CN111397838A - Axial symmetry ventilation model aerodynamic force measurement test device and use method - Google Patents
Axial symmetry ventilation model aerodynamic force measurement test device and use method Download PDFInfo
- Publication number
- CN111397838A CN111397838A CN202010260367.2A CN202010260367A CN111397838A CN 111397838 A CN111397838 A CN 111397838A CN 202010260367 A CN202010260367 A CN 202010260367A CN 111397838 A CN111397838 A CN 111397838A
- Authority
- CN
- China
- Prior art keywords
- tail
- support
- model
- test
- back support
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- 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
-
- 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
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses an axial symmetry ventilation model aerodynamic force measurement test device and a using method thereof, wherein the device comprises the following steps: the axisymmetric ventilation model comprises an axisymmetric ventilation model body and a model shell; 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: tail support, back support and false tail support; correspondingly, the axial symmetry ventilation model aerodynamic force measurement test device comprises three combination modes: firstly, the combination of a tail support and a modified tail nozzle; secondly, the combination of a back support, a false tail support and a modified tail nozzle; thirdly, combining a back support and a prototype tail nozzle; the invention solves the problem of accurate acquisition of the aerodynamic characteristics of the axisymmetric ventilation model, provides a method for modifying the tail nozzle and designing the diversion of the tail support rod, provides a method for correcting the influence of the modification of the tail nozzle and the influence of the tail support rod on the aerodynamic characteristics, and has clear guiding significance for developing relevant model tests in the future.
Description
Technical Field
The invention relates to an axial symmetry ventilation model aerodynamic force measurement test device and a using method thereof, and belongs to the technical field of wind tunnel tests.
Background
The hypersonic air-breathing aircraft adopts a design method of 'propulsion-engine body' height integration, and the aircraft body, the air inlet channel, the combustion chamber and the tail nozzle are highly integrated. The head of the aircraft is also a part of an air inlet channel of a propulsion system, head shock waves generate a strong compression effect on air, the compressed high-temperature and high-pressure air is used as an oxidant of the propulsion system, fuel of the aircraft is ignited in a combustion chamber, and stable combustion required by flight is maintained. The tail of the aircraft is simultaneously used as a jet pipe of a propulsion system, and high-temperature combustion gas flow generated in the combustion chamber reacts on the tail of the aircraft to generate thrust required by the aircraft.
In the aircraft development stage, the aerodynamic characteristics of the aircraft need to be accurately obtained, and input conditions are provided for the design of a control system and a power system. One of the main means for obtaining aerodynamic characteristics of an air-breathing aircraft is a wind tunnel test.
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 second 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.
Therefore, the exploration of the aerodynamic force measurement test device design and test method suitable for the axisymmetric ventilation model has important significance for developing the test in the hypersonic wind tunnel in future. At present, no relevant literature reports exist at home and abroad.
Disclosure of Invention
The invention aims to provide a test device suitable for measuring aerodynamic force of an axisymmetric ventilation model. The invention also aims to provide an aerodynamic force measurement test method for the axisymmetric ventilation model, and by using the device and the method, the aerodynamic force characteristic of the axisymmetric ventilation model can be accurately obtained through a hypersonic wind tunnel test under the condition of effectively ensuring the rigidity of the test device, so that a reliable test data basis is provided for aircraft design.
An object of the present invention is to solve at least the above problems and/or disadvantages and to provide at least the advantages described hereinafter.
To achieve these objects and other advantages in accordance with the purpose of the invention, there is provided an axisymmetric air-breathing model aerodynamic force measurement test device, 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 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: tail support, back support and false tail support;
correspondingly, the axial symmetry ventilation model aerodynamic force measurement test device comprises three combination modes: firstly, the combination of a tail support and a modified tail nozzle; secondly, the combination of a back support, a false tail support and a modified tail nozzle; thirdly, combining a back support and a prototype tail nozzle;
wherein, in the combination of the tail support and the modified tail pipe, the model main body comprises a model precursor and a modified tail pipe which are connected by screw threads; the front end 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 rear 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;
in the combination of the back support, the false tail support and the modified jet nozzle, the model main body comprises a model precursor and a modified jet nozzle which are connected by screw threads; 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;
in the combination of the back support and the prototype tail pipe, the false tail support and the prototype tail pipe in the combination of the back support, the false tail support and the prototype tail pipe are removed, and the prototype tail pipe is replaced.
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 part of the force measuring balance and the model main body and between the rest part of the force measuring balance and the test 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 device comprises a ring-shaped support rod I and a rectifying cone I; the annular support rod I and the rectifying cone I are combined into a complete tail support in a cylindrical surface matching, pin positioning and screw tensioning mode; the front end of the annular support rod I is connected with the force measuring balance through a flange, the rear end of the annular support rod I is connected with the rectifying cone I, and the thickness of the annular support rod I is 20 mm; a rectangular hole is formed in the front end of the annular support rod I behind the flange; a wiring groove is formed in the side face of the annular support rod I, the front end of the wiring groove is communicated with a wiring groove of the force measuring balance, and the rear end of the wiring groove is communicated with an inclined hole in the annular support rod I; 4 drainage holes I are uniformly distributed in the annular support rod I along the axial direction from top to bottom, left to right; and a rectifying cone inclined hole is formed in the rectifying cone I.
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 support rod II with a drainage hole II and a rectifying cone II, and the size and the arrangement mode of the false tail support are the same as those of a real tail support rod; and the annular supporting rod II and the rectifying cone II 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 invention also provides a using method of the axial symmetry ventilation model aerodynamic force measurement test device, which comprises the following steps:
step one, testing with a device of' combination of back support and prototype jet nozzleTest data C of aerodynamic forces/moments are obtained1；
Step two, carrying out a test by using a device of combination of back support, false tail support and modified tail nozzle to obtain test data C of each aerodynamic force/moment2；
Thirdly, carrying out a wind tunnel test by using a device of combination of a tail support and a modified tail nozzle to obtain test data C of each aerodynamic force/moment3；
Step four, the corrected final aerodynamic data, namely the aerodynamic characteristics of the real aircraft, C4：
C4＝C3-(C2-C1)
Preferably, each aerodynamic force/moment comprises: axial force, normal force, lateral force, pitch moment, yaw moment, and roll moment.
The invention at least comprises the following beneficial effects: the test device and the use method for measuring the aerodynamic force of the axisymmetric ventilation model solve the problem of accurately obtaining the aerodynamic characteristics of the axisymmetric ventilation model, provide a method for modifying the tail nozzle and designing the diversion of the tail support rod, provide a method for correcting the influence of the tail nozzle modification and the tail support rod on the aerodynamic characteristics, and have clear guiding significance for developing relevant model tests in the future.
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 cross-sectional view of a combined tail support and modified jet nozzle arrangement of the present invention;
FIG. 2 is a partial schematic view of a model precursor and prototype jet nozzle of an axisymmetric aeration model of the present invention;
FIG. 3 is a schematic illustration of the construction of a force measuring balance according to the invention;
FIG. 4 is a schematic structural view of an annular strut I and a fairing cone I in the combined aft support and modified jet nozzle of the present invention;
FIG. 5 is a schematic view of the construction of annular strut I in the combined aft support and modified jet nozzle apparatus of the present invention;
FIG. 6 is a schematic view of the fairing cone I of the combined aft support and modified jet nozzle assembly of the present invention;
FIG. 7 is a schematic structural view of the combined tail support and modified jet nozzle arrangement of the present invention;
FIG. 8 is a schematic structural view of a combined tail boom and modified jet nozzle apparatus (without a test housing) of the present invention;
FIG. 9 is a schematic view of the coupling structure of the dummy body and balance of the combined apparatus of the aft support and modified jet nozzle of the present invention;
FIG. 10 is a schematic structural view of a mold body of the combined aft support and modified jet nozzle apparatus of the present invention;
FIG. 11 is a schematic structural view of the combined back support, false tail support and modified jet nozzle arrangement of the present invention;
FIG. 12 is a partial schematic structural view of the combined back support, false tail support and modified jet nozzle arrangement of the present invention;
FIG. 13 is a partial schematic structural view of the combined back support, false tail support and modified jet nozzle arrangement of the present invention;
FIG. 14 is a schematic view of the construction of a fairing cone II of the combined back support, false tail support and modified jet nozzle assembly of the present invention;
FIG. 15 is a schematic structural view of an annular strut II and a fairing cone II of the combined back support, false tail support and modified jet nozzle of the present invention;
FIG. 16 is a schematic structural view of the annular strut II of the combined back support, false tail support and modified jet nozzle of the present invention;
FIG. 17 is a schematic structural view of a back support test housing of the combined back support, false tail support and modified jet nozzle apparatus of the present invention;
FIG. 18 is a schematic structural view of an adapter of the combined back support, false tail support and modified jet nozzle apparatus of the present invention;
FIG. 19 is a schematic structural view of the combined back support and prototype jet nozzle apparatus of the present invention;
FIG. 20 is a schematic cross-sectional view of a prototype jet nozzle of the combined back support and prototype jet nozzle apparatus of the present invention;
FIG. 21 is a schematic partial structural view of the combined back support and prototype jet nozzle apparatus of the present invention;
FIG. 22 is a schematic view of the connection configuration of the dummy body and balance of the combined back support and prototype jet nozzle apparatus of the present invention;
FIG. 23 is a schematic view of the modular body of the combined back support and prototype jet nozzle apparatus of the present invention.
The specific implementation mode is as follows:
the present invention is further described in detail below with reference to the attached drawings so that those skilled in the art can implement the invention by referring to the description text.
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 to 23 show an aerodynamic force measurement test device of an axisymmetric ventilation model according to the present invention, 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 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: tail support 2, back support 14 and false tail support 16;
correspondingly, the axial symmetry ventilation model aerodynamic force measurement test device comprises three combination modes: firstly, the combination of a tail support 2 and a modified tail nozzle 4; secondly, the combination of the back support 14, the false tail support 16 and the modified tail nozzle 4; thirdly, the combination of the back support 14 and the prototype jet nozzle 21;
wherein, in the combination of the tail support 2 and the modified tail pipe 4, the model body comprises a model precursor 3 and the modified tail pipe 4 which are connected by screw thread; the end part of the force measuring balance 1 is connected with the model main body, and the model front body 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 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 combination of the back support 14, the dummy nozzle support 16 and the modified jet nozzle 4, the model body (the structure of which is identical to that of the model body of the combination of the tail support and the modified jet nozzle) comprises the model front body 3 and the modified jet nozzle 4 which are connected by screw threads; 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 combination of the back support and the prototype tail pipe, the false tail support and the prototype tail pipe in the combination of the back support, the false tail support and the prototype tail pipe are removed, and the prototype tail pipe 21 is replaced, as shown in fig. 19-23, the model main body comprises a model precursor 3 and the prototype tail pipe 21 which are connected by screw threads; 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 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 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 supports (tail support and back support); the balance material adopts F141 and hardening and tempering hardness HRC 50.
In the technical scheme, compared with the prototype tail nozzle, the modified tail nozzle has the advantages that the molded surface is integrally contracted inwards, and the outlet of the tail nozzle is slightly expanded, 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: the device comprises a ring-shaped support rod I7 and a rectifying cone I8; the annular supporting rod I7 and the rectifying cone I8 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 support rod I7 is connected with the force measuring balance 1 through a flange 9, the rear end of the annular support rod I is connected with the rectifying cone I8, and the thickness of the annular support rod I is 20 mm; for installing pins and screws, a rectangular hole 10 is formed in the front end of the annular support rod I7 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 formed in the side face of the annular support rod I7, 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 in the annular support rod I; 4 drainage holes I13 are uniformly distributed in the annular support rod I7 from top to bottom, left to right and along the axial direction; the rectifying cone 8 is provided with a rectifying cone inclined hole 81; after the annular supporting rod I7 is connected with the rectifying cone I8, the inclined hole 12 on the annular supporting rod I is correspondingly communicated with the rectifying cone inclined hole 81; during testing, a balance lead enters a rectifying cone I8 through a wiring groove 11, an inclined hole 12 and a 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 I13 are uniformly arranged along the axial direction of the support rod from top to bottom and from left to right, and the drain holes I13 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.
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 technical scheme, the false tail support 16 comprises an annular strut II 18 with a discharge hole II 180 and a rectifying cone II 19, and the size and the arrangement mode of the false tail support are the same as those of a real tail strut (namely, a tail support in the combination of the tail support and the modified tail jet pipe); the annular support rod II and the rectifying cone II form 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 support rod II 18, four grooves 191 (the width of the groove needs to be larger than the diameter of the screw hole) are uniformly distributed on the rectifying cone II 19, four threaded holes 171 are arranged on the adapter 17 at intervals of 90 degrees along the circumferential direction in an X shape, four through holes 172 are arranged in a cross shape from top to bottom and from left to right (the diameter should be larger than that of the threaded hole on the annular support rod II 18), during the test, screws are arranged in the four threaded holes 171 arranged in the X shape to tightly press the annular support rod II 18 and the adapter 17, the screw holes 181 of the annular support rod II 18 and the grooves 191 of the rectifier cone II 19 penetrate through the four through holes 172 of the adapter by four screws, and are arranged in the four screw holes 181 arranged in the cross shape of the annular support rod II 18, compressing the rectifying cone II 19, and adjusting the front position and the rear position of the rectifying cone II 19 before compressing to ensure that the distance from the top of the conical surface of the rectifying cone II 19 to the tail part of the model is the same as the distance from the real rectifying cone I to the tail part of the model; the front end of the annular support rod II 18 extends into the model, but is not connected with the force measuring balance and the model; 4 discharge holes II 180 are uniformly distributed on the annular support rod II 18 along the axial direction from top to bottom, left to right.
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 II and a rectifying cone II and is used for guiding out tail jet flow.
The invention also provides a using method of the axial symmetry ventilation model aerodynamic force measurement test device, which comprises the following steps:
step one, carrying out a test by using a device of combination of a back support and a prototype tail nozzle to obtain test data C of each aerodynamic force/moment1；
Step two, carrying out a test by using a device of combination of back support, false tail support and modified tail nozzle to obtain test data C of each aerodynamic force/moment2；
Thirdly, carrying out a wind tunnel test by using a device of combination of a tail support and a modified tail nozzle to obtain test data C of each aerodynamic force/moment3；
Step four, the corrected final aerodynamic data, namely the aerodynamic characteristics of the real aircraft, C4：
C4＝C3-(C2-C1)
In the above technical solution, each aerodynamic force/moment includes: axial force, normal force, lateral force, pitch moment, yaw moment, and roll moment.
While embodiments of the invention have been described above, it is not limited to the applications set forth in the description and the embodiments, which are fully applicable in various fields of endeavor to which the invention pertains, and further modifications may readily be made by those skilled in the art, it being understood that the invention is not limited to the details shown and described herein without departing from the general concept defined by the appended claims and their equivalents.
Claims (10)
1. The utility model provides an axial symmetry model aerodynamic force measurement test device that ventilates 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 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: tail support, back support and false tail support;
correspondingly, the axial symmetry ventilation model aerodynamic force measurement test device comprises three combination modes: firstly, the combination of a tail support and a modified tail nozzle; secondly, the combination of a back support, a false tail support and a modified tail nozzle; thirdly, combining a back support and a prototype tail nozzle;
wherein, in the combination of the tail support and the modified tail pipe, the model main body comprises a model precursor and a modified tail pipe which are connected by screw threads; the front end 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 rear 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;
in the combination of the back support, the false tail support and the modified jet nozzle, the model main body comprises a model precursor and a modified jet nozzle which are connected by screw threads; the front end 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 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;
in the combination of the back support and the prototype tail pipe, the false tail support and the prototype tail pipe in the combination of the back support, the false tail support and the prototype tail pipe are removed, and the prototype tail pipe is replaced.
2. The device for testing the aerodynamic force measurement of an axisymmetric 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 axisymmetric draft model aerodynamic force measurement test device of claim 1, wherein said modified jet nozzle has an overall inwardly converging profile and a slight divergence at the jet nozzle exit compared to the prototype jet nozzle.
4. The aerodynamic force measurement test device of the axisymmetric aeration model according to claim 1, wherein gaps of 6mm and 8mm are respectively reserved between the rest part of the force balance and the model body and the test shell 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 axisymmetric breathing model aerodynamic force measurement test device of claim 1, wherein said tail support includes: the device comprises a ring-shaped support rod I and a rectifying cone I; the annular support rod I and the rectifying cone I are combined into a complete tail support in a cylindrical surface matching, pin positioning and screw tensioning mode; the front end of the annular support rod I is connected with the force measuring balance through a flange, the rear end of the annular support rod I is connected with the rectifying cone I, and the thickness of the annular support rod I is 20 mm; a rectangular hole is formed in the front end of the annular support rod I behind the flange; a wiring groove is formed in the side face of the annular support rod I, the front end of the wiring groove is communicated with a wiring groove of the force measuring balance, and the rear end of the wiring groove is communicated with an inclined hole in the annular support rod I; 4 drainage holes I are uniformly distributed in the annular support rod I along the axial direction from top to bottom, left to right; and a rectifying cone inclined hole is formed in the rectifying cone I.
6. The device for testing the aerodynamic force measurement of an axisymmetric ventilation model of claim 1, wherein said 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.
7. The axial symmetry ventilation model aerodynamic force measurement test device as claimed in claim 1, wherein the false tail support comprises an annular strut II with a drainage hole II and a rectifying cone II, and the size and the arrangement mode of the annular strut II and the rectifying cone II are the same as those of a real tail strut; and the annular supporting rod II and the rectifying cone II are combined into a complete false tail support in a cylindrical surface matching and screw pressing mode.
8. The device for testing the aerodynamic force measurement of an axisymmetric ventilation model of claim 1, wherein the rear end of the dummy tail support is sleeved in the adapter device, and a screw is used for pressing the rear end of the dummy tail support in the device.
9. Use of an axisymmetric breathing model aerodynamic force measurement test device according to any of claims 1-9, characterized in that it comprises the following steps:
step one, assembling by combining back support and prototype tail nozzlePerforming test to obtain test data C of each aerodynamic force/moment1；
Step two, carrying out a test by using a device of combination of back support, false tail support and modified tail nozzle to obtain test data C of each aerodynamic force/moment2；
Thirdly, carrying out a wind tunnel test by using a device of combination of a tail support and a modified tail nozzle to obtain test data C of each aerodynamic force/moment3；
Step four, the corrected final aerodynamic data, namely the aerodynamic characteristics of the real aircraft, C4：
C4＝C3-(C2-C1) 。
10. The method of using an axisymmetric ventilation model aerodynamic force measurement test device of claim 9, wherein each aerodynamic force/moment comprises: axial force, normal force, lateral force, pitch moment, yaw moment, and roll moment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010260367.2A CN111397838B (en) | 2020-04-03 | 2020-04-03 | Axial symmetry ventilation model aerodynamic force measurement test device and use method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010260367.2A CN111397838B (en) | 2020-04-03 | 2020-04-03 | Axial symmetry ventilation model aerodynamic force measurement test device and use method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111397838A true CN111397838A (en) | 2020-07-10 |
| CN111397838B CN111397838B (en) | 2021-09-07 |
Family
ID=71429456
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010260367.2A Active CN111397838B (en) | 2020-04-03 | 2020-04-03 | Axial symmetry ventilation model aerodynamic force measurement test device and use method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111397838B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111638033A (en) * | 2020-06-09 | 2020-09-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel model supports interference force measurement test constructional device |
| CN112051027A (en) * | 2020-09-16 | 2020-12-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Two-degree-of-freedom supporting device for supersonic wind tunnel model |
| CN112284676A (en) * | 2020-10-21 | 2021-01-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | Model supporting device applied to wind tunnel test |
| CN112816173A (en) * | 2021-04-19 | 2021-05-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Skeleton type part and sideslip angle test device |
| CN113588201A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Thermal jet flow interference test device and test method for high-altitude high-speed thin environment |
| CN115326350A (en) * | 2022-10-14 | 2022-11-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Motor-driven wind tunnel jet flow test equivalent simulation device and application method thereof |
| 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 |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1057523A (en) * | 1991-08-03 | 1992-01-01 | 北京光电技术研究所 | Direct method for real-time measurement of angle of side slip of wind tunnel and system thereof |
| JPH1137894A (en) * | 1997-07-23 | 1999-02-12 | Nkk Corp | Aerodynamic measuring device and lift/moment measuring system device using it |
| JP2000337995A (en) * | 1999-05-28 | 2000-12-08 | Mitsubishi Heavy Ind Ltd | Model support with abutment detector |
| CN104807610A (en) * | 2015-05-19 | 2015-07-29 | 中国航天空气动力技术研究院 | Sprayer nozzle used for tail jet flow interference test |
| CN105222984A (en) * | 2015-11-18 | 2016-01-06 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of high-speed wind tunnel tail supports horizontal course aerodynamic characteristic Interference Correction |
| CN105651480A (en) * | 2015-12-31 | 2016-06-08 | 空气动力学国家重点实验室 | Wind tunnel test tail support interference correction method and application thereof |
| CN105823615A (en) * | 2016-05-11 | 2016-08-03 | 中国空气动力研究与发展中心超高速空气动力研究所 | Mechanical-bearing supported small asymmetrical reentry body aerodynamic force measuring apparatus |
| CN207622977U (en) * | 2017-12-06 | 2018-07-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Tail jet Test Integrated model equipment in wind tunnel test |
| CN110207938A (en) * | 2019-06-14 | 2019-09-06 | 北京空天技术研究所 | Ventilating model force measuring method under free jet tunnel experimental condition |
| CN110207944A (en) * | 2019-06-26 | 2019-09-06 | 中国航天空气动力技术研究院 | A kind of wind tunnel experiment high-precision resistance measurement method and device |
-
2020
- 2020-04-03 CN CN202010260367.2A patent/CN111397838B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1057523A (en) * | 1991-08-03 | 1992-01-01 | 北京光电技术研究所 | Direct method for real-time measurement of angle of side slip of wind tunnel and system thereof |
| JPH1137894A (en) * | 1997-07-23 | 1999-02-12 | Nkk Corp | Aerodynamic measuring device and lift/moment measuring system device using it |
| JP2000337995A (en) * | 1999-05-28 | 2000-12-08 | Mitsubishi Heavy Ind Ltd | Model support with abutment detector |
| CN104807610A (en) * | 2015-05-19 | 2015-07-29 | 中国航天空气动力技术研究院 | Sprayer nozzle used for tail jet flow interference test |
| CN105222984A (en) * | 2015-11-18 | 2016-01-06 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of high-speed wind tunnel tail supports horizontal course aerodynamic characteristic Interference Correction |
| CN105651480A (en) * | 2015-12-31 | 2016-06-08 | 空气动力学国家重点实验室 | Wind tunnel test tail support interference correction method and application thereof |
| CN105823615A (en) * | 2016-05-11 | 2016-08-03 | 中国空气动力研究与发展中心超高速空气动力研究所 | Mechanical-bearing supported small asymmetrical reentry body aerodynamic force measuring apparatus |
| CN207622977U (en) * | 2017-12-06 | 2018-07-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Tail jet Test Integrated model equipment in wind tunnel test |
| CN110207938A (en) * | 2019-06-14 | 2019-09-06 | 北京空天技术研究所 | Ventilating model force measuring method under free jet tunnel experimental condition |
| CN110207944A (en) * | 2019-06-26 | 2019-09-06 | 中国航天空气动力技术研究院 | A kind of wind tunnel experiment high-precision resistance measurement method and device |
Non-Patent Citations (5)
| Title |
|---|
| QING MAO,等: "Numerical Study on Enhancing Heat Transfer of the Belt-type Resistance Heater in the Hypersonic Wind Tunnel", 《3RD INTERNATIONAL CONFERENCE ON FLUID MECHANICS AND INDUSTRIAL APPLICATIONS》 * |
| XIONG WANG等: "Fabrication, calibration and proof experiments in hypersonic wind tunnel for a novel MEMS skin friction sensor", 《MICROSYSTEM TECHNOLOGIES-MICRO-AND NANOSYSTEMS-INFORMATION STORAGE AND PROCESSING SYSTEMS》 * |
