An equivalent analysis method and system for aerodynamic loads of adjustable nozzle flaps

Abstract

The present invention relates to the technical field of adjustable nozzle design, and discloses a method and system for equivalent analysis of aerodynamic loads of adjustable nozzle flaps. By constructing a three-dimensional structure model of the adjustable nozzle, dividing the inlet section and the throat section of the adjustable nozzle, and analyzing the engine outlet and the throat section of the adjustable nozzle, the proportional amplification coefficient of the flap is obtained. Then, the proportional amplification coefficient is used to equivalent the initial aerodynamic load of the flap, and the equivalent value of the wall aerodynamic load on the flap is obtained. The equivalent value of the aerodynamic load includes the load transmitted by the seal flap, and there is no need to consider the load of the seal flap during the aerodynamic analysis of the adjustable nozzle, which solves the non-linear problem of line-surface contact between the fish scales (seal flap and flap) during dynamic analysis, and greatly improves the convergence of the calculation model.

Description

Technical Field

[0001] The present invention relates to the technical field of adjustable nozzle design, and discloses a method and system for equivalent analysis of aerodynamic loads on adjustable nozzle flaps. Background Art

[0002] The main function of the jet engine tail nozzle is to expand the combustion gas and accelerate its ejection, thereby generating a forward acting force. The adjustable nozzle is a common device for turbo engines with an afterburner. The nozzle consists of overlapping flaps and seals to form a circular outlet cross-section. Under different flight conditions, by adjusting the nozzle throat area and outlet area, the engine can obtain high performance within a wide operating range.

[0003] As a key component of modern advanced aero-engines, the working reliability of the adjustable nozzle directly affects the maneuverability and safety of the aircraft. Conducting load analysis on the adjustable nozzle motion mechanism is a prerequisite for ensuring the reliable operation of the adjustable nozzle. Currently, there are two difficulties in conducting load analysis and dynamic simulation on adjustable nozzles: First, since the adjustable nozzle is a relatively complex mechanical component, its model needs to be simplified to "remove the rough and retain the fine" so that the simplified calculation model can obtain the load calculation results of the main components; Second, the aerodynamic loads on the inner wall surface of the adjustable nozzle flaps vary under different working conditions. How to accurately simulate the aerodynamic loads is the key to ensuring the accuracy of the load calculation of the motion mechanism. Summary of the Invention

[0004] The purpose of the present invention is to provide a method and system for equivalent analysis of aerodynamic loads on adjustable nozzle flaps, which can solve the non-linear line-surface contact problem between the fish scales (seals and flaps) during the dynamic analysis of adjustable nozzles, and greatly improve the convergence of the calculation model.

[0005] In order to achieve the above technical effects, the technical solution adopted by the present invention is:

[0006] A method for equivalent analysis of aerodynamic loads on adjustable nozzle flaps, comprising:

[0007] Constructing a three-dimensional structure model of the adjustable nozzle, the three-dimensional structure model of the adjustable nozzle includes flaps arranged at the engine outlet, the number of the flaps is multiple, and the multiple flaps are evenly distributed along the circumferential direction of the engine outlet; each flap is movably installed through an actuator, and a seal is further arranged between two adjacent flaps to form an adjustable nozzle of the engine;

[0008] Establish the first circumscribed regular polygon of the circular cross-section at the inlet of the adjustable nozzle, where the number of sides of the first circumscribed regular polygon is equal to the number of regulating vanes; establish the second circumscribed regular polygon of the circular cross-section at the throat of the adjustable nozzle, where the number of sides of the second circumscribed regular polygon is equal to the number of regulating vanes, and the sides of the second circumscribed regular polygon are parallel to the corresponding sides of the first circumscribed regular polygon;

[0009] Connect the corresponding corner points of the first circumscribed regular polygon and the second circumscribed regular polygon to form a frustum structure; according to the number of initial aerodynamic loads of the regulating vanes under the calculated working conditions , divide the frustum structure axially along the engine by a certain proportion into regular polygon analysis cross-sections;

[0010] Calculate the side length of each regular polygon analysis cross-section according to the side length of the first circumscribed regular polygon at the inlet cross-section and the side length of the second circumscribed regular polygon at the throat cross-section; analyze and obtain the width of the regulating vane at each regular polygon analysis cross-section according to the initial width of the regulating vane at the inlet cross-section and the initial width of the regulating vane at the throat cross-section;

[0011] Compare the side length of each regular polygon analysis cross-section with the width of the regulating vane at the corresponding position to obtain the proportional amplification factor of the regulating vane , and use the proportional amplification factor to conduct an equivalent analysis of the initial aerodynamic load of the regulating vane to obtain the equivalent value of the wall aerodynamic load on the regulating vane , which is the initial aerodynamic load under the corresponding working conditions calculated according to the flow field.

[0012] Furthermore, the side length of the first circumscribed regular polygon , where is the radius of the circular cross-section at the inlet of the adjustable nozzle, and

[0013] is the central angle of the first circumscribed regular polygon.

[0013] Furthermore, the side length of the second circumscribed regular polygon , where is the radius of the circular cross-section at the throat of the adjustable nozzle.

[0014] Furthermore, the side length of the th regular polygon analysis cross-section , where , is the side length of the first circumscribed regular polygon, is the side length of the second circumscribed regular polygon; the width of the regulating vane at the th regular polygon analysis cross-section , is the initial width of the regulating vane at the inlet cross-section, is the initial width of the regulating vane at the throat cross-section.

[0015] To achieve the above technical effects, the present invention also provides an equivalent analysis system for the aerodynamic load of an adjustable nozzle regulating vane, which is used to implement the equivalent analysis method for the aerodynamic load of the adjustable nozzle regulating vane, and includes:

[0016] A model construction module, which is used to construct a three-dimensional structure model of an adjustable nozzle. The three-dimensional structure model of the adjustable nozzle includes regulating vanes arranged at the engine outlet. The number of the regulating vanes is multiple, and the multiple regulating vanes are evenly distributed circumferentially along the engine outlet; each regulating vane is movably installed through an actuator, and a sealing vane is also arranged between two adjacent regulating vanes to form an adjustable nozzle of the engine;

[0017] An inlet and outlet cross-section processing module, which is used to establish a first circumscribed regular polygon of the inlet circular cross-section of the adjustable nozzle. The number of sides of the first circumscribed regular polygon is equal to the number of regulating vanes; a second circumscribed regular polygon of the throat circular cross-section of the adjustable nozzle is established. The number of sides of the second circumscribed regular polygon is equal to the number of the regulating vanes, and the sides of the second circumscribed regular polygon are parallel to the corresponding sides of the first circumscribed regular polygon;

[0018] A cross-section division module, which is used to connect the corresponding corner points of the first circumscribed regular polygon and the second circumscribed regular polygon to form a frustum structure; according to the number of the initial aerodynamic loads of the regulating vanes under the calculation conditions , the frustum structure is proportionally divided along the engine axis into regular polygon analysis cross-sections;

[0019] A parameter calculation module, which is used to calculate the side length of each regular polygon analysis cross-section according to the side length of the first circumscribed regular polygon of the inlet cross-section and the side length of the second circumscribed regular polygon of the throat cross-section; according to the initial width of the regulating vane at the inlet cross-section and the initial width of the regulating vane at the throat cross-section, analyze and obtain the width of the regulating vane at each regular polygon analysis cross-section;

[0020] An aerodynamic load equivalent module, which is used to compare the side length of each regular polygon analysis cross-section with the width of the regulating vane at the corresponding position to obtain the proportional amplification coefficient of the regulating vane, and use the proportional amplification coefficient to conduct an equivalent analysis of the initial aerodynamic load of the regulating vane to obtain the equivalent value of the wall surface aerodynamic load on the regulating vane , is the initial aerodynamic load under the corresponding working conditions calculated according to the flow field.

[0021] Further, in the parameter calculation module, the side length of the first circumscribed regular polygon, where is the radius of the circular cross-section at the inlet of the adjustable nozzle, is the central angle of the first circumscribed regular polygon.

[0022] Furthermore, in the parameter calculation module, the side length of the second circumscribed regular polygon , where is the radius of the circular cross-section of the throat of the adjustable nozzle. Furthermore, in the parameter calculation module, the side length of the th regular polygon analysis cross-section , where , is the side length of the first circumscribed regular polygon, is the side length of the second circumscribed regular polygon; the width of the adjusting vane at the th regular polygon analysis cross-section , is the initial width of the adjusting vane at the inlet cross-section, is the initial width of the adjusting vane at the throat cross-section.

[0023] Compared with the prior art, the beneficial effects of the present invention are as follows: By constructing a three-dimensional structural model of the adjustable nozzle, dividing the inlet cross-section and the throat cross-section of the adjustable nozzle, analyzing the engine outlet and the throat cross-section of the adjustable nozzle, the proportional amplification coefficient of the adjusting vane is obtained, and then the initial aerodynamic load of the adjusting vane is equivalent using the proportional amplification coefficient to obtain the equivalent value of the wall aerodynamic load on the adjusting vane; this equivalent aerodynamic load value includes the load transmitted by the sealing vane, and there is no need to consider the load of the sealing vane during the aerodynamic analysis of the adjustable nozzle, solving the non-linear problem of line-surface contact between the fish scales (sealing vane and adjusting vane) during the dynamic analysis, and greatly improving the convergence of the calculation model. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is the flow chart of the method for equivalent analysis of the aerodynamic load of the adjusting vane of the adjustable nozzle in Embodiment 1 or 2;

[0025] Figure 2 is the schematic diagram of the force analysis of the adjusting vane and the sealing vane of the adjustable nozzle in Embodiment 1 or 2;

[0026] Figure 3 is the schematic diagram of the regular polygon structure of the inlet cross-section and the throat cross-section of the adjustable nozzle constructed in Embodiment 1 or 2;

[0027] Figure 4 is the installation schematic diagram of the adjusting vane, the actuator and the sealing vane in Embodiment 1 or 2;

[0028] Figure 5 is the structural block diagram of the system for equivalent analysis of the aerodynamic load of the adjusting vane of the adjustable nozzle in Embodiment 1;

[0029] Among them, 1. Adjusting piece; 2. Sealing piece; 3. Limiting hook; 4. Support mechanism; 5. Roller; 6. Actuating cylinder; 7. Model construction module; 8. Import and export section processing module; 9. Section division module; 10. Parameter calculation module; 11. Aerodynamic load equivalent module. Specific implementation mode

[0030] The present invention will be further described in detail below in conjunction with embodiments and the accompanying drawings. However, this should not be construed as limiting the scope of the above-mentioned subject matter of the present invention to the following embodiments. Any technology implemented based on the content of the present invention belongs to the scope of the present invention.

[0031] Embodiment 1

[0032] See Figures 1 - 5 , a method for equivalent analysis of aerodynamic loads of an adjustable nozzle adjusting piece, including:

[0033] Construct a three-dimensional structure model of an adjustable nozzle. The three-dimensional structure model of the adjustable nozzle includes an adjusting piece 1 arranged at the engine outlet. The number of the adjusting pieces 1 is multiple, and the multiple adjusting pieces 1 are evenly distributed circumferentially along the engine outlet; each adjusting piece 1 is movably installed through an actuating cylinder 6, and a sealing piece 2 is further arranged between two adjacent adjusting pieces 1 for forming an adjustable nozzle of the engine;

[0034] Establish a first circumscribed regular polygon of the inlet circular section of the adjustable nozzle. The number of sides of the first circumscribed regular polygon is equal to the number of the adjusting pieces 1; establish a second circumscribed regular polygon of the throat circular section of the adjustable nozzle. The number of sides of the second circumscribed regular polygon is equal to the number of the adjusting pieces 1, and the sides of the second circumscribed regular polygon are parallel to the corresponding sides of the first circumscribed regular polygon;

[0035] Connect the corresponding corner points of the first circumscribed regular polygon and the second circumscribed regular polygon to form a frustum structure; according to the number of initial aerodynamic loads of the adjusting piece 1 under the calculation working condition , divide the frustum structure into regular polygon analysis sections in proportion along the engine axis;

[0036] Calculate the side length of each regular polygon analysis section according to the side length of the first circumscribed regular polygon of the inlet section and the side length of the second circumscribed regular polygon of the throat section; according to the initial width of the adjusting piece 1 at the inlet section and the initial width of the adjusting piece 1 at the throat section, analyze and obtain the width of the adjusting piece 1 at each regular polygon analysis section;

[0037] Compare the side length of each regular polygon analysis section with the width of the adjusting piece 1 at the corresponding position to obtain the proportional magnification coefficient , the initial aerodynamic load of the regulating vane 1 is equivalently analyzed using a scale factor to obtain the equivalent value of the wall aerodynamic load on the regulating vane 1. , is the initial aerodynamic load under the corresponding working conditions calculated according to the flow field.

[0038] In this embodiment, the adjustable nozzle is a fish-scale structure composed of a sealing vane 2 and a regulating vane 1. By the elongation or shortening of the hydraulic actuator 6, the roller 5 is driven to move on the profile of the support mechanism 4, and then the regulating vane 1 is driven to rotate around the hinge point c (the hinge points a and b will also rotate adaptively). The regulating vane 1 drives the sealing vane 2 to rotate around the hinge point through the limit hook 3 to achieve the adjustment of the nozzle throat area; among them, the aerodynamic load borne by the nozzle is transmitted to the nozzle actuator mechanism through the fish-scale structure. By analyzing the engine outlet and the throat section of the adjustable nozzle, the scale factor of the regulating vane 1 is obtained, and then the scale factor is used to equivalently analyze the initial aerodynamic load of the regulating vane 1 to obtain the equivalent value of the wall aerodynamic load on the regulating vane 1; this equivalent aerodynamic load value includes the load transmitted by the sealing vane 2, and there is no need to consider the load of the sealing vane 2 when performing the aerodynamic analysis of the adjustable nozzle, solving the non-linear problem of line-plane contact between the fish-scale sealing vane 2 and the regulating vane 1 during the dynamic analysis, and greatly improving the convergence of the calculation model.

[0039] Based on the same inventive concept, this embodiment also provides a system for equivalently analyzing the aerodynamic load of an adjustable nozzle regulating vane, including:

[0040] A model construction module 7 for constructing a three-dimensional structure model of the adjustable nozzle. The three-dimensional structure model of the adjustable nozzle includes a regulating vane 1 provided at the engine outlet. The number of the regulating vanes 1 is multiple, and the multiple regulating vanes 1 are evenly distributed circumferentially along the engine outlet; each regulating vane 1 is movably installed through an actuator 6, and a sealing vane 2 is further provided between two adjacent regulating vanes 1 for forming the adjustable nozzle of the engine.

[0041] An inlet and outlet section processing module 8 for establishing a first circumscribed regular polygon of the inlet circular section of the adjustable nozzle. The number of sides of the first circumscribed regular polygon is equal to the number of the regulating vanes 1; establishing a second circumscribed regular polygon of the throat circular section of the adjustable nozzle. The number of sides of the second circumscribed regular polygon is equal to the number of the regulating vanes 1, and the sides of the second circumscribed regular polygon are parallel to the corresponding sides of the first circumscribed regular polygon.

[0042] A section division module 9 for connecting the corresponding corner points of the first circumscribed regular polygon and the second circumscribed regular polygon to form a frustum structure; according to the number of the initial aerodynamic loads of the regulating vane 1 under the calculation working conditions , the frustum structure is proportionally divided along the engine axis into regular polygon analysis sections.

[0043] The parameter calculation module 10 is configured to calculate the side length of each regular polygon analysis section based on the side length of the first circumscribed regular polygon of the inlet section and the side length of the second circumscribed regular polygon of the throat section; analyze and obtain the width of the adjusting piece 1 at each regular polygon analysis section based on the initial width of the adjusting piece 1 at the inlet section and the initial width of the adjusting piece 1 at the throat section.

[0044] The aerodynamic load equivalent module 11 is configured to compare the side length of each regular polygon analysis section with the width of the adjusting piece 1 at the corresponding position to obtain the proportional amplification factor of the adjusting piece 1, and perform equivalent analysis on the initial aerodynamic load of the adjusting piece 1 using the proportional amplification factor to obtain the equivalent value of the wall aerodynamic load on the adjusting piece 1 , where is the initial aerodynamic load under the corresponding working condition calculated according to the flow field.

[0045] Embodiment 2

[0046] Refer to Figures 1 - 4 , a method for equivalent analysis of the aerodynamic load of an adjustable nozzle adjusting piece, including:

[0047] Step 1: Construct a three-dimensional structure model of the adjustable nozzle. The three-dimensional structure model of the adjustable nozzle includes an adjusting piece 1 arranged at the engine outlet. The number of the adjusting pieces 1 is multiple, and the multiple adjusting pieces 1 are evenly distributed along the circumferential direction of the engine outlet; each adjusting piece 1 is movably installed through an actuating cylinder 6, and a sealing piece 2 is further arranged between two adjacent adjusting pieces 1 to form an adjustable nozzle of the engine.

[0048] Step 2: Establish a first circumscribed regular polygon of the inlet circular section of the adjustable nozzle. The number of sides of the first circumscribed regular polygon is equal to the number of the adjusting pieces 1; establish a second circumscribed regular polygon of the throat circular section of the adjustable nozzle. The number of sides of the second circumscribed regular polygon is equal to the number of the adjusting pieces 1, and the sides of the second circumscribed regular polygon are parallel to the corresponding sides of the first circumscribed regular polygon.

[0049] In this embodiment, the side length of the first circumscribed regular polygon , where is the radius of the inlet circular section of the adjustable nozzle, and is the central angle of the first circumscribed regular polygon. The side length of the second circumscribed regular polygon , where is the radius of the throat circular section of the adjustable nozzle.

[0050] Step 3: Connect the corresponding corner points of the first circumscribed regular polygon and the second circumscribed regular polygon to form a frustum structure; according to the number of initial aerodynamic loads of the adjusting vane 1 under the calculation working condition , divide the frustum structure into regular polygon analysis sections proportionally along the axial direction of the engine;

[0051] Step 4: Calculate the side length of each regular polygon analysis section according to the side length of the first circumscribed regular polygon at the inlet section and the side length of the second circumscribed regular polygon at the throat section; according to the initial width of the adjusting vane 1 at the inlet section and the initial width of the adjusting vane 1 at the throat section, analyze and obtain the width of the adjusting vane 1 at each regular polygon analysis section;

[0052] Step 5: Compare the side length of each regular polygon analysis section with the width of the adjusting vane 1 at the corresponding position to obtain the proportional amplification factor of the adjusting vane 1 , and use the proportional amplification factor to conduct an equivalent analysis of the initial aerodynamic load of the adjusting vane 1 to obtain the equivalent value of the wall aerodynamic load on the adjusting vane 1 , where [[ID=]] is the initial aerodynamic load under the corresponding working condition calculated according to the flow field.

[0053] In this embodiment, the side length of the th regular polygon analysis section , where , is the side length of the first circumscribed regular polygon, is the side length of the second circumscribed regular polygon; the width of the adjusting vane 1 at the th regular polygon analysis section , is the initial width of the adjusting vane 1 at the inlet section, is the initial width of the adjusting vane 1 at the throat section.

[0054] The equivalent aerodynamic load can be used for parametric analysis of the dynamics, strength calculation, and life assessment of the adjustable nozzle motion mechanism, etc.

[0055] The above are only the preferred embodiments of the present invention, and are not intended to limit the present invention. Any modifications, equivalent replacements, and improvements made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An equivalent analysis method for aerodynamic loads of adjustable nozzle adjustment plates, characterized in that: include: Constructing a three-dimensional structural model of an adjustable nozzle, the three-dimensional structural model of the adjustable nozzle comprising an adjusting plate arranged at an engine outlet, the adjusting plates being in a plurality and evenly distributed along the circumferential direction of the engine outlet; each adjusting plate being movably installed by an actuator, and a sealing plate being further arranged between two adjacent adjusting plates, so as to form an adjustable nozzle of the engine; Establishing a first circumscribed regular polygon of the circular cross section of the inlet of the adjustable nozzle, wherein the number of sides of the first circumscribed regular polygon is equal to the number of the adjusting plates; establishing a second circumscribed regular polygon of the circular cross section of the throat of the adjustable nozzle, wherein the number of sides of the second circumscribed regular polygon is equal to the number of the adjusting plates, and the sides of the second circumscribed regular polygon are parallel to the corresponding sides of the first circumscribed regular polygon; Connect the corresponding corner points of the first circumscribed regular polygon and the second circumscribed regular polygon to form a prism structure; according to the number of initial aerodynamic loads of the adjustment plate under the calculation conditions , the prism structure is divided into Regular polygonal analytical sections; The side length of each regular polygon analysis section is calculated according to the side length of the first circumscribed regular polygon of the inlet section and the side length of the second circumscribed regular polygon of the throat section; the width of the adjusting piece at each regular polygon analysis section is obtained by analysis according to the initial width of the adjusting piece at the inlet section and the initial width of the adjusting piece at the throat section; Analyze the side length of each regular polygon section The width of the adjustment piece at the corresponding position Compared with the above, the proportional magnification factor of the adjustment piece is obtained. , the initial aerodynamic load of the regulating plate is analyzed equivalently by using the proportional magnification factor to obtain the equivalent value of the wall aerodynamic load on the regulating plate , is the initial aerodynamic load under the corresponding working condition calculated based on the flow field.

