Search

CN-121859428-B - Design method, device, equipment and medium of supersonic speed point sink spray pipe

CN121859428BCN 121859428 BCN121859428 BCN 121859428BCN-121859428-B

Abstract

The application belongs to the technical field of spray pipe design, and relates to a design method, a device, equipment and a medium of a supersonic speed point sink spray pipe. The method comprises the steps of obtaining design parameters of a supersonic speed point-sink spray pipe, obtaining a point-sink flow control equation, a characteristic line equation and a compatibility equation of supersonic speed flow, obtaining a left characteristic line of a spray pipe outlet and a right characteristic line of a spray pipe throat by adopting an improved Euler method, obtaining a point-sink spray pipe flow field by taking the left characteristic line of the spray pipe outlet, the right characteristic line of the spray pipe throat and a symmetrical axis of the spray pipe as boundary conditions and adopting a characteristic line method, obtaining a supersonic speed profile of the supersonic speed point-sink spray pipe by adopting mass conservation along the right characteristic line of the spray pipe throat in the obtained point-sink spray pipe flow field, designing a contraction section of the supersonic speed point-sink spray pipe, connecting with the supersonic speed profile of the supersonic speed point-sink spray pipe, and correcting to obtain the supersonic speed viscous point-sink spray pipe. The application can provide supersonic speed sink flow.

Inventors

  • ZHANG BO
  • ZHAO YUXIN
  • LU XIAOGE
  • YU HUANG

Assignees

  • 中国人民解放军国防科技大学

Dates

Publication Date
20260512
Application Date
20250707

Claims (10)

  1. 1. The design method of the supersonic speed sink spray pipe is characterized by comprising the following steps of: Obtaining design parameters of the supersonic speed point sink spray pipe, and obtaining a point sink flow control equation by mass conservation; obtaining a left-going characteristic line of an outlet of the spray pipe by adopting an improved Euler method according to a point sink flow control equation, a characteristic line equation and a compatibility equation; taking a left-going characteristic line of a spray pipe outlet, a right-going characteristic line of a spray pipe throat and a symmetrical axis of the spray pipe as boundary conditions, and obtaining a converging spray pipe flow field by adopting a characteristic line method; In the obtained flow field of the point converging spray pipe, along the right characteristic line of the throat part of the spray pipe, adopting mass conservation to obtain the supersonic velocity profile of the supersonic velocity point converging spray pipe; The method comprises the steps of designing a contraction section of a supersonic speed sink spray pipe, connecting the contraction section with a supersonic speed profile of the supersonic speed sink spray pipe to obtain a non-sticky sink spray pipe, and carrying out viscosity correction on the non-sticky sink spray pipe to obtain the supersonic speed sticky sink spray pipe.
  2. 2. The method for designing a supersonic sink nozzle according to claim 1, wherein obtaining design parameters of the supersonic sink nozzle and obtaining a sink flow control equation from mass conservation comprises: Obtaining design parameters of a supersonic speed point sink spray pipe, and obtaining a mass conservation equation by mass conservation; and obtaining parameters of the converging flow field by isentropic of the converging flow, and substituting the parameters into a mass conservation equation to obtain a converging flow control equation.
  3. 3. The method for designing a supersonic converging nozzle according to claim 2, wherein the method for designing the supersonic converging nozzle comprises the steps of obtaining converging flow field parameters from isentropic of converging flow, substituting the parameters into a mass conservation equation to obtain a converging flow control equation, and comprising the following steps: Isentropic of the point sink flow is used for obtaining the point sink flow field parameters: ; ; ; ; ; In the formula, For the static temperature, the temperature of the liquid crystal is equal to the static temperature, For the total temperature to be the same, Is a static pressure, and is used for controlling the pressure, As the total pressure of the liquid is to be taken, Is the specific heat ratio of the gas, Is a mach number and is used to determine, Is a gas constant which is a function of the gas, Is the sound velocity; substituting the parameters of the converging flow field into a mass conservation equation to obtain a relation between Mach number and radius: ; And obtaining a point convergence flow control equation according to the relation between Mach number and radius: ; In the formula, In the form of a radial coordinate, For radial coordinates in the critical state, In order to achieve a gas flow density, For the gas flow density to be in the critical state, For the x-direction velocity of the air flow, For the x-direction velocity of the gas flow in the critical state, In the first place of the position, The position is the second position and is used for the second position, Is the mach number of the location one, Mach number for position two.
  4. 4. A method for designing a supersonic sink nozzle according to any one of claims 1 to 3, wherein obtaining design parameters of the supersonic sink nozzle to obtain a characteristic line equation and a compatibility equation of the supersonic flow comprises: ; ; In the formula, Is an air flow The velocity component of the direction is used, Is an air flow The velocity component of the direction is used, Is the speed of sound, As the slope of the characteristic line, In order for the angle of flow to be the same, Is Mach angle.
  5. 5. The method for designing a supersonic converging nozzle according to any one of claims 1 to 3, wherein the method for obtaining a left-hand characteristic line of the nozzle outlet by using an improved euler method according to a converging flow control equation, a characteristic line equation and a compatibility equation, and the method for obtaining a right-hand characteristic line of the nozzle throat by using an improved euler method according to a converging flow control equation, a characteristic line equation and a compatibility equation comprises the steps of: According to a point convergence flow control equation, a characteristic line equation and a compatibility equation, combining the Mach number of the outlet of the spray pipe, and adopting an improved Euler method to obtain a left-going characteristic line of the outlet of the spray pipe; and according to a point convergence flow control equation, a characteristic line equation and a compatibility equation, combining the Mach number of the throat of the spray pipe, and adopting an improved Euler method to obtain the right-going characteristic line of the throat of the spray pipe.
  6. 6. A method of designing a supersonic sink nozzle according to any one of claims 1 to 3, wherein designing the convergent section of the supersonic sink nozzle comprises: ; In the formula, In the form of an x-axis coordinate, In order to constrict the inlet height of the section, For the throat height, the air flow is the throat height, In the form of a radial coordinate, For the contracted segment length.
  7. 7. A method of designing a supersonic sink nozzle according to any one of claims 1 to 3, wherein the viscosity modification of the non-viscous sink nozzle comprises: ; In the formula, In order to correct the coordinates of the sticking surface of the rear nozzle, The coordinates of the non-sticky surface of the spray pipe are obtained; for the thickness of the displacement, Is a wall angle of a non-sticky surface.
  8. 8. A design device of supersonic speed point sink nozzle, characterized by comprising: the system comprises a first module, a second module, a third module, a fourth module, a fifth module, a sixth module, a seventh module and a fourth module, wherein the first module is used for obtaining design parameters of the supersonic speed sink spray pipe and obtaining a sink flow control equation by mass conservation; The second module is used for obtaining a left-going characteristic line of the nozzle outlet by adopting an improved Euler method according to the point convergence flow control equation, the characteristic line equation and the compatibility equation; The third module is used for obtaining a point convergence spray pipe flow field by taking a spray pipe outlet left-going characteristic line, a spray pipe throat right-going characteristic line and a symmetrical axis of the spray pipe as boundary conditions and adopting a characteristic line method; the fourth module is used for obtaining the supersonic velocity profile of the supersonic velocity point sink spray pipe by adopting mass conservation along the right-going characteristic line of the spray pipe throat in the obtained point sink spray pipe flow field; and the fifth module is used for designing a contraction section of the supersonic speed converging spray pipe, connecting the contraction section with the supersonic speed profile of the supersonic speed converging spray pipe to obtain a non-sticky converging spray pipe, and carrying out viscosity correction on the non-sticky converging spray pipe to obtain the supersonic speed sticky converging spray pipe.
  9. 9. A computer device comprising a memory and a processor, the memory storing a computer program, characterized in that the processor implements the steps of the method of any of claims 1 to 7 when the computer program is executed.
  10. 10. A computer readable storage medium, on which a computer program is stored, characterized in that the computer program, when being executed by a processor, implements the steps of the method of any of claims 1 to 7.

Description

Design method, device, equipment and medium of supersonic speed point sink spray pipe Technical Field The application relates to the technical field of spray pipe design, in particular to a design method, a device, equipment and a medium of a supersonic speed point sink spray pipe. Background The warhead front window is critical for high-speed aircraft. For example, the front window can be used for optical detection, target searching, tracking and identifying, the front window can be used for infrared detection, capturing infrared radiation of targets, finding and tracking the targets by utilizing the infrared temperature difference between the targets and the surrounding environment, and the front window can be used for radar detection, transmitting and receiving radar waves, so that an aircraft can range, speed and position the targets in complex weather and electromagnetic environments. As the speed of high-speed aircraft increases, the greater the bullet is subjected to air friction, the higher the temperature. At different altitudes, the temperature is basically between 200K and 300K, but with the increase of the Mach number of the aircraft, the flow of the front edge of the warhead is stagnant, and the total temperature is rapidly increased, and the temperature of the front edge of the warhead of the aircraft can reach 1500K by taking Mach 6 as an example. The front window cannot directly bear the high temperature caused by high-speed flow, which can lead to the heat damage of structures such as optical window glass and the like, and therefore, the front window needs to be cooled. The supersonic air film has good blocking effect on high heat inflow because of low temperature, high speed and high momentum, and the cooling process does not influence the optical, infrared and radar performances of the front window, so that the supersonic air film becomes the optimal scheme for cooling the front window of the warhead of the high-speed aircraft. The supersonic gas film needs to be provided using a supersonic nozzle. Through the development of the supersonic jet pipe in the last century, the basic theory and method of jet pipe design are continuously updated and improved, the existing design method has good precision, high technical maturity and wide engineering application. In the prior art, the conventional design method of the supersonic velocity spray pipe comprises the steps of adopting an arbitrary spray pipe profile design method (such as transonic third-order progressive solution), designing a reference spray pipe, adopting a characteristic line method, and carrying out flow field reverse design to obtain a non-sticky profile of the reference spray pipe, adopting a reference temperature method and a fourth-order Dragon-Gerdostat method, solving a normal differential equation set to obtain thickness distribution of a boundary layer along the spray pipe profile, and designing the obtained supersonic velocity air film spray pipe profile as shown in figure 1. However, as shown in fig. 2, for the front window of the warhead, the air film flow direction points to the center point of the warhead (as shown by the arrow direction in fig. 2), which is essentially a supersonic sink flow in physics, no document currently discloses a supersonic jet design method to realize supersonic sink flow, and in addition, as can be seen from fig. 2, the x-axis is the rotating axis of the warhead, the r-axis is radial, the coordinate system is different from the existing supersonic jet design method, and the flow direction is different from the existing supersonic jet design method, so that the design method of the supersonic sink jet is different from the existing supersonic jet design method. In conclusion, the existing supersonic jet pipe design method cannot realize supersonic converging flow and is not suitable for cooling a bullet front view window. Disclosure of Invention Based on the above, it is necessary to provide a method, a device, equipment and a medium for designing a supersonic sink nozzle, which can design the supersonic sink nozzle, provide a supersonic sink flow, be used for cooling a forward-looking optical window of an aircraft warhead, and can meet the cooling requirement of the warhead forward-looking window. A design method of a supersonic speed point sink spray pipe comprises the following steps: Obtaining design parameters of the supersonic speed point sink spray pipe, and obtaining a point sink flow control equation by mass conservation; obtaining a left-going characteristic line of an outlet of the spray pipe by adopting an improved Euler method according to a point sink flow control equation, a characteristic line equation and a compatibility equation; taking a left-going characteristic line of a spray pipe outlet, a right-going characteristic line of a spray pipe throat and a symmetrical axis of the spray pipe as boundary conditions, and obtaining a converging spray pipe flow field by adopting