CN117686176A - Temporary flushing supersonic wind tunnel flutter test device and method - Google Patents
Temporary flushing supersonic wind tunnel flutter test device and method Download PDFInfo
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- CN117686176A CN117686176A CN202410158137.3A CN202410158137A CN117686176A CN 117686176 A CN117686176 A CN 117686176A CN 202410158137 A CN202410158137 A CN 202410158137A CN 117686176 A CN117686176 A CN 117686176A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The invention discloses a device and a method for a temporary impact supersonic wind tunnel flutter test. The device comprises a wind tunnel lower wall plate, wherein a lower residence chamber is arranged on the outer side of the wind tunnel lower wall plate, an opening opposite to the lower residence chamber is formed in the wind tunnel lower wall plate, a three-degree-of-freedom mechanism is arranged in the lower residence chamber, a model main body is arranged on the three-degree-of-freedom mechanism, a model is arranged on the model main body, and the three-degree-of-freedom mechanism can realize the change adjustment of the model along the wind tunnel airflow direction, the vertical airflow direction and the pitch angle. The method is based on a three-degree-of-freedom mechanism to control the model main body and the test process of the model. The invention has the beneficial effects that: the model main body and the model pitch angle changing function are simple and convenient to realize, complex devices and control systems are not required to be designed, and operability is improved; the design difficulty of the test scheme is reduced, the test safety requirement can be effectively met, and the implementation of the flutter test is ensured; before the wind tunnel is started, the model main body and the model are positioned in the lower residence chamber, and the flow field establishment cannot be influenced by the blockage degree of the test piece.
Description
Technical Field
The invention belongs to the technical field of wind tunnels, and particularly relates to a temporary impact supersonic wind tunnel flutter test device and method.
Background
Flutter is a destructive vibration occurring on an aircraft, and once the flight speed is pressed above a critical value, the amplitude rapidly increases and diverges, thereby causing the aircraft or parts thereon such as wings, rudder plates and the like to break, and serious flight accidents occur. Therefore, the aircraft is never allowed to flutter within the flight envelope. Since the flutter phenomenon is likely to occur mainly in the wings or rudders of an aircraft, the flutter test mainly uses the wings and rudders as main test subjects. Because of the requirement to simulate the mass and stiffness distribution of the wing or rudder, models of the wing or rudder are typically made of metal beams to simulate stiffness, filled with composite materials to meet the form simulation requirements. Overall, such models are much weaker in stiffness and strength than conventional test models. To ensure that the test proceeds smoothly, the chatter test is generally conducted using a model retraction device as shown in fig. 1, in which: 01 is an action cylinder, 02 is a guide rod, 03 is a sliding block, 04 is a support, 05 is a baffle, 1 is a wind tunnel lower wall plate, 2 is an opening, and 8 is a model.
The specific test flow is as follows:
step 1, before the wind tunnel is started, the model main body is installed in the wind tunnel, and the model is received into a residence chamber through the model receiving and releasing device.
And 2, starting the wind tunnel according to a given test working condition, wherein the model is positioned in the residence chamber and cannot bear impact load during starting of the wind tunnel.
And 3, after the flow field is established, controlling the model to extend into the airflow environment of the wind tunnel through the model retraction device.
And 4, changing the wind tunnel rapid pressure according to a given working condition, and measuring the flutter condition of the model through a sensor.
And 5, when all the test steps are completed according to the plan, the model still does not generate vibration or vibration occurs to the model of all the test steps, rapidly recovering the model into the resident chamber through the model recovering and releasing device.
And 6, closing the wind tunnel.
The prior art has the following disadvantages:
firstly, the pitch angle change simulation is difficult, and the description of the section above shows that in order to ensure that the relative position relationship between the model main body and the model is consistent with the real state as much as possible, the model main body is generally provided with a groove at the position of the model, so that the model can be conveniently stretched out and retracted.
