CN215726701U - Hypersonic wind tunnel rod type balance heat shield - Google Patents
Hypersonic wind tunnel rod type balance heat shield Download PDFInfo
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- CN215726701U CN215726701U CN202121811159.3U CN202121811159U CN215726701U CN 215726701 U CN215726701 U CN 215726701U CN 202121811159 U CN202121811159 U CN 202121811159U CN 215726701 U CN215726701 U CN 215726701U
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Abstract
The utility model discloses a hypersonic wind tunnel rod type balance heat shield. The rod balance heat shield comprises a front heat shield and a rear heat shield; the front heat shield comprises a conical section and a pipe section which are integrally processed and formed, the conical section is sleeved on a head cone of the rod type balance and is fixed in a conical surface matching and screw tensioning mode, the pipe section extends backwards and is sleeved on the front half section of the middle section of the rod type balance, and an isolation circular seam I is arranged between the pipe section and the front half section of the measuring section; the rear heat insulation cover comprises a heat insulation ring and a heat insulation sleeve which are processed in a split mode, the heat insulation ring is sleeved and fixed on the balance support rod, the heat insulation sleeve is sleeved and fixed on the heat insulation ring, the heat insulation sleeve extends forwards, the front end of the heat insulation sleeve is sleeved at the rear end of the pipe section, and an isolation circular seam II is arranged between the front end of the heat insulation sleeve and the rear end of the pipe section. The labyrinth type heat insulation protection device formed by the rod type balance heat insulation cover can protect the damage of heat energy or external force to the rod type balance strain element, and the measurement accuracy is ensured.
Description
Technical Field
The utility model belongs to the technical field of high-speed wind tunnel tests, and particularly relates to a rod type balance heat shield for a hypersonic wind tunnel.
Background
A rod balance is a measuring device that converts a physical quantity (force or moment) of a non-electrical quantity into an electrical signal based on the principle of non-electrical quantity measurement. The rod balance consists of a strain element (elastic sensitive element), a strain gauge and a measuring circuit (measuring bridge). The rod balance is widely applied to the high-speed wind tunnel force measurement test, and is generally installed in a test model due to small volume, so that the size, the direction and the acting point of an aerodynamic load acting on the test model are measured.
The hypersonic wind tunnel test model is generally a metal test model, and the surface temperature of the metal test model is very high in the hypersonic wind tunnel test process. Traditional rod-type balance protector mainly is to separate the heat exchanger, separates the heat exchanger and can prevent that rod-type balance body temperature is too high to lead to the too big or circuit damage of temperature effect. The typical heat shield comprises a conical section and a pipe section which are integrally processed and formed, the heat shield is made of heat insulating materials such as glass fiber reinforced plastics and the like, the conical section is arranged on a head cone of the rod type balance and used for isolating the rod type balance from a metal test model, the pipe section extends backwards and is sleeved on the rod type balance, and an isolation gap is formed between the pipe section and the rod type balance. Some lengths of pipe sections of the heat shield are longer, the front measuring section and the rear measuring section of the rod type balance are covered, some lengths of the pipe sections are shorter, only the front measuring section of the rod type balance is covered, and the heat protection of the rear measuring section depends on an inner cavity at the tail part of the test model. Although the head of the test model is opposite to the air flow and the temperature is very high, the rod balance and the head of the test model are physically separated by a heat shield, and the temperature of a strain element conducted to a front measuring section of the rod balance is greatly reduced; and the inner cavity of the tail part of the test model is a dead water area, the air flow speed is basically zero, most of heat at the tail part of the test model can be taken away by hypersonic air flow, and the temperature near the strain element at the rear section of the rod balance cannot be too high, so that mechanical damage cannot be caused.
In order to improve the range, the advanced hypersonic flight vehicle adopts a cruise-level and boosting-level multi-level series structure. The cruise-level model of the multistage hypersonic wind tunnel test model is small in cross section size relative to the boosting-level projectile body, and the cruise-level model of the multistage hypersonic wind tunnel test model is not suitable for mounting a rod balance due to insufficient inner cavity space after the cruise-level model is reduced in equal proportion, and the rod balance is generally mounted on the boosting-level model of the multistage hypersonic wind tunnel test model. If the booster stage model is short, the rear measuring section of the rod balance is exposed at the tail of the test model, on one hand, a strain element of the rear measuring section of the rear section of the rod balance is easily damaged by airflow machinery, and on the other hand, the strain element of the whole rod balance generates abnormal strain due to high-speed high-temperature airflow, so that the rod balance cannot accurately measure aerodynamic force. The mode that adopts the extension to separate the heat exchanger can carry out effective thermal protection to the back measuring section of rod balance. However, in the hypersonic wind tunnel test, if the heat shield is exposed in hypersonic airflow, the heat shield itself will be subjected to aerodynamic force and then is transmitted forwards to the rod balance, so that the aerodynamic force measured by the rod balance is the resultant force of the aerodynamic force of the multistage hypersonic wind tunnel test model and the aerodynamic force of the heat shield, and the aerodynamic force cannot be distinguished, and the purpose of the hypersonic wind tunnel test cannot be achieved.
At present, the development of a hypersonic wind tunnel rod balance heat shield is urgently needed.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem of providing a hypersonic wind tunnel rod type balance heat shield.
The rod type balance comprises a head cone, a front measuring section, a balance middle section, a rear measuring section and a tail cone which are sequentially connected from front to back, and the tail cone of the rod type balance is fixedly connected with a balance support rod before the hypersonic wind tunnel rod type balance heat shield is used; the utility model discloses a rod type balance heat shield for a hypersonic wind tunnel, which is characterized in that the rod type balance heat shield comprises a front heat shield and a rear heat shield;
the front heat shield comprises a conical section and a pipe section which are integrally processed and formed, the conical section is sleeved on a head cone of the rod type balance and is fixed in a conical surface matching and screw tensioning mode, the pipe section extends backwards and is sleeved on the front half section of the middle section of the rod type balance, and an isolation circular seam I is arranged between the pipe section and the front half section of the measuring section;
the rear heat insulation cover comprises a heat insulation ring and a heat insulation sleeve which are processed in a split mode, the heat insulation ring is sleeved and fixed on the balance support rod, the heat insulation sleeve is sleeved and fixed on the heat insulation ring, the heat insulation sleeve extends forwards, the front end of the heat insulation sleeve is sleeved at the rear end of the pipe section, and an isolation circular seam II is arranged between the front end of the heat insulation sleeve and the rear end of the pipe section;
the width of the gap between the isolation circular seam I and the isolation circular seam II is 2 mm-3 mm.
Furthermore, a transition conical section which is in transition with the heat insulation sleeve is also arranged on the balance support rod.
The front heat shield and the rear heat shield in the rod balance heat shield of the hypersonic wind tunnel are made of glass fiber reinforced plastics.
The labyrinth type heat insulation protection device formed by the rod type balance heat insulation cover of the hypersonic wind tunnel can protect the damage of heat energy or external force to the strain element of the rod type balance, and ensure that the rod type balance can accurately measure the aerodynamic force of the multistage hypersonic wind tunnel test model.
Drawings
FIG. 1 is a schematic structural view of a hypersonic wind tunnel rod balance heat shield according to the present invention;
FIG. 2 is a schematic diagram of a multistage hypersonic wind tunnel test model provided with the hypersonic wind tunnel rod balance heat shield.
In the figure, 1, a front heat shield 2, a rear heat shield 3, a rod balance 4, a balance support rod 5, a cruise model 6 and a boosting model;
101. a cone section 102, a pipe section;
201. heat insulating ring 202, heat insulating sleeve;
301. a nose cone 302, a front measuring section 303, a balance middle section 304, a rear measuring section 305 and a tail cone.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
Example 1
The rod balance 3 comprises a nose cone 301, a front measuring section 302, a balance middle section 303, a rear measuring section 304 and a tail cone 305 which are sequentially connected from front to back, and the tail cone 305 of the rod balance 3 is fixedly connected with the balance support rod 4 before the hypersonic wind tunnel rod balance heat shield is used.
The applied multistage hypersonic wind tunnel test model of the embodiment is a two-stage hypersonic wind tunnel test model, and comprises a cruise-stage model 5 and a boosting-stage model 6 which are sequentially connected from front to back;
as shown in fig. 1, the hypersonic wind tunnel rod balance heat shield of the embodiment comprises a front heat shield 1 and a rear heat shield 2;
the front heat shield 1 comprises a conical section 101 and a pipe section 102 which are integrally processed and formed, the conical section 101 is sleeved on a head cone 301 of the rod type balance 3 and is fixed in a conical surface matching and screw tightening mode, the pipe section 102 extends backwards and is sleeved on the front half section of a balance middle section 303 of the rod type balance 3, and an isolation annular seam I is arranged between the pipe section 102 and the front half section of a measuring section 302;
the rear heat shield 2 comprises a heat insulation ring 201 and a heat insulation sleeve 202 which are processed in a split mode, the heat insulation ring 201 is sleeved and fixed on the balance support rod 4, the heat insulation sleeve 202 is sleeved and fixed on the heat insulation ring 201, the heat insulation sleeve 202 extends forwards, the front end of the heat insulation sleeve 202 is sleeved at the rear end of the pipe section 102, and an insulation ring seam II is arranged between the front end of the heat insulation sleeve 202 and the rear end of the pipe section 102;
the width of the gap between the isolation circular seam I and the isolation circular seam II is 2 mm-3 mm.
Furthermore, a transition conical section which is in transition with the heat insulation sleeve is also arranged on the balance support rod.
As shown in fig. 2, the hypersonic wind tunnel rod balance heat shield of the present embodiment is installed in the booster stage model 6, and the heat shield ring 201 and part of the heat shield sleeve 202 extend out of the booster stage model 6.
The front heat shield and the rear heat shield in the rod balance heat shield of the hypersonic wind tunnel are made of glass fiber reinforced plastics.
While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the utility model as defined in the appended claims.
Claims (2)
1. The hypersonic wind tunnel rod type balance heat shield comprises a rod type balance (3) and a hypersonic wind tunnel rod type balance support rod (4), wherein the rod type balance (3) comprises a head cone (301), a front measuring section (302), a balance middle section (303), a rear measuring section (304) and a tail cone (305) which are sequentially connected from front to back, and the tail cone (305) of the rod type balance (3) is fixedly connected with a balance support rod (4) before the rod type balance heat shield is used; the bar balance heat shield is characterized by comprising a front heat shield (1) and a rear heat shield (2);
the front heat shield (1) comprises a conical section (101) and a pipe section (102) which are integrally machined and formed, the conical section (101) is sleeved on a head cone (301) of the rod type balance (3) and is fixed in a conical surface matching and screw tensioning mode, the pipe section (102) extends backwards and is sleeved on the front half section of a balance middle section (303) of the rod type balance (3), and an isolation annular seam I is arranged between the pipe section (102) and a front measuring section (302);
the rear heat insulation cover (2) comprises a heat insulation ring (201) and a heat insulation sleeve (202) which are processed in a split mode, the heat insulation ring (201) is sleeved and fixed on the balance support rod (4), the heat insulation sleeve (202) is sleeved and fixed on the heat insulation ring (201), the heat insulation sleeve (202) extends forwards, the front end of the heat insulation sleeve (202) is sleeved at the rear end of the pipe section (102), and an insulation annular seam II is arranged between the front end of the heat insulation sleeve (202) and the rear end of the pipe section (102);
the width of the gap between the isolation circular seam I and the isolation circular seam II is 2 mm-3 mm.
2. The hypersonic wind tunnel rod balance heat shield according to claim 1, characterized in that a transition taper section which is in transition with the heat shield sleeve (202) is further arranged on the balance support rod (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121811159.3U CN215726701U (en) | 2021-08-05 | 2021-08-05 | Hypersonic wind tunnel rod type balance heat shield |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121811159.3U CN215726701U (en) | 2021-08-05 | 2021-08-05 | Hypersonic wind tunnel rod type balance heat shield |
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| Publication Number | Publication Date |
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| CN215726701U true CN215726701U (en) | 2022-02-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202121811159.3U Active CN215726701U (en) | 2021-08-05 | 2021-08-05 | Hypersonic wind tunnel rod type balance heat shield |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116907785A (en) * | 2023-09-12 | 2023-10-20 | 中国航空工业集团公司沈阳空气动力研究所 | Heat insulation device suitable for ultra-high-speed high-temperature tiny load force measurement test |
| CN116916636A (en) * | 2023-09-14 | 2023-10-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel balance temperature control device |
-
2021
- 2021-08-05 CN CN202121811159.3U patent/CN215726701U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116907785A (en) * | 2023-09-12 | 2023-10-20 | 中国航空工业集团公司沈阳空气动力研究所 | Heat insulation device suitable for ultra-high-speed high-temperature tiny load force measurement test |
| CN116907785B (en) * | 2023-09-12 | 2023-12-08 | 中国航空工业集团公司沈阳空气动力研究所 | Heat insulation device suitable for ultra-high-speed high-temperature tiny load force measurement test |
| CN116916636A (en) * | 2023-09-14 | 2023-10-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel balance temperature control device |
| CN116916636B (en) * | 2023-09-14 | 2023-11-17 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel balance temperature control device |
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