Helicopter aerodynamic force analysis method and device considering rotor interference with aerodynamic components

Abstract

The application provides a helicopter aerodynamic force analysis method and device considering rotor interference with aerodynamic components, and the method comprises the following steps: calculating a critical inflection point of a position relationship between downwash of a helicopter rotor and a plurality of aerodynamic components and a wake tilt angle of the helicopter according to a back chamfer of the helicopter rotor; establishing a linear correlation between an interference coefficient of the critical inflection point and the wake tilt angle, and obtaining a target three-axis speed of a target aerodynamic component under the interference of the helicopter rotor according to the linear correlation and three-axis speed of the helicopter, and analyzing aerodynamic force of the helicopter according to the target three-axis speed; wherein the target aerodynamic component belongs to the plurality of aerodynamic components. The method improves the simulation effect of the flight performance of the helicopter, and improves the efficiency and accuracy of the helicopter aerodynamic force analysis.

Description

Technical Field

[0001] This invention relates to the field of helicopter flight mechanics and aerodynamics, and in particular to a helicopter aerodynamic analysis method and apparatus that takes into account the interference of the rotor on aerodynamic components. Background Technology

[0002] For flight simulation equipment, the realism of flight performance is a key element of its simulation; and for helicopters, such as helicopters, the interference of rotor downwash airflow on aerodynamic components is an important part of helicopter flight performance simulation.

[0003] In related technologies, the simulation of the interference of rotor downwash on helicopter aerodynamic components is achieved in two ways: (1) The CFD method is used to numerically simulate the interference flow field of the helicopter rotor and calculate the dynamic aerodynamic load of the helicopter components. However, this method cannot reflect the characteristics of the helicopter during the transition speed stage, such as pitching up and dropping altitude. The simulation accuracy is low, resulting in inaccurate aerodynamic load results. Moreover, the algorithm takes a long time to run, which is difficult to meet the requirements of real-time calculation of flight simulation equipment. (2) A set of differential equations of helicopter flight dynamics is established. The differential equations are linearized with small disturbances under a specific trim state, and the multi-rotor interference problem is simulated from the level of basic physical theory. However, this method is generally only for a specific trim point and it is difficult to realize the simulation of infinitely many states within the full envelope of the helicopter by flight simulation equipment. Summary of the Invention

[0004] This invention provides a helicopter aerodynamic analysis method and apparatus that considers the interference of the rotor on aerodynamic components. It addresses the shortcomings of existing technologies that use CFD methods to calculate the dynamic aerodynamic loads of helicopter components, resulting in low accuracy and efficiency, and that use methods that establish a set of differential equations for helicopter flight dynamics to simulate an infinite number of states within the full flight envelope of a helicopter in flight simulation equipment. The method described in this invention improves the simulation effect of helicopter flight performance and simultaneously enhances the efficiency and accuracy of helicopter aerodynamic analysis.

[0005] This invention provides a helicopter aerodynamic analysis method considering the interference of the rotor on aerodynamic components, comprising: The critical inflection point of the positional relationship between the downwash airflow of the helicopter rotor and multiple aerodynamic components, as well as the helicopter's wake angle, are calculated based on the rear chamfer of the helicopter rotor. A linear correlation is established between the interference coefficient of the critical inflection point and the wake tilt angle. Based on the linear correlation and the helicopter's three-axis velocity, the target three-axis velocity of the target aerodynamic component under the interference of the helicopter rotor is obtained. The aerodynamic forces of the helicopter are analyzed based on the target three-axis velocity. The target aerodynamic component belongs to the plurality of aerodynamic components.

[0006] According to the present invention, a helicopter aerodynamic analysis method considering the interference of the rotor on aerodynamic components is provided. The critical inflection point includes the coordinates of the front boundary point and the rear boundary point of the helicopter rotor during the rotation process, as well as the front boundary coordinates and the rear boundary coordinates of the side profile of each aerodynamic component. The critical inflection point is obtained through the following steps: Based on the rear chamfer, the center coordinates of the helicopter rotor in the helicopter structural coordinate system, and the radius of the helicopter rotor, the coordinates of the front boundary point and the rear boundary point are obtained. The coordinates of the front boundary of the side profile are determined based on the coordinates of the front boundary point, and the coordinates of the rear boundary of the side profile are determined based on the coordinates of the rear boundary point.

[0007] According to the present invention, a helicopter aerodynamic analysis method considering rotor interference with aerodynamic components, before establishing a linear correlation between the interference coefficient at the critical inflection point and the wake slope angle, the method further includes: Based on the dimensional relationship between the helicopter rotor and the plurality of aerodynamic components, the included angles corresponding to the front boundary point coordinates, rear boundary point coordinates, front boundary coordinates of the side profile, and rear boundary coordinates of the side profile of the helicopter rotor during rotation are sorted.

[0008] According to the present invention, a helicopter aerodynamic analysis method considering the interference of the rotor on aerodynamic components is provided, wherein the plurality of aerodynamic components include the fuselage, horizontal stabilizer and vertical stabilizer of the helicopter.

[0009] According to the present invention, a helicopter aerodynamic analysis method considering rotor interference with aerodynamic components is provided, wherein the aerodynamic analysis of the helicopter based on the target three-axis velocity includes: Calculate the angle of attack and sideslip angle of the target aerodynamic component based on the target's triaxial velocity; The aerodynamic coefficient of the target aerodynamic component is calculated based on the angle of attack and the sideslip angle, and the aerodynamic force and torque of the target aerodynamic component are calculated based on the aerodynamic coefficient. The forces acting on the helicopter are calculated based on the aerodynamic forces and torques corresponding to each aerodynamic component.

[0010] The present invention also provides a helicopter aerodynamic analysis device that takes into account the interference of the rotor on aerodynamic components, comprising: The calculation module is used to calculate the critical inflection point of the positional relationship between the downwash airflow of the helicopter rotor and multiple aerodynamic components, as well as the helicopter's wake tilt angle, based on the rear chamfer of the helicopter rotor. The analysis module is used to establish a linear correlation between the interference coefficient of the critical inflection point and the wake tilt angle, and to obtain the target three-axis velocity of the target aerodynamic component under the interference of the helicopter rotor based on the linear correlation and the helicopter's three-axis velocity, and to analyze the aerodynamic forces of the helicopter based on the target three-axis velocity; wherein, the target aerodynamic component belongs to the plurality of aerodynamic components.

[0011] According to the present invention, a helicopter aerodynamic analysis device considering the interference of the rotor on aerodynamic components is provided, the device further comprising: The sorting module is used to sort the included angles corresponding to the front boundary point coordinates, rear boundary point coordinates, front boundary coordinates of the side profile, and rear boundary coordinates of the side profile during the rotation process, according to the dimensional relationship between the helicopter rotor and the multiple aerodynamic components before establishing the linear correlation between the interference coefficient of the critical inflection point and the wake tilt angle.

[0012] The present invention also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the helicopter aerodynamic analysis method considering rotor interference with aerodynamic components as described above.

[0013] The present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements a helicopter aerodynamic analysis method considering rotor interference with aerodynamic components as described above.

[0014] The present invention also provides a computer program product, including a computer program that, when executed by a processor, implements a helicopter aerodynamic analysis method considering rotor interference with aerodynamic components as described above.

[0015] The present invention provides a helicopter aerodynamic analysis method and apparatus that considers rotor interference with aerodynamic components. It calculates the critical inflection point of the positional relationship between the downwash airflow of the helicopter rotor and multiple aerodynamic components, as well as the helicopter's wake angle, by using the helicopter rotor's back chamfer angle. Then, it establishes a linear correlation between the interference coefficient of the critical inflection point and the wake angle, and obtains the target three-axis velocity of the target aerodynamic component under helicopter rotor interference based on the linear correlation and the helicopter's three-axis velocity. Finally, it analyzes the helicopter's aerodynamics based on the target three-axis velocity, thereby improving the simulation effect of helicopter flight performance and increasing the efficiency and accuracy of helicopter aerodynamic analysis. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0017] Figure 1 This is one of the flowcharts of the helicopter aerodynamic analysis method that considers the interference of the rotor on aerodynamic components provided by the present invention.

