Air flow control method and system for aircraft engine air environment simulation test

Abstract

The present invention belongs to the field of aviation engine air environment simulation test, and provides an air flow path control method and system for aviation engine air environment simulation test, the method is used to control the air pipe network of the aviation engine air flight environment simulation test bench, including: according to the air environment simulation test subject, constructing the compressed air flow path on-off characteristic matrix of the air pipe network; obtaining the on-off prediction state of all compressed air flow paths at the next moment through the compressed air flow path on-off characteristic matrix and the actual on-off state of all compressed air flow paths at the previous moment; according to the compressed air flow path on-off characteristic matrix and the on-off prediction state, outputting the on-off control state of each compressed air flow path in the air pipe network at the next moment. The present invention can perform operation guidance and state judgment on the state control of different compressed air flow paths in the test, ensure the reliability and safety of the test, and reduce the probability of low-level quality accidents caused by human factors.

Description

Technical Field

[0001] The present invention belongs to the field of aerial environment simulation test of aircraft engines, relates to an intake and exhaust condition control technology of an environmental simulation test bench, and specifically relates to an air flow path control method and system for aerial environment simulation test of aircraft engines. Background Art

[0002] During the flight environment simulation test of aircraft engines, the intake and exhaust conditions in the air are simulated in the test bench to test the key performance functions of the engine. At present, the flight environment simulation test of large bypass ratio civil power is usually carried out in the flight environment simulation test bench. The test process has the remarkable characteristics of large air flow (hundreds of kilograms per second) and ultra-wide adjustable range, and complex test process, which makes the air pipe network layout structure of the test bench very large and complex, and the compressed air flow path has the characteristics of intricate.

[0003] When conducting an aerial flight environment simulation test, the on / off and coordination status of different compressed air flow paths is directly determined by the specific test process. Different flow paths have different temperature and pressure properties. If the on / off coordination status of the air flow path is abnormal and inconsistent with the test purpose and process, it will cause irreparable and significant losses to the tested engine, the supporting air supply and exhaust equipment, the compressed air treatment equipment, and other test bench tests. For example: The air pipe network of the aerial flight environment simulation test bench for large bypass ratio aircraft engines contains more than 20 air branches, and there are nearly 50 valves used to control the on / off and coordination of the air flow path. The coordination status is more complicated, which greatly increases the technical difficulty of compressed air flow path control.

[0004] At present, the control of the compressed air flow path of the test bench mainly relies on the operator manually. The excessive reliance on humans makes the fault tolerance of the test platform low, and it is inconsistent with the test safety requirements of the high bypass ratio aircraft engine aerial flight environment simulation test. Summary of the invention

[0005] In order to solve the technical problem that manual control of the air pipe network of the air flight environment simulation test bench is easy to cause harm to the test equipment and potential safety hazards due to misjudgment or operation errors, the present invention discloses an air flow path control method for an air engine air environment simulation test, the method is used to control the air pipe network of the air engine air flight environment simulation test bench, and the method comprises the following steps:

[0006] S101, constructing a compressed air flow path on-off characteristic matrix of the air pipe network according to the air environment simulation test subject;

[0007] S102, obtaining the predicted on-off status of all the compressed air flow paths at the next moment through the on-off characteristic matrix of the compressed air flow paths and the actual on-off status of all the compressed air flow paths at the previous moment;

[0008] S103, outputting the on-off control state of each compressed air flow path in the air pipe network at the next moment according to the on-off characteristic matrix of the compressed air flow path and the on-off prediction state.

[0009] In an optional embodiment of the above step S101, a compressed air flow path on-off characteristic matrix of the air pipe network is constructed according to the air environment simulation test subject, including:

[0010] S1011. Analyze the air environment simulation test subject according to the test process to obtain the test requirements of the aircraft engine at each moment, wherein the test requirements include the total intake air temperature, the total intake air pressure, the total exhaust air temperature, the total exhaust air pressure and the cabin static pressure;

[0011] S1012. According to the test requirements, the control information of each compressed air flow path in the air pipe network at each moment is obtained to obtain the on-off characteristic matrix of the compressed air flow path, wherein the control information includes on-off control instructions and adjustment device identifiers.

[0012] In an optional embodiment, the air environment simulation test subjects include engine ground test, air environment calibration test, headwind resistance test, windmill start test and plateau start test.

[0013] In an optional embodiment of the above step S102, obtaining the predicted on-off state of all the compressed air flow paths at the next moment through the compressed air flow path on-off characteristic matrix and the actual on-off state of all the compressed air flow paths at the previous moment includes:

[0014] S1021, obtaining the actual on-off state of each compressed air flow path according to the actual on-off information of the regulating device of each compressed air flow path at the previous moment;

[0015] S1022, extracting each on-off control instruction of the compressed air flow path corresponding to the previous moment in the on-off characteristic matrix of the compressed air flow path;

[0016] S1023. Through the discrete-time state equation of the compressed air flow path, according to the actual on-off state of all the compressed air flow paths at the previous moment and the on-off control instructions, the on-off state of each of the compressed air flow paths at the next moment is estimated to obtain the on-off predicted state of all the compressed air flow paths.

[0017] Furthermore, in the above step S1023, the expression of the discrete time state equation of the compressed air flow path is:

[0018] , where A is the key boundary locking condition set, that is, the state set of the regulating device of the associated flow path required by each compressed air flow path state, representing the fixed relationship for determining the flow path state, is the actual on-off state of all compressed air flow paths in the air pipe network at time k, B is the conversion matrix that maps the on-off control instructions to the on-off state of the corresponding compressed air flow path in the on-off feature matrix of the compressed air flow path, is the input of the on-off control command of the regulating device of the compressed air flow path at time k, It is the set of predicted on / off states of all compressed air flow paths in the air network at time k+1.

[0019] In an improved embodiment of the air flow path control method for the above-mentioned aircraft engine air environment simulation test, the method further includes:

[0020] S104. According to the test process of the aerial environment simulation test subject, the associated flow paths related to each of the compressed air flow paths are obtained, and a key boundary locking condition set of the air pipe network is established according to the associated flow paths.

[0021] In an optional embodiment of the above step S104, according to the test process of the air environment simulation test subject, an associated flow path related to each of the compressed air flow paths is obtained, and a key boundary locking condition set of the air pipe network is established according to the associated flow paths, including:

[0022] S1041. Analyze the air environment simulation test subject according to the test process to obtain the test requirements of the aircraft engine at each moment, wherein the test requirements include the total intake air temperature, the total intake air pressure, the total exhaust air temperature, the total exhaust air pressure and the cabin static pressure;

[0023] S1042, according to the test requirements, identifying the associated flow path of each compressed air flow path in the air pipe network at each moment;

[0024] S1043. According to the test requirements of the aircraft engine at each moment, establish locking conditions for the associated flow paths of each of the compressed air flow paths to obtain the key boundary locking condition set.

[0025] In an optional embodiment of the above step S103, outputting the on-off control state of each compressed air flow path in the air pipe network at the next moment according to the on-off characteristic matrix of the compressed air flow path and the on-off prediction state includes:

[0026] According to the formula , real-time control of each compressed air flow path in the air pipe network, where C is the on-off characteristic matrix of the compressed air flow path, It is the set of on-off control states of all compressed air flow paths in the air network at time k+1.

[0027] An embodiment of the present invention further provides an air flow control system for an aero-engine aerial environment simulation test, the system comprising a first building module, a prediction model and a control module.

[0028] The first construction module is used to construct the compressed air flow path on-off characteristic matrix of the air pipe network according to the air environment simulation test subject;

[0029] The prediction model is used to obtain the predicted on-off status of all the compressed air flow paths at the next moment through the compressed air flow path on-off characteristic matrix and the actual on-off status of all the compressed air flow paths at the previous moment;

[0030] The control module is used to output the on-off control state of each compressed air flow path in the air pipe network at the next moment according to the on-off characteristic matrix of the compressed air flow path and the on-off prediction state.

[0031] In an optional embodiment of the above system, the system also includes a second construction module, which is used to obtain associated flow paths related to each of the compressed air flow paths according to the test process of the air environment simulation test subject, and establish a set of key boundary locking conditions for the air pipe network based on the associated flow paths.

[0032] An embodiment of the present invention also provides a computer device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements any of the above-mentioned air flow control methods for aerial environment simulation tests of aircraft engines when executing the computer program, so as to solve the technical problem that manual control of the air duct network of the aerial flight environment simulation test bench is prone to damage to the test equipment and potential safety hazards due to misjudgment or operational errors.

[0033] An embodiment of the present invention also provides a computer-readable storage medium, which stores a computer program for executing any of the above-mentioned air flow control methods for aircraft engine air environment simulation tests, so as to solve the technical problem that manual control of the air duct network of the air flight environment simulation test bench is prone to damage to the test equipment and safety hazards due to misjudgment or operational errors.

[0034] Compared with the prior art, the at least one technical solution adopted in the embodiments of this specification can achieve the following beneficial effects:

[0035] The method of the present invention provides a control method for the compressed air flow path of a large bypass ratio aircraft engine air flight environment simulation test bench, which can provide operational guidance and state judgment for the state control of different compressed air flow paths during the test. Compared with relying entirely on manual operation, the method greatly improves the reliability and safety of the intake and exhaust condition control platform of the large bypass ratio aircraft engine air flight environment simulation test bench in the test process operation, reduces the probability of low-level quality accidents caused by human factors, has significant engineering practical value in the field of test bench environment construction technology, and plays an important role in promoting the design and application of other subsequent large-scale test bench environment simulation platforms.

[0036] Furthermore, by locking the on / off of key related flow paths, the disadvantages of traditional methods that are prone to misjudgment or operational errors or damage and safety hazards to aerial flight environment simulation tests through human control can be eliminated, greatly improving the safety of the test and ensuring the smooth development of large bypass ratio aircraft engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0038] Figure 1 A flow chart of an air flow path control method for an aero-engine air environment simulation test disclosed in an embodiment of the present invention;

[0039] Figure 2 The compressed air flow control logic in the air pipe network disclosed in the embodiment of the present invention;

[0040] Figure 3 The structure diagram of the air flow control system for the air environment simulation test of the aircraft engine disclosed in the embodiment of the present invention;

[0041] Figure 4 A schematic diagram of a computer device disclosed in an embodiment of the present invention;

[0042] Among them, 301 is a first building module; 302 is a prediction model; 303 is a control module; 304 is a second building module; 401 is a memory; and 402 is a processor. DETAILED DESCRIPTION

[0043] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0044] The following describes the implementation methods of the present application through specific specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that the following embodiments and the features of the embodiments can be combined with each other in the absence of conflict. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0045] The embodiment of the present invention discloses an air flow control method for an aircraft engine air environment simulation test, the method is used to control the air pipe network of an aircraft engine air flight environment simulation test bench, see Figure 1 and Figure 2 As shown, the method comprises the following steps:

[0046] S101, constructing a compressed air flow path on-off characteristic matrix of the air pipe network according to the air environment simulation test subject;

[0047] S102, obtaining the predicted on-off status of all the compressed air flow paths at the next moment through the on-off characteristic matrix of the compressed air flow paths and the actual on-off status of all the compressed air flow paths at the previous moment;

[0048] S103, outputting the on-off control state of each compressed air flow path in the air pipe network at the next moment according to the on-off characteristic matrix of the compressed air flow path and the on-off prediction state.

[0049] In an optional embodiment of the above step S101, a compressed air flow path on-off characteristic matrix of the air pipe network is constructed according to the air environment simulation test subject, including:

[0050] S1011. Analyze the air environment simulation test subject according to the test process to obtain the test requirements of the aircraft engine at each moment, wherein the test requirements include the total intake temperature, the total intake pressure, the total exhaust temperature, the total exhaust pressure and the cabin static pressure.

[0051] S1012. According to the test requirements, the control information of each compressed air flow path in the air pipe network at each moment is obtained to obtain the on-off characteristic matrix of the compressed air flow path, wherein the control information includes on-off control instructions and adjustment device identifiers.

[0052] In specific implementation, by analyzing the air environment simulation test subjects, the test requirements of the aircraft engine at each moment in the test process can be obtained, and then it can be obtained at each moment which compressed air flow paths in the air pipeline network should be blocked and which compressed air flow paths should be connected, so as to obtain the on-off control instructions of the corresponding control devices on each compressed air flow path, and establish the compressed air flow path on-off feature matrix of the air pipeline network suitable for different test subjects.

[0053] In an optional embodiment, the air environment simulation test subjects include engine ground test, air environment calibration test, windward resistance test, windmill start test and plateau start test. Different test subjects have different experimental processes, and their test requirements are different at each moment. By analyzing different test subjects, corresponding information can be obtained.

[0054] In an optional embodiment of the above step S102, obtaining the predicted on-off state of all the compressed air flow paths at the next moment through the compressed air flow path on-off characteristic matrix and the actual on-off state of all the compressed air flow paths at the previous moment includes:

[0055] S1021, obtaining the actual on-off state of each compressed air flow path according to the actual on-off information of the regulating device of each compressed air flow path at the previous moment;

[0056] S1022, extracting each on-off control instruction of the compressed air flow path corresponding to the previous moment in the on-off characteristic matrix of the compressed air flow path;

[0057] S1023. Through the discrete-time state equation of the compressed air flow path, according to the actual on-off state of all the compressed air flow paths at the previous moment and the on-off control instructions, the on-off state of each of the compressed air flow paths at the next moment is estimated to obtain the on-off predicted state of all the compressed air flow paths.

[0058] Furthermore, in the above step S1023, the expression of the discrete time state equation of the compressed air flow path is:

[0059] , where A is the key boundary locking condition set, that is, the state set of the regulating device of the associated flow path required by each compressed air flow path state, representing the fixed relationship for determining the flow path state, is the actual on-off state of all compressed air flow paths in the air pipe network at time k, B is the conversion matrix that maps the on-off control instructions to the on-off state of the corresponding compressed air flow path in the on-off feature matrix of the compressed air flow path, is the input of the on-off control command of the regulating device of the compressed air flow path at time k, It is the set of predicted on / off states of all compressed air flow paths in the air network at time k+1.

[0060] In an improved embodiment of the air flow control method for the above-mentioned aircraft engine air environment simulation test, when executing the test process of the air environment simulation test subject, since each compressed air flow path has different pressure and temperature properties and uses, for example: the secondary flow path is mainly used to adjust the ambient temperature in the test chamber. If the flow path is throttled or blocked too little in a short time, it will not cause direct damage. However, if there is a mistake in blocking the atmospheric environment and the high pressure, high temperature, negative pressure, negative temperature and other flow paths, it will directly cause serious damage to the test object and equipment. Therefore, in order to avoid damage to the test object and equipment, it is necessary to obtain the associated flow paths of the compressed air flow path and control them. Specifically, the method of the present invention also includes:

[0061] S104. According to the test process of the aerial environment simulation test subject, the associated flow paths related to each of the compressed air flow paths are obtained, and a key boundary locking condition set of the air pipe network is established according to the associated flow paths.

[0062] In an optional embodiment of the above step S104, according to the test process of the air environment simulation test subject, an associated flow path related to each of the compressed air flow paths is obtained, and a key boundary locking condition set of the air pipe network is established according to the associated flow paths, including:

[0063] S1041. Analyze the air environment simulation test subject according to the test process to obtain the test requirements of the aircraft engine at each moment, wherein the test requirements include the total intake air temperature, the total intake air pressure, the total exhaust air temperature, the total exhaust air pressure and the cabin static pressure;

[0064] S1042, according to the test requirements, identifying the associated flow path of each compressed air flow path in the air pipe network at each moment;

[0065] S1043. According to the test requirements of the aircraft engine at each moment, establish locking conditions for the associated flow paths of each of the compressed air flow paths to obtain the key boundary locking condition set.

[0066] In an optional embodiment of the above step S103, outputting the on-off control state of each compressed air flow path in the air pipe network at the next moment according to the on-off characteristic matrix of the compressed air flow path and the on-off prediction state includes:

[0067] According to the formula , real-time control of each compressed air flow path in the air pipe network, where C is the on-off characteristic matrix of the compressed air flow path, It is the set of on-off control states of all compressed air flow paths in the air network at time k+1.

[0068] The method of the present invention provides a control method for the compressed air flow path of a large bypass ratio aircraft engine air flight environment simulation test bench, which can provide operational guidance and state judgment for the state control of different compressed air flow paths during the test. Compared with relying entirely on manual operation, the method greatly improves the reliability and safety of the intake and exhaust condition control platform of the large bypass ratio aircraft engine air flight environment simulation test bench in the test process operation, reduces the probability of low-level quality accidents caused by human factors, has significant engineering practical value in the field of test bench environment construction technology, and plays an important role in promoting the design and application of other subsequent large-scale test bench environment simulation platforms.

[0069] Furthermore, by locking the on / off of key associated flow paths, the disadvantages of the traditional method of human control that easily lead to misjudgment or operational errors or cause harm and safety hazards to the air flight environment simulation test can be eliminated, which greatly improves the safety of the test and is conducive to ensuring the smooth development of the large bypass ratio aircraft engine development test.

[0070] Based on the same inventive concept, an air flow control system for an aircraft engine aerial environment simulation test is also provided in an embodiment of the present invention, as described in the following embodiment. Since the principle of solving the problem by the air flow control system is similar to the air flow control method for the above-mentioned aircraft engine aerial environment simulation test, the implementation of the air flow control system can refer to the implementation of the above-mentioned air flow control method, and the repeated parts will not be repeated. As used below, the term "unit" or "module" can be a combination of software and / or hardware that implements a predetermined function. Although the device described in the following embodiments is preferably implemented in software, the implementation of hardware, or a combination of software and hardware, is also possible and conceivable.

