CN209938981U - Aircraft airspeed tube angle adjusting device - Google Patents
Aircraft airspeed tube angle adjusting device Download PDFInfo
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- CN209938981U CN209938981U CN201920451158.9U CN201920451158U CN209938981U CN 209938981 U CN209938981 U CN 209938981U CN 201920451158 U CN201920451158 U CN 201920451158U CN 209938981 U CN209938981 U CN 209938981U
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- angle
- angle adjusting
- mounting plate
- adjusting disc
- airspeed
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Abstract
An angle adjusting device of an aircraft pitot tube comprises a pitot tube, an angle adjusting disc and an auxiliary mounting plate, wherein the angle adjusting disc is embedded into an annular groove of the auxiliary mounting plate, so that an angle indicating line of the angle adjusting disc corresponds to an angle scale line of the auxiliary mounting plate, and then a pitot tube base is placed on the angle adjusting disc for positioning; fixedly connecting the pitot tube base, the angle adjusting disc and the auxiliary mounting plate by using a connecting piece; when the installation angle of airspeed tube needs to be adjusted, the connecting piece is loosened, the angle adjusting disc is taken out from the annular groove of the auxiliary mounting plate, the relative relation between the angle indicating line of the angle adjusting disc and the angle scale line of the auxiliary mounting plate meets the installation angle requirement of the airspeed tube, and the airspeed tube base, the angle adjusting disc and the auxiliary mounting plate are fixedly connected by the connecting piece.
Description
Technical Field
The application relates to the technical field of installation and design of aircraft airspeed tubes, in particular to an airspeed tube angle adjusting technology for test flight of an aircraft in development and approval.
Background
Newly-researched aircraft must test the calibration process of flying to the airspeed head, need adjust the installation angle of airspeed head according to the data that the aircraft tested the data of flying in-process and gathered to confirm the best installation angle of airspeed head, the installation of airspeed head selects best installation angle after the aircraft is batched and does not just adjust its angle no longer. Civil aircraft airspeed head is generally installed on aircraft nose outer skin, it is a comparatively trouble thing to adjust airspeed head angle on the aircraft is criticized in the development, the method of current domestic and foreign generally adopts sets up the keysets, rivet the keysets on aircraft nose skin, with airspeed head installation base direct mount on the keysets, when adjusting airspeed head installation angle, tear airspeed head off from the keysets earlier, then demolish and scrap the keysets from aircraft nose skin, redesign the new keysets of manufacturing according to the angle that the airspeed head needs to be adjusted, install new keysets on aircraft nose skin, thereby install airspeed head on the keysets and realize airspeed head installation angle's regulation. The prior art has the advantage of simple structural design. The prior art has the following defects: 1) one mounting plate needs to be scrapped every time the mounting angle of the airspeed head is adjusted, and a new mounting plate is designed and manufactured again, so that the cost is high; 2) the adapter plate is generally connected by riveting or screwing to ensure air tightness, the dismounting and replacing process is long, and the test flight period is influenced to a certain extent; 3) the adapter plate is disassembled and assembled for many times, which has certain influence on the air tightness of the machine head.
Disclosure of Invention
In order to solve the problem of the difficult adjustment of the installation angle of the pilot aircraft airspeed tube, the utility model aims to provide a pilot aircraft airspeed tube angle adjusting device which reduces the design and maintenance cost, shortens the pilot flight period, and realizes the functions of fast adjustment and fast reading of the installation angle of the airspeed tube.
The utility model provides an aircraft airspeed tube angle adjusting device contains airspeed tube, angle adjusting disk and supplementary mounting panel, a serial communication port, the angle adjusting disk is an annular structure who takes the external tooth, and the base of airspeed tube can be fixed on the angle adjusting disk, supplementary mounting panel be connected with the aircraft organism, the center of supplementary mounting panel has a ring channel that matches with the angle adjusting disk, is equipped with the internal tooth that corresponds with the adjusting disk external tooth on the cell wall of ring channel, is equipped with the slotted hole of installation angle adjusting disk on the tank bottom of ring channel.
The auxiliary mounting plate on be equipped with the angle scale mark of airspeed head, be equipped with the angle indicating line of airspeed head on the angle dial.
When the device is used, the angle adjusting disc is embedded into the annular groove of the auxiliary mounting plate, so that the angle indicating line of the angle adjusting disc corresponds to the angle scale line of the auxiliary mounting plate, and then the pitot tube base is placed on the angle adjusting disc for positioning; and the airspeed tube base, the angle adjusting disc and the auxiliary mounting plate are fixedly connected by a connecting piece. When the installation angle of airspeed tube needs to be adjusted, the connecting piece is loosened, the angle adjusting disc is taken out from the annular groove of the auxiliary mounting plate, the relative relation between the angle indicating line of the angle adjusting disc and the angle scale line of the auxiliary mounting plate meets the installation angle requirement of the airspeed tube, and the airspeed tube base, the angle adjusting disc and the auxiliary mounting plate are fixedly connected by the connecting piece.
A layer of rubber sealing gasket is arranged between the angle adjusting disc and the auxiliary mounting plate, so that the air tightness between the angle adjusting disc and the auxiliary mounting plate is ensured;
the aircraft has the beneficial effects that 1) the structural design is simple, the size of the angle adjusting disc is small, and the overall structure of the aircraft is not influenced; 2) the functions of quickly adjusting and reading the mounting angle of the airspeed head are realized; 3) the design and maintenance cost is effectively reduced, and the test flight period is shortened; 4) the structural form ensures high reliability and safety.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a schematic diagram of an aircraft airspeed head angle adjustment device
FIG. 2 is an axial view of an angle adjusting disk
FIG. 3 is an axial view of an auxiliary mounting plate
The numbering in the figures illustrates: 1 airspeed head, 2 bases, 3 connecting pieces, 4 angle adjusting disks, 5 external teeth, 6 rubber sealing gaskets, 7 auxiliary mounting plates, 8 annular grooves, 9 internal teeth, 10 slotted holes, 11 angle indicating lines, 12 connection limiting holes and 13 angle scale lines.
Detailed Description
Referring to the attached drawings, the angle adjusting device for the airspeed head of the airplane comprises an airspeed head 1, an angle adjusting disc 4 and an auxiliary mounting plate 7, wherein the angle adjusting disc 4 is of an annular structure with external teeth 5, a connecting limiting hole 12 corresponding to a base 2 of the airspeed head is formed in the angle adjusting disc 4, and the base 2 of the airspeed head and the angle adjusting disc 4 can be limited through a connecting piece, namely the base 2 of the airspeed head is fixed on the angle adjusting disc 4; in order to ensure the air tightness of an airplane body, the auxiliary mounting plate 7 can be directly fixed on the airplane through rivets, the center of the auxiliary mounting plate 7 is provided with an annular groove 8 matched with the angle adjusting disc, the groove wall of the annular groove 8 is provided with internal teeth 9 corresponding to the external teeth 5 of the adjusting disc, the angle adjusting disc 4 is embedded into the annular groove 8 of the auxiliary mounting plate, the external teeth 5 of the angle adjusting disc are mutually meshed with the internal teeth 9 on the groove wall of the annular groove of the auxiliary mounting plate, and the limit of the angle adjusting disc 4 and the auxiliary mounting plate 7 is realized; when the angle adjusting disc 4 adjusts the installation angle, the connecting piece 3 rotates along with the angle adjusting disc, so the slotted hole 10 is arranged at the bottom of the annular groove 8.
Be equipped with airspeed tube 1's angle scale mark 13 on the supplementary mounting panel 7, be equipped with airspeed tube's angle indicator line 11 on angle adjusting disk 4, can directly read airspeed tube installation angle, when airspeed tube 1 installation angle adjusts, can realize aiming at the angle fast and install simultaneously.
A layer of rubber sealing gasket 6 is arranged between the angle adjusting disc 4 and the auxiliary mounting plate 7, so that the air tightness between the angle adjusting disc 4 and the auxiliary mounting plate 7 is ensured;
when the airspeed tube base 2 is installed on the angle adjusting disk 4, a sealant is coated, so that the air tightness between the airspeed tube base 2 and the angle adjusting disk 4 is ensured.
When the airspeed tube 1 is installed, the angle adjusting disc 4 is embedded into the annular groove 8 of the auxiliary mounting plate, so that an angle indicating line 11 of the angle adjusting disc 4 corresponds to an angle scale line 13 of the auxiliary mounting plate 7, the airspeed tube base 2 is placed on the angle adjusting disc 4, and the airspeed tube base 2, the angle adjusting disc 4, the rubber sealing gasket 6 and the auxiliary mounting plate 7 are fixed by connecting pieces; the angle adjusting disc 4 is provided with a connecting limiting hole 12 corresponding to the pitot tube base 2, and the pitot tube base 2 and the angle adjusting disc 4 can be fixed through the connecting piece 3; the external teeth 5 of the angle adjusting disc are meshed with the internal teeth 9 on the groove wall of the annular groove 8 of the auxiliary mounting plate so as to realize angle restraint.
When the mounting angle of the airspeed tube 1 is adjusted, the connecting piece 3 is loosened, the angle adjusting disc 4 is taken out from the annular groove 8 of the auxiliary mounting plate, the relative relation between the angle indicating line 11 of the angle adjusting disc 4 and the angle scale line 13 of the auxiliary mounting plate 7 is adjusted, the mounting angle requirement of the airspeed tube 1 is met, and the airspeed tube base 2, the angle adjusting disc 4 and the auxiliary mounting plate 7 are fixedly connected through the connecting piece 3.
Claims (3)
1. The utility model provides an aircraft airspeed tube angle adjusting device contains airspeed tube, angle adjusting disk and supplementary mounting panel, a serial communication port, the angle adjusting disk is an annular structure who takes the external tooth, and the base of airspeed tube can be fixed on the angle adjusting disk, supplementary mounting panel be connected with the aircraft organism, the center of supplementary mounting panel has a ring channel that matches with the angle adjusting disk, is equipped with the internal tooth that corresponds with the adjusting disk external tooth on the cell wall of ring channel, is equipped with the slotted hole of installation angle adjusting disk on the tank bottom of ring channel.
2. An aircraft pitot tube angle adjustment device as claimed in claim 1, wherein the auxiliary mounting plate is provided with angle graduations of the pitot tube and the angle adjustment dial is provided with angle indicating lines of the pitot tube.
3. An aircraft pitot tube angle adjustment device as claimed in claim 1, wherein a rubber gasket is provided between the angle adjustment disk and the auxiliary mounting plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920451158.9U CN209938981U (en) | 2019-04-03 | 2019-04-03 | Aircraft airspeed tube angle adjusting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920451158.9U CN209938981U (en) | 2019-04-03 | 2019-04-03 | Aircraft airspeed tube angle adjusting device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209938981U true CN209938981U (en) | 2020-01-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920451158.9U Active CN209938981U (en) | 2019-04-03 | 2019-04-03 | Aircraft airspeed tube angle adjusting device |
Country Status (1)
| Country | Link |
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| CN (1) | CN209938981U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109878747A (en) * | 2019-04-03 | 2019-06-14 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft airspeed tube angulation regulating device and adjusting method |
-
2019
- 2019-04-03 CN CN201920451158.9U patent/CN209938981U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109878747A (en) * | 2019-04-03 | 2019-06-14 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft airspeed tube angulation regulating device and adjusting method |
| CN109878747B (en) * | 2019-04-03 | 2023-08-04 | 西安飞机工业（集团）有限责任公司 | Device and method for adjusting angle of airspeed tube of aircraft |
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