CN-121997451-A - Nozzle layout method, device, equipment and medium for weakening pitching interference moment

CN121997451ACN 121997451 ACN121997451 ACN 121997451ACN-121997451-A

Abstract

The invention provides a nozzle layout method, device, equipment and medium for weakening pitching interference moment, the method comprises the steps of establishing an aircraft three-dimensional model, arranging an original rail control nozzle on the aircraft three-dimensional model, solving a jet flow interference flow field of the aircraft three-dimensional model in a target flight state, extracting a symmetrical plane cloud image of the aircraft three-dimensional model, obtaining a head laser inclination angle from the cloud image, rotating the original rail control nozzle in the symmetrical plane of the aircraft by taking the outlet center of the original rail control nozzle as a rotation center, forming an inclined rail control nozzle, wherein the rotation angle is determined according to the head laser inclination angle, carrying out jet flow interference flow field numerical simulation on the inclined rail control nozzle layout under the rotation angle, optimizing and verifying layout effect by adopting pitching moment optimizing efficiency and normal force optimizing efficiency, ensuring that pitching interference moment is reduced, and the jet flow normal control efficiency reaches the standard, so as to solve the problems of overlarge control capacity of the rail control jet flow and reduced control stability.

Inventors

LI YAN
LIU YUWEI
MA JIKUI
LI KANGKANG
LIU YAOFENG

Assignees

中国航天空气动力技术研究院

Dates

Publication Date: 20260508
Application Date: 20251225

Claims (10)

1. A nozzle placement method for reducing pitch disturbance moment, comprising the steps of: establishing an aircraft three-dimensional model comprising a blunt end, a cone section and a tail rudder, wherein an original rail control spray pipe is arranged on the aircraft three-dimensional model, the jet flow direction of the original rail control spray pipe is perpendicular to the longitudinal axis of the projectile body, and the jet flow passes through the center of mass; solving a jet flow interference flow field of the three-dimensional model of the aircraft in a target flight state by adopting a numerical simulation method, extracting a cloud image of a symmetrical plane of the three-dimensional model of the aircraft based on the jet flow interference flow field, and obtaining a head laser dip angle from the cloud image; The method comprises the steps that an outlet center of an original rail control spray pipe is taken as a rotation center, the original rail control spray pipe is rotated in a symmetrical plane of an aircraft to form an inclined rail control spray pipe, an outlet of an expansion section of the inclined rail control spray pipe is attached to the upper edge of a projectile body, and the rotation angle is determined according to the inclination angle of a shock wave; And carrying out jet flow interference flow field numerical simulation on the layout of the inclined rail control jet pipe under the rotation angle, and carrying out optimization verification on the layout effect by adopting pitching moment optimization efficiency and normal force optimization efficiency, so as to ensure that the pitching interference moment is reduced and the jet flow normal control efficiency reaches the standard.
2. The nozzle layout method for weakening pitching interference moment according to claim 1, wherein the jet flow interference flow field of the three-dimensional model of the aircraft in the target flight state is solved by adopting a numerical simulation method, and based on the jet flow interference flow field, a cloud image of a symmetry plane of the three-dimensional model of the aircraft is extracted and a head laser inclination angle is obtained, and the method specifically comprises the following steps: Solving a jet flow interference flow field of the three-dimensional model of the aircraft in a target flight state by adopting a data simulation method for solving a three-dimensional compressible Navier-Stokes equation, and outputting speed and pressure information of the jet flow interference flow field; Generating a flow field cloud picture of a symmetrical plane of the three-dimensional model of the aircraft based on the speed and pressure information; And calculating the included angle between the head shock wave and the longitudinal axis of the projectile body by identifying the boundary contour of the head shock wave in the flow field cloud picture, so as to obtain the head shock wave inclination angle.
3. The nozzle layout method for weakening the pitching interference moment according to claim 2, wherein the method for solving the jet interference flow field of the three-dimensional model of the aircraft in the target flight state by adopting a data simulation method for solving a three-dimensional compressible Navier-Stokes equation outputs speed and pressure information of the jet interference flow field, and specifically comprises the following steps: determining a three-dimensional compressible Navier-Stokes equation: ; Wherein Q is a conservation variable, F, G, H is a non-sticky flux vector in three directions of a coordinate system x, y and z, F v 、G v 、H v is a sticky flux vector in three directions of the coordinate system x, y and z, t is time, x is a coordinate system flow direction, y is a coordinate system normal direction, and z is a coordinate system circumferential direction; the coordinate system adopts a three-dimensional Cartesian rectangular coordinate system, and a coordinate origin is selected as a midpoint of the front edge of the three-dimensional model of the aircraft; Solving the three-dimensional compressible Navier-Stokes equation to obtain a conservation variable Q, wherein the expression is as follows: ; Wherein ρ represents density, u, v, w represent flow direction velocity, normal velocity, and circumferential velocity, respectively, and E represents fluid energy per unit mass; and extracting speed and pressure information of the jet flow interference flow field through a conservation variable Q.
4. A method of nozzle placement for damping pitch disturbance moment according to claim 3, wherein said solving said three-dimensional compressible Navier-Stokes equation comprises the steps of: Solving the three-dimensional compressible Navier-Stokes equation by fluid simulation software; The time discrete format can be USGS, the space discrete format can be Roe format, and the turbulence model can be S-A model.
5. The method for nozzle placement for damping pitch disturbance moment according to claim 1, wherein said rotation angle is determined based on a bow shock tilt angle, comprising the steps of: The ratio of the rotation angle to the shock wave tilt angle of the head is within the range of 0-1.
6. The nozzle placement method for reducing pitch disturbance moment according to claim 1, wherein the optimization verification of the placement effect by using pitch moment optimization efficiency and normal force optimization efficiency comprises the following steps: the characterization normal force optimization efficiency and the pitching moment optimization efficiency are respectively expressed as follows: normal force optimization efficiency ; Pitching moment optimization efficiency ; Wherein, the Representing the pitch moment disturbance caused by the optimally distributed rail-controlled jets, Representing pitch moment disturbance caused by the original jet pipe layout rail control jet flow, Representing the normal force disturbance caused by the optimally placed rail-controlled jets, Representing the normal force disturbance caused by the rail-controlled jet of the original jet pipe layout.
7. The method of nozzle placement for damping pitch disturbance moment according to claim 6, further comprising the steps of: no optimization is performed on the representative layout design; Representing layout design to have adverse effects; Representing layout design produces an optimization effect, and The higher the optimization efficiency representing smaller layout designs; the additional pitch adverse disturbances representing the layout design completely disappear, No optimization is performed on the representative layout design; Representing layout design to have adverse effects; Representing layout design produces an optimization effect, and The higher the optimization efficiency representing a larger layout design.
8. A layout device applying the nozzle layout method for reducing pitching moment according to any one of claims 1 to 7, comprising: The model building module is used for an aircraft three-dimensional model comprising a blunt end, a cone section and a tail rudder, wherein an original rail control spray pipe is arranged on the aircraft three-dimensional model, the jet flow direction of the original rail control spray pipe is perpendicular to the longitudinal axis of the projectile body, and the jet flow passes through the mass center; The solving module is used for solving a jet flow interference flow field of the three-dimensional model of the aircraft in a target flight state by adopting a numerical simulation method, extracting a cloud image of a symmetrical plane of the three-dimensional model of the aircraft based on the jet flow interference flow field, and obtaining a head laser wave inclination angle from the cloud image; The rotating module is used for rotating the original rail control spray pipe in the plane of symmetry of the aircraft by taking the outlet center of the original rail control spray pipe as a rotating center to form an inclined rail control spray pipe, wherein the outlet of an expansion section of the inclined rail control spray pipe is attached to the upper edge of the projectile body, and the rotating angle is determined according to the inclination angle of the shock wave; And the optimization verification module is used for carrying out jet flow interference flow field numerical simulation on the layout of the inclined rail control jet pipe under the rotation angle, carrying out optimization verification on the layout effect by adopting pitching moment optimization efficiency and normal force optimization efficiency, and ensuring that the pitching interference moment is reduced and the jet flow normal control efficiency reaches the standard.
9. A computer device comprising a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the processor implements the method of nozzle placement for damping pitch disturbance moment according to any one of claims 1to 7 when executing the computer program.
10. A computer readable storage medium storing a computer program, wherein the computer program when executed by a processor implements the steps of the nozzle placement method of reducing pitch disturbance moment according to any one of claims 1 to 7.

Description

Nozzle layout method, device, equipment and medium for weakening pitching interference moment Technical Field The present invention relates to the field of flow control technologies, and in particular, to a method, an apparatus, a device, and a medium for nozzle placement for reducing pitching interference moment. Background The jet flow control technology is a pneumatic control technology for changing the flight track or the gesture of the aircraft through the reaction force generated by jet flow, can be applied to the aircraft with wide speed range and large airspace, and has the advantages of high control precision, high response speed, no influence of atmospheric environment and the like. The future flight range of the new high-speed aircraft involves low to high altitudes, covering dense to rarefied atmospheric environments. The jet flow control technology is widely applied to the field of high-speed aircraft control due to the advantages, so that the aircraft can achieve the effects of high-precision control and quick response, and is one of key technologies for high-speed aircraft research. When the flow of the rail control engine becomes large, jet flow and incoming flow can generate large interference moment, and the method of arranging the attitude control engine at a position far away from the mass center is generally adopted at home and abroad to control so as to reduce the interference moment generated by the rail control. However, under certain conditions (such as the flight conditions that jet flows directly face the wind, low altitude and high Mach number), the rail-controlled jet flow has overlarge disturbance moment, the control capability of the attitude control engine is insufficient, and the control stability is reduced. Therefore, a nozzle layout method for weakening pitching interference moment is needed to solve the technical problems of overlarge track control jet flow interference moment, insufficient control capability of a gesture control engine and reduced control stability. Disclosure of Invention In order to overcome the problems in the related art, the present disclosure provides a nozzle layout method, device, equipment and medium for weakening pitch disturbance moment, so as to solve the technical problems of overlarge rail control jet disturbance moment, insufficient control capability of a gesture control engine and reduced control stability in the related art. One or more embodiments of the present disclosure provide a nozzle placement method for reducing pitch disturbance moment, including the steps of: establishing an aircraft three-dimensional model comprising a blunt end, a cone section and a tail rudder, wherein an original rail control spray pipe is arranged on the aircraft three-dimensional model, the jet flow direction of the original rail control spray pipe is perpendicular to the longitudinal axis of the projectile body, and the jet flow passes through the center of mass; solving a jet flow interference flow field of the three-dimensional model of the aircraft in a target flight state by adopting a numerical simulation method, extracting a cloud image of a symmetrical plane of the three-dimensional model of the aircraft based on the jet flow interference flow field, and obtaining a head laser dip angle from the cloud image; The method comprises the steps that an outlet center of an original rail control spray pipe is taken as a rotation center, the original rail control spray pipe is rotated in a symmetrical plane of an aircraft to form an inclined rail control spray pipe, an outlet of an expansion section of the inclined rail control spray pipe is attached to the upper edge of a projectile body, and the rotation angle is determined according to the inclination angle of a shock wave; And carrying out jet flow interference flow field numerical simulation on the layout of the inclined rail control jet pipe under the rotation angle, and carrying out optimization verification on the layout effect by adopting pitching moment optimization efficiency and normal force optimization efficiency, so as to ensure that the pitching interference moment is reduced and the jet flow normal control efficiency reaches the standard. Preferably, the method for solving the jet flow interference flow field of the three-dimensional model of the aircraft in the target flight state by adopting a numerical simulation method extracts a cloud image of a symmetry plane of the three-dimensional model of the aircraft and obtains a head laser wave inclination angle from the cloud image based on the jet flow interference flow field, and specifically comprises the following steps: Solving a jet flow interference flow field of the three-dimensional model of the aircraft in a target flight state by adopting a data simulation method for solving a three-dimensional compressible Navier-Stokes equation, and outputting speed and pressure information of the jet flow interference flow field; Generating a