Spray pipe layout method and device for weakening pitching disturbance torque, equipment and medium

Abstract

The invention provides a nozzle layout method and device for weakening pitching disturbance torque, equipment and a medium, and the method comprises the steps: building a three-dimensional model of an aircraft, and arranging an original orbit control nozzle on the three-dimensional model of the aircraft; solving a jet flow interference flow field of the aircraft three-dimensional model in a target flight state, extracting a cloud picture of a symmetry plane of the aircraft three-dimensional model, and obtaining a head shock wave inclination angle from the cloud picture; the outlet center of the original orbit control spray pipe serves as the rotation center, the original orbit control spray pipe is rotated in the symmetry plane of the aircraft to form an inclined orbit control spray pipe, and the rotation angle is determined according to the head shock wave inclination angle; jet flow disturbing flow field numerical simulation is carried out on the inclined orbit control nozzle layout under the rotation angle, optimization verification is carried out on the layout effect through pitching moment optimization efficiency and normal force optimization efficiency, it is ensured that pitching disturbance moment is reduced, jet flow normal control efficiency reaches the standard, and the problems that the orbit control jet flow disturbance moment is too large, and the layout effect is influenced are solved. The control capability of an attitude control engine is insufficient, and the control stability is reduced.

Description

Technical Field

[0001] This invention relates to the field of flow control technology, and in particular to a nozzle layout method, apparatus, equipment and medium for reducing pitch disturbance torque. Background Technology

[0002] Jet jet control technology is an aerodynamic control technique that uses the reaction force generated by a jet stream to alter the flight trajectory or attitude of an aircraft. It can be applied to aircraft with a wide speed range and large airspace, offering advantages such as high control precision, fast response speed, and insensitivity to atmospheric conditions. Future high-speed aircraft will operate at altitudes ranging from low to high, covering both dense and thin atmospheres. Due to these advantages, jet jet control technology is widely used in the field of high-speed aircraft control, enabling high-precision control and rapid response, and is one of the key technologies in high-speed aircraft research.

[0003] When the flow rate of the orbit control engine increases, the jet stream and the incoming airflow will generate a large disturbance torque. Domestically and internationally, the common approach is to place attitude control engines at a location far from the center of gravity to reduce the disturbance torque generated by the orbit control. However, under certain conditions (such as direct headwinds, low-altitude flight, and high Mach number flight conditions), the disturbance torque of the orbit control jet stream becomes too large, the attitude control engine's control capability is insufficient, and the control stability is reduced.

[0004] Therefore, there is an urgent need for a nozzle layout method to reduce pitch interference torque in order to solve the technical problems of excessive interference torque of the orbit control jet, insufficient control capability of the attitude control engine, and reduced control stability. Summary of the Invention

[0005] To overcome the problems existing in the related technologies, this disclosure provides a nozzle layout method, device, equipment and medium to reduce pitch interference torque, so as to solve the technical problems of excessive interference torque of the orbital control jet, insufficient control capability of attitude control engine and reduced control stability in the related technologies.

[0006] This specification provides one or more embodiments of a nozzle layout method for reducing pitch disturbance moment, including the following steps: A three-dimensional model of the aircraft, including a blunt nose, a conical section, and a tail rudder, is established. The three-dimensional model of the aircraft is equipped with an original orbital control nozzle. The jet direction of the original orbital control nozzle is perpendicular to the longitudinal axis of the projectile and the jet passes through the center of mass. The jet interference flow field of the three-dimensional model of the aircraft under the target flight state is solved by numerical simulation. Based on the jet interference flow field, the symmetry plane cloud map of the three-dimensional model of the aircraft is extracted and the head shock wave tilt angle is obtained from it. Using the exit center of the original orbital control nozzle as the rotation center, the original orbital control nozzle is rotated within the symmetry plane of the aircraft to form an inclined orbital control nozzle. The expansion section exit of the inclined orbital control nozzle is in contact with the upper edge of the projectile body. The rotation angle is determined according to the head shock wave tilt angle. Numerical simulation of the jet flow interference field was performed on the inclined track control nozzle layout under the aforementioned rotation angle. The layout effect was optimized and verified by using pitch moment optimization efficiency and normal force optimization efficiency to ensure that the pitch interference moment is reduced and the jet flow normal control efficiency meets the standard.