[0018] Figure 2 This is a schematic diagram showing the relationship between the interference coefficient and the tail tilt angle provided by the present invention.

[0019] Figure 3 This is a structural schematic diagram of the aerodynamic components of a helicopter in the structural coordinate system, corresponding to the tail tilt angle and boundary position coordinates.

[0020] Figure 4 This is the second flowchart of the helicopter aerodynamic analysis method that considers the interference of the rotor on aerodynamic components provided by the present invention.

[0021] Figure 5 This is a schematic diagram of the structure of the helicopter aerodynamic analysis device that considers the interference of the rotor on aerodynamic components provided by the present invention.

[0022] Figure 6 This is a schematic diagram of the structure of the electronic device provided by the present invention. Detailed Implementation

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

[0024] The following is combined Figures 1-5 The present invention describes a helicopter aerodynamic analysis method and apparatus that takes into account the interference of rotor on aerodynamic components.

[0025] Figure 1 This is one of the flowcharts illustrating the helicopter aerodynamic analysis method considering rotor interference with aerodynamic components provided by this invention, such as... Figure 1 As shown, the method includes the following steps: Step 110: Calculate the critical inflection point of the positional relationship between the downwash airflow of the helicopter rotor and multiple aerodynamic components, as well as the helicopter's tail roll angle, based on the rear chamfer of the helicopter rotor.

[0026] In this step, the rear chamfer of the helicopter rotor is the angle at which the rotor cone tilts backward due to the forward aerodynamic load. This angle directly affects the direction of the rotor thrust vector: when the rear chamfer increases, the rearward component of the thrust vector increases, causing the impact position of the downwash airflow on the downstream aerodynamic components (such as the horizontal stabilizer and vertical stabilizer) to shift backward.

[0027] In this embodiment, the critical inflection point can be the location where the airflow separation or interference intensity abruptly changes when the angle of attack between the current washing airflow velocity direction and the aerodynamic component (such as the horizontal stabilizer) reaches a specific threshold.

[0028] In this embodiment, the wake inclination angle is the angle between the rotor wake centerline and the horizontal plane, which is determined by the back chamfer and the flight state.

[0029] For example, the wake inclination angle can be calculated based on the critical point and inflection point of the interference coefficient of each aerodynamic component affected by the rotor downwash airflow.

[0030] In this embodiment, multiple aerodynamic components, including the helicopter fuselage, horizontal stabilizer, and vertical stabilizer, are analyzed aerodynamically under the interference of the helicopter rotor. This achieves the decomposition of the forces acting on the entire helicopter and improves the accuracy of the aerodynamic analysis.

[0031] Step 120: Establish a linear relationship between the interference coefficient of the critical inflection point and the wake tilt angle, and obtain the target three-axis velocity of the target aerodynamic component under the interference of the helicopter rotor based on the linear relationship and the three-axis velocity of the helicopter, and analyze the aerodynamic force of the helicopter based on the target three-axis velocity; wherein, the target aerodynamic component belongs to multiple aerodynamic components.

[0032] In this step, linear correlation can refer to the fact that the interference coefficient between the wake tilt angle and the critical inflection point has a linear correlation. Within different wake tilt angle ranges, the interference coefficient between the wake tilt angle and the critical inflection point can be positively correlated or negatively correlated.

[0033] Figure 2 This is a schematic diagram illustrating the relationship between the interference coefficient and the wake tilt angle provided by the present invention. Figure 2 In the illustrated embodiment, it is assumed that the interference coefficients at the critical inflection points are k1 and k2, respectively. Typically, max (k1, k2) The interference coefficient is within the full speed envelope. k Following the tail tilt angle Relationship of change such as Figure 2 As shown, the linear correlation function can be calculated from this. k( ) .

