A flight trajectory continuous simulation integrated digital simulation system and method

Abstract

The invention relates to the technical field of simulation of aerial flight environment of aircraft engines, and discloses a flight trajectory continuous simulation integrated digital simulation system and method. By obtaining in advance the target task parameters in the task profile grid points and the set of reachable points of the test bench task, a reachable set evaluation method and an optimization idea network projection mapping model are adopted to evaluate the matching ability of the test bench supply / exhaust resource configuration and the task profile; if the capabilities match, a corresponding aerial simulation control instruction is generated according to the task profile, and the flight trajectory is continuously simulated; otherwise, the task profile is adjusted or the test bench supply / exhaust resource configuration is optimized until the test bench supply / exhaust resource configuration matches the task profile, so as to ensure that the task can be safely tested under the current test bench capability conditions to complete the flight trajectory simulation, and ensure that the intake and exhaust environment conditions matching the aerial working state can be provided for the tested engine, so as to simulate the engine continuous running state in the air more realistically and effectively.

Description

Technical Field

[0001] The invention relates to the technical field of simulation of aerial flight environment of aircraft engines, and discloses a flight trajectory continuous simulation integrated digital simulation system and method. Background Art

[0002] The transient characteristics of aircraft engines and the working characteristics of multi-mission profile flight trajectories are bound to become the key concerns and difficulties in the current development of aircraft engines and their aerial simulation test research. If continuous simulation and experimental research on the multi-mission profile flight environment of aircraft engines can be achieved, the air working characteristics of the engine, especially the combat capability and effectiveness, can be reflected on the ground in advance. During the operation of the engine in the complex mission profile in the air, the performance of its components, working stability, common working characteristics, combustion characteristics and structural clearances will change with the change of flight environment conditions. The continuous change of the working environment in the air will have a significant impact on the performance and characteristics of the engine. Continuous and complex flight mission profiles can only be simulated and tested under the conditions of continuously changing flight environments.

[0003] The flight environment simulation system is a key test equipment for the test bench to simulate the flight altitude and Mach number of aircraft engines. The quality of the system's adjustment performance directly determines the confidence of the engine test bench simulation test. The relevant control technology is a key technology that is very distinctive and representative in the test bench test. With the intensification of the engine development process, clear task requirements have been put forward for the continuous simulation of multi-mission profile flight trajectories. In order to explore the engine's operating status and working boundaries within the full flight envelope, the environmental simulation system needs to continuously and dynamically adjust the altitude and Mach number according to a specific flight trajectory under a certain time span and specific incoming flow conditions, so as to provide the test engine with intake and exhaust environmental conditions that match the working status in the air, and more realistically and effectively simulate the engine's continuous operation status in the air.

[0004] Compared with aerial simulation tests under specific working conditions test points, when conducting continuous simulation tests of aerial multi-mission profile flight trajectories on the test bench, the matching requirements between the various operational equipment of the flight environment simulation system are more stringent, the coupling correlation between the subsystems is more complex, the safe operation requirements between multiple systems are higher, and the system multi-variable control is more difficult. Summary of the invention

[0005] The purpose of the present invention is to provide a flight trajectory continuous simulation integrated digital simulation system and method, which can ensure that the mission can be completed by safe testing under the current test bench capability conditions. Flight trajectory simulation.

[0006] In order to achieve the above technical effects, the technical solution adopted by the present invention is:

[0007] A flight trajectory continuous simulation integrated digital simulation method, comprising:

[0008] Acquire an engine flight trajectory mission, and decompose the flight trajectory mission to generate a flight mission profile;

[0009] Acquire target mission parameters in the mission profile grid points, wherein the target mission parameters of each grid point include target gas pressure, target gas temperature, and target mass flow rate;

[0010] According to the test bench design parameters, a set of task reachable points of the test bench is constructed, wherein the task reachable point set includes a combination set of gas pressure, gas temperature and gas mass flow rate that can be provided by the test bench;

[0011] The reachable set evaluation method and the optimal thought network projection mapping model are used to evaluate the matching ability between the test bench supply / extraction resource configuration and the mission profile;

[0012] If the capabilities match, the corresponding air simulation control instructions are generated according to the mission profile to continuously simulate the flight trajectory; otherwise, the mission profile is adjusted or the test bench supply / exhaust resource configuration is optimized until the test bench supply / exhaust resource configuration matches the mission profile.