| 许晓斌 等: "吸气式飞行器高超声速风洞气动力试验技术研究进展", 《实验流体力学》 * |
| 许晓斌: "轴对称模型试验特种环式天平研制", 《中国空气动力学会测控技术专委会第六届四次学术交流会》 * |
| 谢飞 等: "吸气式高超声速飞行器气动力试验研究", 《第九届全国实验流体力学学术会议论文》 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111638033A (en) * | 2020-06-09 | 2020-09-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel model supports interference force measurement test constructional device |
| CN112051027A (en) * | 2020-09-16 | 2020-12-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Two-degree-of-freedom supporting device for supersonic wind tunnel model |
| CN112284676A (en) * | 2020-10-21 | 2021-01-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | Model supporting device applied to wind tunnel test |
| CN112816173A (en) * | 2021-04-19 | 2021-05-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Skeleton type part and sideslip angle test device |
| CN113588201A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Thermal jet flow interference test device and test method for high-altitude high-speed thin environment |
| 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 |
| CN115326350A (en) * | 2022-10-14 | 2022-11-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Motor-driven wind tunnel jet flow test equivalent simulation device and application method thereof |
| CN115326350B (en) * | 2022-10-14 | 2022-12-27 | 中国空气动力研究与发展中心高速空气动力研究所 | Motor-driven wind tunnel jet test equivalent simulation device and application method thereof |
| 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 |
| CN115628874B (en) * | 2022-12-20 | 2023-03-10 | 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111397838B (en) | 2021-09-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111397838B (en) | Axial symmetry ventilation model aerodynamic force measurement test device and use method | |
| CN106840591B (en) | A kind of experimental rig directly measuring jet flow thrust | |
| CN109250149B (en) | Wind tunnel test device for separation simulation of air suction type hypersonic vehicle fairing | |
| CN108088649B (en) | Model device for fixedly connecting spray pipe with shape in wind tunnel test and test method | |
| CN107860554A (en) | Tail jet Test Integrated model equipment and test method in wind tunnel test | |
| CN211504603U (en) | Aerodynamic force measurement test device of axisymmetric ventilation model of tail support | |
| CN105973565B (en) | Lateral jet system for wind-tunnel interference test | |
| CN112763177B (en) | Rail-controlled jet flow interference test device based on rod type balance and installation and positioning method thereof | |
| CN211504602U (en) | Axial symmetry ventilation model aerodynamic force measurement test device of back support-false tail support | |
| CN103048110A (en) | Experimental facility for realizing thrust deflexion and experimental technique thereof | |
| CN211373995U (en) | Test device for measuring hinge moment of control surface of axisymmetric ventilation model | |
| CN211178915U (en) | Separation wind tunnel test device for plane-symmetric hypersonic aircraft hood | |
| CN110793746B (en) | Wind tunnel test device for measuring thrust of oblique cutting spray pipe of hypersonic vehicle | |
| CN111337218A (en) | Mars wind tunnel with sand simulation function | |
| CN107655652B (en) | Air supply device and air supply method for small-thrust jet nozzle in wind tunnel test | |
| CN113588200B (en) | High-flow reverse jet test device and method for hypersonic aircraft | |
| CN113588202A (en) | Multi-body thermal separation test simulation device and test method for high-altitude high-speed thin environment | |
| CN111780941A (en) | Aircraft force measurement test model and method | |
| JP2011252830A (en) | Support equipment for wind tunnel test model | |
| CN211504600U (en) | False tail support for axial symmetry ventilation model aerodynamic force measurement test device | |
| CN114486166A (en) | Model and system for control surface jet flow interference force measurement test | |
| CN106500957A (en) | Ventilating model is tested in a kind of water | |
| CN110567673B (en) | Wind tunnel test method for thrust measurement of oblique cutting nozzle of hypersonic vehicle | |
| CN110057534B (en) | Device and method for connecting balance and ventilation type support rod | |
| CN211602351U (en) | Tail support for axial symmetry ventilation model aerodynamic force measurement test |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |