CN115146373A

CN115146373A - Flight simulation method, flight simulation device, flight simulation equipment, storage medium and program product

Info

Publication number: CN115146373A
Application number: CN202210563957.1A
Authority: CN
Inventors: 胡湘洪; 蔡玉红; 黄铎佳; 王春辉; 李麦亮; 谢丽梅; 乔丽娜; 刘事成
Original assignee: China Electronic Product Reliability and Environmental Testing Research Institute
Current assignee: China Electronic Product Reliability and Environmental Testing Research Institute
Priority date: 2022-05-23
Filing date: 2022-05-23
Publication date: 2022-10-04

Abstract

The present application relates to a flight simulation method, apparatus, computer device, storage medium and computer program product. The method comprises the following steps: acquiring simulation parameters of the ejection hatch cover, wherein the simulation parameters comprise initial values of a plurality of flight state parameters of the ejection hatch cover, update step lengths of the flight state parameters and update cut-off values of the flight state parameters; according to the simulation parameters, circularly executing multiple times of simulation operation until each flight state parameter reaches a corresponding updating cut-off value, and acquiring aerodynamic force and aerodynamic moment of the ejection hatch cover obtained by each time of simulation operation; wherein, the ith simulation operation comprises the following steps: determining target values of the flight state parameters corresponding to the ith simulation operation according to the initial values of the flight state parameters and the updating step length of each flight state parameter; and calculating aerodynamic force and aerodynamic moment of the ejection hatch corresponding to the target value according to the target value. By adopting the method, the working efficiency of the ejection safety test work of the ejection hatch cover can be improved.

Description

Flight simulation method, flight simulation device, flight simulation equipment, storage medium and program product

Technical Field

The present application relates to the field of aircraft technologies, and in particular, to a flight simulation method, apparatus, device, storage medium, and program product for ejecting a hatch.

Background

The plane ejection lifesaving system is an emergency departure device provided for a pilot, and the safety departure of the pilot is ensured when the plane has irretrievable conditions. When a pilot uses the plane ejection lifesaving system to carry out ejection lifesaving, the ejection hatch cover is required to be ensured not to collide with an ejection flight seat in the ejection process so as to threaten the life safety of the pilot. Therefore, it is necessary to test and verify the ejection safety of the ejection hatch.

In the prior art, ground sliding rail tests are generally carried out in hatch cover ejection tests, but the tests cannot truly reproduce the external environment faced by the hatch cover in an actual ejection state, and the test cost and the risk are high, so that the ejection safety of the ejection hatch cover is generally tested and verified by adopting a flight simulation method before the tests are carried out.

Therefore, the improvement of the working efficiency of the ejection flight safety test and verification of the ejection hatch cover becomes a technical problem which needs to be solved urgently.

Disclosure of Invention

In view of the above, there is a need to provide a flight simulation method, device, computer readable storage medium and computer program product capable of improving the work efficiency of the ejection safety test work of the ejection hatch.

In a first aspect, the present application provides a flight simulation method. The method comprises the following steps:

acquiring simulation parameters of the ejection hatch cover, wherein the simulation parameters comprise initial values of a plurality of flight state parameters of the ejection hatch cover, update step lengths of the flight state parameters and update cut-off values of the flight state parameters;

according to the simulation parameters, circularly executing multiple times of simulation operation until each flight state parameter reaches a corresponding updating cut-off value, and acquiring aerodynamic force and aerodynamic moment of the ejection hatch cover obtained by each time of simulation operation;

wherein, the ith simulation operation comprises the following steps:

determining target values of the flight state parameters corresponding to the ith simulation operation according to the initial values of the flight state parameters and the updating step length of each flight state parameter;

and calculating the aerodynamic force and aerodynamic moment of the ejection hatch corresponding to the target value according to the target value.

In one embodiment, the determining the target value of each flight state parameter corresponding to the ith simulation operation according to the initial values of the flight state parameters and the update step length of each flight state parameter includes:

for each flight state parameter, determining whether the flight state parameter meets an updating condition;

and for the target flight state parameters meeting the updating conditions, determining the target values of the target flight state parameters corresponding to the ith simulation operation according to the initial values of the target flight state parameters and the updating step length of the target flight state parameters.

In one embodiment, the determining whether the flight status parameter satisfies the update condition for each flight status parameter includes:

acquiring a flight state parameter updating sequence;

for each flight state parameter, if the flight state parameter is not the first sequence element in the flight state parameter updating sequence, determining whether each flight state parameter positioned before the flight state parameter in the flight state parameter updating sequence reaches a corresponding updating cut-off value; if yes, determining that the flight state parameters meet the updating conditions;

and if the flight state parameter is the first sequence element in the flight state parameter updating sequence, determining whether the flight state parameter reaches a corresponding updating cut-off value, and if not, determining that the flight state parameter meets the updating condition.

In one embodiment, determining the target value of each target flight state parameter corresponding to the ith simulation operation according to the initial value of the target flight state parameter and the update step length of the target flight state parameter includes:

determining the updating times k of the target flight state parameters before the ith simulation operation;

calculating the product of the update step length of the target flight state parameter and k + 1;

and taking the sum of the initial value and the product of the target flight state parameter as the target value of the target flight state parameter.

In one embodiment, the plurality of flight state parameters includes a flight airspeed parameter; calculating aerodynamic force and aerodynamic moment of the ejection hatch corresponding to the target value according to the target value, and the method comprises the following steps:

determining a resolving equation and a turbulence model corresponding to the target value;

acquiring an airspeed target value corresponding to the flight airspeed parameter, determining an airspeed vector corresponding to the airspeed target value under a model coordinate system of the ejection hatch cover, and determining a convergence judgment condition corresponding to a resolving equation according to the airspeed vector;

and obtaining aerodynamic force and aerodynamic moment of the ejection hatch cover corresponding to the target value based on the resolving equation, the turbulence model and the convergence judgment condition.

In one embodiment, obtaining aerodynamic force and aerodynamic moment of the ejection hatch corresponding to the target value based on the solving equation, the turbulence model and the convergence determination condition comprises:

obtaining aerodynamic force components and aerodynamic moment components corresponding to each grid surface, which are included in a model corresponding to the ejection hatch cover, based on a resolving equation, a turbulence model and a convergence judgment condition;

determining aerodynamic force integral vectors and aerodynamic moment integral vectors corresponding to each grid surface according to the target values;

performing vector integral operation on each aerodynamic force component based on each aerodynamic force integral vector to obtain the aerodynamic force of the ejection hatch cover;

and carrying out vector integral operation on each pneumatic moment component based on each pneumatic moment integral vector to obtain the pneumatic moment of the ejection hatch cover.

In one embodiment, the method further comprises:

obtaining a pneumatic reference matrix based on the target values and the aerodynamic force and the aerodynamic moment of the ejection hatch corresponding to the target values, and storing the pneumatic reference matrix in a server;

and when target simulation values corresponding to the flight state parameters are received, outputting aerodynamic force and aerodynamic moment corresponding to the target simulation values according to the aerodynamic reference matrix and the interpolation algorithm corresponding to the target simulation values.

In a second aspect, the application also provides a flight simulation device. The device includes:

the acquisition module is used for acquiring simulation parameters of the ejection hatch cover, wherein the simulation parameters comprise initial values of a plurality of flight state parameters of the ejection hatch cover, update step lengths of the flight state parameters and update cut-off values of the flight state parameters;

the simulation module is used for circularly executing multiple times of simulation operation according to the simulation parameters until each flight state parameter reaches a corresponding updating cut-off value, and acquiring aerodynamic force and aerodynamic moment of the ejection hatch cover obtained through each time of simulation operation;

the simulation module is specifically configured to:

determining target values of the flight state parameters corresponding to the ith simulation operation according to the initial values of the flight state parameters and the updating step length of each flight state parameter; and calculating the aerodynamic force and aerodynamic moment of the ejection hatch corresponding to the target value according to the target value.

In one embodiment, the simulation module is further specifically configured to:

acquiring a flight state parameter updating sequence;

In one embodiment, the simulation module is further specifically configured to:

In one embodiment, the plurality of flight state parameters includes an airspeed parameter; the simulation module is further specifically configured to:

and obtaining aerodynamic force and aerodynamic moment of the ejection hatch cover corresponding to the target value based on a resolving equation, a turbulence model and a convergence judgment condition.

In one embodiment, the simulation module is further specifically configured to:

and performing vector integral operation on each aerodynamic moment component based on each aerodynamic moment integral vector to obtain the aerodynamic moment of the ejection hatch cover.

In one embodiment, the apparatus is further configured to:

In a third aspect, the present application also provides a computer device. The computer device comprises a memory storing a computer program and a processor implementing the aircraft simulation method according to any of the first aspects as described above when the computer program is executed by the processor.

In a fourth aspect, the present application further provides a computer-readable storage medium. The computer-readable storage medium having stored thereon a computer program which, when executed by a processor, implements the aircraft simulation method as described in any one of the first aspects above.

In a fifth aspect, the present application further provides a computer program product. The computer program product comprising a computer program which, when executed by a processor, implements the aircraft simulation method as described in any one of the above first aspects.

The flight simulation method, the flight simulation device, the computer equipment, the storage medium and the computer program product obtain the simulation parameters of the ejection hatch cover, wherein the simulation parameters comprise initial values of a plurality of flight state parameters of the ejection hatch cover, update step lengths of the flight state parameters and update cut-off values of the flight state parameters; according to the simulation parameters, circularly executing multiple times of simulation operation until each flight state parameter reaches a corresponding updating cut-off value, and acquiring aerodynamic force and aerodynamic moment of the ejection hatch cover obtained by each time of simulation operation; wherein, the ith simulation operation comprises the following steps: determining target values of the flight state parameters corresponding to the ith simulation operation according to the initial values of the flight state parameters and the updating step length of each flight state parameter; and calculating the aerodynamic force and aerodynamic moment of the ejection hatch corresponding to the target value according to the target value. According to the method and the device, the target value of each flight state parameter corresponding to the ith simulation operation is determined according to the initial values of the flight state parameters and the updating step length of each flight state parameter, so that the purposes of automatically updating the flight state parameters and automatically calculating the target value of the flight state parameter according to the updated flight state parameters are achieved, the debugging time of each flight state parameter of technicians is remarkably saved, the time cost required by the establishment of a subsequent pneumatic reference matrix is reduced, and the ejection safety testing work efficiency of the ejection hatch cover is improved.

Drawings

FIG. 1 is a schematic flow chart diagram of a flight simulation method in one embodiment;

FIG. 2 is a schematic flow chart illustrating the determination of the target values of the flight state parameters corresponding to the ith simulation operation in one embodiment;

FIG. 3 is a flow chart illustrating step 202 in one embodiment;

FIG. 4 is a schematic diagram of a process for calculating aerodynamic and aerodynamic moments of an ejection deck lid corresponding to a target value based on the target value in one embodiment;

FIG. 5 is a schematic flow chart diagram of a flight simulation method in another embodiment;

FIG. 6 is a schematic flow chart illustrating the process of determining multiple sets of target values corresponding to various flight state parameters according to one embodiment;

FIG. 7 is a schematic flow chart diagram of a flight simulation method in yet another embodiment;

FIG. 8 is a schematic diagram illustrating a flow chart of an ith simulation operation in one embodiment;

FIG. 9 is a schematic flow chart diagram of a flight simulation method in yet another embodiment;

FIG. 10 is a block diagram showing the structure of an aircraft simulation apparatus according to an embodiment;

FIG. 11 is a diagram illustrating an internal structure of a computer device in one embodiment.

Detailed Description

In order to make the objects, technical solutions and advantages of the present application more apparent, the present application is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of and not restrictive on the broad application.

The embodiment of the application provides a flight simulation method. The execution main body of the flight simulation method can be a flight simulation device, and the flight simulation device can be realized to be a part or all of a terminal or a server in a software, hardware or software and hardware combined mode. The terminal can be a personal computer, a notebook computer, a media player, an intelligent television, a smart phone, a tablet computer and portable wearable equipment; the server may be implemented as a stand-alone server or as a server cluster consisting of a plurality of servers.

In the following method embodiments, the following method embodiments are described by taking an execution subject as an example. It is understood that the method can also be applied to a terminal, and can also be applied to a system comprising the terminal and a server, and is realized through the interaction of the terminal and the server.

Referring to fig. 1, a flowchart of a flight simulation method provided in an embodiment of the present application is shown. As shown in fig. 1, the flight simulation method may include the steps of:

step 101, acquiring simulation parameters of the ejection hatch cover.

The simulation parameters comprise initial values of a plurality of flight state parameters of the ejection hatch cover, updating step length of each flight state parameter and updating cut-off values of each flight state parameter.

In an alternative implementation, the flight state parameters include altitude H, airspeed V, angle of flight attack α, and angle of flight sideslip β. In another alternative implementation, the flight state parameters include atmospheric pressure P, atmospheric temperature T, atmospheric density ρ, and local sound velocity V ₁ Flying airspeed V ₂ A flight angle of attack α and a flight angle of sideslip β.

Optionally, the update step lengths corresponding to different flight state parameters are different. Specifically, the updating step length corresponding to the flying height H is greater than the updating step lengths corresponding to the flying attack angle α and the flying sideslip angle β; the updating step length corresponding to the flight airspeed V is larger than the updating step length corresponding to the flight attack angle alpha and the flight sideslip angle beta.

Alternatively, the updated cutoff value may be determined based on a corresponding maximum altitude of the aircraft.

And 102, circularly executing multiple times of simulation operation according to the simulation parameters until each flight state parameter reaches a corresponding updating cut-off value, and acquiring aerodynamic force and aerodynamic moment of the ejection hatch cover obtained by each time of simulation operation.

Wherein, the ith simulation operation comprises: determining target values of the flight state parameters corresponding to the ith simulation operation according to the initial values of the flight state parameters and the updating step length of each flight state parameter; and calculating the aerodynamic force and aerodynamic moment of the ejection hatch corresponding to the target value according to the target value.

Optionally, the simulation operation method includes a numerical calculation method based on Computational Fluid Dynamics (CFD).

Optionally, the obtaining manner of the target values of the corresponding flight state parameters obtained by the ith simulation operation includes: aiming at the ith simulation operation, selecting an adjustable flight state parameter from the flight state parameters, and determining the corresponding updating times of the adjustable flight state parameter before the ith simulation operation; determining a target value corresponding to the flight state parameter according to the updating times, the initial value of the flight state parameter and the updating step length of the flight state parameter; and the values of other flight state parameters except the adjustable flight state parameter in the flight state parameters are the same as the values of the other corresponding flight state parameters in the i-1 st simulation operation.

Optionally, in order to improve the computational efficiency of the simulation operation, the server is set as a server cluster. The server cluster comprises a plurality of execution nodes, and each simulation operation can be executed by the plurality of execution nodes in parallel. Specifically, when the server is a server cluster, simulation operation execution tasks are distributed to each execution node based on an MPI multithreading method.

In the embodiment, simulation parameters of the ejection hatch cover are obtained, wherein the simulation parameters comprise initial values of a plurality of flight state parameters of the ejection hatch cover, update step lengths of the flight state parameters and update cut-off values of the flight state parameters; according to the simulation parameters, circularly executing multiple times of simulation operation until each flight state parameter reaches a corresponding updating cut-off value, and acquiring aerodynamic force and aerodynamic moment of the ejection hatch cover obtained by each time of simulation operation; wherein, the ith simulation operation comprises the following steps: determining target values of the flight state parameters corresponding to the ith simulation operation according to the initial values of the flight state parameters and the updating step length of each flight state parameter; and calculating aerodynamic force and aerodynamic moment of the ejection hatch corresponding to the target value according to the target value. According to the method and the device, the target value of each flight state parameter corresponding to the ith simulation operation is determined according to the initial values of the flight state parameters and the updating step length of each flight state parameter, so that the purposes of automatically updating the flight state parameters and automatically calculating the target value of the flight state parameter according to the updated flight state parameters are achieved, the debugging time of each flight state parameter of technicians is remarkably saved, the time cost required by the establishment of a subsequent pneumatic reference matrix is reduced, and the ejection safety testing work efficiency of the ejection hatch cover is improved.

Further, as shown in fig. 2, based on the embodiment shown in fig. 1, the embodiment relates to an implementation process for determining a target value of each flight state parameter corresponding to the ith simulation operation according to initial values of a plurality of flight state parameters and an update step size of each flight state parameter in the ith simulation operation, and the implementation process includes steps 201 and 202:

step 201, for each flight state parameter, determining whether the flight state parameter meets an update condition.

Optionally, the step 201 includes the following two implementation manners:

mode (1): the updating condition is that the flight state parameter does not reach the corresponding updating cut-off value.

Mode (2): acquiring a flight state parameter updating sequence; for each flight state parameter, if the flight state parameter is not the first sequence element in the flight state parameter updating sequence, determining whether each flight state parameter positioned before the flight state parameter in the flight state parameter updating sequence reaches a corresponding updating cut-off value; if so, determining that the flight state parameters meet the updating conditions; and if the flight state parameter is the first sequence element in the flight state parameter updating sequence, determining whether the flight state parameter reaches a corresponding updating cut-off value, and if not, determining that the flight state parameter meets the updating condition.

Specifically, the acquiring process of the flight state parameter update sequence in the method (2) includes: and sequencing the flight state parameters, and obtaining the flight state parameter updating sequence according to the sequenced flight state parameters.

Taking the flight state parameters as flight altitude H, flight airspeed V, flight attack angle α and flight sideslip angle β as examples, sequencing the flight state parameters, wherein the sequencing order sequentially comprises: the flight altitude H, the flight airspeed V, the flight angle of attack alpha and the flight sideslip angle beta, and the obtained flight state parameter update sequence can be { the flight altitude H, the flight airspeed V, the flight angle of attack, the flight sideslip angle beta }; optionally, the flight state parameter update sequence may also be {1,2,3,4}, where 1,2,3, and 4 are parameter identifiers corresponding to the flight altitude H, the flight airspeed V, the flight angle of attack α, and the flight sideslip angle β, respectively.

Step 202, for the target flight state parameters meeting the updating conditions, determining the target values of the target flight state parameters corresponding to the ith simulation operation according to the initial values of the target flight state parameters and the updating step length of the target flight state parameters.

With respect to the above-described mode (1), a plurality of candidate flight state parameters satisfying the update condition are determined, and one of the candidate flight state parameters is selected as the target flight state parameter.

In the above aspect (2), the flight state parameter satisfying the update condition is set as the target flight state parameter.

Optionally, determining the target value of each target flight state parameter corresponding to the ith simulation operation according to the initial value of the target flight state parameter and the update step length of the target flight state parameter, where the determining includes: aiming at the target value of each target flight state parameter, acquiring the update times k of the target flight state parameter before the ith simulation operation; and calculating the product value between the k power of the updating step length of the target flight state parameter and the initial value, and taking the product value as the target value of the target flight state parameter.

In the embodiment, whether each flight state parameter meets the updating condition is determined, the target value of each target flight state parameter corresponding to the ith simulation operation is determined for the target flight state parameter meeting the updating condition according to the initial value of the target flight state parameter and the updating step length of the target flight state parameter, the purpose of determining the target flight state parameter based on the judgment result corresponding to whether each flight state parameter meets the updating condition is achieved, further, whether the flight state parameter needs to be updated is automatically determined, and the automation level of the simulation of the ejection hatch is improved.

In the embodiment of the present application, as shown in fig. 3, based on the embodiment shown in fig. 2, the implementation process of determining the target value of each target flight state parameter corresponding to the ith simulation operation according to the initial value of the target flight state parameter and the update step length of the target flight state parameter in step 202 includes the following steps:

step 301, determining the update times k of the target flight state parameters before the ith simulation operation.

Optionally, the server counts the number of updates corresponding to each flight state parameter. For a certain flight status parameter, every time a parameter update is performed, the corresponding count is incremented by 1.

And step 302, calculating the product of the update step length of the target flight state parameter and k + 1.

And step 303, taking the sum of the initial value and the product of the target flight state parameter as the target value of the target flight state parameter.

Specifically, the calculation formula of the target value of the target flight state parameter is as follows:

value′＝value ₀ +(k+1)*Δvalue，

wherein value' represents a target value of a target flight state parameter, value ₀ And k represents the corresponding updating times of the target flight state parameter before the ith simulation operation, and delta value represents the updating step length of the target flight state parameter.

In the embodiment, the updating times k of the target flight state parameters before the ith simulation operation are determined, the product of the updating step length of the target flight state parameters and k +1 is calculated, and the sum of the initial value of the target flight state parameters and the product is used as the target value of the target flight state parameters.

Further, in accordance with any of the above embodiments, the plurality of flight state parameters includes an aircraft airspeed parameter. As shown in fig. 4, the step of calculating the implementation process of aerodynamic force and aerodynamic moment of the ejection hatch corresponding to the target value according to the target value comprises the following steps:

step 401, determining a solution equation and a turbulence model corresponding to the target value.

Optionally, the solution equation includes an N-S equation and an euler equation; corresponding discrete formats are also set for the solution equations.

Optionally, the turbulence model includes a k-e model, a low Reynolds number k-e model, a RNG k-e model, an algebraic Reynolds stress model, a derivative Reynolds stress model, and a derivative Reynolds flux model.

And 402, acquiring an airspeed target value corresponding to the flight airspeed parameter, determining an airspeed vector corresponding to the airspeed target value in a model coordinate system of the ejection hatch cover, and determining a convergence judgment condition corresponding to a resolving equation according to the airspeed vector.

Optionally, the model coordinate system is a model coordinate system corresponding to a grid model corresponding to the ejection hatch.

Optionally, the method for constructing the grid model corresponding to the ejection hatch cover includes: acquiring a three-dimensional geometric model corresponding to the ejection hatch cover; and setting a calculation domain and a model coordinate system, and carrying out gridding processing on the three-dimensional geometric model according to the calculation domain and the model coordinate system to obtain a grid model corresponding to the ejection hatch cover. Optionally, the three-dimensional geometric model is subjected to gridding processing by ANSYS SCDM software.

And 403, obtaining aerodynamic force and aerodynamic moment of the ejection hatch cover corresponding to the target value based on the calculation equation, the turbulence model and the convergence judgment condition.

Optionally, based on a resolving equation, a turbulence model and a convergence judgment condition, obtaining aerodynamic force components and aerodynamic moment components corresponding to each grid surface included in a model corresponding to the ejection hatch cover; determining aerodynamic force integral vectors and aerodynamic moment integral vectors corresponding to each grid surface according to the target values; performing vector integral operation on each aerodynamic force component based on each aerodynamic force integral vector to obtain the aerodynamic force of the ejection hatch cover; and performing vector integral operation on each aerodynamic moment component based on each aerodynamic moment integral vector to obtain the aerodynamic moment of the ejection hatch cover.

Optionally, when the flight state parameter includes a flight height H, it is required to obtain a corresponding flight height H according to the flight height HAtmospheric pressure P, atmospheric temperature T, atmospheric density ρ, and local sound velocity V ₁ . Then the atmospheric pressure P, the atmospheric temperature T, the atmospheric density ρ and the local sound velocity V ₁ And substituting other flight state parameters into a resolving equation and a turbulence model, and acquiring the aerodynamic force and aerodynamic moment of the corresponding ejection hatch cover under the condition of meeting the convergence judgment condition.

In the embodiment, a resolving equation and a turbulence model corresponding to a target value are determined, an airspeed target value corresponding to a flight airspeed parameter is obtained, an airspeed vector corresponding to the airspeed target value in a model coordinate system of the ejection hatch cover is determined, a convergence judgment condition corresponding to the resolving equation is determined according to the airspeed vector, and aerodynamic force and aerodynamic moment of the ejection hatch cover corresponding to the target value are obtained based on the resolving equation, the turbulence model and the convergence judgment condition. The method achieves the purpose of determining a resolving equation, a turbulence model and a convergence judgment condition according to the target value so as to be used for calculating aerodynamic force and aerodynamic moment, and is high in calculation accuracy.

In the embodiment of the present application, as shown in fig. 5, the flight simulation method further includes steps 501 and 502:

and 501, obtaining a pneumatic reference matrix based on the target values and the aerodynamic force and the aerodynamic moment of the ejection hatch corresponding to the target values, and storing the pneumatic reference matrix in a server.

Optionally, the pneumatic reference matrix is saved in a cellular array manner.

Optionally, when the server executing the simulation operation is a server cluster, the server for storing the pneumatic reference matrix may be any server in the server cluster, or may not be a server included in the server cluster.

And 502, when target simulation values corresponding to the flight state parameters are received, outputting aerodynamic force and aerodynamic moment corresponding to the target simulation values according to the aerodynamic reference matrix and the interpolation algorithm corresponding to the target simulation values.

Optionally, according to the target simulation value corresponding to each flight state parameter, obtaining multiple groups of target values corresponding to each flight state parameter closest to the target simulation value in the pneumatic reference matrix; determining a corresponding interpolation algorithm according to the value intervals of the multiple groups of target values; and calculating aerodynamic force and aerodynamic moment corresponding to the target simulation value according to the multiple groups of target values and an interpolation algorithm.

Specifically, as shown in fig. 6, obtaining multiple sets of target values corresponding to a plurality of flight state parameters closest to the target simulation value in the pneumatic reference matrix according to the target simulation value corresponding to each flight state parameter includes:

step 5021, calculating a distance value between a certain group of target values corresponding to each flight state parameter in the pneumatic reference matrix and a target simulation value by using an Euclidean distance formula;

taking the number of the flight state parameters as 4 as an example, the euclidean distance formula is expressed as follows:

wherein x is ₁ 、x ₂ 、x ₃ 、x ₄ Respectively a group of target values corresponding to each flight state parameter in the pneumatic reference matrix; x' ₁ 、x′ ₂ 、x′ ₃ 、x′ ₄ Respectively are target simulation values corresponding to the flight state parameters.

Step 5022, the sets of target values with the minimum distance values are taken as a plurality of sets of target values corresponding to the flight state parameters closest to the target simulation value in the pneumatic reference matrix.

Optionally, the number of groups corresponding to the target value is a preset number. Optionally, the number of groups corresponding to the target value may also be determined according to a difference between the distance value and the preset distance.

In this embodiment, a pneumatic reference matrix is obtained based on each target value and the aerodynamic force and the aerodynamic moment of the ejection hatch corresponding to each target value, the pneumatic reference matrix is stored in the server, and when a target simulation value corresponding to each flight state parameter is received, the aerodynamic force and the aerodynamic moment corresponding to the target simulation value are output according to the pneumatic reference matrix and an interpolation algorithm corresponding to each target simulation value. The pneumatic reference matrix is generated based on a large amount of debugging data, and the pneumatic reference matrix can systematically present the change rule of the aerodynamic force and the aerodynamic moment of the ejection hatch cover in the ejection process along with the flight state parameters in detail, so that the aerodynamic force and the aerodynamic moment corresponding to the target simulation value are obtained by calculation based on the generated pneumatic reference matrix, and the calculation errors of the aerodynamic force and the aerodynamic moment corresponding to the target simulation value can be reduced.

In an embodiment of the present application, as shown in fig. 7, the embodiment provides a flight simulation method, which includes the following steps:

step 601, acquiring simulation parameters of the ejection hatch cover.

And step 602, circularly executing multiple times of simulation operations according to the simulation parameters until each flight state parameter reaches a corresponding update cut-off value, and acquiring aerodynamic force and aerodynamic moment of the ejection hatch cover obtained through each time of simulation operations.

As shown in fig. 8, the ith simulation operation includes:

step 6020, for each flight state parameter, determining whether the flight state parameter meets the update condition.

Wherein the determining process comprises: acquiring a flight state parameter updating sequence; for each flight state parameter, if the flight state parameter is not the first sequence element in the flight state parameter updating sequence, determining whether each flight state parameter positioned before the flight state parameter in the flight state parameter updating sequence reaches a corresponding updating cut-off value; if so, determining that the flight state parameters meet the updating conditions; and if the flight state parameter is the first sequence element in the flight state parameter updating sequence, determining whether the flight state parameter reaches a corresponding updating cut-off value, and if not, determining that the flight state parameter meets the updating condition.

Step 6021, for the target flight state parameter meeting the update condition, determining the update times k of the target flight state parameter before the ith simulation operation.

Step 6022, calculating the product of the update step length of the target flight state parameter and k + 1.

Step 6023, the sum of the initial value and the product of the target flight state parameter is used as the target value of the target flight state parameter.

And 6024, determining a solving equation and a turbulence model corresponding to the target value.

Step 6025, obtaining an airspeed target value corresponding to the flight airspeed parameter, determining an airspeed vector corresponding to the airspeed target value in a model coordinate system of the ejection cabin cover, and determining a convergence judgment condition corresponding to the resolving equation according to the airspeed vector.

And 6026, obtaining aerodynamic force components and aerodynamic moment components corresponding to each grid surface included in the model corresponding to the ejection hatch cover based on the resolving equation, the turbulence model and the convergence judgment condition.

Step 6027, determining the aerodynamic force integral vector and the aerodynamic moment integral vector corresponding to each grid surface according to the target value.

In step 6028, a vector integral operation is performed on each aerodynamic component based on each aerodynamic integral vector to obtain the aerodynamic force of the ejection hatch.

Step 6029, performing vector integral operation on each aerodynamic moment component based on each aerodynamic moment integral vector to obtain the aerodynamic moment of the ejection hatch.

Step 603, obtaining a pneumatic reference matrix based on the target values and the aerodynamic force and the aerodynamic moment of the ejection hatch corresponding to the target values, and storing the pneumatic reference matrix in a server.

And step 604, outputting aerodynamic force and aerodynamic moment corresponding to the target simulation values according to the aerodynamic reference matrix and the interpolation algorithm corresponding to each target simulation value when the target simulation values corresponding to each flight state parameter are received.

Taking the flight state parameters including the flight altitude H, the flight airspeed V, the flight attack angle α and the flight sideslip angle β as an example, the implementation flow corresponding to the flight simulation method is illustrated in fig. 9. The specific implementation process is as follows:

obtaining initial values of a plurality of flight state parameters of the ejection hatch (namely, hatch flight parameter calculation in fig. 9), and determining an airspeed vector (namely, a calculated hatch airspeed vector in fig. 9) corresponding to an airspeed target value under a model coordinate system of the ejection hatch and aerodynamic force integral vectors and aerodynamic moment integral vectors (namely, a calculated hatch aerodynamic force and moment integral vector in fig. 9) corresponding to each grid surface according to the flight state parameters; calculating aerodynamic force and aerodynamic moment of the ejection hatch cover (namely CFD calculation solution and extraction of calculation results of the aerodynamic force and moment in figure 9); judging whether the flight angle of attack alpha reaches an updated cut-off value;

if the flight attack angle alpha does not reach the updating cut-off value, updating the flight attack angle alpha according to the updating step length of the flight attack angle alpha, and executing the solution of aerodynamic force and aerodynamic moment of the ejection hatch cover;

if the flight angle of attack alpha reaches the update cut-off value, judging whether the flight sideslip angle beta reaches the update cut-off value, if the flight sideslip angle beta does not reach the update cut-off value, updating the flight sideslip angle beta according to the update step length of the flight sideslip angle beta, and executing the solution of aerodynamic force and aerodynamic moment of the ejection hatch cover;

if the flight sideslip angle beta reaches the updated cut-off value, judging whether the flight airspeed V reaches the updated cut-off value, if the flight airspeed V does not reach the updated cut-off value, updating the flight airspeed V according to the updated step length of the flight airspeed V, and executing solution of aerodynamic force and aerodynamic moment of the ejection hatch cover;

if the flying airspeed V reaches the updating cut-off value, judging whether the flying altitude H reaches the updating cut-off value, if the flying altitude H does not reach the updating cut-off value, acquiring the atmospheric pressure, the atmospheric temperature, the atmospheric density and the local sound velocity corresponding to the flying altitude H, and executing the solution of the aerodynamic force and the aerodynamic moment of the ejection hatch cover;

if the flying height H reaches the update cutoff value, a pneumatic reference matrix is obtained based on each target value and the aerodynamic force and the aerodynamic moment of the ejection hatch corresponding to each target value, and the pneumatic reference matrix is stored in the user server (i.e., the calculation result in fig. 9 is stored).

Target simulation values (namely, the flight state data of the cabin cover in fig. 9) corresponding to the flight state parameters are input through an input port of the user server, and aerodynamic force and aerodynamic moment (namely, the pneumatic data output of the cabin cover in fig. 9) corresponding to the target simulation values are output through an output port of the user server according to the pneumatic reference matrix and the interpolation algorithm (namely, the data calculation processing in fig. 9) corresponding to the target simulation values.

It should be understood that, although the steps in the flowcharts related to the embodiments described above are shown in sequence as indicated by the arrows, the steps are not necessarily performed in sequence as indicated by the arrows. The steps are not performed in the exact order shown and described, and may be performed in other orders, unless explicitly stated otherwise. Moreover, at least a part of the steps in the flowcharts related to the embodiments described above may include multiple steps or multiple stages, which are not necessarily performed at the same time, but may be performed at different times, and the execution order of the steps or stages is not necessarily sequential, but may be rotated or alternated with other steps or at least a part of the steps or stages in other steps.

Based on the same inventive concept, the embodiment of the application also provides a flight simulation device for realizing the flight simulation method. The implementation scheme for solving the problem provided by the device is similar to the implementation scheme recorded in the method, so the specific limitations in one or more embodiments of the flight simulation device provided below can be referred to the limitations of the flight simulation method in the above, and are not described herein again.

In one embodiment, as shown in fig. 10, there is provided a flight simulator comprising: an acquisition module 100 and a simulation module 200, wherein:

the acquiring module 100 is configured to acquire simulation parameters of the ejection hatch, where the simulation parameters include initial values of a plurality of flight state parameters of the ejection hatch, update step lengths of the flight state parameters, and update cutoff values of the flight state parameters;

the simulation module 200 is used for circularly executing multiple times of simulation operations according to the simulation parameters until each flight state parameter reaches a corresponding update cut-off value, and acquiring aerodynamic force and aerodynamic moment of the ejection hatch cover obtained through each time of simulation operations;

wherein the simulation module 200 comprises a determining unit 2010 and a calculating unit 2020, wherein:

a determining unit 2010, configured to determine, according to the initial values of the multiple flight state parameters and the update step length of each flight state parameter, a target value of each flight state parameter corresponding to the ith simulation operation;

and a calculation unit 2020 for calculating aerodynamic force and aerodynamic moment of the ejection hatch corresponding to the target value, based on the target value.

In one embodiment, the determining unit 2010 is specifically configured to:

for each flight state parameter, determining whether the flight state parameter meets an updating condition; and for the target flight state parameters meeting the updating conditions, determining the target values of the target flight state parameters corresponding to the ith simulation operation according to the initial values of the target flight state parameters and the updating step length of the target flight state parameters.

In an embodiment, the determining unit 2010 is further specifically configured to:

In one embodiment, the determining unit 2010 is further specifically configured to:

acquiring a flight state parameter updating sequence; for each flight state parameter, if the flight state parameter is not the first sequence element in the flight state parameter updating sequence, determining whether each flight state parameter positioned before the flight state parameter in the flight state parameter updating sequence reaches a corresponding updating cut-off value; if yes, determining that the flight state parameters meet the updating conditions;

determining the updating times k of the target flight state parameters before the ith simulation operation; calculating the product of the update step length of the target flight state parameter and k + 1; and taking the sum of the initial value and the product of the target flight state parameter as the target value of the target flight state parameter.

In one embodiment, the plurality of flight state parameters includes an airspeed parameter; the computing unit is specifically configured to:

determining a resolving equation and a turbulence model corresponding to the target value; acquiring an airspeed target value corresponding to the flight airspeed parameter, determining an airspeed vector corresponding to the airspeed target value under a model coordinate system of the ejection hatch cover, and determining a convergence judgment condition corresponding to a resolving equation according to the airspeed vector; and obtaining aerodynamic force and aerodynamic moment of the ejection hatch cover corresponding to the target value based on the resolving equation, the turbulence model and the convergence judgment condition.

In one embodiment, the computing unit 2020 is further specifically configured to:

In one embodiment, the apparatus is further configured to:

obtaining a pneumatic reference matrix based on the target values and the aerodynamic force and the aerodynamic moment of the ejection hatch cover corresponding to the target values, and storing the pneumatic reference matrix into a server;

The various modules in the flight simulation apparatus described above may be implemented in whole or in part by software, hardware, and combinations thereof. The modules can be embedded in a hardware form or independent of a processor in the computer device, and can also be stored in a memory in the computer device in a software form, so that the processor can call and execute operations corresponding to the modules.

In one embodiment, a computer device is provided, which may be a terminal, and its internal structure diagram may be as shown in fig. 11. The computer device includes a processor, a memory, a communication interface, a display screen, and an input device connected by a system bus. Wherein the processor of the computer device is configured to provide computing and control capabilities. The memory of the computer device comprises a nonvolatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of an operating system and computer programs in the non-volatile storage medium. The communication interface of the computer device is used for carrying out wired or wireless communication with an external terminal, and the wireless communication can be realized through WIFI, a mobile cellular network, NFC (near field communication) or other technologies. The computer program is executed by a processor to implement a flight simulation method. The display screen of the computer equipment can be a liquid crystal display screen or an electronic ink display screen, and the input device of the computer equipment can be a touch layer covered on the display screen, a key, a track ball or a touch pad arranged on the shell of the computer equipment, an external keyboard, a touch pad or a mouse and the like.

Those skilled in the art will appreciate that the architecture shown in fig. 11 is merely a block diagram of some of the structures associated with the disclosed aspects and is not intended to limit the computing devices to which the disclosed aspects apply, as particular computing devices may include more or less components than those shown, or may combine certain components, or have a different arrangement of components.

In one embodiment, a server is provided comprising a memory having a computer program stored therein and a processor that implements the following steps when executing the computer program.

wherein, the ith simulation operation comprises the following steps:

In one embodiment, the processor, when executing the computer program, further performs the steps of:

In one embodiment, the processor when executing the computer program further performs the steps of:

acquiring a flight state parameter updating sequence; for each flight state parameter, if the flight state parameter is not the first sequence element in the flight state parameter updating sequence, determining whether each flight state parameter positioned before the flight state parameter in the flight state parameter updating sequence reaches a corresponding updating cut-off value; if yes, determining that the flight state parameters meet the updating conditions; and if the flight state parameter is the first sequence element in the flight state parameter updating sequence, determining whether the flight state parameter reaches a corresponding updating cut-off value, and if not, determining that the flight state parameter meets the updating condition.

determining a resolving equation and a turbulence model corresponding to the target value; acquiring an airspeed target value corresponding to the flight airspeed parameter, determining an airspeed vector corresponding to the airspeed target value under a model coordinate system of the ejection hatch cover, and determining a convergence judgment condition corresponding to a resolving equation according to the airspeed vector; and obtaining aerodynamic force and aerodynamic moment of the ejection hatch cover corresponding to the target value based on a resolving equation, a turbulence model and a convergence judgment condition.

obtaining aerodynamic force components and aerodynamic moment components corresponding to each grid surface, which are included in a model corresponding to the ejection hatch cover, based on a resolving equation, a turbulence model and a convergence judgment condition; determining aerodynamic force integral vectors and aerodynamic moment integral vectors corresponding to each grid surface according to the target values; performing vector integral operation on each aerodynamic force component based on each aerodynamic force integral vector to obtain the aerodynamic force of the ejection hatch cover; and carrying out vector integral operation on each pneumatic moment component based on each pneumatic moment integral vector to obtain the pneumatic moment of the ejection hatch cover.

obtaining a pneumatic reference matrix based on the target values and the aerodynamic force and the aerodynamic moment of the ejection hatch corresponding to the target values, and storing the pneumatic reference matrix in a server; and when target simulation values corresponding to the flight state parameters are received, outputting aerodynamic force and aerodynamic moment corresponding to the target simulation values according to the aerodynamic reference matrix and the interpolation algorithm corresponding to the target simulation values.

In one embodiment, a computer-readable storage medium is provided, having stored thereon a computer program which, when executed by a processor, performs the steps of:

wherein, the ith simulation operation comprises the following steps:

In one embodiment, the computer program when executed by the processor further performs the steps of:

obtaining aerodynamic force components and aerodynamic moment components corresponding to each grid surface, which are included in a model corresponding to the ejection hatch cover, based on a resolving equation, a turbulence model and a convergence judgment condition; determining aerodynamic force integral vectors and aerodynamic moment integral vectors corresponding to each grid surface according to the target values; performing vector integral operation on each aerodynamic force component based on each aerodynamic force integral vector to obtain the aerodynamic force of the ejection hatch cover; and performing vector integral operation on each aerodynamic moment component based on each aerodynamic moment integral vector to obtain the aerodynamic moment of the ejection hatch cover.

In one embodiment, a computer program product is provided, comprising a computer program which, when executed by a processor, performs the steps of:

acquiring simulation parameters of the ejection hatch, wherein the simulation parameters comprise initial values of a plurality of flight state parameters of the ejection hatch, update step lengths of the flight state parameters and update cut-off values of the flight state parameters;

wherein, the ith simulation operation comprises the following steps:

It will be understood by those skilled in the art that all or part of the processes of the methods of the embodiments described above can be implemented by hardware instructions of a computer program, which can be stored in a non-volatile computer-readable storage medium, and when executed, can include the processes of the embodiments of the methods described above. Any reference to memory, database, or other medium used in the embodiments provided herein may include at least one of non-volatile and volatile memory. The nonvolatile Memory may include Read-Only Memory (ROM), magnetic tape, floppy disk, flash Memory, optical Memory, high-density embedded nonvolatile Memory, resistive Random Access Memory (ReRAM), magnetic Random Access Memory (MRAM), ferroelectric Random Access Memory (FRAM), phase Change Memory (PCM), graphene Memory, and the like. Volatile Memory can include Random Access Memory (RAM), external cache Memory, and the like. By way of illustration and not limitation, RAM can take many forms, such as Static Random Access Memory (SRAM) or Dynamic Random Access Memory (DRAM), for example. The databases referred to in various embodiments provided herein may include at least one of relational and non-relational databases. The non-relational database may include, but is not limited to, a block chain based distributed database, and the like. The processors referred to in the embodiments provided herein may be general purpose processors, central processing units, graphics processors, digital signal processors, programmable logic devices, quantum computing based data processing logic devices, etc., without limitation.

All possible combinations of the technical features in the above embodiments may not be described for the sake of brevity, but should be considered as being within the scope of the present disclosure as long as there is no contradiction between the combinations of the technical features.

The above-mentioned embodiments only express several embodiments of the present application, and the description thereof is more specific and detailed, but not construed as limiting the scope of the present application. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the concept of the present application, and these are all within the scope of protection of the present application. Therefore, the protection scope of the present application shall be subject to the appended claims.

Claims

1. A flight simulation method, the method comprising:

acquiring simulation parameters of an ejection hatch cover, wherein the simulation parameters comprise initial values of a plurality of flight state parameters of the ejection hatch cover, updating step length of each flight state parameter and updating cut-off values of each flight state parameter;

according to the simulation parameters, multiple times of simulation operation are executed in a circulating mode until each flight state parameter reaches a corresponding updating cut-off value, and aerodynamic force and aerodynamic moment of the ejection hatch cover obtained through each time of simulation operation are obtained;

wherein, the ith simulation operation comprises the following steps:

determining a target value of each flight state parameter corresponding to the ith simulation operation according to the initial values of the flight state parameters and the updating step length of each flight state parameter;

and calculating aerodynamic force and aerodynamic moment of the ejection hatch cover corresponding to the target value according to the target value.

2. The method according to claim 1, wherein the determining the target value of each flight state parameter corresponding to the i-th simulation operation according to the initial values of the flight state parameters and the update step length of each flight state parameter comprises:

for each flight state parameter, determining whether the flight state parameter meets an update condition;

3. The method of claim 2, wherein the determining whether the flight status parameters satisfy an update condition for each of the flight status parameters comprises:

acquiring a flight state parameter updating sequence;

for each flight state parameter, if the flight state parameter is not the first sequence element in the flight state parameter update sequence, determining whether each flight state parameter located before the flight state parameter in the flight state parameter update sequence reaches a corresponding update cut-off value; if so, determining that the flight state parameters meet the updating conditions;

4. The method according to claim 2, wherein the determining the target value of each target flight state parameter corresponding to the i-th simulation operation according to the initial value of the target flight state parameter and the update step length of the target flight state parameter comprises:

and taking the sum of the initial value of the target flight state parameter and the product as the target value of the target flight state parameter.

5. The method of any of claims 2 to 4, wherein the plurality of flight state parameters includes a flight airspeed parameter; the calculating the aerodynamic force and aerodynamic moment of the ejection hatch corresponding to the target value according to the target value comprises the following steps:

acquiring an airspeed target value corresponding to the flight airspeed parameter, determining an airspeed vector corresponding to the airspeed target value in a model coordinate system of the ejection hatch cover, and determining a convergence judgment condition corresponding to the resolving equation according to the airspeed vector;

and obtaining aerodynamic force and aerodynamic moment of the ejection hatch cover corresponding to the target value based on the calculation equation, the turbulence model and the convergence judgment condition.

6. The method according to claim 5, wherein the deriving aerodynamic force and aerodynamic moment of the ejection deck lid corresponding to the target value based on the solved equation, the turbulence model, and the convergence determination condition includes:

obtaining aerodynamic force components and aerodynamic moment components corresponding to each grid surface included in a model corresponding to the ejection hatch cover based on the resolving equation, the turbulence model and the convergence judgment condition;

determining aerodynamic force integral vectors and aerodynamic moment integral vectors corresponding to the grid surfaces according to the target values;

and carrying out vector integral operation on each aerodynamic moment component based on each aerodynamic moment integral vector to obtain the aerodynamic moment of the ejection hatch cover.

7. The method of claim 1, further comprising:

obtaining a pneumatic reference matrix based on each target value and the aerodynamic force and the aerodynamic moment of the ejection hatch cover corresponding to each target value, and storing the pneumatic reference matrix into a server;

8. A flight simulator, the device comprising:

the acquiring module is used for acquiring simulation parameters of the ejection hatch cover, wherein the simulation parameters comprise initial values of a plurality of flight state parameters of the ejection hatch cover, updating step lengths of the flight state parameters and updating cut-off values of the flight state parameters;

the simulation module is used for circularly executing multiple times of simulation operation according to the simulation parameters until each flight state parameter reaches a corresponding updating cut-off value, and acquiring aerodynamic force and aerodynamic moment of the ejection hatch cover obtained by each time of simulation operation;

wherein, the simulation module is specifically configured to:

determining a target value of each flight state parameter corresponding to the ith simulation operation according to the initial values of the flight state parameters and the updating step length of each flight state parameter; and calculating aerodynamic force and aerodynamic moment of the ejection hatch cover corresponding to the target value according to the target value.

9. A server comprising a memory and a processor, the memory storing a computer program, characterized in that the processor, when executing the computer program, implements the steps of the method of any of claims 1 to 7.

10. A computer-readable storage medium, on which a computer program is stored, which, when being executed by a processor, carries out the steps of the method of any one of claims 1 to 7.

11. A computer program product comprising a computer program, characterized in that the computer program realizes the steps of the method of any one of claims 1 to 7 when executed by a processor.