[0071] Figure 3 : is a structural block diagram of an air flow control system for an aero-engine air environment simulation test disclosed in an embodiment of the present invention, such as Figure 3 As shown, the system includes a first construction module 301, a prediction model 302 and a control module 303, and the structure is described below.

[0072] The first construction module 301 is used to construct the compressed air flow path on-off characteristic matrix of the air pipe network according to the air environment simulation test subject;

[0073] The prediction model 302 is used to obtain the predicted on-off status of all the compressed air flow paths at the next moment through the compressed air flow path on-off characteristic matrix and the actual on-off status of all the compressed air flow paths at the previous moment;

[0074] The control module 303 is used to output the on-off control state of each compressed air flow path in the air pipe network at the next moment according to the on-off characteristic matrix of the compressed air flow path and the on-off prediction state.

[0075] In an alternative embodiment of the above system, see Figure 3 As shown, the system also includes a second construction module 304, which is used to obtain associated flow paths related to each of the compressed air flow paths according to the test process of the air environment simulation test subject, and establish a key boundary locking condition set of the air pipe network according to the associated flow paths.

[0076] In this embodiment, a computer device is provided, such as Figure 4 As shown, it includes a memory 401, a processor 402 and a computer program stored in the memory and executable on the processor, and when the processor executes the computer program, the air flow control method for any of the above-mentioned aircraft engine air environment simulation tests is implemented.

[0077] Specifically, the computer device may be a computer terminal, a server or a similar computing device.

[0078] In this embodiment, a computer-readable storage medium is provided, wherein the computer-readable storage medium stores a computer program for executing any of the above-mentioned air flow path control methods for the aircraft engine air environment simulation test.

[0079] Specifically, computer-readable storage media include permanent and non-permanent, removable and non-removable media that can be used to store information by any method or technology. Information can be computer-readable instructions, data structures, program modules or other data. Examples of computer-readable storage media include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technology, compact disk read-only memory (CD-ROM), digital versatile disk (DVD) or other optical storage, magnetic cassettes, tape disk storage or other magnetic storage devices or any other non-transmission media that can be used to store information that can be accessed by a computing device. As defined herein, computer-readable storage media does not include temporary computer-readable media (transitory media), such as modulated data signals and carrier waves.

[0080] Obviously, those skilled in the art should understand that the modules or steps of the above-mentioned embodiments of the present invention can be implemented by a general computing device, they can be concentrated on a single computing device, or distributed on a network composed of multiple computing devices, and optionally, they can be implemented by a program code executable by a computing device, so that they can be stored in a storage device and executed by the computing device, and in some cases, the steps shown or described can be executed in a different order from that here, or they can be made into individual integrated circuit modules, or multiple modules or steps therein can be made into a single integrated circuit module for implementation. In this way, the embodiments of the present invention are not limited to any specific combination of hardware and software.

[0081] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the embodiments of the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An air flow control method for an aircraft engine air environment simulation test, the method is used to control the air pipe network of an aircraft engine air flight environment simulation test bench, characterized in that: The method comprises: According to the air environment simulation test subjects, a compressed air flow path on-off characteristic matrix of the air pipe network is constructed; The on-off prediction state of all the compressed air flow paths at the next moment is obtained through the on-off characteristic matrix of the compressed air flow path and the actual on-off state of all the compressed air flow paths at the previous moment, including: obtaining the actual on-off state of each compressed air flow path according to the actual on-off information of the regulating device of each compressed air flow path at the previous moment; extracting the on-off control instruction of each compressed air flow path corresponding to the previous moment in the on-off characteristic matrix of the compressed air flow path; and estimating the on-off state of each compressed air flow path at the next moment according to the actual on-off state and the on-off control instruction of all the compressed air flow paths at the previous moment through the discrete time state equation of the compressed air flow path, so as to obtain the on-off prediction state of all the compressed air flow paths, wherein the expression of the discrete time state equation of the compressed air flow path is: , where A is the key boundary locking condition set, is the actual on-off state of all compressed air flow paths in the air pipe network at time k, B is the conversion matrix that maps the on-off control instructions to the on-off state of the corresponding compressed air flow path in the on-off feature matrix of the compressed air flow path, is the input of the on-off control command of the regulating device of the compressed air flow path at time k, is the set of predicted on / off states of all compressed air flow paths in the air pipe network at time k+1; According to the compressed air flow path on-off characteristic matrix and the on-off prediction state, the on-off control state of each compressed air flow path in the air pipe network at the next moment is output.

