CN115237051A - Temporary-impulse wind tunnel flow field control method based on behavior configuration - Google Patents
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Abstract
The invention provides a behavior configuration-based temporary-impulse wind tunnel flow field control method, which is characterized in that a wind tunnel test process is controlled in a mode of an upper computer and a lower PLC, and the upper computer provides an interactive interface; the lower PLC configures the wind tunnel test process into a preparation stage, a starting stage, an adjusting stage, a test stage and a shutdown stage, and establishes a plurality of working condition configuration modules for calling each stage of the test process; according to aerodynamic force test requirements, flow field control working condition configuration tables at different stages are determined, working condition configuration is completed in an interactive interface of an upper computer, and a lower PLC calls corresponding working condition configuration modules in the test process to combine and complete flow field control in the wind tunnel process. The invention has flexible working condition configuration, small workload of program development and maintenance, strong engineering adaptability and expandability, can meet various special requirements of aircraft simulation tests in the field of aerospace, can greatly save the program development cost, improve the reuse rate of the program and shorten the development period.
Description
Technical Field
The invention relates to the field of aerospace craft ground simulation tests, in particular to a temporary-impulse wind tunnel flow field control method based on behavior configuration.
Background
The wind tunnel is the indispensable ground simulation equipment of aeronautics and astronautics aircraft for carrying out aerodynamic experiments. In the wind tunnel test, according to the test requirements, force/pressure tests under different model postures, test curves under different mach number working conditions, speed change pressure tests for testing flight envelope lines and the like are often carried out, and especially the load constraints of a rigid model and an elastic model are required to be realized, and modes such as linear switching on and off, high-switching charging pressure, conventional switching off and the like are required to be realized in the process of switching on and off the vehicle in the wind tunnel. In order to meet the test requirements, flow field control programs with different functions and versions are often developed, such as variable-speed pressure, static aeroelastic, flow field control programs for wind tunnel tests of an embedded weapon bay, conventional constant total pressure, constant Mach number, variable attack angle, parachute opening and rudder opening and other versions of test programs. On one hand, the development cycle of the test program is long, the maintenance workload is large, and the expansion of the program function is limited; secondly, the determined program flow and version can limit the complex requirements of the wind tunnel test of the aircraft in a certain program, and the special requirements of the aerodynamic force test cannot be better met.
Disclosure of Invention
Aiming at the problems that the existing wind tunnel test flow field control program is multiple in version, single in program function, time-consuming and labor-consuming in the test process and limits the complex requirements of the aircraft wind tunnel test, a temporary impact type wind tunnel flow field control method based on behavior configuration is provided, and the wind tunnel aerodynamic tests with different functions, working conditions and processes are realized through the behavior configuration.
The technical scheme adopted by the invention is as follows: a temporary-impulse wind tunnel flow field control method based on behavior configuration controls a wind tunnel test process in a mode of an upper computer and a lower PLC, wherein the upper computer provides an interactive interface for working condition selection; the lower PLC configures the wind tunnel test process into a preparation stage, a starting stage, an adjusting stage, a test stage and a shutdown stage, and establishes a plurality of working condition configuration modules for calling each stage of the test process;
determining flow field control working condition configuration tables at different stages according to aerodynamic force test requirements, completing working condition configuration in an interactive interface of an upper computer, writing the working condition configuration tables into a lower PLC, calling corresponding working condition configuration modules by the lower PLC in the test process, and completing flow field control in the wind tunnel process in a combined mode.
Further, in the wind tunnel test process:
a preparation stage: initializing a system and operating each mechanism to a preset value;
a starting stage: pressurizing the wind tunnel, and enabling the total pressure to reach a stable value; in the process, the closed-loop control of the main guide pressure, the presetting of the standing current and the closed-loop control of the standing pressure are completed, and then the total pressure closed-loop control is realized;
and (3) adjusting: accurate Mach number adjustment is realized through a grid finger mechanism and standing current, and an accurate wind tunnel flow field is constructed;
and (3) a test stage: finishing an aircraft aerodynamic simulation test based on a preset test mode;
a vehicle shutdown stage: and (5) closing the vehicle in a wind tunnel.
Further, the operating condition configuration module comprises: high-opening charging pressure, linear charging pressure, dynamic standing regulation, dynamic standing flow, movable grid fingers, standing flow regulation Mach number, grid finger regulation Mach number, step variable Mach number, continuous variable Mach number, variable attack angle, variable speed pressure, linear shutdown and conventional shutdown.
Further, in the starting stage, the main guide pressure and the total pressure are controlled by selecting high opening charging pressure or linear charging pressure, and when the Mach number Ma is larger than or equal to 0.85, the dynamic stagnation and the dynamic standing flow are required to be called.
Furthermore, in the adjusting stage, when the Mach number Ma is less than or equal to 0.85, the combination of the moving gate finger and the standing current adjusting Mach number is called to finish the Mach number fine adjustment; when the Mach number Ma is less than 1.05 and 0.85 is less than Ma, calling the combination of the moving gate finger and the stationary stream modulation Mach number to finish Mach number fine adjustment, or calling the combination of the moving stationary stream and the gate finger modulation Mach number to finish Mach number fine adjustment; and when the Mach number Ma is larger than or equal to 1.05, calling the combination of the moving standing current and the standing current to adjust the Mach number to finish the fine adjustment of the Mach number.
Furthermore, in the test stage, the test is carried out by selecting and calling the step variable Mach number, the continuous variable Mach number, the variable attack angle and the variable speed pressure according to the working condition configuration.
Further, in the stage of shutting down, linear shutting down or conventional shutting down is selected and called to complete wind tunnel shutting down.
Furthermore, the working condition configuration module further comprises an umbrella opening and rudder opening module, a large attack angle module, a special test working condition module of DMC and third-party communication, and a corresponding configuration interface is provided in the upper computer.
Compared with the prior art, the beneficial effects of adopting the technical scheme are as follows: the vehicle-starting mode and the flow-field adjusting mode can be set arbitrarily under different working conditions, the program version is single, and the workload of program development and maintenance is reduced; the test working condition is simple, convenient and flexible by configuring a program by an upper computer; the lower PLC has good expansibility for wind tunnel control. Compared with the traditional method, the flow field control method based on behavior configuration has the advantages of clear structure, time and labor saving in development and maintenance, strong expansibility and engineering applicability and high efficiency. Therefore, the method has the characteristics of clear program architecture, low development and maintenance cost, strong engineering adaptability and the like, is particularly suitable for organizing the architecture design of the temporary-filling type wind tunnel flow field control program, and can also be applied to the development of other wind tunnel flow field control programs.
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Fig. 1 is a schematic diagram of a method for controlling a flow field of a transient impulse type wind tunnel based on a behavior configuration according to the present invention.
FIG. 2 is a flow chart of a preparation phase in an embodiment of the present invention.
FIG. 3 is a flowchart of a boot phase according to an embodiment of the invention.
FIG. 4 is a flow chart of an adjustment phase in an embodiment of the present invention.
FIG. 5 is a flowchart of an experimental phase according to an embodiment of the present invention.
FIG. 6 is a flowchart of the shutdown phase according to an embodiment of the present invention.
Detailed Description
Reference will now be made in detail to embodiments of the present application, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar modules or modules having the same or similar functionality throughout. The embodiments described below with reference to the accompanying drawings are illustrative and are only for the purpose of explaining the present application and are not to be construed as limiting the present application. On the contrary, the embodiments of the application include all changes, modifications and equivalents coming within the spirit and terms of the claims appended hereto.
Before describing the embodiments, a general term/abbreviation referred to throughout this disclosure and the accompanying drawings shall be described:
presetting a main tone: the main pressure regulating valve operates to a set opening degree;
the main adjustment is in place: the main pressure regulating valve operates to a set opening degree, and the deviation between the set opening degree and the feedback opening degree is less than 30mm;
main height adjustment and opening: the actual given displacement of the main pressure regulating valve is 1.05 to 1.2 times of the set displacement;
total pressure switching point: the total pressure reaches 0.9 to 0.98 times of the preset pressure;
a main leading closed loop: the main pressure regulating valve performs closed-loop regulation on the pressure of the main ejector;
leading the steel wire to the right position: the feedback pressure of the main ejector reaches 0.99 times of the set pressure;
the main row is in place: the main exhaust valve is operated to a set opening, and the deviation between the set opening and the feedback is less than or equal to 35mm;
linear variable speed pressure (linear charging pressure): in the starting and pressurizing process of the wind tunnel, in order to reduce the impact load of the test model, the total pressure slowly rises at a set speed;
high-opening pressurizing: in the process of starting and pressurizing the wind tunnel, the total pressure of the wind tunnel quickly reaches a set value in a high opening mode of a main pressure regulating valve;
total pressure closed loop: the main exhaust valve carries out closed-loop accurate regulation on the total pressure;
the total pressure is stable: the deviation between the total pressure setting and the feedback is less than or equal to 0.2 percent, and the total pressure is judged to be stable after 100 control periods are delayed;
standing flow is high: the actual given displacement of the resident chamber flow valve is 1.1 times of the set displacement;
standing flow in place: the resident chamber flow valve is operated to a set opening degree, and when the deviation between the setting and the feedback is less than 30mm and the time is delayed for 2.5s, the resident chamber flow valve is determined to be in place;
moving and standing and adjusting: the precondition of the operation of the room pressure regulating valve is that the room pressure regulating valve can be operated;
presetting standing and adjusting: the room pressure regulating valve is operated to a set opening degree;
standing and adjusting in place: the resident chamber pressure regulating valve operates to a set opening degree, and the deviation between the setting and the feedback is less than 15mm;
a parking guide closed loop: the resident chamber pressure regulating valve is used for carrying out closed-loop accurate regulation on the resident chamber injection pressure;
closed loop of gate finger mach number: the Mach number is accurately adjusted in a closed loop by a grid value mechanism;
closed loop of standing current Mach number: the Mach number is precisely adjusted in a closed loop mode by the flow valve of the resident chamber;
the Mach number is stable: after the Mach number enters an error range of 0.002 to 0.005, delaying for 120 control cycles, and then delaying for 0.2s to determine that the Mach number is stable;
dynamic attack angle: the attack angle mechanism runs to a set angle;
the angle of attack is in place: the attack angle mechanism operates to a set angle, and when the deviation between the set angle and the feedback is less than 0.3 degrees, the attack angle mechanism is determined to be in place after delaying for 1 s;
flow field stabilization: the total pressure is stable, the Mach number is stable, and the flow field is determined to be stable after the attack angle is in place.
Linearly turning off the vehicle: and after the test is finished, reducing the total pressure to the set total pressure for shutting down the vehicle through the set speed, and shutting down the vehicle through the wind tunnel.
As shown in fig. 1, the embodiment provides a transient wind tunnel flow field control method based on behavior configuration, which controls a wind tunnel test process by means of an upper computer and a lower PLC, wherein the upper computer provides an interactive interface for selecting a working condition; the lower PLC configures the wind tunnel test process into a preparation stage, a starting stage, an adjusting stage, a test stage and a shutdown stage, and establishes a plurality of working condition configuration modules for calling each stage of the test process;
determining flow field control working condition configuration tables at different stages according to aerodynamic force test requirements, completing working condition configuration in an interactive interface of an upper computer, writing the working condition configuration tables into a lower PLC, calling corresponding working condition configuration modules by the lower PLC in the test process, and completing flow field control in the wind tunnel process in a combined mode.
Specifically, each stage in the wind tunnel test process specifically includes:
a preparation stage: initializing a system and operating each mechanism to a preset value;
a starting stage: pressurizing the wind tunnel, and enabling the total pressure to reach a stable value; in the process, closed-loop control of main guide pressure, pre-setting of standing flow and closed-loop control of standing guide pressure are completed, and then total pressure closed-loop control is realized;
and (3) a regulating stage: accurate Mach number adjustment is realized through a grid finger mechanism and standing current, and an accurate wind tunnel flow field is constructed;
and (3) a test stage: finishing an aircraft aerodynamic simulation test based on a preset test mode;
a vehicle shutdown stage: and (5) shutting off the vehicle in the wind tunnel.
In this embodiment, the operating condition configuration module mainly includes: the method comprises the steps of high-opening charging, linear charging, dynamic standing adjustment, dynamic standing flow, movable grid fingers, standing flow adjusting Mach numbers, grid finger adjusting Mach numbers, step variable Mach numbers, continuous variable Mach numbers, variable attack angles, variable speed pressure, linear vehicle closing and conventional vehicle closing, and is called by a lower PLC according to requirements in test engineering.
In the actual test process, according to aerodynamic test requirements, working conditions and a flow field control mode, the type, the supporting mode, the flow field pressurizing mode, the adjusting mode, the test mode (variable speed pressure/attack angle/Mach number and the like), the shutdown mode and the special test working condition of the sensor are determined, working condition configuration tables of different flow field control stages are formed, the working condition configuration tables are arranged in an upper computer, and a lower PLC executes a specific wind tunnel test process.
Specifically, as shown in fig. 2, in the preparation stage, the test system is initialized, the preparation start stage is performed, whether the interlock is normal is determined, after the interlock is determined to be normal, the quick valve is opened, the gate finger is adjusted to the preset position, the attack angle is adjusted to the starting angle, the main adjustment/parking adjustment full-close and the main exhaust full-close are performed, and the start stage is performed after the configuration is completed.
As shown in FIG. 3, in the starting stage, the charging mode includes two working conditions of high opening charging and linear charging, which are suitable for controlling the main pilot pressure and the total pressure, and at high Mach number (Ma is greater than or equal to 0.85), two working conditions of dynamic parking and dynamic standing flow are also needed.
As shown in fig. 4, in the adjusting stage, the mach number adjusting mode includes a gate finger, a fixed standing-current gate finger, a fixed gate finger standing-current and a standing-current, and the mach number fine adjusting mode mainly includes two working conditions of a standing-current mach number and a gate finger mach number, and when the mach number Ma is less than or equal to 0.85, the moving gate finger and the standing-current mach number are combined to complete the mach number fine adjustment; when the Mach number Ma is less than 1.05 and 0.85 is less than Ma, calling the combination of the moving gate finger and the standing-stream modulation Mach number to finish the Mach number fine adjustment, or calling the combination of the moving standing-stream modulation Mach number and the gate finger modulation Mach number to finish the Mach number fine adjustment; and when the Mach number Ma is larger than or equal to 1.05, calling the combination of the moving standing current and the standing current to finish the Mach number fine adjustment.
As shown in fig. 5, in the test stage, the test modes mainly include a step-variable mach number, a continuous mach number, a step (continuous) variable attack angle, a variable speed pressure condition, and the like.
As shown in fig. 6, in the shutdown stage, the linear shutdown or the conventional shutdown is selected and invoked to complete the wind tunnel shutdown.
In this embodiment, the functional operation implemented at each stage may be to invoke the corresponding operating condition configuration module through the selected operating condition.
In addition, aiming at some special working conditions, the lower PLC is also correspondingly provided with a special test working condition module for realizing the tests of parachute opening and rudder opening, large attack angle, DMC and third-party communication, and meanwhile, the upper computer provides a corresponding configuration interface.
In this embodiment, the upper computer develops a human-computer interaction interface based on a C + + programming language, the working condition configuration interface includes a conventional configuration (a pressure sensor and a model support mode), a test flow working condition configuration (a pressurization mode, an adjustment mode, a test mode, a vehicle closing mode and the like), a special test working condition configuration (an umbrella opening and rudder opening mode, a large attack angle, DMC and third-party communication and the like), and working conditions in each stage of a wind tunnel test process can be conveniently and flexibly configured.
And the lower PLC realizes the main flow of the wind tunnel test based on a ladder diagram or a text language and provides a working condition configuration module for calling the test process. Wherein the main flow of the lower PLC has working condition selectivity.
For a certain type aerodynamic test as an example, a variable-speed pressure starting/shutting down mode and a step variable Mach number test mode are adopted, the Mach number Ma is less than or equal to 0.85, no special test working condition exists, and the wind tunnel flow field control process is specifically explained:
according to the test working condition and the aerodynamic force test requirement, working condition configuration is completed in the upper computer, the working condition configuration module calling condition in the test process is determined by the lower PLC, and the process is as follows: in the preparation stage, an initialization and preparation driving working condition configuration module is used, and whether the interlocking is normal or not is judged; in the starting stage, according to a linear pressurizing working condition configured by an upper computer, a lower PLC selects a main guide and total pressure adjusting mode as linear pressurizing, and calls a corresponding module until the main guide pressure and the total pressure are stable; in the adjusting stage, according to the working conditions of the movable grid fingers and the grid fingers which are configured by the upper computer and used for adjusting the Mach number, the lower PLC calls the corresponding modules to realize the closed-loop adjustment of the Mach number of the grid fingers, and when the attack angle is in place and the flow field is stable, the test stage is started; in the test stage, according to the step variable Mach number working condition configured by the upper computer, the lower PLC selects and calls the corresponding module to realize a step variable Mach number test mode; in the shutdown stage, according to the linear shutdown working condition configured by the upper computer, the lower PLC selects a linear shutdown mode, and the wind tunnel shuts down the vehicle after the total pressure reaches the shutdown total pressure and the attack angle is in a set range. Through the process, the flow field control of the current test can be completed through the behavior configuration.
For special requirements in the aerodynamic test process, such as umbrella opening and rudder opening, explosion camera shooting, emergency car closing systems and the like, special working condition configuration can be completed through an upper computer interactive interface, and corresponding modules are called in a lower PLC (programmable logic controller), so that flow field control under special working conditions can be realized through a behavior configuration mode.
The method has the advantages of simple thought, flexible working condition configuration, small workload of program development and maintenance, and strong engineering adaptability and expandability, meets various special requirements of aircraft simulation tests in the aerospace field, and can greatly save the program development cost, improve the reuse rate of the program and shorten the development period.
It should be noted that, in the description of the embodiments of the present invention, unless otherwise explicitly specified or limited, the terms "disposed" and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; may be directly connected or may be indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood as specific cases to those of ordinary skill in the art; the drawings in the embodiments are used for clearly and completely describing the technical scheme in the embodiments of the invention, and obviously, the described embodiments are a part of the embodiments of the invention, but not all of the embodiments. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Although embodiments of the present application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present application, and that variations, modifications, substitutions and alterations may be made to the above embodiments by those of ordinary skill in the art within the scope of the present application.
Claims (8)
1. A temporary-impulse wind tunnel flow field control method based on behavior configuration is characterized in that a wind tunnel test process is controlled in a mode of an upper computer and a lower PLC, and the upper computer provides an interactive interface for working condition selection; the lower PLC configures the wind tunnel test process into a preparation stage, a starting stage, an adjusting stage, a test stage and a shutdown stage, and establishes a plurality of working condition configuration modules for calling each stage of the test process;
determining flow field control working condition configuration tables at different stages according to aerodynamic force test requirements, completing working condition configuration in an interactive interface of an upper computer, writing the working condition configuration tables into a lower PLC (programmable logic controller), calling corresponding working condition configuration modules by the lower PLC in the test process, and combining to complete flow field control in the wind tunnel process.
2. The transient wind tunnel flow field control method based on behavior configuration according to claim 1, wherein the transient wind tunnel flow field control method is divided into the following steps in the wind tunnel test process:
a preparation stage: initializing a system and operating each mechanism to a preset value;
a starting stage: pressurizing the wind tunnel, and enabling the total pressure to reach a stable value; in the process, the closed-loop control of the main guide pressure, the presetting of the standing current and the closed-loop control of the standing pressure are completed, and then the total pressure closed-loop control is realized;
and (3) adjusting: accurate Mach number adjustment is realized through a grating finger mechanism and standing current, and an accurate wind tunnel flow field is constructed;
and (3) a test stage: completing an aircraft aerodynamic simulation test based on a preset test mode;
a shutdown stage: and (5) shutting off the vehicle in the wind tunnel.
3. The behavior configuration-based temporary-impulse wind tunnel flow field control method according to claim 1 or 2, wherein the operating condition configuration module comprises: high-opening charging pressure, linear charging pressure, dynamic standing regulation, dynamic standing flow, movable grid fingers, standing flow regulation Mach number, grid finger regulation Mach number, step variable Mach number, continuous variable Mach number, variable attack angle, variable speed pressure, linear shutdown and conventional shutdown.
4. The method according to claim 3, wherein during a startup phase, main pilot pressure and total pressure control is performed by selecting high on-state charging or linear charging, and when the Mach number Ma is greater than or equal to 0.85, a dynamic parking state and a dynamic standing current are required to be called.
5. The method for controlling the flow field of the temporary impulse type wind tunnel based on the behavioral configuration according to claim 4, wherein in the adjusting stage, when the Mach number Ma is less than or equal to 0.85, the Mach number fine adjustment is completed by calling the combination of the moving gate finger and the stationary flow modulation Mach number; when the Mach number Ma is less than 1.05 and 0.85 is less than Ma, calling the combination of the moving gate finger and the stationary stream modulation Mach number to finish Mach number fine adjustment, or calling the combination of the moving stationary stream and the gate finger modulation Mach number to finish Mach number fine adjustment; and when the Mach number Ma is larger than or equal to 1.05, calling the combination of the moving standing current and the standing current to finish the Mach number fine adjustment.
6. The method according to claim 5, wherein in the test stage, a stepwise Mach number, a continuous Mach number, a variable attack angle, and a variable speed pressure are selected and called according to working condition configuration for testing.
7. The transient-impulse-type wind tunnel flow field control method based on behavior configuration of claim 6, wherein in a shutdown phase, a linear shutdown or a conventional shutdown is selected and called to complete a wind tunnel shutdown.
8. The transient type wind tunnel flow field control method based on behavior configuration according to claim 1, wherein the operating condition configuration module further comprises a special test operating condition module for parachute opening and rudder opening, large attack angle, DMC and third party communication, and a corresponding configuration interface is provided in the upper computer.
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