Pneumatic thrust vectoring nozzle with simplified structure and control method thereof

Abstract

The invention discloses a structure-simplified pneumatic thrust vectoring nozzle and a control method thereof, and the structure-simplified pneumatic thrust vectoring nozzle comprises a nozzle outer wall surface, a nozzle inlet and a nozzle outlet which are respectively positioned at two ends of the nozzle outer wall surface, and a bypass secondary flow inlet, a bypass valve, a front convergence section, a nozzle throat, a bypass secondary flow outlet and a self-adaptive bypass cavity which are positioned in the nozzle outer wall surface, the front convergent section is hinged to the outer wall face of the spray pipe through a front hinge, and the rear expansion section is hinged to the outer wall face of the spray pipe through a rear hinge. A space defined by the outer wall surface of the spray pipe, the front convergent section and the rear expansion section jointly forms a self-adaptive bypass cavity; the upstream of the bypass secondary flow inlet communicates with the outer wall surface of the spray pipe and the front convergent section, and the downstream communicates with the self-adaptive bypass cavity; the upstream of the bypass secondary flow outlet communicates with the self-adaptive bypass cavity, and the downstream communicates with the spray pipe throat and the rear expansion section. The self-adaptive bypass channel structure is simplified, the complexity of the structure is reduced, the weight is reduced, the thrust vector angle and the flow capacity are adjusted at the same time, and the aerodynamic performance is better.

Description

Technical Field

[0001] The invention belongs to the field of advanced aero-engine exhaust system design, and in particular relates to an aerodynamic thrust vector nozzle and a control method thereof. Background Art

[0002] The research on aerodynamic thrust vectoring nozzles is a hot research direction in the field of aviation propulsion technology. Compared with the complex adjustment mechanism of traditional mechanical vectoring nozzles, aerodynamic thrust vectoring nozzles have very obvious advantages. Among them, the throat-offset aerodynamic vectoring nozzle deflects the velocity cross section of the airflow at the throat by asymmetrically injecting secondary flow near the throat of the nozzle, thereby deflecting the mainstream and generating a stable thrust vector. With its fixed geometric configuration, simple mechanical structure, and excellent vectoring performance, it has become the research focus of various countries.

[0003] The current adaptive bypass aerodynamic thrust vectoring nozzle adjusts the thrust vectoring angle of the nozzle by controlling the opening of the bypass valve. However, most of its bypass channels have complex structures, heavy weight, fixed and non-adjustable geometry, and low reliability.

[0004] Therefore, the present invention provides a simplified aerodynamic thrust vector nozzle and a control method thereof, which condenses the typical flow characteristics of the adaptive bypass aerodynamic thrust vector nozzle, simplifies the bypass channel structure design, reduces structural complexity, reduces weight, and reduces costs, laying the foundation for subsequent applications. Summary of the invention

[0005] In order to overcome the deficiencies in the prior art, the purpose of the present invention is to provide a simplified aerodynamic thrust vector nozzle and a control method thereof, so as to reduce the weight caused by the complex bypass channel, achieve simultaneous adjustment of the thrust vector angle and flow capacity, and have better aerodynamic performance.

[0006] To achieve the above object, the present invention adopts the following technical solution:

[0007] A simplified aerodynamic thrust vector nozzle comprises a nozzle outer wall, a nozzle inlet and a nozzle outlet respectively located at two ends of the nozzle outer wall, a bypass secondary flow inlet located inside the nozzle outer wall, a bypass valve, a front convergent section, a nozzle throat, a bypass secondary flow outlet, and an adaptive bypass cavity, wherein:

[0008] The front convergent section is hinged to the outer wall of the nozzle through a front hinge, and the rear expansion section is hinged to the outer wall of the nozzle through a rear hinge; the space enclosed by the outer wall of the nozzle, the front convergent section, and the rear expansion section constitutes the adaptive bypass cavity;

[0009] The nozzle throat is located at the junction of the front convergent section and the rear divergent section;

[0010] The bypass secondary flow inlet is connected to the nozzle outer wall and the front convergent section upstream, and is connected to the adaptive bypass cavity downstream;

[0011] The bypass secondary flow outlet is connected to the adaptive bypass cavity upstream and to the nozzle throat and the rear expansion section downstream;

[0012] The bypass valve is arranged at the bypass secondary flow inlet and is used to control the flow rate of the secondary flow injected into the adaptive bypass cavity.

