CN109657356B - Control parameter calculation method and device - Google Patents
Control parameter calculation method and device Download PDFInfo
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Abstract
The application provides a control parameter calculation method and a control parameter calculation device, which are applied to computer equipment in a wind tunnel test model, wherein the method comprises the following steps: in a calibration mode, acquiring an open-loop transfer function of the wind tunnel test model; under a test mode, obtaining a closed loop transfer function of the wind tunnel test model; calculating a closed loop characteristic equation of the wind tunnel test model according to the closed loop transfer function; obtaining the pole position of the wind tunnel test model; and calculating to obtain a control parameter for controlling the piezoelectric stack element to generate and inhibit the vibration of the supporting rod according to the closed-loop characteristic equation, the open-loop transfer function and the pole position. The control parameter calculation method provided by the application is adopted to obtain the parameters required by the wind tunnel test model, the whole process basically does not need the participation of personnel with professional knowledge, and the method is suitable for various wind tunnel test models and has strong engineering practicability.
Description
Technical Field
The application relates to the field of experimental aerodynamics, in particular to a control parameter calculation method and device.
Background
In the prior art, a tail support mode is usually adopted in a high-speed wind tunnel force measurement test. The test model is connected with the bending knife mechanism through the strain balance and the supporting rod to form a cantilever structure. In order to reduce the support interference, the support rod is generally designed to be slender; meanwhile, in order to improve the sensitivity of the balance, the structural rigidity of the balance is designed to be smaller, so that the overall rigidity of the model supporting system is smaller. In the wind tunnel test process, when the model is excited by airflow, the phenomenon of violent model vibration is easy to occur. The problem of model vibration not only affects the precision of test data and test envelope, but also can cause the support rod to be broken, thereby endangering the safety of the model and the wind tunnel. Due to the high unsteady pneumatic excitation energy of the high-speed wind tunnel, the severely limited space available for installing a vibration reduction actuator and the like, the vibration reduction acting force of the common passive vibration reduction mode is difficult to generate obvious vibration reduction effect.
Currently, various vibration damping structures have been explored, including passive vibration damping structures based on tuned dampers, passive vibration damping structures based on viscoelastic materials, active vibration damping structures based on electromagnetic actuators, and active vibration damping structures based on piezoelectric stack elements, etc. Among them, the active vibration damping system based on the piezo-stack element is currently the most promising vibration suppression method due to the high energy density of the actuator. However, the existing wind tunnel model active vibration reduction method based on the piezoelectric stack element has many unsolved technical problems, so that the method is not put into a large amount of engineering for use. Among them, it is difficult to determine the control parameters for controlling the piezoelectric stack elements.
In view of the above, how to determine the control parameters of the piezoelectric stack element is a problem to be solved at present.
Disclosure of Invention
The application aims to provide a control parameter calculation method and device.
In a first aspect, the present application provides a control parameter calculation method, which is applied to a computer device in a wind tunnel test model, wherein the wind tunnel test model further includes a support rod, a test aircraft model to be tested, a piezoelectric stack element and a strain balance, one end of the support rod is connected with the strain balance, the piezoelectric stack element is arranged in the support rod, the strain balance is arranged in the test aircraft model to be tested, and the method includes:
in a calibration mode, acquiring an open-loop transfer function of the wind tunnel test model;
under a test mode, obtaining a closed loop transfer function of the wind tunnel test model;
calculating a closed loop characteristic equation of the wind tunnel test model according to the closed loop transfer function;
obtaining the pole position of the wind tunnel test model;
and calculating to obtain control parameters for controlling the piezoelectric stack element to generate and restrain the support rod vibration according to the closed-loop characteristic equation, the open-loop transfer function and the pole position.
Optionally, the step of obtaining an open-loop transfer function of the wind tunnel test model includes:
according to the acting force generated by the control piezoelectric stack element, acting on the airplane model to be tested, and acquiring a first dynamic signal of the strain balance in the airplane model to be tested to obtain an open-loop signal flow diagram of the wind tunnel test model;
and obtaining a corresponding open-loop transfer function according to the open-loop signal flow diagram.
Optionally, the step of obtaining a closed-loop transfer function of the wind tunnel test model includes:
acting on the airplane model to be tested according to the external excitation force, collecting a second dynamic signal of the strain balance in the airplane model to be tested, controlling the acting force generated by the piezoelectric stack element according to the second dynamic signal, and acting on the airplane model to be tested to obtain a closed-loop signal flow diagram of the wind tunnel test model;
and obtaining a corresponding closed loop transfer function according to the closed loop signal flow diagram.
