CN211504602U - Axial symmetry ventilation model aerodynamic force measurement test device of back support-false tail support - Google Patents
Axial symmetry ventilation model aerodynamic force measurement test device of back support-false tail support Download PDFInfo
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- CN211504602U CN211504602U CN202020478171.6U CN202020478171U CN211504602U CN 211504602 U CN211504602 U CN 211504602U CN 202020478171 U CN202020478171 U CN 202020478171U CN 211504602 U CN211504602 U CN 211504602U
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Abstract
The utility model discloses an axial symmetry model aerodynamic force measurement test device that ventilates that back of body supported-false tail supported, a serial communication port, 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 supporting device and the model main body; a support device, comprising: back support and false tail support; the end part of the force measuring balance 1 is connected with the model main body; the back support is connected with the force measuring balance through the adapter; the model precursor is arranged in the force measuring balance in a penetrating way; the test shell is a back 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 back of body supported-false 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 configuration of the lifting body, two tail modification methods have been 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 main test data is still obtained by adopting a tail support mode. And the tail nozzle has to be modified by adopting the tail support. The existence of the aft support and the modification of the jet nozzle change the aerodynamic characteristics of the model, and the influence quantity of the aerodynamic characteristics of the model caused by the existence of the aft support and the modification of the jet nozzle must be deducted.
Therefore, the aerodynamic force measurement test device suitable for the axial symmetry ventilation model of the back support-false tail support is explored, the influence of the existence of the tail support and the modification of the tail nozzle on the aerodynamic characteristics of the model is accurately simulated, and the aerodynamic force measurement test device has important significance for carrying out the test in the hypersonic wind tunnel to eliminate the influence of the existence of the tail support and the modification of the tail nozzle on the aerodynamic characteristics of the model.
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 ventilation model aerodynamic force measurement test device of back support-false tail support, comprising:
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 supporting device and the model main body;
a support device, comprising: back support and false tail support;
wherein, the end part of the force measuring balance 1 is connected with the model main body; the back support is connected with the force measuring balance through the adapter; the model precursor is arranged in the force measuring balance in a penetrating way; the test shell is a back 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; the front end of the false tail support extends into a back support test shell of the model main body but is not contacted with the model main body, the force measuring balance, the adapter and the back support, and the tail end of the modified tail spray pipe is positioned inside the front end of the false tail support; the rear section of the false tail support is arranged on the wind tunnel attack angle mechanism through a switching device; a groove is formed in the back support test shell, and a gap of 2mm is reserved between the model main body and the back support test shell.
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 back support is mounted on the wind tunnel angle of attack mechanism; the end part of the adapter is connected with the other end part of the force measuring balance by adopting a flange and positioned by adopting a pin; the wall surface of the adapter is connected with the back support through a clamping groove.
Preferably, the false tail support comprises an annular strut with a drainage hole and a rectifying cone; the annular supporting rod and the rectifying cone are combined into a complete false tail support in a cylindrical surface matching and screw pressing mode.
Preferably, the rear end of the false tail support is sleeved in the adapter device, and the rear end of the false tail support is pressed in the adapter device by screws.
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 back of body supported-false tail supported can the accurate influence of the modification of the existence of simulation tail support and jet-propelled pipe to the model aerodynamic characteristic.
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 structural diagram of an axial-symmetric ventilation model aerodynamic force measurement test device for back support-false tail support according to 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 view of the connection structure of the model main body and the balance of the axial symmetry ventilation model aerodynamic force measurement test device of the back support-false tail support of the utility model;
FIG. 5 is a schematic structural diagram of a model main body of the axial-symmetry ventilation model aerodynamic force measurement test device for back support-false tail support according to the present invention;
fig. 6 is a schematic view of a partial structure of the aerodynamic force measurement test device of the axial symmetry ventilation model of the back support-false tail support of the present invention;
fig. 7 is a schematic view of a partial structure of the aerodynamic force measurement test device of the axial symmetry ventilation model of the back support-false tail support of the present invention;
FIG. 8 is a schematic structural diagram of a rectification cone II of the axial symmetry ventilation model aerodynamic force measurement test device of the back support-false tail support of the present invention;
fig. 9 is a schematic structural view of an annular strut and a fairing cone of the axial-symmetric ventilation model aerodynamic force measurement test device of the back support-false tail support of the utility model;
fig. 10 is a schematic structural diagram of an annular strut of an axial-symmetric ventilation model aerodynamic force measurement test device of a back support-false tail support according to the present invention;
fig. 11 is a schematic structural diagram of a back support test casing of the axial-symmetric ventilation model aerodynamic force measurement test device of the back support-false tail support of the present invention;
fig. 12 is a schematic structural diagram of an adapter of the axial-symmetric ventilation model aerodynamic force measurement test device for back support-false tail support according to the present invention;
FIG. 13 is a schematic illustration of the structure 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. 1-13 show the utility model discloses an axial symmetry model aerodynamic force measurement test device that ventilates that back of body supported-false 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 supporting device and the model main body;
a support device, comprising: a back support 14 and a false tail support 16;
wherein, the end part of the force measuring balance 1 is connected with the model main body; the back support 14 is connected with the force measuring balance through the adapter 15; the model precursor 3 is arranged in the force measuring balance 1 in a penetrating way; the test shell is a back support test shell 20 which is cylindrical, 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; the front end of the false tail support 16 extends into a back support test shell 20 of the model main body but is not in contact with the model main body, the force measuring balance 1, the adapter 15 and the back support 14, and the tail end of the modified tail nozzle 4 is positioned inside the front end of the false tail support 16; the rear section of the false tail support 16 is arranged on the wind tunnel attack angle mechanism through a switching device 17; a groove is formed in the back support test shell 20, and a gap of 2mm is reserved between the model main body and the back support test shell; in order to prevent the wind tunnel from being affected by aerodynamic force after being started, the balance force measurement result is distorted due to the collision of the model main body and the back support, and a gap with a certain width is required to be reserved between the model main body and the back support test shell, so that a groove is formed in the back support test shell 20, the width of the groove is larger than the deformation of the balance after being stressed, but the groove is not too large, and the width is taken as 2 mm; for the convenience of installation, the back support test shell is cut into a left half and a right half by taking the symmetrical surface of the groove as a reference, and is fixed on the model front body 3 by screws during the test.
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 back support; the balance material adopts F141 and hardening and tempering hardness HRC 50.
In the above solution, the modified jet nozzle has a profile that is generally inwardly convergent, with a slight divergence at the jet nozzle exit, as compared to the prototype jet nozzle (fig. 13).
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 technical scheme, the back support is arranged on the wind tunnel attack angle mechanism; the back support is used for carrying out a tail support influence correction test, the upper end of the back support is connected with the force measuring balance through an adapter provided with a flange plate, and the lower end of the back support is connected with the wind tunnel attack angle mechanism; the end part of the adapter piece 15 is connected with the other end part of the force measuring balance by adopting a flange and is positioned by adopting a pin; the wall surface of the adapter 15 is connected with the back support 14 through a clamping groove.
In the above technical solution, the false tail support 16 includes an annular strut 18 with a drainage hole 180 and a rectifying cone 19, and the size and arrangement thereof are the same as those of a real tail strut; the annular supporting rod and the rectifying cone are combined into a complete false tail support in a cylindrical surface matching and screw pressing mode 3; four screw holes 181 are uniformly distributed on the upper, lower, left and right sides of the annular supporting rod 18, four grooves 191 (the groove width needs to be larger than the diameter of the screw hole) are uniformly distributed on the rectifying cone 19, four screw holes 171 are arranged on the adapter device 17 in an X shape, four through holes 172 are arranged on the upper, lower, left and right sides in a cross shape (the diameter needs to be larger than the diameter of the screw hole on the annular supporting rod 18), during the test, screws are arranged in the four screw holes 171 arranged in the X shape to tightly press the annular supporting rod 18 and the adapter device 17, the screw holes 181 of the annular supporting rod 18 and the grooves 191 of the rectifying cone 19 penetrate through the four through holes 172 of the adapter device by four screws, the screws are arranged in the four screw holes 181 arranged in the cross shape of the annular supporting rod 18 to tightly press the rectifying cone 19, and the distance from the top of the conical surface; the front end of the annular supporting rod 18 extends into the model, but is not connected with the force measuring balance and the model; the annular strut 18 is provided with 4 drain holes 180 which are uniformly distributed up, down, left and right along the axial direction. The role of the drain hole is as follows: for discharging the air flow of the model exhaust nozzle into the incoming flow of the wind tunnel
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.
The false tail support is used for simulating the installation state of the tail support when a back support test is carried out, the front end of the false tail support extends into the tail part of the model for a certain distance, but does not contact with the balance and the inner and outer walls of the model, and the false tail support is provided with a drainage hole and a rectifying cone and used for guiding out tail jet flow.
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 (7)
1. The utility model provides a back of body supports-pseudo-tail supports axial symmetry ventilation model aerodynamic force measurement test device 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 supporting device and the model main body;
a support device, comprising: back support and false tail support;
wherein, the end part of the force measuring balance is connected with the model main body; the back support is connected with the force measuring balance through the adapter; the model precursor is arranged in the force measuring balance in a penetrating way; the test shell is a back 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; the front end of the false tail support extends into a back support test shell of the model main body but is not contacted with the model main body, the force measuring balance, the adapter and the back support, and the tail end of the modified tail nozzle is positioned inside the front end of the false tail support; the rear section of the false tail support is arranged on the wind tunnel attack angle mechanism through a switching device; a groove is formed in the back support test shell, and a gap of 2mm is reserved between the model main body and the back support test shell.
2. The device for testing the aerodynamic force measurement of the back support-false tail support axial symmetry ventilation model of claim 1, wherein the front end and the rear end of the force measuring balance are provided with a flange, a threaded hole and a pin hole.
3. The back support-false tail support axisymmetric breathing model aerodynamic force measurement test device of claim 1, wherein said modified jet nozzle has an overall inwardly contracted profile and a slight expansion at the jet nozzle exit compared to the prototype jet nozzle.
4. The back support-false tail support axial symmetry ventilation model aerodynamic force measurement test device of claim 1, characterized in that, except that the front end of the force measuring balance is contacted with the model body, gaps of 6mm and 8mm are respectively reserved between the rest part of the force measuring balance and the model body and the model shell; the front end cylindrical section of the force measuring balance is provided with a platform.
5. The back support-false tail support axial symmetry ventilation model aerodynamic force measurement test device of claim 1, characterized in that the back support is mounted on a wind tunnel angle of attack mechanism; the end part of the adapter is connected with the other end part of the force measuring balance by adopting a flange and positioned by adopting a pin; the wall surface of the adapter is connected with the back support through a clamping groove.
6. The back support-false tail support axisymmetric breathing model aerodynamic force measurement test device of claim 1, wherein said false tail support includes an annular strut with a vent hole and a fairing cone; the annular supporting rod and the rectifying cone are combined into a complete false tail support in a cylindrical surface matching and screw pressing mode.
7. The device for testing the aerodynamic force measurement of the back support-false tail support axial symmetry ventilation model of claim 1, wherein the back end of the false tail support is sleeved in the adapter device, and the back end of the false tail support is pressed in the device by a screw.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112268675A (en) * | 2020-10-15 | 2021-01-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Intelligent false strut device for high-speed wind tunnel |
| CN114001918A (en) * | 2021-12-28 | 2022-02-01 | 中国航空工业集团公司沈阳空气动力研究所 | Air inlet channel force measurement integrated test model |
-
2020
- 2020-04-03 CN CN202020478171.6U patent/CN211504602U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112268675A (en) * | 2020-10-15 | 2021-01-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Intelligent false strut device for high-speed wind tunnel |
| CN114001918A (en) * | 2021-12-28 | 2022-02-01 | 中国航空工业集团公司沈阳空气动力研究所 | Air inlet channel force measurement integrated test model |
| CN114001918B (en) * | 2021-12-28 | 2022-03-29 | 中国航空工业集团公司沈阳空气动力研究所 | Air inlet channel force measurement integrated test model |
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