CN111856072A - Air flow speed calculation method, system and equipment and storage medium - Google Patents
Air flow speed calculation method, system and equipment and storage medium Download PDFInfo
- Publication number
- CN111856072A CN111856072A CN202010747052.0A CN202010747052A CN111856072A CN 111856072 A CN111856072 A CN 111856072A CN 202010747052 A CN202010747052 A CN 202010747052A CN 111856072 A CN111856072 A CN 111856072A
- Authority
- CN
- China
- Prior art keywords
- pressure
- air flow
- measuring device
- coefficient
- relation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P5/00—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft
- G01P5/14—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid
- G01P5/16—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes, e.g. Machmeter
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P13/00—Indicating or recording presence, absence, or direction, of movement
- G01P13/02—Indicating direction only, e.g. by weather vane
- G01P13/025—Indicating direction only, e.g. by weather vane indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Indicating Or Recording The Presence, Absence, Or Direction Of Movement (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to the field of meteorological measurement, in particular to an airflow speed calculation method, an airflow speed calculation system, airflow speed calculation equipment and a storage medium. The method comprises the steps of firstly establishing a first-third relation among a yaw angle coefficient, a total pressure coefficient and a static pressure coefficient, a pressure measuring hole measuring value of a first pressure measuring device, a total pressure value and a static pressure value of a flow field, measuring the total pressure value and the static pressure value of current airflow at the same time when the first pressure measuring device is calibrated in the early stage, introducing the measured values into calibration calculation of the first pressure measuring device, and establishing a functional relation among the yaw angle coefficient, the total pressure coefficient and the static pressure coefficient and each pressure measuring value to be more practical; in practical measurement application, according to the first-third relational expression and each three-dimensional relational surface graph obtained by calibration, the size and the direction of the air flow speed of the measured flow field can be calculated through the measurement value of the first pressure measuring device, in the calculation process, a speed verification and iteration method is introduced, and the measurement error is ensured to be in a small range through iteration calculation.
Description
Technical Field
The invention relates to the field of meteorological measurement, in particular to an airflow speed calculation method, an airflow speed calculation system, airflow speed calculation equipment and a storage medium.
Background
The multi-hole pressure measuring device, such as a three-hole probe, a five-hole probe and other various kinds of anisotropic multi-hole pressure measuring devices, is provided with pressure measuring holes at different positions. During measurement, the pressure measured by each pressure measuring hole is different, and the size and the direction of the air flow speed of the measured flow field can be calculated by analyzing and processing the measured pressure value.
Taking the five-hole pressure measuring device (also called a five-hole probe, the pressure measuring hole of which comprises a central Q1 and four sides Q2-Q5) shown in fig. 1 and fig. 2 as an example, the existing calibration and calculation methods are mostly calibrated in a wind tunnel, and the relational expressions (5), (6) and (7) among the yaw angle coefficient K α, the pitch angle coefficient K β and the velocity coefficient Kv and the measured pressures Q1, Q2, Q3, Q4 and Q5 of each opening are established under a single wind speed, so that calibration curves (fig. 3 and fig. 4) of K α and K β and the calibration coefficient Kv of the airflow velocity v are further obtained. Therefore, in actual measurement, the air flow speed and the air flow speed of the measured flow field are calculated according to the measured pressure of each pressure measuring hole and by contrasting with the calibration curve.
And rho is the density of the fluid where the five-hole pressure measuring device is located.
When the method is used for calculating the airflow direction, the relationship between Ka and Kbeta and the pressure measuring holes needs to be assumed to be approximately unchanged under different wind speeds, and the same calibration curve can be used for calculation; in calculating the gas flow velocity, it is assumed that the total pressure hole measurement (Q5) is always the total pressure of the measured flow field in different gas flow directions. However, in practice, the relationship between K α, K β and the pressure taps varies with the air flow velocity, with different calibration curves corresponding to different velocities. In addition, when the air flow direction has an offset angle and is no longer opposite to the total pressure hole of the measuring device, the measured value of the total pressure hole is deviated from the total pressure value of the measured flow field. Therefore, the calibration and calculation method has certain errors in practical application, and the errors are larger when the deflection angle (yaw and pitch) of the airflow is larger.
Disclosure of Invention
The invention provides a method, a system and a device for calculating air velocity and a storage medium, which solve the technical problems that: in the existing method, the air flow speed and direction of a measured flow field are calculated by measuring pressure according to each pressure measuring hole and contrasting with calibration curves of a yaw angle coefficient K alpha and a pitch angle coefficient K beta, and when an air flow deflection angle (yaw and pitch) is larger, the error is larger.
The basic scheme provided by the invention is as follows:
an airflow velocity calculation method comprising the steps of:
s1, introducing a total pressure value and a static pressure value of a flow field, and respectively establishing a first-third relation among a yaw angle coefficient, the total pressure coefficient and the static pressure coefficient, a pressure measuring hole measuring value of a first pressure measuring device, and the total pressure value and the static pressure value of the flow field;
s2, measuring the total pressure value and the static pressure value of the flow field by using a second pressure measuring device according to the first-third relation, calibrating the first pressure measuring device under different air flow speed sizes and different air flow directions, and establishing a first three-dimensional relation curved surface among a yaw angle coefficient, the air flow speed sizes and the air flow directions, a first three-dimensional relation curved surface among the total pressure coefficient, the air flow speed sizes and the air flow directions, and a first three-dimensional relation curved surface among the static pressure coefficient, the air flow speed sizes and the air flow directions;
and S3, obtaining the size and the direction of the air flow speed corresponding to a specific pressure measuring hole measurement group value through iterative calculation according to the first relation, the third relation and the first-third three-dimensional relation curved surface.
The calculation principle of the basic scheme is as follows:
firstly, introducing a total pressure value and a static pressure value of a flow field, and establishing a functional relation (a first relation and a third relation) among a yaw angle coefficient, the total pressure coefficient and the static pressure coefficient, each pressure measurement value of a first pressure measurement device, and the total pressure value and the static pressure value of the flow field;
then, calibrating the first pressure measuring device under the given different air flow speed sizes and directions, and calibrating the first pressure measuring device according to the established function relation, wherein the total pressure value and the static pressure value of the flow field are measured by using the second pressure measuring device, and a first-third three-dimensional relation curved surface of three coefficients of a yaw angle coefficient, the total pressure coefficient and the static pressure coefficient, the air flow speed sizes and the air flow directions is established;
and finally, placing the first pressure measuring device in the flow field to be calculated, outputting a specific pressure measuring hole measurement group value of the current airflow by the first pressure measuring device, and calculating the size and the direction of the airflow speed corresponding to the specific pressure measuring hole measurement group value according to the first relation, the third relation and the first three-dimensional relation curved surface.
