CN211504603U - Aerodynamic force measurement test device of axisymmetric ventilation model of tail support - Google Patents
Aerodynamic force measurement test device of axisymmetric ventilation model of tail support Download PDFInfo
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- CN211504603U CN211504603U CN202020479453.8U CN202020479453U CN211504603U CN 211504603 U CN211504603 U CN 211504603U CN 202020479453 U CN202020479453 U CN 202020479453U CN 211504603 U CN211504603 U CN 211504603U
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Abstract
The utility model discloses an axial symmetry model aerodynamic force measurement test device that ventilates that tail supported, include: the axial symmetry ventilation model is characterized in that an air inlet channel of the axial symmetry ventilation model adopts a lower jaw type or abdomen air inlet mode, and inner flow channels behind the air inlet channel are all in an axial symmetry configuration; the axisymmetric ventilation model comprises a model main body and a test shell; the model main body comprises a model precursor and a modified tail nozzle which are connected in a threaded manner; the force measuring balance is a six-component ring balance and is respectively connected with the tail support and the model main body; the end part of the force measuring balance is connected with the model main body, and the model front body is arranged in the force measuring balance in a penetrating way; the other end of the force measuring balance is connected with the tail support; the model precursor and the modified tail nozzle are arranged in the tail support in a penetrating way; the test shell is a tail support test shell which is cylindrical, the front end of the test shell is connected with the model front body through a screw, and the rear end of the test shell is suspended.
Description
Technical Field
The utility model relates to an axial symmetry model aerodynamic force measurement test device that ventilates that tail supported belongs to wind-tunnel test technical field.
Background
The currently used air-breathing aircraft has two main structural forms: one is a lifting body structure, the whole aircraft is in a relatively flat plane symmetrical structure, and most typically, the aircraft is X-43A in the United states; and the other is an axisymmetric configuration, the air inlet channel is positioned below the compression surface of the aircraft forebody, and the inner flow channels (outlet of the spray pipe of the isolating section) behind the air inlet channel are all axisymmetric configurations.
For the aircraft with a lifting body configuration or an axisymmetric configuration, the tail nozzle of the propulsion system occupies most space at the tail part of the aircraft, and the residual space cannot meet the installation requirement of the wind tunnel test model supporting device. Therefore, the aircraft tail (nozzle outlet) must be suitably modified.
For the modification of the lifting body, two tail modification methods are adopted:
firstly, do not change tail nozzle expansion angle, model branch directly passes the spray tube, for avoiding model and branch direct contact to influence the balance measuring result, need remain certain gap between spray tube and the branch. The test result shows that the air flow pressure near the tail spray pipe is high, the pressure of the inner cavity of the model is low, and the external air flow flows backwards to the inner cavity of the model through the gap between the spray pipe and the support rod, so that the pressure distribution of the wall surface of the spray pipe is changed, the measurement accuracy of the pneumatic characteristic is seriously influenced, and the CFD method is difficult to correct.
Secondly, the molded surface of the jet pipe is prevented from being damaged, and the expansion angle of the tail jet pipe is changed, so that the defects of the first method are effectively overcome. Changes in aerodynamic properties caused by profile changes can be corrected by CFD or other methods of designing tests. Years of practice have shown that this method is effective.
For the axisymmetric aircraft, the method is directly adopted, the balance and the support rod can only be biased to the upper side of the inner flow channel, the sizes of the balance and the support rod are strictly limited, and the rigidity of the support device is possibly insufficient; on the other hand, the space below the inner flow path is not effectively utilized.
And the back support mode is adopted, so that the molded surface of the tail spray pipe can be prevented from being damaged. But due to the existence of the back support, the model flow field behind the back support is damaged, and the influence on the aerodynamic characteristics is larger.
Therefore, the research of the aerodynamic force measurement test device of the axisymmetric ventilation model suitable for the tail support has important significance for developing the test in the hypersonic wind tunnel in the future.
SUMMERY OF THE UTILITY MODEL
An object of the present invention is to solve at least the above problems and/or disadvantages and to provide at least the advantages which will be described later.
To achieve these objects and other advantages in accordance with the purpose of the invention, there is provided an axial symmetry aeration model aerodynamic force measurement test device of a tail support, including:
the axial symmetry ventilation model is characterized in that an air inlet channel of the axial symmetry ventilation model adopts a lower jaw type or abdomen air inlet mode, and inner flow channels behind the air inlet channel are all in an axial symmetry configuration; the axisymmetric ventilation model comprises a model main body and a test shell; the model main body comprises a model precursor and a modified tail nozzle which are connected in a threaded manner;
the force measuring balance is a six-component ring balance and is respectively connected with the tail support and the model main body;
the end part of the force measuring balance is connected with the model main body, and the model front body is arranged in the force measuring balance in a penetrating way; the other end of the force measuring balance is connected with the tail support; the model precursor and the modified tail nozzle are arranged in the tail support in a penetrating way; the test shell is a tail support test shell which is cylindrical, the front end of the test shell is connected with the model front body through a screw, and the rear end of the test shell is suspended;
preferably, the front end and the rear end of the force measuring balance are provided with a flange, a threaded hole and a pin hole.
Preferably, the modified jet nozzle has an overall inwardly converging profile and a slight divergence at the jet nozzle exit compared to the prototype jet nozzle.
Preferably, gaps of 6mm and 8mm are reserved between the rest parts of the force measuring balance and the model main body and the model shell respectively except that the front end of the force measuring balance is contacted with the model main body; the front end cylindrical section of the force measuring balance is provided with a platform.
Preferably, the tail support includes: the annular support rod and the rectifying cone; the annular supporting rod and the rectifying cone are combined into a complete tail support in a cylindrical surface matching, pin positioning and screw tensioning mode; the front end of the annular supporting rod is connected with the force measuring balance through a flange, the rear end of the annular supporting rod is connected with the rectifying cone, and the thickness of the annular supporting rod is 20 mm; a rectangular hole is formed in the front end of the annular supporting rod behind the flange; a wiring groove is arranged on the side surface of the annular supporting rod, the front end of the wiring groove is communicated with the wiring groove of the force measuring balance, and the rear end of the wiring groove is communicated with an inclined hole on the annular supporting rod; 4 discharge holes are uniformly distributed on the annular supporting rod along the axial direction from top to bottom, left to right; the rectifying cone is provided with a rectifying cone inclined hole.
The utility model discloses at least, include following beneficial effect: the utility model discloses an axial symmetry model aerodynamic force measurement test device that ventilates that tail supported provides tail nozzle modification and tail branch water conservancy diversion design method.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.
Description of the drawings:
FIG. 1 is a schematic view of a cross-sectional structure of an axial-symmetry ventilation model aerodynamic force measurement test device of the tail support of the present invention;
FIG. 2 is a partial schematic view of a prior art mold precursor and prototype jet nozzle of an axisymmetric aeration model;
fig. 3 is a schematic structural view of the force measuring balance according to the present invention;
FIG. 4 is a schematic structural diagram of an annular strut I and a rectifying cone I of the tail-supported axial-symmetry ventilation model aerodynamic force measurement test device of the utility model;
FIG. 5 is a schematic structural diagram of an annular strut I of the aerodynamic force measurement test device of the axisymmetric ventilation model of the tail support of the utility model;
FIG. 6 is a schematic structural diagram of a rectification cone I of the tail-supported axial-symmetry ventilation model aerodynamic force measurement test device of the utility model;
FIG. 7 is a schematic structural view of the aerodynamic force measurement test device of the axisymmetric ventilation model of the tail boom of the present invention;
fig. 8 is a schematic structural diagram of the aerodynamic force measurement test device (without test shell) of the axisymmetric ventilation model of the tail boom of the present invention;
fig. 9 is a schematic view of a connection structure of a model main body and a balance of the tail-supported axial-symmetry ventilation model aerodynamic force measurement test device of the present invention;
fig. 10 is a schematic structural view of a model main body of the tail-supported axial-symmetry ventilation model aerodynamic force measurement test device of the present invention;
FIG. 11 is a schematic illustration of the construction of a prototype jet nozzle used in the prior art.
The specific implementation mode is as follows:
the present invention is further described in detail below with reference to the drawings so that those skilled in the art can implement the invention with reference to the description.
It will be understood that terms such as "having," "including," and "comprising," as used herein, do not preclude the presence or addition of one or more other elements or groups thereof.
Fig. 1-11 show the utility model discloses an axial symmetry model aerodynamic force measurement test device of ventilating that tail supported, include:
the axial symmetry ventilation model is characterized in that an air inlet channel of the axial symmetry ventilation model adopts a lower jaw type or abdomen air inlet mode, and inner flow channels behind the air inlet channel are all in an axial symmetry configuration; the axisymmetric ventilation model comprises a model main body and a test shell; the model body comprises a model precursor 3 and a modified tail nozzle 4 which are connected in a threaded manner;
the force measuring balance 1 is a six-component ring balance, and the force measuring balance 1 is respectively connected with the tail support and the model main body;
the end part of the force measuring balance 1 is connected with the model main body, and the model precursor 3 is arranged in the force measuring balance 1 in a penetrating way; the other end of the force measuring balance 1 is connected with a tail support 2; the model precursor and the modified tail nozzle are arranged in the tail support 2 in a penetrating way; the test shell is a tail support test shell 5 which is a cylindrical model shell, the front end of the test shell is connected with the model front body 3 through a screw, and the rear end of the test shell is suspended.
In the technical scheme, the front end and the rear end of the force measuring balance are provided with the flange, the threaded hole and the pin hole, so that the force measuring balance can be conveniently connected with the model body and the tail support; the balance material adopts F141 and hardening and tempering hardness HRC 50.
In the above technical solution, compared with the prototype jet nozzle (fig. 11), the modified jet nozzle has the profile wholly contracted inwards and slightly expanded at the outlet of the jet nozzle, so that the tail part of the model has enough space to ensure that the tail support 2 can penetrate out and does not collide with the model.
In the technical scheme, except that the front end of the force measuring balance is contacted with the model main body, gaps of 6mm and 8mm are reserved between the rest part of the force measuring balance and the model main body as well as between the rest part of the force measuring balance and the test shell respectively; the front end cylindrical section of the force measuring balance is provided with a platform which is used as an installation reference before balance calibration and wind tunnel test.
In the above technical solution, the tail support includes: an annular strut 7 and a fairing cone 8; the annular supporting rod 7 and the rectifying cone 8 are combined into a complete tail support 2 in a cylindrical surface matching, pin positioning and screw tensioning mode; the front end of the annular supporting rod 7 is connected with the force measuring balance 1 through a flange 9, the rear end of the annular supporting rod is connected with the rectifying cone 8, and the thickness of the annular supporting rod is 20 mm; for installing pins and screws, a rectangular hole 10 is formed in the front end of the annular supporting rod 7 behind the flange 9; the width and length of the rectangular hole 10 are designed to ensure the rigidity and strength of the support rod, and the pins and the screws are convenient to mount; a wiring groove 11 is arranged on the side surface of the annular supporting rod 7, the front end of the wiring groove 11 is communicated with a wiring groove of the force measuring balance, and the rear end of the wiring groove 11 is communicated with an inclined hole 12 on the annular supporting rod; 4 discharge holes 13 are uniformly distributed on the annular strut 7 along the axial direction from top to bottom, left to right; the rectifying cone 8 is provided with a rectifying cone inclined hole 81; after the annular supporting rod 7 is connected with the rectifying cone 8, the inclined hole 12 on the annular supporting rod is correspondingly communicated with the inclined hole 81 of the rectifying cone; during testing, a balance lead enters the rectifying cone 8 through the wiring groove 11, the inclined hole 12 and the rectifying cone inclined hole 81, is led out to the leeward side of the mechanism through an inner hole of the wind tunnel attack angle mechanism, and is connected with a data acquisition system circuit; 4 drain holes 13 are uniformly arranged along the axial direction of the strut from top to bottom and from left to right, and the drain holes 13 are used for discharging tail jet flow and discharging airflow of the model tail jet pipe into the wind tunnel incoming flow; the length of the tail part of the model exposed by the drainage hole after the test device is installed is preferably not less than 1 time of the diameter of the bottom part; the effect of fairing cone is: the tail jet flow is prevented from directly colliding with a vertical wall surface at the tail end of the drainage hole, strong normal shock waves are generated, and the interference with the flow around the outside of the model is avoided, so that the pressure distribution and the flow field structure of the outer surface of the model are influenced, and the full-elastic pneumatic characteristic is further influenced; meanwhile, the tail jet flow in the drainage hole has a certain flow guiding function, so that the tail jet flow is smoothly discharged into the external incoming flow, and the blockage of the inner cavity of the support rod is prevented.
While the embodiments of the invention have been described above, it is not intended to be limited to the details shown, or described, but rather to cover all modifications, which would come within the scope of the appended claims, and all changes which come within the meaning and range of equivalency of the art are therefore intended to be embraced therein.
Claims (5)
1. The utility model provides an axisymmetric ventilation model aerodynamic force measurement test device of tail support which characterized in that includes:
the axial symmetry ventilation model is characterized in that an air inlet channel of the axial symmetry ventilation model adopts a lower jaw type or abdomen air inlet mode, and inner flow channels behind the air inlet channel are all in an axial symmetry configuration; the axisymmetric ventilation model comprises a model main body and a test shell; the model main body comprises a model precursor and a modified tail nozzle which are connected in a threaded manner;
the force measuring balance is a six-component ring balance and is respectively connected with the tail support and the model main body;
the end part of the force measuring balance is connected with the model main body, and the model front body is arranged in the force measuring balance in a penetrating way; the other end of the force measuring balance is connected with the tail support; the model precursor and the modified tail nozzle are arranged in the tail support in a penetrating way; the test shell is a tail support test shell which is cylindrical, the front end of the test shell is connected with the model front body through a screw, and the rear end of the test shell is suspended.
2. The tail-supported axisymmetric aeration model aerodynamic force measurement test device of claim 1, wherein said force-measuring balance has flanges, threaded holes and pin holes at its front and rear ends.
3. The aft-supported axisymmetric draft model aerodynamic force measurement test device of claim 1, wherein said modified jet nozzle has an overall inward contraction in profile and an expansion at the jet nozzle exit compared to the prototype jet nozzle.
4. The tail-supported axisymmetric aeration model aerodynamic force measurement test device of claim 1, wherein gaps of 6mm and 8mm are reserved between the rest part of the force balance and the model body and the test shell respectively except that the front end of the force balance is in contact with the model body; the front end cylindrical section of the force measuring balance is provided with a platform.
5. The tail boom axisymmetric breathing model aerodynamic force measurement test device of claim 1, wherein said tail boom includes: the annular support rod and the rectifying cone; the annular supporting rod and the rectifying cone are combined into a complete tail support in a cylindrical surface matching, pin positioning and screw tensioning mode; the front end of the annular supporting rod is connected with the force measuring balance through a flange, the rear end of the annular supporting rod is connected with the rectifying cone, and the thickness of the annular supporting rod is 20 mm; a rectangular hole is formed in the front end of the annular supporting rod behind the flange; a wiring groove is arranged on the side surface of the annular supporting rod, the front end of the wiring groove is communicated with the wiring groove of the force measuring balance, and the rear end of the wiring groove is communicated with an inclined hole on the annular supporting rod; 4 discharge holes are uniformly distributed on the annular supporting rod along the axial direction from top to bottom, left to right; the rectifying cone is provided with a rectifying cone inclined hole.
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| CN202020479453.8U CN211504603U (en) | 2020-04-03 | 2020-04-03 | Aerodynamic force measurement test device of axisymmetric ventilation model of tail support |
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| CN202020479453.8U CN211504603U (en) | 2020-04-03 | 2020-04-03 | Aerodynamic force measurement test device of axisymmetric ventilation model of tail support |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113514222A (en) * | 2021-06-07 | 2021-10-19 | 中国航天空气动力技术研究院 | Aerodynamic force measurement device and method for air breathing model of air breathing type air inlet aircraft |
| CN114061896A (en) * | 2021-11-17 | 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 | Method for processing internal resistance measurement test data of lifting body ventilation model |
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2020
- 2020-04-03 CN CN202020479453.8U patent/CN211504603U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113514222A (en) * | 2021-06-07 | 2021-10-19 | 中国航天空气动力技术研究院 | Aerodynamic force measurement device and method for air breathing model of air breathing type air inlet aircraft |
| CN114061896A (en) * | 2021-11-17 | 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 | Method for processing internal resistance measurement test data of lifting body ventilation model |
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