CN214947383U - Bolt tool for firewall of general airplane - Google Patents
Bolt tool for firewall of general airplane Download PDFInfo
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- CN214947383U CN214947383U CN202121617088.3U CN202121617088U CN214947383U CN 214947383 U CN214947383 U CN 214947383U CN 202121617088 U CN202121617088 U CN 202121617088U CN 214947383 U CN214947383 U CN 214947383U
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Abstract
The utility model discloses a bolt frock of hot wall is prevented to general aircraft, including bolt and nut to and ring sleeve, ring sleeve is equipped with annular boss, and ring sleeve supports presses on the stainless steel plate of preventing hot wall, and the cooperation of annular boss is in the stainless steel diaphragm orifice, and the bolt passes ring sleeve hole and combined material and strengthens the inserts hole, cooperates with the nut. Prevent that hot wall accomplishes preliminary splicing back, install the bolt frock, wait to prevent that hot wall precuring accomplishes the back and take off the bolt frock. The circular boss can ensure that the centers of the hole of the stainless steel plate of the firewall and the hole of the composite material reinforcing insert are positioned on the same axis; the annular sleeve can ensure that stainless steel plate and combined material level and smooth laminating prevent that annular boss from producing the extrusion to the stainless steel diaphragm orifice, reduce the rate of reprocessing of part.
Description
Technical Field
The utility model relates to a general purpose aircraft, concretely relates to general purpose aircraft prevent hot wall.
Background
A general-purpose aircraft firewall is an insulating structural member for preventing heat generated by an engine from being diffused to other cabins. And also the mounting support for the engine, it also comprises an attachment for the engine mount, with holes for connection to the different systems of the engine, called engine mount holes.
The patent document with the publication number of CN 211001866U discloses a general fireproof wall structure of an aircraft engine cabin, which comprises a stainless steel thin plate layer, a first high-temperature-resistant resin layer, a kaolin cotton layer, a second high-temperature-resistant resin layer and a fireproof glass fiber layer. The stainless steel sheet layer, the first high-temperature-resistant resin layer, the kaolin cotton layer, the second high-temperature-resistant resin layer and the refractory glass fiber layer are sequentially arranged in the direction from the engine compartment to the machine body main body. And high-strength high-temperature-resistant glass fiber inserts are arranged around the engine bracket mounting holes on the firewall.
When the general-purpose aircraft firewall is manufactured, the hole of the stainless steel plate on the engine support mounting hole (namely, the hole on the stainless steel thin plate layer) is slightly larger than the hole of the composite material reinforcing insert (namely, the hole on the high-strength high-temperature-resistant glass fiber insert). If only a common bolt is used, in the manufacturing process, because the high-temperature-resistant resin between the stainless steel plate (namely the stainless steel thin plate layer) and the composite material (the composite material formed by the first high-temperature-resistant resin layer, the kaolin cotton layer, the second high-temperature-resistant resin layer and the refractory glass fiber layer) does not reach the gel point, the sliding between the layers is easy to occur, and the circle centers of the hole of the stainless steel plate and the hole of the composite material reinforcing insert are not on the same axis.
In addition, the thermal expansion coefficients of the stainless steel plate and the composite material are different greatly, so that the thermal stress is mismatched, and the holes of the stainless steel plate are easy to tilt and the like. So, influence the quality of engine support mounting hole, lead to subsequent engine installation difficulty.
SUMMERY OF THE UTILITY MODEL
The utility model solves the technical problem that: the circle centers of the stainless steel plate hole and the composite material reinforcing insert hole of the general airplane firewall are not on the same axis.
In order to solve the technical problem, the utility model provides a following technical scheme: the utility model provides a bolt frock that general aircraft prevented hot wall, includes bolt and nut to and ring sleeve, ring sleeve is equipped with annular boss, and ring sleeve supports presses on the stainless steel sheet of preventing hot wall, and the cooperation of annular boss is in the stainless steel diaphragm orifice, and the bolt passes ring sleeve hole and combined material and strengthens the inserts hole, cooperates with the nut.