[0013] Furthermore, the shape of the outer wall of the nozzle is variable to change the shape of the adaptive bypass cavity.

[0014] Furthermore, the front convergent section can rotate around the front hinge, and the rear expansion section can rotate around the rear hinge to change the nozzle throat height H throat , to achieve the adjustment of the nozzle flow capacity.

[0015] Furthermore, the rotation angle α of the front convergent section satisfies 20°≤α≤40°, where α is the angle between the front convergent section and the outer wall of the nozzle; the rotation angle β of the rear expansion section satisfies 10°≤β≤20°, where β is the angle between the rear expansion section and the outer wall of the nozzle.

[0016] Furthermore, the upper and lower sides of the front convergent section can rotate symmetrically or asymmetrically. When the pressure drop ratio is 4, when only the upper and lower sides of the front convergent section rotate and the angle difference is greater than or equal to 3°, the absolute value of the thrust vector angle is not less than 5°.

[0017] Furthermore, the upper and lower sides of the rear expansion section can rotate asymmetrically. When the pressure drop ratio is 4, when only the upper and lower sides of the rear expansion section rotate and the angle difference is greater than or equal to 2°, the absolute value of the thrust vector angle is not less than 8°.

[0018] Furthermore, the nozzle throat height H throat Height H of nozzle inlet in The relationship between them satisfies 0.28≤H throat / H in ≤0.49.

[0019] Furthermore, the length of the front convergent section L1 and the nozzle inlet height H in The relationship between them satisfies 0.38≤L1 / H in ≤0.46.

[0020] Furthermore, the length L2 of the rear expansion section is related to the nozzle inlet height H in The relationship between them satisfies 0.84≤L2 / H in ≤0.92.

[0021] Furthermore, the height H of the bypass secondary flow channelbypass Height H of nozzle inlet in The relationship between them satisfies 0.05≤H bypass / H in ≤0.15.

[0022] Furthermore, the nozzle outlet height H out Height H of nozzle inlet in The relationship between them satisfies 0.65≤H out / H in ≤1.15.

[0023] Furthermore, the structure of the aerodynamic thrust vector nozzle is applicable to a Laval nozzle, a double-throat aerodynamic thrust vector nozzle or an axisymmetric fluid thrust vector nozzle.

[0024] A control method for the aerodynamic thrust vector nozzle comprises the following steps: the front convergent section can rotate around a front hinge, and the rear expansion section can rotate around a rear hinge, and the throat area is adjusted by combining the two to achieve the adjustment of the nozzle flow capacity.

[0025] Furthermore, in the non-vector state, the front convergent section and the rear divergent section are synchronously rotated to adjust the height H of the nozzle throat. throat , to achieve the adjustment of the nozzle flow capacity.

[0026] Furthermore, in the vector state, the bypass valve is actuated in conjunction with the front convergent section and the rear expansion section to achieve simultaneous adjustment of the thrust vector and the flow capacity.

[0027] Beneficial effects: The simplified aerodynamic thrust vector nozzle and control method thereof of the present invention have the following advantages over the prior art:

[0028] (1) In the present invention, the chamber formed by the front convergent section, the rear divergent section and the outer wall of the nozzle is used as the adaptive bypass channel, which greatly simplifies the structure of the adaptive bypass channel and has the advantages of easy processing, light weight, and good maintainability. A single adaptive bypass channel is expected to reduce weight by more than 50%.

[0029] (2) The present invention utilizes the rotation of the front convergent section and the rear divergent section to adjust the nozzle throat area and thus the flow capacity. Compared with the traditional fixed geometry structure, the present invention is expected to achieve a flow adjustment range of 80% to 120%. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a schematic diagram of the structure of an aerodynamic thrust vector nozzle in one embodiment of the present invention;

[0031] Figure 2A dimensioned diagram of an aerodynamic thrust vector nozzle and a control method thereof in one embodiment of the present invention;

[0032] Figure 3 It is a schematic structural diagram of a design scheme for a bypass type double-throat nozzle in one embodiment of the present invention;

[0033] Figure 4 This is the numerical simulation Mach number cloud diagram of the traditional bypass double-throat nozzle in the vector state;

[0034] Figure 5 A numerically simulated Mach number cloud diagram of a design scheme for a bypass double-throat nozzle under a vector state in one embodiment of the present invention;

