CN115597817A - Method for repairing profile line in hypersonic velocity spray pipe - Google Patents
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Abstract
The invention relates to a hypersonic velocity spray pipe inner molded line repairing method, belonging to the field of wind tunnel tests; carrying out numerical simulation on the molded line of the spray pipe; analyzing whether the flow field of the spray pipe is in an under-expansion state or an over-expansion state by combining the calibration and measurement data of the flow field at the outlet of the spray pipe; aiming at the under-expansion state or the over-expansion state of the spray pipe, a left-going characteristic line region correction method or a right-going characteristic line region correction method is adopted for repairing; on the basis of the original spray pipe molded surface, the flow field quality can reach excellent indexes only by locally repairing the molded surface, and meanwhile, the method is low in cost and short in period, and can be quickly applied to a hypersonic spray pipe with a poor flow field; the invention can provide high-quality pneumatic data for hypersonic wind tunnel test for aircraft development and can simulate flight environment.
Description
Technical Field
The invention belongs to the field of wind tunnel tests and relates to a hypersonic velocity spray pipe internal profile line repairing method.
Background
In a hypersonic wind tunnel test, a spray pipe is a key component for obtaining required uniform test airflow in a hypersonic wind tunnel test section, and the quality of the hypersonic test airflow is influenced. The hypersonic flow speed is fast, the gradient is large, the discontinuity is strong, the thermal coupling is complex, the propagation area is limited, and the corresponding design technology is very complex. With the development of modern aerodynamics, the research content of wind tunnel tests is more and more diversified, and the requirement on the wind tunnel test capability is higher and higher.
The development of the hypersonic wind tunnel has already been in the history of decades, the corresponding nozzle design technology has also been developed for decades, the design method and theory of the hypersonic nozzle designed originally are relatively lagged behind, and the nozzle outlet flow field index cannot meet the development of the existing wind tunnel test. Meanwhile, the new spray pipe is high in processing cost and long in cycle, and in order to save cost and improve the flow field quality, a hypersonic spray pipe inner profile line repairing method needs to be developed urgently to improve the flow field quality of a test section, so that the flow field quality meets excellent indexes, and corresponding support is provided for high-quality wind tunnel test pneumatic data required by advanced aircraft development.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects in the prior art are overcome, the hypersonic velocity spray pipe inner profile repairing method is provided, on the basis of the original spray pipe profile, the profile is only required to be locally repaired, the flow field quality can reach excellent indexes, meanwhile, the cost is low, the period is short, and the hypersonic velocity spray pipe inner profile repairing method can be rapidly applied to a hypersonic velocity spray pipe with a poor flow field.
The technical scheme of the invention is as follows:
a hypersonic velocity spray pipe inner molded line repairing method comprises the following steps:
carrying out numerical simulation on the molded line of the spray pipe;
analyzing whether the flow field of the spray pipe is in an under-expansion state or an over-expansion state by combining the calibration and measurement data of the flow field at the outlet of the spray pipe;
and (3) repairing the underexpansion state or the overexpansion state of the spray pipe by adopting a left-line characteristic line area correction method or a right-line characteristic line area correction method.
In the method for repairing the inner molded line of the hypersonic velocity spray pipe, when the total temperature of the resident spray pipe chamber is less than 800K, an ideal gas equation is adopted for numerical simulation; when the total temperature of the spray pipe resident chamber is 800-1600K, the numerical simulation adopts a complete gas equation; when the total temperature of the spray pipe resident chamber is 1600-2500K, a chemical non-equilibrium gas equation is adopted for numerical simulation; when the total temperature of the spray pipe resident chamber is more than 2500K, adopting a thermochemical non-equilibrium gas equation for numerical simulation; when the nozzle chamber contains liquid or solid particles, the numerical simulation adopts a multiphase flow gas equation.
In the above hypersonic velocity nozzle internal profile line repairing method, the nozzle expansion section is composed of 3 parts or 2 parts; when the number is 3, the part comprises a left row area section TA, a conical flow area section GA and a right row area section AD; when the points G and A of the hypersonic velocity nozzle coincide, only 2 parts are included, namely a left-row area section TA and a right-row area section AD.
In the hypersonic velocity nozzle internal profile line restoration method, the nozzle profile line slope is calculated by a polynomial interpolation method, and the calculation is carried out by a Hermit interpolation polynomial method.
In the method for repairing the inner molded line of the hypersonic velocity spray pipe, when the spray pipe is in an under-expanded state, the numerical simulation result shows that a Mach number Ma1 closed area appears on the central axis of the spray pipe; selecting slope beta at the G point, using the slope beta as a conic curve, extending G to the F point along the T direction, wherein the abscissa of the F point is x F Ordinate is y F 。
In the above method for repairing the profile in the hypersonic velocity nozzle, the equation of the TF curve is as follows:
in the formula, x and y are coordinate points of the TF curve equation.
In the hypersonic velocity spray pipe internal profile line repairing method, NT, TF, FG, GA and AD are connected to generate a new spray pipe profile line; using a numerical simulation technology to carry out numerical value correction; and when the quality of the test flow field does not meet the requirement, modifying the position of the F point, wherein the modification standard can be that the air flow deflection angle alpha is changed, and iteration is carried out, wherein the alpha value selected in each iteration is 0.2-0.5 degrees until the requirement is met.
In the method for repairing the inner molded line of the hypersonic velocity spray pipe, when the spray pipe is in an over-expansion state, the numerical simulation result shows that a boundary layer is sharply increased on the outlet of the spray pipe, so that Mach number Ma2 is sharply deflected to the central line; reconstructing a right-row region section by adopting Bezier curves for 7-8 times; selecting a point A as a starting point of an initial end of a Bezier curve, a point D1 as a terminal end point of the Bezier curve, a point D1 as a point D, wherein the radial extension distance is D, and the value range of D is 5-15 mm; the reconstructed Bezier curve is monotonous, and the second derivative of the reconstructed Bezier curve is continuous.
In the method for repairing the internal profile of the hypersonic velocity nozzle, the Bezier curve is formed by combining the position vector of the vertex of the characteristic polygon and a Bernstein basis function, and the expression is as follows:
in the formula, n is the frequency of a Bezier curve;
i is the serial number of the vertex of the characteristic line, and i is more than or equal to 0 and less than or equal to n;
u is a parameter, and u is more than or equal to 0 and less than or equal to 1; vi is the position loss of the characteristic polygon vertex;
J n,i in order to be a function of the Bernstein basis,
is the number of combinations.
In the method for repairing the inner profile of the hypersonic velocity spray pipe, a characteristic curve of the right line of the spray pipe reconstructed by Bezier curves for 7-8 times is selected, the first 3 vertexes ensure the continuity of the parameters of the initial point and the derivatives of the 1 st order and the 2 nd order, the last 3 points ensure the continuity of the parameters of the final point and the derivatives of the 1 st order and the 2 nd order, and other points are used for controlling the curve shape; carrying out numerical value correction on the new curve by using a numerical value simulation technology; and when the quality of the test flow field does not meet the index, changing the point coordinates for controlling the curve shape, and iterating until the requirement is met.
Compared with the prior art, the invention has the beneficial effects that:
(1) On the basis of the original spray pipe molded surface, the molded surface is only required to be locally repaired, and the flow field quality can reach excellent indexes;
(2) The invention has low cost and short period, and can be quickly applied to the hypersonic velocity spray pipe with poor flow field. The invention can provide high-quality pneumatic data for hypersonic wind tunnel test for aircraft development and can simulate flight environment.
Drawings
FIG. 1 is a schematic view of the profile and corresponding slope of the inventive nozzle;
FIG. 2 is a schematic flow diagram of an under-expanded nozzle flow field according to the present invention;
FIG. 3 is a schematic representation of the flow field flow of the over-expanded nozzle of the present invention;
FIG. 4 is a flow chart of the hypersonic velocity nozzle inner line repairing process.
Detailed Description
The invention is further illustrated by the following examples.
The invention provides a hypersonic velocity spray pipe internal profile repairing method, and relates to the field of wind tunnel tests. For the hypersonic wind tunnel nozzle, the influence of a nozzle inlet boundary layer is not considered at the beginning of design; or due to the fact that the design age is earlier, the design is not carried out by using a characteristic line method, or the boundary layer correction is not ideal and other factors, the flow field of the spray pipe is in an under-expansion or over-expansion state, the flow field of the outlet of the spray pipe is uneven, the quality of the flow field of the test section does not meet excellent indexes, and the pneumatic parameters of the test model have larger deviation. If a new spray pipe is redesigned and developed, the cost is high and the period is long. On the basis of the original spray pipe molded surface, the invention only needs to locally repair the molded surface, the flow field quality can reach excellent indexes, and meanwhile, the invention has low cost and short period, and can be quickly applied to the hypersonic spray pipe with poor flow field. The invention can provide high-quality pneumatic data for hypersonic wind tunnel test for aircraft development and can simulate flight environment.
The method for repairing the inner molded line of the hypersonic velocity spray pipe specifically comprises the following steps:
and carrying out numerical simulation on the molded line of the spray pipe. When the total temperature of the jet pipe in the residence chamber is less than 800K, the numerical simulation adopts an ideal gas equation; when the total temperature of the spray pipe resident chamber is 800-1600K, the numerical simulation adopts a complete gas equation; when the total temperature of the spray pipe resident chamber is 1600-2500K, a chemical non-equilibrium gas equation is adopted for numerical simulation; when the total temperature of the spray pipe resident chamber is more than 2500K, adopting a thermochemical non-equilibrium gas equation for numerical simulation; when the nozzle chamber contains liquid or solid particles, the numerical simulation adopts a multiphase flow gas equation.
And analyzing whether the flow field of the spray pipe is in an under-expansion state or an over-expansion state by combining the calibration and measurement data of the flow field at the outlet of the spray pipe.
And aiming at the under-expansion state or the over-expansion state of the spray pipe, repairing by adopting a method of correcting the characteristic line area of the left row or correcting the characteristic line area of the right row.
The expansion section of the spray pipe consists of 3 parts or 2 parts; when 3 parts, the left row area section TA, the cone flow area section GA, and the right row area section AD are included, as shown in fig. 1. When the points G and A of the hypersonic velocity nozzle coincide, only 2 parts are included, namely a left-going area section TA and a right-going area section AD.
The slope of the molded line of the spray pipe is calculated by a polynomial interpolation method, and the calculation is carried out by a Hermit interpolation polynomial method.
When the nozzle is in an under-expanded state, as shown in fig. 2, the numerical simulation result shows that a mach number Ma1 closed region appears on the central axis of the nozzle; selecting a slope beta at the G point, taking the slope beta as a conical curve, extending the G to the F point along the T direction, wherein the abscissa of the F point is x F Ordinate is y F . The equation for the TF curve is:
in the formula, x and y are coordinate points of the TF curve equation.
Connecting NT, TF, FG, GA and AD to generate a new spray pipe molded line; using a numerical simulation technology to carry out numerical correction; and when the quality of the test flow field does not meet the requirement, modifying the position of the F point, wherein the modification standard can be that the air flow deflection angle alpha is changed, and iteration is carried out, wherein the alpha value selected in each iteration is 0.2-0.5 degrees until the requirement is met.
When the nozzle is in an over-expansion state, as shown in fig. 3, the numerical simulation result shows that a boundary layer sharply increases at the nozzle outlet, which causes the mach number Ma2 to sharply deflect to the center line; reconstructing a right-row region segment by adopting a Bezier curve for 7-8 times; selecting a point A as a starting point of an initial end of a Bezier curve, a point D1 as a terminal end point of the Bezier curve, a point D1 as a point D, wherein the radial extension distance is D, and the value range of D is 5-15 mm; the reconstructed Bezier curve is monotonous, and the second derivative of the reconstructed Bezier curve is continuous.
The Bezier curve is combined by adopting a position vector of a characteristic polygon vertex and a Bernstein basis function, and the expression is as follows:
in the formula, n is the frequency of a Bezier curve;
i is the serial number of the vertex of the characteristic line, and i is more than or equal to 0 and less than or equal to n;
u is a parameter, and u is more than or equal to 0 and less than or equal to 1; vi is the position loss of the characteristic polygon vertex;
J n,i in order to be a function of the Bernstein basis,
is the number of combinations.
Selecting a characteristic line curve of the right row of the spray pipe reconstructed by 7-8 Bezier curves, ensuring the continuity of the parameters of the initial point and the derivatives of the 1 st order and the 2 nd order at the first 3 vertexes, ensuring the continuity of the parameters of the end point and the derivatives of the 1 st order and the 2 nd order at the last 3 points, and using other points to control the curve shape; carrying out numerical value correction on the new curve by using a numerical value simulation technology; and when the quality of the test flow field does not meet the index, changing the point coordinates for controlling the curve shape, and iterating until the requirement is met.
Examples
The specific steps are shown in fig. 4.
Step 1: and (3) carrying out numerical simulation on the molded line of the spray pipe, and analyzing whether the flow field of the spray pipe is in an underexpansion state or an overexpansion state by combining the calibration and measurement data of the flow field at the outlet of the spray pipe. And (3) repairing the underexpansion state or the overexpansion state of the spray pipe by adopting a left-line characteristic line area correction method or a right-line characteristic line area correction method.
Step 2: when the total temperature of the spray pipe resident chamber is less than 800K, the numerical simulation adopts an ideal gas equation; when the total temperature of the spray pipe resident chamber is 800-1600K, the numerical simulation adopts a complete gas equation; when the total temperature of the spray pipe in the residence chamber is 1600-2500K, the numerical simulation adopts a chemical non-equilibrium gas equation; when the total temperature of the jet pipe in the residence chamber is more than 2500K, the numerical simulation adopts a thermochemical unbalanced gas equation. When the nozzle chamber contains liquid or solid particles, the numerical simulation adopts a multiphase flow gas equation.
And step 3: the nozzle expansion section consists of 3 parts or 2 parts, a left-hand line section TA, a conical flow section GA and a right-hand line section AD, and is shown in figure 1. Some hypersonic velocity nozzles have coincident points G and a, and can be regarded as having only 2 parts, namely, a left-hand region section TA and a right-hand region section AD. The slope of the molded line of the spray pipe is calculated by a polynomial interpolation method, and the calculation is carried out by a Hermit interpolation polynomial method.
And 4, step 4: in the nozzle under-expanded state, as a result of numerical simulation in fig. 2, a closed region of mach number Ma1 appears on the nozzle central axis. Selection GThe slope beta of the point is used as a conic curve to extend G to F along the T direction, and the abscissa of the F is x F Ordinate is y F . The equation of the TF curve is
Wherein x and y are coordinate points of the TF curve equation.
NT, TF, FG, GA, and AD were ligated to generate new nozzle profiles. And (4) carrying out numerical value correction by using a numerical value simulation technology. If the quality of the test flow field does not meet the excellent indexes, the position of the F point is modified, the modification standard can be that the air flow deflection angle alpha is changed, iteration is carried out, and the alpha value selected in each iteration is 0.2-0.5 degrees until the requirement is met.
And 5: nozzle over-expansion conditions as a result of numerical simulations in fig. 3, a sharp boundary layer increase condition occurs at the nozzle exit, resulting in a sharp centerline deflection of mach number Ma 2. At this time, the Bezier curve is adopted for 7-8 times to reconstruct the right line region segment. Selecting point A as the initial end starting point of the Bezier curve, point D1 as the terminal end point of the Bezier curve, point D1 as point D, and the radial extension distance is D, and the D value range is 5-15 mm. The reconstructed Bezier curve is monotonous, and the second derivative of the reconstructed Bezier curve is continuous. The specific method comprises the following steps:
the Bezier curve adopts the combination of the position vector of the characteristic polygon vertex and Bernstein basis function, and the expression is
In the formula, n is the frequency of a Bezier curve; i is a radicalThe serial number of the vertex of the sign line is that i is more than or equal to 0 and less than or equal to n; u is a parameter, and u is more than or equal to 0 and less than or equal to 1; vi is the position loss of the characteristic polygon vertex, J n,i In order to be a function of the Bernstein basis,
is the number of combinations. And selecting a characteristic line curve of the right row of the spray pipe reconstructed by 7-8 Bezier curves, wherein the first 3 vertexes ensure the continuity of the parameters of the initial point and the derivatives of the 1 st order and the 2 nd order, the last 3 points ensure the continuity of the parameters of the final point and the derivatives of the 1 st order and the 2 nd order, and other points are used for controlling the curve shape. And (4) carrying out numerical value proofreading on the new curve by utilizing a numerical value simulation technology. If the quality of the test flow field does not meet excellent indexes, the point coordinates for controlling the curve shape are iterated until the requirements are met.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. A hypersonic velocity spray pipe inner profile line repairing method is characterized by comprising the following steps: the method comprises the following steps:
carrying out numerical simulation on the molded line of the spray pipe;
analyzing whether the flow field of the spray pipe is in an under-expansion state or an over-expansion state by combining the calibration and measurement data of the flow field at the outlet of the spray pipe;
and (3) repairing the underexpansion state or the overexpansion state of the spray pipe by adopting a left-line characteristic line area correction method or a right-line characteristic line area correction method.
2. The hypersonic velocity nozzle internal profile line repairing method according to claim 1, characterized in that: when the total temperature of the spray pipe resident chamber is less than 800K, the numerical simulation adopts an ideal gas equation; when the total temperature of the spray pipe resident chamber is 800-1600K, the numerical simulation adopts a complete gas equation; when the total temperature of the spray pipe resident chamber is 1600-2500K, a chemical non-equilibrium gas equation is adopted for numerical simulation; when the total temperature of the spray pipe resident chamber is more than 2500K, adopting a thermochemical non-equilibrium gas equation for numerical simulation; when the nozzle chamber contains liquid or solid particles, the numerical simulation adopts a multiphase flow gas equation.
3. The hypersonic velocity nozzle internal profile line repairing method according to claim 1, characterized in that: the expansion section of the spray pipe consists of 3 parts or 2 parts; when the number is 3, the part comprises a left row area section TA, a conical flow area section GA and a right row area section AD; when the points G and A of the hypersonic velocity nozzle coincide, only 2 parts are included, namely a left-row area section TA and a right-row area section AD.
4. The hypersonic velocity nozzle internal profile line repairing method according to claim 3, characterized in that: the slope of the molded line of the spray pipe is calculated by a polynomial interpolation method, and the calculation is carried out by a Hermit interpolation polynomial method.
5. The hypersonic velocity nozzle internal profile line repairing method according to claim 4, characterized in that: when the spray pipe is in an under-expansion state, the numerical simulation result shows that a Mach number Ma1 closed area appears on the central axis of the spray pipe; selecting slope beta at the G point, using the slope beta as a conic curve, extending G to the F point along the T direction, wherein the abscissa of the F point is x F On the ordinate of y F 。
6. The hypersonic velocity nozzle internal profile line repairing method according to claim 5, characterized in that: the equation for the TF curve is:
in the formula, x and y are coordinate points of the TF curve equation.
7. The method for restoring the profile line in the hypersonic velocity nozzle according to claim 6, characterized in that: connecting NT, TF, FG, GA and AD to generate a new spray pipe molded line; using a numerical simulation technology to carry out numerical correction; and when the quality of the test flow field does not meet the requirement, modifying the position of the F point, wherein the modification standard can be that the air flow deflection angle alpha is changed, and iteration is carried out, wherein the alpha value selected in each iteration is 0.2-0.5 degrees until the requirement is met.
8. The hypersonic velocity nozzle internal profile line repairing method according to claim 7, characterized in that: when the spray pipe is in an overexpansion state, the numerical simulation result shows that a boundary layer sharply increases on the outlet of the spray pipe, so that the Mach number Ma2 sharply deflects to a central line; reconstructing a right-row region segment by adopting a Bezier curve for 7-8 times; selecting a point A as a starting point of an initial end of a Bezier curve, a point D1 as a terminal end point of the Bezier curve, a point D1 as a point D, wherein the radial extension distance is D, and the value range of D is 5-15 mm; the reconstructed Bezier curve is monotonous, and the second derivative of the reconstructed Bezier curve is continuous.
9. The hypersonic velocity nozzle internal profile line repairing method according to claim 8, characterized in that: the Bezier curve is combined by adopting a position vector of a characteristic polygon vertex and a Bernstein basis function, and the expression is as follows:
in the formula, n is the frequency of a Bezier curve;
i is the serial number of the vertex of the characteristic line, and i is more than or equal to 0 and less than or equal to n;
u is a parameter, and u is more than or equal to 0 and less than or equal to 1; vi is the position loss of the characteristic polygon vertex;
J n,i is a function of the Bernstein basis,
is the number of combinations.
10. The hypersonic velocity nozzle internal profile line repairing method according to claim 9, characterized in that: selecting a characteristic line curve of the right row of the spray pipe reconstructed by 7-8 Bezier curves, ensuring the continuity of the parameters of the initial point and the derivatives of the 1 st order and the 2 nd order at the first 3 vertexes, ensuring the continuity of the parameters of the end point and the derivatives of the 1 st order and the 2 nd order at the last 3 points, and using other points to control the curve shape; carrying out numerical value correction on the new curve by using a numerical value simulation technology; and when the quality of the test flow field does not meet the index, changing the point coordinates for controlling the curve shape, and iterating until the requirement is met.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117490968A (en) * | 2023-12-22 | 2024-02-02 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet simulator rectifying device and jet design method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117490968A (en) * | 2023-12-22 | 2024-02-02 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet simulator rectifying device and jet design method |
| CN117490968B (en) * | 2023-12-22 | 2024-03-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet simulator rectifying device and jet design method |
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