CN110567673B - Wind tunnel test method for thrust measurement of oblique cutting nozzle of hypersonic vehicle - Google Patents
Wind tunnel test method for thrust measurement of oblique cutting nozzle of hypersonic vehicle Download PDFInfo
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Abstract
The invention discloses a wind tunnel test method for thrust measurement of a beveling nozzle of a hypersonic vehicle. The method is based on a wind tunnel test device for thrust measurement of the oblique cutting nozzle of the hypersonic vehicle, five components of normal force, lateral force, pitching moment, yawing moment and rolling moment under a body axis system are measured and obtained under the guidance of a cold jet flow simulation method, the axial force component under the body axis system and the distance of a thrust action point relative to the center correction of a five-component thrust balance are calculated and obtained, and finally the thrust direction and the thrust magnitude of the oblique cutting nozzle are obtained through force decomposition and translation. The wind tunnel test method adopts a wind tunnel test scaling model to solve the problem of thrust measurement of the oblique cutting nozzle, and can provide basic data for a reverse thrust method or a numerical calculation method of the thrust of a real rocket engine.
Description
Technical Field
The invention belongs to the technical field of hypersonic wind tunnel tests, and particularly relates to a wind tunnel test method for measuring thrust of a beveling nozzle of a hypersonic aircraft.
Background
The oblique cutting spray pipe is different from the axial symmetry spray pipe, the outlet of the spray pipe is oblique cut, unnecessary protrusions on the surface of the aircraft are avoided, and the aerodynamic shape of the aircraft is prevented from being damaged. Hypersonic aircraft (hereinafter referred to as hypersonic aircraft) bevel jet pipes are usually arranged on a reverse thrust rocket engine of a booster or a fairing of the hypersonic aircraft, and provide a part of driving force for separating the booster from the hypersonic aircraft or separating the fairing from the hypersonic aircraft so as to complete the whole separation process quickly and safely. The thrust direction, the thrust magnitude and the thrust action point of the reverse rocket engine are important input parameters in the design of the separation scheme and need to be known in advance.
For a normal axisymmetric nozzle, jet flow parameters at the outlet of the nozzle are uniform, the thrust direction of the reverse thrust rocket engine is coincident with the axis of the reverse thrust rocket engine, the thrust can be obtained by calculation of a theoretical formula, and the thrust action point is theoretically at the center of the outlet surface of the nozzle. Because the jet pipe is obliquely cut, jet flow parameters at the outlet of the jet pipe are not uniform, the thrust direction of the reverse thrust rocket engine deviates from the axis of the reverse thrust rocket engine, the actual thrust direction of the reverse thrust rocket engine is related to the parameters of the outlet of the obliquely cut jet pipe and environmental conditions, and the thrust size and the thrust action point are not easy to obtain and determine through theoretical calculation. The engine test bed can measure the thrust direction, the thrust magnitude and the thrust action point of the oblique cutting jet pipe of the real reverse-thrust rocket engine, but the time and the economic cost for measuring the thrust of the real reverse-thrust rocket engine on the engine test bed are not small due to the factors of large volume, large thrust, complex structure, high gas temperature and the like of the real reverse-thrust rocket engine. Therefore, there is a need for a fast and cost effective solution for measuring thrust of a hypersonic aircraft miter nozzle.
At present, a cold jet flow simulation method of a scaling model is adopted in a hypersonic wind tunnel according to a similar criterion, namely, a high-temperature fuel gas jet flow of a rocket engine is simulated by a normal-temperature compressed air jet flow in a spray pipe of the scaling model, and three major effects of the high-temperature fuel gas jet flow of the rocket engine, namely direct action, injection effect and volume effect, can be well simulated. Therefore, a set of wind tunnel test device and a method for measuring the thrust of the oblique cutting nozzle of the hypersonic vehicle can be provided based on a cold jet flow simulation method, the thrust direction, the thrust magnitude and the thrust action point of the nozzle of the scaling model of the wind tunnel test are obtained, and then the thrust direction, the thrust magnitude and the thrust action point of the real reverse rocket engine are obtained by extrapolation in a certain mode; or checking the numerical calculation method by adopting the thrust direction, the thrust magnitude and the thrust action point of the wind tunnel test scaling model spray pipe measured in the wind tunnel, and then calculating to obtain the real thrust direction, the thrust magnitude and the thrust action point of the reverse rocket engine by adopting the numerical calculation method verified by checking.
Currently, a method for measuring the thrust direction, the thrust magnitude and the thrust action point of a scaling oblique cutting nozzle in a hypersonic wind tunnel is needed to be developed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a wind tunnel test method for thrust measurement of a beveling nozzle of a hypersonic vehicle.
The invention discloses a wind tunnel test method for thrust measurement of a beveling nozzle of a hypersonic vehicle, which is characterized by comprising the following steps of: the wind tunnel test device used by the wind tunnel test method comprises a beveling spray pipe, a pressure regulating adapter, a five-component thrust balance, a ventilating support rod, a spray pipe sealing washer, a balance air outlet end sealing washer, a balance air inlet end sealing washer and a positioning pin.
The pressure regulating adapter is a cube, a beveling spray pipe mounting interface is arranged above the pressure regulating adapter, the beveling spray pipe is fixed on the pressure regulating adapter through a screw, and the beveling spray pipe and the pressure regulating adapter are sealed through a spray pipe sealing washer; two groups of positioning pin holes of 0 degree and 90 degrees are arranged at the mounting interface of the beveling spray pipe, and the beveling spray pipe is mounted on the pressure regulating adapter along the direction of 0 degree or 90 degrees according to the test requirements.
The side of the pressure regulating adapter is provided with a five-component thrust balance mounting interface, the air outlet end of the five-component thrust balance is fixed on the pressure regulating adapter through a screw, and the air outlet end of the five-component thrust balance and the pressure regulating adapter are sealed through a balance air outlet end sealing gasket; the air inlet end of the five-component thrust balance is fixed on the ventilating support rod through a screw, and the air inlet end of the five-component thrust balance and the ventilating support rod are positioned through a positioning pin and sealed through a balance air inlet end sealing gasket.
And a pressure monitoring sensor mounting interface is arranged below the pressure regulating adapter.
The oblique cutting spray pipe is a wind tunnel test model spray pipe obtained by the real reverse thrust rocket engine scaling according to the similar criterion of a cold jet simulation method, the oblique cutting spray pipe is a Laval spray pipe, and the contraction section and the expansion section of the oblique cutting spray pipe are both in a conical configuration.
The five-component thrust balance is made of F141 materials, a normal-temperature compressed air conduit is mounted on the axis of the five-component thrust balance, and the five-component thrust balance measures five components of normal force, lateral force, pitching moment, yawing moment and rolling moment under the body axis system.
The wind tunnel angle measuring device is characterized in that the ventilating support rod is made of a 30CrMnSiA material, one end of the ventilating support rod is connected with the air inlet end of the five-component thrust balance, the other end of the ventilating support rod is connected with the wind tunnel supporting device, the surface of the ventilating support rod is provided with an angle measuring platform, and a ventilating pipeline communicated with a normal-temperature compressed air conduit of the five-component thrust balance is arranged in the ventilating support rod.
The spray pipe sealing washer, the balance air outlet end sealing washer and the balance air inlet end sealing washer are all manufactured by red copper materials.
The wind tunnel test method for thrust measurement of the oblique cutting nozzle of the hypersonic vehicle comprises the following steps of:
a. according to the similarity criterion of the cold jet flow simulation method, the jet flow parameters of a real reverse-thrust rocket engine and the wind tunnel simulation static pressure parameters, obtaining the jet flow parameters of the inclined cutting jet pipe of the wind tunnel test scaling model; when the five-component thrust balance is calibrated, normal-temperature compressed air with the same pressure as the pressure during measurement is introduced into the normal-temperature compressed air guide pipe; when the five-component thrust balance is used for measuring, keeping the same measurement environment pressure as the wind tunnel simulation static pressure parameter;
b. the beveling nozzle is arranged on the pressure regulating adapter along the direction of 0 degree, which is defined as the first direction, a normal force component N1 of the thrust of the beveling nozzle is measured by adopting a five-component thrust balance, and a pitching moment component Mz1 of which the moment center is positioned at the calibration center of the five-component thrust balance;
c. the bevel spray pipe is arranged on the pressure regulating adapter along the direction of 90 degrees, the direction is defined as a second direction, a normal force component N2 and a lateral force component Z2 generated by the bevel spray pipe are measured by adopting a five-component thrust balance, and a pitching moment component Mz2, a yawing moment component My2 and a rolling moment component Mx2 of which the moment centers are located at the alignment center of the five-component thrust balance;
d. according to five equations of N1-N2, A1-Z2, Mz 1-N1 × d1-A1 × d3, Mx 2-N2 × d2+ Z2 × d3 and Mz 2-N2 × (d1+ d2), the axial force component A1 and the distances d1, d2 and d3 are obtained through measurement data calculation, and the mounting accuracy of the beveling nozzle in the first direction and the second direction is checked through the measurement value of the yaw moment component My 2;
e. according to the measurement and calculation data of the steps b, c and d, the thrust direction and the thrust magnitude of the beveling nozzle and the acting point of the beveling nozzle, which is corrected relative to the five-day-five-component thrust balance, are obtained by resolving and translating the force in the first direction.
The wind tunnel test device for thrust measurement of the hypersonic aircraft oblique cutting nozzle can measure and obtain the thrust direction, the thrust magnitude and the thrust action point of the oblique cutting nozzle.
Drawings
FIG. 1 is a schematic structural diagram of a wind tunnel test device for thrust measurement of a bevel nozzle of a hypersonic vehicle (the bevel nozzle is arranged in a direction of 0 degree);
FIG. 2 is a front cross-sectional view of the wind tunnel test device for thrust measurement of the oblique cutting nozzle of the hypersonic vehicle (the oblique cutting nozzle is arranged in a direction of 0 degree);
FIG. 3 is a schematic structural diagram of the wind tunnel test device for thrust measurement of the oblique cutting nozzle of the hypersonic vehicle (the oblique cutting nozzle is installed in a direction of 90 degrees);
FIG. 4 is a side sectional view of the wind tunnel test device for thrust measurement of the bevel nozzle of the hypersonic vehicle (the bevel nozzle is installed in a 90-degree direction);
FIG. 5 is a partial enlarged view of the wind tunnel test device for thrust measurement of the oblique cutting nozzle of the hypersonic vehicle of the invention;
FIG. 6 is a schematic diagram of a pressure regulating adapter in the wind tunnel test device for thrust measurement of the oblique cutting nozzle of the hypersonic vehicle according to the invention;
FIG. 7 is a cross-sectional view of a bevel nozzle in a wind tunnel test device for thrust measurement of a bevel nozzle of a hypersonic vehicle according to the invention;
FIG. 8 is a schematic diagram of a five-component thrust balance in a wind tunnel test device for thrust measurement of a hypersonic vehicle oblique cutting nozzle of the present invention;
FIG. 9 is a front cross-sectional view of a five-component thrust balance in a wind tunnel test device for thrust measurement of a hypersonic vehicle oblique cutting nozzle of the present invention;
FIG. 10 is a front cross-sectional view of a ventilating strut in a wind tunnel test device for thrust measurement of a beveling nozzle of a hypersonic vehicle according to the invention;
FIG. 11 is a schematic front view of thrust of a beveling nozzle under a body axis in a wind tunnel test device for measuring thrust of the beveling nozzle of a hypersonic vehicle, provided by the invention (the beveling nozzle is installed in a direction of 0 degrees);
FIG. 12 is a schematic front view of thrust of a beveling nozzle under a body axis system (the beveling nozzle is installed in a 90-degree direction) in the wind tunnel test device for measuring the thrust of the beveling nozzle of the hypersonic vehicle;
fig. 13 is a schematic diagram of the thrust of the oblique cutting nozzle under a body axis in a wind tunnel test device for measuring the thrust of the oblique cutting nozzle of the hypersonic vehicle, provided by the invention, from the right side (the oblique cutting nozzle is installed in a 90-degree direction).
In the figure, 1, a beveling spray pipe 2, a pressure regulating adapter 3, a five-component thrust balance 4, a ventilation support rod 5, a spray pipe sealing washer 6, a balance air outlet end sealing washer 7, a balance air inlet end sealing washer 8 and a positioning pin are arranged.
Detailed Description
The invention is described in detail below with reference to the figures and examples.
Example 1
As shown in fig. 1-5, the wind tunnel test device for thrust measurement of the hypersonic aircraft oblique cutting nozzle comprises an oblique cutting nozzle 1, a pressure regulating adapter 2, a five-component thrust balance 3, a ventilating support rod 4, a nozzle sealing washer 5, a balance air outlet end sealing washer 6, a balance air inlet end sealing washer 7 and a positioning pin 8.
As shown in fig. 6, the pressure regulating adapter 2 is a cube, an installation interface of the oblique cutting nozzle 1 is arranged above the pressure regulating adapter 2, the oblique cutting nozzle 1 is fixed on the pressure regulating adapter 2 through screws, and the oblique cutting nozzle 1 and the pressure regulating adapter 2 are sealed through a nozzle sealing washer 5; two groups of positioning pin holes of 0 degree and 90 degrees are arranged at the mounting interface of the beveling spray pipe 1, and the beveling spray pipe 1 is mounted on the pressure-regulating adapter 2 along the direction of 0 degree or 90 degrees according to the test requirements.
The side of the pressure regulating adapter 2 is provided with a mounting interface of the five-component thrust balance 3, the air outlet end of the five-component thrust balance 3 is fixed on the pressure regulating adapter 2 through a screw, and the air outlet end of the five-component thrust balance 3 and the pressure regulating adapter 2 are sealed through a balance air outlet end sealing gasket 6; the air inlet end of the five-component thrust balance 3 is fixed on the ventilating support rod 4 through a screw, and the air inlet end of the five-component thrust balance 3 and the ventilating support rod 4 are positioned through a positioning pin 8 and sealed through a balance air inlet end sealing washer 7.
And a pressure monitoring sensor mounting interface is arranged below the pressure regulating adapter 2.
As shown in fig. 7, the oblique cutting nozzle 1 is a wind tunnel test model nozzle obtained by a real reverse thrust rocket engine contraction ratio according to a similar principle of a cold jet simulation method, the oblique cutting nozzle 1 is a laval nozzle, and a contraction section and an expansion section of the oblique cutting nozzle 1 are both in a conical configuration.
As shown in fig. 8 and 9, the five-component thrust balance 3 is manufactured by using F141 material, a normal temperature compressed air conduit is installed on the axis of the five-component thrust balance 3, and the five-component thrust balance 3 measures five components of normal force, lateral force, pitching moment, yawing moment and rolling moment under a body axis.
As shown in fig. 10, the vent strut 4 is made of 30CrMnSiA material, one end of the vent strut 4 is connected with the air inlet end of the five-component thrust balance 3, the other end of the vent strut 4 is connected with the wind tunnel supporting device, the surface of the vent strut 4 is provided with an angle measuring platform, and a vent pipeline communicated with a normal-temperature compressed air conduit of the five-component thrust balance 3 is arranged inside the vent strut 4.
The spray pipe sealing washer 5, the balance air outlet end sealing washer 6 and the balance air inlet end sealing washer 7 are all made of red copper materials.
The implementation steps of this example are as follows:
a. according to the similarity criterion of the cold jet flow simulation method, the jet flow parameters of a real reverse-thrust rocket engine and the wind tunnel simulation static pressure parameters, obtaining the jet flow parameters of the inclined cutting nozzle 1 of the wind tunnel test scaling model; when the five-component thrust balance 3 is calibrated, normal-temperature compressed air with the same pressure as the pressure during measurement is introduced into the normal-temperature compressed air guide pipe; when the five-component thrust balance 3 is used for measurement, the measured environment pressure is kept to be the same as the wind tunnel simulation static pressure parameter;
b. as shown in fig. 11, the bevel nozzle 1 is mounted on the pressure-regulating adapter 2 along the direction of 0 ° and defined as the direction one, and the normal force component N1 of the thrust of the bevel nozzle 1 and the pitching moment component Mz1 with the moment center located at the center of the five-component thrust balance 3 are measured by using the five-component thrust balance 3;
c. as shown in fig. 12 and 13, the bevel nozzle 1 is mounted on the pressure-regulating adapter 2 along the direction of 90 ° and is defined as the second direction, and a normal force component N2 and a lateral force component Z2 generated by the bevel nozzle 1, and a pitching moment component Mz2, a yawing moment component My2 and a rolling moment component Mx2 with moment centers located at the center of alignment of the five-component thrust balance 3 are measured by using the five-component thrust balance 3;
d. according to five equations of N1-N2, A1-Z2, Mz 1-N1 × d1-A1 × d3, Mx 2-N2 × d2+ Z2 × d3 and Mz 2-N2 × d1+ d2, the axial force component A1 and the distances d1, d2 and d3 are obtained through measurement data calculation, and the mounting accuracy of the beveling nozzle 1 in the first direction and the second direction is checked through the measurement value of the yaw moment component My 2;
e. according to the measurement and calculation data of the steps b, c and d, the thrust direction and the thrust magnitude of the beveled nozzle 1 and the action point of the beveled nozzle 1 in alignment relative to the five-day-five-component thrust balance 3 are obtained by resolving and translating the force in the first direction.
Claims (1)
1. A wind tunnel test method for thrust measurement of a beveling nozzle of a hypersonic vehicle is characterized by comprising the following steps: the wind tunnel test device used by the wind tunnel test method comprises a beveling spray pipe (1), a pressure regulating adapter (2), a five-component thrust balance (3), a ventilating support rod (4), a spray pipe sealing washer (5), a balance air outlet end sealing washer (6), a balance air inlet end sealing washer (7) and a positioning pin (8);
the pressure regulating adapter (2) is a cube, a beveling spray pipe (1) mounting interface is arranged above the pressure regulating adapter (2), the beveling spray pipe (1) is fixed on the pressure regulating adapter (2) through a screw, and the beveling spray pipe (1) and the pressure regulating adapter (2) are sealed through a spray pipe sealing washer (5); two groups of positioning pin holes of 0 degree and 90 degrees are arranged at the mounting interface of the beveling spray pipe (1), and the beveling spray pipe (1) is mounted on the pressure regulating adapter (2) along the direction of 0 degree or 90 degrees according to the test requirements;
a five-component thrust balance (3) mounting interface is arranged on the side of the pressure regulating adapter (2), the air outlet end of the five-component thrust balance (3) is fixed on the pressure regulating adapter (2) through a screw, and the air outlet end of the five-component thrust balance (3) and the pressure regulating adapter (2) are sealed through a balance air outlet end sealing gasket (6); the air inlet end of the five-component thrust balance (3) is fixed on the ventilating support rod (4) through a screw, and the air inlet end of the five-component thrust balance (3) and the ventilating support rod (4) are positioned through a positioning pin (8) and sealed through a balance air inlet end sealing washer (7);
a pressure monitoring sensor mounting interface is arranged below the pressure regulating adapter (2);
the oblique cutting spray pipe (1) is a wind tunnel test model spray pipe obtained by the real reverse thrust rocket engine contraction ratio according to the similar criterion of a cold jet simulation method, the oblique cutting spray pipe (1) is a Laval spray pipe, and the contraction section and the expansion section of the oblique cutting spray pipe (1) are both in a conical configuration;
the five-component thrust balance (3) is made of F141 materials, a normal-temperature compressed air conduit is mounted on the axis of the five-component thrust balance (3), and the five-component thrust balance (3) is used for measuring five components of normal force, lateral force, pitching moment, yawing moment and rolling moment under a body axis system;
the device is characterized in that the ventilating support rod (4) is made of a 30CrMnSiA material, one end of the ventilating support rod (4) is connected with the air inlet end of the five-component thrust balance (3), the other end of the ventilating support rod (4) is connected with the wind tunnel supporting device, the surface of the ventilating support rod (4) is provided with an angle measuring platform, and a ventilating pipeline communicated with a normal-temperature compressed air conduit of the five-component thrust balance (3) is arranged in the ventilating support rod (4);
the spray pipe sealing washer (5), the balance air outlet end sealing washer (6) and the balance air inlet end sealing washer (7) are all made of red copper materials;
the wind tunnel test method for measuring thrust of the oblique cutting nozzle of the hypersonic vehicle comprises the following steps:
a. according to the similarity criterion of the cold jet flow simulation method, the jet flow parameters of a real reverse-thrust rocket engine and the wind tunnel simulation static pressure parameters, the jet flow parameters of the inclined cutting nozzle (1) of the wind tunnel test scaling model are obtained; when the five-component thrust balance (3) is calibrated, normal-temperature compressed air with the same pressure as the pressure during measurement is introduced into the normal-temperature compressed air guide pipe; when the five-component thrust balance (3) is used for measurement, the measured environment pressure is kept to be the same as the wind tunnel simulation static pressure parameter;
b. the beveling nozzle (1) is arranged on the pressure regulating adapter (2) along the 0-degree direction, which is defined as a first direction, a normal force component N1 of the thrust of the beveling nozzle (1) is measured by adopting a five-component thrust balance (3), and a pitching moment component Mz1 of which the moment center is positioned at the correction center of the five-component thrust balance (3);
c. the bevel cutting nozzle (1) is arranged on the pressure regulating adapter (2) along the 90-degree direction, which is defined as a second direction, a normal force component N2 and a lateral force component Z2 generated by the bevel cutting nozzle (1) are measured by adopting a five-component thrust balance (3), and a pitching moment component Mz2, a yawing moment component My2 and a rolling moment component Mx2 of which the moment centers are positioned at the center of alignment of the five-component thrust balance (3);
d. according to five equations of N1-N2, A1-Z2, Mz 1-N1 × d1-A1 × d3, Mx 2-N2 × d2+ Z2 × d3 and Mz 2-N2 × (d1+ d2), the axial force component A1 and the distances d1, d2 and d3 are obtained through measurement data calculation, and the mounting accuracy of the beveling nozzle (1) in the first direction and the second direction is checked through the measurement value of the yaw moment component My 2;
wherein d1 is the distance of the normal force component N1 of the first direction and the five-component thrust balance (3) in the X-axis direction, d2 is the distance of the normal force component N2 of the second direction and the five-component thrust balance (3) in the X-axis direction, and d3 is the distance of the axial force component A1 of the first direction and the five-component thrust balance (3) in the Y-axis direction;
e. according to the measurement and calculation data of the steps b, c and d, the thrust direction and the thrust magnitude of the beveling nozzle (1) are obtained through force decomposition and translation in the opposite direction I, and the action point of the beveling nozzle (1) is calibrated relative to the five-component-per-day thrust balance (3).
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| CN110793746B (en) * | 2019-09-10 | 2024-03-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel test device for measuring thrust of oblique cutting spray pipe of hypersonic vehicle |
| CN115436010B (en) * | 2022-11-08 | 2023-02-03 | 中国空气动力研究与发展中心高速空气动力研究所 | Jet pipe thrust measurement test method based on afterbody and jet pipe integrated design |
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