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この報告は,ゼータ補強板の研究の近況を報告するにある.まずゼータ補強板の剛性とそのメカニズムを説明し,これによりゼータ補強板の形状最適化の方向を示す.またこれによって設計をおこなったモデルの試案を示す.また一般に,この種の新しい構造モデルの自動化製作のために設備した数値制御モデル製作装置について説明する., The purpose of this paper is to report the recent developments of the study of the zeta-stiffened panel. First, the mechanism of stiffening by a doublly corrugated plate is explained in some details and then, the guiding principle of optimizing the zeta-stiffened panel. The automation of fabricating the structural model of compicated configuration, such as this panel, by use of the NC machine is also discussed in the paper., 資料番号: SA0125858000

資料番号: SA0124455000

Many fundamental testings for the heat insulation coating of SSR were done in our laboratory. Some results of our testings are available in the actual rocket. This report describes also about some results of experimental research, which are not used in actual rocket. These tests were done by the torch-burner method. This report includes mainly about the test result of graphite inpregnated by silicone oil and of epoxy resin mixed with phenolic resin powder, which shows good ablation effect, though these are not used in the actual structure of SSR-Rocket., 資料番号: SA0124880000

グラファイトは固体ロケットモータのノズルとして使用されるが,その耐熱特性の改善のためにシリコーンオイルをグラファイトの試験片に真空槽で含浸させ,酸素-アセチレンバーナで試験片に吹付け,裏面温度を測定しその効果を検討したものである.浸透されたシリコーンオイルは加熱によってアブレーション効果でグラファイトの浸蝕と,内部への熱伝達を弱める.シリコーンオイルの含浸量は10～15%程度のわずかな量に対しても,試験片の温度上昇は含浸させないものに比較して約50～60%くらい低く,その効果が非常に大きい., Graphite is commonly used for the nozzle of rocket motors. To improve the heat-resisting characteristic of graphite, silicone oil is penetrayed into the graphite specimen in a vacuum vessel. As a basic test hot gas was blown by the torch burner on the face of the specimen and the temperature change on the back was measured. The heat-resisting characteristic of graphite is mainly due to its ablation effect. When silicone oil is penetrated graphite, the ablation effect increases remarkably, though the increase of weight is slight., 資料番号: SA4135103000

This paper presents an experimental evidence that the discontinuity of buckle pattern tessellation exists in the elastic postbuckling configuration of cylindrical shells of variable curvature. This raises the question on the validity of some assumptions generally prevail in analytical studies about the problem., 資料番号: SA2400797000

This report describes the details of the fundamental testing and the strength test of the actual recket body. The contents are a) Calculation of the bending strength and stiffness of the rocket body, b) Measurement of stress and stiffness of the bending of the rocket body, c) Strength of the motor cylinder and its forehead structure subjected by the internal pressure, d) Strength of the nose cone, e) Strength of the tail surfaces and its shraud. f) Calculation of the aeroelastic critical speed of the rocket body., 資料番号: SA0124877000

ロケットボディの外皮を空力加熱から守るために,しばしばアブレーション材料が用いられ,また,固型推薬ロケットエンジンのシリンダの内側にもこれらを用いることがある.アブレーションの一般理論は空気力学の理論および熱伝導理論の両者に亘る複雑なものであるが,われわれがここに提唱する積層箔の場合には問題をかなり簡単化することができる.それはこの場合,アブレーション材料の気化と固相における熱層の存在を無視できるからである.実験結果はここに示す簡単化した理論結果とかなり良い一致を示している., It is sometimes recommended to use the ablation materials for the outer skin of rocket body to protect the construction from the aerodynamic heating and also some ablation materials can be used as the heat insulation coating inside the cylinder wall of solid propellant rocket motors. General theory of ablation is very complicated, since it is the combination of the theories of both aerodynamics and heat conduction. However, in the case of laminated foil construction, which we propose in this papare, we can simplify considerably the problem, since the gasifying of the material and the existence of thermal layer in the solid phase of the material can be neglected. Test results by the torch burner method have shown a good agreement with the simplied theory shown in the report., 資料番号: SA4135007000

