CN112758348A - Pressure distribution measuring device for flight test and pressure measuring belt modification method - Google Patents
Pressure distribution measuring device for flight test and pressure measuring belt modification method Download PDFInfo
- Publication number
- CN112758348A CN112758348A CN202011555584.0A CN202011555584A CN112758348A CN 112758348 A CN112758348 A CN 112758348A CN 202011555584 A CN202011555584 A CN 202011555584A CN 112758348 A CN112758348 A CN 112758348A
- Authority
- CN
- China
- Prior art keywords
- aluminum foil
- pressure measuring
- pressure
- fairing
- adhesive tape
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The invention provides a pressure distribution measuring device for a flight test and a pressure measuring belt modification method, and particularly provides a modification method on an MEMS pressure measuring belt flight test machine using conventional materials such as double faced adhesive tape and aluminum foil.
Description
Technical Field
The invention belongs to the field of flight tests, and relates to a modification method for a MEMS pressure measuring belt flight test machine.
Background
The pressure distribution measurement of the existing flight test is carried out by a test piece punching method, the measurement method can damage the wing structure, and the cost is high. MEMS (micro electro mechanical system based) pressure measuring belt is a novel intelligent flexible pressure measuring belt and can be used for air pressure measurement.
Disclosure of Invention
The purpose of the invention is as follows: the improved technological method and the improved measuring device for the MEMS pressure measuring belt machine are provided, the pressure distribution of a flight test is measured under the condition that wings are not damaged, and the cost is reduced.
The technical scheme of the invention is as follows: in one aspect, a pressure distribution measuring device for a flight test is provided, the measuring device comprising a pressure measuring belt, an aluminum foil and a fairing;
the aluminum foil is bonded with the airplane wing, and the pressure measuring belt is bonded with the aluminum foil; the fairing is of a trapezoidal structure with an opening on the bottom surface, and is matched with the airplane wings to cover the aluminum foil and the pressure measuring belt; the edge of the fairing is fixedly connected with the aircraft wing.
Furthermore, the upper surface and the lower surface of the pressure measuring belt are respectively bonded with the aluminum foil and the inner surface of the fairing through double-sided adhesive tapes.
Furthermore, the outer surface of the fairing is covered with an aluminum foil for fixedly connecting the edge of the fairing with the aircraft wing; and the surface of the aluminum foil is attached with an adhesive.
Furthermore, a pressure sensor is arranged on the pressure measuring belt, an opening is formed in the fairing, and the pressure sensor and the opening are correspondingly arranged.
Further, the fairing is a flexible material. Can be used in the bending of the leading edge of the airplane wing.
In another aspect, there is provided a method of retrofitting a MEMS pressure strip flight tester, using a measurement device as described above, the method comprising:
step 1: determining a section to be measured on the airplane wing and cleaning a corresponding area on the surface of the wing; then pasting an aluminum foil on the surface of the cleaning area to enable the aluminum foil to be attached to the surface of the wing;
step 2: determining pressure measuring points on the wings of the airplane, and positioning and marking the pressure measuring points; the pressure measuring point is positioned in the aluminum foil covering area;
and step 3: cleaning the surface of the aluminum foil, and then paving a double-sided adhesive tape on the surface of the aluminum foil;
and 4, step 4: the pressure measuring belt is bonded with the aluminum foil through double-sided adhesive tape; the pressure testing unit on the pressure measuring belt is superposed with the pressure measuring point;
and 5: after the pressure measuring belt is pasted, the pressure measuring belt and the test cable are connected; the test cable is bonded with the aluminum foil through double-sided adhesive tape;
step 6: bonding a double-sided adhesive tape at the periphery of the pressure measuring band, and then covering the whole pressure measuring band by using a fairing;
and 7: the cowling and test cable were encapsulated using aluminum foil.
Furthermore, the coverage area of the double-sided adhesive tape on the upper surface of the aluminum foil is larger than the area of the pressure measuring belt, so that the double-sided adhesive tape on the upper surface of the aluminum foil is bonded with the edge of the fairing.
Furthermore, the inner surface of the fairing is provided with a concave hole matched with the upper component of the pressure measuring belt, so that the inner surface of the fairing is attached to the upper surface of the pressure measuring belt conveniently.
The invention has the technical effects that:
the method provides a convenient and effective method for refitting the MEMS pressure measuring tape machine through common materials such as double-sided adhesive tape, aluminum foil and the like.
The modification method of the MEMS pressure measuring belt flight testing machine uses conventional materials such as aluminum foil, double faced adhesive tape and the like to modify the MEMS pressure measuring belt and related test cables on the test wing surface for measuring the pressure distribution of the flight test. The wind tunnel and flight test verify that the refitting method is safe and reliable and can meet the test requirements of the flight test.
The invention can be used for the modification of a film or sheet structure flight testing machine with smaller mass similar to an MEMS pressure measuring belt.
Drawings
FIG. 1 is a schematic view of a modified section of a pressure band.
Detailed Description
Example 1
Fig. 1 is a schematic view of a modified section of a pressure measuring strip, and as shown in fig. 1, a pressure distribution measuring device for a flight test is provided, wherein the measuring device comprises a pressure measuring strip 2, an aluminum foil 3 and a fairing 4; the aluminum foil is bonded with the airplane wing 1, and the pressure measuring belt is bonded with the aluminum foil; the fairing is of a trapezoidal structure with an opening on the bottom surface, and is matched with the airplane wings to cover the aluminum foil and the pressure measuring belt; the edge of the fairing is fixedly connected with the aircraft wing.
Specifically, the upper and lower surfaces of the pressure measuring tape are bonded to the aluminum foil and the inner surface of the cowling respectively through the double-sided adhesive tape 5. The outer surface of the fairing is covered with an aluminum foil for fixedly connecting the edge of the fairing with the aircraft wing; and the surface of the aluminum foil is attached with an adhesive. And a pressure sensor is arranged on the pressure measuring belt, an opening is formed in the fairing, and the pressure sensor and the opening are correspondingly arranged.
In this embodiment, the fairing is a flexible material. Can be used in the bending of the leading edge of the airplane wing.
The invention can meet the requirement of the flight test of the MEMS pressure measuring belt and the disassembled pressure measuring belt can be reused.
Example 2
The embodiment provides a method for modifying an MEMS pressure measuring belt flight testing machine, which comprises the following specific steps:
step 1: determining the position of a pressure measuring point on the machine and cleaning the surface of the structure by using absolute ethyl alcohol, wherein the cleaning width of two sides of the pressure measuring point is not less than 100mm, after the absolute ethyl alcohol is volatilized, adhering an aluminum foil adhesive tape on the surface of a cleaning area, and using a scraper to ensure that the surface of an aluminum foil is smooth and is fully contacted with the structure;
step 2: positioning and marking the pressure measuring point, positioning and marking the outer contour of the pressure measuring belt after ensuring that a pressure testing unit on the pressure measuring belt is superposed with the pressure measuring point, and placing the fairing at the installation position to mark the outer contour of the fairing;
and step 3: cleaning the surface of the aluminum foil by using absolute ethyl alcohol, reserving a positioning mark during cleaning, paving a double-sided adhesive tape on the surface of the aluminum foil after the absolute ethyl alcohol is volatilized, keeping the surface of the double-sided adhesive tape flat and bubble-free and fully adhering to the bottom aluminum foil, and ensuring that the boundary of the double-sided adhesive tape is 20mm larger than the positioning mark of the contour of the fairing in the step 2;
and 4, step 4: and lightly placing the MEMS pressure measuring belt on the double faced adhesive tape according to the position of the pressure measuring point, and lightly pressing the pressure measuring belt to ensure that the bottom surface of the pressure measuring belt is fully contacted with the double faced adhesive tape after the position is confirmed to be correct.
And 5: after the pressure measuring tape is adhered, the pressure measuring tape and the test cable are connected, and the test cable is adhered to the surface of the structure by the same method as the pressure measuring tape is adhered.
Step 6: laying a layer of double faced adhesive tape on the periphery of the pressure measuring tape component, mounting the fairing on the pressure measuring tape after laying, and gradually pressing the fairing from inside to outside to ensure that the fairing is completely bonded with the pressure measuring tape and the bottom layer aluminum foil;
and 7: and the pressure measuring belt, the fairing and the test cable are packaged by using the aluminum foil, so that the pressure measuring sensor is completely exposed and is in smooth transition with a surrounding area during packaging, and meanwhile, the packaging surface is kept smooth and neat without bubbles.
This embodiment, aluminium foil, double faced adhesive tape that the repacking was used will have and to guarantee that pressure measuring belt, radome fairing and structure can fully contact and can not drop and be indestructible bonding strength when guaranteeing the surperficial atress simultaneously.
In the embodiment, the test flight is completed within 2 months after the modification is completed, so that the modification surface damage or peeling caused by overlong test flight period is avoided. After each flight, the inspection is needed, and if the surface is damaged or peeled off, the maintenance is needed immediately.
Claims (8)
1. A pressure distribution measuring device for a flight test is characterized by comprising a measuring belt, an aluminum foil and a fairing;
the aluminum foil is bonded with the airplane wing, and the pressure measuring belt is bonded with the aluminum foil; the fairing is of a trapezoidal structure with an opening on the bottom surface, and is matched with the airplane wings to cover the aluminum foil and the pressure measuring belt; the edge of the fairing is fixedly connected with the aircraft wing.
2. The measuring device of claim 1, wherein the upper and lower surfaces of the pressure measuring tape are bonded to the aluminum foil and the inner surface of the cowling, respectively, by double-sided adhesive tape.
3. A measuring device according to claim 2, wherein the outer surface of the fairing is covered with aluminium foil for fixedly attaching the edge of the fairing to the aircraft wing; and the surface of the aluminum foil is attached with an adhesive.
4. A measuring device as claimed in claim 2, characterized in that a pressure sensor is arranged on the pressure measuring belt, and an opening is arranged in the fairing, said pressure sensor being arranged in correspondence with said opening.
5. A measuring device according to claim 2, wherein the fairing is of a flexible material. Can be used in the bending of the leading edge of the airplane wing.
6. A method of retrofitting a MEMS pressure tap flight tester using the measurement device of any of claims 1 to 5, the method comprising:
step 1: determining a section to be measured on the airplane wing and cleaning a corresponding area on the surface of the wing; then pasting an aluminum foil on the surface of the cleaning area to enable the aluminum foil to be attached to the surface of the wing;
step 2: determining pressure measuring points on the wings of the airplane, and positioning and marking the pressure measuring points; the pressure measuring point is positioned in the aluminum foil covering area;
and step 3: cleaning the surface of the aluminum foil, and then paving a double-sided adhesive tape on the surface of the aluminum foil;
and 4, step 4: the pressure measuring belt is bonded with the aluminum foil through double-sided adhesive tape; the pressure testing unit on the pressure measuring belt is superposed with the pressure measuring point;
and 5: after the pressure measuring belt is pasted, the pressure measuring belt and the test cable are connected; the test cable is bonded with the aluminum foil through double-sided adhesive tape;
step 6: bonding a double-sided adhesive tape at the periphery of the pressure measuring band, and then covering the whole pressure measuring band by using a fairing;
and 7: the cowling and test cable were encapsulated using aluminum foil.
7. The retrofitting method of claim 6, wherein the double-sided adhesive tape on the top surface of the aluminum foil covers an area greater than the area of said pressure measuring tape for adhering the double-sided adhesive tape on the top surface of the aluminum foil to the edges of the fairing.
8. The retrofitting method of claim 6, wherein said inner surface of said fairing is provided with recesses for mating with components on said pressure strip to facilitate mating of said inner surface of said fairing with said upper surface of said pressure strip.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011555584.0A CN112758348A (en) | 2020-12-24 | 2020-12-24 | Pressure distribution measuring device for flight test and pressure measuring belt modification method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011555584.0A CN112758348A (en) | 2020-12-24 | 2020-12-24 | Pressure distribution measuring device for flight test and pressure measuring belt modification method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112758348A true CN112758348A (en) | 2021-05-07 |
Family
ID=75694215
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011555584.0A Pending CN112758348A (en) | 2020-12-24 | 2020-12-24 | Pressure distribution measuring device for flight test and pressure measuring belt modification method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112758348A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113593736A (en) * | 2021-07-23 | 2021-11-02 | 中国核动力研究设计院 | Pulsating pressure measuring device and using method thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0412201A (en) * | 1990-05-01 | 1992-01-16 | Komatsu Ltd | Detecting sensor for bending angle of articulation |
| CN206876373U (en) * | 2017-04-20 | 2018-01-12 | 中国商用飞机有限责任公司 | Surface pressure measuring device of aircraft slat covering |
| CN208537133U (en) * | 2018-05-17 | 2019-02-22 | 中国航空工业集团公司哈尔滨空气动力研究所 | Fluctuation pressure sensor attachment structure in a kind of low-speed buffeting test |
-
2020
- 2020-12-24 CN CN202011555584.0A patent/CN112758348A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0412201A (en) * | 1990-05-01 | 1992-01-16 | Komatsu Ltd | Detecting sensor for bending angle of articulation |
| CN206876373U (en) * | 2017-04-20 | 2018-01-12 | 中国商用飞机有限责任公司 | Surface pressure measuring device of aircraft slat covering |
| CN208537133U (en) * | 2018-05-17 | 2019-02-22 | 中国航空工业集团公司哈尔滨空气动力研究所 | Fluctuation pressure sensor attachment structure in a kind of low-speed buffeting test |
Non-Patent Citations (2)
| Title |
|---|
| 尹振吉: "压力分布传感器在飞机尾翼上粘接安装工艺研究", 《民用飞机设计与研究》, no. 2, pages 59 - 63 * |
| 李亚南等: "压力分布飞行实测进展研究", 《科技传播》, no. 11, pages 175 - 179 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113593736A (en) * | 2021-07-23 | 2021-11-02 | 中国核动力研究设计院 | Pulsating pressure measuring device and using method thereof |
| CN113593736B (en) * | 2021-07-23 | 2024-01-23 | 中国核动力研究设计院 | Pulsation pressure measuring device and application method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US5874671A (en) | Instrumented device of small thickness forming a skin | |
| US6953982B1 (en) | Flexible skin incorporating MEMS technology | |
| CN111415877B (en) | Manufacturing method and mold of solar cell bonding quality detection standard sample | |
| KR101856269B1 (en) | Quick composite repair template tool and method | |
| CN105424238B (en) | Stress strain sensor | |
| US7596997B2 (en) | Methods and apparatus for an in-flight precipitation static sensor | |
| JP6937106B2 (en) | Systems and methods for monitoring the structural integrity of joined components | |
| CN106121906A (en) | Component is installed to the method for wind turbine blade and wind turbine blade and component | |
| EP2159560A2 (en) | Resistive contact sensors for large blade and airfoil fluid dynamic parameter measurements | |
| CN112758348A (en) | Pressure distribution measuring device for flight test and pressure measuring belt modification method | |
| US5289722A (en) | Preassembled, easily mountable strain gage | |
| CN201093998Y (en) | Polyimide film substrate deformeter | |
| CN104564949B (en) | A kind of localization method of piston type foil gauge fast-positioning device | |
| CN100538323C (en) | Utilize the method for EAA films test vacuum aluminized film aluminium lamination adhesion | |
| EP2159559A2 (en) | Resistive contact sensors for large blade and airfoil pressure measurements | |
| CN103261021A (en) | Multi-directional load joint system | |
| CN105026136B (en) | The manufacture method of panel layer stack and solid state method of discrimination | |
| US20120326915A1 (en) | Housing for aircraft mounted components | |
| CN101278185B (en) | Traction pad for device testing adhesion of a coating on a substrate | |
| CN102700723A (en) | Installation method of simulated ice-shaped product | |
| US20080191423A1 (en) | Sealant template for use in sealing joints and method of sealing joints | |
| CN108318218B (en) | Flexible film type multi-measuring-point pressure measuring belt for low-speed wind tunnel | |
| CN112098324A (en) | Method for testing peel strength of electronic adhesive and adhered PC (polycarbonate) substrate sample | |
| CN202189005U (en) | Peel strength testing device | |
| US20160313150A1 (en) | Measurement device comprising sensors arranged in recesses covered by a single film |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |