CN111046497B - Rapid assessment device for high-altitude high-speed airplane penetration viability - Google Patents
Rapid assessment device for high-altitude high-speed airplane penetration viability Download PDFInfo
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- CN111046497B CN111046497B CN201911348515.XA CN201911348515A CN111046497B CN 111046497 B CN111046497 B CN 111046497B CN 201911348515 A CN201911348515 A CN 201911348515A CN 111046497 B CN111046497 B CN 111046497B
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Abstract
The application belongs to the aircraft general design field, in particular to a high-altitude high-speed aircraft sudden-defense viability rapid evaluation device, which comprises: the missile performance model is used for simulating the missile all-airspace trajectory and outputting missile flight information in real time; the airplane performance model is used for truly simulating the aerodynamic characteristics and maneuverability of the airplane; the simulation framework module is used for calling the airplane performance model and the missile performance model; the processing module cluster is controlled by the simulation framework module and is used for realizing the rapid evaluation, simulation and parallel calculation of the penetration and defense viability of the high-altitude and high-speed aircraft; the simulation section setting module is used for providing a simulation range and a step length of corresponding parameters; and the simulation result analysis module is used for analyzing the simulation result data. The device for rapidly evaluating the high-altitude high-speed aircraft penetration viability can rapidly evaluate the high-altitude high-speed aircraft penetration viability, accelerate the design iteration of an aircraft platform scheme and a penetration scheme, rapidly verify the feasibility of the scheme, and improve the design efficiency.
Description
Technical Field
The application belongs to the field of overall design of airplanes, and particularly relates to a device for rapidly evaluating the penetration viability of a high-altitude and high-speed airplane.
Background
The air strength plays a crucial role in modern war, and is the core of the air strength of the national military, the high-altitude high-speed aircraft is one of important air strengths, and the penetration viability of the high-altitude high-speed aircraft facing the air-to-air missile is an important index for evaluating the performance of the aircraft, so that the rapid evaluation method of the penetration viability of the high-altitude high-speed aircraft becomes an important research subject for aviation engineers.
The high-altitude high-speed aircraft penetration survivability is closely related to stealth capacity, maneuverability, engine thrust, penetration strategy and the like of the aircraft, so that the high-altitude high-speed aircraft relates to a plurality of parameters at the initial design stage, and in order to ensure that the aircraft has high penetration survivability facing an air-to-air missile, the penetration survivability of the aircraft under different parameter combinations needs to be rapidly evaluated so as to accelerate the iterative process of aircraft performance parameter design.
In the design stage of the airplane scheme, when the traditional method is used for assessing the survivability of the defense, theoretical analysis is often performed through an expert review method, and the method strongly depends on expert experience. Because of numerous variables of the factors influencing the survival of the defense, the theoretical analysis is difficult, and often only qualitative conclusions can be given, so that the design of the scheme is poorly instructive.
Disclosure of Invention
In order to solve at least one of the technical problems, the application provides a device for rapidly evaluating the penetration viability of a high-altitude high-speed aircraft.
The application discloses quick evaluation device of high altitude high speed aircraft suddenly-defense viability includes:
the missile performance model is used for simulating the missile all-airspace trajectory and outputting missile flight information in real time;
the airplane performance model is used for truly simulating the aerodynamic characteristics and maneuverability of the airplane and responding to the control command;
the simulation framework module is used for calling the airplane performance model and the missile performance model;
the processing module cluster is controlled by the simulation framework module and is used for realizing the rapid evaluation, simulation and parallel calculation of the penetration and defense viability of the high-altitude and high-speed aircraft;
the simulation profile setting module is used for providing a simulation range and a step length of corresponding parameters before the processing module cluster carries out simulation parallel calculation aiming at different tasks;
and the simulation result analysis module is used for analyzing the simulation result data obtained by the simulation framework module.
According to at least one embodiment of the present application, the missile performance model includes:
the information interaction module is used for completing input and output information interaction with the airplane simulation platform;
the missile guidance module is used for finishing missile guidance law calculation;
the missile stabilization module is used for simulating the overload response characteristic of the missile;
and the kinematics and dynamics module is used for calculating the preset movement information of the missile.
According to at least one embodiment of the application, the aircraft performance model comprises an aircraft dynamics model or a kinematics model.
According to at least one embodiment of the application, the aircraft dynamics model or the kinematics model adopts a dynamic inverse method to realize the attitude control of the inner ring of the aircraft, and utilizes a PID method to realize the automatic control of the course and the altitude of the outer ring.
According to at least one embodiment of the present application, the simulation framework module includes:
and the dynamic link library calling unit is used for calling the missile dynamic link library model.
According to at least one embodiment of the present application, the parameters provided in the simulation profile setting module include 9, which are: the system comprises a bullet shooting moment loader height, a bullet shooting moment loader speed, a bullet shooting moment loader high speed, a bullet shooting moment loader overload, a bullet shooting moment initial distance, a loader radar frame angle, a bullet shooting moment entrance angle and a bullet shooting moment azimuth angle in a sudden prevention process.
According to at least one embodiment of the present application, the simulation profile setting module includes:
the emergency boundary value solving unit is used for taking the simulation range and the step length of each parameter as cycle parameters; wherein
The processing module cluster can automatically complete the simulation calculation of all parameter combinations.
According to at least one embodiment of the present application, the breakthrough safety boundary value solving unit is further configured to obtain the breakthrough safety boundary value of the corresponding parameter in the fixed scene by a dichotomy.
According to at least one embodiment of the application, the device for rapidly evaluating the penetration viability of the high-altitude and high-speed aircraft further comprises:
and the display module is used for displaying the dynamic process of the relative position change of the missile and the airplane in the airplane defense process according to the simulation result data.
The application has at least the following beneficial technical effects:
the device for rapidly evaluating the penetration viability of the high-altitude high-speed aircraft can rapidly evaluate the penetration viability of the high-altitude high-speed aircraft, accelerates the design iteration of an aircraft platform scheme and a penetration scheme, rapidly verifies the feasibility of the scheme, and improves the design efficiency.
Drawings
FIG. 1 is a schematic structural diagram of a rapid assessment device for the penetration viability of a high-altitude and high-speed aircraft.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described are some, but not all embodiments of the disclosure. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The device and the method integrate a missile model and an airplane model through a simulink simulation platform, and simultaneously build a simulation scheduling and simulation result analysis module, so that the whole-process closed-loop simulation of the high-altitude high-speed airplane penetration viability is realized, the rationality of an airplane platform scheme and a penetration strategy is verified quickly, and the design iteration of the scheme is accelerated. The technical problems to be solved are as follows:
a) Rapidly modeling a missile performance model;
b) Rapidly modeling an airplane performance model;
c) Designing a simulation framework based on simulink software;
d) Setting a module design for the simulation section;
e) And (5) designing a simulation result analysis module.
The functions of the modules of the rapid assessment device for the survivability of the high-altitude and high-speed aircraft penetration are explained in an implementation step form with reference to the attached drawing 1.
The application of the device for rapidly evaluating the penetration viability of the high-altitude and high-speed aircraft comprises the following implementation steps:
1. rapid modeling of missile performance model
The missile performance model (simulation model) adopts a three-degree-of-freedom mass center kinematics and a dynamics model, is obtained by simplifying a six-degree-of-freedom simulation model, and comprises the steps of realizing missile all-airspace trajectory simulation, inputting the position and speed of a carrier at the moment of launching, the target position, speed, RCS and other information, and outputting missile flight information in real time after trajectory simulation calculation, wherein the missile flight information comprises the information of the position, speed, attitude angle, attack angle, sideslip angle, angular speed, miss distance and the like of a missile.
Further, the preferred missile performance model consists of the following modules:
1) The information interaction module is used for finishing input and output information interaction with the airborne simulation platform;
2) The missile guidance module is used for finishing missile guidance law calculation;
3) The missile stabilization module is used for simulating the overload response characteristic of a missile;
4) And the kinematics and dynamics module comprises a missile kinematics dynamics differential equation, a pneumatic model and a general parameter model and is used for completing the calculation of the movement information such as the position, the speed, the attitude and the like of the missile.
The missile performance model is developed by adopting a standard C/C + + language and is packaged in a dynamic link library form, so that the modular design is realized, and the follow-up model is convenient to update and replace. The encapsulated model provides 3 interface functions of a simulation initialization function, a stepping function and a termination function for the outside for the calling of the simulation framework module.
2. Rapid modeling of aircraft performance model
In the rapid assessment process of the aircraft penetration viability, rapid assessment and design iteration aiming at various platform schemes are required. In simulation, an airplane model capable of truly simulating aerodynamic characteristics and maneuvering capacity of an airplane needs to be applied, and the airplane is required to respond to instructions such as overload and course, so that for each airplane scheme, principle control law rapid design and development needs to be carried out on the basis of a real airplane dynamics model, and the evaluation rapidity is guaranteed.
In view of the above requirements, a simulink tool is utilized for aircraft dynamics/kinematics model and principle control law development. The method is characterized in that a six-degree-of-freedom model is adopted for aircraft kinematics/dynamics simulation, the attitude control of an inner ring of the aircraft is realized by using a dynamic inverse method, and the automatic control of the course and the height of an outer ring is realized by using a classical PID method. The inner ring control law designed by a dynamic inverse method can realize automatic calculation of control parameters after airplane data is replaced, and control parameters are not required to be repeatedly designed in the iteration process of a design scheme, so that the efficiency is improved.
3. Simulation framework module design
The simulation framework (or simulation framework module) is responsible for calling the airplane performance model and the missile performance model, and the high-altitude and high-speed airplane penetration viability is quickly evaluated through model joint simulation. The simulation framework utilizes Simulink software to carry out development and design, and a numerical calculation tool and a kinematics and dynamics simulation module provided by Simulink are applied, so that the development efficiency is improved.
3.1 dynamic link library invocation:
and a dynamic link library calling unit in the simulation framework calls the missile dynamic link library model by utilizing the S function provided by Simulink. The S function is a method capable of integrating C/C + + codes in a Simulink model, firstly, a missile model dynamic link library is loaded by writing the C/C + + codes and method functions in the missile model dynamic link library are called, and then the codes are compiled into binary files which can be identified by the Simulink by utilizing a Mex compiling tool provided by Matlab. And creating an S function module in Simulink, calling a binary file generated by compiling in the S function module, and integrating the missile model into a simulation framework by the method.
3.2 parallel computing:
the variable dimension of the high-altitude high-speed aircraft penetration test section is multiple, and the simulation calculation amount is large, so that the high-altitude high-speed aircraft penetration test section can also comprise a processing module cluster (namely a parallel calculation toolbox); the simulation framework adopts a Matlab parallel computing toolbox to realize the penetration viability evaluation simulation parallel computing, and the simulation efficiency is improved. The Matlab parallel computing toolkit can solve the computing problem and the data intensive problem by using a multi-core processor, a GPU and a computer cluster, and can run a plurality of simulations of one model in parallel by being matched with Simulink.
The simulation framework first obtains the number of available processors (processing module clusters) using the parpool function provided by matlab software, and starts parallel computing using a default configuration. And then reading the setting file of the simulation profile setting module, classifying simulation calculation tasks to be executed, and distributing the calculation tasks to different processors by using a parfor function to perform parallel calculation.
4. Simulation profile setting module design
The simulation profile setting comprises a plurality of parameters, the simulation range and the step length of each parameter need to be set before the simulation is started, and the specific parameters are as follows by 9 parameters: the height of the loader is measured at the moment of shooting; the loading speed is measured at the moment of shooting; the machine is high-speed when shooting; the speed of the machine at the moment of shooting; the machine is overloaded in the process of emergency defense; initial distance of the bullet eyes at the moment of shooting; a radar frame angle of the machine; the bullet hitting moment enters the angle; and (4) a shooting moment azimuth angle.
4.1 round robin Algorithm
One method for solving the breakthrough prevention boundary value is to traverse the combination of all parameters, and artificial traversal cannot be realized due to excessive parameter combinations.
Furthermore, another method for solving the breakthrough boundary value by the breakthrough boundary value solving unit is a dichotomy, wherein 9 simulation parameters are used in the aircraft breakthrough simulation, the value of 8-dimensional parameters is fixed, and the remaining one-dimensional parameters are solved by the dichotomy, so that the breakthrough boundary value of the one-dimensional parameters under a fixed scene can be obtained.
5 simulation result analysis module design
And judging whether the missile hits a high-altitude high-speed airplane or not according to the variation of the height, the speed and the miss distance of the missile in the penetration simulation result, and if the missile does not hit the high-altitude high-speed airplane, analyzing the miss reason, wherein the reason may be that the missile falls on the ground, the speed is too low, the miss distance is too large and the like.
In addition, in order to observe the penetration simulation result more intuitively, the system also comprises a display module, and the simulation result is visually processed through a foldath 3d plug-in, so that the whole process of the high-altitude high-speed aircraft penetration can be demonstrated in an animation mode, and an aircraft designer can intuitively know the dynamic process of the relative position change of a missile and an aircraft in the aircraft penetration process, so that simulation parameters can be better designed, and the penetration boundary value can be more efficiently solved.
In summary, the device for rapidly evaluating the penetration viability of the high-altitude high-speed aircraft can rapidly evaluate the penetration viability of the high-altitude high-speed aircraft, accelerate the design iteration of the aircraft platform scheme and the penetration scheme, rapidly verify the feasibility of the scheme and improve the design efficiency. In the design stage of the airplane scheme, when the traditional method is used for carrying out the defense burst viability evaluation, theoretical analysis is often carried out through an expert review method, only qualitative conclusion can be given by strongly depending on expert experience, and the guidance capability of the airplane scheme design is poor.
The method applies a six-degree-of-freedom model with airplane aerodynamic characteristics in simulation, and utilizes a dynamic inverse method to design a principle control law, so that not only can the simulation precision be ensured, but also the rapidity of design can be improved. In the simulation process, if a controller is designed by using a classical control law design method, the development period is long, once an airplane scheme is changed, the control law needs to be redesigned, and the inner-ring control law is designed by using a dynamic inverse method, so that the automatic calculation of control parameters after the airplane data is replaced can be realized, the control parameters do not need to be repeatedly designed in the scheme iteration process, and the evaluation efficiency is improved.
Furthermore, in order to solve the problem of combined explosion of a plurality of simulation parameters in the design process, a parallel computing algorithm and a dichotomy boundary value solving algorithm are designed in simulink, so that the simulation efficiency is greatly improved, and the iteration period of the aircraft parameter design is shortened. Aiming at a complex simulation result, the simulation data is visually processed, so that an aircraft designer can visually observe the whole process of the penetration viability simulation and the penetration result.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (9)
1. The utility model provides a high altitude high speed aircraft suddenly prevents quick evaluation device of viability which characterized in that includes:
the missile performance model is used for simulating the missile all-airspace trajectory and outputting missile flight information in real time;
the airplane performance model is used for truly simulating the aerodynamic characteristics and maneuverability of an airplane and responding to a control command;
the simulation framework module is used for calling the airplane performance model and the missile performance model;
the processing module cluster is controlled by the simulation frame module and is used for realizing the rapid evaluation, simulation and parallel calculation of the high-altitude high-speed aircraft penetration survivability;
the simulation section setting module is used for providing a simulation range and a step length of corresponding parameters before the processing module cluster carries out simulation parallel computation aiming at different tasks;
and the simulation result analysis module is used for analyzing the simulation result data obtained by the simulation framework module.
2. The device for rapidly evaluating the penetration viability of the high-altitude high-speed aircraft according to claim 1, wherein the missile performance model comprises:
the information interaction module is used for completing input and output information interaction with the airplane simulation platform;
the missile guidance module is used for finishing missile guidance law calculation;
the missile stabilization module is used for simulating the overload response characteristic of the missile;
and the kinematics and dynamics module is used for calculating the preset motion information of the missile.
3. The device for rapidly evaluating the penetration viability of the high-altitude and high-speed aircraft according to claim 1, wherein the aircraft performance model comprises an aircraft dynamics model or a kinematics model.
4. The device for rapidly evaluating the penetration viability of the high-altitude high-speed aircraft according to claim 3, wherein the aircraft dynamics model or the kinematics model adopts a dynamic inverse method to realize the attitude control of the inner ring of the aircraft, and utilizes a PID method to realize the automatic control of the course and the altitude of the outer ring.
5. The device for rapidly evaluating the penetration viability of the high-altitude high-speed aircraft according to claim 2, wherein the simulation framework module comprises:
and the dynamic link library calling unit is used for calling the missile dynamic link library model.
6. The device for rapidly evaluating the penetration viability of the high-altitude and high-speed aircraft according to claim 1, wherein the parameters provided in the simulation profile setting module comprise 9 parameters which are respectively: the system comprises a bullet shooting moment loader height, a bullet shooting moment loader speed, a bullet shooting moment loader high speed, a bullet shooting moment loader overload, a bullet shooting moment initial distance, a loader radar frame angle, a bullet shooting moment entrance angle and a bullet shooting moment azimuth angle in a sudden prevention process.
7. The device for rapidly evaluating the penetration viability of the high-altitude and high-speed aircraft according to claim 6, wherein the simulation profile setting module comprises:
the emergency boundary value solving unit is used for taking the simulation range and the step length of each parameter as cycle parameters; wherein
The processing module cluster can automatically complete the simulation calculation of all parameter combinations.
8. The apparatus for rapidly evaluating the penetration viability of a high-altitude high-speed aircraft according to claim 7, wherein the penetration boundary value solving unit is further configured to obtain the penetration boundary values of the corresponding parameters in the fixed scene by a dichotomy.
9. The device for rapidly evaluating the penetration viability of the high-altitude and high-speed aircraft according to claim 1, further comprising:
and the display module is used for displaying the dynamic process of the relative position change of the missile and the airplane in the airplane defense process according to the simulation result data.
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