CN-115438534-B - Analysis method and device for pneumatic characteristics of remote tail control guided projectile

CN115438534BCN 115438534 BCN115438534 BCN 115438534BCN-115438534-B

Abstract

The invention discloses a method and a device for analyzing pneumatic characteristics of a remote tail control guided projectile. The method comprises the steps of carrying out physical modeling on a shell body of the shell to obtain a shell model, carrying out unstructured grid division on the shell model, setting boundary conditions, and carrying out aerodynamic characteristic analysis on the shell model based on the divided grids and the set boundary conditions to obtain the change rule of aerodynamic characteristics of the shell model along with flight Mach number and attack angle. The invention solves the technical problem of high control difficulty caused by high rotating speed of the high-rotation shell.

Inventors

LIU FUCHAO
WANG GUIQI
LIU NING
WANG LIANGMING
SU ZHONG
FU MENGYIN
DENG ZHIHONG
SHEN KAI

Assignees

北京信息科技大学
南京理工大学
北京理工大学

Dates

Publication Date: 20260508
Application Date: 20220809

Claims (6)

1.A method for analyzing aerodynamic characteristics of a remote tail-controlled guided projectile, comprising: performing physical modeling on the projectile body of the projectile to obtain a projectile model; Unstructured meshing is carried out on the shell model, and boundary conditions are set; Based on the divided grids and the set boundary conditions, carrying out aerodynamic characteristic analysis on the shell model to obtain the change rule of aerodynamic characteristics of the shell model along with flight Mach number and attack angle; The method comprises the steps of constructing a front cabin section of the shell model, constructing a spin-reducing stern of the shell model, wherein the spin-reducing stern is in non-hard connection with the front cabin section through a bearing device, and friction force on the bearing device can drive the spin-reducing stern to rotate so that the shell can reduce rotation after the shell of the shell exits a cavity; modeling a projectile body calculation domain of the projectile model, and performing grid division, wherein the closer to the projectile body, the denser the grid is, the sparser the grid is, and the denser the grid is, the more dense the grid is, and when the boundary condition is set, a density-based coupling explicit solver is selected for solving, and far-field boundary conditions and viscous boundary conditions are respectively selected for incoming flows and object planes; Before unstructured meshing of the shell model, the method further comprises the steps of determining a resistance coefficient expression and a lift coefficient expression of the shell model through an engineering calculation method, determining a continuity equation and a traffic equation of the shell model, and solving an energy equation of the shell model; The method comprises the steps of calculating resistance coefficients, lift coefficients and moment coefficients under different attack angles and different Mach angles, carrying out dynamic monitoring window analysis to obtain the change rules of the lift coefficients, the resistance coefficients and the moment coefficients of the shell model along with the flight Mach numbers and the attack angles, calculating X-direction velocity distribution cloud charts and shell surface pressure distribution cloud charts under different attack angles and different Mach angles, carrying out air-around shell flow condition window analysis to obtain the change rules of shock waves and shell surface pressure of the shell model along with the flight Mach numbers and the attack angles, and calculating final converged resistance, lift force and moment of the shell model, so as to carry out stress analysis of the shell model, and obtain the change rules of the stress of the shell model along with the flight Mach numbers and the attack angles.
2. The method of claim 1, wherein deriving a law of variation of lift coefficient, drag coefficient, and moment coefficient of the shell model with flight mach number and angle of attack comprises at least one of: under the condition of a certain attack angle, the resistance coefficient is continuously increased along with the increase of Mach number; Under the condition of a certain attack angle, the lift coefficient is continuously increased along with the increase of Mach number; under the condition of a certain attack angle, as the Mach number increases, the moment coefficient also increases continuously.
3. The method of claim 1, wherein deriving a variation law of shock and projectile surface pressure of the projectile model with flight mach number and angle of attack comprises at least one of: under the condition of a certain attack angle, the shock wave gradually decreases along with the rising of Mach number; under the condition of a certain attack angle, the pressure of the surface of the bullet gradually increases along with the increase of Mach number, wherein the pressure born by the bullet is the largest.
4. The method of claim 1, wherein deriving a law of variation of stress of the shell model with flight mach number and angle of attack comprises at least one of: Under the condition of a certain attack angle, the resistance is continuously increased along with the increase of the Mach number, and the upward lift degree is gradually changed from rapid to slow, but finally the upward trend is presented, and at the moment of a certain Mach number, the resistance is firstly decreased and then is increased to a peak value and then is decreased along with the increase of the attack angle, but the upward trend is presented overall; At a certain attack angle, the lift force is continuously increased along with the increase of the Mach number, wherein at the attack angle of 0 degrees, the increase rate is small, but the lift force coefficient is continuously increased along with the increase of the Mach number at the rest attack angles, and the larger the attack angle is, the faster the increase trend of the lift force coefficient is, at the moment of the Mach number, the lift force is continuously increased along with the increase of the attack angle, and the larger the Mach number is, the faster the increase trend of the lift force coefficient is; At a certain attack angle, the moment coefficient is continuously increased along with the increase of the Mach number, the increment difference value of the moment coefficient is gradually increased along with the increase of the attack angle, the larger the attack angle is, the faster the increase trend of the lift coefficient is, and at a certain Mach number, the moment coefficient is gradually increased along with the increase of the attack angle, and the lift degree is gradually slow.
5. The method according to any one of claims 1 to 4, characterized in that after deriving a law of variation of the aerodynamic properties of the projectile model with the mach number and angle of attack of the flight, the method further comprises manufacturing a despin guided projectile based on the law of variation.
6. An analysis device for pneumatic characteristics of a remote tail control guided projectile, comprising: the model construction module is used for carrying out physical modeling on the projectile body of the projectile to obtain a projectile model; The setting module is used for carrying out unstructured grid division on the shell model and setting boundary conditions; The analysis module is used for carrying out aerodynamic characteristic analysis on the shell model based on the divided grids and the set boundary conditions to obtain the change rule of the aerodynamic characteristics of the shell model along with the flight Mach number and attack angle; The model building module is further configured to build a front cabin section of the shell model, build a spin-reducing stern of the shell model, wherein the spin-reducing stern is not hard-connected with the front cabin section through a bearing device, and friction on the bearing device can drive the spin-reducing stern to rotate so that a shell of the shell can reduce rotation after the shell is out of a bore; The setting module is further configured to model a projectile body calculation domain of the projectile body model, and conduct grid division, wherein grids closer to the projectile body are denser, grids farther away from the projectile body are relatively sparse, and grids of a bullet head part are the denser; wherein prior to unstructured meshing of the shell model, the apparatus is further configured to determine drag coefficient expression and lift coefficient expression of the shell model by an engineering calculation method, determine continuity equation and traffic equation of the shell model, and solve energy equation of the shell model; the analysis module is further configured to calculate resistance coefficients, lift coefficients and moment coefficients under different attack angles and different machs to conduct dynamic monitoring window analysis to obtain change rules of the lift coefficients, the resistance coefficients and the moment coefficients of the shell model along with flight mach numbers and attack angles, calculate X-direction speed distribution cloud patterns and shell surface pressure distribution cloud patterns under different attack angles and different machs to conduct air flow around the shell to conduct window analysis to obtain change rules of shock waves and shell surface pressure of the shell model along with flight mach numbers and attack angles, and calculate final converged resistance, lift and moment of the shell model to conduct stress analysis of the shell model to obtain change rules of stress of the shell model along with flight mach numbers and attack angles.

Description

Analysis method and device for pneumatic characteristics of remote tail control guided projectile Technical Field The invention relates to the technical field of high dynamic navigation, in particular to a method and a device for analyzing pneumatic characteristics of a remote tail control guided projectile. Background In modern war, the projectile has become the killer and plays a vital role. The conventional guided projectile can keep higher rotating speed in flight, and how to reduce the rotating speed and improve the precision is a currently studied hot problem. In the prior art, the dynamic characteristics of the end trajectory of the seal control bullet umbrella system are researched by utilizing a multi-rigid-body dynamics method, so that the end trajectory of the seal control bullet meets the design requirement, and the seal control bullet can be reduced to an ideal value by the rotation reducing blades. In addition, the prior art provides a rolling motion stabilization area and a rotation reduction strategy suitable for the electromagnetic emission ultra-high speed guided projectile, and the active rotation and rotation reduction and swing stop control strategy provides a novel and feasible method for the electromagnetic emission ultra-high speed guided projectile flight control. However, these prior arts have a problem of a high control difficulty caused by a high rotational speed of the high-rotation guided projectile. In view of the above problems, no effective solution has been proposed at present. Disclosure of Invention The embodiment of the invention provides a method and a device for analyzing pneumatic characteristics of a remote tail control guided projectile, which are used for at least solving the technical problem of high control difficulty caused by high rotating speed of the high-rotation guided projectile. According to one aspect of the embodiment of the invention, the analysis method for the aerodynamic characteristics of the remote tail control guided projectile comprises the steps of carrying out physical modeling on the projectile body of the projectile to obtain a projectile model, carrying out unstructured grid division on the projectile model and setting boundary conditions, and carrying out aerodynamic characteristic analysis on the projectile model based on the divided grids and the set boundary conditions to obtain the change rule of the aerodynamic characteristics of the projectile model along with flight Mach number and attack angle. According to one aspect of the embodiment of the invention, the analysis device for the aerodynamic characteristics of the remote tail control guided projectile comprises a model construction module, a setting module and an analysis module, wherein the model construction module is used for carrying out physical modeling on the projectile body of the projectile to obtain a projectile model, the setting module is used for carrying out unstructured grid division on the projectile model and setting boundary conditions, and the analysis module is used for carrying out aerodynamic characteristic analysis on the projectile model based on the divided grids and the set boundary conditions to obtain the change rule of the aerodynamic characteristics of the projectile model along with flight Mach number and attack angle. According to the embodiment of the invention, the projectile body of the projectile is subjected to physical modeling to obtain the projectile model, unstructured grid division is carried out on the projectile model, boundary conditions are set, aerodynamic characteristic analysis is carried out on the projectile model based on the divided grids and the set boundary conditions, and the change rule of the aerodynamic characteristics of the projectile model along with the flight Mach number and attack angle is obtained, so that the technical problem of high control difficulty caused by high rotation speed of the high rotation guided projectile is solved. Drawings The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application and do not constitute an undue limitation of the application. In the drawings: FIG. 1 is a schematic illustration of a physical shell model according to an embodiment of the present invention; FIG. 2 is a flow chart of a method of analyzing aerodynamic characteristics of a remote tail control lead projectile in accordance with an embodiment of the invention; FIG. 3 is a flow chart of another method of analyzing aerodynamic characteristics of a remote tail control lead projectile in accordance with an embodiment of the invention FIG. 4 is a schematic illustration of a computational domain and meshing according to an embodiment of the present invention; FIG. 5 is a schematic illustration of meshing around a