JP4458418B2 - Ram Rocket - Google Patents

Ram Rocket Download PDF

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JP4458418B2
JP4458418B2 JP2004175033A JP2004175033A JP4458418B2 JP 4458418 B2 JP4458418 B2 JP 4458418B2 JP 2004175033 A JP2004175033 A JP 2004175033A JP 2004175033 A JP2004175033 A JP 2004175033A JP 4458418 B2 JP4458418 B2 JP 4458418B2
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generating agent
gas generating
ram
combustion
chamber
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JP2005351230A (en
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春雄 清水
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IHI Aerospace Co Ltd
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Description

本発明は、飛翔体の飛翔推力を得るのに利用されるラムロケット（ラムジェットと称することもある。）に関するものである。   The present invention relates to a ram rocket (also referred to as a ramjet) used for obtaining a flight thrust of a flying object.

従来、上記したラムロケットとしては、例えば、ラム燃焼室と、このラム燃焼室の前方に位置するガス発生器と、ラム燃焼室の先端部に接続するディフューザと、ラム燃焼室の後端に設けたノズルを備えたものがある。ガス発生器は、ガス発生剤をチャンバ内に充填して成っており、ラム燃焼時には、上記ガス発生剤を燃焼させた際の熱分解で生じる可燃性ガスをラム燃焼室に供給するようになっている。   Conventionally, as the above-mentioned ram rocket, for example, a ram combustion chamber, a gas generator positioned in front of the ram combustion chamber, a diffuser connected to the tip of the ram combustion chamber, and a rear end of the ram combustion chamber are provided. Some are equipped with a nozzle. The gas generator is configured by filling the chamber with a gas generating agent, and at the time of ram combustion, combustible gas generated by thermal decomposition when the gas generating agent is burned is supplied to the ram combustion chamber. ing.

このラムロケットは、ラム燃焼時において、ディフューザのインレットから流入する空気をラム圧により圧縮した状態でラム燃焼室に導入し、この圧縮された空気とガス発生器から供給される可燃性ガスとを混合して連続燃焼させ、高温の燃焼ガスをノズルから後方に向けて飛翔速度以上の速度で噴出させることにより、飛翔推力を得るようにしている。上記ガス発生器のガス発生剤には、ラム燃焼初期の着火性を向上させるべく金属添加物としてのジルコニウムを含んだ組成のものを使用している。
特開平５−３４０３０７号公報 During ram combustion, this ram rocket introduces air flowing from the diffuser inlet into the ram combustion chamber in a state compressed by ram pressure, and the compressed air and combustible gas supplied from a gas generator are used. The mixture is continuously burned, and high-temperature combustion gas is ejected backward from the nozzle at a speed equal to or higher than the flight speed to obtain a flight thrust. As the gas generating agent of the gas generator, a composition containing zirconium as a metal additive is used in order to improve the ignitability at the initial stage of ram combustion.
JP-A-5-340307

ところが、上記した従来のラムロケットでは、ガス発生器のチャンバ内に充填したガス発生剤が、ラム燃焼初期の着火性を重視するために金属添加物としてジルコニウムを含んだ組成としてあることから、推進性能を必ずしも重視しているとは言えないのに加えて、輝炎（ノズルから噴出する炎）が明るくなって、遠方からでも容易に認識されてしまうという問題を有しており、これらの問題を解決することが従来の課題となっていた。   However, in the above-described conventional ram rocket, the gas generating agent filled in the chamber of the gas generator has a composition containing zirconium as a metal additive in order to place importance on the ignitability at the initial stage of ram combustion. In addition to the fact that performance is not always emphasized, there is a problem that the bright flame (flame ejected from the nozzle) becomes bright and easily recognized even from a distance. It has been a conventional problem to solve the problem.

本発明は、上述した従来の課題に着目してなされたものであって、ラム燃焼初期の着火性を良好に保ちつつ、ラム燃焼中には高飛翔推力を得ることが可能であり、しかも、認識され難い、すなわち、低視認性に優れたラムロケットを提供することを目的としている。   The present invention has been made by paying attention to the above-described conventional problems, and it is possible to obtain a high flight thrust during ram combustion while maintaining good ignitability at the initial stage of ram combustion, An object of the present invention is to provide a ram rocket that is difficult to recognize, that is, excellent in low visibility.