When the pitch angle of the model needs to be adjusted, an angle automatic rotating device can be added to the retraction device, the model rotates to a required model angle after extending out of place, and the model is firstly rotated back to a zero pitch angle before the test is finished and then the parking chamber is retracted, but the difficulty of structural design and control is increased, once the rotating device fails, the model cannot be retracted into the parking chamber, and the model is damaged when a wind tunnel is shut down; if the model is adjusted to a required pitch angle before the test in a manual mode, an independent device is required to be designed on the model main body in order to ensure that the model extends out of the model main body smoothly, so that the slotting angle is consistent with the model pitch angle.
When the model main body and the model pitch angle are adjusted together, because of the limitation of the structure of the model retraction device, in order to ensure that the model normally extends into and extends out of the model main body, the model main body can only rotate to adjust the pitch angle by taking the position of the model as an axis, and the test limit on the model positioned at the tail part (such as a tail rudder) of the model main body is very large, because the pitch angle adjustment easily causes the head part of the model main body to be too close to other side wall plates of a wind tunnel. Even though the above-mentioned problems do not exist in flutter tests such as those using wing models, since the model body is fixed to the wind tunnel wall plate, a large number of fixing points need to be designed on the wind tunnel wall plate, which is an unrecoverable damage to the wind tunnel wall plate. Meanwhile, an independent device needs to be designed to realize automatic or manual pitching angle change of the model.
Secondly, the model main body is always exposed in a wind tunnel flow field environment, and is in a state with a pitch angle when the wind tunnel is started/shut down, and the impact load born by the model main body is several times of that of a zero pitch angle state, so that the model main body is required to have higher strength and rigidity, the strength check of the model main body possibly cannot meet the requirement of test safety, and further the test cannot be implemented.
Thirdly, the model main body is always exposed in the wind tunnel flow field environment, and the blocking degree of the model main body can influence the establishment of the supersonic flow field when the wind tunnel is started/shut down, so that the size of the model main body can be limited to a certain extent, the model shrinkage is larger, and the simulation of the real state of the model is influenced.
Disclosure of Invention
The invention aims at: the invention provides a device and a method for a temporary-flushing supersonic wind tunnel flutter test, which solve the problems in three aspects when the temporary-flushing supersonic wind tunnel develops the flutter test: firstly, the pitch angle changing difficulty is high; secondly, the wind tunnel is started under the condition that the main body of the model is provided with a pitch angle, so that the impact load born by the model is large; thirdly, the model main body is always exposed in the wind tunnel flow field, and in order to meet the requirement of blocking degree, the size of the model main body is limited.
The aim of the invention is achieved by the following technical scheme:
the utility model provides a supersonic wind tunnel flutter test device of dashing temporarily, includes the wind tunnel lower wallboard, and the outside of wind tunnel lower wallboard is equipped with down and resides the room, has seted up on the wind tunnel lower wallboard with down the relative opening of room, is equipped with three degree of freedom mechanisms down in the residence, is equipped with the model main part on the three degree of freedom mechanisms, is equipped with the model on the model main part, and three degree of freedom mechanisms can realize the change adjustment of model along wind tunnel air current direction, the direction of perpendicular air current and pitch angle.
Further, the three-degree-of-freedom mechanism comprises an x-axis guide rail, a y-axis guide rail and a curved knife mechanism, wherein the x-axis guide rail is arranged in the lower residence chamber, the y-axis guide rail is arranged on the x-axis guide rail, the curved knife mechanism is arranged on the y-axis guide rail, and the curved knife mechanism is provided with a model main body.
Further, the model is horizontally arranged.
Further, the three-degree-of-freedom mechanism is connected with the tail of the model main body through a tail support.
Further, the model is vertically arranged.
Further, the three-degree-of-freedom mechanism is connected with the tail end side part of the model main body through a U-shaped tray support.
Further, the model is arranged upside down.
A temporary impact supersonic wind tunnel flutter test method adopts the test device, and comprises the following steps:
step 1, controlling a model main body and a model to be positioned in a lower residence chamber through a three-degree-of-freedom mechanism, wherein the model is in a state with a pitch angle;
step 2, starting a wind tunnel;
and 3, after the wind tunnel flow field is established, controlling the model to move upwards through the three-degree-of-freedom mechanism, and throwing the model into the wind tunnel flow field. The pitch angle of the mechanism is adjusted while moving upwards, so that the mechanism is restored to the pitch angle state of the mechanism required by the test as soon as possible;
step 4, controlling the reverse airflow movement of the model through a three-degree-of-freedom mechanism to enable the model to be positioned in a test area;
step 5, returning to a pitch angle state before blowing after finishing the set test steps;
step 6, controlling the model to move along the airflow through a three-degree-of-freedom mechanism so as to enable the model to return to the throwing position;
step 7, controlling the model to return to the lower residence chamber through the three-degree-of-freedom mechanism;
and 8, closing the wind tunnel.
A temporary impact supersonic wind tunnel flutter test method adopts the test device, and comprises the following steps:
step 1, adjusting the transverse angle of a model main body on a three-degree-of-freedom mechanism to realize the simulation of a model pitch angle;
step 2, adjusting the pitch angle of the mechanism through a three-degree-of-freedom mechanism, and controlling the model main body and the model to be positioned in a lower residence chamber, wherein the model is in a state with the pitch angle;
step 3, starting the wind tunnel;
step 4, after the wind tunnel flow field is established, controlling the model to move upwards through the three-degree-of-freedom mechanism, throwing the model into the wind tunnel flow field, and adjusting the pitch angle of the mechanism while moving upwards, so that the mechanism can be restored to the mechanism pitch angle state required by the test as soon as possible;
step 5, controlling the reverse airflow movement of the model through a three-degree-of-freedom mechanism to enable the model to be positioned in a test area;
step 6, completing a test according to a set test ladder, and restoring the mechanism to a pitch angle state before blowing after the test is completed;
step 7, controlling the model to move along the airflow through a three-degree-of-freedom mechanism so as to enable the model to return to the throwing position;
step 8, controlling the model to return to the lower residence chamber downwards through the three-degree-of-freedom mechanism;
and 9, closing the wind tunnel.
The invention has the beneficial effects that:
firstly, the model main body and the model pitch angle changing function are easy to realize, a complex device and a control system are not required to be designed, and the operability is improved.
Secondly, the problem that the main body test piece is started with a pitch angle to bear huge impact load does not exist, the design difficulty of a test scheme is reduced, the test safety requirement can be effectively met, and the implementation of a flutter test is ensured.
Thirdly, the model main body and the model are positioned in the lower residence chamber before the wind tunnel is started, the flow field is established and cannot be influenced by the blocking degree of the test piece, and the wind tunnel control requirement is reduced.
The foregoing inventive subject matter and various further alternatives thereof may be freely combined to form a plurality of alternatives, all of which are employable and claimed herein; and the invention can be freely combined between the (non-conflicting choices) choices and between the choices and other choices. Various combinations will be apparent to those skilled in the art from a review of the present disclosure, and are not intended to be exhaustive or all of the present disclosure.
Drawings
Fig. 1 is a schematic diagram of a conventional flutter test model retraction device.
Fig. 2 is a schematic diagram of the flutter test of example 1.
Fig. 3 is a schematic diagram of the flutter test of example 2.
Fig. 4 is a schematic view of the tail support of example 1.
Fig. 5 is a schematic view of the tray support of embodiment 2.
In the figure: the device comprises a 1-wind tunnel lower wall plate, a 2-opening, a 3-lower residence chamber, a 4-x axis guide rail, a 5-y axis guide rail, a 6-knife bending mechanism, a 7-model main body, an 8-model, a 9-tail support and a 10-tray support; 01-action cylinder, 02-guide rod, 03-slide block, 04-support and 05-baffle.
Detailed Description
The following non-limiting examples illustrate the invention.