[0007] Preferably, the step of using numerical simulation to solve the jet interference flow field of the three-dimensional model of the aircraft under the target flight state, and extracting the symmetry plane cloud map of the three-dimensional model of the aircraft and obtaining the head shock wave tilt angle from it, specifically includes the following steps: The jet interference flow field of the three-dimensional aircraft model under the target flight state is solved by data simulation method of solving the three-dimensional compressible Navier-Stokes equations, and the velocity and pressure information of the jet interference flow field are output. Based on the velocity and pressure information, a flow field cloud map of the symmetry plane of the three-dimensional model of the aircraft is generated; By identifying the boundary contour of the head shock wave in the flow field cloud diagram, the angle between the head shock wave and the longitudinal axis of the projectile is calculated to obtain the head shock wave tilt angle.

[0008] Preferably, the method of solving the jet interference flow field of the three-dimensional aircraft model under the target flight state using the data simulation method of solving the three-dimensional compressible Navier-Stokes equations, and outputting the velocity and pressure information of the jet interference flow field, specifically includes the following steps: Determine the three-dimensional compressible Navier-Stokes equations: ; Where Q is a conserved variable, and F, G, and H are the inviscid flux vectors in the x, y, and z directions of the coordinate system, respectively. v G v H v These are the viscous flux vectors in the x, y, and z directions of the coordinate system, respectively. t is time, x is the flow direction in the coordinate system, y is the normal direction in the coordinate system, and z is the circumferential direction in the coordinate system. The coordinate system adopted is a three-dimensional Cartesian rectangular coordinate system, and the origin of the coordinate system is selected as the midpoint of the leading edge of the three-dimensional model of the aircraft. Solving the three-dimensional compressible Navier-Stokes equations, we obtain the conserved variable Q, expressed as: ; Where ρ represents density, u, v, and w represent flow velocity, normal velocity, and circumferential velocity, respectively, and E represents fluid energy per unit mass. The velocity and pressure information of the jet interference flow field are extracted by the conserved variable Q.

[0009] Preferably, solving the three-dimensional compressible Navier-Stokes equations specifically includes the following steps: The three-dimensional compressible Navier-Stokes equations were solved using fluid simulation software. The time discretization scheme can be LUSGS, the spatial discretization scheme can be Roe scheme, and the turbulence model can be SA model.

[0010] Preferably, the rotation angle is determined based on the head shock wave tilt angle, specifically including the following steps: The ratio of the rotation angle to the head shock wave tilt angle is in the range of 0 to 1.

[0011] Preferably, the optimization and verification of the layout effect using pitch moment optimization efficiency and normal force optimization efficiency specifically includes the following steps: The optimization efficiency of normal force and pitch moment are represented as follows: Optimization efficiency of normal force ; Pitch moment optimization efficiency ; in, This represents the pitch moment disturbance caused by the optimized layout of the track control jet. This represents the pitch moment disturbance caused by the orbital control jet of the original nozzle layout. This represents the normal force disturbance caused by the optimized layout of the track control jet. This represents the normal force interference caused by the original nozzle layout and the track-controlled jet.

[0012] Preferably, the method further includes the following steps: This means the layout design offers no optimization whatsoever. This indicates that the layout design has a negative impact. This indicates that the layout design has been optimized, and Smaller layouts are more efficient at optimizing design. The additional adverse effects of pitch on the layout design have completely disappeared. This means the layout design offers no optimization whatsoever. This indicates that the layout design has a negative impact. This indicates that the layout design has been optimized, and The larger the layout, the higher the optimization efficiency.