[0034] In this embodiment, different pneumatic components correspond to different target triaxial velocities.

[0035] In this embodiment, the above linear correlation describes the pneumatic components at different wake inclination angles. The corresponding critical inflection point interference coefficient can be used to deduce the target triaxial velocity of each aerodynamic component under helicopter rotor interference by combining the critical inflection point interference coefficient of each aerodynamic component and the triaxial velocity of the helicopter.

[0036] In this embodiment, after determining the target triaxial velocity of each aerodynamic component, the angle of attack and sideslip angle of each component are calculated respectively, and then the starting coefficient of each aerodynamic component is derived and the aerodynamic force and its torque are calculated to realize the force analysis of each aerodynamic component of the helicopter.

[0037] This invention provides a helicopter aerodynamic analysis method that considers rotor interference with aerodynamic components. It calculates the critical inflection point of the positional relationship between the helicopter rotor's downwash airflow and multiple aerodynamic components, as well as the helicopter's wake angle, using the rotor's back chamfer. Then, it establishes a linear correlation between the interference coefficient of the critical inflection point and the wake angle. Based on this linear correlation and the helicopter's three-axis velocities, it obtains the target three-axis velocities of the target aerodynamic components under rotor interference. Finally, it analyzes the helicopter's aerodynamics based on these target three-axis velocities, improving the simulation effect of helicopter flight performance and enhancing the efficiency and accuracy of helicopter aerodynamic analysis.

[0038] In some embodiments, the critical inflection point includes the coordinates of the front boundary point and the rear boundary point of the helicopter rotor during rotation, as well as the coordinates of the front boundary point and the rear boundary point of the side profile of each aerodynamic component. The critical inflection point is obtained through the following steps: the coordinates of the front boundary point and the rear boundary point are obtained based on the rear chamfer, the center coordinates of the helicopter rotor in the helicopter structural coordinate system, and the radius of the helicopter rotor; the coordinates of the front boundary point are determined based on the front boundary point coordinates, and the coordinates of the rear boundary point are determined based on the rear boundary point coordinates.

[0039] In this embodiment, the origin of the helicopter's structural coordinate system is set at the helicopter's plane of symmetry, and the XYZ axes of the structural coordinate system are forward, rightward, and downward along the helicopter, respectively. Furthermore, during normal flight, except for high-speed side-flight, the rotor's interference with aerodynamic components is mainly manifested along the X and Z axes. Therefore, this example uses a helicopter side profile for calculation. Assume the rotor center coordinates are Given a rotor radius of R and a rotor back chamfer of A1S (back chamfer is positive), then the forward boundary point during rotor rotation... and back boundary point The coordinates are obtained using the following formulas: ; .

[0040] In this embodiment, taking the fuselage as an example, assuming the helicopter fuselage is in the structural coordinate system, the front and rear boundary positions of the side section are respectively... and The included angle is calculated from the relative positions of different aerodynamic components and the rotor (including...). , , The following formula can be used to calculate: ; ; ; ; .

[0041] in, The wake angle is the position of the front boundary of the side section of the aerodynamic component and the position of the rear boundary of the helicopter rotor during rotation. This represents the wake angle corresponding to the rear boundary position of the side profile and the rear boundary position of the helicopter rotor. The wake angle is the position of the front boundary of the side section and the position of the front boundary of the helicopter rotor. The tail tilt angle is the position of the rear boundary of the side profile and the position of the front boundary of the helicopter rotor.

[0042] This invention provides a helicopter aerodynamic analysis method considering the interference of the rotor on aerodynamic components. The critical inflection point includes the coordinates of the front and rear boundary points of the helicopter rotor during rotation, as well as the front and rear boundary coordinates of the side profiles of each aerodynamic component. The front and rear boundary point coordinates are obtained by using the back chamfer, the center coordinates of the helicopter rotor in the helicopter structural coordinate system, and the radius of the helicopter rotor. The front boundary point coordinates of the side profile are determined based on the front boundary point coordinates, and the rear boundary coordinates of the side profile are determined based on the rear boundary point coordinates. This method can quickly determine the critical inflection points and wake tilt angles of different aerodynamic components, providing reliable data support for subsequent calculation of the target three-axis velocities of each aerodynamic component under the interference of the helicopter rotor, and improving the efficiency of the algorithm.