[0013] Furthermore, the method of using the reachable set evaluation method and the optimization thought network projection mapping model to evaluate the matching ability of the test bench supply / extraction resource configuration and the mission profile includes:

[0014] Taking the target task parameters of all grid points on the task profile as input, the task reachable optimization set is analyzed and obtained through the optimization thought network projection mapping model based on the reachable time;

[0015] Analyze and obtain the Hausdorff distances from all grid points of the mission profile to the set of mission reachable points;

[0016] If the Hausdorff distance is less than or equal to the preset threshold, it means that the test bench supply / extraction resource configuration matches the mission profile within the mission reachable terminal time, otherwise the test bench supply / extraction resource configuration does not match the mission profile.

[0017] Furthermore, the optimal thought network projection mapping model based on reachable time is: ,in is the input state, , Output air flow pressure for the test bench, Test bench output air flow temperature, Output airflow mass flow rate for the test bench, for The differential of the input state at each moment, is the pressure of the test bench chamber, is the test bench chamber temperature, is the differential symbol, is an output reachable point, and , is the state sequence within the reachable time, is the initial output state, is the initial input state, for The set of feasible inputs that always satisfy the system input constraints, To meet the lower bound of the input constraint, To satisfy the upper limit of the input constraint, is the cost function, is the time it takes for the task to reach the terminal, is the reachable terminal state of the task, are the grid points, ,in is the target gas pressure, is the target gas temperature, is the target gas mass flow rate.

[0018] In order to achieve the above technical effects, the present invention also provides a flight trajectory continuous simulation integrated digital simulation system, including

[0019] A task decomposition module, used for obtaining an engine flight trajectory task, and decomposing the flight trajectory task to generate a flight mission profile;

[0020] A target task acquisition module, used to acquire target task parameters in the task profile grid points, wherein the target task parameters of each grid point include target gas pressure, target gas temperature and target mass flow rate;

[0021] A task reachable point set construction module is used to construct a test bench task reachable point set according to the test bench design parameters, wherein the task reachable point set includes a combination set of gas pressure, gas temperature and gas mass flow rate that can be provided by the test bench;

[0022] An evaluation module is used to evaluate the matching capability between the test bench supply / extraction resource configuration and the mission profile using the reachable set evaluation method and the optimization thought network projection mapping model;

[0023] The flight trajectory simulation module is used to generate corresponding air simulation control instructions according to the mission profile when the test bench air supply / extraction resource configuration matches the mission profile, and continuously simulate the flight trajectory.

[0024] Furthermore, the evaluation module includes:

[0025] An optimization unit, used for taking the target task parameters of all grid points on the task profile as input, and analyzing and obtaining a task reachable optimization set through an optimization thought network projection mapping model based on reachable time;

[0026] An analysis unit, used for analyzing and obtaining the Hausdorff distances from all grid points of the mission profile to the set of mission reachable points;

[0027] A comparison and judgment unit is used to compare the Hausdorff distance with a preset threshold. If the Hausdorff distance is less than or equal to the preset threshold, it means that the test bench supply / exhaust resource configuration matches the mission profile within the mission reachable terminal time, otherwise the test bench supply / exhaust resource configuration does not match the mission profile.

[0028] Furthermore, in the optimization unit, the optimal thought network projection mapping model based on reachable time is: ,in is the input state, , Output air flow pressure for the test bench, Test bench output air flow temperature, Output airflow mass flow rate for the test bench, for The differential of the input state at each moment, is the pressure of the test bench chamber, is the test bench chamber temperature, is the differential symbol, is an output reachable point, and , is the state sequence within the reachable time, is the initial output state, is the initial input state, for The set of feasible inputs that always satisfy the system input constraints, To meet the lower bound of the input constraint, To satisfy the upper limit of the input constraint, is the cost function, is the time it takes for the task to reach the terminal, is the reachable terminal state of the task, are the grid points, ,in is the target gas pressure, is the target gas temperature, is the target gas mass flow rate.

