle of the aircraft is difficult to adjust in the prior art. The aircraft spraying pipe system comprises a spraying 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] The present invention relates to the technical field of aircraft, and in particular to an aircraft nozzle system, an aircraft and a nozzle adjustment method. Background Art

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

[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 on the water flow, the water spray pipe needs to extend out of the rotor downwash influence area. When the water spray pipe is connected to different aircraft, the installation error will cause the water spray pipe to be offset to varying degrees. Since the water spray pipe sprays liquid over a long distance, if the water spray pipe is not adjusted, the sprayed liquid will have a large deviation. Summary of the invention

[0004] In view of the above analysis, the present invention aims to provide an aircraft nozzle system, an aircraft and a nozzle adjustment method, so as to solve the problem that it is difficult to adjust the nozzle of the aircraft in the prior art.

[0005] The purpose of the present invention is mainly achieved through the following technical solutions:

[0006] In one aspect, the present invention provides an aircraft nozzle system, comprising a nozzle, a pull rod, an upper connecting member, a front connecting assembly and a rear connecting unit;

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

[0008] Furthermore, the front connection assembly includes a first front connection member, which includes a half ring and a shaft rod, the shaft rod is arranged on the half ring, and two half rings are connected to form a circular ring structure connected to the nozzle.

[0009] Furthermore, the front connection assembly further comprises a second front connection member and a push bolt, the first front connection member further comprises a top plate; the second front connection member comprises a ring sleeve;

[0010] The push bolt passes through the ring sleeve and contacts the top plate, so as to push the top plate to move.

[0011] Furthermore, the second front connecting member also includes a locking tongue, which is inserted into the gap between the two half 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, wherein the lower adjusting block is connected to the mounting plate, the upper adjusting block is arranged on both sides of the nozzle, the upper adjusting block is connected to the lower adjusting block to form a pin hole, and the pin shaft is arranged in the pin hole.

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

[0015] Further, the mounting plate is provided with a movable groove, a push boss and a positioning hole, the push boss is provided with two, the movable groove is provided between the push bosses, and the pin assembly includes a movable pin and a fixed pin;

[0016] The movable pin is threadedly connected to the lower adjusting block and penetrates through the lower adjusting block to enter the movable groove, and the fixed pin is connected to the lower adjusting block and penetrates through the lower adjusting block to enter the positioning hole.

[0017] Further, the adjustment assembly comprises a first pair of pushing bolts and a second pair of pushing bolts, wherein the first pair of pushing bolts and the second pair of pushing bolts are respectively connected to the pair of pushing bosses on both sides of the moving groove;

[0018] The first pair of pushing bolts and the second pair of pushing bolts are used to push the moving pin to move along the moving slot.

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

[0020] On the other hand, the present invention further provides an aircraft, comprising a frame and the above-mentioned aircraft nozzle system, wherein the upper connecting member and the rear connecting unit are connected to the frame.

[0021] On the other hand, the present invention also provides a nozzle adjustment method according to the above-mentioned aircraft nozzle system, comprising the following steps:

[0022] S1: Connect the nozzle to the pull rod;

[0023] S2: Connect the aircraft nozzle system to the frame;

[0024] S3: Adjust the direction and pitch angle of the nozzle.

[0025] Furthermore, step S3 specifically includes the following steps:

[0026] S31: Adjust the direction of the nozzle so that the nozzle is centered relative to the frame;

[0027] S32: Adjust the pitch angle of the nozzle to make the nozzle in a horizontal state;

[0028] In step S31, the locking nut, the movable pin and the fixed pin on the rod end bearing are loosened, and the length of the first push bolt and / or the second push bolt screwed into the push boss is adjusted to center the position of the nozzle relative to the frame, and then the locking nut, the movable pin and the fixed pin are tightened;

[0029] In step S32, the locking nut on the rod end bearing is loosened, and the push bolt is adjusted so that the push bolt pushes the top plate to move, driving the nozzle to rotate around the pin shaft as the axis. After the nozzle is adjusted to a horizontal state, the locking nut is tightened.

[0030] Furthermore, step S2 specifically includes the following steps:

[0031] S21: Connect the nozzle to the frame;

[0032] S22: Connect the pull rod to the frame.

[0033] Further, in step S21, the pin shaft is placed on the lower adjusting block, and the upper adjusting block is connected so that the upper adjusting block cooperates with the lower adjusting block to form a pin hole, and the pin shaft is fixed in the pin hole so that the upper adjusting block is located on both sides of the nozzle, thereby connecting the nozzle to the frame through the rear connecting unit.

[0034] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0035] (1) The aircraft nozzle system of the present invention supports and adjusts the nozzle through the front connecting assembly 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 in combination with different aircraft models, and meeting diverse usage requirements.

[0036] (2) The aircraft nozzle system of the present invention can fix the nozzle's tumbling by inserting a locking tongue into the gap between the two half rings, thereby preventing the nozzle from rotating and improving the stability of the structure.

[0037] (3) The aircraft of the present invention, by adopting the aircraft nozzle system, improves the stability and adaptability of the connection between the nozzle and the frame. By adjusting the direction and pitch angle of the nozzle, the spray direction of the nozzle can be better controlled, thereby improving the applicability of the aircraft in fire fighting and other scenarios. The structure is stable and the operation is simple.

[0038] (4) The nozzle adjustment method of the present invention adjusts the direction and pitch angle of the nozzle through step S3, so that the nozzle can be adapted to different aircraft, the spray direction of the nozzle is more accurate, and the adaptability and accuracy of the nozzle combined with different aircraft models are improved. By loosening the locking nut, the moving pin and the fixed pin on the rod end bearing, adjusting the length of the first push bolt and / or the second push bolt screwed into the push boss, the first push bolt and / or the second push bolt push the moving pin to move along the moving groove, thereby adjusting the position of the nozzle, so that the position of the nozzle relative to the frame is centered; by loosening the locking nut on the rod end bearing, adjusting the push bolt, the push bolt pushes the top plate to move, and the rod end bearing moves along the pull rod with the movement of the first front connecting member, thereby driving the nozzle to rotate with the pin shaft as the axis, and adjusting the nozzle to a horizontal state. The operation is simple and the adjustment is convenient, and the accuracy of the nozzle spray can be improved.

[0039] In the present invention, the above-mentioned technical solutions can also be combined with each other to achieve more preferred combination solutions. Other features and advantages of the present invention will be described in the subsequent description, and some advantages can become obvious from the description, or can be understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained through the contents particularly pointed out in the embodiments of the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] The accompanying drawings are only for the purpose of illustrating the particular invention and are not to be considered as limiting the invention. The same reference symbols denote the same components throughout the accompanying drawings.

[0041] Figure 1 Schematic diagram of the overall structure of the aircraft nozzle system of Example 1 of the present invention;

[0042] Figure 2 It is a partial structural schematic diagram of the connection between the pull rod and the front connecting assembly of Example 1 of the present invention;

[0043] Figure 3 It is a partial structural schematic diagram of the front connection assembly of Example 1 of the present invention;

[0044] Figure 4 It is a partial structural schematic diagram of the second front connecting member of Example 1 of the present invention;

[0045] Figure 5 It is a schematic diagram of the partial structure of the connection between the nozzle and the pin shaft in Example 1 of the present invention;

[0046] Figure 6 It is a schematic diagram of a partial structure of the connection between the nozzle and the rear connection unit of Example 1 of the present invention;

[0047] Figure 7This is a schematic structural diagram of the rear connection unit connection of Example 1 of the present invention;

[0048] Figure 8 It is a structural schematic diagram of a mounting plate according to Embodiment 1 of the present invention;

[0049] Fig. 9 It is a schematic flow chart of the nozzle adjustment method of Example 3 of the present invention.

[0050] Reference numerals:

[0051] 1-nozzle; 11-pin shaft; 2-pull rod; 21-rod end bearing; 211-locking nut; 3-upper connecting piece; 4-front connecting assembly; 41-first front connecting piece; 411-semi-ring; 412-top plate; 413-axle rod; 414-rod end fixing piece; 42-second front connecting piece; 421-ring sleeve; 422-locking tongue; 43-thrust bolt; 5-rear connecting unit; 51-mounting plate; 511-movable 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-movable pin; 552-fixed pin. DETAILED DESCRIPTION

[0052] The preferred embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings, wherein the accompanying drawings constitute a part of the present invention and are used to explain the principles of the present invention together with the present invention.

[0053] Example 1

[0054] A specific embodiment of the present invention discloses an aircraft nozzle system, such as Figure 1 As shown, the nozzle 1 includes a pull rod 2, an upper connecting member 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 frame through the upper connecting member 3. The nozzle 1 is connected to the frame through 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.

[0055] There are two pull rods 2 and two upper connecting members 3. One end of the upper connecting member 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.