The beneficial effect of this basic scheme lies in:
1. establishing a first-third relation among a yaw angle coefficient, a total pressure coefficient and a static pressure coefficient, a pressure measuring hole measuring value of a first pressure measuring device, a total pressure value and a static pressure value of a flow field, calibrating the first pressure measuring device in the early stage, simultaneously measuring the total pressure value and the static pressure value of the current airflow through another auxiliary pressure measuring device (a second pressure measuring device), introducing the measuring values into calibration calculation of the first pressure measuring device, and establishing the relation, namely the functional relation among the yaw angle coefficient, the total pressure coefficient and the static pressure coefficient and each pressure measuring value, which is more practical;
2. in practical measurement application, the size and the direction of the airflow speed of the measured flow field can be calculated through the measurement value of the first pressure measuring device according to the first relational expression-the third relational expression obtained through calibration and the three-dimensional relational surface maps of the yaw angle coefficient, the total pressure coefficient, the static pressure coefficient and the size and the direction of the airflow speed. In the calculation process, a speed verification and iteration method is introduced, and through iterative calculation, the influence of air flow deflection angles (yaw and pitch) is avoided, so that the measurement error is ensured to be in a small range, and the measurement precision of the pressure measuring device is improved.
In further embodiments:
in the step S1, the first pressure measuring device is of an airfoil structure, and is provided with three pressure measuring holes, including a total pressure hole, a first static pressure hole and a second static pressure hole; if the upper and lower wing profiles of the first pressure measuring device are taken as the top surface and the bottom surface, the total pressure hole is formed in the arc top end of the arc side surface, and the first static pressure hole and the second static pressure hole are formed in the arc side surfaces on the two sides of the arc top end in an equal mode.
The beneficial effect of this scheme lies in:
compare traditional three holes, five hole needle type pressure measuring device, this scheme adopts the airfoil structure of three holes for the first time, on the circular arc top of circular arc side, set up respectively on the circular arc side of equal both sides and press the hole altogether, first static pressure hole and second static pressure hole, because the test is obtained, the sensitivity of circular arc top to the air current declination is highest, the static pressure hole of cooperation both sides, be convenient for mark, establish the yaw angle coefficient, press the pressure coefficient altogether, the functional relation formula of static pressure coefficient and each pressure measurement value, be used for the later stage to calculate, the functional relation formula that obtains is also more accurate than traditional pressure measuring device.
In a further embodiment, in said step S1,
the first relational expression is specifically as follows:
the second relational expression is specifically as follows:
the third relational expression is specifically as follows:
k alpha, Kpt and Kps respectively represent a yaw angle coefficient, a total pressure coefficient and a static pressure coefficient; p2, P1 and P3 respectively represent the pressure values measured by the total pressure hole, the first static pressure hole and the second static pressure hole,
ptotal and Pstic are respectively a total pressure value and a static pressure value measured by the second pressure measuring device.
The scheme is as follows:
under a specific air flow speed and direction, measuring and obtaining corresponding P1, P2, P3, Ptotal and Pstic, establishing specific contents of a first relation and a third relation, determining indirect expressions of a yaw angle coefficient, a total pressure coefficient and a static pressure coefficient as well as the air flow speed and direction, and facilitating later-stage calculation.
In a further embodiment, the step S2 specifically includes:
s21, measuring the total pressure value and the static pressure value of the flow field by using a second pressure measuring device according to the first-third relation formula, calibrating the first pressure measuring device under different air flow speed sizes and different air flow directions respectively to obtain a first relation curve cluster and a second relation curve cluster of a yaw angle coefficient K alpha corresponding to the air flow speed size v and the air flow direction alpha, a third relation curve cluster and a fourth relation curve cluster of a total pressure coefficient Kpt corresponding to the air flow speed size v and the air flow direction alpha, a fifth relation curve cluster and a sixth relation curve cluster of a static pressure coefficient Kps corresponding to the air flow speed size v and the air flow direction alpha;
s22, establishing a first three-dimensional relation curved surface of a yaw angle coefficient K alpha, an airflow speed v and an airflow direction alpha according to the first relation curve cluster and the second relation curve cluster, establishing a second three-dimensional relation curved surface of a total pressure coefficient Kpt, an airflow speed v and an airflow direction alpha according to the third relation curve cluster and the fourth relation curve cluster, and establishing a third three-dimensional relation curved surface of a static pressure coefficient Kps, an airflow speed v and an airflow direction alpha according to the fifth relation curve cluster and the sixth relation curve cluster.
The scheme is as follows:
the method comprises the steps of giving different air flow speed sizes and directions, outputting corresponding measured values by a first pressure measuring device and a second pressure measuring device, calculating corresponding yaw angle coefficients K alpha, total pressure coefficients Kpt and static pressure coefficients Kps according to a first-third relation, drawing curve clusters of the coefficients and the air flow speed sizes v and the air flow directions alpha through an interpolation approximation method, synthesizing three-dimensional curved surfaces of the coefficients and the speed sizes and the air flow directions according to the curve clusters, determining direct expressions of the yaw angle coefficients K alpha, the total pressure coefficients Kpt and the static pressure coefficients Kps and the air flow speed sizes v and the air flow directions alpha, calculating the yaw angle coefficients, the total pressure coefficients or the static pressure coefficients through the first-third relation, and solving the corresponding air flow speed sizes and the air flow directions through the known yaw angle coefficients, the known total pressure coefficients or the known static pressure coefficients.
In a further embodiment, the step S3 specifically includes: the step S3 specifically includes:
s31, obtaining specific pressure measuring hole measurement group values p1, p2 and p3 of the first pressure measuring device, wherein the p2, the p1 and the p3 are respectively measured by the total pressure hole, the first static pressure hole and the second static pressure hole;
s32, substituting p1, p2 and p3 into the first relational expression to obtain a corresponding yaw angle coefficient K alpha 1;
s33, defining the initial air flow velocity v0；
S34. based on K alpha 1 and v0Obtaining the corresponding airflow direction alpha according to the first three-dimensional relation curved surface1；
S35. based on v0、α1Obtaining a corresponding total pressure coefficient Kpt1 according to the second three-dimensional relation curved surface, and obtaining a corresponding static pressure coefficient Kps1 according to the third three-dimensional relation curved surface;
s36, based on Kpt1, p1, p2 and p3, obtaining the corresponding total pressure value Ptotal according to the second relation1(ii) a Based on Kps1 and p1, p2 and p3, obtaining the corresponding static pressure value Pstic according to the third relation1；
S37. based on Ptotal1、Pstatic1Obtaining the corresponding air velocity v according to the relational expression of the velocity, the total pressure and the static pressure1；
S38, judging e1＝v1-v0If it is less than the set error value, if it is, the matched v1、α1The sizes and the directions of the airflow speeds corresponding to p1, p2 and p 3.
