CN117782503A - Method for actively simulating wind tunnel test of ship-based aircraft landing process ship tail flow field - Google Patents
Method for actively simulating wind tunnel test of ship-based aircraft landing process ship tail flow field Download PDFInfo
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Abstract
The invention discloses a ship-based aircraft landing process ship-based flow field active simulation wind tunnel test method, belongs to the technical field of wind tunnel tests, overcomes the defect of passive simulation capability of the existing ship-based flow field, solves the problem that landing speed and aircraft carrier navigation speed cannot be unified in the process of developing ship-based aircraft landing characteristic research, generates speed turbulence at the downstream of a test section and carries out speed measurement by means of a flow field calibration system by installing a ship-based flow field active simulation device at the inlet of the test section, acquires a time domain speed model by utilizing a ship-based flow field mathematical modeling method, calculates a panel swing gain control coefficient by calibrating a disturbance speed field, and finally obtains panel motion swing angle data corresponding to a target ship-based flow field.
Description
Technical Field
The invention belongs to the technical field of wind tunnel tests, and relates to a method for actively simulating a wind tunnel test by a ship-based aircraft landing process ship tail flow field.
Background
In order to land on the aircraft carrier deck, the aircraft carrier needs to pass through the aircraft carrier flight deck Fang Kongyu in the process of advancing and landing, and finally land on the inclined deck landing area, wherein the ship tail gas flow field is one of the main interference factors causing landing errors in the process, so that the simulation of the ship tail gas flow field becomes an extremely important content in the research of the ship carrier advancing and landing technology of the aircraft carrier, the current research means mainly comprise two types of numerical simulation and wind tunnel test simulation, and compared with the numerical simulation, the wind tunnel test has higher precision, and the simulation method becomes an important means for developing the research of the ship tail gas flow field in the process of landing of the aircraft carrier at present.
At present, a passive simulation method is mostly adopted in a ship-tail flow field simulation wind tunnel test, namely, a wind tunnel test section is provided with a carrier scaling model, so that airflow flows through the carrier model to generate a similar ship-tail flow field at the rear part of the carrier scaling model, and the carrier scaling model used in the passive simulation is sometimes oversized due to the limited wind tunnel size, so that the simulation precision of the wake field is greatly reduced and is difficult to adjust, and meanwhile, when the research on the landing characteristics of the fixed-wing carrier aircraft is carried out, the method can bring the problem that the landing speed and the carrier navigation speed cannot be simulated simultaneously.
Disclosure of Invention
In order to solve the problems, the invention provides a method for actively simulating a wind tunnel test of a ship-borne aircraft landing process by using a ship-borne flow field, which overcomes the defect of the passive simulation capability of the existing ship-borne flow field, solves the problem that the landing speed and the aircraft carrier navigation speed cannot be unified in the research of the ship-borne aircraft landing characteristics, and widens the application of the wind tunnel test in the evaluation of the ship landing aerodynamic characteristics of the ship-borne aircraft.
The technical scheme adopted for solving the technical problems is as follows: a method for actively simulating wind tunnel test of a ship-based aircraft landing process ship-based wake field comprises the following steps:
step one, installing a flow field calibration system and correcting the installation angle of the hot wire probe: arranging a flow field calibration system in a test area at the downstream of a wind tunnel test section, wherein the flow field calibration system comprises a two-dimensional hot wire probe sensor, a Data acquisition system and a moving measurement frame, the moving measurement frame can move in three degrees of freedom, the two-dimensional hot wire probe sensor is arranged on the moving measurement frame and is connected with the Data acquisition system through a Data wire, the direction of the two-dimensional hot wire probe sensor is adjusted to meet the requirements of measuring incoming flow wind speed and vertical wind speed, a wind tunnel is started to a target wind speed and is stabilized for a plurality of seconds, the Data acquisition system is triggered to acquire incoming flow wind speed Data1 and vertical speed Data2 of the wind tunnel test section, and the vertical installation angle of the two-dimensional hot wire probe sensor is obtained through calculation of the measurement DataThe calculation formula is as follows:
（1）