[0043] In some embodiments, before establishing a linear correlation between the interference coefficient of the critical inflection point and the wake tilt angle, the helicopter aerodynamic analysis method considering the rotor's interference with aerodynamic components further includes: sorting the included angles corresponding to the front boundary point coordinates, rear boundary point coordinates, front boundary coordinates of the side profile, and rear boundary coordinates of the side profile during the rotation process of the helicopter rotor according to the dimensional relationship between the helicopter rotor and multiple aerodynamic components.

[0044] Figure 3 This is a structural schematic diagram of the aerodynamic components of a helicopter in the structural coordinate system, corresponding to the wake tilt angle and boundary position coordinates. Figure 3 In the embodiment shown, Relative positional relationships such as Figure 3 As shown, then The size relationships are as follows: in, It is the origin of the structural coordinate system (including the X and Z axes) in which the helicopter fuselage is located.

[0045] This invention provides a helicopter aerodynamic analysis method that considers the interference of the rotor on aerodynamic components. Before establishing a linear correlation between the interference coefficient at the critical inflection point and the wake tilt angle, the method sorts the included angles corresponding to the coordinates of the front boundary point, rear boundary point, front boundary of the side profile, and rear boundary of the side profile during the helicopter rotor's rotation process, based on the dimensional relationship between the helicopter rotor and multiple aerodynamic components. This quantifies the geometric relationship between the rotor boundary points and aerodynamic components, predicts the critical inflection point of the wake tilt angle, and provides input conditions for the abrupt change analysis of the interference coefficient.

[0046] In some embodiments, the aerodynamic analysis of the helicopter based on the target three-axis velocity includes: calculating the angle of attack and sideslip angle of the target aerodynamic components based on the target three-axis velocity; calculating the aerodynamic coefficients of the target aerodynamic components based on the angle of attack and sideslip angle, and calculating the aerodynamic force and torque of the target aerodynamic components based on the aerodynamic coefficients; and performing force calculation on the helicopter based on the aerodynamic force and torque corresponding to each aerodynamic component.

[0047] In this embodiment, the target aerodynamic component is taken as the fuselage of a helicopter for illustration; this embodiment achieves the force calculation of the helicopter through the following steps: (1) Calculate the target three-axis velocity of the computer body according to the following formula: + V ; in, For rotor induced velocity, V The three-axis speeds are the speeds of the fuselage along the corresponding axis system. This is the interference coefficient corresponding to the critical inflection point of the pneumatic component.

[0048] (2) The angle of attack of the computer body is calculated by the following formula. and sideslip angle : ; ; (3) Calculate the aerodynamic coefficients of the aerodynamic components based on the angle of attack and sideslip angle interpolation, and then calculate the aerodynamic force and torque. Through the above steps (1)-(3), the aerodynamic force and torque of the fuselage considering the interference of the rotor on the fuselage can be calculated. The aerodynamic force and torque of the vertical tail and horizontal tail under the interference of the rotor can also be calculated according to the above method, and then the force calculation of the entire helicopter can be completed.

[0049] This invention provides a helicopter aerodynamic analysis method considering the interference of the rotor on aerodynamic components. The method calculates the angle of attack and sideslip angle of the target aerodynamic components using the target's three-axis velocities; calculates the aerodynamic coefficients of the target aerodynamic components based on the angle of attack and sideslip angles; and calculates the aerodynamic forces and moments of the target aerodynamic components based on the aerodynamic coefficients. The method then performs force calculations on the helicopter based on the corresponding aerodynamic forces and moments of each aerodynamic component. This enables real-time simulation calculation of the interference coefficient of the rotor downwash airflow on aerodynamic components across the entire velocity envelope of the helicopter, and improves the accuracy of the helicopter aerodynamic analysis calculation results.

