JPS6071585A - Rocket propellant - Google Patents

Rocket propellant

Info

Publication number
JPS6071585A
JPS6071585A JP17554983A JP17554983A JPS6071585A JP S6071585 A JPS6071585 A JP S6071585A JP 17554983 A JP17554983 A JP 17554983A JP 17554983 A JP17554983 A JP 17554983A JP S6071585 A JPS6071585 A JP S6071585A
Authority
JP
Japan
Prior art keywords
fuel
rocket
combustion chamber
pressure air
propellant
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
Application number
JP17554983A
Other languages
Japanese (ja)
Inventor
覚 鈴木
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to JP17554983A priority Critical patent/JPS6071585A/en
Priority to DE19843412450 priority patent/DE3412450A1/en
Priority to GB08408437A priority patent/GB2147052A/en
Priority to FR8406105A priority patent/FR2552422A1/en
Publication of JPS6071585A publication Critical patent/JPS6071585A/en
Pending legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/425—Propellants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers

Abstract

(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

【発明の詳細な説明】 本発明はロケットの推進剤に関するものである。[Detailed description of the invention] The present invention relates to rocket propellants.

ジェットエンジンは、燃料の燃焼に空気中の酸紫を補給
して推進している。そして、この空気は燃＄＝１の気化
を促進し、かつ圧縮された空気の反発力を利用して推進
力を得ている。ところで、ロケット幻空気のない宇宙空
間を飛行するものであるため、その推進剤として燃料と
、この燃料を燃焼するための酸化剤とを搭載している。Jet engines propel themselves by burning fuel and supplementing it with acid purple in the air. This air promotes the vaporization of $1 of fuel, and uses the repulsive force of the compressed air to obtain propulsive force. By the way, since rockets fly in space without air, they carry fuel as a propellant and an oxidizer to burn this fuel.

本発明の目的は、燃料と酸化剤との他に推進剤としての
高圧空気を北載し、この高圧空気を燃焼室内へ噴出して
燃料の気化作用と噴出力を利用して推進力を高めること
ができるようにすることによシ、ロケットの推進力を増
加、向上し得るようにしたロケットの推進剤を提供する
ことにある。The purpose of the present invention is to carry high-pressure air as a propellant in addition to fuel and oxidizer, and to eject this high-pressure air into a combustion chamber to increase propulsive force by utilizing the vaporization effect and ejection force of the fuel. The object of the present invention is to provide a rocket propellant that can increase and improve the propulsive force of a rocket.

以下本発明の一実施例を図面に基づいて詳細に説明する
。An embodiment of the present invention will be described in detail below based on the drawings.

図面はロケットに推進剤を搭載した概略図を示しており
、ｌはロケットの外殻体、２は下端に噴射ノズル２ａを
有する燃焼室である。３は燃料タンクで、燃焼室２へ配
管３ａで接続されている。The drawing shows a schematic view of a rocket loaded with propellant, where l is the outer shell of the rocket, and 2 is a combustion chamber having an injection nozzle 2a at its lower end. 3 is a fuel tank, which is connected to the combustion chamber 2 through a pipe 3a.

４は酸化剤タンクであって、配管４ａで燃焼室２へ接続
されている。なお、上記配管３ａ、４ａには流量調節バ
ルブが設けであるがヒ１では省略しである。一方、５は
同圧空気タンクで、このタンク５内の高圧空気は配管５
ａを介して上記燃（、ｌｊｃ室２へ直接接続してあり、
配管５ａに傅１圧ト）季シ、の吹出し圧力をコントロー
ルする制御バルブ６を備えている。4 is an oxidizer tank, which is connected to the combustion chamber 2 through a pipe 4a. Note that although the pipes 3a and 4a are provided with flow rate regulating valves, they are omitted in H1. On the other hand, 5 is the same pressure air tank, and the high pressure air in this tank 5 is supplied to the pipe 5.
directly connected to the combustion chamber 2 via a,
The piping 5a is equipped with a control valve 6 for controlling the blowout pressure.

上記のように構成したことによシ、燃焼室２内ヘ噴出し
た燃料タンク３内の燃料はド′化剤タンク４からの酸化
剤によシ燃焼してノズル２ａかう噴射し、ロケットの推
進力となる。しかして本発明にあっては燃焼室２内へ高
圧空気タンク５からの高圧空気が噴出される。この高圧
空気の噴出により燃焼室２内へ噴出した燃料の気化作用
が得られるので、より完全な燃焼が行なえると共に高圧
空気の噴出力によりロケットの推進力を高めることがで
きる。尚、２５気圧の高圧空気タンクで３０分程度の噴
出力を保持し得る。With the above configuration, the fuel in the fuel tank 3 that has been injected into the combustion chamber 2 is combusted by the oxidizing agent from the deoxidizing agent tank 4 and is injected through the nozzle 2a to propel the rocket. It becomes power. According to the present invention, high-pressure air from the high-pressure air tank 5 is blown into the combustion chamber 2. This ejection of high-pressure air provides a vaporization effect on the fuel ejected into the combustion chamber 2, so that more complete combustion can be achieved and the propulsive force of the rocket can be increased by the ejection force of the high-pressure air. Incidentally, a high-pressure air tank of 25 atmospheres can maintain the ejection force for about 30 minutes.