本発明は、ラム燃焼室と、チャンバ内にガス発生剤を充填してラム燃焼時には上記ガス発生剤を燃焼させて生じる可燃性ガスを上記ラム燃焼室に供給するガス発生器を備えたラムロケットにおいて、上記ガス発生器のガス発生剤が、推進性能及び低視認性を重視した組成の主ガス発生剤と、着火性を重視した組成の副ガス発生剤であって、チャンバ内において主ガス発生剤を端面燃焼式に充填すると共に、主ガス発生剤の機軸方向にわたって副ガス発生剤を設けて、この主ガス発生剤の初期燃焼面としての端面の少なくとも一部に副ガス発生剤を配置した構成としたことを特徴としており、このラムロケットの構成を前述した従来の課題を解決するための手段としている。 The present invention relates to a ram combustion chamber, and a ram rocket including a gas generator that fills the chamber with a gas generating agent and supplies combustible gas generated by burning the gas generating agent during ram combustion to the ram combustion chamber. in the gas generating agent of the gas generator, propulsion performance and the main gas generating agent having a composition with an emphasis on low visibility, a secondary gas generating agent composition with an emphasis on wearing fire resistance, mainly in the chamber gas In addition to filling the generating agent in an end face combustion type, a secondary gas generating agent is provided over the axial direction of the main gas generating agent, and the secondary gas generating agent is disposed on at least a part of the end face as the initial combustion surface of the main gas generating agent. The configuration of the ram rocket is used as a means for solving the above-described conventional problems.

本発明のラムロケットでは、上記した構成としているので、ラム燃焼初期の着火性が良好であるのは勿論のこと、ラム燃焼中における推進性能及び低視認性の向上をも実現することが可能であると共に、ラム燃焼中の着火性及び低視認性の双方を維持することができるという非常に優れた効果がもたらされ、また、例えば、ラム燃焼室に充填したブースタ推進薬の燃焼によりラム燃焼時に至るまでの飛翔推力を得る場合には、ラム燃焼室内に着火源を設ける必要がない分だけブースタ推進薬の充填量を多くすることができると共に、ラム燃焼室の構造の複雑化を避けることが可能であるという非常に優れた効果がもたらされる。 Since the ram rocket of the present invention has the above-described configuration, it is possible to improve the propulsion performance and low visibility during ram combustion as well as good ignitability at the initial stage of ram combustion. In addition, there is an excellent effect that both ignitability and low visibility during ram combustion can be maintained , and ram combustion is achieved by, for example, combustion of a booster propellant filled in the ram combustion chamber. When obtaining flight thrust up to time, it is possible to increase the amount of booster propellant charged as much as it is not necessary to provide an ignition source in the ram combustion chamber, and to avoid complication of the structure of the ram combustion chamber It has a very good effect that it is possible.

本発明のラムロケットにおいて、主ガス発生剤には、例えば、ＧＡＰ（グリシジルアジ化ポリマー）を主成分としてカーボンを含有させたものを用いることができ、一方、副ガス発生剤には、例えば、主ガス発生剤と同じくＧＡＰを主成分として金属添加物を含有させたものを用いることができる。この際、金属添加物として、ジルコニウム又はマグナリウムを用いることが望ましい。 In the ram rocket of the present invention, as the main gas generating agent, for example, a gas containing GAP ( glycidyl azide polymer) as a main component and containing carbon can be used, while the auxiliary gas generating agent includes, for example, Similar to the main gas generating agent, those containing GAP as a main component and containing a metal additive can be used. At this time, it is desirable to use zirconium or magnalium as the metal additive.

さらに、本発明のラムロケットにおいては、副ガス発生剤を円柱状に配置する構成や、副ガス発生剤を円筒状に配置する構成を採用することができ、このような構成を採用すれば、ラム燃焼中の着火性及び低視認性の双方を維持することができる。 Further, in the ram rocket present invention, a configuration in which the auxiliary gas generating agent disposed in the cylindrical, it is possible to employ a configuration to place a secondary gas generating agent in a cylindrical shape, by employing such a configuration, Both ignitability and low visibility during ram combustion can be maintained.

以下、本発明を図面に基づいて説明するが、本発明は以下の実施例に限定されるものではない。   Hereinafter, the present invention will be described with reference to the drawings, but the present invention is not limited to the following examples.

図１は本発明に係わるラムロケットの参考例を示しており、図１に示すように、このラムロケット１は、ラム燃焼室２と、このラム燃焼室２の前方（図示左方）に位置するガス発生器３と、ラム燃焼室２の先端部に接続するディフューザ４と、ラム燃焼室２の後端に設けたノズル５を備えている。 FIG. 1 shows a reference example of a ram rocket according to the present invention. As shown in FIG. 1, the ram rocket 1 is located in a ram combustion chamber 2 and in front of the ram combustion chamber 2 (left side in the figure). A gas generator 3, a diffuser 4 connected to the tip of the ram combustion chamber 2, and a nozzle 5 provided at the rear end of the ram combustion chamber 2.

ガス発生器３は、ガス発生剤６をチャンバ７内に充填して成っており、ラム燃焼時には、ガス発生剤６の熱分解で生じる可燃性ガスを噴射器３ａを介してラム燃焼室２に供給するようになっている。   The gas generator 3 is configured by filling the gas generating agent 6 in the chamber 7, and at the time of ram combustion, combustible gas generated by thermal decomposition of the gas generating agent 6 is supplied to the ram combustion chamber 2 via the injector 3a. It comes to supply.

この場合、ガス発生器３のガス発生剤６は、推進性能及び低視認性を重視した組成、すなわち、ＧＡＰ（グリシジルアジ化ポリマー）を主成分としてカーボンを含有させた組成の主ガス発生剤６Ａと、着火性を重視した組成、すなわち、ＧＡＰを主成分として金属添加物を含有させた組成の副ガス発生剤６Ｂとから構成してあり、副ガス発生剤６Ｂは、チャンバ７内において端面燃焼式に充填した主ガス発生剤６Ａの初期燃焼面としての端面６ａを覆うようにして配置してある。 In this case, the gas generating agent 6 of the gas generator 3 has a composition in which propulsion performance and low visibility are emphasized, that is, a main gas generating agent 6A having a composition containing GAP ( glycidyl azide polymer) as a main component and carbon. And an auxiliary gas generating agent 6B having a composition that places importance on ignitability, that is, a composition containing GAP as a main component and containing a metal additive, and the auxiliary gas generating agent 6B is end face combustion in the chamber 7 It arrange | positions so that the end surface 6a as an initial stage combustion surface of the main gas generating agent 6A with which it filled with the type | formula may be covered.

このラムロケット１では、ラム燃焼に必要な飛翔速度を得た段階において、細線矢印に示すように、ディフューザ４のインレット４ａから流入する空気をラム圧により圧縮した状態でポート２ａを通してラム燃焼室２に導入し、この圧縮された空気とガス発生器３から噴射器３ａを介して白抜き矢印に示すようにして供給される可燃性ガスとを混合して連続燃焼させ、高温の燃焼ガスをノズル５から後方に向けて飛翔速度以上の速度で噴出させることにより、飛翔推力を得るようにしている。   In the ram rocket 1, when the flight speed necessary for ram combustion is obtained, the ram combustion chamber 2 passes through the port 2 a in a state where the air flowing from the inlet 4 a of the diffuser 4 is compressed by the ram pressure as indicated by the thin line arrows. The compressed air and the combustible gas supplied from the gas generator 3 through the injector 3a through the injector 3a are mixed and continuously burned, and the high-temperature combustion gas is injected into the nozzle. Flying thrust is obtained by ejecting from 5 toward the rear at a speed higher than the flying speed.

このラムロケット１において、着火性を重視した組成の副ガス発生剤６Ｂが、チャンバ７内において端面燃焼式に充填した主ガス発生剤６Ａの初期燃焼面としての端面６ａを覆うようにして配置してあるので、ラム燃焼初期の段階でガス発生剤６の着火が確実に成され、その結果、ガス発生剤６の熱分解で生じる可燃性ガスがラム燃焼室２に確実に供給されることとなる。   In this ram rocket 1, the auxiliary gas generating agent 6B having a composition that emphasizes ignitability is disposed so as to cover the end face 6a as the initial combustion surface of the main gas generating agent 6A filled in the end face combustion type in the chamber 7. Therefore, the ignition of the gas generating agent 6 is surely performed at the initial stage of the ram combustion, and as a result, the combustible gas generated by the thermal decomposition of the gas generating agent 6 is reliably supplied to the ram combustion chamber 2. Become.

そして、ラム燃焼中は、副ガス発生剤６Ｂの燃焼が既に終了していて、ガス発生器３では、端面燃焼式に充填した主ガス発生剤６Ａの端面６ａが徐々に熱分解するので、認識され難い状態で高飛翔推力が継続して得られることとなる。   During the ram combustion, the combustion of the auxiliary gas generating agent 6B has already ended, and in the gas generator 3, the end face 6a of the main gas generating agent 6A filled in the end face combustion type is gradually pyrolyzed. High flight thrust will be continuously obtained in a state where it is difficult to do.

上記した参考例では、チャンバ７内において主ガス発生剤６Ａを端面燃焼式に充填すると共に、主ガス発生剤６Ａの端面６ａを覆うようにして副ガス発生剤６Ｂを配置する場合を例に挙げて説明したが、本発明に係わるラムロケットの実施例では、図２に一点鎖線で示すように、主ガス発生剤６Ａの機軸方向にわたって副ガス発生剤６Ｂを円柱状に配置したり、図２に二点鎖線で示すように、主ガス発生剤６Ａの機軸方向にわたって副ガス発生剤６Ｂを円筒状に配置する。 In the reference example described above, the case where the main gas generating agent 6A is filled in the end face combustion type in the chamber 7 and the auxiliary gas generating agent 6B is disposed so as to cover the end face 6a of the main gas generating agent 6A is taken as an example. However , in the embodiment of the ram rocket according to the present invention, as shown by a one-dot chain line in FIG. 2, the auxiliary gas generating agent 6B is arranged in a columnar shape over the axial direction of the main gas generating agent 6A . As shown by a two-dot chain line, the secondary gas generating agent 6B is arranged in a cylindrical shape over the axial direction of the main gas generating agent 6A .

本発明のラムロケットの参考例を示す軸心に沿う方向の断面説明図である。 It is sectional explanatory drawing of the direction in alignment with the axial center which shows the reference example of the ram rocket of this invention . 本発明のラムロケットの一実施例を示す軸心に沿う方向の断面説明図である。 It is sectional explanatory drawing of the direction in alignment with the axial center which shows one Example of the ram rocket of this invention .

符号の説明Explanation of symbols

１ ラムロケット
２ ラム燃焼室
３ ガス発生器
６Ａ（６）主ガス発生剤（ガス発生剤）
６Ｂ（６）副ガス発生剤（ガス発生剤）
６ａ 初期燃焼面としての端面
７ チャンバ 1 Ram Rocket 2 Ram Combustion Chamber 3 Gas Generator 6A (6) Main Gas Generating Agent (Gas Generating Agent)
6B (6) Sub-gas generating agent (gas generating agent)
6a End face as initial combustion face 7 Chamber

Claims (5)

ラム燃焼室と、チャンバ内にガス発生剤を充填してラム燃焼時には上記ガス発生剤を燃焼させて生じる可燃性ガスを上記ラム燃焼室に供給するガス発生器を備えたラムロケットにおいて、上記ガス発生器のガス発生剤が、推進性能及び低視認性を重視した組成の主ガス発生剤と、着火性を重視した組成の副ガス発生剤であって、チャンバ内において主ガス発生剤を端面燃焼式に充填すると共に、主ガス発生剤の機軸方向にわたって副ガス発生剤を設けて、この主ガス発生剤の初期燃焼面としての端面の少なくとも一部に副ガス発生剤を配置したことを特徴とするラムロケット。 In a ram rocket having a ram combustion chamber and a gas generator for supplying the ram combustion chamber with a combustible gas generated by filling the chamber with a gas generating agent and burning the gas generating agent during ram combustion. end face generator gas generating agent, and the main gas generating agent composition with an emphasis on propulsion performance and low visibility, a secondary gas generating agent composition with an emphasis on wearing fire resistance, the main gas generating agent in the chamber In addition to filling in the combustion type, a secondary gas generating agent is provided over the axial direction of the main gas generating agent, and the secondary gas generating agent is disposed on at least a part of the end face as an initial combustion surface of the main gas generating agent. A ram rocket. 副ガス発生剤が金属添加物を含んでいる請求項１に記載のラムロケット。   The ram rocket according to claim 1, wherein the auxiliary gas generating agent contains a metal additive. 金属添加物をジルコニウム又はマグナリウムとした請求項２に記載のラムロケット。   The ram rocket according to claim 2, wherein the metal additive is zirconium or magnalium. 副ガス発生剤を円柱状に配置した請求項１〜３のいずれか１項に記載のラムロケット。   The ram rocket according to any one of claims 1 to 3, wherein the auxiliary gas generating agent is arranged in a columnar shape. 副ガス発生剤を円筒状に配置した請求項１〜３のいずれか１項に記載のラムロケット。   The ram rocket according to any one of claims 1 to 3, wherein the auxiliary gas generating agent is arranged in a cylindrical shape.
JP2004175033A 2004-06-14 2004-06-14 Ram Rocket Expired - Fee Related JP4458418B2 (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112196692A (en) * 2020-10-14 2021-01-08 中国人民解放军国防科技大学 Electrode combustible thrust continuously adjustable riches fires automatically controlled solid ramjet

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114251191B (en) * 2021-12-22 2023-04-11 北京理工大学 Gas generator integrating flow regulation and mixing

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112196692A (en) * 2020-10-14 2021-01-08 中国人民解放军国防科技大学 Electrode combustible thrust continuously adjustable riches fires automatically controlled solid ramjet

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