CN110595729A - Multi-jet flow interference test device for hypersonic wind tunnel surface symmetry model - Google Patents
Multi-jet flow interference test device for hypersonic wind tunnel surface symmetry model Download PDFInfo
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- CN110595729A CN110595729A CN201910851080.4A CN201910851080A CN110595729A CN 110595729 A CN110595729 A CN 110595729A CN 201910851080 A CN201910851080 A CN 201910851080A CN 110595729 A CN110595729 A CN 110595729A
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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
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
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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
- G01M9/08—Aerodynamic models
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Abstract
The invention discloses a multi-jet flow interference test device for a hypersonic wind tunnel surface symmetry model. The device comprises a model device and a jet device. The device has comprehensively considered the requirement that the test device supported the model, the air feed of many spouts, the room structure of staying, and the air feed branch possesses the function that the model supported and multichannel spout air feed, and the room of staying possesses the function that different spouts of equidirectional different spouts total pressures independently air feed, and the whole set of test device easily installs and removes, convenient to use. The wind tunnel test device solves the key technical problems of model support, realization of independent simulation of multiple jet flows in a limited narrow space and the like in the current wind tunnel test, ensures the similarity of the protective cover, does not introduce additional interference which is difficult to correct, and obtains reliable pneumatic load data of the protective cover under the interaction of multiple paths of reverse jet flows and incoming flows.
Description
Technical Field
The invention belongs to the technical field of hypersonic wind tunnel tests, and particularly relates to a multi-jet interference test device for a hypersonic wind tunnel surface symmetry model.
Background
At present, attitude control of various aircraft protective covers is mostly realized by arranging a plurality of thrust reversal rocket engines on the protective covers, interaction between multiple jet flows and flows is very obvious under the hypersonic speed condition, and the aerodynamic characteristics and the static stability of the protective covers are seriously influenced by the interference of the multiple jet flows, so that the aerodynamic characteristics and the static stability of the hypersonic speed protective covers during the interference of the multiple jet flows are obtained through wind tunnel tests, and the method has important significance for design of the protective covers.
However, due to the size limitation of a test model, the current hypersonic wind tunnel multi-jet interference test cannot realize full-size simulation, and the problems of small model, narrow internal space, complex structural design and the like exist, so that a plurality of problems are brought to test measurement.
Disclosure of Invention
The invention aims to provide a multi-jet flow interference test device for a hypersonic wind tunnel surface symmetry model.
The invention relates to a multi-jet flow interference test device for a hypersonic wind tunnel surface symmetry model, which is characterized in that the test device comprises a model device and a jet flow device;
the model device comprises a protective cover head, a protective cover tail, a six-component ring balance, an air supply support rod, a tail support rod, a balance sleeve, a bottom cover plate and a jet flow cover plate; the protective cover comprises a protective cover head, a jet flow cover plate, a gas supply support rod, a tail support rod, a middle flange, a six-component ring balance, a gap, a balance sleeve, a bottom cover plate and a balance sleeve, wherein the protective cover head and the jet flow cover plate are integrally formed; the tail part of the protective cover is fixed on the front end surface of the six-component ring type balance, the head part of the protective cover is arranged on the tail part of the protective cover, and the head part of the protective cover and the tail part of the protective cover are in smooth transition;
the jet flow device comprises a reverse thrust jet pipe, a parking chamber, a support rod end face flange, an air supply support rod and a red copper pipeline; the thrust-back spray pipe and the parking chamber are integrally processed and formed, the red copper pipeline is welded on the rear end conical surface of the tail support rod and is communicated with the air supply support rod and the ventilation pipeline inside the tail support rod, the support rod end face flange is arranged at the front end of the air supply support rod through threads, and the parking chamber is fixed on the support rod end face flange; the red copper pipeline is communicated with an external air source; normal-temperature compressed air of an external air source enters the reverse thrust spray pipe through the red copper pipeline, the ventilation pipeline inside the air supply supporting rod and the tail supporting rod and the parking chamber to form jet flow.
The ventilation pipelines in the air supply supporting rod and the tail supporting rod are divided into two groups of ventilation pipelines for independent air supply, one group of ventilation pipelines provides side-push jet flow, and the other group of ventilation pipelines provides shaft-push jet flow.
The protective cover head and the jet flow cover plate are integrally processed and replaced by a plurality of independent protective cover heads, and each protective cover head corresponds to a jet flow state.
The middle flange of the air supply supporting rod is provided with an inner ring positioning mounting hole and an outer ring positioning mounting hole along the circumferential direction, the inner hexagonal counter bore and the pin hole which are uniformly distributed on the inner ring are used for fixing the six-component ring type balance on the front end face of the air supply supporting rod flange, and the threaded holes which are uniformly distributed on the outer ring are used for fixing the balance sleeve on the rear end face of the air supply supporting rod flange.
The number of the stagnation chambers is 3, and the stagnation chambers are respectively a single spraying stagnation chamber, two spraying stagnation chambers and a plurality of spraying stagnation chambers, and the single spraying stagnation chamber is communicated with a ventilation pipeline of side-push jet flow; the two spraying chambers are communicated with a ventilation pipeline of the shaft-pushing jet flow; the multi-spraying room is provided with a clapboard which divides the room into a plurality of independent rooms, and each independent room is communicated with a ventilation pipeline of side-push spraying flow or a ventilation pipeline of shaft-push spraying flow.
The shape of the conical nozzle of the reverse thrust nozzle is consistent with that of the head of the protective cover; the relationship between the short-side outlet cross section of the thrust-back nozzle and the cross section of the nozzle throat conforms to the simulation criteria of equal jet pressure ratio and similar jet momentum.
The contact surfaces of all parts in the vent pipeline are sealed by red copper gaskets.
The reverse thrust jet pipe extends out of the interior of the model, is not in contact with the model, has a gap width range of 0.5-0.8 mm, and avoids the direct action of the thrust of the reverse thrust jet flow on the six-component ring balance.
The balance sleeve is connected with the rear end of the middle flange of the air supply supporting rod, is not in contact with the model and the balance, has a gap width range of 1-2 mm, and avoids influencing the force measurement of the balance.
The bottom cover plate is connected with the balance sleeve, is not in contact with the model, has a gap width range of 1-2 mm, and avoids influencing the balance force measurement.
The six-component ring balance used in the multi-jet interference test device of the hypersonic wind tunnel surface symmetry model is of an internal hollow structure, an air supply support rod is allowed to penetrate through the middle of the balance, and two ends of the balance are connected through flanges.
The thrust-back spray pipe and the parking chamber in the multi-jet interference test device for the hypersonic wind tunnel surface symmetry model are core components of a jet flow device and are used for simulating gas jet flow of a thrust-back rocket engine. The multi-spraying room is divided into an upper small room and a lower small room by a partition board, and the pressure in the small rooms can be independently adjusted to meet the requirements of different total pressures of the spraying flow in different directions. A pressure monitoring hole is formed in the wall surface of the parking chamber, and is used for installing a pressure sensor when jet pressure is adjusted so as to judge whether the pressure of the parking chamber meets the requirement or not; between the room and the air supply supporting rod, a small bulge and a small groove are used for circumferential positioning, a red copper gasket is used for sealing, and a supporting rod end face flange is arranged at the front end of the air supply supporting rod and is connected with the room through a screw.
In the area behind the short-side outlet of the thrust-back nozzle in the multi-jet interference test device for the hypersonic wind tunnel surface symmetry model, jet flow parameters are not uniform on the cross section perpendicular to the axis of the nozzle. When the spray pipe is designed, the cross section of the short side outlet of the conical nozzle is used as the theoretical outlet of the spray pipe, and the jet flow parameters on the cross section are used as the input parameters of the reverse-thrust jet flow simulation.
The multi-jet flow interference test device for the hypersonic wind tunnel surface symmetry model has the following advantages:
1. the supporting parts are all positioned in the protective cover, the integrity of the protective cover is not damaged, and an interference flow field of the interaction of the reverse-thrust jet flow and the incoming flow is not damaged by other interference factors.
2. Each spare part easy dismounting, sound construction is reliable.
3. When the jet flow is closed, the design of the protective cover with the jet flow cover plate can ensure the integrity of the appearance of the protective cover.
4. The gas supply supporting rod and the tail supporting rod are processed into a whole, and the multi-way ventilation pipeline is positioned inside the supporting rods, is stably connected and is not influenced by the interference of an external flow field.
5. The integrated design of the standing chamber is convenient to connect, and the independent control of the reverse thrust jet flow in different total pressures in different directions in a limited space can be realized.
The invention relates to a multi-jet interference test device for a hypersonic wind tunnel surface symmetry model, which is a model and a jet device designed based on an integrated idea, wherein the device comprehensively considers the requirements of the test device on model support, multi-jet air supply and chamber standing structure, an air supply support rod has the functions of model support and multi-path jet air supply, the chamber standing structure has the functions of different jet total pressure independent air supply in different directions, and the whole set of test device is easy to assemble and disassemble and convenient to use. The multi-jet interference test device for the hypersonic wind tunnel surface symmetry model solves the key technical problems of model support, realization of multi-jet independent simulation in a limited narrow space and the like in the conventional wind tunnel test, ensures the similarity of the protection cover, does not introduce extra interference which is difficult to correct, and obtains reliable pneumatic load data of the protection cover under the interaction of multi-path reverse-thrust jets and incoming flow.
Drawings
FIG. 1 is a schematic structural diagram (front view) of a multi-jet disturbance testing device for a hypersonic wind tunnel surface symmetry model according to the present invention;
FIG. 2 is a schematic structural diagram (cross-sectional view) of a multi-jet disturbance testing device for a hypersonic wind tunnel surface symmetry model according to the invention;
FIG. 3 is a partial enlarged view of the multi-jet disturbance testing device for the surface symmetry model of the hypersonic wind tunnel according to the invention;
FIG. 4a is a schematic structural diagram (three-jet) of a head of a protective cover in the multi-jet interference testing device for the surface symmetry model of the hypersonic wind tunnel according to the present invention;
FIG. 4b is a schematic structural diagram (double jet) of a head of a protective cover in the multi-jet interference testing device for the surface symmetry model of the hypersonic wind tunnel according to the present invention;
FIG. 4c is a schematic structural diagram (single jet) of a head of a protective cover in the multi-jet interference testing device for the surface symmetry model of the hypersonic wind tunnel according to the present invention;
FIG. 4d is a schematic structural diagram (no jet) of a head of a protective cover in the multi-jet interference testing apparatus for the surface symmetry model of the hypersonic wind tunnel according to the present invention;
FIG. 5a is a schematic structural diagram (three-jet) of a stagnation chamber in the multi-jet interference testing apparatus for the surface symmetry model of the hypersonic wind tunnel according to the present invention;
FIG. 5b is a schematic structural diagram (double jet) of a stagnation chamber in the multi-jet disturbance testing apparatus for the surface symmetry model of the hypersonic wind tunnel according to the present invention;
FIG. 5c is a schematic structural diagram (single jet) of a stagnation chamber in the multi-jet disturbance testing apparatus for the surface symmetry model of the hypersonic wind tunnel according to the present invention;
FIG. 6 is a partial enlarged view of a thrust reverser nozzle in the multi-jet disturbance testing device for the surface symmetry model of the hypersonic wind tunnel.
In the figure, 1, a protective cover head 2, a protective cover tail 3, a reverse thrust spray pipe 4, a parking chamber 5, a support rod end face flange 6, a six-component ring balance 7, an air supply support rod 8, a red copper pipeline 9, a tail support rod 10, a balance sleeve 11, a bottom cover plate 12 and a jet flow cover plate are arranged.
Detailed Description
The invention is described in detail below with reference to the figures and examples.
As shown in FIGS. 1 to 3, the wind tunnel test device for the multi-jet interference of the surface-symmetric hypersonic protective cover comprises a model device and a jet device;
the model device comprises a protective cover head 1, a protective cover tail 2, a six-component ring balance 6, an air supply support rod 7, a tail support rod 9, a balance sleeve 10, a bottom cover plate 11 and a jet flow cover plate 12; the protective cover comprises a protective cover head 1, a jet flow cover plate 12, a gas supply strut 7, a tail strut 9, a gas pipeline, a middle flange, a six-component ring balance 6, a gap, a balance sleeve 10, a bottom cover plate 11, a balance sleeve 10 and the bottom cover plate 11, wherein the protective cover head 1 and the jet flow cover plate 12 are integrally formed, the gas supply strut 7 and the tail strut 9 are integrally formed, the gas pipeline is arranged inside the gas supply strut 7 and the tail strut 9, the middle flange is arranged in the middle of the gas supply strut 7, the six-component ring balance 6 is sleeved on the gas supply strut 7, the gap is reserved between the six-component ring balance 6 and the gas supply strut 7, the rear end face of the six-component ring balance 6 is fixed on the; the protective cover tail part 2 is fixed on the front end face of the six-component ring type balance 6, the protective cover head part 1 is arranged on the protective cover tail part 2, and the protective cover head part 1 and the protective cover tail part 2 are in smooth transition;
the jet flow device comprises a reverse thrust jet pipe 3, a parking chamber 4, a support rod end face flange 5, an air supply support rod 7 and a red copper pipeline 8; the thrust-back spray pipe 3 and the parking chamber 4 are integrally processed and formed, a red copper pipeline 8 is welded on the rear end conical surface of the tail support rod 9 and is communicated with the air supply support rod 7 and the air vent pipeline inside the tail support rod 9, the support rod end surface flange 5 is installed at the front end of the air supply support rod 7 through threads, and the parking chamber 4 is fixed on the support rod end surface flange 5; the red copper pipeline 8 is communicated with an external air source; normal-temperature compressed air from an external air source enters the thrust-back spray pipe 3 through the red copper pipeline 8, the ventilation pipelines inside the air supply supporting rod 7 and the tail supporting rod 9 and the stagnation chamber 4 to form jet flow.
The ventilation pipelines in the air supply strut 7 and the tail strut 9 are divided into two groups of ventilation pipelines for independent air supply, one group of ventilation pipelines provides side-push jet flow, and the other group of ventilation pipelines provides shaft-push jet flow.
As shown in fig. 4a to 4d, the protective cover head 1 and the jet cover plate 12 are integrally formed and replaced by a plurality of independent protective cover heads 1, and each protective cover head 1 corresponds to a jet state.
The middle flange of the air supply supporting rod 7 is provided with an inner ring positioning mounting hole and an outer ring positioning mounting hole along the circumferential direction, the inner hexagonal counter bore and the pin hole which are uniformly distributed on the inner ring are used for fixing the six-component ring balance 6 on the front end face of the flange of the air supply supporting rod 7, and the threaded holes which are uniformly distributed on the outer ring are used for fixing the balance sleeve 10 on the rear end face of the flange of the air supply supporting rod 7.
As shown in fig. 5a-5c, there are 3 kinds of said stagnation chambers 4, including a single stagnation chamber, two stagnation chambers and a plurality of stagnation chambers, the single stagnation chamber is communicated with the ventilation pipeline of the side-push jet; the two spraying chambers are communicated with a ventilation pipeline of the shaft-pushing jet flow; the multi-spraying room is provided with a partition board which divides the room 4 into a plurality of independent rooms, and each independent room is communicated with a ventilation pipeline of side-push spraying flow or a ventilation pipeline of shaft-push spraying flow.
As shown in fig. 6, the conical nozzle of the thrust-back nozzle 3 is in accordance with the shape of the protective cover head 1; the relationship between the short-side outlet cross section of the thrust-back nozzle 3 and the nozzle throat cross section accords with the simulation criteria of equal jet pressure ratio and similar jet momentum.
The contact surfaces of all parts in the vent pipeline are sealed by red copper gaskets.
The thrust-back spray pipe 3 extends out of the interior of the model, is not in contact with the model, has a gap width range of 0.5-0.8 mm, and avoids thrust of thrust-back spray flow from directly acting on the six-component ring balance 6.
The balance sleeve 10 is connected with the rear end of the middle flange of the air supply supporting rod 7, is not in contact with the model and the balance, has the gap width range of 1-2 mm, and avoids influencing the force measurement of the balance.
The bottom cover plate 11 is connected with the balance sleeve 10 and is not in contact with a model, the width range of the gap is 1-2 mm, and the balance force measurement is prevented from being influenced.
Example 1
In this embodiment, the jet flow device is first assembled and mounted on the air supply strut 7, and after the jet flow pressure is adjusted, the jet flow device and the model device are assembled together to form a complete test device.
1. Assembling a jet flow device and debugging jet flow pressure, and completing the steps as follows:
1a, screwing a support rod end face flange 5 at the front end of an air supply support rod 7 through threads;
1b, a parking chamber 4 is arranged on a flange 5 on the end face of the support rod in a flange butt joint mode, a boss positioning mode, a red copper gasket sealing mode and an inner hexagon screw fastening mode;
1c, after the jet flow device is assembled, connecting a red copper pipeline 8 to a wind tunnel wall air source, and installing a sensor for monitoring the pressure of the parking chamber on the parking chamber 4;
1d, ventilating in a test mode, checking whether an air supply pipeline and a jet flow device leak air or not, after leakage detection is finished, debugging the pressure of each small parking chamber of the parking chamber 4 to a target value, and recording parameters of a wind tunnel cold jet flow control system;
1e, replacing the parking chamber 4, repeating the steps 1 b-1 d, and obtaining the parameters of the wind tunnel cold jet flow control system corresponding to the target pressure of the backward thrust nozzle parking chamber when the parking chamber is used.
2. After the jet flow pressure is debugged, the jet flow device and the model device are assembled together to form a test device, a wind tunnel test is carried out, and the method comprises the following steps:
2a, mounting the integrally processed air supply strut 7 and tail strut 9 on an attack angle mechanism of the wind tunnel;
2b, a six-component ring balance 6 penetrates through the gas supply support rod 7 and is arranged at the front end of a flange in the middle of the gas supply support rod 7 in a flange butt joint, inner hexagon screw fastening and pin positioning mode;
2c, the tail part 2 of the protective cover is arranged at the front end of the six-component ring type balance 6 in a flange butt joint mode, an inner hexagonal screw fastening mode and a pin positioning mode;
2d, fastening the balance sleeve 10 at the rear end of the middle flange of the gas supply strut 7 through a hexagon socket head cap screw;
2e, fixing the bottom cover plate 11 on the rear end face of the balance sleeve 10 in a cross countersunk head screw mode;
2f, screwing the support rod end face flange 5 at the front end of the air supply support rod 7 through threads;
2g, mounting a parking chamber 4 on a flange 5 on the end face of the support rod in a flange butt joint mode, a boss positioning mode, a red copper gasket sealing mode and an inner hexagon screw fastening mode;
2h, mounting the head part 1 of the protective cover on the tail part 2 of the protective cover in a cross countersunk head screw fastening mode;
2i, connecting a red copper pipeline 8 to a wind tunnel wall air source, and installing a sensor for monitoring the pressure of the parking chamber on the parking chamber 4;
2j, developing a wind tunnel test, and collecting and processing test data;
2k, disassembling the test device according to the reverse order of the assembly until the parking chamber 4 is disassembled;
and 2l, replacing the parking chamber 4, installing the protective cover head 1 matched with the parking chamber 4, and then carrying out a corresponding wind tunnel test.
The present invention is not limited to the above-described embodiments, and those skilled in the art will be able to make various modifications without creative efforts from the above-described conception, and fall within the scope of the present invention.
Claims (10)
1. A multi-jet flow interference test device for a hypersonic wind tunnel surface symmetry model is characterized in that: the test device comprises a model device and a jet flow device;
the model device comprises a protective cover head (1), a protective cover tail (2), a six-component ring balance (6), an air supply support rod (7), a tail support rod (9), a balance sleeve (10), a bottom cover plate (11) and a jet flow cover plate (12); the utility model discloses a safety cover, including safety cover head (1) and jet flow apron (12) integrated into one piece, air feed branch (7) and tail branch (9) integrated into one piece, there is the air vent line inside air feed branch (7) and tail branch (9), there is the middle flange at the middle part of air feed branch (7), six weight ring balance (6) cover is on air feed branch (7), leave the gap between six weight ring balance (6) and air feed branch (7), the rear end face of six weight ring balance (6) is fixed on the preceding terminal surface of middle flange, balance sleeve (10) are installed on the rear end face of middle flange, six weight ring balance (6) stretch into in balance sleeve (10), the bottom cover plate (11) is fixed on the rear end face of the balance sleeve (10), and the balance sleeve (10) and the bottom cover plate (11) protect the six-component ring balance (6) from being influenced by environmental airflow; the protective cover tail part (2) is fixed on the front end face of the six-component ring type balance (6), the protective cover head part (1) is arranged on the protective cover tail part (2), and the protective cover head part (1) and the protective cover tail part (2) are in smooth transition;
the jet flow device comprises a reverse thrust spray pipe (3), a parking chamber (4), a support rod end face flange (5), an air supply support rod (7) and a red copper pipeline (8); the reverse thrust spray pipe (3) and the parking chamber (4) are integrally processed and formed, a red copper pipeline (8) is welded on the conical surface of the rear end of the tail support rod (9) and is communicated with the air supply support rod (7) and the ventilation pipeline inside the tail support rod (9), the support rod end face flange (5) is installed at the front end of the air supply support rod (7) through threads, and the parking chamber (4) is fixed on the support rod end face flange (5); the red copper pipeline (8) is communicated with an external air source; normal-temperature compressed air of an external air source enters the reverse thrust spray pipe (3) through the red copper pipeline (8), the ventilation pipeline inside the air supply supporting rod (7) and the tail supporting rod (9) and the stagnation chamber (4) to form jet flow.
2. The multi-jet disturbance testing device for the hypersonic wind tunnel surface symmetry model according to claim 1, characterized in that: the ventilation pipelines in the air supply supporting rod (7) and the tail supporting rod (9) are divided into two groups of ventilation pipelines for independent air supply, one group of ventilation pipelines provides side-push jet flow, and the other group of ventilation pipelines provides shaft-push jet flow.
3. The multi-jet disturbance testing device for the hypersonic wind tunnel surface symmetry model according to claim 1, characterized in that: the protective cover head (1) and the jet flow cover plate (12) are integrally machined, formed and replaced by a plurality of independent protective cover heads (1), and each protective cover head (1) corresponds to a jet flow state.
4. The multi-jet disturbance testing device for the hypersonic wind tunnel surface symmetry model according to claim 1, characterized in that: the middle flange of air feed branch (7) have inside and outside two rings location mounting hole along circumference, the hexagon socket head hole and the cotter hole of inner circle equipartition are used for fixing six weight ring balance (6) terminal surface before air feed branch (7) flange, the screw hole of outer lane equipartition is used for fixing balance sleeve (10) at air feed branch (7) flange rear end face.
5. The multi-jet disturbance testing device for the hypersonic wind tunnel surface symmetry model according to claim 1, characterized in that: the number of the chambers (4) is 3, the chambers are respectively a single spraying chamber, two spraying chambers and a plurality of spraying chambers, and the single spraying chamber is communicated with a ventilation pipeline of side-push jet flow; the two spraying chambers are communicated with a ventilation pipeline of the shaft-pushing jet flow; the multi-spraying room is provided with a partition board which divides the room (4) into a plurality of independent rooms, and each independent room is communicated with a ventilation pipeline of side-push spraying flow or a ventilation pipeline of shaft-push spraying flow.
6. The multi-jet disturbance testing device for the hypersonic wind tunnel surface symmetry model according to claim 1, characterized in that: the shape of the conical nozzle of the thrust-back spray pipe (3) is consistent with that of the protective cover head part (1); the relationship between the short-side outlet cross section of the thrust-back nozzle (3) and the nozzle throat cross section accords with the simulation criteria of equal jet pressure ratio and similar jet momentum.
7. The multi-jet disturbance testing device for the hypersonic wind tunnel surface symmetry model according to claim 1, characterized in that: the contact surfaces of all parts in the vent pipeline are sealed by red copper gaskets.
8. The multi-jet disturbance testing device for the hypersonic wind tunnel surface symmetry model according to claim 1, characterized in that: the thrust-back spray pipe (3) extends out of the interior of the model, is not in contact with the model, has a gap width range of 0.5-0.8 mm, and avoids the thrust of thrust-back spray flow from directly acting on the six-component ring balance (6).
9. The multi-jet disturbance testing device for the hypersonic wind tunnel surface symmetry model according to claim 1, characterized in that: the balance sleeve (10) is connected with the rear end of the middle flange of the air supply supporting rod (7), is not in contact with the model and the balance, has a gap width range of 1-2 mm, and avoids influencing the force measurement of the balance.
10. The multi-jet disturbance testing device for the hypersonic wind tunnel surface symmetry model according to claim 1, characterized in that: the bottom cover plate (11) is connected with the balance sleeve (10) and is not in contact with the model, the width range of the gap is 1-2 mm, and the balance force measurement is prevented from being influenced.
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| CN111780941A (en) * | 2020-07-23 | 2020-10-16 | 北京空天技术研究所 | Aircraft force measurement test model and method |
| CN112763177A (en) * | 2020-12-25 | 2021-05-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Rail-controlled jet flow interference test device based on rod type balance and installation and positioning method thereof |
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| CN115436010A (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 | Jet pipe thrust measurement test method based on afterbody and jet pipe integrated design |
| CN115628874A (en) * | 2022-12-20 | 2023-01-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel closed test section model supporting device |
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| CN115791069A (en) * | 2023-01-09 | 2023-03-14 | 中国空气动力研究与发展中心超高速空气动力研究所 | Device with position-adjustable sealing spray pipe in wind tunnel test and application method |
| CN115808285A (en) * | 2023-01-11 | 2023-03-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Deep hole sealing assembly in wind tunnel jet test and application method |
| CN117740308A (en) * | 2024-02-19 | 2024-03-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Jet micro-embedded turbulence method and device for controlling large-scale high-speed jet noise |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111780941A (en) * | 2020-07-23 | 2020-10-16 | 北京空天技术研究所 | Aircraft force measurement test model and method |
| CN112763177A (en) * | 2020-12-25 | 2021-05-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Rail-controlled jet flow interference test device based on rod type balance and installation and positioning method thereof |
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