CN111859692A - Axial symmetry vectoring nozzle actuating system loaded analysis modeling method - Google Patents
Axial symmetry vectoring nozzle actuating system loaded analysis modeling method Download PDFInfo
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Abstract
The invention discloses a loaded analysis modeling method for an actuation system of an axisymmetric vectoring nozzle. The invention couples the space pose of the current deflection state of the steering control ring, the pull rod and the expansion adjusting sheet of the actuating system A9 with the pneumatic load characteristic of each expansion adjusting sheet to carry out the mechanical analysis of the actuating system, thereby establishing a vector deflection loaded analysis mechanical model. Compared with the prior art, the method can accurately describe the loading condition of the axisymmetric vectoring nozzle A9 actuating system in the actual working state, thereby providing an important theoretical basis for the design and test of the axisymmetric vectoring nozzle actuating system.
Description
Technical Field
The invention belongs to the field of system modeling and simulation in aerospace propulsion theory and engineering, and particularly relates to a loaded analysis modeling method for an actuation system of an axisymmetric vectoring nozzle.
Background
With the demand of fighters for high speed and high maneuverability, the traditional control surface control can not meet the operational demand, and the thrust vector technology is natural. The flamboyance and brightness of the zhhai launch fighter-10B thrust vector verifier in 11 and 6 days in 2018 brings the axisymmetric vectoring nozzle technology (AVEN) into public view, and a series of high-difficulty tactical actions show the huge potential of the axisymmetric vectoring nozzle technology for enhancing the maneuvering performance and the short-distance take-off and landing capability of the fighter.
The axisymmetric vectoring nozzle technology was first proposed by the GE company in the last 80 th century, and then a great deal of theoretical research work was carried out by scholars at home and abroad. Rebolo et al studied the vector deflection aerodynamic performance of axisymmetric vectoring nozzle of different geometric configurations through numerical simulation using different turbulence models, and established a performance optimization model [ ]. Wangyxin et al have constructed an axisymmetric vectoring nozzle A8, a9 actuation system space kinematics model through a double swart parallel mechanism, and have revealed a constraint relationship between actuator cylinder output displacement and vector deflection. And the research on the dynamics modeling direction of the axisymmetric vectoring nozzle is less, and Wanghanping et al constructs a multi-body dynamics model of the axisymmetric vectoring nozzle by using ADAMS and AMESim and analyzes the load and dynamic characteristics under working conditions of synchronous actuation mechanism, head swinging and the like in a cold state. However, the dynamic behavior of the vector deflection under operating conditions is still open. Based on an AMESim simulation platform, the Zhang Hao et al builds an A8 ring hydraulic actuating system model, and obtains the A8 actuating system load-bearing characteristic of adjusting the throat area of the spray pipe in a cold state through mechanical-electrical-hydraulic integrated coupling simulation.
The research is limited to the dynamic modeling simulation under the atmospheric environment condition of the non-working state of the vectoring nozzle, and the research on the dynamic characteristics of vector deflection under the actual working state of the engine, in particular the loaded analysis of the A9 actuating system for realizing the vector deflection is not related. In actual engineering, the driving force of the actuating cylinder of the actuating system is unknown, the accuracy of a loading test for simulating the vector deflection characteristic of the engine in a working state under a ground state cannot be guaranteed, and the designed hydraulic actuating system may not meet the requirement of continuous deflection in a vector deflection test run. Therefore, the research on the loaded characteristic of the vector deflection actuating system in the actual working state of the spray pipe has important significance on the design, test and research and development cost reduction of the actuating system of the axisymmetric vectoring spray pipe.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, and provides a loaded analysis modeling method for an actuating system of an axisymmetric vectoring nozzle, which can accurately describe the loaded condition of the actuating system of the axisymmetric vectoring nozzle A9 in an actual working state, thereby providing an important theoretical basis for the design and test of the actuating system of the axisymmetric vectoring nozzle.
The invention adopts the following technical scheme to solve the technical problems:
a load analysis modeling method for an axisymmetric vectoring nozzle actuating system is characterized in that the output force F of No. 1 to No. 3 actuating cylinders of the axisymmetric vectoring nozzle actuating system A9 is calculated through the following formula1、F2、F3：
In the formula, gamma1、γ2The deflection angles of A9 steering control rings, which are respectively the positions of No. 1 and No. 2 actuating cylinders of the axisymmetric vectoring nozzle actuating system A9, are respectively, i is 0 to represent the serial number of the expansion adjusting sheet on the upper wall surface of the nozzle, n is the serial number of the expansion adjusting sheet on the lower wall surface of the nozzle, an accumulation area i is 0 to 2n-1 to represent the serial numbers of all the expansion adjusting sheets in the clockwise direction along the circumferential direction of the nozzle, and L isDPFor the length of the dilatant flap, P (x) is the static pressure distribution along the axial direction of the dilatant flap, S (x) is the area distribution along the axial direction of the dilatant flap,ithe angle between a triangular pull rod corresponding to the ith expansion adjusting sheet and the axial direction is upsiloniThe expansion angle, omega, of the ith expansion adjustment sheetiThe tangential rotation angle phi of the ith sheet expansion adjusting sheetiThe included angle between the end of the triangular rod of the expansion adjusting sheet of the ith sheet and the longitudinal section, diA triangular rod A as the ith expansion regulating sheetiBiTo cross adapter connection point DiThe distance of (c).
Preferably, diThe calculation formula of (a) is specifically as follows:
wherein, thetaiA9 steering control ring deflection angle, L, for the position of the ith vane expansion adjustment vanehFrom hanging point B to the height of the expansion adjustment sheet LDCThe length of the cross adapter.
Preferably, the angular parameters of the expansion adjustment sheet are solved through an axial symmetry vector nozzle space kinematic modeli、υi、ωi、θi、φi。
Preferably, the axisymmetric vectoring nozzle is numerically simulated into a structured hexahedral mesh model in three dimensions, wherein the near-wall surface part, the inlet-outlet section and the throat section of the nozzle are partially encrypted with a scale factor of 1.2.
Preferably, the vector deflection CFD calculation is performed using an S-A (Sparrt-Allmoras) turbulence model, resulting in A static pressure profile P (x) along the axial direction of the dilating-flap.
Compared with the prior art, the technical scheme of the invention has the following beneficial effects:
(1) the established vector deflection dynamic model can effectively simulate the loaded characteristic of the actual vector deflection state actuating system.
(2) The invention can provide a load spectrum for a ground loading test of the vectoring nozzle actuating system and has important engineering application value.
Drawings
FIG. 1 is a flow chart of an axial symmetry thrust vectoring nozzle actuation system load analysis modeling;
FIG. 2 is a two-dimensional view of a vector deflection structure of an axisymmetric vectoring nozzle;
FIG. 3 is a three-dimensional view of a vector deflection structure of an axisymmetric vectoring nozzle;
FIG. 4 is a grid division;
FIG. 5 is a force analysis diagram of the dilating adjustment blade;
FIG. 6 is an exploded view of the triangular bar force in the deflection plane of the A9 steering control ring YOZ;
fig. 7 is a schematic view of the actuator output force in the steering control loop YOZ deflection plane (β 180 °);
fig. 8 is a schematic view of the actuator output force in the deflection plane of the steering control loop YOZ (β ═ 0 °);
FIG. 9 is a plot of PLA-110 vectored nozzle vane load distribution;
FIG. 10 is a force diagram of a different vector deflection angle actuator cylinder;
FIG. 11 is a force diagram of the actuator cylinder with different vector azimuth angles;
FIG. 12 is a two-dimensional interpolation model diagram of the output force of the A9 ram.
Detailed Description
Aiming at the research of the loaded characteristics of an actuating system in the actual working state of a vectoring nozzle, the invention provides a coupling modeling research method based on AVEN space kinematic analysis and vector deflection CFD (computational fluid dynamics), and the specific idea is as shown in figure 1: after a vector deflection instruction is given, firstly, the sectional areas of a throat and an outlet of a spray pipe in the current working state are output by an engine model, and the spatial position and attitude of the current deflection state of a vector deflection actuating system A9 steering control ring, a pull rod and an expansion adjusting sheet are solved according to an established AVEN spatial kinematics model; and then outputting parameters such as total temperature and total pressure of the inlet section of the spray pipe in the current working state, area of each section and the like according to an engine model to perform vector deflection CFD calculation so as to obtain the pneumatic load characteristics of each expansion adjusting sheet. And finally, coupling the two to perform mechanical analysis of the actuating system, thereby establishing a vector deflection loaded analysis mechanical model.
Firstly, a space kinematics mathematical model of the vertical shaft symmetric vectoring nozzle is established (various existing models can be adopted, for example, the related content of motion inverse solution and control compensation of an AVEN device in chapter VI of 'jet engine axisymmetric thrust vectoring nozzle' written in royal jade new teaching of Zhejiang university can be referred). The model inputs parameters including the sectional area of a throat of the spray pipe, the sectional area of an outlet of the spray pipe, a vector deflection angle alpha and a vector azimuth angle beta, and outputs parameters including an expansion adjusting sheet expansion angle upsilon, a triangular pull angle, an A9 steering control ring deflection angle theta and an expansion adjusting sheet tangential angle omega.
Then, a vector deflection CFD calculation is performed to obtain the aerodynamic load characteristics of each blade. The axisymmetric vectoring nozzle can realize 360-degree omnibearing continuous deflection, so that three-dimensional numerical simulation is required. FIG. 2 is a two-dimensional geometry for a vectoring nozzle, with L1, L2 for nozzle convergent and divergent nozzle tab lengths, respectively, and R8, R9 for nozzle throat and exit cross-sectional areas, respectively, determined by an engine model. The vector deflection three-dimensional structure diagram is drawn based on UG according to known dimensional parameters as shown in fig. 3, and the model is used to perform a numerically simulated meshing. In order to ensure the accuracy of the calculation result, local encryption with a scale factor of 1.2 is adopted for the part of the spray pipe close to the wall surface, the inlet and outlet sections and the throat section, and finally a structured hexahedral mesh model is obtained as shown in fig. 4.
The three-dimensional vector deflection simulation calculation of the axisymmetric vectoring nozzle uses FLUENT software. Rostatic et al, Beijing aerospace university, studied the internal flow characteristics of different turbulence model calculation axisymmetric nozzles, and compared and analyzed with experimental datA to draw the conclusion that the numerical simulation precision of an S-A equation model is the highest. Therefore, an S-A turbulence model is selected for vector deflection CFD calculation, the inlet boundary condition is A pressure inlet, and the outlet boundary condition is A pressure outlet. The input parameters are total temperature and total pressure of an inlet of the spray pipe and ambient pressure of an outlet of the spray pipe; the output parameter is the static pressure data of the wall surface of the nozzle expansion adjusting sheet, namely the pneumatic load data of the expansion adjusting sheet.
And finally, coupling the spatial pose of the current deflection state of the steering control ring, the pull rod and the expansion adjusting sheet of the actuating system A9 with the pneumatic load characteristic of each expansion adjusting sheet to carry out mechanical analysis of the actuating system, wherein the specific process is as follows:
when the axisymmetric vectoring nozzle works normally, the axisymmetric vectoring nozzle A9 applies external force to the actuating system, except for the pneumatic load of the expansion section of the nozzle, the external force also applies hydraulic force provided by the actuating cylinder. In the static state, the force balance between the acting force conducted by the hydraulic pressure of the actuating cylinder and the integral of the pneumatic load and the moment balance related to the rotating pair are satisfied. When the hydraulic pressure of the actuating cylinder changes, under the action of resultant force and resultant moment, the adjusting sheet rotates about the rotating shaft (the convergence adjusting sheet rotates in the radial direction, and the expansion adjusting sheet rotates in the radial direction and the tangential direction through the cross joint), and the stress sketch map is shown in fig. 5, and the stress of the adjusting sheet rotating around the R pair is calculated by using an integral method. Among them, the steering control loop is assumed to be ideal, regardless of its moment of inertia and force transmission efficiency. The generalized coordinate system of the actuation system is defined as X-axis along the axial direction (horizontal direction) of the nozzle, Y-axis along the vertical direction, and Z-axis along the direction out of the plane of the paper.
The pneumatic load acting on the expansion seal piece is transmitted to the expansion adjustment piece through the lap joint of the seal piece and the adjustment piece, so the load of the seal piece is considered by increasing the area of the expansion adjustment piece.
The load on the expansion adjustment sheet is:
and P (x) is axial static pressure distribution along the expansion adjusting sheet, load distribution curves of longitudinal sections of the spray pipes in deflection states obtained by CFD calculation are fitted and solved, S (x) is axial area distribution along the expansion adjusting sheet, and an integral area is the length of the expansion adjusting sheet.
The resultant action points of the aerodynamic force of the expansion adjusting sheet are as follows:
the resultant pneumatic force F acting on the expansion adjustment flap is balanced by a triangular pull rod AB. The triangular pull rod is connected with the steering adjusting ring through the rotating pair, and the force applied to the triangular rod along the AB direction balances the aerodynamic moment of the expansion adjusting sheet on the moment of the cross adapter connecting point D. Namely, it is
In the formula diIs a triangular pole AiBiTo point DiTo thereby determine the stress of the triangular bar
Wherein
In the formula areiAngle between triangular rod and axial direction, upsiloniTo expand the flap angle of divergence, omegaiFor expanding the tangential angle of rotation of the flap, thetaiA9 steering control ring deflection angle, L, for the position of the ith vane expansion adjustment vanehFrom hanging point B to the height of the expansion adjustment sheet LDCIs the length of a cross adapter, LDPTo expand the flap length.
The angle parameters can be solved through an axial symmetry vector nozzle space kinematic model:
marking the upper wall surface regulating sheet of the spray pipe as No. 0, marking the lower wall surface regulating sheet as No. n, and regulating sheets from No. 0 to No. ni、υiApproximately linearly change, can be obtained
When the vector azimuth angle is 0 ° or 180 °, i.e., pitch yaw, the angle parameter of the tab with the serial number greater than n is the same as the angle parameter of the tab with the serial number less than n corresponding to the XOY plane symmetric position thereof, due to symmetry.
The force of the triangular rods is transmitted to the A9 steering control ring through the revolute pair, and the force of the single triangular rod acting on the A9 steering control ring is
When friction of the A9 steering control ring centering device is not considered, the axial force on the steering control ring is balanced by three A9 rams. The resultant force of the triangular pull rod acting on the steering control ring is
Three actuating cylinders output force F1、F2、F3And
for two axes y on A9 steering control ring1、z1Is balanced with respect to moment, and F1+F2+F3+FCombination of Chinese herbsThe force applied to the three actuating cylinders can be obtained when the force is 0.
When the vector yaw angle is changed (the vector azimuth angle is fixed at 180 degrees, namely downward pitching deflection), the triangular rod connecting the expansion adjusting sheet and the A9 steering control ring is stressed to be decomposed in the A9 steering control ring YOZ deflection plane, and the schematic diagram is shown in figure 6.
The tangential component of the force of the triangular rod caused by the tangential deflection of the expansion adjusting sheet is
The normal component of the force applied to the triangular rod can be decomposed into a component parallel to the X axis (inward from the plane of the paper) of the deflection axis of the A9 steering control ring
And a component in the radial direction of the A9 steering control ring
Respectively has the size of
As can be derived from the geometric relationships illustrated,
the torque of the Y axis and the Z axis of the steering control ring is 0, then the triangular rod AiBiThe resultant moment of the stress on the Y axis and the Z axis of the steering control ring is as follows:
wherein R is the diameter of the steering control ring, phiiThe angle between the end of the triangular rod and the longitudinal section (XOY plane).
The schematic diagram of the force applied to the actuator cylinder in the deflection plane of the steering control ring YOZ is shown in fig. 7, where the components of the output force of the actuator cylinder along the deflection axis X of the steering control ring are F1′、F2′、F3' the moments of the component forces output by the three actuating cylinders to the Y axis and the Z axis of the steering control ring are
MZ′＝-F1′·R+F2′·R·cos60°+F3′·R·cos60° (14)
MY′＝F2′·R·sin60°-F3′·R·sin60° (15)
M can be obtained by moment balanceZ′+MZ＝0，MY′+M Y0. When the vector azimuth angle β is 180 °, i.e. is deflected only downwards, due to the symmetry F2′＝F3′，MY′＝M Y0. The actuator output force can be calculated by the following equation:
when the vector azimuth angle β is 0 ° (i.e., upward pitch), the same force is applied to the adjustment tab, and only the arrangement position of the actuator cylinder is changed, and the schematic diagram of the output force of the actuator cylinder is shown in fig. 8
The output force of the actuating cylinder is
When the azimuth angles of the vectors are 60 °,120 °, 240 ° and 300 °, the sequence of the actuators of fig. 2 is changed. For example, when β is 60 °, the equivalent is that the No. 3 cylinder in fig. 2 moves to the original No. 1 cylinder position, and the No. 1 and No. 2 cylinders move to the original No. 2 and No. 3 cylinder positions to calculate the cylinder output force.
In summary, the general formula for calculating the output force of the actuator cylinder of the axisymmetric vectoring nozzle actuator system a9 can be summarized as follows:
in the formula, gamma1、γ2The deflection angles of A9 steering control rings, which are respectively the positions of No. 1 and No. 2 actuating cylinders of the axisymmetric vectoring nozzle actuating system A9, are respectively, i is 0 to represent the serial number of the expansion adjusting sheet on the upper wall surface of the nozzle, n is the serial number of the expansion adjusting sheet on the lower wall surface of the nozzle, an accumulation area i is 0 to 2n-1 to represent the serial numbers of all the expansion adjusting sheets in the clockwise direction along the circumferential direction of the nozzle, and L isDPFor the length of the dilatant flap, P (x) is the static pressure distribution along the axial direction of the dilatant flap, S (x) is the area distribution along the axial direction of the dilatant flap,ithe angle between a triangular pull rod corresponding to the ith expansion adjusting sheet and the axial direction is upsiloniThe expansion angle, omega, of the ith expansion adjustment sheetiThe tangential rotation angle phi of the ith sheet expansion adjusting sheetiThe included angle between the end of the triangular rod of the expansion adjusting sheet of the ith sheet and the longitudinal section, diA triangular rod A as the ith expansion regulating sheetiBiTo cross adapter connection point DiThe distance of (c).
In order to verify the effect of the invention, a certain type of double-shaft turbofan mixed engine component level model is combined, the engine working states H-0, M-0 and PLA 50, 60, 70, 90 and 110 are respectively selected as the CFD calculation of the typical vector deflection working condition. Based on commercial CFD calculation software FLUENT, the total pressure and the total temperature of an afterburner outlet calculated by the mathematical model of the state engine are set as pressure inlet boundary conditions, the atmospheric pressure is selected as the backpressure to be set as the pressure outlet boundary conditions, and an S-A (spark-Allmaras) turbulence model is selected to carry out numerical calculation with vector deflection angles of 5 degrees, 10 degrees, 15 degrees and 20 degrees respectively. Assuming that the axisymmetric vectoring nozzle flare is constructed of 24 flare flaps, the corresponding aerodynamic loading model is shown in FIG. 9.
Due to space limitation, the aerodynamic load distribution of each adjusting blade of the nozzle in different vector deflection states is only listed when PLA is 110. In the figure, the angle represents the included angle between the adjusting sheet and the longitudinal section of the spray pipe, the adjusting sheet is arranged in the clockwise direction, 0 degrees represent the upper wall surface of the spray pipe, and 180 degrees represent the lower wall surface. As can be seen from the figure, the load distribution of the inner wall surface which has different angles with the longitudinal section of the spray pipe in the two states is similar to the change situation along with the increase of the vector deflection angle. The load distribution of the upper wall surface of the spray pipe is maximum, the load distribution of the lower wall surface of the spray pipe is minimum, the load of the upper wall surface is continuously increased along with the increase of the vector deflection angle, and the amplification is large. The load change of the lower wall surface is small, and the load of the wall surface is gradually reduced from the upper wall surface to the lower wall surface.
According to the calculation result of the pneumatic load of vector deflection in the last step, the dynamic simulation model of the vector deflection loaded characteristic of the actuating system is established when the vector azimuth angle is 180 degrees in different working states of the engine by combining the simulation of the kinematic models in different deflection states, and the result is shown in fig. 10 and 11.
Fig. 10 is a simulation result of stress applied to the actuator cylinders with different vector deflection angles a9 in different working states of the engine when the vector azimuth angle is fixed to 180 °, with the increase of the vector deflection angle, the forward output force of the actuator cylinder No. 1 increases continuously, the piston of the actuator cylinder is pushed outwards to output displacement, the reverse output forces of the actuator cylinders No. 2 and No. 3, which are distributed in the same direction as the deflection direction, increase continuously, the piston of the actuator cylinder is pulled inwards to contract displacement, and therefore the downward deflection of the nozzle is realized, and the output forces of the actuator cylinders No. 2 and No. 3 are the same due to the symmetry of the arrangement of the actuator cylinders. In addition, from simulation results, it is known that actuators arranged farther from the vector deflection direction need to output a greater force to complete the vector deflection.
Fig. 11 shows the simulation result of the output force of the actuator cylinder in which the vector azimuth angle is continuously changed from 0 ° to 360 ° in different engine operating states when the vector deflection angle is 20 °. The force variation trends of the actuating cylinders in different working states of the engine are the same. The output forces of the three actuating cylinders change in a sine curve rule, two adjacent curves can be completely overlapped when translating by 120 degrees, and when the vector azimuth angle is the same as the position angle of the actuating cylinder, the stress of the corresponding actuating cylinder reaches the minimum value; when the vector azimuth angle is opposite to the actuator cylinder position angle (for example, the actuator cylinder position angle No. 2 is 120 degrees, and the opposite position angle is 300 degrees), the actuator cylinder stress reaches the maximum value, and the maximum value is consistent with the stress analysis conclusion of the actuator cylinder in the prior literature.
