JPH02166806A - Radome fixing ring for flying object - Google Patents
Radome fixing ring for flying objectInfo
- Publication number
- JPH02166806A JPH02166806A JP32138588A JP32138588A JPH02166806A JP H02166806 A JPH02166806 A JP H02166806A JP 32138588 A JP32138588 A JP 32138588A JP 32138588 A JP32138588 A JP 32138588A JP H02166806 A JPH02166806 A JP H02166806A
- Authority
- JP
- Japan
- Prior art keywords
- radome
- fixing ring
- carbon fiber
- fiber reinforced
- ceramic
- 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
- 239000004918 carbon fiber reinforced polymer Substances 0.000 claims abstract description 12
- 239000000463 material Substances 0.000 claims abstract description 7
- 239000000470 constituent Substances 0.000 claims description 4
- 239000000919 ceramic Substances 0.000 abstract description 11
- 229920000049 Carbon (fiber) Polymers 0.000 abstract description 4
- 239000004917 carbon fiber Substances 0.000 abstract description 4
- 239000003822 epoxy resin Substances 0.000 abstract description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 abstract description 4
- 229920000647 polyepoxide Polymers 0.000 abstract description 4
- 239000011151 fibre-reinforced plastic Substances 0.000 description 2
- 239000003365 glass fiber Substances 0.000 description 2
- 229920001225 polyester resin Polymers 0.000 description 2
- 239000004645 polyester resin Substances 0.000 description 2
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
この発明は、ミサイル等の飛しよう体の弾頭部に設けら
れるレドーム（レーダードーム）を胴体部に固定するた
めの飛しよう体用レドーム固定リングに関するものであ
る。[Detailed Description of the Invention] [Field of Industrial Application] The present invention relates to a radome fixing ring for a flying body such as a missile for fixing a radome (radome) provided on the warhead of a flying body such as a missile to the body. It is related to.
第１図は飛しよう体の一部の断面図であり、図において
、（１）は飛しよう体の弾頭部に設けられるセラミック
環のレドーム、（２）はレドーム（１）と飛しよう体の
胴体部（３）を固定するための固定リングで、ガラスフ
ァイバーとポリエステル樹脂からなる繊維強化プラスチ
ック （Ｆｉｂｅｒ Ｒｅ１ｎｆｏｒｃｅｄＰｌａｓｔ
ｉｃｓ、以下ＦＲＰと称す）によって形成されている。Figure 1 is a cross-sectional view of a part of the flying body. In the figure, (1) is a ceramic ring radome provided on the warhead of the flying body, and (2) is the connection between the radome (1) and the flying body. A fixing ring for fixing the body part (3), made of fiber reinforced plastic (Fiber Reinforced Plast) made of glass fiber and polyester resin.
ics (hereinafter referred to as FRP).
上記の構成において、セラミック環のレドーム（１）は
Ｆ ＲＰ製の固定リング（２）に接着され、さらにＦＲ
Ｐ製の固定リング（２）は胴体部（３）に固定され、こ
れによりセラミック環のレドーム（１）と胴体部（３）
はＦＲＰ製の固定リング（２）を介して固着される。In the above configuration, the ceramic ring radome (1) is glued to the fixing ring (2) made of F RP, and
A fixing ring (2) made of P is fixed to the body part (3), thereby connecting the ceramic ring radome (1) and the body part (3).
is fixed via a fixing ring (2) made of FRP.
しかるに従来の固定リング（２）は、ガラスファイバー
とポリエステル樹脂からなるＦＲＰを用いており、レド
ーム（１）は耐熱性を向上させるためにセラミックを用
いている。このため、固定リング（２）とレドーム（１
）の材料が相違することから、高温時に熱膨張率の違い
による割れが発生する問題があった。However, the conventional fixing ring (2) uses FRP made of glass fiber and polyester resin, and the radome (1) uses ceramic to improve heat resistance. For this reason, the fixing ring (2) and the radome (1
), there was a problem of cracks occurring due to differences in thermal expansion coefficients at high temperatures.
この発明は、上記の問題点を解決するためになされたも
ので、熱膨張率の差が小さく、割れが発生しない飛しょ
う体用レドーム固定リングを得ることを目的とする。The present invention was made to solve the above-mentioned problems, and an object of the present invention is to obtain a radome fixing ring for a flying object that has a small difference in coefficient of thermal expansion and is free from cracks.
この発明に係る飛しょう体用レドーム固定リングは、そ
の構成材料として炭素繊維強化プラスチック（Ｃａｒｂ
ｏｎ Ｆｉｂｅｒ Ｒｅ１ｎｆｏｒｃｅｄ Ｐｌａｓｔ
ｉｃｓ％以下ＣＦＲＰと称す）を用いたものである。The radome fixing ring for a flying object according to the present invention uses carbon fiber reinforced plastic (Carbon fiber reinforced plastic) as its constituent material.
on Fiber Reinforced Plast
ics% (hereinafter referred to as CFRP).
ＣＦＲＰとしてはカーボン繊維とエポキシ樹脂からなる
ものが使用できる。As CFRP, one made of carbon fiber and epoxy resin can be used.
この発明の飛しょう体用レドーム固定リングにおいては
、その構成材料としてＣ：ＦＲＰを用いるため、熱膨張
率がＯ〜Ｉ Ｘ １０−’ と小さく、レドームの材料
であるセラミックの熱膨張率に近いことから、割れが発
生しない。Since the radome fixing ring for a flying object of the present invention uses C:FRP as its constituent material, the coefficient of thermal expansion is as small as O to I x 10-', which is close to the coefficient of thermal expansion of ceramic, which is the material of the radome. Therefore, no cracking occurs.
以下、この発明の一実施例を図について説明する。本発
明の実施例における固定リングを用いた飛しよう体は第
１図と同様に表わされる。図において、セラミック製の
レドーム（１）と胴体部（３）を固定する固定リング（
２）は、カーボン繊維とエポキシ樹脂からなるＣＦＲＰ
によってリング状に形成されている。An embodiment of the present invention will be described below with reference to the drawings. A flying object using a fixing ring according to an embodiment of the present invention is shown in the same manner as in FIG. In the figure, the fixing ring (
2) is CFRP made of carbon fiber and epoxy resin.
It is formed into a ring shape.
上記の構成において、セラミック製のレドーム（１）は
胴体部（３）と固着するために、ＣＦＲＰＩＩの固定リ
ング（２）を介して接着され、胴体部（３）に固着され
る。高温での環境下では、セラミック製のレドーム（１
）とＣＦＲＰ製の固定リング（２）の熱膨張率がほぼ近
いことから、割れが発生しない。固定リング（２）の材
料としては、例えばカーボン繊維とエポキシ樹脂が用い
られる。In the above configuration, the ceramic radome (1) is bonded to the body (3) through a CFRPII fixing ring (2), and is fixed to the body (3). In high temperature environments, ceramic radomes (1
) and the CFRP fixing ring (2) have almost the same coefficient of thermal expansion, so no cracks occur. For example, carbon fiber and epoxy resin are used as materials for the fixing ring (2).
以上のように、この発明によれば、固定リングの構成材
料としてＣＦＲＰを用いたので、熱膨張率をほぼセラミ
ック製レドームと同じにすることができ、これにより割
れの発生が防止できる効果がある。As described above, according to the present invention, since CFRP is used as the constituent material of the fixing ring, the coefficient of thermal expansion can be made almost the same as that of a ceramic radome, which has the effect of preventing the occurrence of cracks. .
第１図はこの発明の一実施例および従来例の飛しよう体
の一部の断面図である。
図において、（１）はレドーム、（２）は固定リング、
（３）は胴体部である。
第１図FIG. 1 is a sectional view of a part of a flying object according to an embodiment of the present invention and a conventional example. In the figure, (1) is a radome, (2) is a fixing ring,
(3) is the body part. Figure 1
Claims (1)
において、その構成材料として、炭素繊維強化プラスチ
ックを用いたことを特徴とする飛しょう体用レドーム固
定リング。(1) A radome fixing ring for a flying body, characterized in that the ring fixes the radome and the fuselage of the flying body, using carbon fiber reinforced plastic as its constituent material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP32138588A JPH02166806A (en) | 1988-12-20 | 1988-12-20 | Radome fixing ring for flying object |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP32138588A JPH02166806A (en) | 1988-12-20 | 1988-12-20 | Radome fixing ring for flying object |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH02166806A true JPH02166806A (en) | 1990-06-27 |
Family
ID=18131967
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP32138588A Pending JPH02166806A (en) | 1988-12-20 | 1988-12-20 | Radome fixing ring for flying object |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH02166806A (en) |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS61138095A (en) * | 1984-12-10 | 1986-06-25 | 三菱電機株式会社 | Method of mounting radome for missile |
-
1988
- 1988-12-20 JP JP32138588A patent/JPH02166806A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS61138095A (en) * | 1984-12-10 | 1986-06-25 | 三菱電機株式会社 | Method of mounting radome for missile |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4520364A (en) | Attachment method-ceramic radome to metal body | |
| US3203849A (en) | Composite heat shield | |
| ATE34968T1 (en) | MACHINE PARTS. | |
| US10792891B2 (en) | Polymer matrix-ceramic matrix hybrid composites for high thermal applications | |
| JP2017139522A (en) | Flight body radome | |
| RU2225664C2 (en) | Cone | |
| Harnisch et al. | Ultra-lightweight C/SiC mirrors and structures | |
| US4967599A (en) | Mechanical and insulating connection between a nozzle and the filament-wound casing of the combustion chamber of a solid propellant rocket motor | |
| JP6278924B2 (en) | Method for manufacturing flying radome | |
| JPH02166806A (en) | Radome fixing ring for flying object | |
| US3103887A (en) | Pre-stressed glass fiber attachment ring | |
| US3116547A (en) | Method for coupling a pair of cylindrical members in end-to-end abutment | |
| EP1099090B1 (en) | Vehicle having a ceramic radome affixed thereto by a compliant metallic "t"-flexure element | |
| JP3899858B2 (en) | Flying radome | |
| RU2090956C1 (en) | Antenna fairing | |
| JPS63311803A (en) | Radome support | |
| US5705012A (en) | Method for molding planar billet of thermally insulative material into predetermined non-planar shape | |
| CA1175241A (en) | Mechanical and insulating connection between a nozzle and the filament-wound casing of the combustion chamber of a rocket motor | |
| US4820955A (en) | Traveling wave tube comprising periodic permanent magnetic focusing system with glass/epoxy retaining means | |
| CN110864681A (en) | Temperature control type optical fiber ring module | |
| RU2189672C1 (en) | Missile antenna nose fairing | |
| JP7154182B2 (en) | flying body | |
| JP7325237B2 (en) | Radome for flying objects | |
| JPS61138095A (en) | Method of mounting radome for missile | |
| Lamicq et al. | Ceramic matrix composite parts design |