CN114218824A - Parafoil fluid-solid coupling numerical simulation method based on compressible flow immersion boundary method - Google Patents
Parafoil fluid-solid coupling numerical simulation method based on compressible flow immersion boundary method Download PDFInfo
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Abstract
The invention discloses a parafoil fluid-solid coupling numerical simulation method based on a compressible flow immersion boundary method, which comprises the steps of establishing a space background grid and a parafoil flow field grid, embedding the parafoil grid into the space background grid, carrying out grid encryption near the parafoil position, determining the intersection condition of the parafoil grid and the space background grid by a geometric intersection method, generating a structure finite element grid of the parafoil and establishing a corresponding relation with the parafoil flow field grid; solving a compressible Navier-Stokes equation on a spatial background grid by using a finite volume method, wherein in the process of boundary conditions, the parafoil adopts a non-slip wall boundary condition, and a FIVER method is adopted to calculate a one-dimensional half Riemann problem to obtain flux on the parafoil boundary; the calculated aerodynamic force of the flow field acts on the parafoil, the structural deformation and the movement of the parafoil are solved by a nonlinear structure dynamics finite element method, and the position of the parafoil grid is updated; analytical studies of the working process of parafoil provide an important reference.
Description
Technical Field
The invention relates to a fluid-solid coupling numerical simulation technology, in particular to a parafoil fluid-solid coupling numerical simulation method based on a compressible flow immersion boundary method.
Background
The parachute is the most common pneumatic speed reducer at present, has wide application in the fields of national defense construction, scientific research, economic construction, sports and the like, and is important equipment for ensuring safe landing of personnel and materials particularly in the aspects of safe return and entrance of a spacecraft, accurate airborne landing and air-drop and the like. With the development of aerospace technology, higher demands are being made on parachutes, with parafoils gaining increased attention for their excellent glide performance and maneuverability. Therefore, the research of the parafoil plays an important role in the development of the aviation field in China.
The parafoil is made of flexible fabric, is in a folded state at the initial stage of the working process, then starts to be inflated and unfolded in the air, and generates huge shape change, and the pneumatic characteristics are also greatly changed in the inflating and unfolding process. After the material is filled, the material reaches a force balance state through the change of the posture and the speed, and then further enters a stable gliding state. And finally, decelerating the sparrow to descend.
The existing research method of the parafoil comprises a test method, a theoretical model and numerical simulation. The test method, particularly the airdrop test, gives the true working and performance of the parafoil, but this method is expensive and time consuming and laborious. The theoretical model is obtained by combining the past experimental data and simplifying the theoretical model according to the actual situation. As the working process of the parafoil relates to the very complicated problem of large deformation unsteady fluid-solid coupling of the flexible fabric, the effect of a theoretical model is relatively limited. The numerical simulation method established with the development of computer technology has gradually become one of the main methods of parafoil analysis and calculation.
Because the working process of the parafoil involves the very complicated problem of large deformation and unsteady fluid-solid coupling of the flexible fabric, the skin-grid method is almost completely ineffective. In particular, parafoils, unlike conventional objects, are considered "zero thickness" objects, which present great difficulties for numerical simulation. The background grid of the dipping boundary method is kept unchanged during the motion of the object, so that the method has great advantages in processing the problem of large deformation unsteady fluid-solid coupling. However, conventional studies have generally considered cases of low-speed incompressible fluids and medium-low reynolds numbers. Therefore, a parafoil fluid-solid coupling numerical simulation method based on a compressible flow immersion boundary method needs to be researched.
Disclosure of Invention
In order to simulate the problem of large-deformation unsteady fluid-solid coupling of the parafoil, the invention provides a parafoil fluid-solid coupling numerical simulation method based on a compressible flow immersion boundary method, aiming at numerically simulating large-deformation unsteady motion of the parafoil by the compressible flow immersion boundary method and providing an effective tool for designing and analyzing the parafoil.
A parafoil fluid-solid coupling numerical simulation method based on a compressible flow immersion boundary method comprises the following steps:
step one, establishing a flow field grid of the surface and the space area of the parafoil;
determining the intersection condition of the parafoil surface grid and the three-dimensional space background grid according to the geometric relationship;
step three, establishing a structural finite element grid of the parafoil, and selecting triangular or quadrilateral units to divide the grid of the parafoil;
establishing a corresponding relation between a parafoil flow field grid and a parafoil structure grid;
step five, setting initial conditions of numerical simulation according to the calculation state of the problem;
step six, using a compressible Navier-Stokes equation on a finite volume method discrete space background grid, directly calculating numerical flux for a non-boundary grid, and for the space background grid intersected with the parafoil surface grid, solving the following one-dimensional half Riemann problem in a local area of the grid by adopting a FIVER method:
wherein the content of the first and second substances,
the grid points of the flow field close to the surface of the parafoil are along the local normal direction of the parafoil
The state of the flow field of (a),
xi is a one-dimensional local normal direction coordinate pointing into the object, i.e. along
The direction of the light beam is changed,
is the speed of movement, Δ t, of the parafoil structural latticenRepresenting a current time step; the solution to the one-dimensional half Riemann problem is used to calculate wall flux, thereby achieving wall boundary conditions;
step seven, performing time advancing on the space background grid to obtain the flow field state of the next time step, and calculating the flow field aerodynamic force on the boundary of the parafoil;
step eight, applying flow field aerodynamic force to the parafoil structure, and obtaining structural deformation and movement of the parafoil through a nonlinear structure dynamic finite element method;
step nine, updating the flow field surface grid of the parafoil by using the structural deformation and the motion of the parafoil, and recalculating the intersection condition of the parafoil surface grid and the space background grid;
step ten, returning to the process of the step six to calculate the flow field state until the fluid-solid coupling calculation process reaches the required time step.
As a preferred technical solution, the first step further includes: for the shape of the parafoil, selecting triangular units to perform mesh division on the parafoil geometric model to generate a certain number of parafoil surface mesh units; carrying out meshing division on a space region by adopting a tetrahedral unit, establishing a space background mesh, and carrying out mesh encryption near the initial position of the parafoil;
preferably, the tetrahedral units used in the spatial background mesh in step one are completely butted, that is, adjacent tetrahedral units have completely corresponding triangular common planes.
As a preferable technical solution, the grid encryption in the step one is performed in a local space near the initial position of the parafoil, the size of the local space grid after encryption is equivalent to that of the parafoil surface grid, and the space grid and the parafoil surface grid do not need to be consistent.
As a preferred technical scheme, the parafoil flow field mesh and the parafoil structural mesh in the fourth step do not need a strict correspondence, and a correspondence is established by a correspondence algorithm to satisfy energy conservation of a fluid-solid coupling interface.
As a preferable technical scheme, a compressible Navier-Stokes equation is adopted in the sixth step, the change of density is considered, the strong discontinuity conditions including shock waves and the like are considered, the method can be used for laminar flow and turbulent flow conditions, a Spalart-Allmoras turbulence model is used for calculating the turbulent flow conditions, and direct calculation or wall functions are used according to the size of a local space grid.
As a preferred technical solution, the cover method in step six is used for calculating the parafoil shape once on both sides of the parafoil surface mesh, respectively, for processing the zero thickness characteristic specific to the parafoil mesh.
Preferably, the nonlinear structure dynamic finite element method in the step eight adopts the membrane unit to process the fabric material characteristics of the parafoil.
Compared with the prior art, the invention has the beneficial effects that:
(1) the problem of large deformation unsteady flow fixed coupling of the parafoil is numerically simulated by a compressible flow immersion boundary method, and compared with other numerical simulation methods, the method overcomes the limitation that the complex large deformation unsteady flow movement of the parafoil cannot be simulated by the conventional numerical simulation method;
(2) the problem of large deformation unsteady flow-solid coupling of the parafoil is numerically simulated by a compressible flow immersion boundary method, and the working process of the parafoil can be analyzed more efficiently and quickly compared with a test method;
(3) the invention has no limit to the structure of the parafoil and has wide applicability;
(4) the method adopts a compressible flow solving method, and can be used for calculating the high-speed flow problem compared with an incompressible numerical simulation method.
Drawings
FIG. 1 is a flow chart of a parafoil fluid-solid coupling numerical simulation method of a compressible flow immersion boundary method provided by the invention;
fig. 2 is a spatial background grid composed of tetrahedral cells.
Detailed Description
Embodiments of the present invention are described in further detail below with reference to the accompanying drawings.
The method utilizes the advantages of the immersion boundary method in the aspect of nonlinear large-deformation fluid-solid coupling simulation to process the problem of the fluid-solid coupling of the parafoil, and provides important reference for the design and analysis of the parafoil.
Referring to fig. 1, the present embodiment provides a parafoil fluid-solid coupling numerical simulation method based on a compressible flow immersion boundary method, which specifically includes:
establishing flow field grids of the parafoil surface and the space region, selecting triangular units for carrying out grid division on a parafoil geometric model for the parafoil appearance, determining the required grid number based on the local characteristics of the parafoil, and generating a certain number of parafoil surface grid units, wherein the parafoil surface grid has the characteristic of zero thickness. And (4) carrying out meshing on the flow field space region by adopting a tetrahedral unit to establish a space background mesh. Unlike the case of a tessellated mesh, tetrahedral cells fill the entire computational space without voids. And the grid encryption is carried out in the local space near the parafoil initial position, the size of the space grid after encryption is equivalent to that of the parafoil surface flow field grid, the space grid and the parafoil surface grid do not need to be consistent, and as shown in figure 2, the grid size of the near-far field area is gradually increased.
And step two, determining the intersection condition of the parafoil surface mesh and the three-dimensional space background mesh according to the geometric relationship, wherein the intersection relationship of the triangle and the tetrahedron is searched because the surface mesh is a triangle and the space background mesh is a tetrahedron.
And step three, establishing a structural finite element grid of the parafoil, and selecting triangular or quadrilateral units to divide the grid of the parafoil.
And fourthly, establishing a corresponding relation between the parafoil flow field grid and the parafoil structure grid, wherein the parafoil flow field grid and the parafoil structure grid do not need a strict corresponding relation, and the corresponding relation is established by a corresponding algorithm to meet the energy conservation of a fluid-solid coupling interface.
And step five, setting initial conditions of numerical simulation according to the calculation state of the problem. Taking the original shape of the parafoil as a rigid body to carry out pure fluid steady simulation, and taking the obtained state as the initial condition of unsteady simulation.
And sixthly, using a compressible Navier-Stokes equation on the grid point format finite volume method discrete space background grid, considering the change of density, including the situation of shock wave and other strong discontinuity, directly calculating the numerical flux by using direct calculation or a wall function for a non-boundary space grid according to the size of a local space grid, calculating the convection flux of the space grid by adopting a windward format, and calculating the flow field gradient for reconstruction and viscous flux calculation by adopting a Green-Gauss method. For the turbulence situation calculation a Spalart-almaras turbulence model was used. For the boundary grid, the far-field boundary employs a non-reflective boundary condition. For a spatial background grid intersected with a parafoil surface grid, solving the following one-dimensional half Riemann problem in a local area of the grid by adopting a FIVER method:
wherein the content of the first and second substances,
the grid points of the flow field close to the surface of the parafoil are along the local normal direction of the parafoil
The state of the flow field of (a),
xi is a one-dimensional local normal direction coordinate pointing into the object, i.e. along
The direction of the light beam is changed,
is the speed of movement, Δ t, of the parafoil structural latticenRepresenting a current time step; the solution to the one-dimensional half Riemann problem is used to calculate the wall flux and thus the wall boundary conditions. The FIVER method is respectively used on two sides of the grid on the surface of the parafoil to process the conditions inside and outside the wall surface, and the characteristic of zero thickness of the parafoil grid is solved.
Step seven, performing time advancing on the space background grid to obtain the flow field state of the next time step, and calculating the flow field aerodynamic force on the boundary of the parafoil;
and step eight, applying the aerodynamic force of the flow field to the parafoil structure, and obtaining the structural deformation and the motion of the parafoil through a nonlinear structure dynamics finite element method. The nonlinear structure dynamics finite element method adopts a membrane unit to process the fabric material characteristics of the parafoil.
Step nine, updating the flow field surface grid of the parafoil by using the structural deformation and the motion of the parafoil, and recalculating the intersection condition of the parafoil surface grid and the space background grid;
step ten, returning to the process of the step six to calculate the flow field state until the fluid-solid coupling calculation process reaches the required time step.
In addition, an embodiment of the present invention further provides a computer-readable storage medium, where the computer-readable storage medium may store a program, and the program when executed includes some or all of the steps of the parafoil fluid-solid coupling numerical simulation method based on the compressible flow immersion boundary method described in the above method embodiments.
In addition, functional units in the embodiments of the present invention may be integrated into one processing unit, or each unit may exist alone physically, or two or more units are integrated into one unit. The integrated unit can be realized in a form of hardware, and can also be realized in a form of a software functional unit.
The integrated unit, if implemented in the form of a software functional unit and sold or used as a stand-alone product, may be stored in a computer readable memory. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a memory and includes several instructions for causing a computer device (which may be a personal computer, a server, a network device, or the like) to execute all or part of the steps of the method according to the embodiments of the present invention. And the aforementioned memory comprises: a U-disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a removable hard disk, a magnetic or optical disk, and other various media capable of storing program codes.
Those skilled in the art will appreciate that all or part of the steps in the methods of the above embodiments may be implemented by associated hardware instructed by a program, which may be stored in a computer-readable memory, which may include: flash Memory disks, Read-Only memories (ROMs), Random Access Memories (RAMs), magnetic or optical disks, and the like.
An exemplary flow chart of a method for simulating a parafoil fluid-solid coupling value according to an embodiment of the invention is described above with reference to the drawings. It should be noted that the numerous details included in the above description are merely exemplary of the invention and are not limiting of the invention. In other embodiments of the invention, the method may have more, fewer, or different steps, and the order, inclusion, function, etc. of the steps may be different from that described and illustrated.
Claims (9)
1. A parafoil fluid-solid coupling numerical simulation method based on a compressible flow immersion boundary method is characterized by comprising the following steps:
step one, establishing a flow field grid of the surface and the space area of the parafoil;
determining the intersection condition of the parafoil surface grid and the three-dimensional space background grid according to the geometric relationship;
step three, establishing a structural finite element grid of the parafoil, and selecting triangular or quadrilateral units to divide the grid of the parafoil;
establishing a corresponding relation between a parafoil flow field grid and a parafoil structure grid;
step five, setting initial conditions of numerical simulation according to the calculation state of the problem;
step six, using a compressible Navier-Stokes equation on a finite volume method discrete space background grid, directly calculating numerical flux for a non-boundary grid, and for the space background grid intersected with the parafoil surface grid, solving the following one-dimensional half Riemann problem in a local area of the grid by adopting a FIVER method:
in the formula (I), the compound is shown in the specification,
the grid points of the flow field close to the surface of the parafoil are along the local normal direction of the parafoil
The state of the flow field of (a),
xi is a one-dimensional local normal direction coordinate pointing into the object, i.e. along
The direction of the light beam is changed,
is the speed of movement, Δ t, of the parafoil structural latticenRepresenting a current time step; the solution to the one-dimensional half Riemann problem is used to calculate wall flux, thereby achieving wall boundary conditions;
step seven, performing time advancing on the space background grid to obtain the flow field state of the next time step, and calculating the flow field aerodynamic force on the boundary of the parafoil;
step eight, applying flow field aerodynamic force to the parafoil structure, and obtaining structural deformation and movement of the parafoil through a nonlinear structure dynamic finite element method;
step nine, updating the flow field surface grid of the parafoil by using the structural deformation and the motion of the parafoil, and recalculating the intersection condition of the parafoil surface grid and the space background grid;
step ten, returning to the process of the step six to calculate the flow field state until the fluid-solid coupling calculation process reaches the required time step.
2. A parafoil fluid-structure interaction numerical simulation method according to claim 1, characterized in that: the first step further comprises the following steps:
for the shape of the parafoil, selecting triangular units to perform mesh division on the parafoil geometric model to generate a certain number of parafoil surface mesh units;
and carrying out meshing division on the space region by adopting the tetrahedral unit, establishing a space background mesh, and carrying out mesh encryption near the initial position of the parafoil.
3. A parafoil fluid-structure interaction numerical simulation method according to claim 2, characterized in that: adjacent tetrahedral cells in the spatial background mesh have fully corresponding triangular common planes.
4. A parafoil fluid-structure interaction numerical simulation method according to claim 2, characterized in that: and the grid encryption in the step one is carried out in a local space near the initial position of the parafoil, and the size of the grid encrypted in the local space is equivalent to that of the grid on the surface of the parafoil.
5. A parafoil fluid-structure interaction numerical simulation method according to claim 1, characterized in that: and establishing a corresponding relation between the parafoil flow field grid and the parafoil structure grid in the fourth step by a corresponding algorithm to meet the energy conservation of a fluid-solid coupling interface.
6. A parafoil fluid-structure interaction numerical simulation method according to claim 1, characterized in that: in the sixth step, a spalar-almaras turbulence model is used for turbulence situation calculation, and direct calculation or a wall function is used according to the local space grid size.
7. A parafoil fluid-structure interaction numerical simulation method according to claim 1, characterized in that: and the FIVER method in the sixth step calculates the shape of the parafoil on two sides of the parafoil surface grid once respectively, and is used for processing the zero-thickness characteristic of the parafoil grid.
8. A parafoil fluid-structure interaction numerical simulation method according to claim 1, characterized in that: and the nonlinear structure dynamic finite element method in the step eight adopts the membrane unit to process the fabric material characteristics of the parafoil.
9. A computer-readable storage medium, comprising: the computer-readable storage medium stores a computer program, wherein the computer program, when executed by a processor, implements the steps of a parafoil fluid-solid coupling numerical simulation method based on a compressible flow immersion boundary method according to any one of claims 1 to 8.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116151082A (en) * | 2023-04-21 | 2023-05-23 | 中国空气动力研究与发展中心计算空气动力研究所 | Flexible wing aerodynamic heat and heat transfer coupling simulation method based on surface data transfer |
| CN116229021A (en) * | 2023-05-08 | 2023-06-06 | 中国空气动力研究与发展中心计算空气动力研究所 | Method, device, equipment and medium for embedding immersed boundary virtual grid |
| CN116486655A (en) * | 2023-05-06 | 2023-07-25 | 南京航空航天大学 | Urban low-altitude unmanned aerial vehicle airway configuration design method |
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2021
- 2021-11-30 CN CN202111441385.1A patent/CN114218824A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116151082A (en) * | 2023-04-21 | 2023-05-23 | 中国空气动力研究与发展中心计算空气动力研究所 | Flexible wing aerodynamic heat and heat transfer coupling simulation method based on surface data transfer |
| CN116151082B (en) * | 2023-04-21 | 2023-06-20 | 中国空气动力研究与发展中心计算空气动力研究所 | Flexible wing aerodynamic heat and heat transfer coupling simulation method based on surface data transfer |
| CN116486655A (en) * | 2023-05-06 | 2023-07-25 | 南京航空航天大学 | Urban low-altitude unmanned aerial vehicle airway configuration design method |
| CN116486655B (en) * | 2023-05-06 | 2024-03-08 | 南京航空航天大学 | Urban low-altitude unmanned aerial vehicle airway configuration design method |
| CN116229021A (en) * | 2023-05-08 | 2023-06-06 | 中国空气动力研究与发展中心计算空气动力研究所 | Method, device, equipment and medium for embedding immersed boundary virtual grid |
| CN116229021B (en) * | 2023-05-08 | 2023-08-25 | 中国空气动力研究与发展中心计算空气动力研究所 | Method, device, equipment and medium for embedding immersed boundary virtual grid |
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