Example 1
Referring to fig. 2 and 4, a temporary impact supersonic wind tunnel flutter test device and a flutter test method based on a special test section, wherein the special test section can ensure that a model is prevented from impact load in a wind tunnel starting/closing stage. The device comprises a wind tunnel lower wall plate 1, an opening 2, a lower residence chamber 3, a three-degree-of-freedom mechanism (comprising an x-axis guide rail 4, a y-axis guide rail 5 and a curved knife mechanism 6), a model main body 7, a model 8 and a tail support 9.
The outer side of the wind tunnel lower wall plate 1 is provided with a lower resident chamber 3, and the wind tunnel lower wall plate 1 is provided with an opening 2 opposite to the lower resident chamber 3 so as to realize that a model enters a wind tunnel flow field and returns to the lower resident chamber. The lower resident chamber 3 is internally provided with a three-degree-of-freedom mechanism, the three-degree-of-freedom mechanism is provided with a model main body 7, the model main body 7 is provided with a model 8, and the three-degree-of-freedom mechanism can realize the change adjustment of the model along the airflow direction of the wind tunnel, the direction vertical to the airflow and the pitch angle.
Specifically, the three-degree-of-freedom mechanism comprises an x-axis guide rail 4 (the x-axis is parallel to the airflow direction), a y-axis guide rail 5 (the y-axis is perpendicular to the airflow direction) and a curved knife mechanism 6, wherein the x-axis guide rail 4 is arranged in the lower residence chamber 3, the x-axis guide rail 4 is used for controlling the model to be adjusted along the airflow direction of the wind tunnel, the y-axis guide rail 5 is arranged on the x-axis guide rail 4, the y-axis guide rail 5 is used for controlling the model to be adjusted along the airflow direction perpendicular to the model, the curved knife mechanism 6 is arranged on the y-axis guide rail 5, the curved knife mechanism 6 is used for controlling the adjustment of the pitch angle of the model, and the curved knife mechanism 6 is provided with a model main body 7.
The model 8 is horizontally arranged, and the three-degree-of-freedom mechanism is connected with the tail of the model main body 7 through a tail support 9.
The test method is based on a special test section, adopts the test device and comprises the following steps: step 1, before the test, the model main body and the model are controlled by a three-degree-of-freedom mechanism to be positioned in a lower residence chamber, and the model is in a state with a pitch angle.
And 2, starting the wind tunnel, wherein the model is not influenced by impact load.
And 3, after the wind tunnel flow field is established, controlling the model to move upwards through a three-degree-of-freedom mechanism (y-axis guide rail 5), throwing the model into the wind tunnel flow field, and adjusting the pitch angle of the mechanism through the three-degree-of-freedom mechanism (knife bending mechanism 6) while moving upwards, so that the mechanism can be restored to the pitch angle state of the mechanism required by the test as soon as possible.
And 4, controlling the model to move in reverse airflow through a three-degree-of-freedom mechanism (an x-axis guide rail 4) so that the model is positioned in a test area.
And 5, returning to a pitch angle state before blowing after completing the set test step (all the vibration tests are performed by changing the total pressure of the fixed attack angle, so that the working condition of the test step refers to the step of changing the total pressure).
And 6, controlling the model to move along the airflow through a three-degree-of-freedom mechanism (the x-axis guide rail 4) so as to enable the model to return to the throwing position.
And 7, controlling the model to return to the lower residence chamber through a three-degree-of-freedom mechanism (the y-axis guide rail 5).
And 8, closing the wind tunnel.
It can be seen that the special test section has the advantages of carrying out the flutter test: firstly, the model main body and the model cannot bear impact load; secondly, when the wind tunnel is started, the model main body and the model are both positioned in the lower resident chamber, the model blocking influence is avoided, and the wind tunnel flow field is smoothly established; thirdly, the pitch angle adjustment of the model body or the model is carried out based on the model body or the supporting device, the wind tunnel wall plate cannot be damaged, and meanwhile, the pitch angle changing design is relatively simple.
