JP2003021500A - Radome for flying objects - Google Patents
Radome for flying objectsInfo
- Publication number
- JP2003021500A JP2003021500A JP2001202032A JP2001202032A JP2003021500A JP 2003021500 A JP2003021500 A JP 2003021500A JP 2001202032 A JP2001202032 A JP 2001202032A JP 2001202032 A JP2001202032 A JP 2001202032A JP 2003021500 A JP2003021500 A JP 2003021500A
- Authority
- JP
- Japan
- Prior art keywords
- radome
- thermal expansion
- flying
- coefficient
- fiber
- 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.)
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Abstract
(57)【要約】
【課題】 超音速で飛しょうする飛しょう体のレドーム
に生じる空力加熱にもとづく熱応力を緩和するレドーム
を提案する。
【解決手段】 飛しょう体用レドームの先端に配置され
たセラミックレドーム１にはめあい接着され、かつ飛し
ょう体本体と嵌合される複合材料製リング２において、
低熱膨張率シート状基材４と高熱膨張率シート状基材５
とを各層毎の長さ比を漸次変化させるようにして超音速
で飛しょうする飛しょう体のレドームに生じる空力加熱
にもとづく熱応力を緩和するものである。
(57) [Summary] [PROBLEMS] To propose a radome for relaxing thermal stress based on aerodynamic heating generated in a radome of a flying object flying at supersonic speed. The composite material ring (2) is fitted and adhered to a ceramic radome (1) disposed at the tip of a flying object radome, and is fitted to the flying object body.
Low thermal expansion coefficient sheet-like substrate 4 and high thermal expansion coefficient sheet-like substrate 5
By gradually changing the length ratio of each layer, thermal stress based on aerodynamic heating generated in the radome of a flying object flying at supersonic speed is relieved.
Description
【０００１】[0001]
【発明の属する技術分野】この発明は、飛しょう体のレ
ドームに関するものである。TECHNICAL FIELD The present invention relates to a radome for a flying object.
【０００２】[0002]
【従来の技術】図５は飛しょう体用レドームの構造の説
明図である。１はセラミックレドーム、２はセラミック
レドーム１にはめあい接着されたリング、３はリング２
と嵌合され締結固定された飛しょう体本体である。2. Description of the Related Art FIG. 5 is an explanatory view of the structure of a radome for a flying object. 1 is a ceramic radome, 2 is a ring which is fitted and adhered to the ceramic radome 1, 3 is a ring 2
It is the main body of the flying body that is fitted, fastened and fixed.
【０００３】図６はセラミックレドーム１、リング２、
飛しょう体本体３の間で生じる熱応力の発生状態を説明
する図であり、セラミックレドーム１、リング２、飛し
ょう体本体３のつなぎの部分の断面図である。FIG. 6 shows a ceramic radome 1, a ring 2,
It is a figure explaining the generation | occurrence | production state of the thermal stress which arises between the flying body main bodies 3, and is sectional drawing of the connection part of the ceramic radome 1, the ring 2, and the flying body main body 3. FIG.
【０００４】飛しょう体が超音速で飛しょうすると空力
加熱により飛しょう体は加熱される。たとえばマッハ4
程度で飛しょう中に先端部の空気温度は1000℃を越え、
耐熱性と電波透過性を兼ね備えるレドーム材料はセラミ
ックしか存在しない。セラミックは一般に熱膨張率が低
く、１×１０−６から４×１０−６ ／℃程度の値を有
する。一方、飛しょう体本体３は軽量化、コストの観点
からアルミ合金で製造されることが一般的である。アル
ミ合金は２０×１０−６程度の値を有する。このように
セラミックレドーム１と飛しょう体本体３の間には大き
な熱膨張率の差があり、両者を直接連結した構造におい
ては、空力加熱により温度が上昇すると、大きな熱応力
が生じる。そのためセラミックレドーム１と飛しょう体
本体３の間に両者の熱応力を緩和するリング２を配置す
る。When a flying object flies at supersonic speed, the flying object is heated by aerodynamic heating. For example Mach 4
The air temperature at the tip exceeds 1000 ℃ while flying
The only radome material that has both heat resistance and radio wave transparency is ceramic. Ceramics generally have a low coefficient of thermal expansion and have a value of about 1 × 10 −6 to 4 × 10 −6 / ° C. On the other hand, the flying body 3 is generally manufactured from an aluminum alloy from the viewpoint of weight reduction and cost. Aluminum alloy has a value of about 20 × 10 −6 . As described above, there is a large difference in the coefficient of thermal expansion between the ceramic radome 1 and the flying body 3, and in the structure in which the two are directly connected, a large thermal stress occurs when the temperature rises due to aerodynamic heating. Therefore, a ring 2 is arranged between the ceramic radome 1 and the flying body 3 to reduce the thermal stress between them.
【０００５】空力加熱を受けたとき、セラミックレドー
ム１の熱膨張量ア、リング２の熱膨張量イ、飛しょう体
本体３の熱膨張量ウは図の矢印のごとくとなり、セラミ
ックレドーム１とリング２間の熱応力エ、リング２と飛
しょう体本体３間の熱応力オとがそれぞれの熱膨張量の
差に応じて発生する。セラミックレドーム１の熱膨張量
ア、リング２の熱膨張量イの差が小さいので、強度の低
い脆性材料であるセラミックレドーム１とリング２の間
の熱応力は小さく抑えることができる。When subjected to aerodynamic heating, the thermal expansion amount a of the ceramic radome 1, the thermal expansion amount a of the ring 2, and the thermal expansion amount c of the flying body 3 become as shown by the arrows in the figure, and the ceramic radome 1 and the ring. The thermal stress between the two and the thermal stress between the ring 2 and the flying body 3 are generated in accordance with the difference in the thermal expansion amounts. Since the difference between the thermal expansion amount A of the ceramic radome 1 and the thermal expansion amount A of the ring 2 is small, the thermal stress between the ceramic radome 1 and the ring 2, which is a brittle material having low strength, can be suppressed to be small.
【０００６】[0006]
【発明が解決しようとする課題】飛しょう体が高速にな
り、空力加熱が厳しくなるにつれて、セラミックレドー
ム１の保護のために、リング２の熱膨張率はセラミック
とより同等に近づける必要がある。このことにより、リ
ング２と飛しょう体本体３の間の熱膨張率差が大きくな
り、かつ空力加熱が厳しくなっていることの相乗で、リ
ング２と飛しょう体本体３間の熱応力が大きくなるとい
う強度上の問題が発生する。In order to protect the ceramic radome 1, it is necessary to make the coefficient of thermal expansion of the ring 2 closer to that of ceramics as the flying body becomes faster and the aerodynamic heating becomes more severe. As a result, the difference in the coefficient of thermal expansion between the ring 2 and the flying body 3 becomes large, and the aerodynamic heating becomes severe, so that the thermal stress between the ring 2 and the flying body 3 becomes large. There is a problem in strength.
【０００７】この発明は、上記従来の課題を解決するた
めになされたものであり、リングと飛しょう体本体の間
に生じる熱応力を低減する飛しょう体用レドームを提案
するものである。The present invention has been made in order to solve the above-mentioned conventional problems, and proposes a radome for a flying object which reduces the thermal stress generated between the ring and the flying object main body.
【０００８】[0008]
【課題を解決するための手段】第１の発明による飛しょ
う体用レドームは、所定の熱膨張率を有する材料で形成
され、飛しょう体本体の先端に配置されるレドームと、
前記レドームの熱膨張率よりも高い熱膨張率を有する材
料で形成された前記飛しょう体本体と前記レドームとを
結合するリングとを具備した飛しょう体用レドームにお
いて、前記リングは、前記レドームに近似する熱膨張率
を有する複合材料で形成される第１のシート状基材と前
記飛しょう体本体と近似する熱膨張率を有する複合材料
で形成される第２のシート状基材とを有し、前記第１及
び第２のシート状基材は前記レドームと飛しょう体本体
との間にあって、かつ前記第１、第２の基材の熱膨張率
が近似するレドーム及び飛しょう体本体側に配置され、
さらに前記第１のシート状基材と前記第２のシート状基
材の積層厚比を漸次変化させるものである。A radome for a flying object according to the first invention is a radome formed of a material having a predetermined coefficient of thermal expansion and arranged at the tip of a flying object main body.
In a radome for a flying vehicle, comprising a ring that connects the flying body and the radome formed of a material having a thermal expansion coefficient higher than that of the radome, wherein the ring is attached to the radome. A first sheet-like base material formed of a composite material having a similar coefficient of thermal expansion and a second sheet-like base material formed of a composite material having a coefficient of thermal expansion similar to that of the flying body. The first and second sheet-shaped base materials are between the radome and the flying body main body, and the thermal expansion coefficients of the first and second base materials are close to each other. Placed in
Further, the lamination thickness ratio of the first sheet-shaped substrate and the second sheet-shaped substrate is gradually changed.
