CN117147093A - Wind tunnel test measuring device for acoustic explosion characteristics of low acoustic explosion supersonic civil aircraft - Google Patents
Wind tunnel test measuring device for acoustic explosion characteristics of low acoustic explosion supersonic civil aircraft Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The invention discloses a measuring device for acoustic explosion characteristics of a low acoustic explosion supersonic civil aircraft, belongs to the technical field of wind tunnel tests, and aims to solve the problem that a small-range pressure scanning valve cannot be directly used for acoustic explosion overpressure test measurement. The pressure measuring device comprises a full-machine model, a supporting system and a pressure measuring rail, wherein the full-machine model is arranged in a wind tunnel test section through the supporting system, the pressure measuring rail is arranged in the wind tunnel test section, a plurality of pressure measuring holes formed in the pressure measuring rail are respectively connected with measuring ends of electronic pressure scanning valves, hole wall pressure measuring holes are formed in the wind tunnel test section, a reference end of each electronic pressure scanning valve, the hole wall pressure measuring holes and a pressure insulating sensor are communicated through a tee joint, and pressure signals generated by the full-machine model fall in the range where the plurality of pressure measuring holes are located during test. According to the invention, the reference end of the electronic pressure scanning valve is communicated with the hole wall pressure measuring hole, so that the effect of obviously reducing the pressure difference between the measuring end of the electronic pressure scanning valve and the reference end is achieved, and the electronic pressure scanning valve of the small-range sensor is used for measuring the pressure of the acoustic explosion near-field space.
Description
Technical Field
The invention belongs to the technical field of wind tunnel tests, and particularly relates to a low-acoustic-explosion supersonic civil aircraft acoustic-explosion characteristic wind tunnel test measuring device.
Background
The problem of acoustic explosion caused by an aircraft in supersonic flight is always a key technical obstacle which plagues the development of supersonic civil aircraft. When the supersonic civil aircraft flies at cruising, incoming flow is compressed at the front edge of the aircraft head and the wing to generate shock waves, the static pressure of air flow is increased by the shock waves to be higher than the initial incoming flow static pressure, then the air flow is expanded at the aircraft body and the wing to generate expansion waves, and the static pressure of the air flow is reduced by the expansion waves to be lower than the initial incoming flow static pressure. The air flow generates shock waves at the tail of the aircraft, so that the aircraft detours and static pressure rises through the shock wave action, and finally, the pressure of the air around the supersonic aircraft is recovered to the pressure of the incoming flow in the far front, and the shock waves and the expansion wave cause the air pressure around the supersonic aircraft to generate severe fluctuation relative to the pressure of the flying environment, which is called near-field acoustic explosion overpressure, and the pressure wave formed by the near-field acoustic explosion overpressure forms huge explosion sound after nonlinear propagation to the ground in the air, namely acoustic explosion which is generally called as acoustic explosion of people. Acoustic explosions are extremely noisy and can seriously affect people's life and work, and even potentially damage ground buildings. Therefore, to develop a new generation of supersonic civil aircraft, the reduction of acoustic explosion is one of the key technologies that first needs to be broken through.
The sonic boom research is generally divided into a near field and a far field, the boundaries of which are not strictly defined, the near field generally referring to a range of radius from a distance several times the length of the aircraft, and the far field generally referring to a range of radius from a distance several tens of times the length of the aircraft to a distance to the ground. Wind tunnel test is an important means for developing acoustic explosion research, is limited by the size of the existing supersonic wind tunnel, and the current acoustic explosion wind tunnel test technology is mainly developed aiming at the near field range. The core of the acoustic explosion wind tunnel test technology is that pressure distribution measurement is carried out in a supersonic wind tunnel aiming at near-field space of an aircraft model, the difference value between near-field pressure data around the model and free inflow environmental pressure represents near-field acoustic explosion overpressure of the aircraft, the near-field acoustic explosion overpressure data are taken as input, and the acoustic explosion overpressure of the far field of the aircraft can be calculated by constructing a corresponding mathematical model.
For a supersonic civil aircraft to develop a near-field acoustic explosion overpressure measurement test in a wind tunnel, a low-acoustic explosion supersonic civil aircraft near-field acoustic explosion overpressure signal is weak, a small-range differential pressure type pressure scanning valve below 5PSID is required to be adopted for measurement, in a traditional acoustic explosion overpressure measurement test, a reference end of the pressure scanning valve is directly communicated with the atmosphere, for example, chinese patent publication No. CN110672295A discloses a jet model acoustic explosion characteristic wind tunnel test device, the atmospheric pressure is taken as reference pressure, the atmospheric pressure is usually measured by an atmospheric pressure gauge, in a supersonic wind tunnel operation environment, the pressure scanning valve measuring end is communicated with the inside of the wind tunnel, the pressure is extremely low, the pressure difference between the pressure scanning valve measuring end and the reference end (which is the atmospheric pressure) is large, and for a small-range scanning valve sensor below 5PSID required to be adopted for the acoustic explosion test, the risk of overranging damage exists, so that the traditional pressure measurement method cannot be directly used. Therefore, development of a novel low-acoustic-explosion supersonic civil aircraft acoustic-explosion characteristic wind tunnel test measuring device is urgently needed.
Disclosure of Invention
The invention aims to provide a low-sonic-explosion supersonic civil aircraft sonic-explosion characteristic wind tunnel test measuring device, which aims to solve the problem that a small-range pressure scanning valve below 5PSID cannot be directly used for sonic-explosion overpressure test measurement. The technical scheme adopted by the invention is as follows:
the utility model provides a low acoustic explosion supersonic speed civil aircraft acoustic explosion characteristic wind tunnel test measuring device, includes full-aircraft model, braced system and pressure measurement rail, and full-aircraft model passes through braced system sets up in the wind tunnel test section, is equipped with the pressure measurement rail on the lower wallboard of wind tunnel test section, has seted up a plurality of interval arrangement's pressure measurement holes along the air current flow direction on the up end of pressure measurement rail, and a plurality of pressure measurement holes all are connected with the measuring end of electronic pressure scanning valve through the air pipe way, have seted up the wall pressure measurement hole on the lower wallboard of wind tunnel test section, and the reference end of electronic pressure scanning valve, wall pressure measurement hole and absolute pressure sensor pass through tee bend intercommunication, and during the test, the pressure signal that full-aircraft model produced falls in the within range that a plurality of pressure measurement holes were located.
Further, the support system comprises a wind tunnel support, a back support strut, a rod type balance and a switching strut, wherein two ends of the wind tunnel support are respectively connected with an upper wall plate and a lower wall plate of the wind tunnel test section, the whole machine model, the back support strut, a balance adapter, a rod type balance, the switching strut and an axial moving mechanism are sequentially connected along the airflow direction, and the axial moving mechanism is fixed on the wind tunnel support;
angle of attack variation for full machine modelSide slip angle variation->And roll angle variation +.>Determined by the following formula:
；
；
；
wherein:
x is axial force, and the unit is N; y is normal force, and the unit is N; z is a lateral force in N;the pitch moment is N.m; />The yaw moment is N.m; />The unit is N.m for rolling moment; a is an attack angle-axial force calibration coefficient, and the unit is DEG/N; b is an attack angle-normal force calibration coefficient, and the unit is DEG/N; c is an attack angle-pitching moment calibration coefficient, and the unit is the angle of attack-pitching moment calibration coefficient (N.m); d is a sideslip angle-lateral force calibration coefficient, and the unit is DEG/N; e is the yaw angle-yaw moment calibration coefficient in units of °/(N.m); f is a roll angle-lateral force calibration coefficient in units of DEG/N; g is the roll angle-roll torque calibration coefficient in units of °/(N.m); h is a roll angle-yaw moment calibration coefficient in units of °/(N.m);
X、Y、Z、、/>and->All measured by a bar balance.
Furthermore, both ends of the wind tunnel support along the airflow direction are in wedge structures.
Further, the wind tunnel support is vertically arranged, the axial moving mechanism is fixed in the center of the wind tunnel support, and the wind tunnel support is arranged in the transverse center of the wind tunnel test section.
Further, the axial moving mechanism comprises a transmission nut, a driving gear, a motor, a driven gear and a support, wherein the driving gear is sleeved on an output shaft of the motor, the transmission nut is rotatably arranged on the support, the driven gear is in sleeve joint with the transmission nut and is meshed with the driven gear, a transfer support rod is in threaded fit with the transmission nut, one end of the transfer support rod, which is connected with the transmission nut, is provided with a sliding groove, a sliding block is connected with the support, the sliding groove is in sliding fit with the sliding block, and the support is fixed on the wind tunnel support.
Further, both ends of the pressure measuring rail along the airflow direction are in wedge structures.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the invention, the Reference End (REF) of the electronic pressure scanning valve is communicated with the hole wall pressure measuring hole, so that the effect of obviously reducing the pressure difference between the measurement end and the reference end of the electronic pressure scanning valve is achieved, the electronic pressure scanning valve with the measuring range of a sensor below 5PSID can be used under the operation condition of a supersonic wind tunnel by means of the unique design combination mode, the accurate measurement of the acoustic explosion near-field space pressure signal of the whole machine model is realized, the problem of the over-range damage of the small-range electronic pressure scanning valve is solved, and the reference end of the electronic pressure scanning valve, the hole wall pressure measuring hole and the absolute pressure sensor are communicated through a tee joint, so that the problem of the real-time measurement of the reference pressure of the electronic pressure scanning valve can be solved.
2. The support system adopts the integrated support rod with the built-in rod balance, so that aerodynamic force of the whole machine model in the test process can be measured while the whole machine model is supported, and the attitude angle change of the whole machine model is calculated through the measured aerodynamic force, so that the problem that the attitude angle of the test model under the aerodynamic force in the traditional acoustic explosion test can not be measured is solved.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is an enlarged view at A of FIG. 1;
fig. 3 is a schematic illustration of the cooperation of the axial displacement mechanism and the adapter strut.
In the figure, the wind tunnel test section 1, the full machine model 2, the back support rod 3, the balance adapter 4, the rod balance 5, the pressure signal 6, the switching support rod 7, the axial moving mechanism 8, the motor 81, the driving gear 82, the driven gear 83, the transmission nut 84, the sliding block 85, the supporting seat 86, the absolute pressure sensor 9, the tee joint 10, the hole wall pressure measuring hole 11, the gas pipeline 12, the pressure measuring rail 13, the pressure measuring hole 14 and the electronic pressure scanning valve 15.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the present invention is described below by means of specific embodiments shown in the accompanying drawings. It should be understood that the description is only illustrative and is not intended to limit the scope of the invention. In addition, in the following description, descriptions of well-known structures and techniques are omitted so as not to unnecessarily obscure the present invention.
The connection mentioned in the invention is divided into fixed connection and detachable connection, wherein the fixed connection is a conventional fixed connection mode such as folding connection, rivet connection, bonding connection, welding connection and the like, the detachable connection comprises a conventional detachable mode such as bolt connection, buckle connection, pin connection, hinge connection and the like, and when a specific connection mode is not limited, at least one connection mode can be found in the conventional connection mode by default to realize the function, and the person skilled in the art can select the function according to the needs. For example: the fixed connection is welded connection, and the detachable connection is bolted connection.
The present invention will be described in further detail below with reference to the accompanying drawings, the following examples being illustrative of the present invention and the present invention is not limited to the following examples.
Examples: as shown in figures 1-3, the low-sonic-explosion supersonic civil aircraft sonic-explosion characteristic wind tunnel test measurement device comprises a full-machine model 2, a support system and a pressure measuring rail 13, wherein the full-machine model 2 is arranged in a wind tunnel test section 1 through the support system, the full-machine model 2 is arranged against the airflow direction, the pressure measuring rail 13 is arranged on the lower wall plate of the wind tunnel test section 1, a plurality of pressure measuring holes 14 which are arranged at intervals are arranged on the upper end surface of the pressure measuring rail 13 along the airflow direction, a plurality of pressure measuring holes 14 are connected with the measurement end of an electronic pressure scanning valve 15 through an air pipeline 12, a hole wall pressure measuring hole 11 is arranged on the lower wall plate of the wind tunnel test section 1, the reference end of the electronic pressure scanning valve 15, the hole wall pressure measuring hole 11 and a pressure insulating sensor 9 are communicated through a tee joint 10, and a pressure signal 6 generated by the full-machine model 2 falls in the range of the plurality of pressure measuring holes 14 during test.
Near field acoustic explosion overpressureDetermined by the following formula:
；
wherein:
the unit is Pa for measuring the end pressure of the electronic pressure scanning valve 15;
the unit is Pa for the free inflow ambient pressure of the supersonic wind tunnel.
Measuring end pressure of electronic pressure scanning valve 15Determined by the following formula:
；
wherein:
the unit is Pa, and the pressure difference between the measuring end and the reference end of the electronic pressure scanning valve 15 can be obtained by directly measuring a sensor of the electronic pressure scanning valve 15;
the reference end pressure of the electronic pressure scanning valve 15 is measured by an absolute pressure sensor 9, and the unit is Pa.
Free inflow ambient pressure of supersonic wind tunnelDetermined by the following formula:
；
wherein:
the total pressure of the wind tunnel is Pa, and can be directly measured by a pressure sensor arranged on a stable section of the wind tunnel;
the Mach number of the free incoming flow is obtained through calibration in advance;
for the gas specific heat ratio, 1.4 is usually taken for normal temperature air.
Since the pressure measuring rail 13 is large in size, the interference to the flow field is not negligible, so that the interference to the pressure measuring rail 13 needs to be corrected, and the calculation formula is as follows:
；
wherein:
the dimensionless near-field acoustic explosion overpressure after the interference of the pressure measuring rail 13 is corrected;
the non-dimensional near-field acoustic explosion overpressure including the interference of the pressure measuring rail 13;
errors caused by disturbances in the load rail 13.
According to the invention, the Reference End (REF) of the electronic pressure scanning valve 15 is communicated with the hole wall pressure measuring hole 11, so that the effect of obviously reducing the pressure difference between the measuring end (the internal pressure of the wind tunnel) and the reference end (the internal pressure of the wind tunnel) of the electronic pressure scanning valve 15 is achieved, through the combination mode of the unique design, the electronic pressure scanning valve 15 of a sensor with the measuring range below 5PSID can be used under the supersonic wind tunnel operation condition, the accurate measurement of the acoustic explosion near-field space pressure signal 6 of the whole machine model 2 is realized, the problem of the over-measuring damage of the small-range electronic pressure scanning valve 15 is solved, and the real-time measurement problem of the reference pressure of the electronic pressure scanning valve 15 can be solved by communicating the reference end of the electronic pressure scanning valve 15, the hole wall pressure measuring hole 11 and the absolute pressure sensor 9 through the tee joint 10.
The support system comprises a wind tunnel support, a back support strut 3, a rod balance 5 and an adapter strut 7, wherein two ends of the wind tunnel support are respectively connected with a left wall plate and a right wall plate of the wind tunnel test section 1, the whole machine model 2, the back support strut 3, the balance adapter 4, the rod balance 5, the adapter strut 7 and the axial moving mechanism 8 are sequentially connected along the airflow direction, and the axial moving mechanism 8 is fixed on the wind tunnel support to realize the support of the whole machine model 2 and the measurement of aerodynamic force;
angle of attack variation for full machine model 2Side slip angle variation->And roll angle variation +.>Determined by the following formula:
；
；
；
wherein:
x is axial force, and the unit is N; y is normal force, and the unit is N; z is a lateral force in N;the pitch moment is N.m; />The yaw moment is N.m; />The unit is N.m for rolling moment; a is an attack angle-axial force calibration coefficient, and the unit is DEG/N; b is an attack angle-normal force calibration coefficient, and the unit is DEG/N; c is an attack angle-pitching moment calibration coefficient, and the unit is the angle of attack-pitching moment calibration coefficient (N.m); d is a sideslip angle-lateral force calibration coefficient, and the unit is DEG/N; e is the yaw angle-yaw moment calibration coefficient in units of °/(N.m); f is a roll angle-lateral force calibration coefficient in units of DEG/N; g is the roll angle-roll torque calibration coefficient in units of °/(N.m); h is a roll angle-yaw moment calibration coefficient in units of °/(N.m);
X、Y、Z、、/>and->All measured by a bar balance 5.
In the traditional acoustic explosion overpressure measurement test, the near-field acoustic explosion overpressure of the test model is closely related to the model attitude angle, and the initial attitude angle of the model can be changed due to aerodynamic action of the test model in the wind tunnel test, so that the traditional acoustic explosion test cannot measure the change of the model attitude angle.
The support system of the invention adopts the integrated support rod with the built-in rod balance 5, can measure the aerodynamic force of the whole machine model 2 in the test process while supporting the whole machine model 2, calculates the attitude angle change of the whole machine model 2 through the aerodynamic force obtained by measurement, and solves the problem that the attitude angle of the test model under the aerodynamic force in the traditional acoustic explosion test can not be measured.
The wind tunnel support is in a wedge structure along two ends of the airflow direction.
The wind tunnel support is vertically arranged, the axial moving mechanism 8 is fixed in the center of the wind tunnel support, and the wind tunnel support is arranged in the transverse center of the wind tunnel test section 1.
The axial moving mechanism 8 comprises a transmission nut 84, a driving gear 82, a motor 81, a driven gear 83 and a support 86, wherein the driving gear 82 is sleeved on an output shaft of the motor 81, the transmission nut 84 is rotatably arranged on the support 86, the driven gear 83 is sleeved with the transmission nut 84, the driving gear 82 is meshed with the driven gear 83, the transfer support rod 7 is in threaded fit with the transmission nut 84, a sliding groove is formed in one end, connected with the transmission nut 84, of the transfer support rod 7, a sliding block 85 is connected with the support 86, the sliding groove is in sliding fit with the sliding block 85, and the support 86 is fixed on the wind tunnel support.
Both ends of the pressure measuring rail 13 along the airflow direction are in wedge structures.
The above embodiments are only illustrative of the present invention and do not limit the scope thereof, and those skilled in the art may also make modifications to parts thereof without departing from the spirit of the invention.
Claims (6)
1. The utility model provides a low sound explosion supersonic speed civil aircraft sound explosion characteristic wind tunnel test measuring device which characterized in that: including all-computer model (2), braced system and pressure measurement rail (13), all-computer model (2) pass through braced system sets up in wind tunnel test section (1), be equipped with pressure measurement rail (13) on the lower wallboard of wind tunnel test section (1), a plurality of interval arrangement's pressure measurement holes (14) have been seted up along the air current flow direction on the up end of pressure measurement rail (13), a plurality of pressure measurement holes (14) all are connected with the measuring end of electron pressure scanning valve (15) through air pipe (12), hole wall pressure measurement hole (11) have been seted up on the lower wallboard of wind tunnel test section (1), the reference end of electron pressure scanning valve (15), hole wall pressure measurement hole (11) and absolute pressure sensor (9) are through tee bend (10) intercommunication, during the test, pressure signal (6) that all-computer model (2) produced fall in the within the scope that a plurality of pressure measurement holes (14) are located.
2. The low-sonic boom ultrasonic civil aircraft sonic boom characteristic wind tunnel test measurement device according to claim 1, wherein the device is characterized in that: the support system comprises a wind tunnel support, a back support supporting rod (3), a rod balance (5) and a switching supporting rod (7), wherein two ends of the wind tunnel support are respectively connected with an upper wall plate and a lower wall plate of a wind tunnel test section (1), the full-machine model (2), the back support supporting rod (3), a balance adapter (4), the rod balance (5), the switching supporting rod (7) and an axial moving mechanism (8) are sequentially connected along the airflow direction, and the axial moving mechanism (8) is fixed on the wind tunnel support;
angle of attack variation of full machine model (2)Side slip angle variation->And roll angle variation +.>Determined by the following formula:
；
；
；
wherein:
x is axial force, and the unit is N; y is normal force, and the unit is N; z is a lateral force in N;the pitch moment is N.m; />The yaw moment is N.m; />The unit is N.m for rolling moment; a is an attack angle-axial force calibration coefficient, and the unit is DEG/N; b is the angle of attack-normal force calibration systemNumber in units of DEG/N; c is an attack angle-pitching moment calibration coefficient, and the unit is the angle of attack-pitching moment calibration coefficient (N.m); d is a sideslip angle-lateral force calibration coefficient, and the unit is DEG/N; e is the yaw angle-yaw moment calibration coefficient in units of °/(N.m); f is a roll angle-lateral force calibration coefficient in units of DEG/N; g is the roll angle-roll torque calibration coefficient in units of °/(N.m); h is a roll angle-yaw moment calibration coefficient in units of °/(N.m);
X、Y、Z、、/>and->All measured by a bar balance (5).
3. The low-sonic boom ultrasonic civil aircraft sonic boom characteristic wind tunnel test measurement device according to claim 2, wherein the device is characterized in that: the wind tunnel support is in a wedge structure along two ends of the airflow direction.
4. The low-sonic boom ultrasonic civil aircraft sonic boom characteristic wind tunnel test measurement device according to claim 3, wherein the device is characterized in that: the wind tunnel support is vertically arranged, the axial moving mechanism (8) is fixed in the center of the wind tunnel support, and the wind tunnel support is arranged in the transverse center of the wind tunnel test section (1).
5. The low-sonic boom ultrasonic civil aircraft sonic boom characteristic wind tunnel test measurement device according to claim 2, wherein the device is characterized in that: the axial moving mechanism (8) comprises a transmission nut (84), a driving gear (82), a motor (81), a driven gear (83) and a support (86), wherein the driving gear (82) is sleeved on an output shaft of the motor (81), the transmission nut (84) is rotationally arranged on the support (86), the driven gear (83) is sleeved with the transmission nut (84), the driving gear (82) is meshed with the driven gear (83), a transfer support rod (7) is in threaded fit with the transmission nut (84), a sliding groove is formed in one end, connected with the transmission nut (84), of the transfer support rod (7), a sliding block (85) is connected with the support (86), the sliding groove is in sliding fit with the sliding block (85), and the support (86) is fixed on the wind tunnel support.
6. The low-sonic boom ultrasonic civil aircraft sonic boom characteristic wind tunnel test measurement device according to any one of claims 1 to 5, wherein: both ends of the pressure measuring rail (13) along the airflow direction are in wedge structures.
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| CN202311412802.9A CN117147093B (en) | 2023-10-30 | 2023-10-30 | Wind tunnel test measuring device for acoustic explosion characteristics of low acoustic explosion supersonic civil aircraft |
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| CN202311412802.9A CN117147093B (en) | 2023-10-30 | 2023-10-30 | Wind tunnel test measuring device for acoustic explosion characteristics of low acoustic explosion supersonic civil aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117147090A (en) * | 2023-10-30 | 2023-12-01 | 中国空气动力研究与发展中心高速空气动力研究所 | Device and method for adjusting position and posture of pressure measuring rail in acoustic 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 |
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| CN117147090A (en) * | 2023-10-30 | 2023-12-01 | 中国空气动力研究与发展中心高速空气动力研究所 | Device and method for adjusting position and posture of pressure measuring rail in acoustic explosion test |
| CN117147090B (en) * | 2023-10-30 | 2024-01-02 | 中国空气动力研究与发展中心高速空气动力研究所 | Device and method for adjusting position and posture of pressure measuring rail in acoustic 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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