[0013] This specification provides one or more embodiments of a nozzle layout device that applies the above-described method for reducing pitch disturbance moment, including: The model building module is used to construct a three-dimensional model of an aircraft, which includes a blunt nose, a conical section, and a tail rudder. The three-dimensional model of the aircraft is equipped with an original orbital control nozzle. The jet direction of the original orbital control nozzle is perpendicular to the longitudinal axis of the projectile and the jet passes through the center of mass. The solution module is used to solve the jet interference flow field of the three-dimensional model of the aircraft under the target flight state using numerical simulation methods. Based on the jet interference flow field, the symmetry plane cloud map of the three-dimensional model of the aircraft is extracted and the head shock wave tilt angle is obtained from it. The rotating module is used to rotate the original orbital control nozzle into an inclined orbital control nozzle within the plane of symmetry of the aircraft, with the outlet center of the original orbital control nozzle as the rotation center. The expansion section outlet of the inclined orbital control nozzle is in contact with the upper edge of the projectile body. The rotation angle is determined according to the head shock wave tilt angle. The optimization and verification module is used to perform numerical simulation of the jet flow interference field of the inclined track control nozzle layout under the rotation angle, and to optimize and verify the layout effect by using pitch moment optimization efficiency and normal force optimization efficiency to ensure that the pitch interference moment is reduced and the jet flow normal control efficiency meets the standard.

[0014] This specification provides one or more embodiments of a computer device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor, when executing the computer program, implements the nozzle layout method for reducing pitch interference moment as described above.

[0015] This specification provides one or more embodiments of a computer-readable storage medium storing a computer program that, when executed by a processor, implements the steps of the nozzle layout method for reducing pitch interference moment as described above.

[0016] This disclosure provides a nozzle layout method, device, equipment, and medium for reducing pitch interference moment. Its advantages lie in the following: By constructing a three-dimensional model that closely matches the actual aerodynamic characteristics of a high-speed aircraft, the baseline layout parameters of the original orbital control nozzle are clearly defined. This provides a precise physical basis for subsequent flow field simulation and establishes a baseline state for comparing optimization effects, laying a reliable physical foundation for subsequent nozzle layout optimization. Numerical simulation accurately captures the details of the jet interference flow field, successfully extracting the core baseline parameter of the head shock wave tilt angle, overcoming the limitations of traditional experiments and avoiding the blindness of nozzle angle design, providing data support for the scientific design of subsequent oblique angles. By constructing a dual disturbance reduction mechanism through nozzle oblique placement, the pitch interference moment is effectively reduced, improving the stability of the aircraft under extreme conditions. Furthermore, it does not change the projectile structure and requires no additional energy input, reducing the difficulty of engineering implementation, while initially balancing the disturbance reduction effect and normal control efficiency. Through numerical simulation and quantified efficiency indicators, the torque and control efficiency data before and after optimization are accurately compared, transforming the evaluation of the optimization effect from qualitative to quantitative, ensuring that the layout meets the core objectives of disturbance reduction and efficiency preservation, and providing closed-loop verification for the reliability and engineering applicability of the scheme. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in one or more embodiments of this specification or in 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 only some embodiments recorded in this specification. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 A schematic flowchart illustrating a nozzle layout method for reducing pitch interference moment provided for one or more embodiments of this specification; Figure 2 A schematic diagram of the shock wave at the head of the aircraft flow field and a schematic diagram of the original rotation center of the aircraft's orbital control nozzle, the rotation angle of the inclined orbital control nozzle, and the structure of the interfering flow field provided for one or more embodiments of this specification; Figure 3 A comparison diagram of the jet flow interference streamline of the inclined track control nozzle layout provided in one or more embodiments of this specification (top) and the interference streamline of the original track control nozzle layout (bottom); Figure 4 A schematic diagram illustrating the variation of normal force control efficiency with tilt angle for one or more embodiments of this specification; Figure 5 A schematic diagram illustrating the change in pitch moment optimization efficiency with tilt angle for one or more embodiments of this specification; Figure 6 A schematic diagram of a nozzle layout device for reducing pitch interference moment provided in one or more embodiments of this specification; Figure 7 This is a schematic diagram of the structure of a computer device provided for one or more embodiments of this specification. Detailed Implementation

[0019] To enable those skilled in the art to better understand the technical solutions in one or more embodiments of this specification, the technical solutions in one or more embodiments of this specification will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this specification, and not all of the embodiments. Based on one or more embodiments of this specification, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of this invention.

[0020] The present invention will now be described in detail with reference to specific embodiments and accompanying drawings.

[0021] Method Implementation Examples According to embodiments of the present invention, a nozzle layout method for reducing pitch interference moment is provided, such as... Figure 1 The diagram shown is a flowchart illustrating the nozzle layout method for reducing pitch interference moment provided in this embodiment. The nozzle layout method for reducing pitch interference moment according to this embodiment includes the following steps: S110. A three-dimensional model of the aircraft, including a blunt nose, a conical section, and a tail rudder, is established using CATIA and other three-dimensional solid modeling software. The three-dimensional model of the aircraft is equipped with an original orbital control nozzle. The jet direction of the original orbital control nozzle is perpendicular to the longitudinal axis of the missile body and the jet passes through the center of mass.

[0022] S120. The jet interference flow field of the three-dimensional model of the aircraft under the target flight state is solved by numerical simulation. Based on the jet interference flow field, the cloud map of the symmetry plane of the three-dimensional model of the aircraft is extracted and the head shock wave tilt angle β is obtained from it.

[0023] S130. Using the exit center of the original orbital control nozzle as the rotation center, the original orbital control nozzle is rotated within the symmetry plane of the aircraft to form an inclined orbital control nozzle. The exit of the expansion section of the inclined orbital control nozzle is in contact with the upper edge of the missile body. The rotation angle θ is determined according to the head shock wave tilt angle β. The ratio of the rotation angle θ to the head shock wave tilt angle β is in the range of 0 to 1. Specifically, the rotation angle θ satisfies: θ / β = 0.2 to 1.0.

[0024] S140. Numerical simulation of the jet flow field of the inclined track-controlled nozzle layout under rotation angle θ was performed, and the layout effect was optimized and verified by using pitch moment optimization efficiency and normal force optimization efficiency. Compared with the original nozzle layout, the interference moment of the jet flow in the optimized layout is reduced, the static stability of the jet flow when facing the windward surface is improved, and the pitch interference moment is reduced and the jet flow normal control efficiency meets the standard.

[0025] The method provided in this embodiment constructs a three-dimensional model that closely matches the actual aerodynamic characteristics of a high-speed aircraft, clearly defining the baseline layout parameters of the original orbital control nozzle. This provides a precise physical basis for subsequent flow field simulation and establishes a baseline state for comparing optimization effects, laying a reliable physical foundation for subsequent nozzle layout optimization. Numerical simulation accurately captures the details of the jet interference flow field, successfully extracting the core baseline parameter, the head shock wave tilt angle β, overcoming the limitations of traditional experiments and avoiding the blindness of nozzle angle design, providing data support for the scientific design of subsequent oblique angles. By constructing a dual disturbance reduction mechanism through nozzle oblique placement, the pitch disturbance torque is effectively reduced, improving the stability of the aircraft under extreme conditions. Furthermore, it does not change the projectile structure and requires no additional energy input, reducing the difficulty of engineering implementation, while initially balancing the disturbance reduction effect and normal control efficiency. Through numerical simulation and quantified efficiency indicators, the torque and control efficiency data before and after optimization are accurately compared, transforming the evaluation of the optimization effect from qualitative to quantitative, ensuring that the layout meets the core objectives of disturbance reduction and efficiency preservation, and providing closed-loop verification for the reliability and engineering applicability of the scheme.

[0026] In one embodiment, a numerical simulation method is used to solve the jet interference flow field of the three-dimensional model of the aircraft under the target flight state. Based on the jet interference flow field, the symmetry plane cloud map of the three-dimensional model of the aircraft is extracted and the head shock wave tilt angle β is obtained from it. Specifically, the following steps are included: A data simulation method for solving the three-dimensional compressible Navier-Stokes equations is used to solve the jet interference flow field of the three-dimensional aircraft model under target flight conditions, outputting the velocity and pressure information of the jet interference flow field. Specifically, the three-dimensional compressible Navier-Stokes equations are determined: ; Where Q is a conserved variable, and F, G, and H are the inviscid flux vectors in the x, y, and z directions of the coordinate system, respectively. v G v H v Let t be the viscous flux vectors in the x, y, and z directions of the coordinate system, respectively, where t is time, x is the flow direction in the coordinate system, y is the normal direction in the coordinate system, and z is the circumferential direction in the coordinate system.

[0027] The coordinate system adopted is a three-dimensional Cartesian rectangular coordinate system, with the origin selected as the midpoint of the leading edge of the three-dimensional model of the aircraft.

[0028] Solving the three-dimensional compressible Navier-Stokes equations, we obtain the conserved variable Q, expressed as: ; Where ρ represents density, u, v, and w represent flow velocity, normal velocity, and circumferential velocity, respectively, and E represents fluid energy per unit mass.

[0029] Velocity and pressure information of the jet interference flow field are extracted by conserving the variable Q.

[0030] Flow field cloud maps of the symmetry plane of a three-dimensional model of an aircraft are generated based on velocity and pressure information; By identifying the boundary profile of the head shock wave in the flow field cloud diagram, the angle between the head shock wave and the longitudinal axis of the projectile is calculated, thus obtaining the head shock wave tilt angle β. Figure 2 As shown, Figure 2 (a) is a schematic diagram of the shock wave at the head of the aircraft flow field provided in this embodiment. Figure 2 (b) is a schematic diagram of the original orbit control nozzle rotation center, the inclined orbit control rotation angle θ, and the interference flow field structure.

[0031] Solving the three-dimensional compressible Navier-Stokes equations specifically includes the following steps: The three-dimensional compressible Navier-Stokes equations were solved using fluid simulation software.

[0032] The time discretization scheme can be LUSGS, the spatial discretization scheme can be Roe scheme, and the turbulence model can be SA model.

[0033] The method provided in this embodiment uses numerical simulation by solving the three-dimensional compressible Navier-Stokes equations to accurately recreate the interaction process between the jet and the incoming flow under the target's flight state. It efficiently outputs key data such as flow field velocity and pressure, overcoming the limitation of traditional experiments in accurately capturing the details of high-speed jet interference, and ensuring that the flow field simulation results are highly consistent with actual working conditions. At the same time, based on these data, a flow field cloud map of the symmetry plane of the three-dimensional model of the aircraft is generated, transforming the abstract flow field characteristics into an intuitive visualization image, clearly presenting the distribution pattern of the head shock wave, and providing a convenient basis for shock wave boundary identification. Finally, by accurately identifying the head shock wave boundary and calculating its angle with the longitudinal axis of the projectile, the head shock wave tilt angle β is obtained, providing a scientific and reliable core benchmark parameter for the subsequent nozzle oblique design, effectively avoiding the blindness of nozzle angle design, and laying a key data foundation for nozzle layout optimization that reduces interference and maintains efficiency.

[0034] In one embodiment, such as Figure 3The image shows a comparison of the jet flow interference streamline diagram (top) of the inclined track control nozzle layout provided in this embodiment and the interference streamline diagram (bottom) of the original track control nozzle layout. The layout effect is optimized and verified using pitch moment optimization efficiency and normal force optimization efficiency, specifically including the following steps: The optimization efficiency of normal force and pitch moment are represented as follows: Optimization efficiency of normal force ; Pitch moment optimization efficiency ; in, This represents the pitch moment disturbance caused by the optimized layout of the track control jet. This represents the pitch moment disturbance caused by the orbital control jet of the original nozzle layout. This represents the normal force disturbance caused by the optimized layout of the track control jet. This represents the normal force interference caused by the original nozzle layout and the track-controlled jet.

[0035] in, This means the layout design offers no optimization whatsoever. This indicates that the layout design has a negative impact. This indicates that the layout design has been optimized, and Smaller layouts are more efficient at optimizing design. The additional adverse effects of pitch on the layout design have completely disappeared. This means the layout design offers no optimization whatsoever. This indicates that the layout design has a negative impact. This indicates that the layout design has been optimized, and The larger the layout, the higher the optimization efficiency.

[0036] The following specific implementation case further illustrates the solution: This embodiment focuses on the optimized design of a typical blunt cone, orbit-controlled, tail-rudder aircraft jet model. The flight speed is Mach 8.0, altitude 20km, angle of attack 0°, and orbit-controlled jet thrust is 7200N. The optimization objective is to reduce the pitch disturbance moment generated by the orbit-controlled jet by 15% while ensuring that the change in normal force control efficiency does not exceed 1%. After multiple rounds of optimization calculations, as shown... Figure 4 , Figure 5The figures shown are schematic diagrams illustrating the changes in pitch moment optimization efficiency and normal force control efficiency as the rotation angle θ increases, according to embodiments of the present invention. The final rotation angle θ that meets the design requirements is θ / β=0.6. Under this condition, the interference torque caused by the track control jet is reduced by 18.36%. Here, θ represents the tilt angle, and β represents the head shock wave tilt angle.

[0037] Device Examples According to embodiments of the present invention, a layout apparatus for applying the above-described method for reducing pitch disturbance moment is provided, such as... Figure 6 The diagram shown is a structural schematic of the nozzle layout device for reducing pitch interference moment provided in this embodiment. The nozzle layout device for reducing pitch interference moment according to an embodiment of the present invention includes: Model building module 61 is used to construct a three-dimensional model of an aircraft that includes a blunt nose, a conical section, and a tail rudder. The three-dimensional model of the aircraft is equipped with an original orbital control nozzle. The jet direction of the original orbital control nozzle is perpendicular to the longitudinal axis of the missile body and the jet passes through the center of mass.

[0038] The solver module 62 is used to solve the jet interference flow field of the three-dimensional model of the aircraft under the target flight state using numerical simulation methods. Based on the jet interference flow field, the symmetry plane cloud map of the three-dimensional model of the aircraft is extracted and the head shock wave tilt angle is obtained from it.

[0039] Rotation module 63 is used to rotate the original orbital control nozzle into an inclined orbital control nozzle within the symmetry plane of the aircraft, with the outlet center of the original orbital control nozzle as the rotation center. The expansion section outlet of the inclined orbital control nozzle is in contact with the upper edge of the missile body. The rotation angle is determined according to the head shock wave tilt angle.

[0040] The optimization and verification module 64 is used to perform numerical simulation of the jet flow interference field of the inclined track control nozzle layout under the rotation angle, and to optimize and verify the layout effect by using pitch moment optimization efficiency and normal force optimization efficiency to ensure that the pitch interference moment is reduced and the jet flow normal control efficiency meets the standard.

[0041] The device provided in this embodiment includes a model building module 61 that constructs a three-dimensional model that closely matches the actual aerodynamic characteristics of a high-speed aircraft, clarifying the baseline layout parameters of the original orbital control nozzle. This provides a precise physical basis for subsequent flow field simulation and establishes a baseline state for comparing optimization effects, laying a reliable physical foundation for subsequent nozzle layout optimization. The solution module 62 accurately captures the details of the jet interference flow field through numerical simulation, successfully extracting the core baseline parameter of the head shock wave tilt angle. This overcomes the limitations of traditional experiments, avoids the blindness of nozzle angle design, and provides data support for the scientific design of subsequent oblique angles. The rotation module 63 constructs a dual disturbance reduction mechanism through nozzle oblique placement, effectively reducing pitch interference torque and improving the stability of the aircraft under extreme conditions. It does not change the projectile structure and requires no additional energy input, reducing the difficulty of engineering implementation. At the same time, it initially balances the disturbance reduction effect and normal control efficiency. The optimization verification module 64 accurately compares the torque and control efficiency data before and after optimization through numerical simulation and quantitative efficiency indicators, transforming the evaluation of optimization effects from qualitative to quantitative. This ensures that the layout meets the core objectives of disturbance reduction and efficiency maintenance, providing closed-loop verification for the reliability and engineering applicability of the scheme.

[0042] The embodiments of the present invention are device embodiments corresponding to the above method embodiments. The specific operations of each module processing step can be understood with reference to the description of the method embodiments, and will not be repeated here.

[0043] like Figure 7 As shown, the present invention also provides a computer-readable storage medium having a computer program stored thereon. When the computer program is executed by a processor, it implements the nozzle layout method for reducing pitch interference moment in the above embodiments, or when the computer program is executed by a processor, it implements the nozzle layout method for reducing pitch interference moment in the above embodiments.

[0044] Those skilled in the art will understand that all or part of the processes in the methods of the above embodiments can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium, and when executed, it can include the processes of the embodiments of the above methods. Any references to memory, storage, databases, or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM), or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), dual data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), Rambus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

[0045] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to mutually. Each embodiment focuses on describing the differences from other embodiments. In particular, for apparatus or system embodiments, since they are basically similar to method embodiments, the description is relatively simple; relevant parts can be referred to the descriptions in the method embodiments. The apparatus and system 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 creative effort.

[0046] 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 or all of the technical features. These modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention, and the contents not described in detail in the specification of the present invention are known to those skilled in the art.

Claims

1. A nozzle layout method for reducing pitch interference moment, characterized in that, Includes the following steps: A three-dimensional model of the aircraft, including a blunt nose, a conical section, and a tail rudder, is established. The three-dimensional model of the aircraft is equipped with an original orbital control nozzle. The jet direction of the original orbital control nozzle is perpendicular to the longitudinal axis of the projectile and the jet passes through the center of mass. The jet interference flow field of the three-dimensional model of the aircraft under the target flight state is solved by numerical simulation. Based on the jet interference flow field, the symmetry plane cloud map of the three-dimensional model of the aircraft is extracted and the head shock wave tilt angle is obtained from it. Using the exit center of the original orbital control nozzle as the rotation center, the original orbital control nozzle is rotated within the symmetry plane of the aircraft to form an inclined orbital control nozzle. The expansion section exit of the inclined orbital control nozzle is in contact with the upper edge of the projectile body. The rotation angle is determined according to the head shock wave tilt angle. Numerical simulation of the jet flow interference field was performed on the inclined track control nozzle layout under the aforementioned rotation angle. The layout effect was optimized and verified by using pitch moment optimization efficiency and normal force optimization efficiency to ensure that the pitch interference moment is reduced and the jet flow normal control efficiency meets the standard.

2. The nozzle layout method for reducing pitch interference moment as described in claim 1, characterized in that, The method of using numerical simulation to solve the jet interference flow field of the three-dimensional model of the aircraft under the target flight state, and extracting the symmetry plane cloud map of the three-dimensional model of the aircraft from the jet interference flow field to obtain the head shock wave tilt angle, specifically includes the following steps: The jet interference flow field of the three-dimensional aircraft model under the target flight state is solved by data simulation method of solving the three-dimensional compressible Navier-Stokes equations, and the velocity and pressure information of the jet interference flow field are output. Based on the velocity and pressure information, a flow field cloud map of the symmetry plane of the three-dimensional model of the aircraft is generated; By identifying the boundary contour of the head shock wave in the flow field cloud diagram, the angle between the head shock wave and the longitudinal axis of the projectile is calculated to obtain the head shock wave tilt angle.

3. The nozzle layout method for reducing pitch interference moment as described in claim 2, characterized in that, The method of solving the jet interference flow field of the three-dimensional aircraft model under the target flight state using the data simulation method of solving the three-dimensional compressible Navier-Stokes equations, and outputting the velocity and pressure information of the jet interference flow field, specifically includes the following steps: Determine the three-dimensional compressible Navier-Stokes equations: ； Where Q is a conserved variable, and F, G, and H are the inviscid flux vectors in the x, y, and z directions of the coordinate system, respectively. v G v H v These are the viscous flux vectors in the x, y, and z directions of the coordinate system, respectively. t is time, x is the flow direction in the coordinate system, y is the normal direction in the coordinate system, and z is the circumferential direction in the coordinate system. The coordinate system adopted is a three-dimensional Cartesian rectangular coordinate system, and the origin of the coordinate system is selected as the midpoint of the leading edge of the three-dimensional model of the aircraft. Solving the three-dimensional compressible Navier-Stokes equations, we obtain the conserved variable Q, expressed as: ； Where ρ represents density, u, v, and w represent flow velocity, normal velocity, and circumferential velocity, respectively, and E represents fluid energy per unit mass. The velocity and pressure information of the jet interference flow field are extracted by the conserved variable Q.