[0050] Figure 4 This is the second flowchart of the helicopter aerodynamic analysis method considering rotor interference with aerodynamic components provided by the present invention. Figure 4 In the illustrated embodiment, a helicopter aerodynamic analysis method considering the rotor's interference with aerodynamic components further includes the following steps: (1) Calculate the rotor back chamfer; calculate the geometric position of the rotor boundary point in the airframe coordinate system based on the rotor back chamfer; (2) Calculate the critical inflection point of the relationship between the rotor downwash airflow and the positions of the fuselage, horizontal stabilizer, and vertical stabilizer based on the geometric position of the rotor boundary point in the airframe coordinate system; (3) Determine the relationship between the critical inflection points and calculate the wake tilt angle based on the rotor back chamfer. (4) Determine the relationship between the interference coefficient and the wake tilt angle based on the interference coefficient of each aerodynamic component at the corresponding critical inflection point (corresponding to linear correlation). (5) Calculate the three-axis speed of the helicopter and determine the speed of the aerodynamic components under rotor interference based on the relationship between the interference coefficient and the tail slope angle; (6) Calculate the angle of attack and sideslip angle of the aerodynamic component under rotor interference based on the speed of the aerodynamic component under rotor interference, and then calculate the aerodynamic force of the aerodynamic component under rotor interference.

[0051] The helicopter aerodynamic analysis device considering rotor interference with aerodynamic components provided by the present invention will be described below. The helicopter aerodynamic analysis device considering rotor interference with aerodynamic components described below can be referred to in correspondence with the helicopter aerodynamic analysis method considering rotor interference with aerodynamic components described above.

[0052] Figure 5This is a schematic diagram of the helicopter aerodynamic analysis device considering the interference of the rotor on aerodynamic components provided by the present invention, as shown in the figure. Figure 5 As shown, the helicopter aerodynamic analysis device that considers the rotor's interference with aerodynamic components includes: a calculation module 510 and an analysis module 520.

[0053] The calculation module 510 is used to calculate the critical inflection point of the positional relationship between the downwash airflow of the helicopter rotor and multiple aerodynamic components, as well as the helicopter's wake tilt angle, based on the rear chamfer of the helicopter rotor. Analysis module 520 is used to establish a linear correlation between the interference coefficient of the critical inflection point and the wake tilt angle, and to obtain the target three-axis velocity of the target aerodynamic component under the interference of the helicopter rotor based on the linear correlation and the helicopter's three-axis velocity, and to analyze the aerodynamic forces of the helicopter based on the target three-axis velocity; wherein, the target aerodynamic component belongs to multiple aerodynamic components.

[0054] This invention provides a helicopter aerodynamic analysis device that considers the interference of the rotor on aerodynamic components. It calculates the critical inflection point of the positional relationship between the downwash airflow of the helicopter rotor and multiple aerodynamic components, as well as the helicopter's wake angle, using the rotor's back chamfer. Then, it establishes a linear correlation between the interference coefficient of the critical inflection point and the wake angle. Based on this linear correlation and the helicopter's three-axis velocities, it obtains the target three-axis velocities of the target aerodynamic components under rotor interference. Finally, it analyzes the helicopter's aerodynamics based on these target three-axis velocities, improving the simulation effect of helicopter flight performance and enhancing the efficiency and accuracy of helicopter aerodynamic analysis.

[0055] In some embodiments, the helicopter aerodynamic analysis device that considers the interference of the rotor on aerodynamic components further includes: a sorting module, which sorts the included angles corresponding to the front boundary point coordinates, rear boundary point coordinates, front boundary coordinates of the side profile, and rear boundary coordinates of the side profile during the rotation process according to the dimensional relationship between the interference coefficient of the critical inflection point and the wake inclination angle, before establishing the linear relationship between the interference coefficient of the critical inflection point and the wake inclination angle.

[0056] This invention provides a helicopter aerodynamic analysis device that considers the interference of the rotor on aerodynamic components. Before establishing a linear correlation between the interference coefficient at the critical inflection point and the wake tilt angle, the device sorts the included angles corresponding to the coordinates of the front boundary point, rear boundary point, front boundary of the side profile, and rear boundary of the side profile during the helicopter rotor's rotation process, based on the dimensional relationship between the helicopter rotor and multiple aerodynamic components. This quantifies the geometric relationship between the rotor boundary points and aerodynamic components, predicts the critical inflection point of the wake tilt angle, and provides input conditions for the abrupt change analysis of the interference coefficient.

[0057] Figure 6 An example is a schematic diagram of the physical structure of an electronic device, such as... Figure 6 As shown, the electronic device may include: a processor 610, a communications interface 620, a memory 630, and a communication bus 640. The processor 610, communications interface 620, and memory 630 communicate with each other via the communication bus 640. The processor 610 can call logical instructions in the memory 630 to execute a helicopter aerodynamic analysis method considering the rotor's interference with aerodynamic components. This method includes: calculating the critical inflection point of the positional relationship between the helicopter rotor's downwash airflow and multiple aerodynamic components, as well as the helicopter's wake angle, based on the helicopter rotor's back chamfer angle; establishing a linear correlation between the interference coefficient of the critical inflection point and the wake angle; obtaining the target three-axis velocity of the target aerodynamic component under helicopter rotor interference based on the linear correlation and the helicopter's three-axis velocity; and analyzing the helicopter's aerodynamic forces based on the target three-axis velocity. The target aerodynamic component comprises multiple aerodynamic components.

[0058] Furthermore, the logical instructions in the aforementioned memory 630 can be implemented as software functional units and, when sold or used as independent products, can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, or a part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0059] On the other hand, the present invention also provides a computer program product, which includes a computer program that can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can execute the helicopter aerodynamic analysis method considering the interference of the rotor on aerodynamic components provided by the above methods. The method includes: calculating the critical inflection point of the positional relationship between the downwash airflow of the helicopter rotor and multiple aerodynamic components and the helicopter's wake angle based on the back chamfer angle of the helicopter rotor; establishing a linear correlation between the interference coefficient of the critical inflection point and the wake angle; obtaining the target three-axis velocity of the target aerodynamic component under the interference of the helicopter rotor based on the linear correlation and the helicopter's three-axis velocity; and analyzing the aerodynamic forces of the helicopter based on the target three-axis velocity; wherein the target aerodynamic component belongs to multiple aerodynamic components.

[0060] In another aspect, the present invention also provides a non-transitory computer-readable storage medium storing a computer program thereon, which, when executed by a processor, implements a helicopter aerodynamic analysis method considering rotor interference with aerodynamic components provided by the methods described above. This method includes: calculating the critical inflection point of the positional relationship between the downwash airflow of the helicopter rotor and multiple aerodynamic components, and the helicopter's wake angle, based on the helicopter rotor's back chamfer angle; establishing a linear correlation between the interference coefficient of the critical inflection point and the wake angle; obtaining the target three-axis velocity of the target aerodynamic component under helicopter rotor interference based on the linear correlation and the helicopter's three-axis velocity; and analyzing the helicopter's aerodynamic forces based on the target three-axis velocity; wherein the target aerodynamic component is one of multiple aerodynamic components.

[0061] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.

[0062] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in the various embodiments or some parts of the embodiments.

[0063] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A helicopter aerodynamic analysis method considering the interference of the rotor on aerodynamic components, characterized in that, include: The critical inflection point of the positional relationship between the downwash airflow of the helicopter rotor and multiple aerodynamic components, as well as the helicopter's wake angle, are calculated based on the rear chamfer of the helicopter rotor. A linear correlation is established between the interference coefficient of the critical inflection point and the wake tilt angle. Based on the linear correlation and the helicopter's three-axis velocity, the target three-axis velocity of the target aerodynamic component under the interference of the helicopter rotor is obtained. The aerodynamic forces of the helicopter are analyzed based on the target three-axis velocity. The target aerodynamic component belongs to the plurality of aerodynamic components. The critical inflection point includes the coordinates of the front boundary point and the rear boundary point of the helicopter rotor during rotation, as well as the front boundary coordinates and the rear boundary coordinates of the side profile of each aerodynamic component. The critical inflection point is obtained through the following steps: Based on the rear chamfer, the center coordinates of the helicopter rotor in the helicopter structural coordinate system, and the radius of the helicopter rotor, the coordinates of the front boundary point and the rear boundary point are obtained. The coordinates of the front boundary of the side profile are determined based on the coordinates of the front boundary point, and the coordinates of the rear boundary of the side profile are determined based on the coordinates of the rear boundary point.

2. The helicopter aerodynamic analysis method considering rotor interference with aerodynamic components according to claim 1, characterized in that, Before establishing the linear correlation between the interference coefficient at the critical inflection point and the wake tilt angle, the method further includes: Based on the dimensional relationship between the helicopter rotor and the plurality of aerodynamic components, the included angles corresponding to the front boundary point coordinates, rear boundary point coordinates, front boundary coordinates of the side profile, and rear boundary coordinates of the side profile of the helicopter rotor during rotation are sorted.

3. The helicopter aerodynamic analysis method considering rotor interference with aerodynamic components according to claim 1, characterized in that, The plurality of aerodynamic components include the helicopter's fuselage, horizontal stabilizer, and vertical stabilizer.

4. The helicopter aerodynamic analysis method considering rotor interference with aerodynamic components according to claim 1, wherein the aerodynamic analysis of the helicopter based on the target three-axis velocity includes: Calculate the angle of attack and sideslip angle of the target aerodynamic component based on the target's triaxial velocity; The aerodynamic coefficient of the target aerodynamic component is calculated based on the angle of attack and the sideslip angle, and the aerodynamic force and torque of the target aerodynamic component are calculated based on the aerodynamic coefficient. The forces acting on the helicopter are calculated based on the aerodynamic forces and torques corresponding to each aerodynamic component.

5. A helicopter aerodynamic analysis device considering rotor interference on aerodynamic components, employing the helicopter aerodynamic analysis method considering rotor interference on aerodynamic components as described in claim 1, characterized in that, include: The calculation module is used to calculate the critical inflection point of the positional relationship between the downwash airflow of the helicopter rotor and multiple aerodynamic components, as well as the helicopter's wake tilt angle, based on the rear chamfer of the helicopter rotor. The analysis module is used to establish a linear correlation between the interference coefficient of the critical inflection point and the wake tilt angle, and to analyze the aerodynamic forces of the helicopter under the interference of the helicopter rotor based on the linear correlation and the three-axis velocity of the target aerodynamic component. The target aerodynamic component belongs to the plurality of aerodynamic components.

6. The helicopter aerodynamic analysis device considering rotor interference with aerodynamic components according to claim 5, characterized in that, The device further includes: The sorting module is used to sort the included angles corresponding to the front boundary point coordinates, rear boundary point coordinates, front boundary coordinates of the side profile, and rear boundary coordinates of the side profile during the rotation process, according to the dimensional relationship between the helicopter rotor and the multiple aerodynamic components before establishing the linear correlation between the interference coefficient of the critical inflection point and the wake tilt angle.

7. An electronic device comprising a memory, a processor, and a computer program stored in the memory and running on the processor, characterized in that, When the processor executes the computer program, it implements the helicopter aerodynamic analysis method that considers the rotor's interference with aerodynamic components as described in any one of claims 1 to 4.

8. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the helicopter aerodynamic analysis method as described in any one of claims 1 to 4, which takes into account the interference of the rotor on aerodynamic components.

9. A computer program product, comprising a computer program, characterized in that, When the computer program is executed by the processor, it implements the helicopter aerodynamic analysis method as described in any one of claims 1 to 4, which takes into account the interference of the rotor on aerodynamic components.

Images