CN209841336U - Temporary impulse type supersonic wind tunnel sonic boom measurement test device - Google Patents
Temporary impulse type supersonic wind tunnel sonic boom measurement test device Download PDFInfo
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- CN209841336U CN209841336U CN201920983239.3U CN201920983239U CN209841336U CN 209841336 U CN209841336 U CN 209841336U CN 201920983239 U CN201920983239 U CN 201920983239U CN 209841336 U CN209841336 U CN 209841336U
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Abstract
The application discloses temporary impact type supersonic wind tunnel sonic boom measurement test device, which aims to solve the problem that when a temporary impact type supersonic wind tunnel is adopted for sonic boom measurement test, the test result is not high in accuracy when a probe is used for carrying out the sonic boom measurement test. The temporary-impulse type supersonic wind tunnel sonic boom measurement test device comprises a first wind tunnel test section wallboard, a second wind tunnel test section wallboard, a measurement probe connecting device, a model connecting device, a reference probe fixing device and the like. By adopting the device, the model, the measuring probe and the supporting device thereof can be effectively protected from deformation caused by bearing large impact load at the start/shutdown stage of the supersonic wind tunnel, and the small-range differential pressure sensor is protected from being damaged. Meanwhile, the sound explosion measurement test can be carried out in two modes of model movement and measurement probe movement on the premise of keeping the overall test layout unchanged, so that the accuracy of the sound explosion measurement result is effectively improved.
Description
Technical Field
The invention relates to the field of aerospace wind tunnel tests, in particular to a temporary impulse type supersonic wind tunnel sonic boom measurement test device.
Background
The sonic boom refers to a series of waves generated by the appearance of an aircraft when the running speed of the aircraft reaches supersonic speed, wherein the series of waves interfere with each other and influence each other in the process of spreading to a distance, and finally the series of waves are converged into a front shock wave wrapping the head of the aircraft and a rear shock wave trailing the tail of the aircraft. When this wave system propagates to the ground, it is perceived as two thunder-like loud sounds.
As an independent test technology, the sonic boom measurement test is to acquire sonic boom characteristics generated by an aircraft in a test mode. The basic idea of the sonic boom measurement test is that aiming at a certain test state of an aircraft model, the relative position of the aircraft model and a measuring device along the direction of a flight trajectory line is changed, and the change characteristic of pressure which is relatively to non-interference data when the pressure is subjected to wave system interference generated by the model under the flight trajectory line is obtained. The test conditions for the fixed configuration model mainly include: the attack angle and the roll angle representing the change of the model attitude, and the longitudinal distance between the model centroid representing the sonic boom propagation distance of the model and the measurement position.
There are generally two ways to change the relative position of the aircraft model and the measurement device along the flight trajectory: one is a mode of keeping the position of the model in the wind tunnel unchanged during the test, and changing the relative position of the measuring device in the wind tunnel through a motion mechanism so as to obtain the wave system influence of the complete model; one is to keep the position of the measuring device in the wind tunnel unchanged during the test, and to change the relative position of the model in the wind tunnel through a kinematic mechanism, thereby obtaining the influence of the complete model wave system.
The static pressure probe is used as a main measuring device, and is a typical test mode of a sonic boom measurement test, and a typical layout diagram of the mode in a wind tunnel is shown in fig. 1. In fig. 1, 1 is an upper wall plate of a wind tunnel test section, 2 is a lower wall plate of the wind tunnel test section, 3 is a model, 4 is a model connecting device, 5 is a model actuating mechanism (which is used for controlling the model to move), 6 is a measuring probe, 7 is a measuring probe connecting device, 8 is a probe fixing device or a probe actuating mechanism (if the test adopts the mode of model moving, 8 can be a probe fixing device which is connected with the wall plate of the test section and can also be a probe actuating mechanism which does not act only during the test, if the test adopts the mode of probe moving, 8 is a probe actuating mechanism which controls the probe to move through the part), 9 is a reference probe, and 10 is a reference probe fixing device.
The measuring probe 6 and the reference probe 9 are in a needle-like shape, a static pressure hole is arranged on the surface of the probe at a position which is vertical to the probe head, the static pressure hole is communicated with a pipeline which is arranged in the probe and runs through along the axis, and the pipeline is connected into a pressure measuring device through an external pipeline to realize pressure measurement.
Before the test is started, the model 3 is connected with the model actuating mechanism 5 through the model connecting device 4, the measuring probe 6 is connected with the probe fixing device or the probe actuating mechanism 8 through the measuring probe connecting device 7, and the reference probe 9 is connected with the test section wallboard through the reference probe fixing device 10 and is kept still during the test.
For convenience of description, the following coordinate system is defined:
the x axis is defined as being positioned in a horizontal bisection plane of the wind tunnel, and is positive downstream along the axial direction of the wind tunnel;
the y axis is defined as the vertical wind tunnel horizontal median plane, and is positive when viewed along the airflow direction;
the z-axis satisfies the right hand rule;
the origin is defined as the intersection of the x, y and z axes in the cross section of the entrance of the wind tunnel test section.
It should be noted that the default model and the measurement probe are defined above and installed on the upper and lower wall plates of the wind tunnel test section, and if the default model and the measurement probe are installed on the left and right side walls of the wind tunnel, the default model and the measurement probe are defined and adjusted accordingly.
Taking the test mode of measuring the movement of the probe as an example, the basic flow of the test is as follows:
(a) adjusting the attitude angle of the model according to the test conditions;
(b) adjusting the attitude angle of the measuring probe to ensure that the axis of the probe is parallel to the axis of the wind tunnel;
(c) adjusting the relative positions of the model and the measuring probe in the y direction to meet the requirement that the model and the measuring probe have a given distance h in the y direction;
(d) starting a wind tunnel and establishing a flow field;
(e) the probe actuating mechanism controls the measuring probe to gradually move from an x-position far away from the influence of the model sonic boom along a direction parallel to the axis of the wind tunnel, pass through the model sonic boom influence area and then gradually get away; during the process, the pressure sensed by the measuring probe is detected by the measuring system; during this time, the wind tunnel incoming flow static pressure is measured by using a reference probe;
(f) shutting down the wind tunnel;
(g) and (4) obtaining the model sonic boom characteristic when the distance between the model h and the model h is processed.
When the measurement mode of model movement is adopted, except that the object to be measured and the object at the fixed position are exchanged, other test procedures are consistent.
The sonic boom signature is generally characterized by an "overpressure" parameter Δ P/P, which is defined as follows:
ΔP/P=（Pp-Ps）/Ps；
wherein Pp refers to the static pressure value when a certain measuring position x is influenced by sonic boom;
ps refers to the static pressure value when a certain measurement position x is not affected by a sonic boom, i.e. the reference static pressure.
It should be noted that the above is given as a theoretical calculation formula, and in the test, it is impossible to obtain the static pressure value when a certain measurement position x is affected by the sonic boom and not affected by the sonic boom. Therefore, during a wind tunnel test, the static pressure at a certain position which has good uniformity of a wind tunnel flow field and is not in a model sonic boom influence area is measured by a device and is used as the reference static pressure during calculation of an 'overpressure' parameter; or the static pressure value when the certain measuring position x is not affected by the sonic boom is indirectly obtained through certain data processing by using the measuring result.
The sonic boom measurement test usually needs the model and the measurement probe to perform the test in the y-direction distance interval in a large range so as to obtain the propagation change rule of the sonic boom characteristic of the model along with the distance. This distance is generally characterized in multiples with respect to the model reference length and is defined as h/l, h denoting the distance of the model from the measurement probe in the y-direction and l denoting the model reference length. The larger the achievable h/l value is, the more the propagation rule of the sonic boom characteristic signal can be mastered. According to the real flight behavior example, when the flight height of the aircraft is 10000m and the length of the aircraft is 100m, the sonic boom characteristic signal generated by the aircraft is transmitted to the ground and is felt by people, and the corresponding h/l = 100; the wind tunnel test is restricted by the size of the wind tunnel, and in order to enable h/l to reach a certain value, the size of the model is much smaller than that of a conventional force measurement test model. Taking the sonic boom measurement test carried out in a 2-meter-level supersonic wind tunnel as an example, even if the influence of wall surface shock wave reflection and a boundary layer is not considered, the maximum distance between the model and the measurement probe in the y direction reaches 2000mm, even if only h/l =5 is required, the reference length of the model does not exceed 400mm, and the size is far from the size which can be satisfied by a conventional measurement test model and has the length of 1600 mm. Meanwhile, considering that the sonic boom characteristic signal belongs to the weak signal category, the peak value of delta P is in the magnitude of 100 Pa-1000 Pa, and the simulation of model details is required to be more precise to ensure high-precision measurement, and the small change of the model appearance can generate relatively larger influence on the sonic boom measurement result. Meanwhile, in order to avoid the support interference as much as possible, the support device of the model and the probe is thinner, slimmer and thinner, and has lower strength and rigidity compared with the conventional test support device.
The traditional sonic boom measurement test device is mainly used in a continuous supersonic wind tunnel, and because the impact load is very small when the wind tunnel is started, a model, a probe and a supporting device thereof are exposed in a test section and cannot generate large deformation. For the temporary-impulse type supersonic wind tunnel, a normal shock wave always exists when the wind tunnel operates, and the stable position of the normal shock wave gradually moves to the downstream along with the increase of the total pressure of the wind tunnel; when the normal shock wave stable position is positioned at the downstream of the test model area, the wind tunnel establishes a stable supersonic flow field; at the moment that the normal shock waves scan the area where the model and the probe are located, the model and the probe bear extremely large aerodynamic load and generate severe vibration; at the wind tunnel shutdown stage after the test is finished, the model and the probe bear the great aerodynamic load and generate severe vibration at the moment that the normal shock wave returns back to pass through the area where the model and the probe are located. During the test, the model and the probe are repeatedly subjected to impact load, and the model and the probe are possibly deformed, so that the accuracy of the sonic boom measurement result is influenced.
In addition, because the magnitude of the delta P is far smaller than the static pressure of the wind tunnel incoming flow, in order to ensure the measurement accuracy, a small-range differential pressure sensor is generally selected for measurement, the reference end pressure of the sensor is to measure the static pressure of a certain position in the wind tunnel flow field with good uniformity and without the model sonic boom influence area through a device, and the measurement end pressure is the value measured by a measurement probe. At a certain moment in the starting/closing stage of the wind tunnel, the measured values of the measuring end and the reference end are respectively from the upstream and the downstream of the normal shock wave, and the sensor is possibly damaged by the generated large pressure difference.
Furthermore, although both the model and the measuring probe have the movement capability in the conventional sonic boom measurement test, the difference of the movement capability is large, and the requirement of carrying out the test by adopting one test mode of model movement and measuring probe movement can only be met. Taking a measurement probe movement test mode as an example, an actuating mechanism matched with the measurement probe often has the adjusting capability of the degrees of freedom such as x, y, attack angle and the like, wherein the change of a test state is realized by using the adjusting capability of the x and y directions, and the adjusting capability of the attack angle is mainly used for ensuring the installation requirement of the probe at a zero attack angle; and the mechanism or the fixing device matched with the model ensures that the model always keeps the same state during the test, or only has the adjusting capability of the x direction and the attack angle, wherein the adjusting capability of the x direction is far weaker than the adjusting capability of the x direction of the actuating mechanism matched with the measuring probe, and only has the local moving capability and does not have the capability of carrying out the sonic boom measurement test based on the movement of the model. The situation is similar when the test mode of model movement is adopted.
The probe movement test mode has the advantages that the model is always in a fixed position, and the change of the wave system of the model is relatively fixed; the disadvantage is that the probe is sensitive to the change of the measuring value, and if the background pressure fluctuation in the moving interval of the measuring probe is larger, the measuring result of the measuring probe can be influenced. The model movement test mode has the advantages that the position of the measuring probe is fixed, the interference on the measuring probe is a fixed quantity, the system is poor when data are corrected, and the data are relatively well processed; the disadvantage is that the moving interval of the model may cause the sonic boom characteristic curve not to be the result corresponding to the same state if the background pressure fluctuation is large. In summary, both test modes have advantages and disadvantages, and the way in which more reliable test data can be obtained may be different for different situations.
In addition, in view of the weak signal property of the sonic boom characteristics, no matter whether the sonic boom measurement tests based on the two moving modes are respectively carried out in different wind tunnels or the test comparison research based on the two test modes is realized in the same wind tunnel by changing the layout of the model and the measurement probe in the wind tunnel, a plurality of interference factors are introduced to influence the analysis of test data.
Therefore, the ability of simultaneously adopting two test modes to carry out the test in the same period of test can obtain better test data, and is more favorable for the comparative analysis of the test data.
Disclosure of Invention
The invention aims to: in order to overcome the problem that the accuracy of a test result is not high when a temporary impulse type supersonic wind tunnel is adopted to carry out a sonic boom measurement test and the conventional probe is utilized to carry out the sonic boom measurement test, the temporary impulse type supersonic wind tunnel sonic boom measurement test device is provided. By adopting the device, the model, the measuring probe and the supporting device thereof can be effectively protected from deformation caused by bearing large impact load at the start/shutdown stage of the supersonic wind tunnel, and the small-range differential pressure sensor is protected from being damaged. Meanwhile, the sound explosion measurement test can be carried out in two modes of model movement and measurement probe movement on the premise of keeping the overall test layout unchanged, so that the accuracy of the sound explosion measurement result is effectively improved.
In order to achieve the purpose, the invention adopts the following technical scheme:
a temporary-impulse type supersonic wind tunnel sonic boom measurement test device comprises a first wind tunnel test section wallboard, a second wind tunnel test section wallboard, a measurement probe connecting device, a model connecting device used for being connected with a model to be tested, a reference probe and a reference probe fixing device, wherein the first wind tunnel test section wallboard and the second wind tunnel test section wallboard are arranged oppositely, and a temporary-impulse type supersonic wind tunnel test section is formed between the first wind tunnel test section wallboard and the second wind tunnel test section wallboard;
the device also comprises a first parking chamber matched with the first wind tunnel test section wall plate, a second parking chamber matched with the second wind tunnel test section wall plate, a first degree of freedom action mechanism, a second degree of freedom action mechanism, a first test section turning plate and a second test section turning plate;
the first wind tunnel test section wallboard is provided with a first open slot, the first test section turning plate is arranged on the first open slot, and the first test section turning plate can be opened and closed relative to the first open slot; the measuring probe is connected with the first degree-of-freedom action mechanism through the measuring probe connecting device, and the first degree-of-freedom action mechanism can drive the measuring probe to realize the movement in the X direction, the Y direction, the attack angle and the roll angle direction through the measuring probe connecting device; the first parking chamber is arranged on the outer wall of the first wind tunnel test section wallboard, a first temporary storage space is formed between the first parking chamber and the first wind tunnel test section wallboard, the first degree-of-freedom action mechanism is arranged in the first temporary storage space, and the first degree-of-freedom action mechanism can drive the measuring probe to enter the temporary impact type supersonic wind tunnel test section through the first open slot;
a second open slot is formed in the second wind tunnel test section wall plate, the second test section turning plate is arranged on the second open slot, and the second test section turning plate can be opened and closed relative to the second open slot; the two ends of the model connecting device are respectively connected with the model to be tested and the second degree-of-freedom action mechanism, and the second degree-of-freedom action mechanism can drive the model to be tested to realize the movement in the X direction, the Y direction, the attack angle and the roll angle direction through the model connecting device; the second parking chamber is arranged on the outer wall of a second wind tunnel test section wallboard, a second temporary storage space is formed between the second parking chamber and the second wind tunnel test section wallboard, the second degree-of-freedom action mechanism is arranged in the second temporary storage space, and the second degree-of-freedom action mechanism can drive the model to be tested to enter the temporary impact type supersonic wind tunnel test section through a second open slot;
and the reference probe is connected with the temporary-impulse type supersonic wind tunnel test section through a reference probe fixing device.
The first wind tunnel test section wallboard is a wind tunnel test section upper wallboard, and the second wind tunnel test section wallboard is a wind tunnel test section lower wallboard.
The first wind tunnel test section wallboard is a wind tunnel test section left wallboard, and the second wind tunnel test section wallboard is a wind tunnel test section right wallboard.
The part of the first degree-of-freedom action mechanism extending into the temporary impulse type supersonic wind tunnel test section and the part of the second degree-of-freedom action mechanism extending into the temporary impulse type supersonic wind tunnel test section adopt streamline design.
The reference probe is connected with the first wind tunnel test section wallboard or the second wind tunnel test section wallboard through the reference probe fixing device, and the position of the reference probe is such that a wave system generated by the reference probe cannot influence the airflow flow near the model.
The measuring method using the test device comprises the following steps:
a. before testing, the measuring probe is positioned in the first room, the model to be tested is positioned in the second room, and the first test section turning plate and the second test section turning plate are respectively kept closed;
b. after the supersonic flow field of the temporary impulse type supersonic wind tunnel is established, a first test section turning plate and a second test section turning plate are respectively opened, a measuring probe extends out of a first parking chamber through a first degree-of-freedom action mechanism, and a model to be measured extends out of a second parking chamber through a second degree-of-freedom action mechanism;
c. after the measuring probe respectively runs to the initial test position of the temporary impulse type supersonic wind tunnel test section through the first degree of freedom action mechanism and the model to be measured through the second degree of freedom action mechanism, the first test section turning plate and the second test section turning plate are closed;
d. changing the posture of the model to be tested according to a given test state, and starting a test according to a given test mode;
e. after the test is finished, the first test section turning plate and the second test section turning plate are opened, the measuring probe is retracted into the first parking chamber through the first degree-of-freedom action mechanism, the model to be tested is retracted into the second parking chamber through the second degree-of-freedom action mechanism, and the turning plates are closed;
f. and (5) shutting down the vehicle by using the temporary-flushing type supersonic wind tunnel to finish the test.
In order to solve the problems, the application provides a temporary impulse type supersonic wind tunnel sonic boom measurement test device. In the test device, a first parking chamber and a second parking chamber are respectively arranged outside an inner cavity of a test section and used for accommodating a model to be tested, a measuring probe and a first freedom degree action mechanism and a second freedom degree action mechanism which are matched with the measuring probe to provide space during a starting/shutting-off stage of a wind tunnel; a first open slot and a second open slot (namely, slots in the middle of the wall plates) are respectively arranged on the wall plates of the first wind tunnel test section and the second wind tunnel test section, are used for replacing the original solid wall plate of the test section and are used as channels for allowing a model and a measuring probe to enter an inner cavity of the test section from a parking room during testing; the first test section turning plate and the second test section turning plate are respectively closed when the measuring probe and the model extend into the inner cavity of the test section for testing, and are used for filling a gap between the wall plate and the multi-degree-of-freedom mechanism. In the application, when the wind tunnel flow field is established and the test is finished, the first test section turning plate and the second test section turning plate are kept open, and channels are reserved for the measurement probe and the model to be measured to enter and exit the parking chamber respectively; the model to be tested realizes the change of the x direction, the y direction, the attack angle and the roll angle through the second degree-of-freedom action mechanism, not only can realize the test mode of model movement, but also can be used for adjusting the posture and the position of the model when a probe movement test mode is adopted. The measuring probe realizes the change of x, y, attack angle and roll angle through the first degree-of-freedom action mechanism, can realize the test mode of measuring probe movement, and can be used for adjusting the posture and position of the measuring probe when adopting the model movement test mode.
In this application, first test section turns over board, second test section turns over board when closed state, except that leaving necessary passageway for the removal of degree of freedom actuating mechanism, requires that the gap of wallboard and degree of freedom actuating mechanism is minimum as far as possible, and simultaneously, first test section turns over board, second test section turns over board and test section and does not laminate as far as possible to reduce the interference to the wind-tunnel flow field. In addition, the positions of the model and the measuring probe in the room should ensure that the turnover plate can not interfere with the model to be measured and the measuring probe when being opened. Meanwhile, the first degree-of-freedom action mechanism and the second degree-of-freedom action mechanism are respectively designed with high precision, which is beneficial to ensuring that the actual test state is consistent with the given theoretical test state as much as possible so as to reduce the influence of the difference of the test states on the test result. Furthermore, the parts of the first degree-of-freedom action mechanism and the second degree-of-freedom action mechanism extending into the inner cavity of the test section are as small as possible on the premise of meeting the strength requirement and ensuring the test safety, and the streamline design is adopted, so that the interference on the flow field of the wind tunnel is reduced as much as possible.
In this application, when the room size of staying only need can satisfy the wind-tunnel start/shut down stage, the model that awaits measuring, measuring probe and supporting first degree of freedom action mechanism, second degree of freedom action mechanism the space requirement can, and need not like many traditional wind-tunnel stay rooms need be big enough and with including the test section parcel to keep test section inner chamber air current unobstructed nature and stability.
In the application, the adoption of the first degree-of-freedom action mechanism and the second degree-of-freedom action mechanism can realize that the two test modes of model movement and measurement probe movement are adopted simultaneously to develop the capability of the sonic boom measurement test on the premise of keeping the whole layout of the test unchanged in the same wind tunnel. Meanwhile, the first degree of freedom action mechanism and the second degree of freedom action mechanism are adopted, so that the requirement for changing the test state can be met, the capability of eliminating the installation errors of the model, the measuring probe and the matched connecting device is improved, and the consistency of the actual test state and the given test state can be better ensured. Furthermore, the adoption of the first degree-of-freedom action mechanism and the second degree-of-freedom action mechanism can meet the requirement of utilizing the measuring probe to carry out an air wind tunnel background pressure measurement test on one hand; on the other hand, one set of freedom degree action mechanism can be ensured to be out of order during the test, and when the emergency shutdown is needed, the other set of freedom degree action mechanism controls the model or the measuring probe connected with the other set of freedom degree action mechanism to return to the safe position, so that all test devices are not damaged.
Furthermore, the method and the device are adopted for testing, so that the testing is facilitated, and interference factors influencing the accuracy of the test result are reduced as much as possible.
In conclusion, the sound explosion measurement test can avoid the problems that the model and the measurement probe are deformed due to repeated impact load bearing, and the small-range differential pressure sensor is damaged due to the measurement of the differential pressure before and after the normal shock wave; the test device has the capability of developing a test by respectively adopting two modes of model movement and measurement probe movement on the premise of unchanging the overall layout of the test; the method can effectively eliminate the installation errors of the model, the measuring probe and the matched connecting device thereof, so that the actual test state is kept consistent with the required test state as far as possible, and the accuracy and the reliability of the sonic boom measurement result obtained based on the temporary impulse type supersonic wind tunnel are effectively ensured.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
fig. 1 is a typical test mode for a sonic boom measurement test in the prior art, which uses a static pressure probe as a main measurement device.
Figure 2 is a schematic view of the apparatus of the present invention with the mold and measurement probe received in the chamber and the flap held open.
FIG. 3 is a schematic view of the apparatus of the present invention with the mold and measurement probe extended into the test section and the flap held closed.
Fig. 4 is a view from direction a of fig. 3.
Fig. 5 is a view from direction B of fig. 3.
The labels in the figure are: 1. the wind tunnel test section comprises an upper wind tunnel test section wall plate, a lower wind tunnel test section wall plate, a model connecting device, a model actuating mechanism, a measuring probe connecting device, a measuring probe fixing device or a probe actuating mechanism, a reference probe fixing device, a first parking chamber, a first degree-of-freedom actuating mechanism, a first test section turning plate, a first 14, a second parking chamber, a second 15, a second degree-of-freedom actuating mechanism, and a second test section turning plate.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
Any feature disclosed in this specification may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
Example 1
As shown in the figure, the temporary-impulse type supersonic wind tunnel sonic boom measurement test device of the embodiment comprises a first wind tunnel test section wallboard, a second wind tunnel test section wallboard, a measurement probe connecting device, a model connecting device used for being connected with a model to be tested, a reference probe and a reference probe fixing device, wherein the first wind tunnel test section wallboard and the second wind tunnel test section wallboard are arranged oppositely, and a temporary-impulse type supersonic wind tunnel test section is formed between the first wind tunnel test section wallboard and the second wind tunnel test section wallboard. In this embodiment, the first wind tunnel test section wall plate is a wind tunnel test section upper wall plate, and the second wind tunnel test section wall plate is a wind tunnel test section lower wall plate.
The testing device of the embodiment further comprises a first parking chamber matched with the upper wall plate of the wind tunnel testing section, a second parking chamber matched with the lower wall plate of the wind tunnel testing section, a first degree-of-freedom action mechanism, a second degree-of-freedom action mechanism, a first testing section turning plate and a second testing section turning plate.
In this embodiment, a first open slot is formed in an upper wall plate of the wind tunnel test section, a first test section turning plate is arranged on the first open slot, and the measuring probe is connected with the first degree-of-freedom action mechanism through a measuring probe connecting device. The first parking chamber is arranged on the outer wall of the wind tunnel test section upper wall plate, a first temporary storage space is formed between the first parking chamber and the wind tunnel test section upper wall plate, and the first degree-of-freedom action mechanism is arranged in the first temporary storage space. In the structure, the first test section turning plate can be opened and closed relative to the first open slot, and the first degree-of-freedom action mechanism can drive the measuring probe to realize the movement in the X direction, the Y direction, the attack angle and the roll angle direction through the measuring probe connecting device; the first degree-of-freedom action mechanism can drive the measuring probe to enter the temporary impulse type supersonic wind tunnel test section through the first open slot so as to realize corresponding extension and retraction.
Meanwhile, a second open slot is arranged below a lower wall plate of the wind tunnel test section, a turning plate of the second test section is arranged on the second open slot, two ends of the model connecting device are respectively connected with the model to be tested and the second degree of freedom action mechanism, and the second degree of freedom action mechanism can drive the model to be tested to realize the movement in the X direction, the Y direction, the attack angle and the roll angle direction through the model connecting device. The second parking chamber is arranged on the outer wall of the lower wall plate of the wind tunnel test section, a second temporary storage space is formed between the second parking chamber and the lower wall plate of the wind tunnel test section, and the second degree-of-freedom action mechanism is arranged in the second temporary storage space.
The reference probe is connected with the upper wall plate of the wind tunnel test section through the reference probe fixing device.
In this embodiment, a first open slot is formed in the first wind tunnel test section wall plate, and a second open slot is formed in the second wind tunnel test section wall plate, so as to replace the original solid wall plate of the wind tunnel, and form an airflow channel together with the original left and right side walls. Meanwhile, the parking chamber is positioned outside the inner cavity of the test section and is connected with the wall plate of the test section, the mounting end face is sealed to ensure that no external air flow enters the inner cavity of the test section through the mounting end face during the test, the model is connected with the second degree-of-freedom action mechanism through the model connecting device, and the second degree-of-freedom action mechanism is mounted in the second parking chamber; the measuring probe is connected with the first degree-of-freedom action mechanism through the measuring probe connecting device, and the first degree-of-freedom action mechanism is arranged in the first resident chamber; the reference probe is connected with an upper wall plate of the wind tunnel test section through a reference probe fixing device and is kept still during the test.
The measuring method based on the test device comprises the following steps:
a. before testing, the measuring probe is positioned in the first room, the model to be tested is positioned in the second room, and the first test section turning plate and the second test section turning plate are respectively kept closed;
b. after the supersonic flow field of the temporary impulse type supersonic wind tunnel is established, a first test section turning plate and a second test section turning plate are respectively opened, a measuring probe extends out of a first parking chamber through a first degree-of-freedom action mechanism, and a model to be measured extends out of a second parking chamber through a second degree-of-freedom action mechanism;
c. after the measuring probe respectively runs to the initial test position of the temporary impulse type supersonic wind tunnel test section through the first degree of freedom action mechanism and the model to be measured through the second degree of freedom action mechanism, the first test section turning plate and the second test section turning plate are closed;
d. changing the posture of the model to be tested according to a given test state, and starting a test according to a given test mode;
e. after the test is finished, the first test section turning plate and the second test section turning plate are opened, the measuring probe is retracted into the first parking chamber through the first degree-of-freedom action mechanism, the model to be tested is retracted into the second parking chamber through the second degree-of-freedom action mechanism, and the turning plates are closed;
f. and (5) shutting down the vehicle by using the temporary-flushing type supersonic wind tunnel to finish the test.
The principle of improving the accuracy of the sonic boom measurement test result is based on the following two points: firstly, considering that no matter the size of a model or a measuring probe in a sonic boom measuring test is far smaller than that of a conventional test model, but the requirement on simulation refinement of the shape of the model is far higher than that of the conventional test, and meanwhile, the probe is used as pressure sensitive measuring equipment, and the measured value is also influenced by the change of the shape; on the other hand, the normal shock wave which is inevitably existed in the starting/shutting-down stage of the temporary-impulse type supersonic wind tunnel sweeps through the test section, and the model and the measuring probe are enabled to bear the great impact load and have the risk of deformation. In order to solve the contradiction between the two aspects, the model and the measuring probe are retracted into the parking chamber and enter the air flow after the supersonic flow field is established in the wind tunnel start-up/shut-down stage through the device of the invention, so that the model and the measuring probe are prevented from being deformed due to repeated impact load bearing. Meanwhile, the invention also avoids the damage of the small-range differential pressure sensor caused by measuring the over-range pressure before and after the normal shock wave in the starting/shutting-off stage of the wind tunnel. In addition, aiming at the condition that the sonic boom signal belongs to the weak signal category and the measurement result is obviously influenced by the background pressure distribution, the sonic boom measurement test method and the sonic boom measurement test system realize the sonic boom measurement test by adopting two modes of model movement and measurement probe movement on the premise of ensuring that the overall layout of the test is not changed by utilizing two sets of mutually independent high-precision wide-range long-stroke multi-degree-of-freedom mechanisms, so that the optimal mode is selected under different working conditions, and more reliable test results can be obtained.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (5)
1. A temporary-impulse type supersonic wind tunnel sonic boom measurement test device comprises a first wind tunnel test section wallboard, a second wind tunnel test section wallboard, a measurement probe connecting device, a model connecting device used for being connected with a model to be tested, a reference probe and a reference probe fixing device, wherein the first wind tunnel test section wallboard and the second wind tunnel test section wallboard are arranged oppositely, and a temporary-impulse type supersonic wind tunnel test section is formed between the first wind tunnel test section wallboard and the second wind tunnel test section wallboard;
the device is characterized by also comprising a first parking chamber matched with the first wind tunnel test section wall plate, a second parking chamber matched with the second wind tunnel test section wall plate, a first degree of freedom action mechanism, a second degree of freedom action mechanism, a first test section turning plate and a second test section turning plate;
the first wind tunnel test section wallboard is provided with a first open slot, the first test section turning plate is arranged on the first open slot, and the first test section turning plate can be opened and closed relative to the first open slot; the measuring probe is connected with the first degree-of-freedom action mechanism through the measuring probe connecting device, and the first degree-of-freedom action mechanism can drive the measuring probe to realize the movement in the X direction, the Y direction, the attack angle and the roll angle direction through the measuring probe connecting device; the first parking chamber is arranged on the outer wall of the first wind tunnel test section wallboard, a first temporary storage space is formed between the first parking chamber and the first wind tunnel test section wallboard, the first degree-of-freedom action mechanism is arranged in the first temporary storage space, and the first degree-of-freedom action mechanism can drive the measuring probe to enter the temporary impact type supersonic wind tunnel test section through the first open slot;
a second open slot is formed in the second wind tunnel test section wall plate, the second test section turning plate is arranged on the second open slot, and the second test section turning plate can be opened and closed relative to the second open slot; the two ends of the model connecting device are respectively connected with the model to be tested and the second degree-of-freedom action mechanism, and the second degree-of-freedom action mechanism can drive the model to be tested to realize the movement in the X direction, the Y direction, the attack angle and the roll angle direction through the model connecting device; the second parking chamber is arranged on the outer wall of a second wind tunnel test section wallboard, a second temporary storage space is formed between the second parking chamber and the second wind tunnel test section wallboard, the second degree-of-freedom action mechanism is arranged in the second temporary storage space, and the second degree-of-freedom action mechanism can drive the model to be tested to enter the temporary impact type supersonic wind tunnel test section through a second open slot;
and the reference probe is connected with the temporary-impulse type supersonic wind tunnel test section through a reference probe fixing device.
2. The temporary-impulse type supersonic wind tunnel sonic boom measurement test device according to claim 1, wherein the first wind tunnel test section wall plate is a wind tunnel test section upper wall plate, and the second wind tunnel test section wall plate is a wind tunnel test section lower wall plate.
3. The temporary-impulse type supersonic wind tunnel sonic boom measurement test device according to claim 1, wherein the first wind tunnel test section wall plate is a wind tunnel test section left wall plate, and the second wind tunnel test section wall plate is a wind tunnel test section right wall plate.
4. The transient impulse type supersonic wind tunnel sonic boom measurement test device according to claim 1, wherein a part of the first degree of freedom action mechanism extending into the transient impulse type supersonic wind tunnel test section and a part of the second degree of freedom action mechanism extending into the transient impulse type supersonic wind tunnel test section adopt streamline design.
5. The temporary-impulse supersonic wind tunnel sonic boom measurement test apparatus according to any one of claims 1 ~ 4, wherein the reference probe is connected to the first wind tunnel test section wall plate or the second wind tunnel test section wall plate through a reference probe fixing device, and the position of the reference probe is such that a wave system generated by the reference probe cannot influence the airflow flow near the model.
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| CN110132528A (en) * | 2019-06-27 | 2019-08-16 | 中国空气动力研究与发展中心高速空气动力研究所 | It is a kind of temporarily to rush formula supersonic wind tunnel sonic boom measurement experimental rig and measuring method |
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| CN111380667A (en) * | 2020-05-06 | 2020-07-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Device for reducing scouring damage of hypersonic wind tunnel tail gas to test model sensor |
| CN111380667B (en) * | 2020-05-06 | 2024-05-28 | 中国空气动力研究与发展中心超高速空气动力研究所 | Device for reducing scouring damage of hypersonic wind tunnel tail gas to test model sensor |
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| CN115452313A (en) * | 2022-11-14 | 2022-12-09 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for quickly calibrating angular sensitivity of probe in sonic explosion test |
| CN115452313B (en) * | 2022-11-14 | 2023-03-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for quickly calibrating angular sensitivity of probe in sonic explosion test |
| CN117760681A (en) * | 2024-02-22 | 2024-03-26 | 中国空气动力研究与发展中心高速空气动力研究所 | combined type acoustic explosion test device and method suitable for large supersonic wind tunnel |
| CN117760681B (en) * | 2024-02-22 | 2024-05-31 | 中国空气动力研究与发展中心高速空气动力研究所 | Combined type acoustic explosion test device and method suitable for large supersonic wind tunnel |
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