Optionally, the obtaining a pole position of the wind tunnel test model includes:
calculating to obtain a control output energy function for controlling the piezoelectric stack element according to a closed-loop signal flow diagram of the wind tunnel test model;
calculating a minimum value of the control output energy function;
and obtaining the pole position of the wind tunnel test model according to the minimum value of the control output energy function.
Optionally, the calculating, according to the closed-loop characteristic equation, the open-loop transfer function, and the pole position, a control parameter for controlling the piezoelectric stack element to generate a control signal for suppressing the vibration of the supporting rod includes:
calculating to obtain an operation matrix according to the open-loop transfer function and the pole position;
and obtaining a control parameter for controlling the piezoelectric stack element to generate and restrain the vibration of the supporting rod according to the closed-loop characteristic equation and the operation matrix.
In a second aspect, the application provides a control parameter calculation device, is applied to the computer equipment in the wind tunnel test model, the wind tunnel test model still includes the bracing piece, the test aircraft model that awaits measuring, piezoelectric stack component and balance that meets an emergency, the one end and the balance that meets an emergency of bracing piece are connected, piezoelectric stack component sets up in the bracing piece, the balance that meets an emergency sets up in the test aircraft model that awaits measuring, the device includes:
the calibration module is used for acquiring an open-loop transfer function of the wind tunnel test model in a calibration mode;
the test module is used for obtaining a closed-loop transfer function of the wind tunnel test model in a test mode;
the acquisition module is used for acquiring the pole position of the wind tunnel test model;
the calculation module is used for calculating a closed loop characteristic equation of the wind tunnel test model according to the closed loop transfer function;
and the control parameter for controlling the piezoelectric stack element to generate and restrain the support rod vibration is calculated and obtained according to the closed-loop characteristic equation, the open-loop transfer function and the pole position.
Optionally, the calibration module is specifically configured to:
according to the acting force generated by the control piezoelectric stack element, acting on the airplane model to be tested, and acquiring a first dynamic signal of the strain balance in the airplane model to be tested to obtain an open-loop signal flow diagram of the wind tunnel test model;
and obtaining a corresponding open-loop transfer function according to the open-loop signal flow diagram.
Optionally, the test module is specifically configured to:
acting on a to-be-tested airplane model according to external excitation force, acquiring a second dynamic signal of the strain balance in the to-be-tested airplane model, controlling acting force generated by a piezoelectric stack element according to the second dynamic signal, and acting on the to-be-tested airplane model to obtain a closed-loop signal flow diagram of the wind tunnel test model;
and obtaining a corresponding closed loop transfer function according to the closed loop signal flow diagram.
Optionally, the obtaining module is specifically configured to:
calculating to obtain a control output energy function for controlling the piezoelectric stack element according to a closed-loop signal flow diagram of the wind tunnel test model;
calculating a minimum value of the control output energy function;
and obtaining the pole position of the wind tunnel test model according to the minimum value of the control output energy function.
Optionally, the calculation module is specifically configured to:
calculating to obtain an operation matrix according to the open-loop transfer function and the pole position;
and obtaining a control parameter for controlling the piezoelectric stack element to generate and restrain the vibration of the supporting rod according to the closed-loop characteristic equation and the operation matrix.
Compared with the prior art, the beneficial effects provided by the application comprise: the application provides a control parameter calculation method and device, is applied to the computer equipment in the wind-tunnel test model, the wind-tunnel test model still includes bracing piece, the test plane model that awaits measuring, piezoelectric stack component and balance that meets an emergency, the one end and the balance that meets an emergency of bracing piece are connected, piezoelectric stack component sets up in the bracing piece, the balance that meets an emergency sets up in the test plane model that awaits measuring, the method includes: in a calibration mode, acquiring an open-loop transfer function of the wind tunnel test model; under a test mode, obtaining a closed loop transfer function of the wind tunnel test model; calculating a closed loop characteristic equation of the wind tunnel test model according to the closed loop transfer function; obtaining the pole position of the wind tunnel test model; and calculating to obtain a control parameter for controlling the piezoelectric stack element to generate and inhibit the vibration of the supporting rod according to the closed-loop characteristic equation, the open-loop transfer function and the pole position. The control parameter calculation method provided by the application is adopted to obtain the parameters required by the wind tunnel test model, the whole process basically does not need the participation of personnel with professional knowledge, and the method is suitable for various wind tunnel test models and has strong engineering practicability.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly described below. It is appreciated that the following drawings depict only certain embodiments of the application and are therefore not to be considered limiting of its scope. It is obvious to a person skilled in the art that other relevant figures can also be derived from these figures without inventive effort.
FIG. 1 is a block diagram schematically illustrating a structure of a computer device according to an embodiment of the present disclosure;
FIG. 2 is a schematic block diagram illustrating a flow of steps of a control parameter calculation method according to an embodiment of the present disclosure;
FIG. 3 is a schematic block diagram illustrating a flow of sub-steps of step S201 in FIG. 2;
FIG. 4 is an open-loop signal flow diagram of a wind tunnel test model according to an embodiment of the present application;
FIG. 5 is a block diagram illustrating a flow of sub-steps of step S202 in FIG. 2;
FIG. 6 is a closed-loop signal flow diagram of a wind tunnel test model according to an embodiment of the present application;
FIG. 7 is a block diagram illustrating a flow of substeps of step S204 of FIG. 2;
fig. 8 is a closed-loop signal flow diagram of a wind tunnel test model controller provided in an embodiment of the present application at a station position;
FIG. 9 is a block diagram illustrating a flow of substeps of step S205 of FIG. 2;
fig. 10 is a block diagram schematically illustrating a structure of a control parameter calculation device according to an embodiment of the present application.
Icon: 100-a computer device; 110-control parameter calculation means; 111-a memory; 112-a processor; 113-a communication unit; 1101-a calibration module; 1102-a test module; 1103-obtaining module; 1104-a calculation module.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present application, presented in the accompanying drawings, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present application, it is to be understood that the terms "upper", "lower", "inner", "outer", "left", "right", and the like, refer to orientations or positional relationships that are based on the orientations or positional relationships shown in the drawings, or the orientations or positional relationships that the products of the application conventionally position when in use, or the orientations or positional relationships that are conventionally understood by those skilled in the art, and are used for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore, should not be construed as limiting the present application.
Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.
In the description of the present application, it is also to be noted that, unless otherwise explicitly stated or limited, the terms "disposed" and "connected" are to be interpreted broadly, for example, "connected" may be a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; the connection may be direct or indirect through an intermediate medium, and the connection may be internal to the two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
The following detailed description of embodiments of the present application will be made with reference to the accompanying drawings.
Referring to fig. 1, fig. 1 is a schematic block diagram of a computer device 100 according to an embodiment of the present disclosure. The computer apparatus 100 includes a control parameter calculation device 110, a memory 111, a processor 112, and a communication unit 113.
The memory 111, the processor 112 and the communication unit 113 are electrically connected to each other directly or indirectly to realize data transmission or interaction. For example, the components may be electrically connected to each other via one or more communication buses or signal lines. The three-dimensional resource management apparatus 110 includes at least one software function module which can be stored in the memory 111 in the form of software or firmware (firmware) or solidified in an Operating System (OS) of the computer device 100. The processor 112 is used for executing executable modules stored in the memory 111, such as software functional modules and computer programs included in the control parameter calculation device 110.
The Memory 111 may be, but is not limited to, a Random Access Memory (RAM), a Read Only Memory (ROM), a Programmable Read-Only Memory (PROM), an Erasable Read-Only Memory (EPROM), an electrically Erasable Read-Only Memory (EEPROM), and the like. The memory 111 is used to store programs or data. The communication unit 113 is configured to establish communication connection between the computer device 100 and other functional units in the wind tunnel test model.
Referring to fig. 2, fig. 2 is a schematic block diagram illustrating a flow of steps of a control parameter calculation method according to an embodiment of the present disclosure. The computer equipment 100 is applied to a wind tunnel test model, the wind tunnel test model further comprises a support rod, a test airplane model to be tested, a piezoelectric stack element and a strain balance, one end of the support rod is connected with the strain balance, the piezoelectric stack element is arranged in the support rod, the strain balance is arranged in the test airplane model to be tested, and the method comprises the following steps:
step S201, in a calibration mode, obtaining an open-loop transfer function of the wind tunnel test model.
Step S202, under the test mode, obtaining a closed loop transfer function of the wind tunnel test model.
And S203, calculating a closed loop characteristic equation of the wind tunnel test model according to the closed loop transfer function.
And step S204, obtaining the pole position of the wind tunnel test model.
And S205, calculating to obtain a control parameter for controlling the piezoelectric stack element to generate the vibration suppression support rod according to the closed-loop characteristic equation, the open-loop transfer function and the pole position.
Referring to fig. 3, fig. 3 is a schematic block diagram illustrating a flow of sub-steps of step S201 in fig. 2. In this embodiment, step S201 may include sub-steps S2011 and S2012:
step S2011, acting on the airplane model to be tested according to the acting force generated by the control piezoelectric stack element, and acquiring a first dynamic signal of the strain balance in the airplane model to be tested to obtain an open-loop signal flow diagram of the wind tunnel test model.
In this embodiment, the wind tunnel test model may further include a controller and a signal collector. Before the experiment begins, the wind tunnel test model may be calibrated, and the calibration process may be:
the control controller sends a control signal to the piezo-electric stack element.
And applying the acting force generated by the piezoelectric stacking element in response to the control signal to the airplane model to be tested.
And sending a first dynamic signal generated by the strain balance according to the power to a controller through the signal collector.
An open-loop signal flow diagram of the wind tunnel test model is obtained according to a signal flow direction between a controller, a piezoelectric stack element, a signal collector, a to-be-tested aircraft model and a strain balance arranged inside the to-be-tested aircraft model, please refer to fig. 4, and fig. 4 is the open-loop signal flow diagram of the wind tunnel test model provided in the embodiment of the present application.
And S2012, obtaining a corresponding open loop transfer function according to the open loop signal flow diagram. In this embodiment, according to the open-loop signal flow diagram of the wind tunnel test model shown in fig. 4, the obtained open-loop transfer function of the wind tunnel test model is:
x r (s)＝G A (s)CH(s)bg c (s)u r (s)
wherein u is r (s) is the control signal, C is the output matrix, H(s) is to beTest of the dynamics of the aircraft model, b being the control matrix, G A (s) transfer characteristic of controller front-end device, x r (s) is a skyward dynamic signal vector,
an open loop transfer function of the wind tunnel test model.
Referring to fig. 5, fig. 5 is a schematic block diagram illustrating a flow of sub-steps of step S202 in fig. 2. In this embodiment, step S202 may include sub-step S2021 and sub-step S2022:
step S2021, acting on the airplane model to be tested according to the external excitation force, collecting a second dynamic signal of the strain balance in the airplane model to be tested, controlling the acting force generated by the piezoelectric stack element according to the second dynamic signal, and acting on the airplane model to be tested to obtain a closed-loop signal flow diagram of the wind tunnel test model.
In this embodiment, the wind tunnel test model after calibration may enter a test mode, and the process of the test mode may be:
sending a second dynamic signal generated by the strain balance according to the exciting force of the test airflow to a controller through a signal collector;
controlling the controller to correspondingly output a control signal to the piezoelectric stack element according to the second dynamic signal;
and applying the acting force generated by the piezoelectric stack element according to the control signal to the airplane model to be tested so as to keep the strain balance at a preset position.
And obtaining a closed-loop signal flow diagram of the wind tunnel test model according to the signal flow direction among the controller, the piezoelectric stack element, the signal collector and the strain balance, and referring to fig. 6, fig. 6 is a closed-loop signal flow diagram of the wind tunnel test model provided by the embodiment of the application.
It should be noted that, in this embodiment, the control on the aircraft model to be tested may be control on longitudinal vibration of the model, and the dynamic signals generated by the strain balance according to the vibration are dynamic signals of Y element and Mz element (i.e. corresponding to the normal force and the pitching moment of the aircraft body shafting), it should be understood that the first dynamic signal and the second dynamic signal may represent dynamic signals generated by the strain balance in the calibration mode and the test mode, respectively, and the signal sources of the two signals may be the same. In other embodiments, the signal sources of the first dynamic signal and the second dynamic signal may be different.
And step S2022, obtaining a corresponding closed-loop transfer function according to the closed-loop signal flow diagram.
According to the closed-loop signal flow diagram of the wind tunnel test model shown in fig. 6, the closed-loop transfer function of the wind tunnel test model can be obtained through analysis.
In this embodiment, the generalized driving force of the piezoelectric stack can be expressed as follows according to a closed-loop signal flow diagram:
the kinetic equation for a closed loop system can be expressed as:
Ms 2 x(s)+Esx(s)+Kx(s)＝bu(s)+p(s)
the expression form of the generalized driving force u(s) of the piezoelectric stack can be substituted into the formula, and the closed-loop transfer function is obtained by sorting:
m is a mass matrix of the airplane model to be tested, E is a damping matrix of the airplane model to be tested, K is a rigidity matrix of the airplane model to be tested, u(s) is a piezoelectric stack generalized driving force, x(s) is a generalized state vector, p(s) is a generalized airflow exciting force, G A (s) is the transfer characteristic of the front-end equipment of the controller, C is an output matrix, cx(s) is an output expression of the wind tunnel test model system, and g C (s) is the transfer characteristic of the back-end equipment of the controller, g is the proportional link gain vector, f is the differential link gain vector, s is the Rayleigh variable,
and the closed loop transfer function of the wind tunnel test model.
It should be noted that, in this embodiment, the adopted control law structure may be a PD control structure, and the PD (proportional differential) control structure adopts a negative feedback form to control, and mainly uses the proportional and differential links of the strain balance dynamic signal to control, and the gain vector g of the proportional link and the gain vector f of the differential link may be control parameters in this embodiment.
In this embodiment, according to the closed-loop transfer function of the wind tunnel test model and the scherman-Morrison formula, another expression form of the closed-loop transfer function can be obtained:
it should be understood that in the process of obtaining the above expression form, the dynamics expression H(s) = (Ms) of the aircraft model to be tested is applied 2 +Es+K) -1 。
The closed-loop characteristic equation of the wind tunnel test model can be obtained according to the formula as follows:
1-g c (s)(sf+g) T G A (s)CH(s)b＝0
wherein g is c (s) is a scalar. According to the closed-loop characteristic equation and the open-loop transfer function obtained in the calibration mode, the closed-loop characteristic equation of the wind tunnel test model can be expressed as follows:
referring to fig. 7, fig. 7 is a schematic block diagram illustrating a flow of sub-steps of step S204 in fig. 2. In this embodiment, step S204 may include sub-step S2041, sub-step S2042, and sub-step S2043:
step S2041, calculating to obtain a control output energy function for controlling the piezoelectric stack element according to a closed-loop signal flow diagram of the wind tunnel test model.
In this embodiment, the controller end may be used as a station site, and the closed-loop signal flow diagram of fig. 6 may be simplified into the form of fig. 8. It can be assumed that the k-th order target control mode natural frequency of the closed loop system is ω k And the pneumatic excitation is also at a frequency omega k The whole system will vibrate in constant amplitude at the frequency. At this time, x in FIG. 8 A (s) can be expressed as:
the control output can be obtained from the closed-loop signal flow diagram at the controller station position provided in fig. 8 as:
in this embodiment, u c Represents the energy of the controller, and the control output energy function can be obtained according to the formula:
P k ＝(ω k f T Φ k ) 2 +(g T Φ k ) 2
wherein u is c To output a signal, omega k Is the natural frequency, q A For a generalized amplitude, phi k Is the k-th generalized mode shape.
In this embodiment, the closed loop signal flow diagram of fig. 6 can be simplified to the form of fig. 8 in the controller station state, where T(s) is the system transfer characteristic when the controller is a breakpoint.
Step S2042, a minimum value of the control output energy function is calculated.
In this embodiment, the minimum value of the calculated control output energy function may be a minimum value in which the pole position is a variable.
And step S2043, obtaining the pole position of the wind tunnel test model according to the minimum value of the control output energy function.
On the bookIn an embodiment, the pole positions of the wind tunnel test model can calculate a series of P according to a series of frequencies and a closed-loop target modal damping ratio specified by a user k Picking out P k The frequency at the minimum value is taken as the natural frequency ω of the corresponding target mode k Then according to the natural frequency omega k And calculating the position mu of the extreme point according to the specified modal damping ratio k 。
It should be understood that the above calculation of P as a function of frequency and modal damping ratio is described k The process of (3) needs to calculate the proportional-element gain vector g and the differential-element gain vector f, so the process can be iterated with step S205.
Referring to fig. 9, fig. 9 is a schematic block diagram illustrating a flow of sub-steps of step S205 in fig. 2. In this embodiment, step S205 may include sub-step S2051 and sub-step S2052:
step S2051, an operation matrix is calculated according to the open-loop transfer function and the pole position.
In this embodiment, the operation matrix can be calculated according to the open-loop transfer function and the pole position:
wherein, mu k For the pole positions, k =1,2, … 2n, n is the target number of modes that the user wants to control.
And S2052, obtaining a control parameter for controlling the piezoelectric stack element to generate and inhibit the vibration of the supporting rod according to the closed-loop characteristic equation and the operation matrix.
In this embodiment, a control parameter for controlling the piezoelectric stack element to generate the damping vibration of the supporting rod may be obtained according to the closed-loop characteristic equation and the operation matrix, and the calculation formula may be:
the matrix G is an operation matrix, and the proportional link gain vector G and the differential link gain vector f are control parameters.
Referring to fig. 10, fig. 10 is a schematic block diagram of a control parameter calculation device 110 according to an embodiment of the present disclosure. The embodiment of the present application still provides a control parameter calculation device 110, is applied to computer equipment 100 in the wind-tunnel test model, the wind-tunnel test model still includes bracing piece, the test aircraft model that awaits measuring, piezoelectric stack component and strain balance, the one end and the strain balance of bracing piece are connected, piezoelectric stack component sets up in the bracing piece, strain balance sets up in the test aircraft model that awaits measuring, the device includes:
a calibration module 1101, configured to obtain an open-loop transfer function of the wind tunnel test model in a calibration mode;
a test module 1102, configured to obtain a closed-loop transfer function of the wind tunnel test model in a test mode;
an obtaining module 1103, configured to obtain a pole position of the wind tunnel test model;
a calculating module 1104, configured to calculate a closed-loop characteristic equation of the wind tunnel test model according to the closed-loop transfer function;
and the control parameter for controlling the piezoelectric stack element to generate and restrain the support rod vibration is calculated and obtained according to the closed-loop characteristic equation, the open-loop transfer function and the pole position.
Further, the calibration module 1101 is specifically configured to:
according to the acting force generated by the control piezoelectric stack element, acting on the airplane model to be tested, and acquiring a first dynamic signal of the strain balance in the airplane model to be tested to obtain an open-loop signal flow diagram of the wind tunnel test model;
and obtaining a corresponding open-loop transfer function according to the open-loop signal flow diagram.
Further, the test module 1102 is specifically configured to:
acting on a to-be-tested airplane model according to external excitation force, acquiring a second dynamic signal of the strain balance in the to-be-tested airplane model, controlling acting force generated by a piezoelectric stack element according to the second dynamic signal, and acting on the to-be-tested airplane model to obtain a closed-loop signal flow diagram of the wind tunnel test model;
and obtaining a corresponding closed loop transfer function according to the closed loop signal flow diagram.
Further, the obtaining module 1103 is specifically configured to:
calculating to obtain a control output energy function for controlling the piezoelectric stack element according to a closed-loop signal flow diagram of the wind tunnel test model;
calculating a minimum value of the control output energy function;
and obtaining the pole position of the wind tunnel test model according to the minimum value of the control output energy function.
Further, the calculating module 1104 is specifically configured to:
calculating to obtain an operation matrix according to the open-loop transfer function and the pole position;
and obtaining a control parameter for controlling the piezoelectric stack element to generate and restrain the vibration of the supporting rod according to the closed-loop characteristic equation and the operation matrix.
To sum up, the application provides a control parameter calculation method and device, is applied to the computer equipment in the wind-tunnel test model, the wind-tunnel test model still includes bracing piece, the test aircraft model that awaits measuring, piezoelectric stack component and balance that meets an emergency, the one end and the balance that meets an emergency of bracing piece are connected, piezoelectric stack component sets up in the bracing piece, the balance that meets an emergency sets up in the test aircraft model that awaits measuring, the method includes: in a calibration mode, acquiring an open-loop transfer function of the wind tunnel test model; under a test mode, obtaining a closed loop transfer function of the wind tunnel test model; calculating a closed loop characteristic equation of the wind tunnel test model according to the closed loop transfer function; obtaining the pole position of the wind tunnel test model; and calculating to obtain a control parameter for controlling the piezoelectric stack element to generate and inhibit the vibration of the supporting rod according to the closed-loop characteristic equation, the open-loop transfer function and the pole position. The control parameter calculation method provided by the application is adopted to obtain the parameters required by the wind tunnel test model, the whole process basically does not need the participation of personnel with professional knowledge, and the method is suitable for various wind tunnel test models and has strong engineering practicability.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (4)
1. A control parameter calculation method is characterized by being applied to computer equipment in a wind tunnel test model, wherein the wind tunnel test model further comprises a support rod, a test airplane model to be tested, a piezoelectric stack element and a strain balance, one end of the support rod is connected with the strain balance, the piezoelectric stack element is arranged in the support rod, the strain balance is arranged in the test airplane model to be tested, and the method comprises the following steps:
in a calibration mode, acquiring an open-loop transfer function of the wind tunnel test model;
in a test mode, acting on a to-be-tested airplane model according to external excitation force, acquiring a second dynamic signal of the strain balance in the to-be-tested airplane model, controlling acting force generated by a piezoelectric stack element according to the second dynamic signal, and acting on the to-be-tested airplane model to obtain a closed-loop signal flow diagram of the wind tunnel test model;
obtaining a corresponding closed loop transfer function according to the closed loop signal flow diagram;
calculating a closed loop characteristic equation of the wind tunnel test model according to the closed loop transfer function;
calculating to obtain a control output energy function for controlling the piezoelectric stack element according to a closed-loop signal flow diagram of the wind tunnel test model;
calculating a minimum value of the control output energy function;
obtaining the pole position of the wind tunnel test model according to the minimum value of the control output energy function;
calculating to obtain an operation matrix according to the open-loop transfer function and the pole position;
and obtaining a control parameter for controlling the piezoelectric stack element to generate and restrain the vibration of the supporting rod according to the closed-loop characteristic equation and the operation matrix.
2. The method of claim 1, wherein said step of obtaining an open-loop transfer function of said wind tunnel test model comprises:
according to the acting force generated by the control piezoelectric stack element, acting on the airplane model to be tested, and acquiring a first dynamic signal of the strain balance in the airplane model to be tested to obtain an open-loop signal flow diagram of the wind tunnel test model;
and obtaining a corresponding open-loop transfer function according to the open-loop signal flow diagram.
3. The utility model provides a control parameter calculation device which characterized in that is applied to the computer equipment in the wind-tunnel test model, the wind-tunnel test model still includes bracing piece, the test plane model that awaits measuring, piezoelectric stack component and strainable balance, the one end and the strainable balance of bracing piece are connected, piezoelectric stack component sets up in the bracing piece, strainable balance sets up in the test plane model that awaits measuring, the device includes:
the calibration module is used for acquiring an open-loop transfer function of the wind tunnel test model in a calibration mode;
the test module is used for acting on the airplane model to be tested according to the external excitation force in the test mode, acquiring a second dynamic signal of the strain balance in the airplane model to be tested, controlling the acting force generated by the piezoelectric stack element according to the second dynamic signal, and acting on the airplane model to be tested to obtain a closed-loop signal flow diagram of the wind tunnel test model; obtaining a corresponding closed loop transfer function according to the closed loop signal flow diagram;
the acquisition module is used for calculating to obtain a control output energy function for controlling the piezoelectric stack element according to a closed-loop signal flow diagram of the wind tunnel test model; calculating a minimum value of the control output energy function; obtaining the pole position of the wind tunnel test model according to the minimum value of the control output energy function;
the calculation module is used for calculating a closed loop characteristic equation of the wind tunnel test model according to the closed loop transfer function;
the system is also used for calculating to obtain an operation matrix according to the open-loop transfer function and the pole position; and obtaining a control parameter for controlling the piezoelectric stack element to generate and restrain the vibration of the supporting rod according to the closed-loop characteristic equation and the operation matrix.
4. The apparatus of claim 3, wherein the calibration module is specifically configured to:
according to the acting force generated by the control piezoelectric stack element, acting on the airplane model to be tested, and acquiring a first dynamic signal of the strain balance in the airplane model to be tested to obtain an open-loop signal flow diagram of the wind tunnel test model;
and obtaining a corresponding open-loop transfer function according to the open-loop signal flow diagram.
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| CN113295359B (en) * | 2021-07-28 | 2022-02-22 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Simulation test device for inhibiting ejector supporting plate vibration and vibration inhibition method |
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