以上説明したように本発明によれば、推進剤としての燃
料と、この燃料を燃焼室内で燃焼させるノこめの酸化剤
とを有するロケットの推進剤において、上記燃料と酸化
剤との他に推進剤となる高圧空気を備え、この高圧空気
を燃焼室内へ噴出するようにしたので、燃焼室内へ噴出
する燃料の気化作用がイ１↑られてより完全な燃焼が行
なわれると共に、高圧空気の噴出力をロケットの推進力
として利用することができ、これにょシ推進力の向上を
８することかできるので、必ｉｓ　ｈ推進力を得るため
に燃料の燃焼量を太きぐするような従来の推進手段が不
要と々る上、燃料や酸化剤の搭載量を大幅に低減し、か
つロケットの軽量化と低コスト化をｂ」ることかできる
々どの効果がある・As explained above, according to the present invention, in a rocket propellant having fuel as a propellant and an oxidizing agent for burning this fuel in a combustion chamber, in addition to the above fuel and oxidizing agent, This high-pressure air is injected into the combustion chamber, so that the vaporization effect of the fuel injected into the combustion chamber is increased, resulting in more complete combustion, and the ejection of high-pressure air is The power can be used as the propulsion force of a rocket, and this can improve the propulsion force by 8 times, so it is necessary to increase the amount of fuel burned to obtain the propulsion force, compared to conventional propulsion. Not only does it not require any additional means, it also significantly reduces the amount of fuel and oxidizer carried, and it also has the effect of reducing the weight and cost of the rocket.

【図面の簡単な説明】[Brief explanation of the drawing]

図面は本発明の一実施例を示すロケットの概略図である
。 ２・・・燃焼量、３・・・燃料タンク、４・・・酸化剤
タンク、５・・・高圧空気タンク。 ２αThe drawing is a schematic diagram of a rocket showing an embodiment of the present invention. 2... Burning amount, 3... Fuel tank, 4... Oxidizer tank, 5... High pressure air tank. 2α

Claims (1)

【特許請求の範囲】[Claims] 推進剤としての燃料と、この燃料を燃焼室内で酸化燃焼
させるための酸化剤とを有するロケットの推進剤におい
て、上記燃料と酸化剤との他に推進剤となる高圧空気を
備え、この高圧空気は上記燃焼室内へ噴出して燃料の気
化作用と推進力として用いることを特徴とするロケット
の推進剤。A rocket propellant that has a fuel as a propellant and an oxidizing agent for oxidizing and burning this fuel in a combustion chamber includes high-pressure air as a propellant in addition to the fuel and oxidizing agent, and this high-pressure air is a propellant for a rocket, which is ejected into the combustion chamber and used for vaporization of fuel and propulsive force.
JP17554983A 1983-09-22 1983-09-22 Rocket propellant Pending JPS6071585A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
JP17554983A JPS6071585A (en) 1983-09-22 1983-09-22 Rocket propellant
DE19843412450 DE3412450A1 (en) 1983-09-22 1984-03-30 FUEL FOR A ROCKET ENGINE AND ROCKET ENGINE
GB08408437A GB2147052A (en) 1983-09-22 1984-04-02 Additional propellant for rocket
FR8406105A FR2552422A1 (en) 1983-09-22 1984-04-18 PROPULSIVE AGENT FOR ROCKET ENGINES

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP17554983A JPS6071585A (en) 1983-09-22 1983-09-22 Rocket propellant

Publications (1)

Publication Number Publication Date
JPS6071585A true JPS6071585A (en) 1985-04-23

Family

ID=15998018

Family Applications (1)

Application Number Title Priority Date Filing Date
JP17554983A Pending JPS6071585A (en) 1983-09-22 1983-09-22 Rocket propellant

Country Status (4)

Country Link
JP (1) JPS6071585A (en)
DE (1) DE3412450A1 (en)
FR (1) FR2552422A1 (en)
GB (1) GB2147052A (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4437524C2 (en) * 1994-10-20 1997-04-24 Kunkel Klaus Dr Ing Method for operating a missile propulsion system and missile propulsion
DE4439073C1 (en) * 1994-11-02 1996-05-15 Kunkel Klaus Dr Ing Discus-shaped missile with a jet engine and a rocket engine arrangement
RU2451199C1 (en) * 2011-05-24 2012-05-20 Открытое акционерное общество "Конструкторское бюро химавтоматики" Liquid-propellant rocket engine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE467726A (en) *
FR615352A (en) * 1925-09-25 1927-01-06 Improvement in power supply processes for automotive torpedo engines
US2962934A (en) * 1955-06-13 1960-12-06 Garrett Corp Vehicle propulsion apparatus
FR1270683A (en) * 1960-07-22 1961-09-01 New combustion engine

Also Published As

Publication number Publication date
GB8408437D0 (en) 1984-05-10
GB2147052A (en) 1985-05-01
FR2552422A1 (en) 1985-03-29
DE3412450A1 (en) 1985-04-04

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