【０００９】第２の発明による飛しょう体用レドーム
は、所定の熱膨張率を有する材料で形成され、飛しょう
体本体の先端に配置されるレドームと、前記レドームの
熱膨張率よりも高い熱膨張率を有する材料で形成された
前記飛しょう体本体と前記レドームとを結合するリング
とを具備した飛しょう体用レドームにおいて、前記リン
グは、前記レドームに近似する熱膨張率を有する複合材
料で形成される第１の繊維と前記飛しょう体本体と近似
する熱膨張率を有する複合材料で形成される第２の繊維
とを有し、前記第１及び第２の繊維は前記レドームと飛
しょう体本体との間にあって、かつ前記第１、第２の繊
維の熱膨張率が近似するレドーム及び飛しょう体本体側
に配置され、さらに前記第１の繊維と前記第２の繊維の
積層厚比を漸次変化させるものである。The radome for a flying object according to the second aspect of the invention is formed of a material having a predetermined coefficient of thermal expansion, and the radome disposed at the tip of the flying object main body and the thermal expansion coefficient higher than those of the radome. In a radome for a flying vehicle comprising a flying body main body formed of a material having an expansion coefficient and a ring connecting the radome, the ring is a composite material having a thermal expansion coefficient close to that of the radome. A first fiber formed and a second fiber formed of a composite material having a coefficient of thermal expansion similar to that of the flying body main body, wherein the first and second fibers fly with the radome It is arranged between the body and the radome and the body of the flying body, where the thermal expansion coefficients of the first and second fibers are similar to each other, and the laminated thickness ratio of the first fiber and the second fiber. Gradually change It is intended to.
【００１０】第３の発明による飛しょう体用レドーム
は、所定の熱膨張率を有する材料で形成され、飛しょう
体本体の先端に配置されるレドームと、前記レドームの
熱膨張率よりも高い熱膨張率を有する材料で形成された
前記飛しょう体本体と前記レドームとを結合するリング
とを具備した飛しょう体用レドームにおいて、前記リン
グは、前記レドームに近似する熱膨張率を有する複合材
料で形成される第１の繊維と前記飛しょう体本体と近似
する熱膨張率を有する複合材料で形成される第２の繊維
とを有し、前記第１及び第２の繊維は前記レドームと飛
しょう体本体との間にあって、かつ前記第１、第２の繊
維の熱膨張率が近似するレドーム及び飛しょう体本体側
に配置され、さらに前記第１の繊維と前記第２の繊維の
配合比を漸次変化させるものである。A radome for a flying object according to a third aspect of the invention is formed of a material having a predetermined coefficient of thermal expansion, and the radome disposed at the tip of the flying object main body has a thermal expansion coefficient higher than that of the radome. In a radome for a flying vehicle comprising a flying body main body formed of a material having an expansion coefficient and a ring connecting the radome, the ring is a composite material having a thermal expansion coefficient close to that of the radome. A first fiber formed and a second fiber formed of a composite material having a coefficient of thermal expansion similar to that of the flying body main body, wherein the first and second fibers fly with the radome It is arranged between the body and the radome and the body of the flying body where the thermal expansion coefficients of the first and second fibers are similar to each other, and the mixing ratio of the first fiber and the second fiber is Gradual change Is shall.
【００１１】第４の発明による飛しょう体用レドーム
は、材料として、セラミックを使用するものである。The radome for a flying object according to the fourth invention uses ceramics as a material.
【００１２】第５の発明による飛しょう体用レドーム
は、第１のシート状基材及び第１の繊維の材料として、
低熱膨張率の材料と、第２のシート状基材及び前記第２
の繊維の材料として、高熱膨張率の材料とを使用するこ
とを特徴とするものである。The radome for a flying vehicle according to the fifth aspect of the present invention comprises, as materials for the first sheet-like base material and the first fiber,
A material having a low coefficient of thermal expansion, a second sheet-shaped substrate and the second
A material having a high coefficient of thermal expansion is used as the fiber material.
【００１３】第６の発明による飛しょう体用レドーム
は、低熱膨張率の材料として、炭素繊維を基材とした複
合材料製からなるものである。The radome for a flying object according to the sixth invention is made of a composite material having carbon fiber as a base material, as a material having a low coefficient of thermal expansion.
【００１４】第７の発明による飛しょう体用レドーム
は、高熱膨張率の材料として、ガラス繊維を基材とした
複合材料製からなるものである。The radome for a flying vehicle according to the seventh invention is made of a composite material having glass fiber as a base material as a material having a high coefficient of thermal expansion.
【００１５】[0015]
【発明の実施の形態】実施の形態１．図１と図２を用い
てこの発明に係わる実施の形態１について説明する。図
１はこの実施の形態におけるリング２の構成を示す断面
図であり、図において４は低熱膨張率シート状基材、５
は高熱膨張率シート状基材である。図２はこの実施の形
態における熱応力の発生状態を説明する図であるBEST MODE FOR CARRYING OUT THE INVENTION Embodiment 1. A first embodiment according to the present invention will be described with reference to FIGS. 1 and 2. FIG. 1 is a cross-sectional view showing the structure of a ring 2 in this embodiment, in which 4 is a sheet-shaped substrate having a low coefficient of thermal expansion, 5
Is a sheet-shaped substrate having a high coefficient of thermal expansion. FIG. 2 is a diagram for explaining the generation state of thermal stress in this embodiment.
【００１６】まず図１において、この発明の実施の形態
１の構成を説明する。図において、低熱膨張率シート状
基材４をセラミックレドーム1側に配置し、高熱膨張率
シート状基材５を飛しょう体本体３側に配置する。基材
を積層するにあたり、低熱膨張率シート状基材４と高熱
膨張率シート状基材５の各層毎の長さ比を漸次変化させ
積層する。この積層構成のため、断面カにおける低熱膨
張率シート状基材４と高熱膨張率シート状基材５の面積
比は、方向キに進むにつれ高熱膨張率シート状基材５が
漸増する。高熱膨張率シート状基材５の面積比が漸増す
るに従い、リング２の熱膨張率も低熱膨張率から高熱膨
張率へ漸増する。ここで使用する低熱膨張率シートの材
料としては、ＣＦＲＰ（Carbon Fiber Reinforced Plas
tics）があり、熱膨張率は０．２×１０−６ ／℃程度
の値を有する。一方、高熱膨張率シートの材料として
は、ＧＦＲＰ（Glass Fiber Reinforced Plastics）が
あり、熱膨張率は８×１０−６ ／℃程度の値を有す
る。First, the configuration of the first embodiment of the present invention will be described with reference to FIG. In the figure, a low thermal expansion coefficient sheet-shaped substrate 4 is arranged on the ceramic radome 1 side, and a high thermal expansion coefficient sheet-shaped substrate 5 is arranged on the flying body 3 side. When laminating the base materials, the length ratio of each layer of the low thermal expansion coefficient sheet-shaped base material 4 and the high thermal expansion coefficient sheet-shaped base material 5 is gradually changed and laminated. Due to this laminated structure, the area ratio of the low thermal expansion coefficient sheet-shaped base material 4 to the high thermal expansion coefficient sheet-shaped base material 5 in the cross section f gradually increases as the direction of the direction increases. As the area ratio of the high thermal expansion coefficient sheet-shaped substrate 5 gradually increases, the thermal expansion coefficient of the ring 2 also gradually increases from the low thermal expansion coefficient to the high thermal expansion coefficient. The material of the low coefficient of thermal expansion sheet used here is CFRP (Carbon Fiber Reinforced Plas).
tics), and the coefficient of thermal expansion has a value of about 0.2 × 10 −6 / ° C. On the other hand, as a material for the high thermal expansion coefficient sheet, there is GFRP (Glass Fiber Reinforced Plastics), which has a thermal expansion coefficient of about 8 × 10 −6 / ° C.
【００１７】次に図２において、この発明の実施の形態
１における熱応力の発生状態を説明する。リング２の熱
膨張率が漸増するため、空力加熱を受けたとき、リング
２の熱膨張量は図中イのように漸増する。セラミックレ
ドーム１とリング２が重なる領域とその近傍では、熱膨
張量が同等となるため、熱応力エが低減される。リング
２と飛しょう体本体３が重なる部分とその近傍において
は、セラミックレドーム１の熱膨張量アと飛しょう体本
体３の熱膨張量ウの熱膨張量差に比べ、リング２の熱膨
張量イと飛しょう体本体３の熱膨張量ウの差は小さくな
っており、熱応力オも低減される。Next, referring to FIG. 2, the state of occurrence of thermal stress in the first embodiment of the present invention will be described. Since the coefficient of thermal expansion of the ring 2 gradually increases, the amount of thermal expansion of the ring 2 gradually increases as indicated by a in the figure when subjected to aerodynamic heating. The thermal expansion amount is reduced in the region where the ceramic radome 1 and the ring 2 overlap and in the vicinity thereof, so that the thermal stress d is reduced. In the portion where the ring 2 and the flying body 3 overlap and in the vicinity thereof, the thermal expansion amount of the ring 2 is larger than the thermal expansion amount of the ceramic radome 1 and the thermal expansion amount of the flying body 3. The difference between the thermal expansion amount c of the flying body 3 and that of the flying body 3 is small, and the thermal stress e is also reduced.
【００１８】ここで、リング２は炭素繊維やガラス繊維
を基材とする複合材料で成型し、金属材料より小さい熱
膨張率を有し、さらに炭素繊維を基材とする複合材料で
あれば、セラミックと同等の熱膨張率を有するものもあ
り、セラミックレドーム１と同等ないしは少し大きい熱
膨張率を有するものを使用する。Here, the ring 2 is made of a composite material having carbon fiber or glass fiber as a base material, has a coefficient of thermal expansion smaller than that of a metal material, and is a composite material having carbon fiber as a base material. Some ceramics have a coefficient of thermal expansion equivalent to that of ceramics, and one having a coefficient of thermal expansion equivalent to or slightly larger than that of the ceramic radome 1 is used.
【００１９】よって、超音速で飛しょうする飛しょう体
のレドームにおいて、リングを構成する低熱膨張率シー
ト状基材と高熱膨張率シート状基材の積層厚比を漸次変
化させることにより、リングの熱膨張率を漸次変化させ
セラミックレドームとリング間、リングと飛しょう体本
体間、リング自体に生じる熱応力を低減することができ
る。Therefore, in a radome of a flying object that flies at supersonic speed, by gradually changing the lamination thickness ratio of the low thermal expansion coefficient sheet-shaped base material and the high thermal expansion coefficient sheet-shaped base material forming the ring, By gradually changing the coefficient of thermal expansion, it is possible to reduce the thermal stress generated between the ceramic radome and the ring, between the ring and the flying body and between the ring itself.
【００２０】実施の形態２．図３を用いてこの発明に係
わる実施の形態２について説明する。図３はこの実施の
形態におけるリング２の構成を示す断面図であり、図に
おいて６は低熱膨張率繊維、７は高熱膨張率繊維であ
る。Embodiment 2. A second embodiment according to the present invention will be described with reference to FIG. FIG. 3 is a cross-sectional view showing the structure of the ring 2 in this embodiment, in which 6 is a low coefficient of thermal expansion fiber and 7 is a high coefficient of thermal expansion fiber.
【００２１】図３において、この発明の実施の形態３の
構成を説明する。図において、リング２はフィラメント
ワインディング法により基材が成形されている。軌跡ク
に従い低熱膨張率繊維６を巻き、途中で高熱膨張率繊維
７に繋ぎ替え軌跡ケに従い積層し、途中で再び低熱膨張
率繊維６に繋ぎ替え軌跡コに従い積層する。同様な工程
を繰り返し外周まで積層する。基材を積層するにあた
り、各層における低熱膨張率繊維６と高熱膨張率繊維７
の長さ比を漸次変化させ積層する。この積層構成のた
め、断面カにおける低熱膨張率繊維６と高熱膨張率繊維
７の面積比は、方向キに進むにつれ高熱膨張率繊維７が
漸増する。高熱膨張率繊維７の面積比が漸増するに従
い、リング２の熱膨張率も低熱膨張率から高熱膨張率へ
漸増する。ここで使用する低熱膨張率繊維６と高熱膨張
率繊維７の材料および熱膨張率は実施の形態１で使用の
低熱膨張率シートおよび高熱膨張率シートで使用のもの
と同じものである。The configuration of the third embodiment of the present invention will be described with reference to FIG. In the figure, the ring 2 has a base material formed by a filament winding method. The low thermal expansion coefficient fiber 6 is wound in accordance with the locus C, laminated along the high thermal expansion coefficient fiber 7 according to the reconnection trajectory K in the middle, and again laminated along the low thermal expansion coefficient fiber 6 according to the reconnection trajectory U in the middle. The same process is repeated to stack up to the outer periphery. When laminating the base material, the low thermal expansion coefficient fiber 6 and the high thermal expansion coefficient fiber 7 in each layer
The length ratio is gradually changed and the layers are laminated. Due to this laminated structure, the area ratio of the low thermal expansion coefficient fiber 6 to the high thermal expansion coefficient fiber 7 in the cross-section F gradually increases as the direction of the direction increases. As the area ratio of the high thermal expansion coefficient fibers 7 gradually increases, the thermal expansion coefficient of the ring 2 also gradually increases from the low thermal expansion coefficient to the high thermal expansion coefficient. The materials and the coefficients of thermal expansion of the low thermal expansion coefficient fiber 6 and the high thermal expansion coefficient fiber 7 used here are the same as those used in the low thermal expansion coefficient sheet and the high thermal expansion coefficient sheet used in the first embodiment.
【００２２】セラミックレドーム１、リング２、飛しょ
う体本体３に生じる熱応力が低減される説明は実施の形
態１と同じである。The explanation for reducing the thermal stress generated in the ceramic radome 1, the ring 2, and the flying body 3 is the same as in the first embodiment.
【００２３】さらに、リング２の炭素繊維やガラス繊維
を基材とする複合材料で成型し、熱膨張率のセラミック
レドーム１や飛しょう体本体３との関係は、実施の形態
１と同じである。Furthermore, the relationship between the ring 2 and the ceramic radome 1 or the flying body 3 which is formed of a composite material having carbon fiber or glass fiber as a base material and has a coefficient of thermal expansion is the same as that of the first embodiment. .
【００２４】以上によれば、超音速で飛しょうする飛し
ょう体のレドームにおいて、リングを構成する低熱膨張
率繊維と高熱膨張率繊維の積層厚比を漸次変化させるこ
とにより、リングの熱膨張率を漸次変化させセラミック
レドームとリング間、リングと飛しょう体本体間、リン
グ自体に生じる熱応力を低減することができる。According to the above, in the radome of a flying object flying at supersonic speed, the thermal expansion coefficient of the ring is gradually changed by gradually changing the lamination thickness ratio of the low thermal expansion coefficient fiber and the high thermal expansion coefficient fiber constituting the ring. Can be gradually changed to reduce the thermal stress generated between the ceramic radome and the ring, between the ring and the flying body, and in the ring itself.
【００２５】実施の形態３．図４を用いてこの発明に係
わる実施の形態３について説明する。図４はこの実施の
形態におけるリング２の構成を示す断面図であり、図に
おいて６は低熱膨張率繊維、７は高熱膨張率繊維であ
る。Embodiment 3. A third embodiment according to the present invention will be described with reference to FIG. FIG. 4 is a cross-sectional view showing the structure of the ring 2 in this embodiment, in which 6 is a low coefficient of thermal expansion fiber and 7 is a high coefficient of thermal expansion fiber.
【００２６】図４において、この発明の実施の形態３の
構成を説明する。図において、リング２はレジントラン
スファーモールディング法により成形されている。基材
を織るあたり、低熱膨張率繊維６と高熱膨張率繊維７の
配合比を方向キに沿って漸次変化させ織込む。この積層
構成のため、断面カにおける低熱膨張率繊維６と高熱膨
張率繊維７の面積比は、方向キに進むにつれ高熱膨張率
繊維７が漸増する。高熱膨張率繊維７の面積比が漸増す
るに従い、リング２の熱膨張率も低熱膨張率から高熱膨
張率へ漸増する。ここで使用する低熱膨張率繊維６と高
熱膨張率繊維７の材料および熱膨張率は実施の形態２で
使用のものと同じものである。The configuration of the third embodiment of the present invention will be described with reference to FIG. In the figure, the ring 2 is formed by a resin transfer molding method. When weaving the base material, the blending ratio of the low thermal expansion coefficient fiber 6 and the high thermal expansion coefficient fiber 7 is gradually changed along the direction key and is woven. Due to this laminated structure, the area ratio of the low thermal expansion coefficient fiber 6 to the high thermal expansion coefficient fiber 7 in the cross-section F gradually increases as the direction of the direction increases. As the area ratio of the high thermal expansion coefficient fibers 7 gradually increases, the thermal expansion coefficient of the ring 2 also gradually increases from the low thermal expansion coefficient to the high thermal expansion coefficient. The materials and the coefficient of thermal expansion of the low thermal expansion coefficient fiber 6 and the high thermal expansion coefficient fiber 7 used here are the same as those used in the second embodiment.
【００２７】セラミックレドーム１、リング２、飛しょ
う体本体３に生じる熱応力が低減される説明は実施の形
態１と同じである。The explanation for reducing the thermal stress generated in the ceramic radome 1, the ring 2, and the flying body 3 is the same as in the first embodiment.
【００２８】さらに、リング２の炭素繊維やガラス繊維
を基材とする複合材料で成型し、熱膨張率のセラミック
レドーム１や飛しょう体本体３との関係は、実施の形態
１と同じである。Further, the relationship between the ring 2 and the ceramic radome 1 and the flying body 3 which are molded from a composite material having carbon fiber or glass fiber as a base material is the same as that of the first embodiment. .
【００２９】これにより、超音速で飛しょうする飛しょ
う体のレドームにおいて、リングを構成する低熱膨張率
繊維と高熱膨張率繊維の積層厚比を漸次変化させること
により、リングの熱膨張率を漸次変化させセラミックレ
ドームとリング間、リングと飛しょう体本体間、リング
自体に生じる熱応力を低減することができる。また基材
の織込みは、普通の布と同様の工程であるため、２種の
繊維の配向の変化は自由度は高く、また容易にできる。As a result, in the radome of a flying object flying at supersonic speed, the thermal expansion coefficient of the ring is gradually changed by gradually changing the laminated thickness ratio of the low thermal expansion coefficient fiber and the high thermal expansion coefficient fiber constituting the ring. It is possible to reduce the thermal stress generated between the ceramic radome and the ring, between the ring and the flying body, and in the ring itself. In addition, the weaving of the base material is a process similar to that of a normal cloth, so that the change of the orientations of the two kinds of fibers has a high degree of freedom and can be easily performed.
【００３０】[0030]
【発明の効果】この発明によれば、リングと飛しょう体
本体の間に生じる熱応力を低減する飛しょう体用レドー
ムが実現可能になる。According to the present invention, it is possible to realize a radome for a flying object that reduces the thermal stress generated between the ring and the flying object main body.
【図１】 この発明の実施の形態１を示す構成図であ
る。FIG. 1 is a configuration diagram showing a first embodiment of the present invention.
【図２】 この発明の実施の形態１を示す説明図であ
る。FIG. 2 is an explanatory diagram showing the first embodiment of the present invention.
【図３】 この発明の実施の形態２を示す構成図であ
る。FIG. 3 is a configuration diagram showing a second embodiment of the present invention.
【図４】 この発明の実施の形態３を示す構成図であ
る。FIG. 4 is a configuration diagram showing a third embodiment of the present invention.
【図５】 従来の飛しょう体用レドームを示す構成図で
ある。FIG. 5 is a configuration diagram showing a conventional radome for a flying vehicle.
【図６】 従来の飛しょう体用レドームの説明図であ
る。FIG. 6 is an explanatory diagram of a conventional radome for a flying object.
１ セラミックレドーム、 ２ リング、 ３ 飛しょ
う体本体、 ４ 低熱膨張率シート状基材、 ５ 高熱
膨張率シート状基材、 ６ 低熱膨張率繊維、７ 高熱
膨張率繊維1 ceramic radome, 2 ring, 3 flying body, 4 low thermal expansion coefficient sheet-like base material, 5 high thermal expansion coefficient sheet-like base material, 6 low thermal expansion coefficient fiber, 7 high thermal expansion coefficient fiber
フロントページの続き (72)発明者 尾崎 毅志 東京都千代田区丸の内二丁目２番３号 三 菱電機株式会社内 Ｆターム(参考） 5J046 AA13 RA01 RA07 RA08 Continued front page (72) Inventor Takeshi Ozaki 2-3 2-3 Marunouchi, Chiyoda-ku, Tokyo Inside Ryo Electric Co., Ltd. F-term (reference) 5J046 AA13 RA01 RA07 RA08
Claims (7)
れ、飛しょう体本体の先端に配置されるレドームと、前
記レドームの熱膨張率よりも高い熱膨張率を有する材料
で形成された前記飛しょう体本体と前記レドームとを結
合するリングとを具備した飛しょう体用レドームにおい
て、前記リングは、前記レドームに近似する熱膨張率を
有する複合材料で形成される第１のシート状基材と前記
飛しょう体本体と近似する熱膨張率を有する複合材料で
形成される第２のシート状基材とを有し、前記第１及び
第２のシート状基材は前記レドームと飛しょう体本体と
の間にあって、かつ前記第１、第２の基材の熱膨張率が
近似するレドーム及び飛しょう体本体側に配置され、さ
らに前記第１のシート状基材と前記第２のシート状基材
の積層厚比を漸次変化させることを特徴とする飛しょう
体用レドーム。1. A radome formed of a material having a predetermined coefficient of thermal expansion and arranged at the tip of a flying body main body, and a material having a coefficient of thermal expansion higher than that of the radome. A radome for a flying object, comprising a flying body and a ring connecting the radome, wherein the ring is a first sheet-like substrate formed of a composite material having a coefficient of thermal expansion similar to that of the radome. And a second sheet-like base material formed of a composite material having a thermal expansion coefficient similar to that of the flying body main body, wherein the first and second sheet-like base materials are the radome and the flying body. The first sheet-shaped base material and the second sheet-shaped material are arranged between the main body and the radome and the flying body main body side where the thermal expansion coefficients of the first and second base materials are similar to each other. Gradual change of laminated thickness ratio of base material A radome for a flying object characterized by:
れ、飛しょう体本体の先端に配置されるレドームと、前
記レドームの熱膨張率よりも高い熱膨張率を有する材料
で形成された前記飛しょう体本体と前記レドームとを結
合するリングとを具備した飛しょう体用レドームにおい
て、前記リングは、前記レドームに近似する熱膨張率を
有する複合材料で形成される第１の繊維と前記飛しょう
体本体と近似する熱膨張率を有する複合材料で形成され
る第２の繊維とを有し、前記第１及び第２の繊維は前記
レドームと飛しょう体本体との間にあって、かつ前記第
１、第２の繊維の熱膨張率が近似するレドーム及び飛し
ょう体本体側に配置され、さらに前記第１の繊維と前記
第２の繊維の積層厚比を漸次変化させることを特徴とす
る飛しょう体用レドーム。2. A radome formed of a material having a predetermined coefficient of thermal expansion and arranged at the tip of a flying body, and a material having a coefficient of thermal expansion higher than that of the radome. In a radome for a flying object, comprising a flying body and a ring connecting the radome, the ring comprises a first fiber formed of a composite material having a coefficient of thermal expansion similar to that of the radome, and the flying member. A second main body formed of a composite material having a thermal expansion coefficient similar to that of the main body, wherein the first and second fibers are located between the radome and the main body of the flying body, and The first and second fibers are arranged on the side of the radome and the flying body that have similar thermal expansion coefficients, and the laminated thickness ratio of the first fiber and the second fiber is gradually changed. Red body Mu.
れ、飛しょう体本体の先端に配置されるレドームと、前
記レドームの熱膨張率よりも高い熱膨張率を有する材料
で形成された前記飛しょう体本体と前記レドームとを結
合するリングとを具備した飛しょう体用レドームにおい
て、前記リングは、前記レドームに近似する熱膨張率を
有する複合材料で形成される第１の繊維と前記飛しょう
体本体と近似する熱膨張率を有する複合材料で形成され
る第２の繊維とを有し、前記第１及び第２の繊維は前記
レドームと飛しょう体本体との間にあって、かつ前記第
１、第２の繊維の熱膨張率が近似するレドーム及び飛し
ょう体本体側に配置され、さらに前記第１の繊維と前記
第２の繊維の配合比を漸次変化させることを特徴とする
飛しょう体用レドーム。3. A radome formed of a material having a predetermined coefficient of thermal expansion and arranged at the tip of a flying body, and a material having a coefficient of thermal expansion higher than that of the radome. In a radome for a flying object, comprising a flying body and a ring connecting the radome, the ring comprises a first fiber formed of a composite material having a coefficient of thermal expansion similar to that of the radome, and the flying member. A second main body formed of a composite material having a thermal expansion coefficient similar to that of the main body, wherein the first and second fibers are located between the radome and the main body of the flying body, and A flight characterized by arranging the first and second fibers on the side of the radome and the flying body which have similar thermal expansion coefficients, and gradually changing the compounding ratio of the first fiber and the second fiber. Body radome .
を使用することを特徴とする請求項１〜請求項３記載の
飛しょう体用レドーム。4. The radome for a flying object according to claim 1, wherein ceramic is used as a material for the radome.
繊維の材料として、低熱膨張率の材料と、前記第２のシ
ート状基材及び前記第２の繊維の材料として、高熱膨張
率の材料とを使用することを特徴とする請求項１〜請求
項４記載の飛しょう体用レドーム。5. A material having a low coefficient of thermal expansion as a material for the first sheet-shaped substrate and the first fiber, and a material having a high thermal expansion as a material for the second sheet-shaped substrate and the second fiber. A radome for a flying object according to any one of claims 1 to 4, characterized by using a material having a specific ratio.
を基材とした複合材料製からなることを特徴とする請求
項５記載の飛しょう体用レドーム。6. The radome for a flying object according to claim 5, wherein the material having a low coefficient of thermal expansion is made of a composite material having carbon fiber as a base material.
維を基材とした複合材料製からなることを特徴とする請
求項５記載の飛しょう体用レドーム。7. The radome for a flying object according to claim 5, wherein the material having a high coefficient of thermal expansion is made of a composite material using glass fiber as a base material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2001202032A JP3899858B2 (en) | 2001-07-03 | 2001-07-03 | Flying radome |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2001202032A JP3899858B2 (en) | 2001-07-03 | 2001-07-03 | Flying radome |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP2003021500A true JP2003021500A (en) | 2003-01-24 |
| JP3899858B2 JP3899858B2 (en) | 2007-03-28 |
Family
ID=19038905
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2001202032A Expired - Lifetime JP3899858B2 (en) | 2001-07-03 | 2001-07-03 | Flying radome |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010052270A (en) * | 2008-08-28 | 2010-03-11 | Mitsubishi Electric Corp | Structural member and radome |
| JP2011135223A (en) * | 2009-12-22 | 2011-07-07 | Kawasaki Heavy Ind Ltd | Radome for flying object |
| JP2012172868A (en) * | 2011-02-18 | 2012-09-10 | Mitsubishi Electric Corp | Missile and radome ring for the same |
| JP2016201640A (en) * | 2015-04-08 | 2016-12-01 | 三菱電機株式会社 | Flying object radome and method for manufacturing flying object radome |
| JP2017501376A (en) * | 2013-10-17 | 2017-01-12 | ローベルト ボッシュ ゲゼルシャフト ミット ベシュレンクテル ハフツング | Covers for automotive radar sensors |
| JP2019184105A (en) * | 2018-04-05 | 2019-10-24 | 三菱電機株式会社 | Radome for flying object |
-
2001
- 2001-07-03 JP JP2001202032A patent/JP3899858B2/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010052270A (en) * | 2008-08-28 | 2010-03-11 | Mitsubishi Electric Corp | Structural member and radome |
| JP2011135223A (en) * | 2009-12-22 | 2011-07-07 | Kawasaki Heavy Ind Ltd | Radome for flying object |
| JP2012172868A (en) * | 2011-02-18 | 2012-09-10 | Mitsubishi Electric Corp | Missile and radome ring for the same |
| JP2017501376A (en) * | 2013-10-17 | 2017-01-12 | ローベルト ボッシュ ゲゼルシャフト ミット ベシュレンクテル ハフツング | Covers for automotive radar sensors |
| US10381718B2 (en) | 2013-10-17 | 2019-08-13 | Robert Bosch Gmbh | Cover for a radar sensor for motor vehicles |
| US10629984B2 (en) | 2013-10-17 | 2020-04-21 | Robert Bosch Gmbh | Cover for a radar sensor for motor vehicles |
| JP2016201640A (en) * | 2015-04-08 | 2016-12-01 | 三菱電機株式会社 | Flying object radome and method for manufacturing flying object radome |
| JP2019184105A (en) * | 2018-04-05 | 2019-10-24 | 三菱電機株式会社 | Radome for flying object |
Also Published As
| Publication number | Publication date |
|---|---|
| JP3899858B2 (en) | 2007-03-28 |
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