CN110793746A - Wind tunnel test device for thrust measurement of oblique cutting nozzle of hypersonic vehicle - Google Patents
Wind tunnel test device for thrust measurement of oblique cutting nozzle of hypersonic vehicle Download PDFInfo
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- 238000012360 testing method Methods 0.000 title claims abstract description 43
- 238000005259 measurement Methods 0.000 title claims abstract description 29
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- 230000001105 regulatory effect Effects 0.000 claims abstract description 35
- 238000007789 sealing Methods 0.000 claims abstract description 33
- 238000000034 method Methods 0.000 claims abstract description 10
- 238000012544 monitoring process Methods 0.000 claims abstract description 4
- 239000000463 material Substances 0.000 claims description 9
- 238000004088 simulation Methods 0.000 claims description 8
- 238000009423 ventilation Methods 0.000 claims description 8
- 230000008602 contraction Effects 0.000 claims description 5
- 238000005096 rolling process Methods 0.000 claims description 4
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052802 copper Inorganic materials 0.000 claims description 3
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- 238000010586 diagram Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 3
- 239000002737 fuel gas Substances 0.000 description 2
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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Abstract
The invention discloses a wind tunnel test device for thrust measurement of a beveling nozzle of a hypersonic vehicle. The wind tunnel test device comprises a beveling spray pipe, a pressure regulating adapter, a five-component thrust balance, a ventilating support rod, a spray pipe sealing gasket, a balance air outlet end sealing gasket, a balance air inlet end sealing gasket and a positioning pin; the pressure regulating adapter is the square, and the top of pressure regulating adapter has oblique cutting spray tube installation interface, and side has five quanta thrust balance installation interfaces, and the below has pressure monitoring sensor installation interface. The air outlet end of the five-component thrust balance is fixed on the pressure regulating adapter, and the air inlet end of the five-component thrust balance is fixed on the ventilating support rod through a screw. The wind tunnel test device can measure and obtain the thrust direction, the thrust magnitude and the thrust action point of the oblique cutting nozzle, solves 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 device 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 device and 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 are needed to be developed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a wind tunnel test device for thrust measurement of a beveling nozzle of a hypersonic vehicle.
The invention relates to a wind tunnel test device for thrust measurement of a beveling nozzle of a hypersonic vehicle, which is characterized in that: the wind tunnel test device comprises a beveling spray pipe, a pressure regulating adapter, a five-component thrust balance, a ventilating support rod, a spray pipe sealing gasket, a balance air outlet end sealing gasket, a balance air inlet end sealing gasket 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 device for thrust measurement of the oblique cutting nozzle of the hypersonic vehicle can measure and obtain the thrust direction, the thrust magnitude and the thrust action point of the oblique cutting nozzle, solves 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 for obtaining the thrust of a real rocket engine.
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.
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.
Example 1
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 (5)
1. A wind tunnel test device for hypersonic vehicle oblique cutting spray tube thrust measurement, its characterized in that: the wind tunnel test device 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);
and a pressure monitoring sensor mounting interface is arranged below the pressure regulating adapter (2).
2. The wind tunnel test device for thrust measurement of the oblique cutting nozzle of the hypersonic vehicle according to claim 1, wherein: 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 principle 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.
3. The wind tunnel test device for thrust measurement of the oblique cutting nozzle of the hypersonic vehicle according to claim 1, wherein: the five-component thrust balance (3) is made of F141 materials, 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) is used for measuring five components of normal force, lateral force, pitching moment, yawing moment and rolling moment under a body shaft system.
4. The wind tunnel test device for thrust measurement of the oblique cutting nozzle of the hypersonic vehicle according to claim 1, wherein: the wind tunnel ventilation device is characterized in that the ventilation support rod (4) is made of a 30CrMnSiA material, one end of the ventilation support rod (4) is connected with the air inlet end of the five-component thrust balance (3), the other end of the ventilation support rod (4) is connected with the wind tunnel supporting device, an angle measuring platform is arranged on the surface of the ventilation support rod (4), and a ventilation pipeline communicated with a normal-temperature compressed air conduit of the five-component thrust balance (3) is arranged in the ventilation support rod (4).
5. The wind tunnel test device for thrust measurement of the oblique cutting nozzle of the hypersonic vehicle according to claim 1, wherein: 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.
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Cited By (6)
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| CN112485012A (en) * | 2020-11-13 | 2021-03-12 | 东北大学 | Solid rocket engine experiment table and stress testing method |
| CN113280995A (en) * | 2021-07-19 | 2021-08-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Cooling device for high-temperature wind tunnel model |
| CN113588201A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Thermal jet flow interference test device and test method for high-altitude high-speed thin environment |
| CN113899516A (en) * | 2021-09-30 | 2022-01-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ground simulation device and method for rocket engine jet flow interference effect |
| CN115356114A (en) * | 2022-10-24 | 2022-11-18 | 中国空气动力研究与发展中心空天技术研究所 | Connecting piece, ground direct connection test thrust measurement system and measurement method thereof |
| CN115436009A (en) * | 2022-11-08 | 2022-12-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Nozzle thrust measurement test system with integrated rear body and nozzle |
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| CN112485012A (en) * | 2020-11-13 | 2021-03-12 | 东北大学 | Solid rocket engine experiment table and stress testing method |
| CN113280995A (en) * | 2021-07-19 | 2021-08-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Cooling device for high-temperature wind tunnel model |
| CN113280995B (en) * | 2021-07-19 | 2022-02-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Cooling device for high-temperature wind tunnel model |
| CN113588201A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Thermal jet flow interference test device and test method for high-altitude high-speed thin environment |
| CN113899516A (en) * | 2021-09-30 | 2022-01-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ground simulation device and method for rocket engine jet flow interference effect |
| CN113588201B (en) * | 2021-09-30 | 2022-04-12 | 中国空气动力研究与发展中心超高速空气动力研究所 | Thermal jet flow interference test device and test method for high-altitude high-speed thin environment |
| CN115356114A (en) * | 2022-10-24 | 2022-11-18 | 中国空气动力研究与发展中心空天技术研究所 | Connecting piece, ground direct connection test thrust measurement system and measurement method thereof |
| CN115436009A (en) * | 2022-11-08 | 2022-12-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Nozzle thrust measurement test system with integrated rear body and nozzle |
| CN115436009B (en) * | 2022-11-08 | 2023-01-31 | 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 system with integrally designed afterbody and jet pipe |
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