CN115165294A - Test device for simulating ablation gas injection coupling effect - Google Patents
Test device for simulating ablation gas injection coupling effect Download PDFInfo
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- CN115165294A CN115165294A CN202210772282.1A CN202210772282A CN115165294A CN 115165294 A CN115165294 A CN 115165294A CN 202210772282 A CN202210772282 A CN 202210772282A CN 115165294 A CN115165294 A CN 115165294A
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- 238000002679 ablation Methods 0.000 title claims abstract description 52
- 238000002347 injection Methods 0.000 title claims abstract description 35
- 239000007924 injection Substances 0.000 title claims abstract description 35
- 238000012360 testing method Methods 0.000 title claims abstract description 24
- 230000001808 coupling effect Effects 0.000 title claims abstract description 21
- 239000000463 material Substances 0.000 claims abstract description 26
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 15
- 239000010959 steel Substances 0.000 claims abstract description 15
- 238000007789 sealing Methods 0.000 claims abstract description 14
- 239000007789 gas Substances 0.000 claims description 83
- 230000001105 regulatory effect Effects 0.000 claims description 9
- 230000000087 stabilizing effect Effects 0.000 claims description 6
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 4
- 229910052734 helium Inorganic materials 0.000 claims description 3
- 229910052754 neon Inorganic materials 0.000 claims description 3
- 239000001307 helium Substances 0.000 claims description 2
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims description 2
- GKAOGPIIYCISHV-UHFFFAOYSA-N neon atom Chemical compound [Ne] GKAOGPIIYCISHV-UHFFFAOYSA-N 0.000 claims description 2
- 229910052757 nitrogen Inorganic materials 0.000 claims description 2
- 238000003780 insertion Methods 0.000 claims 1
- 230000037431 insertion Effects 0.000 claims 1
- 238000004088 simulation Methods 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 13
- 238000000034 method Methods 0.000 description 16
- 230000008859 change Effects 0.000 description 9
- 230000008569 process Effects 0.000 description 6
- 238000011160 research Methods 0.000 description 5
- 230000009471 action Effects 0.000 description 3
- 230000035699 permeability Effects 0.000 description 3
- 239000011148 porous material Substances 0.000 description 3
- 230000001276 controlling effect Effects 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000000737 periodic effect Effects 0.000 description 2
- 238000010998 test method Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010891 electric arc Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000000859 sublimation Methods 0.000 description 1
- 230000008022 sublimation Effects 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
-
- 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
- G01M9/067—Measuring arrangements specially adapted for aerodynamic testing dealing with flow visualisation
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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- General Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to a test device for simulating the injection coupling effect of ablative gas, wherein the front section of a model inner shell and the rear section of the model inner shell are sequentially arranged along the axial direction to form a combined body, and a model outer shell is sleeved outside the combined body; an air supply cavity is formed between the outer wall of the combination body and the inner wall of the model shell; a sealing gasket which divides the cavity into an upper air supply inner cavity and a lower air supply inner cavity is arranged in the air supply cavity; the balance is fixedly connected with the rear section of the model inner shell; the model rear cover is fixedly connected with the model outer shell and the rear section of the model inner shell; an upper gas circuit and a lower gas circuit are arranged in the balance; two flow passages are processed in the rear section of the inner shell of the model; the material of the mould shell enables the gaseous medium in the gas supply cavity to seep outwards. According to the test device, the inner air supply cavity is formed by the outer shell of the air-permeable steel material model and the inner shell of the steel material model, after the air is supplied by the external air channel, the pressure difference is formed between the inner air supply cavity of the model and the outside of the model, and the air seeps to the surface of the model through the air-permeable steel model, so that the purpose of simulating the injection effect of the ablation air is achieved.
Description
Technical Field
The invention relates to a test device for simulating an ablation gas injection coupling effect, and belongs to the field of test aerodynamics.
Background
And the reentry aircraft generates pneumatic ablation in the process of reentry to the atmosphere. Then the ablation material on the surface of the aircraft is heated violently by the friction of the outside air, and is subjected to physical changes such as decomposition, melting, evaporation, sublimation and the like and chemical reaction with the surrounding environment gas, so that the material surface has large mass loss and is mixed into a boundary layer, and the thickness of the boundary layer can be changed by the injection effect of the material, and the aerodynamic characteristics of the aircraft are influenced.