2. The method for equivalent analysis of aerodynamic loads of adjustable nozzle adjustment plates according to claim 1, characterized in that: The side length of the first circumscribed regular polygon ,in is the radius of the circular cross section of the adjustable nozzle inlet, is the central angle of the first circumscribed regular polygon.

3. The method for equivalent analysis of aerodynamic loads of adjustable nozzle adjustment plates according to claim 2, characterized in that: The side length of the second circumscribed regular polygon ,in is the radius of the circular cross section of the adjustable nozzle throat.

4. The method for equivalent analysis of aerodynamic loads of adjustable nozzle adjustment plates according to claim 3, characterized in that: No. The side length of the regular polygonal analytical section ,in , is the side length of the first circumscribed regular polygon, is the side length of the second circumscribed regular polygon; The width of the adjustment piece at the regular polygon analysis section , is the initial width of the regulating piece at the inlet section, is the initial width of the adjusting plate at the throat section.

5. An adjustable nozzle adjustment plate aerodynamic load equivalent analysis system, used to implement the adjustable nozzle adjustment plate aerodynamic load equivalent analysis method according to claim 1; characterized in that: include: A model building module is used to build a three-dimensional structural model of an adjustable nozzle, wherein the three-dimensional structural model of the adjustable nozzle includes an adjusting plate arranged at an engine outlet, wherein the adjusting plates are in a plurality and are evenly distributed along the circumferential direction of the engine outlet; each adjusting plate is movably installed by an actuator, and a sealing plate is further arranged between two adjacent adjusting plates, so as to form an adjustable nozzle of the engine; An inlet and outlet cross-section processing module is used to establish a first circumscribed regular polygon of the inlet circular cross-section of the adjustable nozzle, the number of sides of the first circumscribed regular polygon being equal to the number of adjusting plates; and to establish a second circumscribed regular polygon of the throat circular cross-section of the adjustable nozzle, the number of sides of the second circumscribed regular polygon being equal to the number of adjusting plates, and the sides of the second circumscribed regular polygon being parallel to the corresponding sides of the first circumscribed regular polygon; The cross-section division module is used to connect the corner points corresponding to the first circumscribed regular polygon and the second circumscribed regular polygon to form a prism structure; according to the number of initial aerodynamic loads of the adjustment plate under the calculation condition , the prism structure is divided into Regular polygonal analytical sections; A parameter calculation module is used to calculate the side length of each regular polygon analysis section according to the side length of the first circumscribed regular polygon of the inlet section and the side length of the second circumscribed regular polygon of the throat section; and to analyze and obtain the width of the adjustment piece at each regular polygon analysis section according to the initial width of the adjustment piece at the inlet section and the initial width of the adjustment piece at the throat section; Aerodynamic load equivalence module, used to convert the side length of each regular polygonal analysis section The width of the adjustment piece at the corresponding position Compared with the above, the proportional magnification factor of the adjustment piece is obtained. , the initial aerodynamic load of the regulating plate is analyzed equivalently by using the proportional magnification factor to obtain the equivalent value of the wall aerodynamic load on the regulating plate , is the initial aerodynamic load under the corresponding working condition calculated based on the flow field.

6. The aerodynamic load equivalent analysis system for adjustable nozzle adjustment plate according to claim 5, characterized in that: In the parameter calculation module, the side length of the first circumscribed regular polygon ,in is the radius of the circular cross section of the adjustable nozzle inlet, is the central angle of the first circumscribed regular polygon.

7. The aerodynamic load equivalent analysis system for adjustable nozzle adjustment plate according to claim 6, characterized in that: In the parameter calculation module, the side length of the second circumscribed regular polygon ,in is the radius of the circular cross section of the adjustable nozzle throat.

8. The aerodynamic load equivalent analysis system for adjustable nozzle adjustment plate according to claim 7, characterized in that: In the parameter calculation module, The side length of the regular polygonal analytical section ,in , is the side length of the first circumscribed regular polygon, is the side length of the second circumscribed regular polygon; The width of the adjustment piece at the regular polygon analysis section , is the initial width of the regulating piece at the inlet section, is the initial width of the adjusting plate at the throat section.

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