Engine nozzle folding and unfolding control equipment

Abstract

An engine nozzle retracting and releasing control device belongs to the technical field of aero-engine nozzles and comprises a stress application cylinder, a cross beam is mounted at the tail of the stress application cylinder, a hydraulic actuator cylinder, a rocker arm and a first adjusting piece are hinged to the cross beam, the bottom of the rocker arm is hinged to the cross beam, and the front end of the rocker arm is hinged to the telescopic end of the hydraulic actuator cylinder. The rear end of the rocker arm is hinged to a first adjusting piece through a first pull rod, and the front end of the first adjusting piece is hinged to the stress application barrel. Adjusting sheets II are arranged on the inner sides of the adjusting sheets I at intervals; a guide groove is formed in the outer side face of the second adjusting piece in the length direction, a connecting rod is arranged on the inner side face of the tail of the first adjusting piece, and a roller capable of rolling along the guide groove is arranged at the inner bottom end of the connecting rod. The first adjusting piece is matched with the guide groove of the second adjusting piece through the connecting rod with the rolling wheel, traditional sliding friction is converted into rolling friction, and therefore the friction coefficient is reduced, the motion resistance is greatly reduced, the jamming risk under the high-temperature working condition is effectively avoided, and the thrust response speed of an engine is increased.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine nozzle technology, specifically an engine nozzle retraction and extension control device. Background Technology

[0002] As the core actuator for achieving thrust optimization under all operating conditions, the adjustable exhaust nozzle's technical condition directly determines the engine's thrust performance, fuel economy, and operational reliability.

[0003] Existing technologies suffer from several key defects that severely limit their performance. In particular, the all-state supersonic exhaust nozzle with external control plates requires simultaneous subsonic convergence and supersonic expansion adjustment; its mobility and risk of jamming directly determine the engine's thrust performance and reliability. Existing technologies exhibit the following key defects: excessive frictional resistance of the moving parts is a core issue. The external control plates and supersonic control plates often use rigid sliding contact, resulting in high frictional resistance (sliding friction coefficient 0.3-0.5) and a lack of precise guiding structures. Under high-temperature conditions, thermal expansion of components can easily lead to "thermal jamming." Elastic elements are often randomly configured without fixed quantities, leading to uneven stress on the transition section between the external control plate and the fuselage, causing surface distortion and exacerbating motion resistance. The connection between the external control plate and the fuselage is often rigidly fixed, unable to compensate for assembly errors (such as coaxiality deviation ±0.5mm), easily causing stress concentration and jamming during nozzle retraction and expansion. The aforementioned problems result in poor nozzle movement flexibility and a jamming failure rate of 15%-20%. This not only limits the response speed of nozzle cross-section adjustment but also easily causes component wear, reducing engine thrust performance and service life, and urgently requires targeted solutions. Summary of the Invention

[0004] To address the problem of jamming between the inner and outer adjusting vanes during nozzle retraction and expansion, which affects flexibility, this invention provides an engine nozzle retraction and expansion control device.

[0005] This invention is achieved through the following technical solution: An engine nozzle retraction and extension control device includes a booster cylinder, a crossbeam mounted at the rear of the booster cylinder, a hydraulic actuator, a rocker arm, and an adjusting plate 1 hinged to the crossbeam, the bottom of the rocker arm hinged to the crossbeam, the front end of the rocker arm hinged to the telescopic end of the hydraulic actuator, the rear end of the rocker arm hinged to the adjusting plate 1 via a pull rod, and the front end of the adjusting plate 1 hinged to the booster cylinder; the hydraulic actuator, rocker arm, and adjusting plate 1 are arranged in a ring on the crossbeam; adjusting plate 2 is spaced apart on the inner side of the adjusting plate 1; a guide groove is provided on the outer side of the adjusting plate 2 along its length, a connecting rod is provided on the inner side of the rear of the adjusting plate 1, and a roller capable of rolling along the guide groove is provided at the inner bottom end of the connecting rod; the adjusting plate 2 can be driven by the connecting rod to complete the opening and closing action.

[0006] The annular distribution design of the hydraulic actuator, rocker arm, and adjusting plate one ensures uniform force distribution around the nozzle, avoiding component deformation caused by localized stress concentration. Adjusting plate one, through the cooperation of a connecting rod with rollers and the guide groove of adjusting plate two, transforms traditional sliding friction into rolling friction, thereby reducing the coefficient of friction, significantly reducing motion resistance, and effectively avoiding the risk of jamming under high-temperature conditions. The precise cooperation between the connecting rod and the guide groove ensures the stability of the opening and closing trajectory of adjusting plate two, adapting to the full-condition requirements of subsonic convergence and supersonic expansion, and improving the engine thrust response speed.

[0007] A further improvement of the present invention is that a support arm is provided between the rocker arm and the first pull rod. The front end of the bottom of the support arm is hinged to the rear end of the rocker arm, the rear end of the bottom of the support arm is hinged to the first pull rod, and the top of the support arm is hinged to the crossbeam with a limiter four. As an intermediate component for power transmission, the support arm optimizes the force transmission path between the rocker arm and the first pull rod, reduces transmission gaps, and improves adjustment synchronization. The limiter four can precisely limit the movement stroke of the support arm, avoid component collision damage caused by excessive displacement, and at the same time enhance the structural rigidity of the support arm, reduce vibration deformation, further reduce the incidence of jamming failures, and make the nozzle retraction and extension actions more stable and reliable.

[0008] A further improvement of the present invention is that two tie rods are connected to one support arm, and the two tie rods on two adjacent support arms are jointly hinged to the adjusting plate. This design of two tie rods jointly hinged to the adjusting plate makes the force distribution of the adjusting plate more balanced, avoiding the risk of breakage due to overload of a single tie rod. It also improves the synchronization of the opening and closing of adjacent adjusting plates, prevents circumferential displacement, ensures a flat nozzle profile, reduces aerodynamic drag loss caused by airflow disturbance, and improves the aerodynamic efficiency of the nozzle.

[0009] A further improvement of the present invention is that a pneumatic actuator is hinged between two adjacent adjusting plates, the pneumatic actuator being hinged in the middle section of the adjusting plate. The pneumatic actuator adopts a unidirectional structure, simplifying the internal sealing and reversing mechanism, effectively reducing weight compared to traditional bidirectional actuators, and reducing the number of failure points; the working air source uses compressed air from a high-pressure compressor, eliminating the need for additional high-pressure air cylinders or air pumps, saving aircraft space while utilizing the existing energy flow of the engine, thus reducing fuel consumption; the design of the pairs hinged in the middle section of the adjusting plate assists the hydraulic actuator in achieving rapid response, shortening the adjustment response time, while ensuring uniform opening and closing of the adjusting plates in one circumference, avoiding jamming caused by uneven loading.

[0010] A further improvement of the present invention is that a sealing plate is provided on the inner side between two adjacent adjusting plates. The front end of the sealing plate is movably mounted on the adjusting plate, and the rear end of the sealing plate is connected to the adjacent adjusting plates via a limiter. The limiter restricts the circumferential movement of the sealing plate. The sealing plate effectively prevents high-temperature combustion gas from leaking from the gap between the adjusting plates. Combined with the circumferential limiting function of the limiter, it prevents the sealing plate from shifting under the impact of high-speed airflow, significantly improving the sealing effect. The movable mounting design adapts to the opening and closing action of the adjusting plates, ensuring that the sealing plate always fits the inner surface of the adjusting plate, preventing the sealing gap from widening, improving the internal aerodynamic efficiency of the nozzle, and reducing thrust loss.

[0011] A further improvement of the present invention is that a second sealing plate is provided between adjacent second regulating plates, and the second sealing plate is connected to the adjacent second regulating plates by a second limiter. The second sealing plate and the first sealing plate form a double sealing structure, which fully covers the gap area between the first and second regulating plates, further reducing the amount of gas leakage, improving the continuity of airflow inside the nozzle, and reducing eddy current losses; the second limiter can restrict the displacement of the second sealing plate, ensuring that it opens and closes synchronously with the second regulating plate, avoiding wrinkles or breakage of the second sealing plate, extending the service life of the sealing components, and ensuring sufficient airflow expansion in the supersonic range, thereby improving the supersonic thrust performance of the engine.

[0012] A further improvement of the present invention is that a hinge housing is installed on the tail of the afterburner, and an adjustment plate three is provided between the hinge housing and the adjustment plate two. The front end of the adjustment plate three is hinged to the hinge housing, and the front end of the bottom of the support arm is hinged to the adjustment plate three via a tie rod three. The adjustment plate three realizes the subsonic convergence function, which, in conjunction with the supersonic expansion function of the adjustment plate two, completes the nozzle cross-section adjustment under all operating conditions, adapting to different flight states from takeoff to supersonic cruise. The hinge housing provides stable hinge support for the adjustment plate three, reducing assembly errors. The tie rod three transmits the power of the support arm, ensuring that the adjustment plate three moves in coordination with the adjustment plates one and two, avoiding surface distortion caused by the lag of a single component's movement, and improving the overall aerodynamic performance of the nozzle.

[0013] A further improvement of the present invention is that two tie rods three are connected to one support arm, and the two tie rods three on two adjacent support arms are hinged together to the adjusting plate three. The connection design of the double tie rods three enhances the connection rigidity between the support arm and the adjusting plate three, disperses the stress load, avoids fatigue damage caused by long-term stress on a single tie rod, and improves structural reliability; the tie rods three of the two adjacent support arms work together to further ensure the circumferential force balance of the adjusting plate three, effectively improves the flatness of the nozzle profile when it opens and closes, and can reduce the aerodynamic drag of the rear body, while ensuring that the adjusting plate one and the adjusting plate three move synchronously and avoid motion interference.

[0014] A further improvement of the present invention is that a sealing plate three is provided between adjacent adjusting plates three. The front end of the sealing plate three is mounted on the adjusting plate three by a pin, and the rear end of the sealing plate three is hinged to the sealing plate two. The sealing plate three connects the adjusting plate three and the sealing plate two, forming a complete sealing link, which completely blocks the gas leakage channel; the pin enables the flexible installation of the sealing plate three, adapting to the hinged rotation of the adjusting plate three, and the hinged design of the rear end with the sealing plate two ensures the continuity of the sealing link, avoids sealing gaps caused by differences in component movement, improves airflow stability, reduces aerodynamic losses, and further optimizes engine fuel economy.

[0015] A further improvement of the present invention includes an elastic element, the inner side of which is connected to a support ring. The support ring is connected to the crossbeam via a tie rod four, and the tail end of the elastic element covers the front end of the adjusting plate one. The elastic element adopts a quantitative circumferential distribution design, which can evenly support the front end of the adjusting plate one, avoid surface distortion caused by local force concentration, optimize the transition surface between the fuselage and the nozzle, and reduce vortex drag caused by airflow separation. The hinged structure of the support ring and the tie rod four can compensate for the assembly error between the force-adding cylinder and the crossbeam, allow for a small radial displacement when the adjusting plate one is extended or retracted, and reduce the incidence of jamming failure. The design of the elastic element covering the front end of the adjusting plate one further improves the aerodynamic smoothness of the rear body, increases the overall lift-to-drag ratio, and enhances the structural rigidity of the front end of the adjusting plate one, extending its service life.

[0016] As can be seen from the above technical solutions, the beneficial effects of the present invention are as follows: the annular distribution design of the hydraulic actuator, rocker arm, and adjusting plate one ensures uniform force on the nozzle circumferentially, avoiding component deformation caused by local stress concentration; adjusting plate one, through the cooperation of the connecting rod with rollers and the guide groove of adjusting plate two, transforms traditional sliding friction into rolling friction, thereby reducing the friction coefficient, significantly reducing motion resistance, and effectively avoiding the risk of jamming under high temperature conditions; the precise cooperation between the connecting rod and the guide groove ensures the stability of the opening and closing trajectory of adjusting plate two, adapting to the full-condition requirements of subsonic convergence and supersonic expansion, and improving the thrust response speed of the engine. Attached Figure Description

[0017] To more clearly illustrate the technical solution of the present invention, the accompanying drawings used in the description will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a first structural schematic diagram of a specific embodiment of the present invention.

[0019] Figure 2 This is a schematic diagram of the second structure according to a specific embodiment of the present invention.

[0020] Figure 3 This is a schematic diagram of the third structure of a specific embodiment of the present invention.

[0021] Figure 4 This is a schematic diagram of the structure of the adjustment piece 2 according to a specific embodiment of the present invention.

[0022] In the attached diagram: 1. Force-applying cylinder; 2. Elastic element; 3. Tie rod four; 4. Hydraulic actuator cylinder; 5. Crossbeam; 6. Rocker arm; 7. Limiter four; 8. Support arm; 9. Tie rod one; 10. Pneumatic actuator cylinder; 11. Adjusting plate one; 111. Connecting rod; 112. Roller; 12. Limiter one; 13. Adjusting plate two; 131. Guide groove; 14. Adjusting plate three; 15. Tie rod three; 16. Hinge housing; 17. Support ring. Detailed Implementation

[0023] To make the objectives, features, and advantages of this invention more apparent and understandable, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings of the specific embodiments. Obviously, the embodiments described below are only some embodiments of this invention, and not all embodiments. Based on the embodiments of this patent, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this patent.

[0024] like Figures 1-3 As shown, this invention discloses an engine nozzle retraction and extension control device, including a booster cylinder 1. A crossbeam 5 is installed at the rear of the booster cylinder 1. A hydraulic actuator cylinder 4, a rocker arm 6, and an adjusting plate 11 are hinged to the crossbeam 5. The bottom of the rocker arm 6 is hinged to the crossbeam 5, and the front end of the rocker arm 6 is hinged to the telescopic end of the hydraulic actuator cylinder 4. The rear end of the rocker arm 6 is hinged to the adjusting plate 11 via a pull rod 9. The front end of the adjusting plate 11 is hinged to the booster cylinder 1. The hydraulic actuator cylinder 4, rocker arm 6, and adjusting plate 11 are arranged in a ring on the crossbeam 5. The ring arrangement of the hydraulic actuator cylinder 4, rocker arm 6, and adjusting plate 11 ensures uniform circumferential force on the nozzle and avoids component deformation caused by local stress concentration.

[0025] It also includes an elastic element 2, the inner side of which is connected to a support ring 17. The support ring 17 is connected to the crossbeam 5 via a tie rod 4 3. The tail end of the elastic element 2 covers the front end of the adjusting plate 11. The elastic element 2 adopts a quantitative circumferential distribution design, which can evenly support the front end of the adjusting plate 11, avoid the surface distortion caused by local force concentration, optimize the transition surface between the fuselage and the nozzle, and reduce the vortex resistance caused by airflow separation. The hinge structure of the support ring 17 and the tie rod 4 3 can compensate for the assembly error between the force-adding cylinder 1 and the crossbeam 5, allow for a small radial displacement when the adjusting plate 11 is extended or retracted, and reduce the incidence of jamming failure. The design of the elastic element 2 covering the front end of the adjusting plate 11 further improves the aerodynamic smoothness of the rear body, improves the overall lift-to-drag ratio, and enhances the structural rigidity of the front end of the adjusting plate 11, extending its service life.

[0026] Adjusting plate one 11 has adjusting plate two 13 spaced apart on its inner side; adjusting plate two 13 has a guide groove 131 along its length on its outer side; adjusting plate one 11 has a connecting rod 111 on its inner side at its tail end; the inner bottom end of the connecting rod 111 has a roller 112 that can roll along the guide groove 131; adjusting plate two 13 can complete the opening and closing action through the connecting rod 111 with the roller 112 cooperating with the guide groove 131 of adjusting plate two 13, transforming traditional sliding friction into rolling friction, thereby reducing the coefficient of friction, significantly reducing motion resistance, and effectively avoiding the risk of jamming under high temperature conditions; the precise cooperation between the connecting rod 111 and the guide groove 131 ensures the stability of the opening and closing trajectory of adjusting plate two 13.

[0027] The guide groove 131 has a baffle at the top of at least one side wall, and the gap between the baffle and the bottom of the guide groove 131 is slightly larger than the diameter of the roller 112 and forms a space for the roller 112 to move; preferably, there are two rollers 112.

[0028] A support arm 8 is also provided between the rocker arm 6 and the pull rod 9. The front end of the bottom of the support arm 8 is hinged to the rear end of the rocker arm 6, and the rear end of the bottom of the support arm 8 is hinged to the pull rod 9. A limiter 7 is hinged between the top of the support arm 8 and the crossbeam 5. As an intermediate component for power transmission, the support arm 8 optimizes the force transmission path between the rocker arm 6 and the pull rod 9, reduces transmission gaps, and improves adjustment synchronization. The limiter 7 can precisely limit the movement stroke of the support arm 8, avoid component collision damage caused by excessive displacement, and at the same time enhance the structural rigidity of the support arm 8, reduce vibration deformation, further reduce the incidence of jamming failures, and make the nozzle retraction and extension actions more stable and reliable.

[0029] Two tie rods 9 are connected to one support arm 8, and the two tie rods 9 on two adjacent support arms 8 are hinged together to the adjusting plate 11. The design of the two tie rods 9 hinged together to the adjusting plate 11 makes the force distribution of the adjusting plate 11 more balanced, avoids the risk of breakage caused by overload of a single tie rod, and at the same time improves the synchronization of opening and closing of adjacent adjusting plates 11, prevents circumferential displacement, ensures the flatness of the nozzle profile, reduces aerodynamic drag loss caused by airflow disturbance, and improves the aerodynamic efficiency of the nozzle.

[0030] A pneumatic actuator 10 is hinged between two adjacent adjusting plates 11, and the pneumatic actuator 10 is hinged in the middle section of the adjusting plate 11. The pneumatic actuator 10 adopts a one-way action structure, which simplifies the internal sealing and reversing mechanism, effectively reduces the weight compared with the traditional two-way actuator, and reduces the number of failure points. The working air source is compressed air after high pressure compressor, which eliminates the need for additional high pressure air cylinders or air pumps, saving aircraft space while utilizing the existing energy flow of the engine, thus reducing fuel consumption. The design of the pair hinged in the middle section of the adjusting plate 11 can assist the hydraulic actuator 4 to achieve rapid response, shorten the adjustment response time, and at the same time ensure that the adjusting plate 11 opens and closes evenly in the circumference, avoiding jamming caused by uneven load.

[0031] A sealing plate is also provided on the inner side between two adjacent adjusting plates 11. The front end of the sealing plate 1 is movably mounted on the adjusting plate 11, and the rear end of the sealing plate 1 is connected to the adjacent adjusting plate 11 through a limiter 12. The limiter 12 can restrict the circumferential movement of the sealing plate 1. The sealing plate 1 can effectively prevent high-temperature gas from leaking from the gap of the adjusting plate 11. With the circumferential limiting function of the limiter 12, the sealing plate 1 is prevented from moving under the impact of high-speed airflow, and the sealing effect is significantly improved. The movable installation design is adapted to the opening and closing action of the adjusting plate 11, ensuring that the sealing plate 1 is always in contact with the inner surface of the adjusting plate 11, preventing the sealing gap from increasing, improving the internal aerodynamic efficiency of the nozzle, and reducing thrust loss.

[0032] A hinge housing 16 is installed at the tail of the afterburner 1. An adjustment plate 14 is provided between the hinge housing 16 and the adjustment plate 2 13. The front end of the adjustment plate 3 14 is hinged to the hinge housing 16. The front end of the bottom of the support arm 8 is hinged to the adjustment plate 3 14 via a tie rod 3 15. The adjustment plate 3 14 realizes the subsonic convergence function, which works in conjunction with the supersonic expansion function of the adjustment plate 2 13 to complete the nozzle cross-section adjustment under all operating conditions, adapting to different flight states from takeoff to supersonic cruise. The hinge housing 16 provides stable hinge support for the adjustment plate 3 14, reducing assembly errors. The tie rod 3 15 transmits the power of the support arm 8, ensuring that the adjustment plate 3 14 moves in coordination with the adjustment plate 1 11 and the adjustment plate 2 13, avoiding surface distortion caused by the lag of a single component's movement, and improving the overall aerodynamic performance of the nozzle.

[0033] Two tie rods 15 are connected to one support arm 8, and the two tie rods 15 on two adjacent support arms 8 are hinged together to the adjusting plate 14. The connection design of the double tie rods 15 enhances the connection rigidity between the support arm 8 and the adjusting plate 14, distributes the stress load, avoids fatigue damage caused by long-term stress on a single tie rod, and improves structural reliability. The tie rods 15 of two adjacent support arms 8 work together to further ensure the circumferential force balance of the adjusting plate 14, effectively improves the flatness of the nozzle profile when it opens and closes, reduces the aerodynamic drag of the rear body, and ensures that the adjusting plate 11 and the adjusting plate 14 move synchronously to avoid motion interference.

[0034] A sealing plate 3 is also provided between adjacent regulating plates 3 14. The front end of the sealing plate 3 is installed on the regulating plate 3 14 by a pin. The sealing plate 3 connects the regulating plate 3 14 and the sealing plate 2 to form a complete sealing link, which completely blocks the gas leakage channel. The pin enables the flexible installation of the sealing plate 3, which is adapted to the hinged rotation of the regulating plate 3 14. The hinged design of the tail end with the sealing plate 2 ensures the continuity of the sealing link, avoids sealing gaps caused by differences in component movement, improves airflow stability, reduces aerodynamic losses, and further optimizes engine fuel economy.

[0035] A second sealing plate is provided between adjacent regulating plates 13, and the second sealing plate is connected to the adjacent regulating plates 13 through a limiter 2. The second sealing plate and the first sealing plate form a double sealing structure, which fully covers the gap area between the first regulating plate 11 and the second regulating plate 13, further reducing the amount of gas leakage, improving the continuity of airflow inside the nozzle, and reducing eddy current losses; the limiter 2 can restrict the displacement of the second sealing plate, ensuring that it opens and closes synchronously with the second regulating plate 13, avoiding wrinkles or breakage of the second sealing plate, extending the service life of the sealing components, and ensuring sufficient airflow expansion in the supersonic range, thereby improving the supersonic thrust performance of the engine.

[0036] Among them, the tail end of the sealing sheet three is hinged to the sealing sheet two.

[0037] Among them, there are 16 adjusting plates, sealing plates, limiters and elastic elements 2, and 32 tie rods 9 and 15.

[0038] In summary, the working principle of this device is as follows: When it is necessary to reduce the nozzle area, the hydraulic actuator 4 retracts with the assistance of the pneumatic actuator 10; this drives the rocker arm 6 and the support arm 8 to move, and pulls all the adjusting plates 11 in a synchronized inward rotation through the pull rod 19; the adjusting plates 11, through the connecting rod 111 with rollers 112 and the guide groove 131, simultaneously drive the adjusting plate 2 13 to retract inward; the support arm 8 at the same time pulls the adjusting plate 3 14 inward through the pull rod 3 15.

[0039] Throughout the process, each sealing plate moves adaptively under the action of the limiter, maintaining a tight seal at all times; the elastic element 2 provides stable support and ensures a smooth leading edge profile. Ultimately, this achieves rapid, smooth, and precise convergence of the nozzle.

[0040] When it is necessary to increase the nozzle area, the above process is reversed, the hydraulic actuator 4 extends, and pushes the adjusting plate 11, adjusting plate 2 13, and adjusting plate 3 14 to open outwards simultaneously.

[0041] The engine nozzle retraction and expansion control device of this invention features a ring-shaped design of hydraulic actuator, rocker arm, and adjusting plate one, ensuring uniform force distribution around the nozzle and avoiding component deformation caused by localized stress concentration. Adjusting plate one, through a connecting rod with rollers, engages with the guide groove of adjusting plate two, transforming traditional sliding friction into rolling friction to reduce the friction coefficient, significantly reduce motion resistance, and effectively avoid the risk of jamming under high-temperature conditions. The precise cooperation between the connecting rod and the guide groove ensures stable opening and closing trajectory of adjusting plate two, adapting to the full-condition requirements of subsonic convergence and supersonic expansion, and improving the engine thrust response speed.

[0042] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An engine nozzle retraction and extension control device, comprising an afterburner cylinder (1), characterized in that, A crossbeam (5) is installed at the tail of the booster cylinder (1). A hydraulic actuator (4), a rocker arm (6), and an adjusting plate (11) are hinged on the crossbeam (5). The bottom of the rocker arm (6) is hinged to the crossbeam (5), and the front end of the rocker arm (6) is hinged to the telescopic end of the hydraulic actuator (4). The rear end of the rocker arm (6) is hinged to the adjusting plate (11) via a pull rod (9). The front end of the adjusting plate (11) is hinged to the booster cylinder (1). The hydraulic actuator (4) and the rocker arm (6) are also connected to the booster cylinder (1). Adjusting plate one (11) is distributed in a ring on the crossbeam (5); adjusting plate two (13) is provided at intervals on the inner side of the adjusting plate one (11); the outer side of the adjusting plate two (13) is provided with a guide groove (131) in the length direction; the inner side of the tail of the adjusting plate one (11) is provided with a connecting rod (111); the inner bottom end of the connecting rod (111) is provided with a roller (112) that can roll along the guide groove (131); the adjusting plate two (13) can be driven by the connecting rod (111) to complete the opening and closing action.

2. The engine nozzle retraction and expansion control device according to claim 1, characterized in that, A support arm (8) is provided between the rocker arm (6) and the first pull rod (9). The front end of the bottom of the support arm (8) is hinged to the rear end of the rocker arm (6), the rear end of the bottom of the support arm (8) is hinged to the first pull rod (9), and the top of the support arm (8) is hinged to the fourth limiter (7) between the crossbeam (5).

3. The engine nozzle retraction and expansion control device according to claim 2, characterized in that, Two tie rods (9) are connected to one arm (8), and the two tie rods (9) on two adjacent arms (8) are hinged together to the adjusting plate (11).

4. The engine nozzle retraction and expansion control device according to claim 3, characterized in that, A pneumatic actuator (10) is hinged between two adjacent adjusting plates (11), and the pneumatic actuator (10) is hinged in the middle section of the adjusting plate (11).

5. The engine nozzle retraction and expansion control device according to claim 4, characterized in that, A sealing plate is provided on the inner side between two adjacent adjusting plates (11). The front end of the sealing plate is movably mounted on the adjusting plate (11). The rear end of the sealing plate is connected to the adjacent adjusting plates (11) through a limiter (12). The limiter (12) can restrict the movement of the sealing plate in the circumferential direction.

6. An engine nozzle retraction and expansion control device according to any one of claims 2 to 5, characterized in that, A sealing plate 2 is provided between adjacent adjusting plates 2 (13), and the sealing plate 2 is connected to the adjacent adjusting plates 2 (13) through a limiter 2.

7. The engine nozzle retraction and expansion control device according to claim 6, characterized in that, The tail of the power-adding cylinder (1) is equipped with a hinge housing (16), and an adjustment plate three (14) is provided between the hinge housing (16) and the adjustment plate two (13). The front end of the adjustment plate three (14) is hinged to the hinge housing (16), and the front end of the bottom of the support arm (8) is hinged to the adjustment plate three (14) through the pull rod three (15).

8. The engine nozzle retraction and expansion control device according to claim 7, characterized in that, Two tie rods (15) are connected to one arm (8), and the two tie rods (15) on two adjacent arms (8) are hinged together to the adjusting plate (14).

9. The engine nozzle retraction and expansion control device according to claim 7, characterized in that, A sealing plate three is also provided between adjacent adjusting plate three (14). The front end of the sealing plate three is installed on the adjusting plate three (14) by a pin, and the tail end of the sealing plate three is hinged to the sealing plate two.

10. An engine nozzle retraction and expansion control device according to any one of claims 2 to 5, characterized in that, It also includes an elastic element (2), the inner side of the front end of the elastic element (2) is connected to a support ring (17), the support ring (17) is connected to the crossbeam (5) by a pull rod four (3), and the tail end of the elastic element (2) covers the front end of the adjustment piece one (11).

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