step two: installing a ship tail flow field active simulation device: the method comprises the steps that a ship tail flow field active simulation device is installed at an inlet of a wind tunnel test section, the ship tail flow field active simulation device comprises two blades, a driving motor and a supporting frame, the two blades are rotationally connected to the supporting frame, the two blades are parallel to each other and connected through a blade connecting rod, the driving motor drives the blade connecting rod to move so as to drive the two blades to swing synchronously, the initial positions of the two blades are defined as parallel positions with a wind tunnel horizontal plane, and the positions are set as flat zero positions;
step three: mathematical modeling of the ship tail flow field: the simulated ship tail flow field is a vertical velocity field, the velocity field comprises a steady-state velocity component caused by the ship body shape and a periodic disturbance velocity component caused by the ship body motion, and the steady-state vertical velocity component is subjected to piecewise linearization processing to obtain the mathematical model of the component, which isVortex formed by movement of aircraft carrier bodyWill decay at 85% speed with distance from the stern, thus obtaining a periodic vertical velocity component mathematical model asThe mathematical expressions are as follows:
（2）
（3）
wherein:
（4）
wherein:is a steady-state vertical velocity component, positive downward in ft/s;the unit is ft/s for deck wind speed;the unit is ft, which is the horizontal distance of the carrier-based aircraft from the pitching center point of the ship;is pitch frequency of the aircraft carrier;is the pitching amplitude of the aircraft carrier;is a random phase;the horizontal flight speed of the carrier-based aircraft;
the space-time conversion relation of the ship tail speed field is as follows，The speed of the carrier-based aircraft approaching the speed of the tail deck,for time, i.e. capable of dividing the velocity field、Respectively converted intoAndthe expressions are as follows:
（5）
（6）
wherein:
（7）
step four: and (3) calibrating and measuring a ship tail flow field and calculating a blade swing control gain coefficient of the active simulation device: according to the third step, the mathematical model of the ship tail flow field which needs to be simulated in the wind tunnel can be obtained asModeling the mathematicsGenerating initial blade swing angle sequence by leading into control program of active simulation device of ship tail flow fieldStarting a wind tunnel to a specified wind speed, starting a ship tail flow field active simulation device after the wind speed is stabilized for a few seconds, enabling a blade to swing up and down according to a generated swing angle sequence, triggering a Data acquisition system to acquire incoming flow wind speed Data4 and vertical speed Data3 of a test area, and obtaining a blade swing control gain coefficient K of the ship tail flow field active simulation device, wherein the calculation formula is as follows:
（8）
（9）
（10）
step five: the ship tail flow field simulation, the flow field calibration system is dismantled, and the modeling method in the third step is used for obtaining a ship tail flow field mathematical modelSubstituting the blade swing control gain coefficient K in the fourth step to obtain the swing angle of the plate movementLeading the wind tunnel into a ship wake field active simulation device, starting the wind tunnel to a specified wind speed and stabilizing for a plurality of seconds, starting the ship wake field active simulation device to control the blades to swing according to a target curve, and generating a target aircraft carrier wake flow speed field at the downstream of a wind tunnel test section at the moment, thereby realizing wind tunnel test simulation of the aircraft carrier wake flow speed, wherein the expression of the movement swing angle of the blades is as follows:
（11）。
further, when the swing amplitude angle of the blade is 20 degrees, the swing frequency is not lower than 3Hz.
The invention has the following advantages and beneficial effects: the test method can simulate the aircraft carrier wake field in the wind tunnel environment, has the advantages of strong aircraft carrier wake flow speed field strength simulation capability, wide integral scale adjustment range and good simulation repeatability, has strong engineering practicability, and can provide a reliable test means for evaluating the carrier landing aerodynamic characteristics of the carrier-borne aircraft.
Drawings
FIG. 1 is a schematic diagram of a flow chart of a ship-to-ship wake field active simulation wind tunnel test;
fig. 2 is a view of a wake field active simulation device.
The wind tunnel, the supporting frame, the driving motor, the blade connecting rod, the blade and the blade are arranged in the same sequence, wherein the wind tunnel, the supporting frame, the driving motor, the blade connecting rod and the blade are arranged in the same sequence, and the wind tunnel, the supporting frame, the driving motor, the blade connecting rod and the blade are arranged in the same sequence.
