CN112683485A - Air inlet channel test simulation device and simulation method - Google Patents
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- CN112683485A CN112683485A CN202110268613.3A CN202110268613A CN112683485A CN 112683485 A CN112683485 A CN 112683485A CN 202110268613 A CN202110268613 A CN 202110268613A CN 112683485 A CN112683485 A CN 112683485A
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Abstract
The invention is suitable for the technical field of wind tunnel tests and provides an air inlet channel test simulation device and a simulation method, wherein the air inlet channel test simulation device comprises: the device comprises a model supporting assembly, a model supporting rod, a model, a flow simulator, a simulator supporting assembly and a flexible air suction pipe, wherein the model supporting assembly is connected with the outer periphery of the model through the model supporting rod; one end of the flexible air suction pipe is connected with an air outlet of the model, and the other end of the flexible air suction pipe is connected with an air inlet of the flow simulator; the flow simulator is supported on the simulator support assembly, which is adaptively adjustable as the model support assembly is adjusted. The invention can improve the quality of test data and the test efficiency.
Description
Technical Field
The invention belongs to the technical field of wind tunnel tests, and particularly relates to an air inlet channel test simulation device and method.
Background
In the performance test of the air inlet passage of the low-speed wind tunnel aircraft, the accurate simulation of the flow of the air inlet passage is a key technical link; in a low-speed wind tunnel without a vacuum air suction system, the injection action of an injection type flow simulator is usually used for simulating the flow of an air inlet. As shown in fig. 1, the air inlet passage test simulation device in the prior art discloses a method in the literature of "low-speed wind tunnel air inlet passage test cylindrical distributed ejector optimization design, wukorojun and the like, and aeronautical dynamics science report", when the method is adopted, a model 1 'is fixed in a wind tunnel test section through a supporting device 2' capable of changing an attack angle and a sideslip angle, in order to ensure that the influence of high-speed airflow sprayed by an injection type flow simulator 3 'during working on a local flow field of an aircraft is as small as possible, the injection type flow simulator 3' needs to be fixed on a lower tunnel wall 4 'far away from the model at the downstream of the flow field, the model is connected with the injection type flow simulator 3' through an air suction pipeline 5 ', and 7' is an air inlet passage/engine pneumatic interface.
The prior art can meet the basic requirements of a common air inlet test. However, the prior art has the following defects: (1) the total blockage degree of the model, the injection type flow simulator and other devices on the windward side in the wind tunnel flow field is increased, the adverse effect is generated on the wind tunnel flow field and the like, and the local flow field of the inlet 6' of the air inlet channel of the model is obviously distorted; (2) when the variation ranges of the attack angle and the sideslip angle of the model are large, the relative position between the model and the injection type flow simulator is caused to vary greatly, the effective windward area formed by the model, the injection type flow simulator and the supporting device is increased, the blockage degree in a flow field is increased, and meanwhile, the injection type flow simulator/the air suction pipeline/the model are mutually interfered, so that the test range requirement of the limit attitude angle cannot be completely met; (3) the air suction pipeline between the model and the injection type flow simulator can also be bent greatly, so that the pressure loss of air flow in the pipeline is increased, the efficiency of the injection type flow simulator is greatly reduced, and the flow simulation of the global working range of the air inlet channel is influenced.
In summary, the prior art has drawbacks in terms of test data quality and test efficiency.
Disclosure of Invention
The invention aims to provide an air inlet channel test simulation device and method, and aims to solve the technical problems of poor test data quality and low test efficiency in the prior art.
In a first aspect, the present invention provides an air inlet channel test simulation apparatus, which includes: the device comprises a model supporting assembly, a model supporting rod, a model, a flow simulator, a simulator supporting assembly and a flexible air suction pipe, wherein the model supporting assembly is connected with the outer periphery of the model through the model supporting rod;
one end of the flexible air suction pipe is connected with an air outlet of the model, and the other end of the flexible air suction pipe is connected with an air inlet of the flow simulator;
the flow simulator is supported on the simulator support assembly, which is adaptively adjustable as the model support assembly is adjusted.
Furthermore, the model supporting component can drive the model to move in the X, Y, Z direction and rotate around the Y direction through the model supporting rod, wherein the X direction refers to the central direction of the wind tunnel test section, the Y direction refers to the vertical direction of the wind tunnel test section, and the Z direction refers to the horizontal direction of the wind tunnel test section.
Further, simulator supporting component is including the movable support seat that can follow Y and Z direction removal, the top of movable support seat is provided with the slide rail along the X direction, be provided with the slider that can follow the slide rail removal on the slide rail be fixed with sliding connection board on the slider, the last bearing clamp that is provided with of sliding connection board, slewing bearing's outer lane and bearing clamp interference fit, slewing bearing's inner circle and bearing connection board fixed connection, flow simulator supporting seat fixed mounting be in on the bearing connection board, the flow simulator is installed on the flow simulator supporting seat, slewing bearing's axis is located vertical direction.
In a second aspect, the present invention provides an air inlet channel test simulation method, which includes the following steps:
step S10: arranging the air inlet channel test simulation device on a wind tunnel test section;
step S20: adjusting the model to enable the attitude angle of the model to meet the test requirement;
step S30: causing the simulator support assembly to follow the movement;
step S40: and (5) carrying out air inlet channel test simulation.
Further, the step S20 adjusts the model by: the model supporting component drives the model to move in the direction X, Y, Z and rotate around the Y direction through the model supporting rod.
Further, the step S30 makes the simulator support assembly follow the movement by: the movable supporting seat moves along with the direction Y, Z, the sliding block, the sliding connecting plate, the rotary bearing, the bearing connecting plate, the flow simulator supporting seat and the flow simulator move along with the direction X, and the bearing connecting plate, the flow simulator supporting seat and the flow simulator rotate along with the direction Y.
Further, after steps S20 and S30, the central planes of the model support assembly, the model strut, the model, the flow simulator, the simulator support assembly and the flexible air suction pipe are located on the vertical central plane of the wind tunnel test section.
Compared with the prior art, the invention at least has the following technical effects:
1. in the invention, the simulator supporting component can be adjusted in a self-adaptive manner along with the adjustment of the model supporting component, so that the simulator supporting component is not always in a fixed position but moves along with the model in the attitude adjustment process of the model, and the total blockage degree of a wind tunnel flow field is not increased;
2. in the invention, the flexible air suction pipe cannot be greatly bent in the self-adaptive adjustment process of the simulator support assembly along with the adjustment of the model support assembly, so that the air flow pressure in the flexible air suction pipe can be ensured to be relatively stable;
3. in the invention, the simulator supporting component can be adjusted in a self-adaptive manner along with the adjustment of the model supporting component, so that the flow simulator, the flexible air suction pipe and the model have minimum interference, thereby improving the quality of test data;
4. in the invention, the central planes of the model supporting component, the model supporting rod, the model, the flow simulator, the simulator supporting component and the flexible air suction pipe are positioned on the vertical central plane of the wind tunnel test section, so that the flexible air suction pipe is in a natural straightening state in the X direction of the wind tunnel flow field, the pressure loss in the flexible air suction pipe is minimum, and the windward side of the model supporting component, the model supporting rod, the model, the flow simulator, the simulator supporting component and the flexible air suction pipe in the YOZ plane of the wind tunnel flow field is minimum, thereby minimizing the total blockage degree and improving the test quality.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention or in the description of the prior art will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a prior art inlet test simulator;
FIG. 2 is a schematic diagram of an inlet test simulation apparatus according to a first embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a simulator support assembly according to a first embodiment of the present invention;
FIG. 4 is a schematic diagram of an inlet test simulation method according to a second embodiment of the present invention;
fig. 5 is a schematic diagram of an optimal position of the air inlet channel test simulation apparatus in the second embodiment of the present invention.
Detailed Description
Aspects of the present invention will be described more fully hereinafter with reference to the accompanying drawings. This invention may, however, be embodied in many different forms and should not be construed as limited to any specific structure or function presented throughout this disclosure. Rather, these aspects are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. Based on the teachings herein one skilled in the art should appreciate that the scope of the present invention is intended to encompass any aspect disclosed herein, whether alone or in combination with any other aspect of the invention to accomplish any aspect disclosed herein. For example, it may be implemented using any number of the apparatus or performing methods set forth herein. In addition, the scope of the present invention is intended to cover apparatuses or methods implemented with other structure, functionality, or structure and functionality in addition to the various aspects of the invention set forth herein. It is to be understood that any aspect disclosed herein may be embodied by one or more elements of a claim.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. The terms "comprises," "comprising," and the like, as used herein, specify the presence of stated features, steps, operations, and/or modes, but do not preclude the presence or addition of one or more other features, steps, operations, or modes.
All terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art unless otherwise defined. It is noted that the terms used herein should be interpreted as having a meaning that is consistent with the context of this specification and should not be interpreted in an idealized or overly formal sense.
The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments.
Example one
Fig. 2 is a schematic diagram of an air inlet channel test simulation apparatus according to a first embodiment of the present invention, which includes: a model support assembly 10, a model support rod 11, a model 20, a flow simulator 30, a simulator support assembly 40, and a flexible air suction pipe 50, wherein the model support assembly 10 is connected to the outer peripheral portion of the model 20 through the model support rod 11;
one end of the flexible air suction pipe 50 is connected with an air outlet of the model 20, and the other end of the flexible air suction pipe 50 is connected with an air inlet of the flow simulator 30;
the flow simulator 30 is supported on the simulator support assembly 40, and the simulator support assembly 40 is adaptively adjustable as the model support assembly 10 is adjusted.
In the intake passage test simulation, the flow rate of the intake passage of the model 20 is simulated by the flow rate simulator 30.
In the first embodiment of the present invention, since the simulator support assembly 40 can be adaptively adjusted along with the adjustment of the model support assembly 10, in the process of adjusting the posture of the model 20, the simulator support assembly 40 is not always in a fixed position, but moves along with the fixed position, and therefore, the total blockage degree of the wind tunnel flow field is not increased; on the other hand, the flexible air suction pipe 50 does not bend greatly, so that the air flow pressure in the flexible air suction pipe 50 can be ensured to be relatively stable; moreover, the flow simulator 30, the flexible air suction pipe 50 and the model 20 can have minimum interference, so that the quality and the efficiency of test data are improved;
compared with the prior art, the simulator supporting component in the prior art is fixed, and is always in a fixed position in the posture adjusting process of the model, so that the total blockage degree of a wind tunnel flow field can be greatly increased; moreover, because the simulator supporting assembly in the prior art is fixed, the flexible air suction pipe is greatly bent in the posture adjusting process of the model, so that the air flow pressure in the flexible air suction pipe is very unstable, and the test effect is influenced; in addition, in the prior art, the flow simulator, the flexible air suction pipe and the model are very easy to interfere with each other, when the interference occurs, the test is usually stopped, the interference is eliminated, and the test is continued, so that the test effect and the test efficiency are influenced.
In summary, the air inlet channel test simulation device in the first embodiment of the invention can improve the quality of test data and improve the test efficiency.
Further, the model supporting component 10 can drive the model 20 to move in the direction X, Y, Z and rotate around the direction Y through the model supporting rod 11, wherein the direction X refers to the central direction of the wind tunnel test section, the direction Y refers to the vertical direction of the wind tunnel test section, and the direction Z refers to the horizontal direction of the wind tunnel test section.
This is performed for the purpose of, during the air intake duct test, requiring the model 20 to be tested at each attitude angle and requiring the model 20 at each attitude angle to be always kept at the center position of the wind tunnel test section, so that the model support assembly 10 can adjust both the attitude angle of the model 20 and the position of the model 20.
Further, as shown in fig. 3, a structural schematic view of a simulator support assembly 40 in a first embodiment of the present invention is shown, where the simulator support assembly 40 includes a movable support base 41 capable of moving along Y and Z directions, a slide rail 42 along X direction is disposed on a top of the movable support base 41, a slide block 43 capable of moving along the slide rail 42 is disposed on the slide rail 42, a slide connection plate 44 is fixed on the slide block 43, a bearing clamp 45 is disposed on the slide connection plate 44, an outer ring of a rotary bearing 46 is in interference fit with the bearing clamp 45, an inner ring of the rotary bearing 46 is fixedly connected with the bearing connection plate 47, a flow simulator support base 48 is fixedly mounted on the bearing connection plate 47, the flow simulator 30 is mounted on the flow simulator support base 48, and an axis of the rotary bearing 46 is located in a vertical direction.
With the above-described structure of the simulator support assembly 40, the simulator support assembly 40 can be adaptively adjusted in accordance with the adjustment of the model support assembly 10.
Specifically, when the attitude angle of the model 20 changes, the movable support 41 moves along the Y and Z directions, and at the same time, under the linking action of the flexible air suction pipe 50 and the driving of the air flow in the wind tunnel, the slider 43, the sliding connection plate 44, the slewing bearing 46, the bearing connection plate 47, the flow simulator support 48, and the flow simulator 30 are driven to move along the X direction, and the bearing connection plate 47, the flow simulator support 48, and the flow simulator 30 rotate along the Y direction.
Example two
Fig. 4 is a schematic diagram of an air inlet channel test simulation method in the second embodiment of the present invention, which includes the following steps:
step S10: arranging the air inlet channel test simulation device on a wind tunnel test section;
step S20: adjusting the model 20 to enable the attitude angle of the model 20 to meet the test requirement;
step S30: the simulator support assembly 40 follows the movement;
step S40: and (5) carrying out air inlet channel test simulation.
Further, the step S20 adjusts the model 20 by: the mold support assembly 10 moves the mold 20 in direction X, Y, Z and rotates in the Y direction via the mold support rods 11.
Further, the step S30 makes the simulator support assembly 40 follow the movement by: the movable support 41 moves in the direction Y, Z, the slider 43, the slide link plate 44, the slewing bearing 46, the bearing link plate 47, the flow simulator support 48, and the flow simulator 30 move in the X direction, and the bearing link plate 47, the flow simulator support 48, and the flow simulator 30 rotate in the Y direction.
Further, as shown in fig. 5, which is a schematic diagram of the optimal position of the air inlet channel test simulation device, after steps S20 and S30, the central planes of the model support assembly 10, the model strut 11, the model 20, the flow simulator 30, the simulator support assembly 40 and the flexible air suction pipe 50 are located on the vertical central plane of the wind tunnel test section.
Through the arrangement, the flexible air suction pipe 50 can be in a natural straightening state in the X direction in the wind tunnel flow field, the pressure loss in the flexible air suction pipe 50 is minimum, and the windward side of the model supporting component 10, the model supporting rod 11, the model 20, the flow simulator 30, the simulator supporting component 40 and the flexible air suction pipe 50 in the YOZ plane in the wind tunnel flow field is minimum, so that the total blockage degree can be minimized, and the test quality is improved.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (7)
1. An air inlet channel test simulation device is characterized by comprising: the flow simulator comprises a model supporting assembly (10), a model supporting rod (11), a model (20), a flow simulator (30), a simulator supporting assembly (40) and a flexible air suction pipe (50), wherein the model supporting assembly (10) is connected with the outer periphery of the model (20) through the model supporting rod (11);
one end of the flexible air suction pipe (50) is connected with an air outlet of the model (20), and the other end of the flexible air suction pipe (50) is connected with an air inlet of the flow simulator (30);
the flow simulator (30) is supported on the simulator support assembly (40), the simulator support assembly (40) being adaptively adjustable with adjustment of the model support assembly (10).
2. The air inlet channel test simulation device as claimed in claim 1, wherein the model support assembly (10) can drive the model (20) to move in the direction X, Y, Z and rotate around the direction Y through the model support rod (11), wherein the direction X refers to the central direction of the wind tunnel test section, the direction Y refers to the vertical direction of the wind tunnel test section, and the direction Z refers to the horizontal direction of the wind tunnel test section.
3. The air inlet channel test simulation device as claimed in claim 2, wherein the simulator support assembly (40) comprises a movable support (41) capable of moving along the Y and Z directions, a slide rail (42) along the X direction is arranged at the top of the movable support (41), a slide block (43) capable of moving along the slide rail (42) is arranged on the slide rail (42), a slide connection plate (44) is fixed on the slide block (43), a bearing clamp (45) is arranged on the slide connection plate (44), the outer ring of the slewing bearing (46) is in interference fit with the bearing clamp (45), the inner ring of the slewing bearing (46) is fixedly connected with the bearing connection plate (47), the flow simulator support (48) is fixedly mounted on the bearing connection plate (47), and the flow simulator (30) is mounted on the flow simulator support (48), the axis of the slewing bearing (46) is located in the vertical direction.
4. An air inlet channel test simulation method is characterized by comprising the following steps:
step S10: arranging an air inlet channel test simulation device according to claim 3 in a wind tunnel test section;
step S20: adjusting the model (20) to enable the attitude angle of the model (20) to meet the test requirement;
step S30: causing the simulator support assembly (40) to follow the movement;
step S40: and (5) carrying out air inlet channel test simulation.
5. The method for simulating an inlet test according to claim 4, wherein the step S20 adjusts the model (20) by: the model supporting component (10) drives the model (20) to move in the direction X, Y, Z and rotate around the Y direction through the model supporting rod (11).
6. The air inlet test simulation method according to claim 5, wherein the step S30 is to make the simulator support assembly (40) follow the movement by: the movable supporting seat (41) moves along the direction Y, Z, the sliding block (43), the sliding connecting plate (44), the rotary bearing (46), the bearing connecting plate (47), the flow simulator supporting seat (48) and the flow simulator (30) move along the X direction, and the bearing connecting plate (47), the flow simulator supporting seat (48) and the flow simulator (30) rotate along the Y direction.
7. The air inlet channel test simulation method according to claim 6, wherein after the steps S20 and S30, the central planes of the model support assembly (10), the model strut (11), the model (20), the flow simulator (30), the simulator support assembly (40) and the flexible air suction pipe (50) are located on the vertical central plane of the wind tunnel test section.
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| CN113049211A (en) * | 2021-06-01 | 2021-06-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device |
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| CN113049211B (en) * | 2021-06-01 | 2021-08-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device |
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| 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 |
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| CN115307863A (en) * | 2022-10-12 | 2022-11-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Engine air inlet simulation constant flow air inlet control method and system and storage medium |
| CN115307863B (en) * | 2022-10-12 | 2022-12-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Steady flow intake control method and system for engine intake simulation and storage medium |
| CN116973065A (en) * | 2023-09-22 | 2023-10-31 | 中国航空工业集团公司沈阳空气动力研究所 | Device and method for simulating impact of shock waves on aircraft |
| CN116973065B (en) * | 2023-09-22 | 2023-11-28 | 中国航空工业集团公司沈阳空气动力研究所 | Device and method for simulating impact of shock waves on aircraft |
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