[0056] Preferably, the pull rod 2 is symmetrically arranged with respect to the nozzle 1, so that the nozzle 1 maintains a balanced state.

[0057] Furthermore, if Figure 2-Figure 3As 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, and a locking nut 211 is provided on the rod end bearing 21, and the movement of the rod end bearing 21 can be prevented by tightening the locking nut 211; Figure 3 As shown, the front connection assembly 4 includes a first front connection member 41, and the first front connection member 41 includes a half ring 411 and a shaft rod 413. The shaft rod 413 is arranged on the half ring 411. The two half rings 411 are connected to form a circular ring structure connected to the nozzle 1. The shaft rod 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 connection member 41.

[0058] Preferably, Figure 2 As shown, the first front connecting member 41 further includes a rod end fixing member 414, through which the connection between the shaft rod 413 and the rod end bearing 21 can be fixed, thereby improving the stability of the connection between the shaft rod 413 and the rod end bearing 21. Exemplarily, the rod end fixing member 414 is a buckle.

[0059] Preferably, a hard rubber plate is arranged inside the circular ring structure formed by connecting two half rings 411 to increase the friction between the half rings 411 and the nozzle 1 and prevent the half rings 411 from actively sliding along the nozzle 1 .

[0060] Furthermore, if Figure 3-4 As shown, the first front connecting member 41 also includes a top plate 412, and the front connecting assembly 4 also includes a second front connecting member 42 and a push bolt 43. The second front connecting member 42 includes a ring sleeve 421 and a locking tongue 422. The ring sleeve 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 sleeve 421 and contacts the top plate 412. The push bolt 43 is threadedly connected to the ring sleeve 421. By adjusting the length of the push bolt 43 to tighten the ring sleeve 421, the push bolt 43 can push the top plate 412 to move, so that the rod end bearing 21 moves along the pull rod 2 with the movement of the first front connecting member 41, driving the nozzle 1 to move with the pull rod 2, and adjusting the pitch angle of the nozzle 1. The pull rod 2 is fixed by tightening the locking nut 211, thereby fixing the position of the nozzle 1.

[0061] Furthermore, if Figure 5 As shown, a pin shaft 11 is also provided on the nozzle 1 , and the pin shaft 11 is connected to the outer wall of the nozzle 1 for connecting to the rear connecting unit 5 , so that the nozzle 1 is connected to the frame through the rear connecting unit 5 .

[0062] Preferably, the connection point between the upper connecting member 3 and the frame and the connection point between the rear connecting unit 5 and the frame can be connected to form an isosceles triangle, thereby increasing the stability of the connection between the nozzle 1 and the frame.

[0063] Furthermore, if Figure 6-7As shown, the rear connecting 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 cooperates with the lower adjusting block 52 to form a pin hole, the pin shaft 11 is placed in the pin hole, and the upper adjusting block 53 is located on both sides of the nozzle 1, so that the nozzle 1 is connected to the frame through the rear connecting unit 5.

[0064] Exemplarily, the upper adjusting block 53 and the lower adjusting block 52 are connected by bolts.

[0065] Preferably, boss structures are provided on both sides of the pin shaft 11 to restrict the pin shaft 11 in the pin hole.

[0066] Furthermore, if Figure 7-8 As shown, the rear connection unit 5 further includes an adjustment assembly 54 and a pin assembly 55 . The lower adjustment block 52 is connected to the mounting plate 51 via the pin assembly 55 . The adjustment assembly 54 is connected to the mounting plate 51 for adjusting the position of the lower adjustment block 52 .

[0067] A movable groove 511, a push boss 512 and a positioning hole 513 are provided on the mounting plate 51. Two push bosses 512 are provided. The movable groove 511 is provided between the push bosses 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 penetrates the lower adjusting block 52 into the movable groove 511. The fixed pin 552 is connected to the lower adjusting block 52 and penetrates the lower adjusting block 52 into the positioning hole 513, so that the lower adjusting block 52 remains fixed.

[0068] 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 adjustment 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.

[0069] The adjustment assembly 54 includes a first push bolt 541 and a second push bolt 542, which are respectively connected to the push bosses 512 on both sides of the movable groove 511. By controlling the length of the first push bolt 541 and the second push bolt 542 screwed into the push boss 512, the first push bolt 541 or the second push bolt 542 can push the movable pin 551 to move along the movable groove 511, thereby adjusting the direction of the nozzle 1.

[0070] 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, the first threaded section is threadedly connected to the push boss 512 on one side of the moving groove 511, and 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 to move along the moving groove 511 in the direction close 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, the second threaded section is threadedly connected to the push boss 512 on the other side of the moving groove 511, and 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 to move along the moving groove 511 in the direction close to the first push bolt 541. The first push bolt 541 and the second push bolt 542 are provided to increase the mobility of the moving pin 551 along the moving groove 511 , thereby increasing the flexibility of adjusting the position of the nozzle 1 .

[0071] Example 2

[0072] A specific embodiment of the present invention discloses an aircraft, comprising a frame and the aircraft nozzle system described in Example 1, wherein the aircraft nozzle system is connected to the frame. The upper connecting member 3 and the rear connecting unit 5 are connected to the frame, so that the nozzle 1 is fixed to the frame.

[0073] When it is necessary to adjust the direction of the nozzle 1, loosen the locking nut 211, the movable pin 551 and the fixed pin 552, and adjust the position of the lower adjustment block 52 by controlling the length of the first push bolt 541 and / or the second push bolt 542 to be screwed into the push boss 512, thereby adjusting the direction of the nozzle 1 so that the nozzle 1 is in a centered position relative to the frame, and tighten the locking nut 211, the movable pin 551 and the fixed pin 552 to fix the position of the nozzle 1.

[0074] When the pitch angle of the nozzle 1 needs to be adjusted, the locking nut 211 is loosened, and the top plate 412 is pushed to move by rotating the adjusting push bolt 43, so that the rod end bearing 21 moves along the pull rod 2 with the movement of the first front connecting member 41, and the inclination of the nozzle 1 is adjusted to make the nozzle 1 in a horizontal state.

[0075] Example 3

[0076] A specific embodiment of the present invention discloses a nozzle adjustment method according to the above-mentioned aircraft nozzle system, such as Fig. 9 As shown, the following steps are included:

[0077] S1: Connect the nozzle 1 to the tie rod 2;

[0078] S2: Connect the aircraft nozzle system to the frame;

[0079] S3: Adjust the direction and pitch angle of the nozzle 1.

[0080] In step S1 , specifically, the rod end bearing 21 is connected to the shaft 413 , and the connection between the rod end bearing 21 and the shaft 413 is fixed by the rod end fixing member 414 .

[0081] Furthermore, step S2 specifically includes the following steps:

[0082] S21: Connect the nozzle 1 to the frame;

[0083] S22: Connect the pull rod 2 to the frame.

[0084] In step S21, specifically, the pin shaft 11 is placed on the lower adjusting block 52, and the upper adjusting block 53 is connected so that the upper adjusting block 53 cooperates with the lower adjusting block 52 to form a pin hole, and the pin shaft 11 is fixed in the pin hole so that 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 connecting unit 5.

[0085] In step S22 , specifically, the pull rod 2 is connected to the upper connecting member 3 , so that the pull rod 2 is connected to the frame through the upper connecting member 3 .

[0086] Furthermore, step S3 specifically includes the following steps:

[0087] S31: Adjust the direction of the nozzle 1 so that the nozzle 1 is centered relative to the frame;

[0088] S32: Adjust the pitch angle of the nozzle 1 so that the nozzle 1 is in a horizontal state.

[0089] In step S31, specifically, the locking nut 211, the movable pin 551 and the fixed pin 552 on the rod end bearing 21 are loosened, and the length of the first push bolt 541 and / or the second push bolt 542 screwed into the push boss 512 is adjusted so that the first push bolt 541 and / or the second push bolt 542 push the movable pin 551 to move along the movable groove 511, thereby adjusting the direction of the nozzle 1. After the position of the nozzle 1 is centered relative to the frame, the locking nut 211, the movable pin 551 and the fixed pin 552 are tightened.

[0090] In step S32, specifically, loosen the locking nut 211 on the rod end bearing 21, adjust the push bolt 43, so that the push bolt 43 pushes the top plate 412 to move, so that the rod end bearing 21 moves along the pull rod 2 with the movement of the first front connecting member 41, thereby driving the nozzle 1 to rotate around the pin shaft 11 as the axis, and after adjusting the nozzle 1 to a horizontal state, tighten the locking nut 211.

[0091] Compared with the prior art, the aircraft nozzle system of the present invention supports and adjusts the nozzle 1 through the front connecting assembly 4 and the rear connecting unit 5, thereby controlling the direction and pitch angle of the nozzle 1, making the injection 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 is inserted into the gap between the two half rings 411 to fix the tumbling of the nozzle 1, thereby preventing the nozzle 1 from rotating and improving the stability of the structure.

[0092] The aircraft of the present invention, by adopting the aircraft nozzle system, improves the stability and adaptability of the connection between the nozzle 1 and the frame, and can better control the spray direction of the nozzle 1 by adjusting the direction and pitch angle of the nozzle 1, thereby improving the applicability of the aircraft in scenes such as fire fighting, and has a stable structure and is easy to operate.

[0093] The nozzle adjustment method of the present invention adjusts the direction and pitch angle of the nozzle 1 through step S3, so that the position of the nozzle 1 relative to the frame is centered and in a horizontal state, so that the direction and pitch angle of the nozzle 1 can be adjusted according to different frames, so that the nozzle 1 can cooperate with the frames of different aircraft, thereby improving the adaptability of the nozzle 1 and the accuracy of injection, and the operation is simple and the adjustment is convenient.

[0094] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technical field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. An aircraft nozzle system, characterized in that: It comprises a nozzle (1), a pull rod (2), an upper connecting piece (3), a front connecting component (4) and a rear connecting unit (5); One end of the pull rod (2) is connected to the nozzle (1) through the front connecting component (4), and the other end is connected to the upper connecting member (3). The nozzle (1) is connected to the rear connecting unit (5). The front connecting component (4) and the rear connecting unit (5) cooperate with each other 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) comprises a first front connection member (41), wherein the first front connection member (41) comprises a half ring (411) and a shaft rod (413), wherein the shaft rod (413) is arranged on the half ring (411), and two half rings (411) are connected to form a circular ring structure connected to the nozzle (1).

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

4. The aircraft nozzle system according to claim 3, characterized in that: The second front connecting member (42) further comprises a locking tongue (422), wherein the locking tongue (422) is inserted into the gap between the two half rings (411) to prevent the nozzle (1) from rotating.

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

6. The aircraft nozzle system according to claim 5, characterized in that: The rear connection unit (5) further comprises an adjustment assembly (54) and a pin assembly (55); the lower adjustment block (52) is connected to the mounting plate (51) via the pin assembly (55); and the adjustment assembly (54) is connected to the mounting plate (51) for adjusting 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 movable groove (511), a push boss (512) and a positioning hole (513); the movable groove (511) is provided between the push bosses (512); and the pin assembly (55) includes a movable pin (551) and a fixed pin (552); The movable pin (551) is threadedly connected to the lower adjustment block (52) and penetrates the lower adjustment block (52) to enter the movable groove (511), and the fixed pin (552) is connected to the lower adjustment block (52) and penetrates the lower adjustment block (52) to enter the positioning hole (513).

8. The aircraft nozzle system according to claim 7, characterized in that: The adjustment assembly (54) comprises a first push bolt (541) and a second push bolt (542), wherein 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); The first pair of push bolts (541) and the second pair of push bolts (542) are used to push the moving pin (551) to move along the moving 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), and the shaft rod (413) is connected to the rod end bearing (21).

10. An aircraft, characterized in that: It comprises a frame and the aircraft nozzle system according to any one of claims 1 to 9, wherein the upper connecting member (3) and the rear connecting unit (5) are connected to the frame.

11. The nozzle adjustment method for an aircraft nozzle system according to any one of claims 1 to 9, characterized in that: The steps include: S1: connecting the nozzle (1) to the pull rod (2); S2: Connect the aircraft nozzle system to the frame; S3: Adjust the direction and pitch angle of the nozzle (1).

12. The nozzle adjustment method according to claim 11, characterized in that: Step S3 specifically includes the following steps: S31: adjusting the direction of the nozzle (1) so that the position of the nozzle (1) is centered relative to the frame; S32: adjusting the pitch angle of the nozzle (1) so that the nozzle (1) is in a horizontal state; In step S31, the locking nut (211), the movable pin (551) and the fixed pin (552) on the rod end bearing (21) are loosened, and the length of the first push bolt (541) and / or the second push bolt (542) screwed into the push boss (512) is adjusted to center the position of the nozzle (1) relative to the frame, and then the locking nut (211), the movable pin (551) and the fixed pin (552) are tightened; In step S32, the locking nut (211) on the rod end bearing (21) is loosened, and the push bolt (43) is adjusted so that the push bolt (43) pushes the top plate (412) to move, thereby driving the nozzle (1) to rotate around the pin shaft (11). After adjusting the nozzle (1) to a horizontal state, the locking nut (211) is tightened.

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