The scheme is as follows:
1. obtaining a corresponding yaw angle coefficient according to the first relational expression and a group of air pressure measurement values actually measured by the first pressure measuring device, further giving an initial air flow speed (estimated or measured by other devices), substituting the initial air flow speed into the first three-dimensional relational curved surface to obtain an air flow direction of the initial air flow speed (steps S31-S34), and obtaining the size and the direction of a group of air flow speeds at first so as to facilitate later-stage iterative computation;
2. however, the initial air flow velocity is only a predicted value, is not accurate and cannot represent the actual air flow velocity, and the solved direction cannot represent the actual direction, so the scheme further solves the corresponding total pressure coefficient and static pressure coefficient based on the second three-dimensional relation curved surface and the third three-dimensional relation curved surface, reversely solves the corresponding total pressure value and static pressure value (not actually measured by the second pressure measuring device) according to the total pressure coefficient and static pressure coefficient, and then deduces the air flow velocity under the total pressure value and the static pressure value according to the relation of the velocity, the total pressure and the static pressure, so as to facilitate iterative calculation;
3. therefore, the difference between the airflow speed calculated in the step S34 and the airflow speed calculated in the step S37 can be reduced to be within a preset range through one-step iteration, the airflow speed and the airflow speed are finally determined, and the airflow speed can be closer to reality and have smaller errors.
In a further embodiment, in said step S38, if e1＝v1-v0V is greater than or equal to the set error value1In place of v0Re-executing steps S34-S38 until the determined ei＝vi-vi-1If the error value is less than the set error value, the V is satisfiedi、αiThe sizes and the directions of the airflow speeds corresponding to p1, p2 and p 3.
The scheme is as follows: the error condition of the obtained air speed and direction can be controlled by adjusting the set error value. The ideal error value is zero, but considering that the smaller the set error value is, the more the iteration times is, the larger the workload is, and a certain error tolerance range in actual work is generally set below ± 0.1 m/s.
In further embodiments, the velocity is related to total pressure and static pressure by:
and rho is the density of the fluid where the first pressure measuring device is located.
The scheme is as follows: specific contents of velocity-total pressure and static pressure relations are determined, wherein Ptotal and pstic are a total pressure value and a static pressure value measured by the second pressure measuring device respectively, and ρ is the fluid density at the moment (the first pressure measuring device or the second pressure measuring device can be equipped with a measuring instrument for measuring the fluid density). The relation between the speed and the total pressure and the static pressure can represent the relation between the wind speed and the total pressure, the static pressure and the fluid density, so that the relation can be represented by the known Ptotal in the step S371、Pstatic1Obtaining the corresponding air velocity v1And subsequent iterative computation is facilitated.
The invention also provides an air flow speed calculation system, which comprises a first pressure measuring device, a second pressure measuring device, an air flow control device and an operation module;
the operation module is used for introducing a total pressure value and a static pressure value of a flow field, and respectively establishing a first-third relation among a yaw angle coefficient, the total pressure coefficient, the static pressure coefficient, a pressure measuring hole measuring value of the first pressure measuring device, the total pressure value and the static pressure value of the flow field;
the airflow control device is used for generating a calibration flow field and acting on the first pressure measuring device and the second pressure measuring device;
the first pressure measuring device is used for acquiring pressure measuring hole measuring values of different air flow speeds and directions in the calibration flow field and sending the pressure measuring hole measuring values to the operation module;
the second pressure measuring device is used for acquiring total pressure and static pressure measurement values under the calibration flow field during calibration and sending the total pressure and static pressure measurement values to the operation module;
the operation module is further used for calibrating the first pressure measuring device under different air flow speed sizes and directions according to the first-third relational expressions, and establishing a first three-dimensional relational curved surface of a yaw angle coefficient, the air flow speed sizes and the air flow directions, a second three-dimensional relational curved surface of a total pressure coefficient, the air flow speed sizes and the air flow directions, and a third three-dimensional relational curved surface of a static pressure coefficient, the air flow speed sizes and the air flow directions;
the first pressure measuring device is also used for acquiring a specific pressure measuring hole measurement group value under the flow field to be calculated and sending the specific pressure measuring hole measurement group value to the operation module;
the operation module is further used for calculating the size and the direction of the airflow speed corresponding to the specific pressure measuring hole measurement group value according to the first relation-third relation and the first-third three-dimensional relation curved surface.
The calculation system adopts the first pressure measuring device, the second pressure measuring device, the airflow control device and the operation module to realize the steps in the calculation method, provides a hardware basis for the calculation method and is convenient for the method to implement.
The invention also provides air flow speed calculation equipment which comprises at least one structure of the first pressure measuring device, the second pressure measuring device, the air flow control device and the operation module in the calculation system.
That is, the first pressure measuring device, the second pressure measuring device, the airflow control device and the operation module are made into devices individually or combined randomly, which is the specific image of the above calculation method in implementation.
The present invention also provides a storage medium having stored thereon a computer program for being loaded by the above-described airflow speed calculation system or airflow speed calculation apparatus to implement the above-described airflow speed calculation method. The storage medium may be a magnetic disk, an optical disk, a Read Only Memory (ROM), a Random Access Memory (RAM), or the like.
Drawings
Fig. 1 is a perspective view of a probe part of a five-hole pressure measuring device (provided with five pressure measuring holes) according to the background art of the present invention;
FIG. 2 is a front view of the pressure tap of FIG. 1 as provided by the background of the invention;
FIG. 3 is a calibration curve of a yaw angle coefficient K α obtained according to the five-hole pressure measurement device shown in FIG. 1 according to the background art of the present invention;
FIG. 4 is a velocity coefficient Kv calibration curve obtained from the five-hole pressure measuring device shown in FIG. 1 according to the background art of the present invention;
fig. 5 is a flowchart illustrating steps of a method for calculating an airflow speed according to embodiment 1 of the present invention;
fig. 6 is a perspective view of a first pressure measuring device provided in embodiments 1, 2, and 3 of the present invention;
fig. 7 is a schematic diagram of a first relation curve cluster in an airflow speed calculation method according to embodiment 1 of the present invention;
fig. 8 is a schematic diagram of a second relation curve cluster in the airflow speed calculation method according to embodiment 1 of the present invention;
fig. 9 is a schematic view of a first three-dimensional relational surface in an airflow velocity calculation method according to embodiment 1 of the present invention;
fig. 10 is a flowchart of the operation of step S3 provided in embodiment 1 of the present invention;
fig. 11 is a block diagram of an airflow speed calculation system according to embodiment 2 of the present invention;
fig. 12 is a sectional view of a second pressure measuring device provided in embodiment 2 of the present invention;
fig. 13 is an installation schematic view of a second pressure measuring device provided in embodiment 2 of the present invention;
fig. 14 is a schematic structural diagram of fig. 11 provided in embodiment 2 of the present invention (the airflow direction is opposite to the first pressure measuring device);
fig. 15 is a schematic structural diagram of fig. 11 provided in embodiment 2 of the present invention (an included angle α between an airflow direction and a first pressure measuring device).
Detailed Description
The following is further detailed by the specific embodiments:
example 1
In order to more accurately measure the airflow velocity (including the magnitude and direction) somewhere, the present embodiment provides an airflow velocity calculating method, as shown in fig. 5, including steps S1 to S3.
S1, introducing a total pressure value and a static pressure value of a flow field, and respectively establishing a first-third relation among a yaw angle coefficient, the total pressure coefficient and the static pressure coefficient, a pressure measuring hole measuring value of a first pressure measuring device, and the total pressure value and the static pressure value of the flow field.
In the present step S1, the first pressure measuring device adopts an airfoil structure, and as shown in fig. 6, three pressure measuring holes are provided, including a total pressure hole P2, a first static pressure hole P1 and a second static pressure hole P3; if the upper and lower wing profiles of the first pressure measuring device are taken as the top surface and the bottom surface, the total pressure hole P2 is arranged at the arc top end of the arc side surface, and the first static pressure hole P1 and the second static pressure hole P3 are arranged on the arc side surfaces at two sides of the arc top end in an equal way. The inside cavity of wing section structure for installation trachea or other measuring device, tracheal other end connection pressure measurement appearance, this pressure measurement appearance can directly set up the hollow portion at wing section structure, also can connect outside wing section structure, and this embodiment then connects outside wing section structure to the pressure value in three atmospheric pressure hole of measurable quantity.
Compared with the traditional three-hole and five-hole needle type pressure measuring device, the three-hole airfoil structure is adopted for the first time in the embodiment, the total pressure hole P2, the first static pressure hole P1 and the second static pressure hole P3(P1, P2 and P3 also represent pressure values measured by corresponding hole sites) are respectively arranged at the arc top end of the arc side surface and the arc side surfaces at the two opposite sides, because the test is carried out, the sensitivity of the arc top end to the air flow deflection angle is highest, the calibration is convenient by matching the static pressure holes at the two sides, the functional relation between the yaw angle coefficient, the total pressure coefficient and each pressure measuring value is established for the later stage calculation, and the obtained functional relation is more accurate than that of the traditional pressure measuring device.
In step S1, the second pressure measuring device may be a general pressure measuring device, and placed in the same airflow space as the first pressure measuring device to measure the total pressure value Ptotal and the static pressure value pstic of the airflow, where the pressure measuring value is the total pressure of the airflow when the pressure measuring hole of the second pressure measuring device is directly opposite to the airflow, and the pressure measuring value is the static pressure of the airflow when the pressure measuring hole is perpendicular to the airflow. The second pressure measuring device is always opposite to the air flow direction in the calibration. Therefore, the second pressure measuring device is mainly used for correcting the total pressure and the static pressure.
And the present step S1: placing a first pressure measuring device and a second pressure measuring device in an air flow environment with given speed, direction and fluid density, wherein the second pressure measuring device always faces the air flow (a yaw angle coefficient K alpha, a total pressure coefficient Kpt and a static pressure coefficient Kps are determined), further measuring to obtain a plurality of groups of corresponding P1, P2, P3, Ptotal and Pstic values, and then establishing a corresponding first-third relation as follows:
the first relation is specifically:
the second relation is specifically:
the third relation is specifically:
k alpha, Kpt and Kps respectively represent a yaw angle coefficient, a total pressure coefficient and a static pressure coefficient; p2, P1 and P3 respectively represent the pressure values measured by the total pressure hole P2, the first static pressure hole P1 and the second static pressure hole P3,
ptotal and Pstic are respectively a total pressure value and a static pressure value measured by the second pressure measuring device.
And a first-third relation is established, and indirect expressions of the yaw angle coefficient, the total pressure coefficient, the static pressure coefficient, the air speed and the air direction are determined, so that later-stage calculation is facilitated.
S2, measuring the total pressure value and the static pressure value of the flow field by using a second pressure measuring device according to the first-third relation, calibrating the first pressure measuring device under different air flow speed sizes and different air flow directions, and establishing a first three-dimensional relation curved surface among a yaw angle coefficient, the air flow speed sizes and the air flow directions, a first three-dimensional relation curved surface among the total pressure coefficient, the air flow speed sizes and the air flow directions, and a first three-dimensional relation curved surface among the static pressure coefficient, the air flow speed sizes and the air flow directions.
Step S2 specifically includes:
s21, measuring the total pressure value and the static pressure value of the flow field by using a second pressure measuring device according to the first-third relation formula, calibrating the first pressure measuring device under different air flow speed sizes and directions respectively, and obtaining a first relation curve cluster and a second relation curve cluster of a yaw angle coefficient K alpha corresponding to the air flow speed size v and the air flow direction alpha, a third relation curve cluster and a fourth relation curve cluster of a total pressure coefficient Kpt corresponding to the air flow speed size v and the air flow direction alpha, a fifth relation curve cluster and a sixth relation curve cluster of a static pressure coefficient Kps corresponding to the air flow speed size v and the air flow direction alpha;
s22, establishing a first three-dimensional relation curved surface of a yaw angle coefficient K alpha, an airflow speed v and an airflow direction alpha according to the first relation curve cluster and the second relation curve cluster, establishing a second three-dimensional relation curved surface of a total pressure coefficient Kpt, an airflow speed v and an airflow direction alpha according to the third relation curve cluster and the fourth relation curve cluster, and establishing a third three-dimensional relation curved surface of a static pressure coefficient Kps, an airflow speed v and an airflow direction alpha according to the fifth relation curve cluster and the sixth relation curve cluster.
Step S2 is:
given different air flow speed and direction, the first pressure measuring device and the second pressure measuring device output corresponding measured values, calculating corresponding yaw angle coefficient Ka, total pressure coefficient Kpt and static pressure coefficient Kps according to the first-third relation, drawing curve clusters of each coefficient and the magnitude v and the direction alpha of the airflow speed respectively by an interpolation approximation method, synthesizing three-dimensional curved surfaces of each coefficient and the magnitude and the direction of the speed according to the curve clusters, therefore, the method is equivalent to determining the direct expression of the yaw angle coefficient K alpha, the total pressure coefficient Kpt, the static pressure coefficient Kps, the air flow speed v and the direction alpha, and is convenient for the calculation process in practice, and calculating a yaw angle coefficient, a total pressure coefficient or a static pressure coefficient through the first relation and the third relation, and solving the size and the direction of the corresponding air flow speed through the known yaw angle coefficient, total pressure coefficient or static pressure coefficient.
Taking the yaw angle coefficient K α as an example, a first relationship curve cluster and a second relationship curve cluster of the yaw angle coefficient K α with the airflow speed magnitude v and the direction α are respectively shown in fig. 7 and 8 (1deg is 1 degree, and 1kph is 1km/h per hour), and a first three-dimensional relationship curve synthesized from the first relationship curve cluster and the second relationship curve cluster is shown in fig. 9. For the total pressure coefficient Kpt and the static pressure coefficient Kps, the corresponding relation curve cluster is similar to that in fig. 7 and 8, and the corresponding three-dimensional relation curve graph is similar to that in fig. 9.
And S3, calculating the size and the direction of the air flow speed corresponding to a specific pressure measuring hole measuring group value according to the first relation, the third relation and the first-third three-dimensional relation curved surface.
As shown in fig. 10, step S3 specifically includes:
s31, acquiring specific pressure measuring hole measurement group values P1, P2 and P3 of the first pressure measuring device, wherein the P2, the P1 and the P3 are actually measured by a total pressure hole P2, a first static pressure hole P1 and a second static pressure hole P3 respectively;
s32, substituting p1, p2 and p3 into the first relational expression to obtain a corresponding yaw angle coefficient K alpha 1;
s33, defining the initial air flow velocity v0；
S34. based on K alpha 1 and v0Obtaining the corresponding airflow direction alpha according to the first three-dimensional relation curved surface1；
S35. based on v0、α1According to the second three-dimensional relationshipObtaining a corresponding total pressure coefficient Kpt1, and obtaining a corresponding static pressure coefficient Kps1 according to the third three-dimensional relation curved surface;
s36, based on Kpt1, p1, p2 and p3, obtaining the corresponding total pressure value Ptotal according to a second relation1(ii) a Based on Kps1 and p1, p2 and p3, the corresponding static pressure value Pstic is obtained according to the third relation1；
S37. based on Ptotal1、Pstatic1Obtaining the corresponding air velocity v according to the relational expression of the velocity, the total pressure and the static pressure1；
S38, judging e1＝v1-v0If it is less than the set error value, if it is, the matched v1、α1The sizes and the directions of the airflow speeds corresponding to p1, p2 and p 3.
Specifically, in step S37, the relationship between the speed and the total pressure and the static pressure is:
and rho is the density of the fluid where the first pressure measuring device is located.
Step S37 provides details (physical theorem) of the velocity-total pressure-static pressure relation, where Ptotal and pstic are the total pressure value and the static pressure value measured by the second pressure measuring device, respectively, and ρ is the fluid density at that time (the first pressure measuring device and the second pressure measuring device may be equipped with a measuring instrument for measuring the fluid density). The relation between the speed and the total pressure and the static pressure can represent the relation between the wind speed and the total pressure, the static pressure and the fluid density, so that the relation can be represented by the known Ptotal in the step S371、Pstatic1Obtaining the corresponding air velocity v1And subsequent iterative computation is facilitated.
If e1＝v1-v0V is greater than or equal to the set error value1In place of v0Re-executing steps S34-S38 until the determined ei＝vi-vi-1If the error value is less than the set error value, the V is satisfiedi、αiThe sum of the airflow velocities corresponding to p1, p2 and p3And (4) direction.
This step S3:
1. obtaining a corresponding yaw angle coefficient according to the first relational expression and a group of air pressure measurement values actually measured by the first pressure measuring device, further giving an initial air flow speed (estimated or measured by other devices), substituting the initial air flow speed into the first three-dimensional relational curved surface to obtain an air flow direction of the initial air flow speed (steps S31-S34), and obtaining the size and the direction of a group of air flow speeds at first so as to facilitate later-stage iterative computation;
2. however, the initial air flow velocity is only a predicted value, is not accurate and cannot represent the actual air flow velocity, and the solved direction cannot represent the actual direction, so the scheme further solves the corresponding total pressure coefficient and static pressure coefficient based on the second three-dimensional relational surface and the third three-dimensional relational surface, reversely solves the corresponding total pressure value and static pressure value according to the solved total pressure coefficient and static pressure coefficient (not actually measured by the second pressure measuring device), and then deduces the air flow velocities under the total pressure value and the static pressure value according to the checking relational expression, thereby facilitating iterative calculation;
3. therefore, the difference value between the airflow speed calculated in the step S34 and the airflow speed calculated in the step S37 can be reduced to be within a preset range through one-step iteration, the airflow speed and the airflow speed direction are finally determined, the airflow speed and the airflow speed direction can be closer to reality, and the error is smaller;
4. the error condition of the obtained air speed and direction can be controlled by adjusting the set error value. The ideal error value is zero, but considering that the smaller the set error value is, the more the iteration times are, the larger the workload is, and a certain error tolerance range in actual work is generally set below ± 0.1 kph.
In summary, the calculation principle of the present embodiment is:
firstly, introducing a total pressure value and a static pressure value of a flow field, and establishing a functional relation (a first relation and a third relation) among a yaw angle coefficient, the total pressure coefficient and the static pressure coefficient, each pressure measurement value of a first pressure measurement device, and the total pressure value and the static pressure value of the flow field;
then, calibrating the first pressure measuring device under the given different air flow speed sizes and directions, and calibrating the first pressure measuring device according to the established function relation, wherein the total pressure value and the static pressure value of the flow field are measured by using the second pressure measuring device, and a first-third three-dimensional relation curved surface of three coefficients of a yaw angle coefficient, the total pressure coefficient and the static pressure coefficient, the air flow speed sizes and the air flow directions is established;
and finally, placing the first pressure measuring device in the flow field to be calculated, outputting a specific pressure measuring hole measurement group value of the current airflow by the first pressure measuring device, and calculating the size and the direction of the airflow speed corresponding to the specific pressure measuring hole measurement group value according to the first relation, the third relation and the first three-dimensional relation curved surface.
The beneficial effect of this basic scheme lies in:
1. establishing a first-third relation among a yaw angle coefficient, a total pressure coefficient and a static pressure coefficient, a pressure measuring hole measuring value of a first pressure measuring device, a total pressure value and a static pressure value of a flow field, calibrating the first pressure measuring device in the early stage, simultaneously measuring the total pressure value and the static pressure value of the current airflow through another auxiliary pressure measuring device (a second pressure measuring device), introducing the measuring values into calibration calculation of the first pressure measuring device, and establishing the relation, namely the functional relation among the yaw angle coefficient, the total pressure coefficient and the static pressure coefficient and each pressure measuring value, which is more practical;
2. in practical measurement application, the size and the direction of the airflow speed of the measured flow field can be calculated through the measurement value of the first pressure measuring device according to the first relational expression-the third relational expression obtained through calibration and the three-dimensional relational surface maps of the yaw angle coefficient, the total pressure coefficient, the static pressure coefficient and the size and the direction of the airflow speed. In the calculation process, a speed verification and iteration method is introduced, and through iterative calculation, the influence of air flow deflection angles (yaw and pitch) is avoided, so that the measurement error is ensured to be in a small range, and the measurement precision of the pressure measuring device is improved.
Example 2
Reference numerals in figure 11 of the specification include: the device comprises a first pressure measuring device 10, a second pressure measuring device 20, an airflow control device 30 and an operation module 40.
Corresponding to an airflow speed calculation method of embodiment 1, this embodiment provides an airflow speed calculation system, as shown in fig. 11, including a first pressure measuring device 10, a second pressure measuring device 20, an airflow control device 30, an arithmetic module 40;
the operation module 40 is configured to introduce a total pressure value and a static pressure value of the flow field, and respectively establish first-third relations among a yaw angle coefficient, the total pressure coefficient, the static pressure coefficient, a pressure measurement value of a pressure measurement hole of the first pressure measurement device 10, and the total pressure value and the static pressure value of the flow field;
the airflow control device 30 is used for generating a calibration flow field and acting on the first pressure measuring device 10 and the second pressure measuring device 20;
the first pressure measuring device 10 is used for acquiring pressure measuring hole measuring values of different air flow speeds and directions in a calibration flow field and sending the pressure measuring hole measuring values to the operation module 40;
the second pressure measuring device 20 is used for acquiring total pressure and static pressure measurement values under a calibration flow field during calibration and sending the total pressure and static pressure measurement values to the operation module 40;
the operation module 40 is further configured to perform second calibration on the first pressure measurement device 10 at different airflow speed magnitudes and directions according to the first-third relational expressions, respectively, and establish a first three-dimensional relational curved surface of a yaw angle coefficient, an airflow speed magnitude, and an airflow direction, a second three-dimensional relational curved surface of a total pressure coefficient, an airflow speed magnitude, and an airflow direction, and a third three-dimensional relational curved surface of a static pressure coefficient, an airflow speed magnitude, and an airflow direction;
the first pressure measuring device 10 is further configured to obtain a specific pressure measuring hole measurement group value in the flow field to be calculated and send the specific pressure measuring hole measurement group value to the operation module 40;
the operation module 40 is further configured to calculate the magnitude and the direction of the airflow speed corresponding to the specific pressure measurement set value according to the first relation-the third relation and the first-the third three-dimensional relation curved surface.
For more specific calibration and calculation processes among the first pressure measuring device 10, the second pressure measuring device 20, the airflow control device 30, and the operation module 40, reference is made to embodiment 1, and details of this embodiment are not repeated.
For a specific structure of the first pressure measuring device 10, refer to embodiment 1, and this embodiment is not described again.
As shown in fig. 12, the second pressure measuring device 20 is an L-shaped pitot tube (the diameter of the tube is D, the diameter of the total pressure hole is D, and the distance between the total pressure hole and the static pressure hole is L) as the second pressure measuring device 20AB). As shown in fig. 13, the fixing bracket is used for fixing the L-shaped pitot tube and adjusting the direction of the L-shaped pitot tube, so that the total pressure holes of the L-shaped pitot tube always face the air flow and the static pressure holes always are perpendicular to the air flow in the calibration process. Since the L-shaped pitot tube is the prior art, the present embodiment is not described in detail.
As shown in fig. 14 and 15, the airflow control device 30 mainly includes an airflow generating device, a flow stabilizing system, and an airflow nozzle. The airflow generating device adopts a fan, is used for generating airflow with a given direction but different sizes, is subjected to flow stabilization by the flow stabilization system and then is sprayed out from the airflow nozzle to act on the first pressure measuring device 10 and the second pressure measuring device 20. Wherein the flow stabilizing system can improve the quality of the flow field.
It should be further noted that, in order to change the direction of the first pressure measuring device 10 in the second calibration process, the system is provided with a rotating device (a disk) for fixing the first pressure measuring device 10 (the first pressure measuring device 10 is fixed at the geometric center of the disk). When the direction of the airflow received by the first pressure measuring device 10 needs to be changed, the rotating device is controlled to rotate by a corresponding angle. And the second pressure measuring device 20 (adjusted by the fixed support) always keeps the total pressure hole thereof opposite to the airflow nozzle.
In this embodiment, the operation module 40 is integrated in a computer, and based on software in the computer, calibration and calculation are completed, the first pressure measuring device 10 and the second pressure measuring device 20 are connected to the computer through data lines, and values of measured air pressures and given air flow velocities and directions are transmitted in real time, so that relationships, two-dimensional relationship clusters, three-dimensional curved surfaces and the like are automatically established and stored according to the values. When a space with unknown airflow speed needs to be tested, only the first pressure measuring device 10 needs to be placed in the space, an error value is set in software, and finally the software can directly output the airflow speed and the direction corresponding to the set error value according to the three airflow values output by the first pressure measuring device 10. In the software, a plurality of error values can be set, and the size and the direction of the air flow speed under different error values are calculated, so that the reference value can be larger.
The calculation system adopts the first pressure measuring device 10, the second pressure measuring device 20, the airflow control device 30 and the operation module 40 to realize the steps in the calculation method, provides a hardware basis for the calculation method and is convenient for the method to implement.
Example 3
The present embodiment provides an air flow rate calculation apparatus including any one of the first pressure measuring device 10, the second pressure measuring device 20, the arithmetic module 40, the air flow control device 30, corresponding to an air flow rate calculation method of embodiment 1 and an air flow rate calculation system of embodiment 2, and the difference between the present embodiment and embodiment 2 is that the present embodiment focuses on protecting an apparatus and focuses on structural integrity. That is, this embodiment protects the device made of any one module in embodiment 2, and also protects any two, three, four, or all five devices integrated together.
In the present embodiment, the gas flow rate calculation device includes a calibration device and a calculation device.
Wherein, calibration equipment includes:
an air flow control device 30, which is a device that can be operated alone, as in example 2;
a first pressure measuring device 10, as shown in fig. 6, is also a device that can be operated independently, as in example 1;
a second pressure measuring device 20, which is also a separately operable device, as in example 2;
the operation module 40 is also a device that can be operated independently, such as embodiment 2.
The calibration device is mainly used for executing steps S1 and S2 in embodiment 1, completing calibration of the first pressure measuring device 10, and obtaining a corresponding first-third relation and a first-third three-dimensional curved surface.
Wherein the computing device comprises:
a first pressure measuring device 10, as shown in fig. 6, is also a device that can be operated independently, as in example 1;
the operation module 40 is also a device that can be operated independently, such as embodiment 2.
The first pressure measuring device 10 in the computing equipment and the first pressure measuring device 10 in the calibration equipment are of the same model, and the operation module 40 in the computing equipment and the operation module 40 in the calibration equipment are of the same or different models, and only the same function needs to be realized respectively.
The calculating device is configured to execute step S3 in embodiment 1, where the first pressure measuring device 10 is configured to measure an air pressure value of the flow field to be measured, and the operation module 40 stores a first-third relation, a first-third three-dimensional curved surface, and a relation between a speed and a total pressure, and a static pressure, so that a corresponding air flow speed and a corresponding air flow direction can be obtained according to a set of measured voltage values.
Example 4
The present invention also provides a storage medium having stored thereon a computer program for being loaded by the airflow speed calculation system described in embodiment 2 or the airflow speed calculation apparatus described in embodiment 3 to implement the airflow speed calculation method described in embodiment 1. The storage medium may be a magnetic disk, an optical disk, a Read Only Memory (ROM), a Random Access Memory (RAM), or the like.
The foregoing are merely exemplary embodiments of the present invention, and no attempt is made to show structural details of the invention in more detail than is necessary for the fundamental understanding of the art, the description taken with the drawings making apparent to those skilled in the art how the several forms of the invention may be embodied in practice with the teachings of the invention. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (10)
1. An airflow velocity calculation method characterized by comprising the steps of:
s1, introducing a total pressure value and a static pressure value of a flow field, and respectively establishing a first-third relation among a yaw angle coefficient, the total pressure coefficient and the static pressure coefficient, a pressure measuring hole measuring value of a first pressure measuring device, and the total pressure value and the static pressure value of the flow field;
s2, measuring the total pressure value and the static pressure value of the flow field by using a second pressure measuring device according to the first-third relation, calibrating the first pressure measuring device under different air flow speed sizes and different air flow directions, and establishing a first three-dimensional relation curved surface among a yaw angle coefficient, the air flow speed sizes and the air flow directions, a first three-dimensional relation curved surface among the total pressure coefficient, the air flow speed sizes and the air flow directions, and a first three-dimensional relation curved surface among the static pressure coefficient, the air flow speed sizes and the air flow directions;
and S3, obtaining the size and the direction of the air flow speed corresponding to a specific pressure measuring hole measurement group value through iterative calculation according to the first relation, the third relation and the first-third three-dimensional relation curved surface.
2. An airflow velocity calculating method according to claim 1, wherein in said step S1, said first pressure measuring device is of a wing type structure, and is provided with three pressure measuring holes including a total pressure hole, a first static pressure hole and a second static pressure hole; if the upper and lower wing profiles of the first pressure measuring device are taken as the top surface and the bottom surface, the total pressure hole is formed in the arc top end of the arc side surface, and the first static pressure hole and the second static pressure hole are formed in the arc side surfaces on the two sides of the arc top end in an equal mode.
3. An airflow velocity calculating method according to claim 2, wherein in said step S1,
the first relational expression is specifically as follows:
the second relational expression is specifically as follows:
the third relational expression is specifically as follows:
k alpha, Kpt and Kps respectively represent a yaw angle coefficient, a total pressure coefficient and a static pressure coefficient; p2, P1 and P3 respectively represent the pressure values measured by the total pressure hole, the first static pressure hole and the second static pressure hole,
ptotal and Pstic are respectively a total pressure value and a static pressure value measured by the second pressure measuring device.
4. An airflow speed calculation method according to claim 3, wherein the step S2 specifically includes:
s21, measuring the total pressure value and the static pressure value of the flow field by using a second pressure measuring device according to the first-third relation formula, calibrating the first pressure measuring device under different air flow speed sizes and different air flow directions respectively to obtain a first relation curve cluster and a second relation curve cluster of a yaw angle coefficient K alpha corresponding to the air flow speed size v and the air flow direction alpha, a third relation curve cluster and a fourth relation curve cluster of a total pressure coefficient Kpt corresponding to the air flow speed size v and the air flow direction alpha, a fifth relation curve cluster and a sixth relation curve cluster of a static pressure coefficient Kps corresponding to the air flow speed size v and the air flow direction alpha;
s22, establishing a first three-dimensional relation curved surface of a yaw angle coefficient K alpha, an airflow speed v and an airflow direction alpha according to the first relation curve cluster and the second relation curve cluster, establishing a second three-dimensional relation curved surface of a total pressure coefficient Kpt, an airflow speed v and an airflow direction alpha according to the third relation curve cluster and the fourth relation curve cluster, and establishing a third three-dimensional relation curved surface of a static pressure coefficient Kps, an airflow speed v and an airflow direction alpha according to the fifth relation curve cluster and the sixth relation curve cluster.
5. An airflow speed calculation method according to claim 4, wherein the step S3 specifically includes:
s31, obtaining specific pressure measuring hole measurement group values p1, p2 and p3 of the first pressure measuring device, wherein the p2, the p1 and the p3 are respectively measured by the total pressure hole, the first static pressure hole and the second static pressure hole;
s32, substituting p1, p2 and p3 into the first relational expression to obtain a corresponding yaw angle coefficient K alpha 1;
s33, defining the initial air flow velocity v0；
S34. based on K alpha 1 and v0Obtaining the corresponding airflow direction alpha according to the first three-dimensional relation curved surface1；
S35. based on v0、α1Obtaining a corresponding total pressure coefficient Kpt1 according to the second three-dimensional relation curved surface, and obtaining a corresponding static pressure coefficient Kps1 according to the third three-dimensional relation curved surface;
s36, based on Kpt1, p1, p2 and p3, obtaining the corresponding total pressure value Ptotal according to the second relation1(ii) a Based on Kps1 and p1, p2 and p3, obtaining the corresponding static pressure value Pstic according to the third relation1；
S37. based on Ptotal1、Pstatic1Obtaining the corresponding air velocity v according to the relational expression of the velocity, the total pressure and the static pressure1；
S38, judging e1＝v1-v0If it is less than the set error value, if so, v is1、α1The sizes and the directions of the airflow speeds corresponding to p1, p2 and p 3.
6. An airflow velocity calculation method according to claim 5, characterized by: in the step S38, if e1＝v1-v0V is greater than or equal to the set error value0In place of v0Re-executing steps S34-S38 until the determined ei＝vi-vi-1If the error value is less than the set error value, the V is satisfiedi、αiThe sizes and the directions of the airflow speeds corresponding to p1, p2 and p 3.
7. A method of calculating air flow velocity according to claim 5, wherein said velocity is related to total pressure and static pressure by:
and rho is the density of the fluid where the first pressure measuring device is located.
8. An airflow velocity calculation system, characterized by: the device comprises an airflow control device, a first pressure measuring device, a second pressure measuring device and an operation module;
the operation module is used for introducing a total pressure value and a static pressure value of a flow field, and respectively establishing a first-third relation among a yaw angle coefficient, the total pressure coefficient, the static pressure coefficient, a pressure measuring hole measuring value of the first pressure measuring device, the total pressure value and the static pressure value of the flow field;
the airflow control device is used for generating a calibration flow field and acting on the first pressure measuring device and the second pressure measuring device;
the first pressure measuring device is used for acquiring pressure measuring hole measuring values of different air flow speeds and directions in the calibration flow field and sending the pressure measuring hole measuring values to the operation module;
the second pressure measuring device is used for acquiring total pressure and static pressure measurement values under the calibration flow field during calibration and sending the total pressure and static pressure measurement values to the operation module;
the operation module is further used for calibrating the first pressure measuring device under different air flow speed sizes and directions according to the first-third relational expressions, and establishing a first three-dimensional relational curved surface of a yaw angle coefficient, the air flow speed sizes and the air flow directions, a second three-dimensional relational curved surface of a total pressure coefficient, the air flow speed sizes and the air flow directions, and a third three-dimensional relational curved surface of a static pressure coefficient, the air flow speed sizes and the air flow directions;
the first pressure measuring device is also used for acquiring a specific pressure measuring hole measurement group value under the flow field to be calculated and sending the specific pressure measuring hole measurement group value to the operation module;
the operation module is further used for calculating the size and the direction of the airflow speed corresponding to the specific pressure measuring hole measurement group value according to the first relation-third relation and the first-third three-dimensional relation curved surface.
9. An air flow velocity calculation apparatus characterized by: the device comprises at least one structure of a first pressure measuring device, a second pressure measuring device, an airflow control device and an operation module according to claim 8.
10. A storage medium, characterized by: stored thereon a computer program for being loaded by an air flow rate calculation system according to claim 8 or an air flow rate calculation apparatus according to claim 9 for performing the air flow rate calculation method according to any one of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010747052.0A CN111856072B (en) | 2020-07-29 | 2020-07-29 | Air flow speed calculation method, system and equipment and storage medium |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010747052.0A CN111856072B (en) | 2020-07-29 | 2020-07-29 | Air flow speed calculation method, system and equipment and storage medium |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111856072A true CN111856072A (en) | 2020-10-30 |
| CN111856072B CN111856072B (en) | 2021-10-15 |
Family
ID=72945371
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010747052.0A Active CN111856072B (en) | 2020-07-29 | 2020-07-29 | Air flow speed calculation method, system and equipment and storage medium |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111856072B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113970400A (en) * | 2021-10-22 | 2022-01-25 | 中国汽车工程研究院股份有限公司 | Multi-precision and wide-range airflow deflection angle measuring device based on airfoil structure |
| TWI832466B (en) * | 2022-10-03 | 2024-02-11 | 財團法人成大研究發展基金會 | Wind speed measurement method and device based on three-hole pitot tube |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5830673A (en) * | 1981-08-18 | 1983-02-23 | Natl Aerospace Lab | Pyramidal trapesoid shaped 4-hole pitot tube type probe |
| CN2108926U (en) * | 1991-12-12 | 1992-07-01 | 清华大学 | Omnibearing tow-dimensional speed measurer of air stream |
| JPH10332728A (en) * | 1997-06-03 | 1998-12-18 | Natl Aerospace Lab | Wide speed range flying speed vector measuring system using truncated quadrangular pyramid type five-holed probe |
| CN106096223A (en) * | 2016-05-10 | 2016-11-09 | 中国科学院工程热物理研究所 | A kind of five-hole probe data processing method |
| CN106840268A (en) * | 2017-03-27 | 2017-06-13 | 北京航空航天大学 | A kind of five-hole probe of integrated total temperature measurement |
| CN110470859A (en) * | 2019-09-24 | 2019-11-19 | 西北工业大学 | A method of for the direction tachometric survey of air system interior air-flow |
| CN110514390A (en) * | 2019-08-12 | 2019-11-29 | 北京航空航天大学 | A kind of three pore pressure force probes measurement two-dimensional flow field uncertainty evaluation method |
| CN111257591A (en) * | 2020-03-31 | 2020-06-09 | 中国舰船研究设计中心 | Method and device for measuring wind speed and wind direction of seven-hole probe airflow field |
-
2020
- 2020-07-29 CN CN202010747052.0A patent/CN111856072B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5830673A (en) * | 1981-08-18 | 1983-02-23 | Natl Aerospace Lab | Pyramidal trapesoid shaped 4-hole pitot tube type probe |
| CN2108926U (en) * | 1991-12-12 | 1992-07-01 | 清华大学 | Omnibearing tow-dimensional speed measurer of air stream |
| JPH10332728A (en) * | 1997-06-03 | 1998-12-18 | Natl Aerospace Lab | Wide speed range flying speed vector measuring system using truncated quadrangular pyramid type five-holed probe |
| CN106096223A (en) * | 2016-05-10 | 2016-11-09 | 中国科学院工程热物理研究所 | A kind of five-hole probe data processing method |
| CN106840268A (en) * | 2017-03-27 | 2017-06-13 | 北京航空航天大学 | A kind of five-hole probe of integrated total temperature measurement |
| CN110514390A (en) * | 2019-08-12 | 2019-11-29 | 北京航空航天大学 | A kind of three pore pressure force probes measurement two-dimensional flow field uncertainty evaluation method |
| CN110470859A (en) * | 2019-09-24 | 2019-11-19 | 西北工业大学 | A method of for the direction tachometric survey of air system interior air-flow |
| CN111257591A (en) * | 2020-03-31 | 2020-06-09 | 中国舰船研究设计中心 | Method and device for measuring wind speed and wind direction of seven-hole probe airflow field |
Non-Patent Citations (2)
| Title |
|---|
| 浙江大学 岑可法: "《锅炉燃烧试验研究方法及测量技术》", 31 October 1987, 水利电力出版社 * |
| 陈峻: "《船舶动力装置测试技术》", 28 February 2015, 上海交通大学出版社 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113970400A (en) * | 2021-10-22 | 2022-01-25 | 中国汽车工程研究院股份有限公司 | Multi-precision and wide-range airflow deflection angle measuring device based on airfoil structure |
| TWI832466B (en) * | 2022-10-03 | 2024-02-11 | 財團法人成大研究發展基金會 | Wind speed measurement method and device based on three-hole pitot tube |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111856072B (en) | 2021-10-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111856072B (en) | Air flow speed calculation method, system and equipment and storage medium | |
| CN110514391B (en) | Five-hole pressure probe measurement three-dimensional flow field uncertainty evaluation method | |
| Gallington | MEASUREMENT OF VERY LARGE FLOW ANGLES WITH NON-NIILLING SEVEN-HOLE PROBES | |
| CN113916486B (en) | Low-speed wind tunnel rapid pressure measurement and control method based on multi-parameter pressure regression algorithm | |
| CN110514390B (en) | Three-hole pressure probe measurement two-dimensional flow field uncertainty evaluation method | |
| CN105890804B (en) | A method of it improving temperature sensor and measures total airflow temperature precision | |
| CN116007884B (en) | Five-hole probe spherical coordinate data processing method considering compressibility | |
| CN106096223A (en) | A kind of five-hole probe data processing method | |
| CN114486164A (en) | Three-hole probe gradient flow field test calibration method based on neural network | |
| CN110705002A (en) | Compensation system and method for simulation test | |
| CN110736484A (en) | Background magnetic field calibration method based on fusion of gyroscope and magnetic sensor | |
| CN111273056A (en) | Attack angle observation method of high-speed aircraft without adopting altitude measurement | |
| CN106323587B (en) | The monocular video high-precision measuring method of wing model in wind tunnel flexible deformation | |
| US4972593A (en) | Method and apparatus for measuring the undistorted magnetic field of the earth | |
| CN112326187A (en) | Method for measuring friction force field by applying liquid crystal coating and deep learning algorithm | |
| CN112525474A (en) | Method for obtaining blocking interference factor of transonic wind tunnel | |
| Yao et al. | Optimal design of hemispherical 7-hole probe tip with perpendicular holes | |
| CN114659709B (en) | Three-dimensional centroid measurement method for large winged aerospace vehicle | |
| CN111498141A (en) | Method and device for realizing real-time monitoring of airflow angle based on micro probe | |
| CN114877975A (en) | Ultrasonic water meter flow error correction method based on reynolds number of pipeline inlet | |
| Judd | Calibration of a five tube probe for measuring wind speed and direction | |
| CN111649903A (en) | Method for indirectly measuring aerodynamic drag coefficient by using dynamic model experiment | |
| KR101045006B1 (en) | Calibration system and calibration method of multi-hole pressure probe | |
| CN113514222B (en) | Aerodynamic force measuring device and method for ventilation model of air suction type air inlet channel aircraft | |
| Dunbar et al. | Design of flush air data systems insensitive to manufacturing variance |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |