CN110884688B - Surface pressure measuring device of hypersonic vehicle and pressure guiding pipeline connecting method thereof - Google Patents
Surface pressure measuring device of hypersonic vehicle and pressure guiding pipeline connecting method thereof Download PDFInfo
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- CN110884688B CN110884688B CN201911279712.0A CN201911279712A CN110884688B CN 110884688 B CN110884688 B CN 110884688B CN 201911279712 A CN201911279712 A CN 201911279712A CN 110884688 B CN110884688 B CN 110884688B
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- 238000000034 method Methods 0.000 title claims abstract description 16
- 239000004809 Teflon Substances 0.000 claims abstract description 43
- 229920006362 Teflon® Polymers 0.000 claims abstract description 43
- 239000002184 metal Substances 0.000 claims abstract description 32
- 229910052751 metal Inorganic materials 0.000 claims abstract description 32
- 238000009530 blood pressure measurement Methods 0.000 claims abstract description 19
- 239000000853 adhesive Substances 0.000 claims description 8
- 230000001070 adhesive effect Effects 0.000 claims description 8
- 238000009434 installation Methods 0.000 claims description 7
- 238000007788 roughening Methods 0.000 claims description 7
- 239000011248 coating agent Substances 0.000 claims description 6
- 238000000576 coating method Methods 0.000 claims description 6
- 239000011521 glass Substances 0.000 claims description 6
- 239000004568 cement Substances 0.000 claims description 4
- 239000003292 glue Substances 0.000 claims description 4
- 244000137852 Petrea volubilis Species 0.000 claims description 3
- 239000003795 chemical substances by application Substances 0.000 claims description 3
- 229920002379 silicone rubber Polymers 0.000 claims description 3
- 238000002791 soaking Methods 0.000 claims description 2
- 229910000831 Steel Inorganic materials 0.000 claims 1
- 230000005611 electricity Effects 0.000 claims 1
- 239000010959 steel Substances 0.000 claims 1
- 238000007789 sealing Methods 0.000 abstract description 5
- 230000007704 transition Effects 0.000 abstract description 5
- 238000005259 measurement Methods 0.000 abstract description 3
- 239000010410 layer Substances 0.000 description 2
- 239000012790 adhesive layer Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L11/00—Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group G01L7/00 or G01L9/00
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L19/00—Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L19/00—Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges
- G01L19/14—Housings
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
The invention relates to the field of hypersonic aircraft flight measurement, and discloses a hypersonic aircraft surface pressure measurement device and a pressure guiding pipeline connection method thereof, wherein the hypersonic aircraft surface pressure measurement device comprises a plurality of pressure measuring holes arranged on the surface of an aircraft shell, and the shell is also provided with mounting holes coaxially communicated with the pressure measuring holes; a pressure measuring nozzle is arranged in the pressure measuring hole, the front end of the pressure measuring nozzle is communicated with the pressure measuring hole, and the rear end of the pressure measuring nozzle is provided with a metal pressure guiding pipe; the outer wall of the metal pressure guiding pipe is sleeved with a PVC hose, and the PVC hose is communicated with the electronic pressure scanning valve through a Teflon hose. The pressure guiding pipeline is firmly connected, and the joint has good heat resistance and sealing performance; the pressure measuring process utilizes a pressure measuring hole to introduce external air flow, the air flow flows through a pressure measuring nozzle, a metal pressure guiding pipe and a PVC hose, and the Teflon hose is connected with the PVC hose and an electronic pressure scanning valve to realize the connection transition of different pressure guiding hole calibers; and finally, introducing the air flow into an electronic pressure scanning valve by a Teflon hose to realize the pressure measurement of the surface measuring point of the aircraft along the trajectory.
Description
Technical Field
The invention relates to the field of hypersonic aircraft flight measurement, in particular to a hypersonic aircraft surface pressure measurement device and a pressure guide pipeline connection method thereof.
Background
The surface pressure of the aircraft is an important parameter of flight test measurement, and the surface load and the surface flow characteristics of the aircraft can be obtained through the pressure measurement of the flight surface, so that data support is provided for the research of the flow phenomenon of the aircraft. When the hypersonic aircraft flies in the atmosphere, the surface pressure of the aircraft varies with the flight altitude and the flight speed, the surface pressure variation range is larger, the maximum pressure can reach 0.5-0.6 MPa at low altitude and high speed, and the minimum pressure is only dozens of Pa at high altitude and low speed; meanwhile, the hypersonic aircraft generates a large amount of pneumatic heat due to the fact that the flying speed is high, the surface temperature of the aircraft reaches 500-600 ℃ at the highest, and how to realize heat prevention and sealing of pressure measurement is a key of the hypersonic aircraft surface pressure measurement.
Disclosure of Invention
Based on the problems, the invention provides the hypersonic vehicle surface pressure measuring device and the pressure guiding pipeline connecting method thereof, the pressure guiding pipeline is firmly connected, and the joint has good heat resistance and sealing performance; the pressure measuring process utilizes a pressure measuring hole to introduce external air flow, the air flow flows through a pressure measuring nozzle, a metal pressure guiding pipe and a PVC hose, and the Teflon hose is connected with the PVC hose and an electronic pressure scanning valve to realize the connection transition of different pressure guiding hole calibers; and finally, introducing the air flow into an electronic pressure scanning valve by a Teflon hose to realize the pressure measurement of the surface measuring point of the aircraft along the trajectory.
In order to solve the technical problems, the invention provides a surface pressure measuring device of a hypersonic aircraft, which comprises a plurality of pressure measuring holes arranged on the surface of an aircraft shell, wherein the shell is also provided with mounting holes which are coaxial and communicated with the pressure measuring holes, the mounting holes extend from the inner wall of the shell to the bottom of the pressure measuring holes, and the diameter of the mounting holes is larger than that of the pressure measuring holes; a pressure measuring nozzle is arranged in the pressure measuring hole, a tubular hollow cavity along the axial direction is arranged in the middle of the pressure measuring nozzle, the front end of the pressure measuring nozzle is communicated with the pressure measuring hole, and a metal pressure guiding pipe communicated with the tubular hollow cavity is arranged at the rear end of the pressure measuring nozzle; the outer wall of the metal pressure guiding pipe is sleeved with a PVC hose, and the end of the PVC hose far away from the metal pressure guiding pipe is communicated with the electronic pressure scanning valve through a Teflon hose; the outer diameter of the Teflon hose is smaller than or equal to that of the PVC hose.
Further, the pressure measurement hole is arranged along the thickness direction of the shell, the diameter of the pressure measurement hole is 1mm, and the depth is 2mm.
Further, the mounting hole is provided with an M4 threaded hole, the outer wall of the pressure measuring nozzle is of a cylindrical structure with M4 threads, and the pressure measuring nozzle is pressed in the mounting hole through the M4 threads.
Further, the length of the metal pressure guiding pipe is 15-25mm.
Further, the connection parts of the metal pressure guiding pipe and the PVC hose and the connection parts of the PVC hose and the Teflon hose are bonded by adopting an adhesive; the surface of the connection between the Teflon hose and the electronic pressure scanning valve is coated with a glass adhesive layer.
In order to solve the technical problems, the invention also provides a method for connecting the pressure guiding pipeline for measuring the surface pressure of the hypersonic vehicle, which comprises the following steps:
s1, installing a pressure measuring nozzle: installing the pressure tap on the aircraft shell from the inside of the aircraft shell at the position where the pressure tap and the installation hole are drilled in advance;
s2, connecting a PVC hose and a Teflon hose:
Firstly, before installation, roughening the surface of an inner hole with the length of 15mm of the connecting end of a PVC hose by using a drill bit with the diameter of 1.5mm, and then cutting an opening with a blade for the length of 10mm of the PVC hose from the end head;
secondly, roughening the outer circle surface of the connecting end of the thin tube with the length of 40mm by using fine sand paper;
thirdly, soaking the rough part of the lap joint of the PVC hose and the Teflon hose for 1-2 seconds by using 770 treating agent;
fourthly, inserting the Teflon hose into the PVC hose, and ensuring that the inserting length of the Teflon hose and the PVC hose is about 30mm;
Fifthly, injecting 403 instant adhesive at the opening of the PVC hose, sleeving a 10-15 mm heat shrinkage pipe at the joint after the adhesive is full, and using an electric hair drier to shrink the heat shrinkage pipe;
Sixthly, curing the manufactured PVC hose and a Teflon hose connecting pipeline for 12 hours at room temperature;
S3, connecting the pressure measuring nozzle with the PVC hose: the method comprises the steps of firstly inserting a PVC hose into a pressure measuring nozzle metal pressure guiding pipe by 2-3 mm by utilizing the elasticity of the PVC hose, then coating a circle of 502 glue with the thickness of 1-2mm on the pressure measuring nozzle metal pressure guiding pipe at the end of the PVC hose, and then inserting the PVC pipe into the pressure measuring nozzle metal pressure guiding pipe by 4-5 mm;
s4, connecting a Teflon hose and an electronic pressure scanning valve; and (3) manually inserting the Teflon hose into the pressure measuring holes of the electronic pressure scanning valve, coating a layer of glass cement with the thickness of 8-12 mm on the connecting surface after all the pressure measuring holes are installed, and curing for 12 hours in a room temperature environment.
Further, in the step S1, the outer wall of the pressure measuring nozzle is of a cylindrical structure with M4 threads, 703 silicon rubber is coated at the threads of the pressure measuring nozzle before the pressure measuring nozzle is installed, and a torque wrench of 1 N.m is used for tightening and fixing after the pressure measuring nozzle is screwed.
Compared with the prior art, the invention has the beneficial effects that: the pressure guiding pipeline is firmly connected, and the joint has good heat resistance and sealing performance; the pressure measuring process utilizes a pressure measuring hole to introduce external air flow, the air flow flows through a pressure measuring nozzle, a metal pressure guiding pipe and a PVC hose, and the Teflon hose is connected with the PVC hose and an electronic pressure scanning valve to realize the connection transition of different pressure guiding hole calibers; and finally, introducing the air flow into an electronic pressure scanning valve by a Teflon hose to realize the pressure measurement of the surface measuring point of the aircraft along the trajectory.
Drawings
FIG. 1 is a schematic view of an installation structure of a surface pressure measuring device of a hypersonic vehicle and a connection method of a pressure guiding pipeline in an embodiment;
FIG. 2 is an enlarged schematic view of portion A of FIG. 1;
1, a shell; 2. a pressure measuring hole; 3. a mounting hole; 4. a pressure measuring nozzle; 5. a metal pressure guiding pipe; 6. a PVC hose; 7. a Teflon hose; 8. an electronic pressure scanning valve.
Detailed Description
For the purpose of making apparent the objects, technical solutions and advantages of the present invention, the present invention will be further described in detail with reference to the following examples and the accompanying drawings, wherein the exemplary embodiments of the present invention and the descriptions thereof are for illustrating the present invention only and are not to be construed as limiting the present invention.
Examples:
Referring to fig. 1 and 2, a surface pressure measuring device of a hypersonic vehicle comprises a plurality of pressure measuring holes 2 arranged on the surface of a shell 1 of the hypersonic vehicle, wherein the shell 1 is also provided with mounting holes 3 which are coaxial and communicated with the pressure measuring holes 2, the mounting holes 3 extend from the inner wall of the shell 1 to the bottom of the pressure measuring holes 2, and the diameter of the mounting holes 3 is larger than that of the pressure measuring holes 2; a pressure measuring nozzle 4 is arranged in the pressure measuring hole 2, a tubular hollow cavity along the axial direction is arranged in the middle of the pressure measuring nozzle 4, the front end of the pressure measuring nozzle 4 is communicated with the pressure measuring hole 2, and a metal pressure guiding pipe 5 communicated with the tubular hollow cavity is arranged at the rear end of the pressure measuring nozzle 4; the outer wall of the metal pressure guiding pipe 5 is sleeved with a PVC hose 6, and the end of the PVC hose 6 far away from the metal pressure guiding pipe 5 is communicated with an electronic pressure scanning valve 8 through a Teflon hose 7; the outer diameter of the Teflon hose 7 is smaller than or equal to the outer diameter of the PVC hose 6.