The following problems exist in developing the flutter test based on the test flow: the method is characterized in that the slotting width of the lower wall plate for the model to come in and go out of the lower resident chamber is limited (the maximum width of a runner in a 2 m-level wind tunnel is 2m, the slotting width is not more than 1m in consideration of the fact that the lower wall plate is taken as a bearing part, personnel and equipment pass through and the like), and when a test is carried out in a horizontal arrangement mode, the model is relatively large in shrinkage, so that the simulation of a real state is influenced; secondly, the slotting length of the lower wall plate is limited, and the size of the model meeting the model throwing requirement is limited.
Example 2
In order to solve the above problems, referring to fig. 3 and 5, a temporary impact supersonic wind tunnel flutter test device and a flutter test method based on a special test section are shown. The device comprises a wind tunnel lower wall plate 1, an opening 2, a lower residence chamber 3, a three-degree-of-freedom mechanism, a model main body 7, a model 8 and a tray support 10.
The outer side of the wind tunnel lower wall plate 1 is provided with a lower resident chamber 3, and the wind tunnel lower wall plate 1 is provided with an opening 2 opposite to the lower resident chamber 3 so as to realize that a model enters a wind tunnel flow field and returns to the lower resident chamber. The lower resident chamber 3 is internally provided with a three-degree-of-freedom mechanism, the three-degree-of-freedom mechanism is provided with a model main body 7, the model main body 7 is provided with a model 8, and the three-degree-of-freedom mechanism can realize the change adjustment of the model along the airflow direction of the wind tunnel, the direction vertical to the airflow and the pitch angle.
This embodiment differs from embodiment 1 in that:
firstly, the model 8 is vertically arranged, the model main body and the model of the embodiment 1 are rotated by 90 degrees, namely, a conventional flutter test model is horizontally arranged, the change of a pitch angle simulation angle is mainly changed, after the model is rotated by 90 degrees, the model is vertically arranged, and the pitch angle simulation of the model main body is realized through transverse angle deflection in a horizontal plane.
And secondly, the three-degree-of-freedom mechanism is connected with the tail end side part of the model main body 7 through a U-shaped tray support 10, the traditional tail support mode is improved into a tray support, the pitch angle simulation of the model main body can be realized through the rotation of the model main body around a rotating shaft, and meanwhile, the model length is also increased compared with that of the tail support.
Thirdly, in order to further increase the length of the model main body, compared with the traditional wind tunnel before starting, the model main body is in a mechanism zero pitch angle state, and is improved to be in an initial state of a mechanism with pitch angle state. For example, assuming that the mechanism is in a zero pitch state, the length of the model body capable of satisfying the constraint of the slotting length of the lower wall plate is 1.6m, and when the mechanism angle is 30 °, the model length capable of satisfying the same condition is increased by 1.6/cos (30 °) =1.84 m, and the available length is increased by 15%.
And fourthly, the model 8 is arranged upside down so as to ensure that the model main body and the model are all positioned in the lower residence chamber before the wind tunnel is started, and do not bear impact load. At this time, although the model main body enters the flow field at an angle, the lifting surface is greatly reduced compared with the horizontal arrangement because the model is vertically arranged, the pneumatic load born by the model main body is much smaller, and the test safety is ensured.
The test method adopts the test device and comprises the following steps: and step 1, before the test, adjusting the transverse angle of the model main body on the three-degree-of-freedom mechanism to realize the simulation of the pitch angle of the model.
And 2, adjusting the pitch angle of the mechanism through the three-degree-of-freedom mechanism, and controlling the model main body and the model to be positioned in the lower residence chamber, wherein the model is in a state with the pitch angle.
And 3, starting the wind tunnel, wherein the model is not influenced by impact load.
And 4, after the wind tunnel flow field is established, controlling the model to move upwards through the three-degree-of-freedom mechanism, throwing the model into the wind tunnel flow field, and adjusting the pitch angle of the mechanism while moving upwards, so that the mechanism can be restored to the mechanism pitch angle state required by the test as soon as possible.
And 5, controlling the reverse airflow movement of the model through the three-degree-of-freedom mechanism to enable the model to be positioned in a test area.
And 6, completing the test according to the set test steps, and recovering the mechanism to a pitch angle state before blowing after the test is completed.
And 7, controlling the model to move along the airflow through the three-degree-of-freedom mechanism, so that the model returns to the throwing position.
Step 8, simultaneously adjusting the pitch angle of the mechanism and controlling the model to return to the lower residence chamber through the three-degree-of-freedom mechanism;
and 9, closing the wind tunnel.
The embodiment provides a temporary impact supersonic wind tunnel flutter test device and method, which solve the problems that the pitch angle is difficult to change, a main body test piece is always positioned in a wind tunnel body in the prior art, the size of the main body test piece is limited due to the influence of the model blocking degree requirement, the main body test piece is large in starting impact load with the pitch angle, the strength checking result is difficult to meet the test safety requirement, and the like, expand the capacity covered wire of the flutter test, enable the flutter test which cannot be performed before to be implemented, and improve the test work efficiency.
Firstly, the horizontal arrangement of the model main body and the model is changed into the vertical arrangement, and the transverse deflection angle of the model main body and the model is changed by a special device to realize pitch angle simulation, and meanwhile, the problem of limiting the model scaling by the width dimension of the throwing groove of the special test section is solved.
Secondly, the model installation mode is improved into model reverse installation, so that the spanwise length of the test piece after vertical arrangement can be completely sunk into the lower residence chamber.
And thirdly, the traditional mechanism zero pitch angle throwing mode is improved to the mechanism pitch angle throwing mode, so that the problem of model scaling limitation of the length dimension of a special test section throwing groove is solved.
Details of several designs:
firstly, the position of the rotating shaft of the model main body is positioned in the middle of the model as much as possible so as to increase the achievable transverse deflection angle, namely the pitch angle range of the model.
Secondly, on the premise of meeting the test requirement, the length of the model main body is as short as possible, so that the pitching angle of the mechanism before the test required for ensuring that the model main body is totally sunk into the lower resident room is reduced. Although the vertical lifting surface is far smaller than the horizontal lifting surface, the smaller pitch angle of the mechanism is smaller corresponding to the model main body and the aerodynamic load born by the model, and the test safety is facilitated.
And thirdly, reasonably matching the movement speed of the three-degree-of-freedom mechanism in the vertical direction and the pitch angle change speed of the mechanism when the model enters and exits from the lower resident room, so as to ensure that the model main body and the lower wall plate are not interfered, and test safety accidents are caused.
The method provided by the invention is applied to supersonic wind tunnels, and the flutter test of the model main body and the model with pitch angle is realized by using the device and the method provided by the invention.
The foregoing basic embodiments of the invention, as well as other embodiments of the invention, can be freely combined to form numerous embodiments, all of which are contemplated and claimed. In the scheme of the invention, each selection example can be arbitrarily combined with any other basic example and selection example.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (9)
1. The utility model provides a supersonic wind tunnel flutter test device of dashing temporarily, includes wind tunnel lower wall board (1), its characterized in that: the wind tunnel is characterized in that a lower residence chamber (3) is arranged on the outer side of the wind tunnel lower wall plate (1), an opening (2) opposite to the lower residence chamber (3) is formed in the wind tunnel lower wall plate (1), a three-degree-of-freedom mechanism is arranged in the lower residence chamber (3), a model main body (7) is arranged on the three-degree-of-freedom mechanism, a model (8) is arranged on the model main body (7), and the three-degree-of-freedom mechanism can realize the change adjustment of the model along the wind tunnel airflow direction, the vertical airflow direction and the pitch angle.
2. The temporary impact supersonic wind tunnel flutter test device according to claim 1, wherein: the three-degree-of-freedom mechanism comprises an x-axis guide rail (4), a y-axis guide rail (5) and a curved knife mechanism (6), wherein the x-axis guide rail (4) is arranged in the lower residence chamber (3), the y-axis guide rail (5) is arranged on the x-axis guide rail (4), the curved knife mechanism (6) is arranged on the y-axis guide rail (5), and the curved knife mechanism (6) is provided with a model main body (7).
3. The temporary impact supersonic wind tunnel flutter test device according to claim 1 or 2, wherein: the model (8) is horizontally arranged.
4. A temporary impact supersonic wind tunnel flutter test device according to claim 3, wherein: the three-degree-of-freedom mechanism is connected with the tail of the model main body (7) through a tail support (9).
5. The temporary impact supersonic wind tunnel flutter test device according to claim 1, wherein: the model (8) is vertically arranged.
6. The temporary impact supersonic wind tunnel flutter test device according to claim 5, wherein: the three-degree-of-freedom mechanism is connected with the tail end side part of the model main body (7) through a U-shaped tray support (10).
7. The temporary impact supersonic wind tunnel flutter test device according to claim 5 or 6, wherein: the model (8) is arranged upside down.
8. A method for testing the flutter of a temporary-impact supersonic wind tunnel, which adopts the testing device of any one of claims 1 to 4, and is characterized by comprising the following steps:
step 1, controlling a model main body and a model to be positioned in a lower residence chamber through a three-degree-of-freedom mechanism, wherein the model is in a state with a pitch angle;
step 2, starting a wind tunnel;
step 3, after the wind tunnel flow field is established, controlling the model to move upwards through the three-degree-of-freedom mechanism, throwing the model into the wind tunnel flow field, and adjusting the pitch angle of the mechanism while moving upwards, so that the mechanism can be restored to the mechanism pitch angle state required by the test as soon as possible;
step 4, controlling the reverse airflow movement of the model through a three-degree-of-freedom mechanism to enable the model to be positioned in a test area;
step 5, returning to a pitch angle state before blowing after finishing the set test steps;
step 6, controlling the model to move along the airflow through a three-degree-of-freedom mechanism so as to enable the model to return to the throwing position;
step 7, controlling the model to return to the lower residence chamber through the three-degree-of-freedom mechanism;
and 8, closing the wind tunnel.
9. A method for testing the flutter of a temporary-impact supersonic wind tunnel, which adopts the testing device of any one of claims 5 to 7, and is characterized by comprising the following steps:
step 1, adjusting the transverse angle of a model main body on a three-degree-of-freedom mechanism to realize the simulation of a model pitch angle;
step 2, adjusting the pitch angle of the mechanism through a three-degree-of-freedom mechanism, and controlling the model main body and the model to be positioned in a lower residence chamber, wherein the model is in a state with the pitch angle;
step 3, starting the wind tunnel;
step 4, after the wind tunnel flow field is established, controlling the model to move upwards through the three-degree-of-freedom mechanism, throwing the model into the wind tunnel flow field, and adjusting the pitch angle of the mechanism while moving upwards, so that the mechanism can be restored to the mechanism pitch angle state required by the test as soon as possible;
step 5, controlling the reverse airflow movement of the model through a three-degree-of-freedom mechanism to enable the model to be positioned in a test area;
step 6, completing a test according to a set test ladder, and restoring the mechanism to a pitch angle state before blowing after the test is completed;
step 7, controlling the model to move along the airflow through a three-degree-of-freedom mechanism so as to enable the model to return to the throwing position;
step 8, controlling the model to return to the lower residence chamber downwards through the three-degree-of-freedom mechanism;
and 9, closing the wind tunnel.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202410158137.3A CN117686176A (en) | 2024-02-04 | 2024-02-04 | Temporary flushing supersonic wind tunnel flutter test device and method |
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| CN202410158137.3A CN117686176A (en) | 2024-02-04 | 2024-02-04 | Temporary flushing supersonic wind tunnel flutter test device and method |
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