Prevent that hot wall accomplishes preliminary splicing back, install the bolt frock, wait to prevent that hot wall precuring accomplishes the back and take off the bolt frock.
The annular boss can ensure that the circle centers of the stainless steel plate hole of the firewall and the hole center of the composite material reinforcing insert are positioned on the same axis. The annular sleeve can ensure that the stainless steel plate is smoothly attached to the composite material, the annular boss is prevented from extruding the hole of the stainless steel plate, and the repair rate of the part is reduced.
Drawings
The invention will be further explained with reference to the drawings:
fig. 1 is the utility model discloses a bolt frock prevent hot wall's integrated configuration sketch map with general aircraft.
The symbols in the drawings illustrate that:
1. a bolt; 2. a nut; 3. an annular sleeve; 4. a stainless steel plate; 5. a high temperature resistant resin layer; 6. a layer of kaolin cotton; 7. a refractory fiberglass layer; 8. the composite material reinforces the insert.
Detailed Description
If fig. 1, a bolt frock of hot wall is prevented to general aircraft, including bolt 1 and nut 2 to and annulus 3, the annulus is equipped with annular boss, and the annulus supports to press on the stainless steel board of preventing hot wall, and the cooperation of annular boss is in the stainless steel diaphragm orifice, and the bolt passes annulus hole and combined material and strengthens the inserts hole, cooperates with the nut.
Prevent hot wall and include corrosion resistant plate 4, high temperature resistant resin layer 5, the cotton layer 6 of kaolin, fire-resistant glass fiber layer 7, high temperature resistant glass fiber's inserts 8, these prevent that hot wall component accomplishes preliminary splicing back, the installation bolt frock. The annular boss cooperation is in the stainless steel diaphragm orifice, and the main part of ring sleeve 3 supports to press on preventing hot wall's stainless steel plate 4, and bolt 1 inserts ring sleeve 3's hole, passes combined material again and strengthens the inserts hole, and the bolt is worn out the one end spiro union nut 2 that combined material strengthened the inserts hole. Wherein, the external diameter of annular boss equals the internal diameter in stainless steel plate hole, and the pole portion of bolt 1 equals with the internal diameter of annular sleeve 3, and is equal with the internal diameter in combined material reinforcing insert hole. Therefore, bolt frock can guarantee that stainless steel plate hole and combined material strengthen that the inserts hole centre of a circle is in on same axis, moreover, can guarantee that corrosion resistant plate and combined material level and smooth laminating. The composite material is an integral body formed by gluing a high-temperature-resistant resin layer 5, a kaolin cotton layer 6, a refractory glass fiber layer 7 and an insert 8 of high-temperature-resistant glass fiber. And taking down the bolt tool after the pre-curing of the firewall is finished.
Insert 8 offsets is strengthened with combined material to annular boss, so, stainless steel plate 4 and cotton layer 6 of kaolin, high temperature resistant resin layer 5 between high temperature resistant glass fiber's the insert 8, can only contact with the annular boss of annular sleeve 3, annular boss prevents that high temperature resistant resin from flowing into the stainless steel diaphragm orifice, the combined material strengthens the insert downthehole, and, with bolt 1's screw thread veneer when avoiding the solidification of high temperature resistant resin, reduce the influence to engine support mounting hole quality when the bolt is dismantled.
The method for manufacturing the bolt tool of the utility model is as follows. The bolt 1 and the nut 2 are made of existing metal bolts. And measuring the inner diameter D1 and the depth L1 of the composite material reinforcing insert hole, and selecting a bolt and a nut with proper size and length. The inside diameter D2 of the stainless steel plate hole and the thickness L2 of the stainless steel plate were measured. The inner diameter of the annular sleeve 3 is D1, the maximum outer diameter is 3 times of D2, and the thickness of the main body part of the annular sleeve (the annular sleeve except the annular boss part) is selected to be (5-L2) mm. The annular boss of the annular sleeve 3 has an outer diameter D2 and a thickness L2. The manufacturing method of the annular sleeve 3 comprises the following steps: drawing three concentric circles on a composite laminated plate with the thickness of 5mm, wherein the diameters of the circles are D1, D2 and 3D2 respectively; positioning the circle center by using an electric drill, and expanding the aperture of the circle center to D1; cutting and grinding off excess materials outside the circle with the diameter of 3D2, and grinding out a step of L2 along the outside of the circle with the diameter of D2.
In actual operation, the inner diameter of a hole of the firewall composite reinforcing insert is measured to be 8mm, the depth of the hole is measured to be 10mm, and a bolt 1 and a nut 2 with proper sizes and lengths are selected according to the size. The inner diameter of the stainless steel plate hole of the firewall and the thickness of the stainless steel plate are measured to be 14mm and 0.4mm respectively. The inner diameter of the annular sleeve 3 was 8mm, the maximum outer diameter was 42mm, and the thickness of the main portion of the annular sleeve was 4.6 mm. The outer diameter of the annular boss is 14mm, and the thickness is 0.4 mm. The manufacturing method comprises the following steps: drawing three concentric circles on a composite laminated plate with the thickness of 5mm, wherein the diameters of the three concentric circles are 8mm, 14mm and 42mm respectively; positioning the circle center by using an electric drill, and expanding the aperture to 8 mm; cutting and polishing off excess materials outside the circle with the diameter of 42mm, and then grinding a step with the diameter of 0.4mm along the outside of the circle with the diameter of 14 mm.
Preferably, the material of the annular sleeve 3 is a glass fiber reinforced composite material, so that the annular sleeve and the high temperature resistant resin layer 5 to be cured belong to the same resin and have similar thermal expansion coefficients. In the solidification process after the preliminary cementing of firewall, the resin can give off the heat, because the coefficient of thermal expansion between the resin is close, can reduce the thermal stress of high temperature resistant resin layer 5 to guarantee the quality of engine support mounting hole.
Further, in order to facilitate the disassembly and reuse of the bolt tool and prolong the service life of the bolt tool, the bolt tool is cleaned and waxed before being used. The method comprises the following specific steps: placing the bolt tool in an acetone solution, and cleaning for 10 minutes by using an ultrasonic cleaner; and taking out the bolt tool, wiping the bolt tool with wiping paper, soaking the bolt tool in a release agent for 30 seconds, wiping the bolt tool with the wiping paper after taking out the bolt tool, and repeating the process for 3-5 times.
The above description is only for the preferred embodiment of the present invention, and for those skilled in the art, there are variations on the detailed description and the application scope according to the idea of the present invention, and the content of the description should not be construed as a limitation to the present invention.
Claims (5)
1. The utility model provides a firewall's bolt frock is prevented to general aircraft, includes bolt (1) and nut (2) to and annulus (3), its characterized in that: the annular sleeve is provided with an annular boss, the annular sleeve is pressed on a stainless steel plate of the firewall, the annular boss is matched in a stainless steel plate hole, and the bolt penetrates through an inner hole of the annular sleeve and the composite material reinforcing insert hole to be matched with the nut.
2. The bolt tooling of the general-purpose aircraft firewall is characterized in that: the outer diameter of the annular boss is equal to the inner diameter of the hole of the stainless steel plate.
3. The bolt tooling of the general-purpose aircraft firewall is characterized in that: the annular boss is abutted against the composite material reinforcing insert (8).
4. The bolt tooling of the general-purpose aircraft firewall is characterized in that: the outer diameter of the annular sleeve (3) is three times of the inner diameter of the hole of the stainless steel plate.
5. The bolt tooling of the general-purpose aircraft firewall is characterized in that: the material of the annular sleeve (3) is a glass fiber reinforced composite material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121617088.3U CN214947383U (en) | 2021-07-16 | 2021-07-16 | Bolt tool for firewall of general airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121617088.3U CN214947383U (en) | 2021-07-16 | 2021-07-16 | Bolt tool for firewall of general airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214947383U true CN214947383U (en) | 2021-11-30 |
Family
ID=79072086
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121617088.3U Active CN214947383U (en) | 2021-07-16 | 2021-07-16 | Bolt tool for firewall of general airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214947383U (en) |
-
2021
- 2021-07-16 CN CN202121617088.3U patent/CN214947383U/en active Active
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