In the embodiment, the number of the pressure measuring points on the surface of the aircraft is large, the pressure measuring points are densely distributed, the pressure measuring holes 2 with the diameter of 1mm are drilled at the measuring point position of the aircraft shell 1, the depth is 2mm, and the internal thread mounting holes 3 of M4 are processed in the shell 1; introducing air flow by adopting a pressure measuring nozzle 4 scheme, wherein the pressure measuring nozzle 4 is made of stainless steel, the pressure measuring nozzle 4 is arranged in an inner wall mounting hole 3 of the shell 1 through threads of M4, and a metal pressure guiding pipe 5 with the thickness of 15-25 mm is reserved behind the pressure measuring nozzle 4; the PVC hose 6 is connected with the metal pressure guiding pipe 5 at the rear end of the pressure measuring nozzle 4, the PVC hose 6 and the electronic pressure scanning valve 8 are connected with the Teflon hose 7, and the PVC hose 6 and the Teflon hose 7 are soft and elastic, so that the connection transition of the hole calibers of the pressure guiding pipes 5 of different metals can be realized, and the electronic pressure scanning valve 8 realizes the pressure measurement of the surface measuring point of the aircraft along the trajectory.
The method for connecting the surface pressure measurement pressure guide pipeline of the hypersonic vehicle in the embodiment comprises the following steps of:
S1, installing a pressure measuring nozzle 4: installing the nozzle 4 on the aircraft shell 1 from inside the aircraft shell 1 at positions where the pressure taps 2 and the installation holes 3 are drilled in advance; in the embodiment, 703 silicon rubber is coated on the thread of the pressure tap 4 before the pressure tap 4 is installed, and the pressure tap is screwed on and then screwed and fixed by a torque wrench of 1 N.m.
S2, connecting the PVC hose 6 with the Teflon hose 7:
Firstly, before installation, roughening the surface of an inner hole with the length of 15mm of the connecting end of a PVC hose 6 by using a drill bit with the diameter of 1.5mm, and then cutting an opening with the length of 10mm from the end head of the PVC hose 6 by using a blade;
secondly, roughening the outer circle surface of the connecting end of the thin tube with the length of 40mm by using fine sand paper;
thirdly, using 770 treating agent to soak the rough part of the lap joint of the PVC hose 6 and the Teflon hose 7 for 1-2 seconds;
Fourthly, inserting the Teflon hose 7 into the PVC hose 6, and ensuring that the inserting length of the Teflon hose and the PVC hose is about 30mm;
Fifthly, injecting 403 instant adhesive at the opening of the PVC hose 6, sleeving a 10-15 mm heat shrinkage pipe at the joint after the adhesive is full, and using an electric hair drier to shrink the heat shrinkage pipe;
sixthly, curing the connecting pipeline of the manufactured PVC hose 6 and the Teflon hose 7 for 12 hours in a room temperature environment (the room temperature environment in the implementation is 25+/-5 ℃);
S3, connecting the pressure measuring nozzle 4 with the PVC hose 6: firstly, inserting the PVC hose 6 into the metal pressure guiding pipe 5 of the pressure measuring nozzle 4 by 2-3 mm by utilizing the elasticity of the PVC hose 6, then coating a circle of 502 glue with the thickness of 1-2mm on the metal pressure guiding pipe 5 of the pressure measuring nozzle 4 at the end of the PVC hose 6, and then inserting the PVC pipe into the metal pressure guiding pipe 5 of the pressure measuring nozzle 4 by 4-5 mm;
S4, connecting a Teflon hose 7 and an electronic pressure scanning valve 8; the Teflon hose 7 is manually inserted into the pressure measuring holes 2 of the electronic pressure scanning valve 8, after all the pressure measuring holes 2 are installed, a layer of glass cement with the thickness of 8-12 mm is coated on the connecting surface, and the glass cement is cured for 12 hours at room temperature (25+/-5 ℃).
The pressure guiding pipelines connected through the steps are firmly connected, the pressure guiding pipelines with longer rear ends of the pressure measuring nozzles 4 play a role of heat sink to reduce the temperature, play a role of heat protection, and the sealing performance of the joints of the pressure guiding pipelines is good; in the pressure measurement process, external air flow is introduced by utilizing a pressure measurement hole 2, the air flow flows through a pressure measurement nozzle 4, a metal pressure guiding pipe 5 and a PVC hose 6, a Teflon hose 7 is connected with the PVC hose 6 and an electronic pressure scanning valve 8, and connection transition of different pressure guiding hole calibers is realized; the air flow is finally led into an electronic pressure scanning valve 8 by a Teflon hose 7, so that the pressure measurement of the surface measuring point of the aircraft along the trajectory is realized.
The above is an embodiment of the present invention. The foregoing embodiments and the specific parameters of the embodiments are only for clarity of description of the invention and are not intended to limit the scope of the invention, which is defined by the appended claims, and all equivalent structural changes made in the description and drawings of the invention are intended to be included in the scope of the invention.
Claims (4)
1. A hypersonic vehicle surface pressure measuring device comprises a plurality of devices arranged on the surface of a vehicle housing (1)
Pressure measurement hole (2), its characterized in that: the shell (1) is also provided with a mounting coaxial and communicated with the pressure measuring hole (2)
A hole (3), wherein the mounting hole (3) extends from the inner wall of the shell (1) to the bottom of the pressure measuring hole (2), and the diameter of the mounting hole (3)
Is larger than the diameter of the pressure measuring hole (2); a pressure measuring nozzle (4) is arranged in the pressure measuring hole (2), and the middle part of the pressure measuring nozzle (4) is provided with
Is provided with a tubular hollow cavity along the axial direction, the front end of the pressure measuring nozzle (4) is communicated with the pressure measuring hole (2), and the pressure is measured
The rear end of the pressure nozzle (4) is provided with a metal pressure guiding pipe (5) communicated with the tubular hollow cavity; the metal pressure guiding pipe (5)
The outer wall is sleeved with a PVC hose (6), and the end head of the PVC hose (6) far away from the metal pressure guiding pipe (5) is made of Teflon
The hose (7) is communicated with the electronic pressure scanning valve (8); the outer diameter of the Teflon hose (7) is smaller than or equal to that of a PVC hose
(6) Is a part of the outer diameter of the steel sheet;
The pressure measuring holes (2) are arranged along the thickness direction of the shell (1), the diameter of each pressure measuring hole (2) is 1mm, and the depth is the same as that of the shell
Is 2mm;
the length of the metal pressure guiding pipe (5) is 15-25mm;
the joint of the metal pressure guiding pipe (5) and the PVC hose (6), and the joint of the PVC hose (6) and the Teflon hose (7)
The joints are bonded by adopting an adhesive; the surface coating of the connection of the Teflon hose (7) and the electronic pressure scanning valve (8)
And a glass glue layer is covered.
2. The hypersonic vehicle surface pressure measurement device as set forth in claim 1, wherein: the said
The mounting hole (3) is provided with an M4 threaded hole, the outer wall of the pressure measuring nozzle (4) is of a cylindrical structure with M4 threads, and the pressure measuring nozzle is provided with a cylindrical structure with M4 threads
The pressure measuring nozzle (4) is installed in the installation hole (3) through M4 threads.
3. A method for connecting pressure guiding pipelines for measuring surface pressure of hypersonic vehicle is used for assembling the right
The hypersonic vehicle surface pressure measuring device as set forth in claim 2, including the steps of:
S1, installing a pressure measuring nozzle (4): from the aircraft shell (1) at a position where the pressure taps (2) and the mounting holes (3) have been drilled beforehand
The inner part is provided with a pressure measuring nozzle (4) on the aircraft shell (1);
s2, connecting the PVC hose (6) and the Teflon hose (7):
First, before installation, a drill bit with the diameter of 1.5mm is used for connecting the connecting end of the PVC hose (6) for 15mm in length
Roughening the surface of the inner hole, and cutting the PVC hose (6) with a blade to a length of 10mm from the end
An opening;
secondly, roughening the outer circle surface of the connecting end of the thin tube with the length of 40mm by using fine sand paper;
Third, the 770 treating agent is used for roughening the joint of the PVC hose (6) and the Teflon hose (7)
Soaking for 1-2 seconds;
Fourthly, inserting a Teflon hose (7) into the PVC hose (6) to ensure that the inserting length of the Teflon hose and the PVC hose is about 30mm;
Fifthly, injecting 403 instant adhesive at the opening of the PVC hose (6), sleeving the joint after the adhesive is filled
A 10-15 mm heat shrinkage tube is contracted by an electric hair drier;
Sixthly, connecting the manufactured PVC hose (6) and the Teflon hose (7) with a pipeline at room temperature
Curing for 12 hours;
S3, connecting the pressure measuring nozzle (4) with the PVC hose (6): PVC is firstly put into PVC by utilizing the elasticity of the PVC hose (6)
The hose (6) is inserted into the metal pressure guiding pipe (5) of the pressure measuring nozzle (4) for 2-3 mm, and then the end of the PVC hose (6) is measured
A circle of 502 glue with the thickness of 1-2mm is coated on the metal pressure guiding pipe (5) of the pressure nozzle (4), and then the PVC pipe is inserted
The pressure measuring nozzle (4) is arranged in the metal pressure guiding pipe (5) for 4-5 mm;
s4, connecting a Teflon hose (7) and an electronic pressure scanning valve (8); manually inserting a Teflon hose (7) into the electricity
The sub-pressure scanning valve (8) is used for measuring pressure holes (2), and after all the pressure holes (2) are installed, a layer of coating is coated on the connecting surface
And 8-12 mm glass cement, and curing for 12 hours in a room temperature environment.
4. The method for connecting a pressure-introducing pipeline for measuring the surface pressure of a hypersonic vehicle according to claim 3, which is characterized in that
The method is characterized in that: in the step S1, the outer wall of the pressure measuring nozzle (4) is of a cylindrical structure with M4 threads, and the pressure measuring nozzle (4) is arranged before
Coating 703 silicon rubber on the thread of the pressure measuring nozzle (4), screwing, and then screwing and fixing by using a torque wrench of 1 N.m.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911279712.0A CN110884688B (en) | 2019-12-13 | 2019-12-13 | Surface pressure measuring device of hypersonic vehicle and pressure guiding pipeline connecting method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911279712.0A CN110884688B (en) | 2019-12-13 | 2019-12-13 | Surface pressure measuring device of hypersonic vehicle and pressure guiding pipeline connecting method thereof |
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| Publication Number | Publication Date |
|---|---|
| CN110884688A CN110884688A (en) | 2020-03-17 |
| CN110884688B true CN110884688B (en) | 2024-06-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911279712.0A Active CN110884688B (en) | 2019-12-13 | 2019-12-13 | Surface pressure measuring device of hypersonic vehicle and pressure guiding pipeline connecting method thereof |
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| CN (1) | CN110884688B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112340062B (en) * | 2020-12-28 | 2021-04-06 | 南京理工大学 | Rotor wing pressure measurement system based on air slip ring |
| CN114738543B (en) * | 2022-03-02 | 2023-11-14 | 武汉弘瑞通电子科技有限公司 | Pressure control system of electronic pressure scanning valve |
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| CN110884688A (en) | 2020-03-17 |
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