Detailed Description
As shown in fig. 1, firstly, arranging a flow field calibration system in a test area at the downstream of a wind tunnel test section, blowing air, measuring speed data of the test area in an initial state, and calculating to obtain a vertical installation angle of a hot wire probe; then the active simulation device of the ship tail flow field is arranged at the inlet of the wind tunnel test section and a flat initial zero position is set; then, carrying out mathematical modeling on the ship tail flow field to obtain a mathematical expression of a steady-state speed component caused by the ship body appearance and a periodic disturbance speed component caused by the ship body movement; then, calibrating and measuring a ship tail flow field and calculating a blade swing control gain parameter of the active simulation device; and finally, removing the flow field calibration system, controlling the panel to swing according to the motion curve of the aircraft carrier tail flow field, and performing a target aircraft carrier tail flow field simulation test. The method specifically comprises the following steps:
step one, installing a flow field calibration system and correcting the installation angle of the hot wire probe: arranging a flow field calibration system in a test area at the downstream of a wind tunnel test section, wherein the flow field calibration system comprises a two-dimensional hot wire probe sensor, a data acquisition system and a moving and measuring frame, the moving and measuring frame can move in three degrees of freedom, the moving and measuring frame is provided with the two-dimensional hot wire probe sensor and is connected with the data acquisition system through a data wire, the direction of the two-dimensional hot wire probe sensor is adjusted to meet the requirements of measuring incoming flow wind speed and vertical wind speed, a wind tunnel is started to a target wind speed and is stabilized for a plurality of seconds, and the number of triggers is calculatedCollecting according to a collecting system to obtain incoming flow wind speed Data1 and vertical speed Data2 of a wind tunnel test area, and calculating to obtain the vertical installation angle of the two-dimensional hot wire probe sensor through measurement DataThe calculation formula is as follows:
（1）
step two: installing a ship tail flow field active simulation device: as shown in fig. 2, the active simulation device of the ship-to-ship flow field is installed at the inlet of the wind tunnel test section, the active simulation device of the ship-to-ship flow field comprises two blades 5, a driving motor 3 and a supporting frame 2, the two blades 5 are rotationally connected to the supporting frame 2, the two blades 5 are parallel to each other, the two blades 5 are connected through a blade connecting rod 4, the driving motor 3 drives the blade connecting rod 4 to move so as to drive the two blades 5 to synchronously swing, the initial position of the two blades 5 is defined as a position parallel to the horizontal plane of the wind tunnel 1, and the position is set as a flat zero position; when the swing amplitude angle of the blade 5 is 20 degrees, the swing frequency is not lower than 3Hz;
step three: mathematical modeling of the ship tail flow field: the simulated ship tail flow field is a vertical velocity field, the velocity field comprises a steady-state velocity component caused by the ship body shape and a periodic disturbance velocity component caused by the ship body motion, and the steady-state vertical velocity component is subjected to piecewise linearization processing to obtain the mathematical model of the component, which isVortex formed by movement of aircraft carrier body decays at 85% speed along with distance from the tail of the aircraft carrier, so that a periodic vertical velocity component mathematical model is obtainedThe mathematical expressions are as follows:
（2）
（3）
wherein:
（4）
wherein:is a steady-state vertical velocity component, positive downward in ft/s;the unit is ft/s for deck wind speed;the unit is ft, which is the horizontal distance of the carrier-based aircraft from the pitching center point of the ship;is pitch frequency of the aircraft carrier;is the pitching amplitude of the aircraft carrier;is a random phase;the horizontal flight speed of the carrier-based aircraft;
the space-time conversion relation of the ship tail speed field is as follows，The speed of the carrier-based aircraft approaching the speed of the tail deck,for time, i.e. capable of dividing the velocity field、Respectively converted intoAndthe expressions are as follows:
（5）
（6）
wherein:
（7）
step four: and (3) calibrating and measuring a ship tail flow field and calculating a blade swing control gain coefficient of the active simulation device: according to the third step, the mathematical model of the ship tail flow field which needs to be simulated in the wind tunnel can be obtained asModeling the mathematicsGenerating initial blade swing angle sequence by leading into control program of active simulation device of ship tail flow fieldStarting a wind tunnel to a specified wind speed, starting a ship tail flow field active simulation device after the wind speed is stabilized for a few seconds, enabling a blade to swing up and down according to a generated swing angle sequence, triggering a Data acquisition system to acquire incoming flow wind speed Data4 and vertical speed Data3 of a test area, and obtaining a blade swing control gain coefficient K of the ship tail flow field active simulation device, wherein the calculation formula is as follows:
（8）
（9）
（10）
step five: the ship tail flow field simulation, the flow field calibration system is dismantled, and the modeling method in the third step is used for obtaining a ship tail flow field mathematical modelSubstituting the blade swing control gain coefficient K in the fourth step to obtain the swing angle of the plate movementLeading the wind tunnel into a ship wake field active simulation device, starting the wind tunnel to a specified wind speed and stabilizing for a plurality of seconds, starting the ship wake field active simulation device to control the blades to swing according to a target curve, and generating a target aircraft carrier wake flow speed field at the downstream of a wind tunnel test section at the moment, thereby realizing wind tunnel test simulation of the aircraft carrier wake flow speed, wherein the expression of the movement swing angle of the blades is as follows:
（11）。
the invention can widen the application of the wind tunnel test in evaluating the pneumatic characteristics of carrier landing of the carrier-based aircraft, and provides technical support for wind tunnel simulation test for developing novel carrier landing related technologies.
Claims (2)
1. The method for actively simulating the wind tunnel test of the ship-based aircraft landing process by the ship-based wake field is characterized by comprising the following steps of:
step one, installing a flow field calibration system and correcting the installation angle of the hot wire probe:arranging a flow field calibration system in a test area at the downstream of a wind tunnel test section, wherein the flow field calibration system comprises a two-dimensional hot wire probe sensor, a Data acquisition system and a moving measurement frame, the moving measurement frame can move in three degrees of freedom, the two-dimensional hot wire probe sensor is arranged on the moving measurement frame and is connected with the Data acquisition system through a Data wire, the direction of the two-dimensional hot wire probe sensor is adjusted to meet the requirements of measuring incoming flow wind speed and vertical wind speed, a wind tunnel is started to a target wind speed and is stabilized for a plurality of seconds, the Data acquisition system is triggered to acquire incoming flow wind speed Data1 and vertical speed Data2 of the wind tunnel test section, and the vertical installation angle of the two-dimensional hot wire probe sensor is obtained through calculation of the measurement DataThe calculation formula is as follows:
（1）
step two: installing a ship tail flow field active simulation device: the method comprises the steps that a ship tail flow field active simulation device is installed at an inlet of a wind tunnel test section, the ship tail flow field active simulation device comprises two blades, a driving motor and a supporting frame, the two blades are rotationally connected to the supporting frame, the two blades are parallel to each other and connected through a blade connecting rod, the driving motor drives the blade connecting rod to move so as to drive the two blades to swing synchronously, the initial positions of the two blades are defined as parallel positions with a wind tunnel horizontal plane, and the positions are set as flat zero positions;
step three: mathematical modeling of the ship tail flow field: the simulated ship tail flow field is a vertical velocity field, the velocity field comprises a steady-state velocity component caused by the ship body shape and a periodic disturbance velocity component caused by the ship body motion, and the steady-state vertical velocity component is subjected to piecewise linearization processing to obtain the mathematical model of the component, which isVortex formed by movement of the aircraft carrier body can attenuate at 85% speed along with the distance from the tail of the aircraft carrier, so that periodic sagging is obtainedThe mathematical model of the straight velocity component is +.>The mathematical expressions are as follows:
（2）
（3）
wherein:
（4）
wherein:is a steady-state vertical velocity component, positive downward in ft/s; />The unit is ft/s for deck wind speed; />The unit is ft, which is the horizontal distance of the carrier-based aircraft from the pitching center point of the ship; />Is pitch frequency of the aircraft carrier; />Is the pitching amplitude of the aircraft carrier; />Is a random phase; />Is the level of the carrier planeA flight speed;
the space-time conversion relation of the ship tail speed field is as follows，/>For the carrier aircraft approaching the speed of the stern deck, < >>For time, i.e. the velocity field component can be +.>、/>Respectively transform into->And->The expressions are as follows:
（5）
（6）
wherein:
（7）
step four: and (3) calibrating and measuring a ship tail flow field and calculating a blade swing control gain coefficient of the active simulation device: according to the third step, the mathematical model of the ship tail flow field which needs to be simulated in the wind tunnel can be obtained asThe mathematical model->Leading into a control program of a ship wake field active simulation device to generate an initial blade swing angle sequence +.>Starting a wind tunnel to a specified wind speed, starting a ship tail flow field active simulation device after the wind speed is stabilized for a few seconds, enabling a blade to swing up and down according to a generated swing angle sequence, triggering a Data acquisition system to acquire incoming flow wind speed Data4 and vertical speed Data3 of a test area, and obtaining a blade swing control gain coefficient K of the ship tail flow field active simulation device, wherein the calculation formula is as follows:
（8）
（9）
（10）
step five: the ship tail flow field simulation, the flow field calibration system is dismantled, and the modeling method in the third step is used for obtaining a ship tail flow field mathematical modelSubstituting the blade swing control gain coefficient K in the fourth step to obtain the swing angle of the plate movement +.>Leading the wind tunnel into a ship wake field active simulation device, starting the wind tunnel to a specified wind speed and stabilizing for a plurality of seconds, and starting the ship wake field active simulation device to control the blade to follow the target curveAnd (3) line swinging, wherein a target aircraft carrier wake velocity field is generated at the downstream of the wind tunnel test section, so that wind tunnel test simulation of aircraft carrier wake velocity is realized, and the expression of the blade movement swinging angle is as follows:
（11）。
2. the method for actively simulating wind tunnel test of the ship-based aircraft landing process ship-based wake field, which is characterized by comprising the following steps of: when the swing amplitude angle of the blade is 20 degrees, the swing frequency is not lower than 3Hz.
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