The vector deflection angle and the influence rule of the vector azimuth angle are combined to establish a two-dimensional interpolation model of the stress of the A9 actuator cylinders in different working states of the engine, and the two-dimensional interpolation model is shown in figure 12 when PLA is 110.
The two-dimensional interpolation model can be regarded as the extension of the one-dimensional isovector deflection angle and isovector azimuth angle curve in the deflection angle dimension and the azimuth angle dimension respectively. When the vector deflection angle is 0, the isovector deflection angle lines of the three actuating cylinders are all a fixed value straight line. With the increase of the vector deflection angle, the change trend similar to that of the figure 12 appears on the equal vector deflection angle line, and the amplitude value is gradually increased; the isovector azimuth line has a non-monotonic change rule, and the change of the isovector azimuth line is related to the magnitude of the vector azimuth angle. The two-dimensional difference model describes the relationship between the vector deflection angle and the vector azimuth angle of the axisymmetric vectoring nozzle and the stress of the three actuating cylinders of the A9 actuating system in different working states of the engine, can be used as a load spectrum of a ground loading test for simulating the actual working state of the axisymmetric vectoring nozzle, and has important engineering reference value.
Claims (5)
1. Actuating system of axisymmetric vectoring nozzleThe load analysis modeling method is characterized in that the output force F of the actuating cylinders No. 1 to No. 3 of the axisymmetric vectoring nozzle actuating system A9 is calculated through the following formula1、F2、F3：
In the formula, gamma1、γ2The deflection angles of A9 steering control rings, which are respectively the positions of No. 1 and No. 2 actuating cylinders of the axisymmetric vectoring nozzle actuating system A9, are respectively, i is 0 to represent the serial number of the expansion adjusting sheet on the upper wall surface of the nozzle, n is the serial number of the expansion adjusting sheet on the lower wall surface of the nozzle, an accumulation area i is 0 to 2n-1 to represent the serial numbers of all the expansion adjusting sheets in the clockwise direction along the circumferential direction of the nozzle, and L isDPFor the length of the dilatant flap, P (x) is the static pressure distribution along the axial direction of the dilatant flap, S (x) is the area distribution along the axial direction of the dilatant flap,ithe angle between a triangular pull rod corresponding to the ith expansion adjusting sheet and the axial direction is upsiloniThe expansion angle, omega, of the ith expansion adjustment sheetiThe tangential rotation angle phi of the ith sheet expansion adjusting sheetiThe included angle between the end of the triangular rod of the expansion adjusting sheet of the ith sheet and the longitudinal section, diA triangular rod A as the ith expansion regulating sheetiBiTo cross adapter connection point DiThe distance of (c).
2. The method according to claim 1, wherein d is a weighted analysis of the actuation system of the axisymmetric vectoring nozzleiThe calculation formula of (a) is specifically as follows:
wherein, thetaiA9 steering control ring deflection angle, L, for the position of the ith vane expansion adjustment vanehFrom hanging point B to the height of the expansion adjustment sheet LDCThe length of the cross adapter.
3. The method of claim 1, wherein the angular parameters of the flare stack are solved using an axisymmetric vectoring nozzle space kinematics modeli、υi、ωi、θi、φi。
4. The method according to claim 1, wherein the axisymmetric vectoring nozzle is numerically modeled as a structured hexahedral mesh model in three dimensions, wherein the nozzle near-wall section, the inlet-outlet section, and the throat section are locally encrypted with a scaling factor of 1.2.
5. The method for modeling an axial load analysis of an actuation system of an axisymmetric vectoring nozzle of claim 1, wherein A vector deflection CFD calculation is performed using an S-A turbulence model to obtain an axial static pressure distribution p (x) along the expansion flap.
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| CN113849913B (en) * | 2021-09-27 | 2024-05-24 | 北京环境特性研究所 | Method and device for generating three-dimensional grid of axisymmetric vectoring nozzle |
| CN114201892A (en) * | 2021-10-20 | 2022-03-18 | 中国航发四川燃气涡轮研究院 | Adjusting mechanism load calculation method considering friction influence |
| CN114491874A (en) * | 2022-04-07 | 2022-05-13 | 中国航发四川燃气涡轮研究院 | Method for quickly analyzing inlet pressure and load of binary spray pipe |
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