[0035] Figure 6 A numerically simulated Mach number cloud diagram of a design scheme for a bypass double-throat nozzle under a non-vector state in one embodiment of the present invention;

[0036] Figure 7 A numerically simulated Mach number cloud diagram of an enlarged throat area under a non-vector state for a design of a bypass double-throat nozzle in one embodiment of the present invention;

[0037] Figure 8 A numerically simulated Mach number cloud diagram of the asymmetric inward rotation of the upper and lower front convergent sections of the bypass double-throat nozzle design in a vector state in one embodiment of the present invention;

[0038] In the figure:

[0039] 1. Nozzle inlet, 2. Nozzle outer wall, 3. Front hinge, 4. Bypass secondary flow inlet, 5. Bypass valve, 6. Front convergent section, 7. Nozzle throat, 8. Bypass secondary flow outlet, 9. Adaptive bypass cavity, 10. Rear expansion section, 11. Rear hinge, 12. Nozzle outlet. DETAILED DESCRIPTION

[0040] The present invention will be further explained below in conjunction with the accompanying drawings and embodiments.

[0041] like Figures 1 to 3 As shown, in one embodiment of the present invention, a simplified aerodynamic thrust vector nozzle includes a nozzle inlet 1, a nozzle outer wall 2, a front hinge 3, a bypass secondary flow inlet 4, a bypass valve 5, a front convergent section 6, a nozzle throat 7, a bypass secondary flow outlet 8, an adaptive bypass cavity 9, a rear expansion section 10, a rear hinge 11, and a nozzle outlet 12.

[0042] The nozzle inlet 1 and the nozzle outlet 12 are respectively located at two ends of the nozzle outer wall 2. The fluid flows from the nozzle inlet 1 to the nozzle outlet 12.

[0043] The bypass secondary flow inlet 4 , the bypass valve 5 , the front convergent section 6 , the nozzle throat 7 , the bypass secondary flow outlet 8 , and the adaptive bypass cavity 9 are located inside the nozzle outer wall 2 .

[0044] The front convergent section 6 is hinged to the nozzle outer wall 2 through the front hinge 3 , and the rear divergent section 10 is hinged to the nozzle outer wall 2 through the rear hinge 11 .

[0045] The space enclosed by the nozzle outer wall 2, the front convergent section 6, and the rear expansion section 10 together constitutes an adaptive bypass cavity 9. The adaptive bypass cavity 9 is used to receive the airflow from the bypass secondary flow inlet 4, and after passing through the adaptive bypass cavity 9, the airflow flows out from the bypass secondary flow outlet 8 to disturb the mainstream.

[0046] The nozzle throat 7 is located at the junction of the front convergent section 6 and the rear divergent section 10.

[0047] The bypass secondary flow inlet 4 is connected to the nozzle outer wall 2 and the front convergent section 6 upstream, and is connected to the adaptive bypass cavity 9 downstream.

[0048] The bypass secondary flow outlet 8 is connected to the adaptive bypass cavity 9 upstream, and is connected to the nozzle throat 7 and the rear expansion section 10 downstream.

[0049] The bypass valve 5 is arranged at the bypass secondary flow inlet 4 and is used to control the flow rate of the secondary flow injected into the adaptive bypass cavity 9 .

[0050] The front convergent section 6 can rotate around the front hinge 3, and the rear divergent section 10 can rotate around the rear hinge 11 to change the height H of the nozzle throat 7. throat , to achieve the adjustment of the nozzle flow capacity.

[0051] In one embodiment of the present invention, the shape of the nozzle outer wall 2 is changeable, thereby changing the shape of the adaptive bypass cavity.

[0052] In one embodiment of the present invention, the rotation angle α of the front convergent section 6 satisfies 20°≤α≤40°, where α is the angle between the front convergent section 6 and the outer wall surface 2 of the nozzle; the rotation angle β of the rear expansion section 10 satisfies 10°≤β≤20°, where β is the angle between the rear expansion section 10 and the outer wall surface 2 of the nozzle, such as Figure 2 shown.

[0053] In one embodiment of the present invention, the nozzle throat 7 has a height H throat Height H from nozzle inlet in The relationship between them satisfies 0.28≤H throat / H in ≤0.49.

[0054] In one embodiment of the present invention, the length L1 of the front convergent section 6 is equal to the height H of the nozzle inlet 1. in The relationship between them satisfies 0.38≤L1 / Hin ≤0.46.

[0055] In one embodiment of the present invention, the length L2 of the rear expansion section 10 is equal to the height H of the nozzle inlet 1. in The relationship between them satisfies 0.84≤L2 / H in ≤0.92.

[0056] In one embodiment of the present invention, the height H of the bypass secondary flow channel 8 is bypass Height H from nozzle inlet in The relationship between them satisfies 0.05≤H bypass / H in ≤0.15;

[0057] In one embodiment of the present invention, the nozzle outlet 12 has a height H out Height H from nozzle inlet in The relationship between them satisfies 0.65≤H out / H in ≤1.15.

[0058] In one embodiment of the present invention, a control method for an aerodynamic thrust vector nozzle includes the following steps: the front convergent section 6 can rotate around the front hinge 3, and the rear expansion section 10 can rotate around the rear hinge 11, and the throat area is adjusted by combining the two to achieve the adjustment of the nozzle flow capacity.

[0059] In one embodiment of the present invention, in the non-vector state, the front convergent section 6 and the rear divergent section 10 are synchronously rotated to adjust the height H of the nozzle throat 7. throat , to achieve the adjustment of the nozzle flow capacity.

[0060] In one embodiment of the present invention, in the vector state, the bypass valve 5 is actuated in conjunction with the front convergent section 6 and the rear expansion section 10 to achieve simultaneous regulation of the thrust vector and the flow capacity.

[0061] The simplified aerodynamic thrust vector nozzle of the present invention uses the space formed by the nozzle outer wall, the front convergent section, and the rear expansion section as an adaptive bypass, replacing the original complex bypass pipe structure. Compared with the replaced bypass pipe structure, the solution of using the three existing inner flow channel profiles of the nozzle as the adaptive bypass reduces the number of parts, reduces the weight of the nozzle, and reduces the complexity of the nozzle.

[0062] Compared with the original solution of fixed wall, the present invention solves the problem that the flow rate cannot be adjusted. The front convergent section 6 can rotate around the front hinge 3 located at the front side thereof, and the rear expansion section 10 can rotate around the rear hinge 11 located at the rear side thereof. The two are combined to adjust the throat area and realize the adjustment of the nozzle flow capacity. Preferably, the upper and lower sides of the front convergent section 6 can rotate symmetrically or asymmetrically, and the upper and lower sides of the rear expansion section 10 can rotate symmetrically or asymmetrically to realize the adjustment of the flow capacity and the thrust vector at the same time. In one embodiment of the present invention, the upper and lower sides of the front convergent section 6 can rotate symmetrically or asymmetrically. When the pressure drop ratio is 4, when only the upper and lower sides of the front convergent section 6 rotate and the angle difference is greater than or equal to 3°, the absolute value of the thrust vector angle is not less than 5°. The upper and lower sides of the rear expansion section 10 can rotate asymmetrically. When the pressure drop ratio is 4, when only the upper and lower sides of the rear expansion section 10 rotate and the angle difference is greater than or equal to 2°, the absolute value of the thrust vector angle is not less than 8°.

[0063] When the bypass valve of the nozzle is opened, the secondary flow passes through the bypass channel and merges with the main flow at the nozzle throat. Generally speaking, although the geometric throat area does not change, the injection of the secondary flow will reduce the effective aerodynamic throat area, that is, reduce the flow capacity of the nozzle. The present invention adjusts the geometric throat area by actuating the front convergent section and the rear expansion section to compensate for the flow capacity loss caused by the opening vector. It can also meet the needs of the aircraft for flow regulation during afterburning.

[0064] The structure of the aerodynamic thrust vector nozzle of the present invention is applicable to a Laval nozzle, a double-throat aerodynamic thrust vector nozzle or an axisymmetric fluid thrust vector nozzle.

[0065] The present invention can be better understood with reference to the following examples.

[0066] Embodiment 1:

[0067] Design scheme for bypass double-throat nozzle.

[0068] In this embodiment, the structure of the bypass double-throat nozzle is as follows: it includes a nozzle outer wall surface 2, a nozzle inlet 1 and a nozzle outlet 12 respectively located at both ends of the nozzle outer wall surface 2, and a bypass secondary flow inlet 4, a bypass valve 5, a front convergent section 6, a nozzle throat 7, a bypass secondary flow outlet 8, and an adaptive bypass cavity 9 located in the nozzle outer wall surface 2, wherein: the front convergent section 6 is hinged to the nozzle outer wall surface 2 through a front hinge 3, and the rear expansion section 10 is hinged to the nozzle outer wall surface 2 through a rear hinge 11; the nozzle outer wall surface 2, The space enclosed by the front convergent section 6 and the rear expansion section 10 constitutes an adaptive bypass cavity 9; the nozzle throat 7 is located at the junction of the front convergent section 6 and the rear expansion section 10; the bypass secondary flow inlet 4 is connected to the nozzle outer wall 2 and the front convergent section 6 upstream, and is connected to the adaptive bypass cavity 9 downstream; the bypass secondary flow outlet 8 is connected to the adaptive bypass cavity 9 upstream, and is connected to the nozzle throat 7 and the rear expansion section 10 downstream; the bypass valve 5 is arranged at the bypass secondary flow inlet 4, and is used to control the flow rate of the secondary flow injected into the adaptive bypass cavity 9.

[0069] The front convergent section 6 can rotate around the front hinge 3, and the rear divergent section 10 can rotate around the rear hinge 11 to change the height H of the nozzle throat 7. throat , to achieve the adjustment of the nozzle flow capacity.

[0070] Figure 3 What is shown is a schematic diagram of the structure of the design scheme for the bypass double-throat nozzle of the present invention; Figure 4 This is the numerical simulation Mach number cloud diagram of the traditional bypass double-throat nozzle in the vector state; Figure 5 This is a numerical simulation of the Mach number cloud diagram under the vector state of the design scheme of the bypass double-throat nozzle of the present invention. Through the design of the present invention, when the design pressure drop ratio is 4, according to the simulation calculation results, the thrust vector angle of the configuration of the present invention is about 50% larger than the thrust vector angle of the traditional configuration, showing the technical advantages of the present invention.

[0071] Figure 6 The numerical simulation Mach number cloud diagram of the design scheme of the bypass double-throat nozzle of the present invention under non-vector state is shown; Figure 7 The numerical simulation Mach number cloud diagram of the front convergent sections on the upper and lower sides and the rear expansion sections on the upper and lower sides rotating symmetrically inwards in the non-vector state of the design scheme of the bypass double-throat nozzle of the present invention. Through the design of the present invention, the geometric throat area can be enlarged by changing the inner flow channel profile. When the design pressure drop ratio is 4, according to the simulation calculation results, the flow coefficient of the configuration of the present invention is about 4% larger than the flow coefficient of the traditional configuration, showing the technical advantages of the present invention.

[0072] Figure 8The numerical simulation Mach number cloud diagram of the asymmetric inward rotation of the upper and lower front convergent sections under the vector state of the design scheme of the bypass double-throat nozzle of the present invention is shown. Through the design of the present invention, when the design pressure drop ratio is 4, according to the simulation results, when the opening of the upper and lower bypass valves is the same, the thrust vector angle of about 10° can be achieved by changing the inner flow channel profile through the rotation of the front convergent section, showing the technical advantages of the present invention.

[0073] Example 2

[0074] Application example of the adaptive bypass cavity of the present invention in Laval nozzle

[0075] Based on the traditional Laval nozzle, the adaptive bypass cavity design of the present invention is adopted.

[0076] Example 3

[0077] Application example of the adaptive bypass cavity of the present invention in an axisymmetric fluid thrust vector nozzle

[0078] Based on the traditional axisymmetric fluid thrust vector nozzle, the adaptive bypass cavity design of the present invention is adopted.

[0079] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A simplified aerodynamic thrust vector nozzle, characterized in that: The nozzle comprises a nozzle outer wall (2), a nozzle inlet (1) and a nozzle outlet (12) respectively located at two ends of the nozzle outer wall (2), and a bypass secondary flow inlet (4) located inside the nozzle outer wall (2), a bypass valve (5), a front convergent section (6), a nozzle throat (7), a bypass secondary flow outlet (8), and an adaptive bypass cavity (9), wherein: The front convergent section (6) is hinged to the nozzle outer wall (2) via a front hinge (3), and the rear expansion section (10) is hinged to the nozzle outer wall (2) via a rear hinge (11); the space enclosed by the nozzle outer wall (2), the front convergent section (6), and the rear expansion section (10) together constitutes the adaptive bypass cavity (9); The nozzle throat (7) is located at the junction of the front convergent section (6) and the rear divergent section (10); The bypass secondary flow inlet (4) is connected to the nozzle outer wall (2) and the front convergent section (6) upstream, and is connected to the adaptive bypass cavity (9) downstream; The bypass secondary flow outlet (8) is connected to the adaptive bypass cavity (9) upstream and is connected to the nozzle throat (7) and the rear expansion section (10) downstream; The bypass valve (5) is arranged at the bypass secondary flow inlet (4) and is used to control the flow rate of the secondary flow injected into the adaptive bypass chamber (9).

2. The simplified aerodynamic thrust vector nozzle according to claim 1, characterized in that: The shape of the nozzle outer wall surface (2) is changeable so as to change the shape of the adaptive bypass cavity.

3. The simplified aerodynamic thrust vector nozzle according to claim 1, characterized in that: The front convergent section (6) can rotate around the front hinge (3), and the rear expansion section (10) can rotate around the rear hinge (11) to change the height H of the nozzle throat (7). throat , to achieve the adjustment of the nozzle flow capacity.

4. The simplified aerodynamic thrust vector nozzle according to claim 3, characterized in that: The rotation angle α of the front convergent section (6) satisfies 20°≤α≤40°, wherein α is the angle between the front convergent section (6) and the outer wall surface (2) of the nozzle; the rotation angle β of the rear expansion section (10) satisfies 10°≤β≤20°, wherein β is the angle between the rear expansion section (10) and the outer wall surface (2) of the nozzle.

5. A simplified aerodynamic thrust vector nozzle according to claim 3 or 4, characterized in that: The upper and lower sides of the front convergent section (6) can rotate symmetrically or asymmetrically. When the pressure drop ratio is 4, when only the upper and lower sides of the front convergent section (6) rotate and the angle difference is greater than or equal to 3°, the absolute value of the thrust vector angle is not less than 5°; The upper and lower sides of the rear expansion section (10) can rotate asymmetrically. When the pressure drop ratio is 4, when only the upper and lower sides of the rear expansion section (10) rotate and the angle difference is greater than or equal to 2°, the absolute value of the thrust vector angle is not less than 8°.

6. The simplified aerodynamic thrust vector nozzle according to claim 1, characterized in that: The nozzle throat (7) has a height H throat Height H to nozzle inlet (1) in The relationship between them satisfies 0.28≤H throat / H in ≤0.49; The length L1 of the front convergent section (6) and the height H of the nozzle inlet (1) in The relationship between them satisfies 0.38≤L1 / H in ≤0.46; The length L2 of the rear expansion section (10) and the height H of the nozzle inlet (1) in The relationship between them satisfies 0.84≤L2 / H in ≤0.92; The height H of the bypass secondary flow channel (8) bypass Height H to nozzle inlet (1) in The relationship between them satisfies 0.05≤H bypass / H in ≤0.15; The nozzle outlet (12) has a height H out Height H to nozzle inlet (1) in The relationship between them satisfies 0.65≤H out / H in ≤1.

15.

7. The simplified aerodynamic thrust vector nozzle according to claim 1, characterized in that: The structure of the aerodynamic thrust vector nozzle is applicable to a Laval nozzle, a double-throat aerodynamic thrust vector nozzle or an axisymmetric fluid thrust vector nozzle.

8. A method for controlling an aerodynamic thrust vector nozzle as claimed in claim 1, characterized in that: The following steps are involved: The front convergent section (6) can rotate around the front hinge (3), and the rear expansion section (10) can rotate around the rear hinge (11). The throat area can be adjusted by combining the two to achieve the adjustment of the nozzle flow capacity.

9. The control method according to claim 8, characterized in that: In the non-vector state, the front convergent section (6) and the rear divergent section (10) are rotated synchronously to adjust the height H of the nozzle throat (7) throat , to achieve the adjustment of the nozzle flow capacity.

10. The control method according to claim 8, characterized in that: In the vector state, the bypass valve (5) is actuated in conjunction with the front convergent section (6) and the rear expansion section (10) to achieve simultaneous adjustment of the thrust vector and the flow capacity.

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