[0029] Furthermore, it also includes a simulation demonstration module for dynamically demonstrating the simulation effect of the flight trajectory generated by the flight trajectory simulation module.

[0030] Furthermore, the simulation demonstration module includes a Mach number and altitude command display unit, a throttle lever opening display unit, an engine mass flow display unit, an intake system simulation display unit, and an exhaust system display unit.

[0031] Compared with the prior art, the beneficial effects of the present invention are as follows: the present invention verifies the matching of the mission profile and the test bench air supply / exhaust resource configuration in advance. If the capabilities match, the corresponding air simulation control instructions are generated according to the mission profile to continuously simulate the flight trajectory. Otherwise, the mission profile is adjusted or the test bench air supply / exhaust resource configuration is optimized until the test bench air supply / exhaust resource configuration matches the mission profile, ensuring that the mission can be safely tested under the current test bench capability conditions to complete the flight trajectory simulation, and ensuring that the intake and exhaust environmental conditions matching the air working state of the engine under test can be provided, thereby more realistically and effectively simulating the engine's continuous operation state in the air. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a flow chart of the integrated digital simulation method for continuous simulation of flight trajectory in the embodiment;

[0033] Figure 2 It is a structural block diagram of the integrated digital simulation system for continuous simulation of flight trajectory in the embodiment;

[0034] Among them, 1. Task decomposition module; 2. Target task acquisition module; 3. Task reachable point set construction module; 4. Evaluation module; 401. Optimization unit; 402. Analysis unit; 403 Comparison and judgment unit; 5. Flight trajectory simulation module; 6. Simulation demonstration module; 601. Mach number and altitude instruction display unit; 602. Throttle lever opening display unit; 603. Engine mass flow display unit; 604. Intake system simulation display unit; 605. Exhaust system display unit. DETAILED DESCRIPTION

[0035] The present invention is further described in detail below in conjunction with the embodiments and drawings. However, it should not be understood that the scope of the above subject matter of the present invention is limited to the following embodiments, and all technologies realized based on the content of the present invention belong to the scope of the present invention.

[0036] Example

[0037] See also Figure 1 and Figure 2 , a flight trajectory continuous simulation integrated digital simulation method, including

[0038] Acquire an engine flight trajectory mission, and decompose the flight trajectory mission to generate a flight mission profile;

[0039] Acquire target mission parameters in the mission profile grid points, wherein the target mission parameters of each grid point include target gas pressure, target gas temperature, and target mass flow rate;

[0040] According to the test bench design parameters, a set of task reachable points of the test bench is constructed, wherein the task reachable point set includes a combination set of gas pressure, gas temperature and gas mass flow rate that can be provided by the test bench;

[0041] The reachable set evaluation method and the optimal thought network projection mapping model are used to evaluate the matching ability between the test bench supply / extraction resource configuration and the mission profile;

[0042] If the capabilities match, the corresponding air simulation control instructions are generated according to the mission profile to continuously simulate the flight trajectory; otherwise, the mission profile is adjusted or the test bench supply / exhaust resource configuration is optimized until the test bench supply / exhaust resource configuration matches the mission profile.

[0043] In this embodiment, before performing flight trajectory simulation analysis on the aircraft engine, the target mission parameters in the mission profile grid points and the set of reachable points of the test bench mission are obtained in advance, and then the reachable set evaluation method and the optimization idea network projection mapping model are used to evaluate the matching ability of the test bench supply / exhaust resource configuration and the mission profile; by pre-verifying the matching of the mission profile and the test bench supply / exhaust resource configuration, if the capabilities match, the corresponding air simulation control instructions are generated according to the mission profile, and the flight trajectory is continuously simulated, otherwise the mission profile is adjusted or the test bench supply / exhaust resource configuration is optimized until the test bench supply / exhaust resource configuration matches the mission profile, ensuring that the mission can be safely tested under the current test bench capability conditions to complete the flight trajectory simulation.

[0044] Based on the same inventive concept, this embodiment also provides a flight trajectory continuous simulation integrated digital simulation system, including

[0045] The task decomposition module 1 is used to obtain the engine flight trajectory task, decompose the flight trajectory task, and generate a flight mission profile;

[0046] A target task acquisition module 2 is used to acquire target task parameters in the task profile grid points, wherein the target task parameters of each grid point include target gas pressure, target gas temperature and target mass flow rate;

[0047] A task reachable point set construction module 3 is used to construct a test bench task reachable point set according to the test bench design parameters, wherein the task reachable point set includes a combination set of gas pressure, gas temperature and gas mass flow rate that can be provided by the test bench;

[0048] Evaluation module 4 is used to evaluate the matching capability between the test bench supply / extraction resource configuration and the mission profile by using the reachable set evaluation method and the optimization thought network projection mapping model;

[0049] The flight trajectory simulation module 5 is used to generate corresponding air simulation control instructions according to the mission profile when the test bench air supply / exhaust resource configuration matches the mission profile, and continuously simulate the flight trajectory.

[0050] The evaluation module 4 of this embodiment includes:

[0051] An optimization unit 401 is used to take the target task parameters of all grid points on the task profile as input, and analyze and obtain a task reachable optimization set through an optimization thought network projection mapping model based on reachable time;

[0052] An analysis unit 402 is used to analyze and obtain the Hausdorff distances from all grid points of the mission profile to the mission reachable point set;

[0053] The comparison and judgment unit 403 is used to compare the Hausdorff distance with a preset threshold. If the Hausdorff distance is less than or equal to the preset threshold, it means that the test bench supply / exhaust resource configuration matches the task profile within the task reachable terminal time, otherwise the test bench supply / exhaust resource configuration does not match the task profile.

[0054] In the optimization unit 401 of this embodiment, the optimal thought network projection mapping model based on reachable time is: ,in is the input state, , Output air flow pressure for the test bench, Test bench output air flow temperature, Output airflow mass flow rate for the test bench, for The differential of the input state at each moment, is the pressure of the test bench chamber, is the test bench chamber temperature, is the differential symbol, is an output reachable point, and , is the state sequence within the reachable time, is the initial output state, is the initial input state, for The set of feasible inputs that always satisfy the system input constraints, To meet the lower bound of the input constraint, To satisfy the upper limit of the input constraint, is the cost function, is the time it takes for the task to reach the terminal, is the reachable terminal state of the task, are the grid points, ,in is the target gas pressure, is the target gas temperature, is the target gas mass flow rate.

[0055] The flight trajectory continuous simulation integrated digital simulation system of the present embodiment further comprises a simulation demonstration module 6 for dynamically demonstrating the effect of continuous simulation of the flight trajectory generated by the flight trajectory simulation module.

[0056] The simulation demonstration module 6 in this embodiment includes a Mach number and altitude command display unit 601 , a throttle lever opening display unit 602 , an engine mass flow display unit 603 , an intake system simulation display unit 604 , and an exhaust system display unit 605 .

[0057] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A flight trajectory continuous simulation integrated digital simulation method, characterized in that: include Acquire an engine flight trajectory mission, and decompose the flight trajectory mission to generate a flight mission profile; Acquire target mission parameters in the mission profile grid points, wherein the target mission parameters of each grid point include target gas pressure, target gas temperature, and target mass flow rate; According to the test bench design parameters, a set of task reachable points of the test bench is constructed, wherein the task reachable point set includes a combination set of gas pressure, gas temperature and gas mass flow rate that can be provided by the test bench; A reachable set evaluation method and an optimal network projection mapping model are used to evaluate the matching ability of the test bench supply / exhaust resource configuration and the task profile; wherein, the method of using the reachable set evaluation method and the optimal network projection mapping model to evaluate the matching ability of the test bench supply / exhaust resource configuration and the task profile includes: taking the target task parameters of all grid points on the task profile as input, analyzing and obtaining the task reachable optimization set through the optimal network projection mapping model based on the reachable time; analyzing and obtaining the Hausdorff distance from all grid points of the task profile to the set of task reachable points; if the Hausdorff distance is less than or equal to a preset threshold, it means that the test bench supply / exhaust resource configuration matches the task profile within the task reachable terminal time, otherwise the test bench supply / exhaust resource configuration does not match the task profile; the optimal network projection mapping model based on the reachable time is ,in is the input state, , Output air flow pressure for the test bench, Test bench output air flow temperature, Output airflow mass flow rate for the test bench, for The differential of the input state at each moment, is the pressure of the test bench chamber, is the test bench chamber temperature, is the differential symbol, is an output reachable point, and , is the state sequence within the reachable time, is the initial output state, is the initial input state, for The set of feasible inputs that always satisfy the system input constraints, To meet the lower bound of the input constraint, To satisfy the upper limit of the input constraint, is the cost function, is the time it takes for the task to reach the terminal, is the reachable terminal state of the task, are the grid points, ,in is the target gas pressure, is the target gas temperature, is the target gas mass flow rate; If the capabilities match, the corresponding air simulation control instructions are generated according to the mission profile to continuously simulate the flight trajectory; otherwise, the mission profile is adjusted or the test bench supply / exhaust resource configuration is optimized until the test bench supply / exhaust resource configuration matches the mission profile.

2. A flight trajectory continuous simulation integrated digital simulation system, characterized in that: include A task decomposition module, used for obtaining an engine flight trajectory task, and decomposing the flight trajectory task to generate a flight mission profile; A target task acquisition module, used to acquire target task parameters in the task profile grid points, wherein the target task parameters of each grid point include target gas pressure, target gas temperature and target mass flow rate; A task reachable point set construction module is used to construct a test bench task reachable point set according to the test bench design parameters, wherein the task reachable point set includes a combination set of gas pressure, gas temperature and gas mass flow rate that can be provided by the test bench; An evaluation module is used to evaluate the matching ability of the test bench supply / exhaust resource configuration and the task profile by using a reachable set evaluation method and an optimal thought network projection mapping model; wherein, the method of evaluating the matching ability of the test bench supply / exhaust resource configuration and the task profile by using the reachable set evaluation method and the optimal thought network projection mapping model includes: taking the target task parameters of all grid points on the task profile as input, analyzing and obtaining the task reachable optimization set through the optimal thought network projection mapping model based on reachable time; analyzing and obtaining the Hausdorff distance from all grid points on the task profile to the set of task reachable points; if the Hausdorff distance is less than or equal to a preset threshold, it means that the test bench supply / exhaust resource configuration matches the task profile within the task reachable terminal time, otherwise the test bench supply / exhaust resource configuration does not match the task profile; the optimal thought network projection mapping model based on reachable time is ,in is the input state, , Output air flow pressure for the test bench, Test bench output air flow temperature, Output airflow mass flow rate for the test bench, for The differential of the input state at each moment, is the pressure of the test bench chamber, is the test bench chamber temperature, is the differential symbol, is an output reachable point, and , is the state sequence within the reachable time, is the initial output state, is the initial input state, for The set of feasible inputs that always satisfy the system input constraints, To meet the lower bound of the input constraint, To satisfy the upper limit of the input constraint, is the cost function, is the time it takes for the task to reach the terminal, is the reachable terminal state of the task, are the grid points, ,in is the target gas pressure, is the target gas temperature, is the target gas mass flow rate; The flight trajectory simulation module is used to generate corresponding air simulation control instructions according to the mission profile when the test bench air supply / extraction resource configuration matches the mission profile, and continuously simulate the flight trajectory.

3. The flight trajectory continuous simulation integrated digital simulation system according to claim 2 is characterized in that: It also includes a simulation demonstration module for dynamically demonstrating the effect of continuous simulation of the flight trajectory generated by the flight trajectory simulation module.

4. The flight trajectory continuous simulation integrated digital simulation system according to claim 3 is characterized in that: The simulation demonstration module includes a Mach number and altitude command display unit, a throttle lever opening display unit, an engine mass flow display unit, an intake system simulation display unit, and an exhaust system display unit.

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