4. The nozzle layout method for reducing pitch interference moment as described in claim 3, characterized in that, The solution of the three-dimensional compressible Navier-Stokes equations specifically includes the following steps: The three-dimensional compressible Navier-Stokes equations were solved using fluid simulation software. The time discretization scheme can be LUSGS, the spatial discretization scheme can be Roe scheme, and the turbulence model can be SA model.

5. The nozzle layout method for reducing pitch interference moment as described in claim 1, characterized in that, The rotation angle is determined based on the head shock wave tilt angle, and specifically includes the following steps: The ratio of the rotation angle to the head shock wave tilt angle is in the range of 0 to 1.

6. The nozzle layout method for reducing pitch interference moment as described in claim 1, characterized in that, The optimization and verification of the layout effect using pitch moment optimization efficiency and normal force optimization efficiency specifically includes the following steps: The optimization efficiency of normal force and pitch moment are represented as follows: Optimization efficiency of normal force ; Pitch moment optimization efficiency ; in, This represents the pitch moment disturbance caused by the optimized layout of the track control jet. This represents the pitch moment disturbance caused by the orbital control jet of the original nozzle layout. This represents the normal force disturbance caused by the optimized layout of the track control jet. This represents the normal force interference caused by the original nozzle layout and the track-controlled jet.

7. The nozzle layout method for reducing pitch interference moment as described in claim 6, characterized in that, It also includes the following steps: This means the layout design offers no optimization whatsoever. This indicates that the layout design has a negative impact. This indicates that the layout design has been optimized, and The smaller the representation, the higher the optimization efficiency of the layout design; The additional adverse effects of pitch on the layout design have completely disappeared. This means the layout design offers no optimization whatsoever. This indicates that the layout design has a negative impact. This indicates that the layout design has been optimized, and The larger the value, the higher the optimization efficiency of the layout design.

8. A layout apparatus for applying the nozzle layout method for reducing pitch disturbance moment according to any one of claims 1-7, characterized in that, include: The model building module is used to construct a three-dimensional model of an aircraft, which includes a blunt nose, a conical section, and a tail rudder. The three-dimensional model of the aircraft is equipped with an original orbital control nozzle. The jet direction of the original orbital control nozzle is perpendicular to the longitudinal axis of the projectile and the jet passes through the center of mass. The solution module is used to solve the jet interference flow field of the three-dimensional model of the aircraft under the target flight state using numerical simulation methods. Based on the jet interference flow field, the symmetry plane cloud map of the three-dimensional model of the aircraft is extracted and the head shock wave tilt angle is obtained from it. The rotating module is used to rotate the original orbital control nozzle into an inclined orbital control nozzle within the plane of symmetry of the aircraft, with the outlet center of the original orbital control nozzle as the rotation center. The expansion section outlet of the inclined orbital control nozzle is in contact with the upper edge of the projectile body. The rotation angle is determined according to the head shock wave tilt angle. The optimization and verification module is used to perform numerical simulation of the jet flow interference field of the inclined track control nozzle layout under the rotation angle, and to optimize and verify the layout effect by using pitch moment optimization efficiency and normal force optimization efficiency to ensure that the pitch interference moment is reduced and the jet flow normal control efficiency meets the standard.

9. A computer device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the nozzle layout method for reducing pitch interference torque as described in any one of claims 1 to 7.

10. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it implements the steps of the nozzle layout method for reducing pitch interference moment as described in any one of claims 1 to 7.

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