CN212275091U - Coaxial thermocouple installation device for measuring heat flow in flight test - Google Patents
Coaxial thermocouple installation device for measuring heat flow in flight test Download PDFInfo
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- CN212275091U CN212275091U CN202022010581.0U CN202022010581U CN212275091U CN 212275091 U CN212275091 U CN 212275091U CN 202022010581 U CN202022010581 U CN 202022010581U CN 212275091 U CN212275091 U CN 212275091U
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Abstract
The utility model discloses a coaxial thermocouple installation device for measuring the heat flow of a flight test, which particularly comprises an insulating sealing hoop and a fastener, wherein the insulating sealing hoop and the fastener are fixedly installed with a coaxial thermocouple through a clamping installation mode; the insulating sealing hoop is provided with a through hole a penetrating through the central axis, the front end of the insulating sealing hoop is a cylinder a, and the rear end of the insulating sealing hoop is of a trapezoidal structure; the fastener runs through the axis and is provided with a through-hole b, and the top of fastener sets up to hexagonal structure, and the middle part of fastener sets up to barrel b, and the outer wall of barrel b is provided with the screw thread, and the bottom of fastener sets up to the inclined wall that inclines. The sealing performance between the installed coaxial thermocouple and the aircraft is good, and the end face of the coaxial thermocouple is flush with the outer surface of the aircraft, so that the heat flow distribution on the surface of the aircraft can be accurately measured; the thermocouple mounting structure has high stability; the coaxial thermocouple has higher insulativity with the aircraft body, and avoids signal interference.
Description
Technical Field
The utility model belongs to the technical field of hypersonic flight equipment, concretely relates to be used for flight test thermal current measuring coaxial thermocouple installation device.
Background
In the hypersonic flight, the aircraft surface is subjected to pneumatic heating load to cause ablation of the aircraft body material, and the heat-proof problem is very prominent. The accurate prediction of the pneumatic thermal environment can effectively reduce the allowance of the heat-proof material, increase the effective load and improve the structural efficiency of the aircraft. At present, the ground wind tunnel test is a main means for predicting the aerodynamic thermal environment, but the result of the test has different degrees of deviation from the real flight state. The actual environment load data acquired by the hypersonic flight test is more accurate and reliable, the times of carrying out the flight test in China in recent years are more and more, and the surface heat flow test is carried out by mounting a sensor on the surface of the aircraft, so that precious flight test data is acquired.
The quick response coaxial thermocouple is a heat flow sensor developed based on the surface temperature measurement heat conduction theory, and obtains heat flow through measuring the temperature change course and back calculation. The device has small size, quick response and strong anti-scouring capability, is particularly suitable for high-precision object surface temperature and heat flow measurement in severe environments, is widely applied to shock tunnel pneumatic heat measurement, explosion heat flow measurement and engine test platform transient temperature measurement, and is also used for flight test temperature and heat flow measurement. The end sensitive device of the quick response coaxial thermocouple object is a cylinder with the diameter of 2mm, the length of the cylinder is 15mm, the diameter of the tail end of the cylinder is 3.6mm, and the length of the cylinder is 11 mm.
In flight tests, the installation requirement on the coaxial thermocouple is high. Firstly, sealing between the installed coaxial thermocouple and the aircraft, and enabling the end face of the coaxial thermocouple to be flush with the outer surface of the aircraft, so that the heat flow distribution on the surface of the aircraft can be accurately measured; secondly, the aircraft vibrates greatly in a flight test, meanwhile, the temperature of the model body is increased due to pneumatic heating, and the thermal effect and the vibration effect are coupled with each other to ensure that the thermocouple mounting structure cannot lose efficacy; finally, in the flight test, signal interference is brought to thermocouple measurement due to the fact that all control units and acquisition units are in no reference ground, and the installed coaxial thermocouples are required to be insulated from an aircraft body. However, in the prior art, the installation requirement of the flight test on the coaxial thermocouple is not provided at present, and therefore, no one provides a corresponding installation method of the coaxial thermocouple aiming at the installation requirement of the flight test on the coaxial thermocouple. Therefore, how to develop a coaxial thermocouple installation method for measuring the heat flow in the flight test has important practical significance.
SUMMERY OF THE UTILITY MODEL
To the problem that exists among the prior art, the utility model aims to provide a coaxial thermocouple installation device for flight test thermal current is measured.
The utility model discloses the technical scheme who takes does:
a coaxial thermocouple installation device for measuring heat flow in a flight test specifically comprises an insulating sealing hoop and a fastener, wherein the insulating sealing hoop and the fastener are fixedly installed with a coaxial thermocouple in a clamping installation mode;
the insulating sealing hoop is provided with a through hole a penetrating through the central axis, the front end of the insulating sealing hoop is a cylinder a, and the rear end of the insulating sealing hoop is of a trapezoidal structure;
the fastener runs through the axis and is provided with a through hole b, the top of fastener sets up to hexagonal structure, and the middle part of fastener sets up to barrel b, and the outer wall of barrel b is provided with the screw thread, and the bottom of fastener sets up to the slope skew wall.
Furthermore, the upper inclined plane of the trapezoidal structure of the insulating sealing hoop is mutually clamped with the wall surface of the aircraft; the lower inclined plane of the trapezoidal structure of the insulating sealing hoop is clamped with the inclined wall of the fastener.
Furthermore, the included angle of the upper inclined plane of the trapezoidal structure of the insulating sealing hoop is set to be 90 degrees; the included angle of the lower inclined surface of the trapezoidal structure is set to be 60 degrees.
Further, the inclined wall included angle of the fastener is set to be 60 degrees.
Further, the inner diameters of the through hole a of the insulating sealing hoop and the through hole b of the fastener are close, and the through hole a and the through hole b are matched with the outer diameter of the cylindrical part at the front end of the coaxial thermocouple.
Further, the insulating sealing hoop and the fastener are made of high-temperature-resistant organic synthetic materials, particularly any one of PEEK, PBI or PI materials, and the temperature resistance of the insulating sealing hoop and the fastener is about 350 ℃.
A coaxial thermocouple installation method for flight test heat flow measurement adopts the coaxial thermocouple installation device for flight test heat flow measurement, and specifically comprises the following steps:
(1) firstly, processing a mounting hole on the wall surface of an aircraft according to the size requirement, and sequentially sleeving a fastener and an insulating sealing hoop into the cylindrical part of the coaxial thermocouple;
(2) then placing the insulating sealing hoop and the coaxial thermocouple in a mounting hole on the wall surface of the aircraft, and screwing a fastener by adopting a torque wrench;
(3) the front end of the insulating sealing hoop is extruded by the tightening of the fastener to expose the surface of the aircraft, and the part of the insulating sealing hoop exceeding the surface of the aircraft is cut off after the fastener is fully tightened.
Further, in the step (1), high-temperature curing glue is coated between the wall surface of the aircraft and the fastener, and the connection strength is enhanced through the high-temperature curing glue.
Further, in the step (2), the position of the coaxial thermocouple is adjusted during the tightening process of the fastener, and the surface of the coaxial thermocouple is controlled to be flush with the outer wall surface of the aircraft.
The utility model has the advantages that:
the insulating sealing hoop is used for fixing the coaxial thermocouple, plays a role in sealing, and prevents external airflow from entering the interior of the aircraft due to looseness of the sensor in the flying process; the fastener is used for pressing the insulating sealing hoop, so that the insulating sealing hoop generates small deformation to play a sealing role. In order to increase the friction force between the installed insulating sealing hoop and the coaxial thermocouple, a trapezoidal structure is arranged on the insulating sealing hoop to increase the transverse pressure so as to increase the friction force and play a role in fixing.
Firstly, the sealing performance between the installed coaxial thermocouple and the aircraft is good, and the end face of the coaxial thermocouple is flush with the outer surface of the aircraft, so that the heat flow distribution on the surface of the aircraft can be accurately measured;
secondly, the thermocouple mounting structure is high in stability, can bear the vibration of an aircraft in a flight test, can adapt to the phenomenon that the temperature of a model body is increased due to pneumatic heating, and cannot be invalid due to mutual coupling of a thermal effect and a vibration effect;
finally, the insulation between the coaxial thermocouple and the aircraft body after the installation is high, and signal interference caused by measurement of all control units and acquisition units on the thermocouple in a flight test is avoided.
Drawings
Fig. 1 is a schematic view of the overall structure of the fixing method of the coaxial thermocouple of the present invention.
Fig. 2 is a schematic structural view of the middle insulating sealing band of the present invention.
Fig. 3 is a schematic structural view of the fastener of the present invention.
Fig. 4 is a schematic view of the overall structure of the back of the test piece of the coaxial thermocouple installed in the present invention.
Fig. 5 is a schematic view of the overall structure of the test piece of the coaxial thermocouple installed in the present invention.
Wherein, 1, aircraft wall surface; 2. an insulating seal collar; 3. a fastener; 4. a coaxial thermocouple; 5. a through hole a; 6. a cylinder body a; 7. a lower inclined plane; 8. an upper inclined plane; 9. a through hole b; 10. a hexagonal structure; 11. a cylinder b; 12. the inclined wall is inclined.
Detailed Description
The present invention will be further described with reference to the accompanying drawings.
Example 1
As shown in fig. 1, 2 and 3, a coaxial thermocouple installation device for measuring heat flow in a flight test specifically comprises an insulating sealing hoop 2 and a fastener 3, wherein the insulating sealing hoop 2 and the fastener 3 are fixedly installed with a coaxial thermocouple 4 in a clamping installation manner;
as shown in fig. 2, the insulating sealing band 2 is provided with a through hole a5 penetrating through the central axis, and the inner diameter of the through hole a5 is 2.0 mm; the front end of the insulating and sealing hoop 2 is arranged as a cylinder a6, more specifically: the outer diameter of the 1.7mm part of the front end of the edge sealing hoop is set to be 2.4mm, and the edge sealing hoop is used for insulating the coaxial thermocouple 4 from the aircraft; the rear end of the insulating sealing hoop 2 is arranged to be of a trapezoidal structure, and more specifically: the rear end 2mm of the insulating sealing hoop 2 is arranged into a trapezoidal structure;
the upper inclined plane 8 of the trapezoidal structure of the insulating sealing hoop 2 is clamped with the wall surface 1 of the aircraft; the lower inclined surface 7 of the trapezoid structure of the insulating sealing hoop 2 is clamped with the inclined wall 12 of the fastener 3.
The included angle of an upper inclined plane 8 of the trapezoid structure of the insulating sealing hoop 2 is set to be 90 degrees, and the upper inclined plane 8 plays a sealing role; the included angle of the lower inclined plane 7 of the trapezoid structure is set to be 60 degrees, and the lower inclined plane 7 increases friction force so as to achieve the fastening effect.
As shown in fig. 3, the fastener 3 is provided with a through hole b9 through the central axis, the inner diameter of the through hole b9 is set to 2.06mm, the top end of the fastener 3 is set to be a hexagonal structure 10, which is convenient for screwing with a torque wrench, the middle part of the fastener 3 is set to be a cylinder b11, the outer wall of the cylinder b11 is provided with threads, and more specifically: the middle of the fastener 3 is provided with M5 x 0.5 threads, the length is 4mm, the bottom end of the fastener 3 is provided with an inclined wall 12, the inclined wall 12 of the fastener 3 forms an included angle of 60 degrees, and the fastener is matched with the insulating sealing hoop 2 to achieve the fastening effect.
The inner diameters of the through hole a5 of the insulating sealing hoop 2 and the through hole b9 of the fastener 3 are close to each other, and are mutually matched with the outer diameter of the cylindrical part at the front end of the coaxial thermocouple 4.
The insulating sealing hoop 2 and the fastener 3 are both made of high-temperature-resistant organic synthetic materials, more specifically, any one of PEEK, PBI or PI materials, and the temperature resistance of the insulating sealing hoop and the fastener is about 350 ℃, so that the requirements of the insulating property and the thermal vibration between the coaxial thermocouple 4 and an aircraft on the structure are met.
By adopting the method, the length of the coaxial thermocouple 4 can be conveniently adjusted, so that the end of the coaxial thermocouple 4 is flush with the wall surface 1 of the aircraft, and the installation and the disassembly are more convenient; in the flight test, because the common ground is not available, the flight control equipment can cause noise interference to the flight heat flow measuring sensor through the wall surface 1 of the aircraft, and the installation mode can play a good insulating role;
the fastening problem between coaxial thermocouple 4 and insulating seal hoop 2 has been overcome to this application, through adjusting different trapezoidal angles, has optimized mounting structure's resistance to compression and tensile strength problem, secondly has carried out the hot examination of structure strictly, exerts the variable load heat flow through the flight trajectory, examines the heat-resisting and the shock resistance of structure.
Example 2
On the basis of the embodiment 1, different from the embodiment 1, as shown in fig. 1, a method for installing a coaxial thermocouple for measuring the heat flow in a flight test adopts the installation device for the coaxial thermocouple 4 for measuring the heat flow in the flight test, and specifically comprises the following steps:
(1) firstly, processing a mounting hole on the wall surface 1 of the aircraft according to the size requirement, and sequentially sleeving a fastener 3 and an insulating sealing hoop 2 in a 42mm cylindrical part of a coaxial thermocouple;
(2) then placing the insulating sealing hoop 2 and the coaxial thermocouple 4 in an installation hole of the wall surface 1 of the aircraft, adopting a torque wrench to screw the fastener 3, adjusting the position of the coaxial thermocouple 4 in the screwing process of the fastener 3, and controlling the surface of the coaxial thermocouple to be flush with the outer wall surface of the aircraft;
(3) the front end of the insulating sealing hoop 2 is extruded by screwing the fastener 3 to expose the surface of the aircraft, and the insulating sealing hoop 2 is partially cut off (the thickness of the insulating sealing hoop is only 0.2mm, so that the insulating sealing hoop is convenient to cut off) beyond the surface of the aircraft after the fastener 3 is completely screwed.
The part structure of this application is different from the metal cutting ferrule part on the market, and it adopts the trapezoidal structure design of two special parts of insulating sealed hoop 2 and fastener 3, through the two cooperations, and the main objective is used for increasing the radial pressure between insulating sealed hoop and the coaxial thermocouple to increase frictional force between the two, play fixed and sealed effect simultaneously.
The insulating sealing fastening installation requirement of the coaxial thermocouple 4 in the flight test is met through the operation, and in order to further ensure the stability of the installation result, high-temperature curing glue can be coated between the inner wall surface of the aircraft and the fastening piece 3, and the connection strength is enhanced through the high-temperature curing glue.
The utility model has the advantages that adopt the joint mounting means, can guarantee the sensor with the insulation between the model with sealed, can conveniently adjust the sensor again with the model mounted position, guarantee that the sensor terminal surface flushes with the model surface. The material object diagram of the coaxial thermocouple 4 installed on the test piece by adopting the utility model is shown in fig. 4 and 5.
The utility model discloses a coaxial thermocouple 4 installation device and mounting method for flight test measurement has obtained successful application in transition flight test, has obtained the reliable data that surpasss 130 measurement stations, has played important supporting role to promoting the model development.
The above description is not a limitation of the present invention, and it should be noted that: it will be apparent to those skilled in the art that various changes, modifications, additions and substitutions can be made without departing from the scope of the invention as defined in the accompanying claims.
Claims (8)
1. A coaxial thermocouple installation device for measuring heat flow in a flight test is characterized by specifically comprising an insulating sealing hoop and a fastener, wherein the insulating sealing hoop and the fastener are fixedly installed with a coaxial thermocouple in a clamping installation mode;
the insulating sealing hoop is provided with a through hole a penetrating through the central axis, the front end of the insulating sealing hoop is a cylinder a, and the rear end of the insulating sealing hoop is of a trapezoidal structure;
the fastener runs through the axis and is provided with a through hole b, the top of fastener sets up to hexagonal structure, and the middle part of fastener sets up to barrel b, and the outer wall of barrel b is provided with the screw thread, and the bottom of fastener sets up to the slope skew wall.
2. The coaxial thermocouple installation device for the flight test heat flow measurement according to claim 1, wherein the upper inclined surface of the trapezoidal structure of the insulating sealing hoop is clamped with the wall surface of the aircraft; the lower inclined plane of the trapezoidal structure of the insulating sealing hoop is clamped with the inclined wall of the fastener.
3. The coaxial thermocouple mounting device for the flight test heat flow measurement according to claim 1 or 2, wherein the included angle of the inclined plane on the trapezoidal structure of the insulating sealing hoop is set to be 90 °; the included angle of the lower inclined surface of the trapezoidal structure is set to be 60 degrees.
4. The apparatus of claim 1 or 2, wherein the inclined wall angle of the fastener is set to 60 °.
5. The coaxial thermocouple installation device for flight test heat flow measurement according to claim 1, wherein the through hole a of the insulating sealing hoop and the through hole b of the fastener have inner diameters close to each other and are matched with the outer diameter of the cylindrical part of the front end of the coaxial thermocouple.
6. The apparatus of claim 1, wherein the insulating sealing band and the fastening member are made of a high temperature resistant organic synthetic material, more specifically any one of PEEK, PBI or PI material, and the temperature resistance is about 350 ℃.
7. The coaxial thermocouple installation device for the flight test heat flow measurement according to claim 1, wherein the fastening member and the aircraft wall surface are clamped with each other, and a high temperature curing adhesive is coated between the fastening member and the aircraft wall surface, so that the connection strength is enhanced through the high temperature curing adhesive.
8. The apparatus of claim 1, wherein the fastener adjusts the position of the thermocouple during tightening to control the surface of the thermocouple to be flush with the outer wall of the aircraft.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202022010581.0U CN212275091U (en) | 2020-09-15 | 2020-09-15 | Coaxial thermocouple installation device for measuring heat flow in flight test |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111982321A (en) * | 2020-09-15 | 2020-11-24 | 中国科学院力学研究所 | Coaxial thermocouple installation device and installation method for measuring heat flow in flight test |
| CN116380402A (en) * | 2023-05-26 | 2023-07-04 | 中国空气动力研究与发展中心超高速空气动力研究所 | Transient radiation heat flow sensor for high enthalpy expansion wind tunnel and mounting and manufacturing method |
-
2020
- 2020-09-15 CN CN202022010581.0U patent/CN212275091U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111982321A (en) * | 2020-09-15 | 2020-11-24 | 中国科学院力学研究所 | Coaxial thermocouple installation device and installation method for measuring heat flow in flight test |
| CN116380402A (en) * | 2023-05-26 | 2023-07-04 | 中国空气动力研究与发展中心超高速空气动力研究所 | Transient radiation heat flow sensor for high enthalpy expansion wind tunnel and mounting and manufacturing method |
| CN116380402B (en) * | 2023-05-26 | 2023-08-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Method for installing and manufacturing transient radiation heat flow sensor for high enthalpy expansion wind tunnel |
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