ロケットのエンジンやボディには,しばしば耐熱塗料が用いられる.このようなコーティングに対する要求としては,アブレーション効果のよいことと同時に,加熱中にも母材の金属などに対して接着性のよいことである.フェノール樹脂のあるものはよいアブレーション効果をもっている.しかし,フェノール樹脂をコーティングとして用いるときは熱処理が面倒であるし,金属への接着性もあまりよくないことがある.一方エポキシ樹脂はよい接着性をもっているが,アブレーション効果は前者ほどよくないことがある.このような見地から,接着性のよいエポキシ樹脂に適当な熱処理をほどこしたフェノール樹脂の粉末をまぜた.このような材料を薄いステンレス板に塗布してこれを試験片として用いた.塗布面はトーチ・バーナーで加熱する.実験結果はこのようにフェノール樹脂粉末を混入させたエポキシ樹脂がよい耐熱性のあることを示した.なおこの報告にはフェーノール樹脂自体の実験も付け加えている., Sometimes insulation coatings are used in the rocket engine or body. As the requirement of such insulation coating, the coating material must have good ablation effect and the coating must be surely bonded to the metal during the heating from the surface, some phenolic resin, have a good ablation effect, However, in the case when the phenolic resin is used as a coating the process of curing is troublesome and the bonding to the metal is not so good. On the other hand, some epoxy resins have a good bonding property, but its ablation effect is not better than some phenol resins. On such a point of view, the epoxy resin which has a good bonding property was mixed with the powder of the phenolic resin, which is crushed after proper curing. Such epoxy resin with the powder of phenolic resin was coated to the thin stainless steel which was used as a test specimen. The coated surface was heated by a torch. The result of experiment shows that the coating of the epoxy resin mixed with powder of phenol resin has a good heat-insulation effect., 資料番号: SA0124364000

The structure of the nozzle of the motor of SSR is shown in Fig. 2. Alalloy is capable to be replaced for the steel part in a common conventional design, owing to the good effect of insulator between the graphite of the throat and the Al-alloy casing. By replacement of material the nozzle structure reduces its weight to about 50% in comparison with the conventional design. Furthermore, we tested the new design in which we replaced the FRP for the Alalloy. By this new replacement of FRP the nozzle structure reduced its weight to 36% in comparison with the convention design. However in the actual flying test rocket the nozzle of former type is used to expedite the project instead of using the last type., 資料番号: SA0124876000

The small test rocket SSR, Which reached the altitude 25.8km in the latest flying test, is still possible to be improved from the structural point of view. From the results of the ground tests, the weight of some structual parts can be reduced and the reducible total weight is estimated about 30% of the total structural weight. It is shown that this weight reduction is also possible from the aeroelastic point of view. By this improvment, the increase of the maximum attainable altitude of SSR will be about 4. 7 km. Furthermore, this result is compared with the effects of aerodynamical improvement and of the improvement of the propellant., 資料番号: SA0124881000

Main principles of the structural design of SSR and its somewhat detailed points are already reported in other papers written by the authors. So in this paper we report about the details especially concerning with the end structures of the motor; for examples, the forehead and the nozzle structure. These details reported here are expected to serve for some data to structural designers of rockets., 資料番号: SA0124879000

Main requirements for a insulation coating inside the cylinder wall of solid propellant rocket motor are that it must have a) Good heat insulation effect, b) Good bonding to the cylinder wall, c) Easiness of painting operation. We used, as the insulator, epoxy resin, mixed with a polysulphide plastics and several kinds of metal oxides, which is reinforced by silicon glass cloths. As a fundamental test we take the torch burner method as shown in Fig. 1. From the result of such testings, we find the most favorable components in the insulator and its fundamental insulating properties. By these basic researches, we can estimate the insulating effect of the actual motor in advance and the results of the motor testing had a good agreement with the prediction from the fundamental testing., 資料番号: SA0124885000