2. The air flow path control method for an aircraft engine air environment simulation test according to claim 1, characterized in that: According to the air environment simulation test subjects, a compressed air flow path on-off characteristic matrix of the air pipe network is constructed, including: Analyze the air environment simulation test subject according to the test process to obtain the test requirements of the aircraft engine at each moment, wherein the test requirements include the total intake temperature, the total intake pressure, the total exhaust temperature, the total exhaust pressure and the cabin static pressure; According to the test requirements, the control information of each compressed air flow path in the air pipe network at each moment is obtained to obtain the on-off characteristic matrix of the compressed air flow path, wherein the control information includes on-off control instructions and adjustment device identifiers.

3. The air flow path control method for an aircraft engine air environment simulation test according to claim 1, characterized in that: The air environment simulation test subjects include engine ground test, air environment calibration test, headwind resistance test, windmill start test and plateau start test.

4. The air flow path control method for an aircraft engine air environment simulation test according to claim 1, characterized in that: The method further comprises: According to the test process of the aerial environment simulation test subject, the associated flow paths related to each of the compressed air flow paths are obtained, and a key boundary locking condition set of the air pipe network is established according to the associated flow paths.

5. The air flow path control method for an aircraft engine air environment simulation test according to claim 4, characterized in that: According to the test process of the air environment simulation test subject, the associated flow path related to each of the compressed air flow paths is obtained, and the key boundary locking condition set of the air pipe network is established according to the associated flow paths, including: Analyze the air environment simulation test subject according to the test process to obtain the test requirements of the aircraft engine at each moment, wherein the test requirements include the total intake temperature, the total intake pressure, the total exhaust temperature, the total exhaust pressure and the cabin static pressure; According to the test requirements, identifying the associated flow path of each of the compressed air flow paths in the air pipe network at each moment; According to the test requirements of the aircraft engine at each moment, a locking condition is established for the associated flow path of each compressed air flow path to obtain the key boundary locking condition set.

6. The air flow path control method for an aircraft engine air environment simulation test according to claim 1, characterized in that: Outputting the on-off control state of each compressed air flow path in the air pipe network at the next moment according to the on-off characteristic matrix of the compressed air flow path and the on-off prediction state, including: According to the formula , real-time control of each compressed air flow path in the air pipe network, where C is the on-off characteristic matrix of the compressed air flow path, It is the set of on-off control states of all compressed air flow paths in the air network at time k+1.

7. An air flow control system for an aircraft engine air environment simulation test, characterized in that: The system comprises: A first construction module, the first construction module is used to construct a compressed air flow path on-off characteristic matrix of the air pipe network according to an air environment simulation test subject; A prediction model, the prediction model is used to obtain the predicted on-off state of all the compressed air flow paths at the next moment through the compressed air flow path on-off characteristic matrix and the actual on-off state of all the compressed air flow paths at the previous moment, including: obtaining the actual on-off state of each compressed air flow path according to the actual on-off information of the regulating device of each compressed air flow path at the previous moment; extracting the on-off control instruction of each compressed air flow path corresponding to the previous moment in the compressed air flow path on-off characteristic matrix; through the compressed air flow path discrete time state equation, according to the actual on-off state and the on-off control instruction of all the compressed air flow paths at the previous moment, the on-off state of each compressed air flow path at the next moment is estimated, and the on-off predicted state of all the compressed air flow paths is obtained, wherein the expression of the compressed air flow path discrete time state equation is: , where A is the key boundary locking condition set, is the actual on-off state of all compressed air flow paths in the air pipe network at time k, B is the conversion matrix that maps the on-off control instructions to the on-off state of the corresponding compressed air flow path in the on-off feature matrix of the compressed air flow path, is the input of the on-off control command of the regulating device of the compressed air flow path at time k, is the set of predicted on / off states of all compressed air flow paths in the air pipe network at time k+1; A control module is used to output the on-off control state of each compressed air flow path in the air pipe network at the next moment according to the on-off characteristic matrix of the compressed air flow path and the on-off prediction state.

8. The air flow control system for the aircraft engine air environment simulation test according to claim 7, characterized in that: The system further comprises: The second construction module is used to obtain the associated flow paths related to each of the compressed air flow paths according to the test process of the air environment simulation test subject, and establish a key boundary locking condition set of the air pipe network according to the associated flow paths.

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