Currently, wind tunnel test research aiming at the ablation and aerodynamic characteristic coupling effect of the reentry aircraft is respectively carried out and independently evaluated. If an electric arc heater or a gas flow device is used for carrying out a high-temperature ablation test, a pneumatic ablation result of an ablation material in the real flight of the aircraft is obtained; or the ablation process is simulated by adopting a low-temperature ablation material in the hypersonic wind tunnel, and the influence of the pneumatic parameters on the ablation appearance and the ablation surface form is focused. And after the shape change results before and after ablation are obtained, the aerodynamic characteristics of the aircraft are analyzed through static and dynamic force measurement tests.
Therefore, on one hand, the research purposes of the test methods are to obtain the ablation appearance and surface form change results of the reentry aircraft, and the ejection effect that the ablated material is subjected to mass loss after air friction and mixed into a boundary layer in the ablation process cannot be simulated. On the other hand, the wind tunnel test method for separately analyzing the ablation effect and the aerodynamic characteristic influence is in a decoupling research mode, and the coupling effect and the time-varying characteristic between the ablation effect and the aerodynamic characteristic cannot be directly predicted and researched.
Disclosure of Invention
The technical problems solved by the invention are as follows: the defects in the prior art are overcome, the test device for simulating the ablation gas injection coupling effect is provided, and the ablation gas injection and pneumatic characteristic coupling effect of the reentry aircraft can be simulated.
The technical solution of the invention is as follows:
a test device for simulating ablation gas injection coupling effect comprises: the device comprises a model outer shell, a model inner shell front section, a model inner shell rear section, a balance, a model rear cover and a sealing gasket;
the front section of the inner shell of the model and the rear section of the inner shell of the model are sequentially arranged along the axial direction to form a combined body;
the model shell is sleeved outside the combined body;
an air supply cavity is formed between the outer wall of the combination body and the inner wall of the model shell;
a sealing gasket is arranged in the air supply cavity along the axial direction, so that the cavity is divided into an upper air supply cavity and a lower air supply cavity;
the balance is arranged in the rear section of the model inner shell, and the front end of the balance is fixedly connected with the rear section of the model inner shell; the model rear cover is fixedly connected with the model outer shell and the rear end of the rear section of the model inner shell;
an upper air path and a lower air path are arranged in the balance;
two channels which enable an upper air passage to be communicated with the upper air supply inner cavity and enable a lower air passage to be communicated with the lower air supply inner cavity are processed in the rear section of the model inner shell;
the material of the model shell can enable the gas medium in the gas supply cavity to seep outwards;
an upper air passage and a lower air passage in the balance are connected with an external air source.
Preferably, the connecting areas of the front section of the inner shell and the rear section of the inner shell are in clearance fit.
Preferably, ribs or grooves for installing sealing gaskets are arranged on the outer walls of the front section and the rear section of the model inner shell, and the ribs or grooves and the sealing gaskets form an inserting structure.
Preferably, the gas medium is any one of air, nitrogen, neon or helium.
Preferably, the method further comprises the following steps: a pressure regulating and stabilizing valve and a pressure sensor; the pressure regulating and stabilizing valve is matched with the pressure sensor for use and is used for regulating the airflow pressure of the gas medium flowing into the upper gas path and the lower gas path.
Preferably, the method further comprises the following steps: a pressure sensor; and the upper air path and the lower air path are respectively provided with a pressure sensor for detecting the air flow pressure.
Preferably, the method further comprises the following steps: a flow meter; and the upper gas circuit and the lower gas circuit are respectively provided with a flowmeter for detecting the mass flow of the gas flow.
Preferably, the material of the model outer shell is a breathable steel material, and the front section of the model inner shell and the rear section of the model inner shell are made of steel materials.
Preferably, the wall thickness of the mould shell increases with increasing internal diameter.
Preferably, the method further comprises the following steps: the system comprises a first flow servo control valve, a second flow servo control valve and an upper computer;
the upper computer collects the deformation and the aerodynamic force of the balance through a resistance strain gauge adhered to the balance, and the upper computer respectively adjusts the gas mass flow in the upper gas circuit and the lower gas circuit through a first flow servo control valve and a second flow servo control valve.
Preferably, the method further comprises the following steps: a second tensioning screw; the model rear cover is fixedly connected with the rear ends of the model outer shell and the model inner shell rear section through a plurality of second tensioning screws which are uniformly distributed in the circumferential direction.
Preferably, the method further comprises the following steps: a first tensioning screw and washer; the front end of the balance is of a cone frustum structure, and the front end of the rear section of the model inner shell is provided with a taper hole matched with the cone frustum structure; the front end of the balance is inserted into a taper hole at the front end of the rear section of the model inner shell and is fixedly connected with the gasket through a first tensioning screw.
Compared with the prior art, the invention has the following advantages:
(1) The invention can simulate the gas injection effect that the ablation material on the surface of the aircraft is rubbed by the outside air, decomposed, melted, evaporated, sublimated or chemically reacted and loses mass and is mixed into the boundary layer in the process of reentering the aircraft and ablating. And the purpose of simulating ablation injection of the whole or different model surface positions can be achieved by adjusting gas components of the gas source, the pressure and the flow of the gas source, the air permeability of the model breathable material and the wall thickness of the model.
(2) The method can simulate the ejection of the ablation gas of the reentry aircraft and measure the motion and aerodynamic effect of the model at the same time, and has the capability of researching the coupling effect of the ejection of the ablation gas of the reentry aircraft and the aerodynamic characteristic and the time-varying characteristic in a wind tunnel test.
Drawings
FIG. 1 is a view from the tail to the head of the present invention.
Fig. 2 isbase:Sub>A sectional view taken along linebase:Sub>A-base:Sub>A of fig. 1.
Fig. 3 is a sectional view taken along line B-B of fig. 1.
Fig. 4 is a sectional view of C-C in fig. 1.
Fig. 5 is a partial schematic view of the external air passage of the present invention.
Detailed Description
The invention relates to a test device for simulating the injection coupling effect of ablative gas, which mainly comprises two parts: a mold assembly portion and an external gas circuit portion. As shown in fig. 1 to 4, wherein the mold assembly part includes: the device comprises a model outer shell 1, a model inner shell front section 2, a model inner shell rear section 3, a balance 4, a model rear cover 5, a first tensioning screw 6, a gasket 7, a second tensioning screw 8, a sealing gasket 11, an upper air supply inner cavity 12 and a lower air supply inner cavity 13. As shown in fig. 5, the outer air path portion includes: the device comprises an air source 14, a third pressure sensor 15, a pressure stabilizing and regulating valve 16, a first pressure sensor 17, a second pressure sensor 18, a first flow meter 19, a second flow meter 20, a first flow servo control valve 21, a second flow servo control valve 22 and an upper computer 23. The two parts are connected by an upper air passage 9 and a lower air passage 10.
In the model assembly part, a balance is similar to a conventional wind tunnel test balance, and the deformation and aerodynamic force of an elastic beam are measured by using a resistance strain gauge attached to the elastic beam of the balance. The balance is provided with an elastic beam in the middle, a pitching free vibration system is formed after the balance and the model are installed, and meanwhile, the balance strain gauge is used for measuring the motion of the model and the aerodynamic force applied to the model.
The air-permeable steel material model outer shell and the steel material model inner shell form an internal air supply cavity, the internal air supply cavity of the model forms pressure difference with the outside of the model after external air path air supply, and air seeps to the surface of the model through the air-permeable steel model, so that the purpose of simulating ablation air injection effect is achieved. And simultaneously, the balance is used for measuring the motion and aerodynamic force of the model, and a balance signal is fed back to the upper computer to control the external gas path flow servo control valve to adjust the gas path gas flow change in real time.
When the wind tunnel balance is installed, the rear end of the balance 4 is fixedly connected with the wind tunnel supporting strut mechanism through the conical surface and the wedge. The conical surface of the rear section 3 of the inner shell of the model is firstly sleeved on the front end (the left side as shown in figure 2) of the balance 4 and is tensioned and fixed by a first tensioning screw 6 and a gasket 7. Then, the model inner shell front section 2 is sleeved on the model inner shell rear section 3, the model outer shell 1 is sleeved on the model inner shell front section 2 and the model inner shell rear section 3, the model rear cover 5 is covered on the model rear portion, and the model outer shell 1, the model inner shell rear section 3 and the model rear cover 5 are fixedly connected by the second tensioning screw 8. After installation, an internal air supply cavity is formed between the model outer shell 1 and the model inner shell front section 2 and the model inner shell rear section 3. The model outer shell 1 is made of breathable steel materials, and the front section 2 and the rear section 3 of the model inner shell are made of steel materials.
Because the ablation conditions of the windward side and the leeward side in the ablation process of the reentry aircraft are different greatly: the erosion of the windward side is violent, the ablation ejection effect is large, the mass flow of the ejection gas is high, and the leeward side is not. The ablation injection effect of the windward side and the leeward side of the model needs to be simulated respectively, and the gas mass flow of the model needs to be controlled respectively. Rib structures are respectively designed on two sides of the front section 2 and the rear section 3 of the model inner shell, and concave sealing strips 11 can be embedded into the rib structures. After being connected with the model outer shell 1, the sealing strip 11 can divide the air supply inner cavity inside the model into an upper air supply inner cavity 12 and a lower air supply inner cavity 13 which are independent, and an upper air path 9 and a lower air path 10 are communicated in the rear section 3 of the model inner shell and the balance 4 and are respectively connected with the upper air supply inner cavity 12 and the lower air supply inner cavity 13.
The upper air passage 9 and the lower air passage 10 are connected to an external air passage. The gas is supplied by a gas source 14, and is divided into an upper gas path 9 and a lower gas path 10 after being regulated to the required gas flow pressure through a pressure regulating and stabilizing valve 16 and a third pressure sensor 15. The two gas paths respectively measure and acquire the gas flow pressure through a first pressure sensor 17 and a second pressure sensor 18, and respectively measure and acquire the gas flow mass and flow rate change through a first flowmeter 19 and a second flowmeter 20. After the balance 4 collects the model motion change signal, the model motion change signal is fed back to the upper computer 23, and the first flow servo control valve 21 and the second flow servo control valve 22 are controlled through a given control law, so that the purposes of respectively adjusting the gas in the upper gas path 9 and the lower gas path 10 to generate the dynamic periodic change of the mass flow with the same frequency, the set amplitude, the set average value and the phase difference are achieved. The upper/lower gas circuit is connected with the model assembly part to achieve the purpose of respectively simulating, controlling and collecting the ablation gas injection action of the upper and lower surfaces (windward surface and leeward surface) of the model.
The working principle of the invention is as follows:
in a wind tunnel test environment, a free vibration system is formed by the test device, the model freely vibrates in the wind tunnel, and the balance measures the motion of the model and the aerodynamic force applied to the model. After the balance 4 collects the model motion change signal, the signal is fed back to the upper computer 23, the flow servo control valves of the two gas paths are controlled by a given control law to dynamically adjust the mass flow of the gas in each gas path, and dynamic periodic changes of the mass flow with the vibration frequency, the set amplitude, the set mean value and the phase difference of the model are generated.
In order to simulate different ablation conditions of the windward surface and the leeward surface in the ablation process of the reentry aircraft, the inner cavity of the model is divided into an upper part and a lower part which are independent by a sealing gasket 11 and respectively connected with an upper gas circuit and a lower gas circuit, so that the aim of respectively simulating, controlling and collecting the ablation gas injection action of the upper surface and the lower surface (the windward surface and the leeward surface) of the model is fulfilled.
During testing, the appearance of the model simulating ablation injection is acted by aerodynamic force in the wind tunnel, the motion and aerodynamic force are collected by a balance and feedback-controlled to ablate injection gas mass flow, and the change of the injection effect influences the aerodynamic force action on the model. The ablation gas injection effect and the pneumatic characteristic form a mutual feedback closed loop, so that the research on the coupling effect of the ablation gas injection and the pneumatic characteristic is facilitated.
According to different requirements of ablation injection of different research objects, the invention can adjust the components of ablation injection gas and the total mass flow. The method and principle are as follows: gas source gas compositions are adjusted according to molecular weight or specific heat ratio, and gas compositions that may be used include, but are not limited to: air, N 2 Ne and He; the model shell 1 is made of a breathable steel material selected according to air permeability, and the types of breathable steel materials that can be used include, but are not limited to: PM-35-7 (mean pore size 7 μm), PM-35-25 (mean pore size 25 μm), PM-35-35 (mean pore size 35 μm);
meanwhile, due to the fact that ablation injection conditions of different surface positions of the model are different, the invention can adjust the mass flow of the ablation injection gas of different surface positions of the model. The method and principle are as follows: the wall thickness of the model shell 1 is different in the length direction, and the air permeability of the breathable steel material is inversely proportional to the material thickness, so that the mass flow of the injection gas at the thinner part of the model wall thickness is larger, and vice versa, and the purpose of simulating the ablation injection effect of different model surface positions can be achieved.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above. In the present embodiment, the technical features in the embodiments may be combined with each other without conflict.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (12)
1. The utility model provides a test device that simulation ablation gas draws penetrates coupling effect which characterized in that includes: the device comprises a model outer shell (1), a model inner shell front section (2), a model inner shell rear section (3), a balance (4), a model rear cover (5) and a sealing gasket (11);
the front section (2) of the inner shell of the model and the rear section (3) of the inner shell of the model are sequentially arranged along the axial direction to form a combined body;
the model shell (1) is sleeved outside the combination body;
an air supply cavity is formed between the outer wall of the combination body and the inner wall of the model shell (1);
a sealing gasket (11) is arranged in the air supply cavity along the axial direction, and the air supply cavity is divided into an upper air supply cavity (12) and a lower air supply cavity (13) by the sealing gasket (11);
the balance (4) is arranged inside the rear section (3) of the model inner shell, and the front end of the balance (4) is fixedly connected with the front end of the rear section (3) of the model inner shell; the model rear cover (5) is fixedly connected with the model outer shell (1) and the rear end of the model inner shell rear section (3);
an upper gas circuit (9) and a lower gas circuit (10) are arranged in the balance (4);
two channels which enable an upper air channel (9) to be communicated with an upper air supply inner cavity (12) and a lower air channel (10) to be communicated with a lower air supply inner cavity (13) are processed in the rear section (3) of the model inner shell;
the material of the model shell (1) can enable the gas medium in the gas supply cavity to seep outwards;
an upper air path (9) and a lower air path (10) in the balance (4) are connected with an external air source (14).
2. The test device for simulating the ablation gas injection coupling effect according to claim 1, wherein the connection region of the front section (2) of the model inner shell and the connection region of the rear section (3) of the model inner shell are in clearance fit.
3. The device for simulating the ablation gas injection coupling effect according to claim 1, wherein ribs or grooves for mounting the sealing gaskets (11) are arranged on the outer walls of the front section (2) and the rear section (3) of the model inner shell, and the ribs or grooves and the sealing gaskets (11) form an insertion structure.
4. The device for simulating the ablation gas injection coupling effect according to claim 1, wherein the gas medium is any one of air, nitrogen, neon and helium.
5. The device of claim 1, further comprising: a pressure regulating and stabilizing valve (16) and a pressure sensor (15); the pressure regulating and stabilizing valve (16) is matched with the pressure sensor (15) for use and is used for regulating the airflow pressure of the gas medium flowing into the upper gas circuit (9) and the lower gas circuit (10).
6. The device of claim 1, further comprising: a pressure sensor; and the upper air path (9) and the lower air path (10) are respectively provided with a pressure sensor for detecting the air flow pressure.
7. The device of claim 1, further comprising: a flow meter; the upper gas circuit (9) and the lower gas circuit (10) are respectively provided with a flowmeter for detecting the mass flow of the gas flow.
8. The test device for simulating the ablation gas injection coupling effect according to claim 1, wherein the model outer shell (1) is made of a breathable steel material, and the front section (2) and the rear section (3) of the model inner shell are made of a steel material.
9. A test device for simulating the ablation gas injection coupling effect according to any one of claims 1 to 8, characterized in that the wall thickness of the model shell (1) is increased along with the increase of the inner diameter.
10. The test device for simulating the ablation gas injection coupling effect according to any one of claims 1 to 8, further comprising: a first flow servo control valve (21), a second flow servo control valve (22) and an upper computer (23);
the upper computer (23) collects the deformation and the pneumatic force of the balance (4) through a resistance strain gauge adhered to the balance (4), and the upper computer (23) respectively adjusts the mass flow of gas in the upper gas circuit (9) and the lower gas circuit (10) through the first flow servo control valve (21) and the second flow servo control valve (22).
11. The test device for simulating the ablation gas injection coupling effect according to any one of claims 1 to 8, characterized by further comprising: a second tensioning screw (8); and the model rear cover (5) is fixedly connected with the rear ends of the model outer shell (1) and the model inner shell rear section (3) through a plurality of second tensioning screws (8) which are uniformly distributed in the circumferential direction.
12. The test device for simulating the ablation gas injection coupling effect according to any one of claims 1 to 8, further comprising: a first tensioning screw (6) and a shim (7); the front end of the balance (4) is of a cone frustum structure, and a taper hole matched with the cone frustum structure is processed at the front end of the rear section (3) of the model inner shell; the front end of the balance (4) is inserted into a taper hole at the front end of the rear section (3) of the model inner shell and is fixedly connected with a gasket (7) through a first tensioning screw (6).
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115824575A (en) * | 2023-02-22 | 2023-03-21 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test method for obtaining influence of model surface micro-jet on aerodynamic characteristics |
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| CN113390600A (en) * | 2021-07-26 | 2021-09-14 | 中国空气动力研究与发展中心计算空气动力研究所 | Shock tunnel test simulation device and method for pneumatic thermal effect of pyrolysis gas |
| CN113884273A (en) * | 2021-08-30 | 2022-01-04 | 中国航天空气动力技术研究院 | Wind tunnel test standard model for simultaneously measuring aerodynamic force and surface heat flow |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115824575A (en) * | 2023-02-22 | 2023-03-21 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test method for obtaining influence of model surface micro-jet on aerodynamic characteristics |
| CN115824575B (en) * | 2023-02-22 | 2023-04-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test method for obtaining influence of model surface micro-jet on aerodynamic characteristics |
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