JP2004218465A - Solid rocket - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a solid rocket capable of performing combustion control of a solid propellant. <P>SOLUTION: This solid rocket 1 is provided with a hollow combustion chamber 2 with a spherical outline; a solid propellant 9 positioned in the combustion chamber 2; a laser part 24 for irradiating the solid propellant 9 with laser L; a water injection part 50; a pressure sensor; and a control device 47. The pressure sensor measures pressure in the combustion chamber 2. The control device 47 controls the laser part 24 according to the pressure in the combustion chamber 2 measured by the pressure sensor. The control device 47 increases/decreases thrust by making the laser L strong/weak. The control device 47 makes the laser strong/weak to reduce fluctuation when the pressure in the combustion chamber 2 measured by the pressure sensor fluctuates. The control device 47 injects water toward the solid propellant 9 from an injection nozzle 52 of the water injection part 50 after irradiating the solid propellant 9 with the laser L of strength which causes a dynamic quenching phenomenon. <P>COPYRIGHT: (C)2004,JPO&NCIPI

Description

【０１１９】
【表２】

ここで、型式Ｂの燃焼室２には上記以外に、燃焼室２の北半球２ａに固体酸化剤５６などからなる補助燃料部５５が取り付けられている。
【０１２０】
次に、本発明の第２の実施形態にかかる固体燃料ロケット１を、図１６を参照して説明する。図１６に示された固体燃料ロケット１は、アウタケース１０を設けずに、燃焼室２全体に固体推進薬９を充填している。また、本実施形態では、前述した第１の実施形態と同様に、レーザＬを着火部７から固体推進薬９に照射することにより、前記固体推進薬９を燃焼させる。
【０１２１】
また、本実施形態では、前述した第１の実施形態と同様に、レーザＬを照射して固体推進薬９を着火するとともに、レーザＬを強弱することにより、燃焼ガスの発生量則ち推力を増減する。さらに、本実施形態では、固体推進薬９を自燃性の固体推進薬２２から構成しても良く、非自燃性の固体推進薬２１から構成しても良い。
【０１２２】
固体推進薬９を非自燃性の固体推進薬２１から構成すると、レーザＬの照射を止めて、固体推進薬９を消火する。さらに、本実施形態でも、圧力センサ４６が測定した燃焼室２内の圧力が変動すると、この圧力の変動が減少するようにレーザ部２４にレーザＬの強度を強弱させる。
【０１２３】
本実施形態によれば、前述した第１の実施形態と同様に、非自燃性の固体推進薬９の場合、点火・燃焼及び消火を複数回行うことができ、取り扱いが容易で複数回噴射できる固体燃料ロケット１を得ることができる。
【０１２４】
さらに、本発明では、レーザＬの光源として、半導体レーザ３３の他にＮｄ：ＹＡＧレーザやガラスレーザ等の高出力固体レーザを利用することもできる。
【０１２５】
【発明の効果】
以上説明したように、請求項１に記載の本発明によれば、固体推進薬にレーザを照射することにより固体推進薬を点火するようになっており、固体推進薬がレーザの照射を止めても燃焼を継続する自燃性となっている。また、燃焼室内の圧力を測定する測定手段を備え、この測定手段が測定した燃焼室内の圧力に応じてレーザの強度を制御する。さらに、燃焼室内の圧力が変動すると、この変動が減少するように照射手段にレーザの強度を強弱させる制御手段を備えている。
【０１２６】
このため、レーザの強度を制御することにより、固体推進薬の燃焼制御（推力の増減など）を行うことができる。また、燃焼室内の圧力の変動則ち推力の変動が減少するようにレーザの強度を制御するので、固体推進薬を安定的に燃焼させることができる。
【０１２７】
請求項２に記載の本発明によれば、固体推進薬にレーザを照射することにより固体推進薬を点火するようになっており、固体推進薬がレーザの照射を止めても燃焼を継続する自燃性となっている。また、燃焼室内の圧力を測定する測定手段を備え、この測定手段が測定した燃焼室内の圧力に応じてレーザの強度を制御する。さらに、動的消炎現象が起きる強さのレーザを固体推進薬に照射して、固体推進薬に噴射手段が水を噴射する。
【０１２８】
このため、レーザの強度を制御することにより、固体推進薬の燃焼制御（推力の増減など）を行うことができる。また、動的消炎現象が起きる強さのレーザを固体推進薬に照射するので、固体推進薬を燃焼して発生した火炎が一時的に固体推進薬の表面から離れる。このため、固体推進薬の表面では、急激に温度が下がりかつ圧力が減少して、固体推進薬が消火される。
【０１２９】
また、動的消炎現象が起きる強さのレーザを固体推進薬に照射して、固体推進薬に噴射手段が水を噴射するので、固体推進薬の表面から一時的に離れた火炎に向かって水が噴射される。このため、前述した火炎の温度が急激に下がり、この火炎が固体推進薬を再着火することを防止できる。
【０１３０】
したがって、レーザの強度を制御することにより、固体推進薬の燃焼制御（推力の増減など）を行うことができる。また、非自燃性の固体推進薬の場合、消火を行うことができる。したがって、固体推進薬の点火・燃焼及び消火を複数回行うことができ、取り扱いが容易で複数回噴射できる固体燃料ロケットを得ることができる。
【０１３１】
請求項３に記載の本発明によれば、固体推進薬にレーザを照射することにより固体推進薬を点火するようになっており、固体推進薬がレーザの照射を止めても燃焼を継続する自燃性となっている。また、燃焼室内の圧力を測定する測定手段を備え、この測定手段が測定した燃焼室内の圧力に応じてレーザの強度を制御する。さらに、燃焼室内の圧力が変動すると、この変動が減少するように照射手段にレーザの強度を強弱させる制御手段を備えている。
【０１３２】
また、動的消炎現象が起きる強さのレーザを固体推進薬に照射して、固体推進薬に噴射手段が水を噴射する。このため、動的消炎現象が起きる強さのレーザを固体推進薬に照射するので、固体推進薬を燃焼して発生した火炎が一時的に固体推進薬の表面から離れる。このため、固体推進薬の表面では、急激に温度が下がりかつ圧力が減少して、固体推進薬が消火される。
【０１３３】
また、動的消炎現象が起きる強さのレーザを固体推進薬に照射して、固体推進薬に噴射手段が水を噴射するので、固体推進薬の表面から一時的に離れた火炎に向かって水が噴射される。このため、前述した火炎の温度が急激に下がり、この火炎が固体推進薬を再着火することを防止できる。
【０１３４】
したがって、レーザの強度を制御することにより、固体推進薬の燃焼制御（推力の増減など）を行うことができる。また、燃焼室内の圧力の変動則ち推力の変動が減少するようにレーザの強度を制御するので、固体推進薬を安定的に燃焼させることができる。さらに、固体推進薬の消火を行うことができる。したがって、固体推進薬の点火・燃焼及び消火を複数回行うことができ、取り扱いが容易で複数回噴射できる固体燃料ロケットを得ることができる。
【０１３５】
請求項４に記載の発明によれば、固体推進薬にレーザを照射することにより推力を発生するようになっており、固体推進薬がレーザの照射を止めると燃焼を停止する非自燃性となっている。このため、レーザの照射を制御することにより、固体推進薬の点火・燃焼及び消火を複数回行うことができる。したがって、取り扱いが容易で複数回噴射できる固体燃料ロケットを得ることができる。また、レーザの強度を制御することにより、固体推進薬の燃焼制御（推力の増減など）を行うことができる。
【０１３６】
請求項５に記載の本発明によれば、燃焼室内の圧力を測定する測定手段を備え、この測定手段が測定した燃焼室内の圧力に応じてレーザの強度を制御する。燃焼室内の圧力に応じてレーザの強度を制御するので、所望の燃焼室内の圧力則ち所望の推力を得ることができる。
【図面の簡単な説明】
【図１】本発明の第１の実施形態にかかる固体燃料ロケットの平面図である。
【図２】図１に示された固体燃料ロケットの矢印ＩＩ方向からみた側面図である。
【図３】図１中のＡ−Ｂ−Ｃ−Ｄ−Ｅ−Ｆ−Ｇ−Ｈ−Ｉ線に沿う断面図である。
【図４】図１に示された固体燃料ロケットの着火部などの構成を示す説明図である。
【図５】図１に示された固体燃料ロケットの燃料部の断面図である。
【図６】図１に示された固体燃料ロケットの気体供給部などの構成を示す説明図である。
【図７】図１に示された固体燃料ロケットの固体推進薬を燃焼したときの圧力の変化を示す説明図である。
【図８】（ａ）は、図１に示された固体燃料ロケットの固体推進薬を燃焼したときに圧力の変動が発生した状態を示す説明図である。（ｂ）は、図８（ａ）の時に、変動を減少させるレーザの強度などを説明する説明図である。
【図９】図１に示された固体燃料ロケットの固体推進薬が着火、燃焼、動的消炎現象などを発生するときの条件などを示す説明図である。
【図１０】図１に示された固体燃料ロケットで動的消炎現象などが発生した状態を模式的に示す説明図である。
【図１１】図１に示された固体燃料ロケットの燃焼室の変形例を示す平面図である。
【図１２】図１１中のａ−ｂ−ｃ−ｄ−ｅ−ｆ−ｇ−ｈ−ｉ線に沿う断面図である。
【図１３】図１に示された固体燃料ロケットの燃料部の変形例を示す断面図である。
【図１４】図１に示された固体燃料ロケットの燃料部などの他の変形例を示す断面図である。
【図１５】図１に示された固体燃料ロケットに取り付けられる２次燃焼室などを示す断面図である。
【図１６】本発明の第２の実施形態にかかる固体燃料ロケットの断面図である。
【符号の説明】
１ 固体燃料ロケット
２ 燃焼室
３ ノズル
９ 固体推進薬
２１ 非自燃性の固体推進薬
２２ 自燃性の固体推進薬
２４ レーザ部（照射手段）
４６ 圧力センサ（測定手段）
４７ 制御装置（制御手段）
５０ 水噴射部（噴射手段）[0001]
TECHNICAL FIELD OF THE INVENTION
The present invention relates to a solid fuel rocket having a solid propellant ignited by a laser and capable of burning in space or the like.
[0002]
[Prior art]
As long-term manned space activities take place in space, the need for immediate use, easy maintenance, and reusable rocket-specific rockets arises.
[0003]
When a rocket is stored in outer space for a long time so that it can be used at any time, in a rocket using a liquid propellant or a hybrid rocket, the temperature control of the liquid propellant becomes a problem from the viewpoint of the boiling point and the melting point. Liquid propellants with good storability, such as ammonia and chlorine pentafluoride, whose temperature can be easily controlled, require careful handling during maintenance and inspection work such as fuel filling.
[0004]
Solid rockets (for example, see Patent Literature 1) are greatly reduced in terms of temperature control, harmfulness, and danger compared to liquid rockets, and are particularly serious problems without special temperature control devices or measures against harmful substances. Does not occur. Further, the simple structure facilitates maintenance and inspection.
[0005]
[Patent Document 1]
JP-A-7-127527
[0006]
[Problems to be solved by the invention]
However, once the conventional solid rocket is ignited, it is difficult to stop the combustion or change the thrust by combustion control. Therefore, the above-mentioned conventional solid rocket is not suitable for a propulsion device that repeatedly performs ignition, combustion, and fire extinguishing in space such as an artificial satellite. As described above, the conventional solid rocket cannot control the combustion of the solid propellant.
[0007]
Therefore, an object of the present invention is to provide a solid fuel rocket that can control combustion of a solid propellant.
[0008]
[Means for Solving the Problems]
In order to solve the above problems and achieve the object, a solid fuel rocket according to the present invention according to claim 1, comprises a hollow combustion chamber, a solid propellant positioned in the combustion chamber, and a laser mounted on the solid propellant. Irradiation means for irradiating the solid propellant to generate combustion gas, and a nozzle penetrating the wall surface of the combustion chamber and guiding the combustion gas inside the combustion chamber to the outside of the combustion chamber. In the rocket, the solid propellant is a self-combustible solid propellant that continues burning even after stopping laser irradiation, and a measuring means for measuring a pressure in the combustion chamber, and a combustion measured by the measuring means. Control means for controlling the irradiation means in accordance with the pressure in the room, and the control means increases or decreases the amount of combustion gas generated by increasing or decreasing the intensity of the laser irradiated by the irradiation means. , Serial pressure in the combustion chamber measuring means has measured is characterized in that to strength the strength of the laser in the irradiation unit so as to reduce fluctuations of said pressure to vary.
[0009]
The solid fuel rocket according to the present invention according to claim 2, wherein the solid propellant is burned by irradiating a laser to the hollow combustion chamber, the solid propellant positioned in the combustion chamber, and the solid propellant. In a solid fuel rocket comprising irradiation means for generating combustion gas, and a nozzle penetrating the wall surface of the combustion chamber and guiding the combustion gas in the combustion chamber out of the combustion chamber, the solid propellant performs laser irradiation. It is a self-combustible solid propellant that continues burning even when stopped, and includes an injection unit that injects water toward the solid propellant, and a control unit that controls the irradiation unit and the injection unit, The control means increases or decreases the intensity of the combustion gas by increasing or decreasing the intensity of the laser irradiated by the irradiation means, and the control means sets the laser having the intensity at which the dynamic quenching phenomenon occurs in the irradiation means. After irradiating the body propellant, it is characterized by jetting toward the water to the solid propellant to the injection means.
[0010]
The solid fuel rocket according to the present invention according to claim 3, wherein the solid propellant is burned by irradiating a laser to the hollow combustion chamber, the solid propellant positioned in the combustion chamber, and the solid propellant. In a solid fuel rocket comprising irradiation means for generating combustion gas, and a nozzle penetrating the wall surface of the combustion chamber and guiding the combustion gas in the combustion chamber out of the combustion chamber, the solid propellant performs laser irradiation. It is a self-combustible solid propellant that continues burning even when stopped, measuring means for measuring the pressure in the combustion chamber, injection means for injecting water toward the solid propellant, and the measuring means Controlling the irradiating means according to the measured pressure in the combustion chamber, and controlling means for controlling the injecting means, the control means to increase or decrease the intensity of the laser irradiated by the irradiating means The amount of combustion gas generated is increased or decreased, and when the pressure in the combustion chamber measured by the measuring means fluctuates, the intensity of the laser is increased or decreased by the irradiation means so that the fluctuation of the pressure is reduced, and the control means sets the After irradiating the solid propellant with a laser having an intensity that causes a dynamic quenching phenomenon to the irradiating means, water is jetted toward the solid propellant by the jetting means.
[0011]
The solid fuel rocket according to the present invention according to claim 4, wherein a hollow combustion chamber, a solid propellant positioned in the combustion chamber, and irradiating the solid propellant with a laser to burn the solid propellant. A solid fuel rocket comprising: an irradiation unit for generating combustion gas; and a nozzle penetrating a wall surface of the combustion chamber and guiding the combustion gas in the combustion chamber to outside the combustion chamber. It is a non-combustible solid propellant that stops burning when it is stopped.
[0012]
A solid fuel rocket according to a fifth aspect of the present invention is the solid fuel rocket according to the fourth aspect, wherein a measuring means for measuring the pressure in the combustion chamber and a pressure in the combustion chamber measured by the measuring means are provided. Control means for controlling the irradiation means, the control means increases or decreases the intensity of the laser irradiated by the irradiation means to increase or decrease the generation amount of the combustion gas, and the irradiation means Is stopped to stop the combustion of the solid propellant.
[0013]
According to the solid fuel rocket according to the first aspect of the present invention, the solid propellant is ignited by irradiating the solid propellant with a laser. Is self-combustible. Further, a measuring means for measuring the pressure in the combustion chamber is provided, and the intensity of the laser is controlled in accordance with the pressure in the combustion chamber measured by the measuring means. Further, when the pressure in the combustion chamber fluctuates, the irradiation means is provided with a control means for increasing or decreasing the intensity of the laser so as to reduce the fluctuation.
[0014]
For this reason, by controlling the intensity of the laser, it is possible to control the combustion of the solid propellant (eg, increase or decrease the thrust). Further, since the laser intensity is controlled so that the fluctuation of the pressure in the combustion chamber, that is, the fluctuation of the thrust is reduced, the solid propellant can be stably burned.
[0015]
According to the solid fuel rocket of the present invention described in claim 2, the solid propellant is ignited by irradiating the solid propellant with a laser, so that the solid propellant burns even if the laser irradiation is stopped. Is self-combustible. Further, a measuring means for measuring the pressure in the combustion chamber is provided, and the intensity of the laser is controlled in accordance with the pressure in the combustion chamber measured by the measuring means. Further, the solid propellant is irradiated with a laser having a strength at which the dynamic quenching phenomenon occurs, and the injection means injects water into the solid propellant.
[0016]
For this reason, by controlling the intensity of the laser, it is possible to control the combustion of the solid propellant (eg, increase or decrease the thrust). In addition, since the solid propellant is irradiated with a laser having an intensity at which the dynamic quenching phenomenon occurs, the flame generated by burning the solid propellant temporarily leaves the surface of the solid propellant. Therefore, on the surface of the solid propellant, the temperature rapidly decreases and the pressure decreases, and the solid propellant is extinguished.
[0017]
In addition, the solid propellant is irradiated with a laser having an intensity that causes a dynamic quenching phenomenon, and the jetting means jets water onto the solid propellant, so that the water is directed toward a flame temporarily separated from the surface of the solid propellant. Is injected. For this reason, the temperature of the above-mentioned flame falls sharply, and this flame can be prevented from re-igniting the solid propellant.
[0018]
Therefore, by controlling the intensity of the laser, it is possible to control the combustion of the solid propellant (such as increasing or decreasing the thrust). In addition, it is possible to extinguish the solid propellant. Therefore, the solid propellant can be ignited, burned and extinguished a plurality of times, and a solid fuel rocket that is easy to handle and can be injected a plurality of times can be obtained.
[0019]
According to the solid fuel rocket of the present invention described in claim 3, the solid propellant is ignited by irradiating the solid propellant with a laser, so that the solid propellant burns even if the laser irradiation is stopped. Is self-combustible. Further, a measuring means for measuring the pressure in the combustion chamber is provided, and the intensity of the laser is controlled in accordance with the pressure in the combustion chamber measured by the measuring means. Further, when the pressure in the combustion chamber fluctuates, the irradiation means is provided with a control means for increasing or decreasing the intensity of the laser so as to reduce the fluctuation.
[0020]
Further, the solid propellant is irradiated with a laser having an intensity at which the dynamic quenching phenomenon occurs, and the jetting means jets water to the solid propellant. For this reason, the solid propellant is irradiated with a laser having an intensity that causes the dynamic quenching phenomenon, so that the flame generated by burning the solid propellant is temporarily separated from the surface of the solid propellant. Therefore, on the surface of the solid propellant, the temperature rapidly decreases and the pressure decreases, and the solid propellant is extinguished.
[0021]
In addition, the solid propellant is irradiated with a laser having an intensity that causes a dynamic quenching phenomenon, and the jetting means jets water onto the solid propellant, so that the water is directed toward a flame temporarily separated from the surface of the solid propellant. Is injected. For this reason, the temperature of the above-mentioned flame falls sharply, and this flame can be prevented from re-igniting the solid propellant.
[0022]
Therefore, by controlling the intensity of the laser, it is possible to control the combustion of the solid propellant (such as increasing or decreasing the thrust). Further, since the laser intensity is controlled so that the fluctuation of the pressure in the combustion chamber, that is, the fluctuation of the thrust is reduced, the solid propellant can be stably burned. Furthermore, fire extinguishing of the solid propellant can be performed. Therefore, the solid propellant can be ignited, burned and extinguished a plurality of times, and a solid fuel rocket that is easy to handle and can be injected a plurality of times can be obtained.
[0023]
According to the solid fuel rocket of the present invention described in claim 4, thrust is generated by irradiating the solid propellant with a laser, and combustion stops when the solid propellant stops irradiating the laser. It is non-combustible. Therefore, by controlling the irradiation of the laser, ignition, combustion and extinguishing of the solid propellant can be performed a plurality of times. Therefore, it is possible to obtain a solid fuel rocket that is easy to handle and can be injected a plurality of times. Further, by controlling the intensity of the laser, combustion control of the solid propellant (increase or decrease in thrust) can be performed.
[0024]
According to the fifth aspect of the present invention, there is provided a solid fuel rocket according to the present invention, comprising a measuring means for measuring the pressure in the combustion chamber, and controlling the laser intensity according to the pressure in the combustion chamber measured by the measuring means. Since the intensity of the laser is controlled in accordance with the pressure in the combustion chamber, a desired pressure in the combustion chamber, that is, a desired thrust can be obtained.
[0025]
The solid propellant described in the present specification generally indicates a solid fuel and a solid oxidizer. In addition, the solid propellant described in this specification also includes a solid propellant that originally contains more fuel than the oxidant and should be called a fuel-rich solid propellant, and originally contains more oxidant than fuel. Also includes solid propellants which should be referred to as oxidizer-rich solid propellants.
[0026]
Further, the non-combustible solid propellant refers to a solid propellant that extinguishes (stops combustion) when the supply of external energy such as a laser is stopped. The self-combustible solid propellant refers to a solid propellant that keeps burning even when external energy such as a laser is not supplied.
[0027]
BEST MODE FOR CARRYING OUT THE INVENTION
Hereinafter, a solid fuel rocket 1 according to a first embodiment of the present invention will be described with reference to FIGS. As shown in FIGS. 1 to 3, the solid fuel rocket 1 includes a spherical combustion chamber 2, a nozzle 3, a plurality of combustion units 4, a water injection unit 50 as an injection unit (shown in FIG. 6), A pressure sensor 46 (shown in FIG. 6) as measuring means and a control device 47 (shown in FIG. 4) as control means are provided.
[0028]
As shown in FIG. 3, the combustion chamber 2 includes a hollow chamber body 8 having a spherical outer shape and a plurality of outer cases 10. The combustion chamber 2, that is, the combustion chamber 2 is formed to be hollow, and the inside thereof is filled with combustion gas generated by combustion of a solid propellant 9 of a later-described fuel unit 6 of the combustion unit 4. As shown in FIG. 5, the outer case 10 includes a disk-shaped bottom plate 12, a cylindrical portion 13 formed in a cylindrical shape and connected to an outer edge of the bottom plate 12, and an outer edge of the cylindrical portion 13 on a side away from the bottom plate 12. And a disc-shaped flange portion 14 connected to the main body.
[0029]
The flange portion 14 is formed to have an inner diameter equal to the outer diameter of the cylindrical portion 13, and protrudes from the outer edge of the cylindrical portion 13 toward the outer periphery of the cylindrical portion 13. The flange portion 14 is provided with a bolt through hole 15. The flange portion 14 is placed on the outer surface of the wall surface 5 of the room main body 8 and attached to the wall surface 5, that is, the room main body 8. The wall surface 5 is provided with a screw hole 17 that matches the bolt through hole 15 and into which the bolt 16 is screwed. Further, an O-ring 18 is provided between the flange portion 14 and the wall surface 5 to keep the space therebetween airtight.
[0030]
The nozzle 3 is attached to a wall surface 5 (shown in FIG. 3 and the like) of the combustion chamber 2. The nozzle 3 penetrates the wall surface 5 of the chamber main body 8 and guides the combustion gas inside the combustion chamber 2 to the outside of the combustion chamber 2. The upper half of the combustion chamber 2 which is away from the nozzle 3 and located on the upper side in FIG. 2 is hereinafter referred to as a northern hemisphere 2a, and the lower half located near the nozzle 3 and located on the lower side in FIG. 2 is hereinafter referred to as a southern hemisphere 2b.
[0031]
Three or more combustion units 4 are provided. In the illustrated example, three combustion units 4 are provided. The combustion unit 4 includes a fuel section 6 and an ignition section 7, as shown in FIG.
[0032]
As shown in FIG. 5, the fuel section 6 includes an inner case 11 and a solid propellant 9 accommodated in the inner case 11. The inner case 11 includes a disc-shaped bottom plate 19 and a cylindrical portion 20 formed in a cylindrical shape and connected to an outer edge of the bottom plate 19. The outer diameters of the bottom plate 19 and the cylindrical portion 20 are equal to the inner diameter of the cylindrical portion 13 of the outer case 10. The inner case 11 is accommodated in the outer case 10 with the bottom plate 19 overlapping the bottom plate 12.
[0033]
The solid propellant 9 is housed in an inner case 11 housed in an outer case 10. For this reason, the solid propellant 9 is located in the combustion chamber 2. The solid propellant 9 described in the present specification generally indicates a solid fuel and a solid oxidizer. Further, the solid propellant 9 described in the present specification contains a large amount of oxidant in the fuel, and also includes a solid propellant which should be originally called a fuel-rich solid propellant, and contains a large amount of fuel in the oxidant. It also includes a solid propellant which should be called an oxidizer-rich solid propellant.
[0034]
Of the fuel units 6 of the three combustion units 4, the solid propellants 9 of the two fuel units 6 shown in FIG. 3 are composed of a solid fuel and a solid oxidizer, and are in excess of fuel. The solid propellant of the remaining one fuel section 6 is made of a solid oxidizer.
[0035]
Further, the solid propellant 9 of the two fuel sections 6 shown in FIG. 3 includes a non-combustible solid propellant 21 and a self-combustible solid propellant 22. The non-combustible solid propellant 21 is formed in a cylindrical shape and is housed in the inner case 11 of the housing 8. The self-combustible solid propellant 22 is formed in a columnar shape and is accommodated in the non-combustible solid propellant 21. Thus, the solid propellant 9 is composed of the self-combustible solid propellant 22 and the like.
[0036]
The non-combustible solid propellant 21 described in this specification refers to a solid propellant that extinguishes (stops combustion) when the supply of external energy such as the laser L is stopped. That is, the non-combustible solid propellant 21 stops burning (extinguishes) when the irradiation of the laser L stops. The self-combustible solid propellant 22 refers to a solid propellant that keeps burning even when external energy such as the laser L is not supplied. That is, the self-combustible solid propellant 22 continues burning even when the irradiation of the laser L is stopped.
[0037]
When the irradiation time of the laser L and the intensity of the laser L change, the self-combustible solid propellant 22 ignites, burns, or causes a dynamic extinction phenomenon (Dynamic Extension), as shown in FIG. If the irradiation time of the laser L is shorter than that of the boundary S1 in FIG. 9 and the intensity of the laser L is weak, the self-combustible solid propellant 22 does not burn (ignite).
[0038]
Further, when the intensity of the laser L is higher than the boundary S2 in FIG. 9 (in a region indicated by oblique lines in FIG. 9), the self-combustible solid propellant 22 causes a dynamic quenching phenomenon. In the dynamic quenching phenomenon, the pressure and temperature of the flame generated by the burning of the solid propellant 22 temporarily increase, and the above-mentioned flame separates from the surface of the solid propellant 22. Then, the temperature near the surface of the solid propellant 22 is significantly reduced, and the solid propellant 22 is extinguished. That is, the dynamic quenching phenomenon is a phenomenon in which the temperature near the surface of the solid propellant 22 is significantly reduced, and the solid propellant 22 is extinguished. Furthermore, between the boundary S1 and the boundary S2 in FIG. 9, the self-combustible solid propellant 22 burns (ignites) without causing a dynamic quenching phenomenon or the like.
[0039]
The non-combustible and self-combustible solid propellants 21 and 22 are fuel-rich composite propellants comprising a polymer material of terminal hydroxyl group polybutadiene (HTPB) as a solid fuel and ammonium perchlorate as a solid oxidizer, A small amount of carbon black is added in consideration of the absorption of the laser L and the like. If necessary, a combustion catalyst such as ferric oxide is added.
[0040]
Other constituents of the solid propellants 21, 22 include ammonium nitrate as an oxidizing agent, and a polymer material such as glycidyl azide polymer (GAP) or unsaturated polyester resin as a solid fuel. In addition to the examples given above, any solid energy substance suitable for the solid propellants 21 and 22 can be used. The non-self-combustible solid propellant 21 is obtained with a mixture ratio of the solid fuel and the oxidizing agent so that the flame is extinguished when the heating by the laser L is stopped after the fuel is excessive. Thus, if the laser L is turned off during the combustion of the non-combustible solid propellant 21, the combustion cannot be continued, and the combustion can be stopped (extinguished).
[0041]
The self-combustible solid propellant 22 is obtained with a mixture ratio of the solid fuel and the oxidant such that the fuel is excessive and the combustion is continued without heating by the laser L. Thus, the self-combustible solid propellant 22 continues burning even when the laser L is turned off during burning.
[0042]
Further, in the solid propellants 21 and 22 described above, if the intensity of the laser L is changed, the burning speed changes accordingly, so that the magnitude of the thrust of the rocket can be controlled. The surface of the solid propellants 21 and 22 recedes as the combustion proceeds, but since the change in the intensity of the laser L is small, the influence is not usually a problem.
[0043]
The above-described fuel unit 6 is manufactured as follows. After attaching a liner (not shown) in the cylindrical inner case 11, first, a non-combustible solid propellant 21 is filled along the inner surface of the inner case 11. After that, the self-combustible solid propellant 22 is filled inside the non-combustible solid propellant 21.
[0044]
Further, the configuration of the remaining one fuel unit 6 is the same as the configuration of the fuel unit 6 described above. The solid propellant of the fuel section 6 is composed of an oxidant such as ammonium perchlorate or ammonium nitrate, and a fuel such as a polymer material such as glycidyl azide polymer (GAP) or unsaturated polyester resin. The solid propellant is accommodated in the inner case 11. The above-described fuel section 6 is manufactured by attaching a liner (not shown) in a cylindrical inner case 11 and then filling the above-described solid propellant.
[0045]
The fuel unit 6 having the above-described configuration fills (stores) the solid propellants 21 and 22 in the inner case 11 and stores the inner case 11 in the outer case 10. After attaching the O-ring 18 to the flange portion 14, the flange portion 14 is overlaid on the wall surface 5. Then, the bolt through hole 15 and the screw hole 17 are aligned with each other, and the bolt 16 is passed through them. The bolt 16 is screwed in, and the flange 14, that is, the outer case 10 is attached to the wall surface 5 of the combustion chamber 2.
[0046]
When the solid propellants 21 and 22 in the inner case 11 have been burned, the outer case 10 is removed from the wall 5, and the burned solid propellants 21 and 22 are removed from the outer case 10 together with the inner case 11. The solid propellants 21 and 22 before combustion are accommodated in the outer case 10 together with the inner case 11. The outer case 10 is attached to the wall 5, that is, the combustion chamber 2 again, and is reused as the fuel unit 6. Further, in the combustion chamber 2, when the solid propellant 9 of the fuel section 6 of the three combustion units 4 burns, combustion gas with excessive fuel is generated.
[0047]
The ignition unit 7 includes a cavity 23, a laser unit 24 as an irradiation unit, and a gas supply unit 25, as shown in FIG. The cavity 23 is formed integrally with the wall surface 5 of the combustion chamber 2 and is disposed at a position facing the fuel section 6 with the center J (shown in FIG. 3 and the like) of the combustion chamber 2 interposed therebetween. The cavity 23 is formed to be concave from the inner surface of the wall 5 and to be convex from the outer surface of the wall 5. The cavity 23 is formed in a cylindrical shape and is continuous with the wall surface 5, and covers a cylindrical portion 26 extending from the wall surface 5 in the outer peripheral direction of the combustion chamber 2, and an edge 26 a of the cylindrical portion 26 on the side away from the wall surface 5. And a wall portion 27.
[0048]
The laser unit 24 includes a laser generation unit 28, an ultrasonic displacement meter 29, and a laser control unit 30. The laser generator 28 includes a laser power source 31, a laser controller 32, a semiconductor laser 33 as a laser source, a beam shaping unit 34, a beam homogenizer 35, a zoom unit 36, and an optical glass window 37. ing.
[0049]
The laser power supply 31 applies a voltage to the semiconductor laser 33 via the laser controller 32. The laser controller 32 controls electric power applied to the semiconductor laser 33 based on a command from the control device 47 or the like. The semiconductor laser 33 generates a laser L for burning the solid propellant 9. The semiconductor laser 33 emits the laser L toward the beam shaping unit 34. The beam shaping unit 34 forms the laser L from the semiconductor laser 33 into a circular cross section and emits the laser L toward the beam homogenizer 35.
[0050]
The beam homogenizer 35 makes the intensity of the laser L having a circular cross section uniform and emits the light toward the zoom unit 36. The zoom unit 36 includes a convex lens 38, a concave lens 39, and the like. The convex lens 38 is arranged closer to the beam homogenizer 35 than the concave lens 39. The concave lens 39 is disposed closer to the optical glass window 37 than the convex lens 38 is. At least one of the lenses 38 and 39 is slidable so that the distance between the convex lens 38 and the concave lens 39 can be changed.
[0051]
The laser beam L emitted from the beam homogenizer 35 enters the convex lens 38 and then enters the concave lens 39. Then, the laser beam L emitted from the concave lens 39 is guided to the optical glass window 37. The zoom unit 36 can change the angles θ1 and θ2 (shown in FIG. 4 and the like) at which the laser emitted from the concave lens 39 spreads by changing the distance between the convex lens 38 and the concave lens 39. Thus, the zoom unit 36 guides the laser L from the semiconductor laser 33 to the optical glass window 37 and changes the spread of the laser L (corresponding to the angles θ1 and θ2 described above).
[0052]
The optical glass window 37 is attached to the wall 27. The optical glass window 37 allows the above-described laser L to pass therethrough and does not allow the above-described combustion gas and the like to pass therethrough. The optical glass window 37 faces the solid propellant 9 of the fuel section 6 with the center J of the combustion chamber 2 interposed therebetween.
[0053]
The ultrasonic displacement meter 29 includes a tracing stylus 29 a attached to the wall 27. Therefore, the ultrasonic displacement meter 29 is attached to the wall 27. The tracing stylus 29a emits ultrasonic waves toward the surface 9a of the solid propellant 9 of the fuel unit 6. The tracing stylus 29a receives the ultrasonic waves reflected from the surface 9a of the solid propellant 9 of the fuel section 6. The surface 9 a of the solid propellant 9 is a surface of the solid propellant 9 that is exposed inside the combustion chamber 2.
[0054]
The ultrasonic displacement meter 29 is configured such that the tracing stylus 29a radiates ultrasonic waves to the surface 9a of the solid propellant 9 and receives ultrasonic waves reflected from the surface 9a. And measure the interval. The ultrasonic displacement meter 29 outputs information according to the distance between the wall 27 and the surface 9 a of the solid propellant 9 toward a motor controller 40 of the laser control unit 30 described below.
[0055]
The laser controller 30 includes a motor controller 40, a driver 41, and a stepping motor 42 for increasing or decreasing the distance between the lenses 38 and 39 of the zoom unit 36. The motor controller 40 controls the stepping motor 42 via the driver 41.
[0056]
The motor controller 40 changes the spread (angles θ1 and θ2) of the laser L based on the distance between the wall 27 and the surface 9a of the solid propellant 9 measured by the ultrasonic displacement meter 29. The motor controller 40 irradiates the laser L to the entire surface of the self-combustible solid propellant 22 and irradiates the outer edge of the non-combustible solid propellant 21, that is, the outer edge of the solid propellant 9. The spread (angles θ1, θ2) of the laser L is changed so as not to irradiate the part 20 and the like.
[0057]
Thus, the motor controller 40 irradiates the laser L to the outer edge of the surface of the solid propellant 9 based on the distance between the wall 27 measured by the ultrasonic displacement meter 29 and the surface 9a of the solid propellant 9. The zoom unit 36 is controlled so that the irradiation is not performed on the cylindrical section 20 (to restrict the irradiation on the cylindrical section 20). The laser unit 24 having the above-described configuration irradiates the solid propellant 9 with the laser L to burn the solid propellant 9 and generate combustion gas.
[0058]
As shown in FIG. 6, the gas supply unit 25 includes a gas tank 43 as a gas supply source, a through hole 44, a pipe 45, and a flow controller 48. The gas tank 43 stores a gas such as air in a pressurized state. The gas tank 43 supplies gas into the cavity 23 through the through hole 44.
[0059]
As shown in FIG. 4, the through-hole 44 penetrates the above-described edge 26a of the cylindrical portion 26. The pipe 45 connects the gas tank 43 and the through hole 44. The pipe 45 guides the gas in the gas tank 43 into the through hole 44. The flow controller 48 changes the flow rate of the gas supplied from the gas tank 43 into the cavity 23 through the through hole 44 according to a command from the control device 47.
[0060]
The ignition unit 7 having the above-described configuration generates a laser L from the semiconductor laser 33 as a heating source. The laser beam L emitted from the semiconductor laser 33 passes through the beam shaping unit 34 and is shaped into a column, and the intensity is made uniform by the next beam homogenizer 35.
[0061]
Information on the distance between the surface 9a of the solid propellant 9 and the wall 27 measured by the ultrasonic displacement meter 29 is analyzed in real time by the motor controller 40 or the like, and the surface 9a of the solid propellant 9 is irradiated with an appropriate laser L. The zoom unit 36 is adjusted by controlling the stepping motor 42 so that the zooming is performed.
[0062]
As described above, since the laser L spreads radially through the optical glass window 37 by controlling the zoom unit 36 by the stepping motor 42, a connection portion 49 between the cavity 23 and the wall surface 5 (shown in FIG. 4 and the like) ) Can be made sufficiently smaller than the cross-sectional area of the solid propellant 9, so that the flow rate of gas flowing into the cavity 23 can be reduced.
[0063]
Next, the laser beam L is transmitted through the optical glass window 37 and is irradiated on the surface 9 a of the solid propellant 9 of the fuel section 6. The irradiation area of the laser L here is smaller than the surface 9a of the solid propellant 9 so as not to heat the cylindrical portion 20 and the like. Thus, some solid propellants 9 are not heated, but they decompose and burn due to convective heat transfer by the surrounding high-temperature burned gas. As described above, the solid propellant 9 burns in the end face combustion type while being irradiated with the laser L. The solid propellant 9 is burned or gasified by the laser L, and combustion gas is generated in the combustion chamber 2.
[0064]
While the above-described laser L is being radiated, that is, while the solid propellant 9 is burning, the gas that has passed through the flow rate regulator 48 from the gas tank 43 or the like is always jetted into the cavity 23 through the through hole 44. are doing. This cools the optical glass window 37 heated by the radiation from the laser L or the flame of the combustion gas and prevents the combustion products from adhering to the optical glass window 37. Thus, the solid propellant 9 is irradiated with the laser L through the optical glass window 37 to burn the solid propellant 9 and to supply gas into the cavity 23 from the gas tank 43 through the through hole 44.
[0065]
The flow rate of the gas ejected through the through-hole 44 is optimally controlled by the flow rate regulator 48 while monitoring the pressure in the combustion chamber 2 with the pressure sensor 46 and the control device 47. In the case where the connecting portion 49 between the cavity 23 and the wall surface 5 is set to a supersonic nozzle in the above-described ignition section 7, an external signal is sent to the measuring element 29a of the ultrasonic displacement meter 29 installed in the cavity 23. Not reach. Therefore, in this case, the tracing stylus 29a of the ultrasonic displacement meter 29 is installed outside the cavity 23.
[0066]
When air is used as the gas, the gas injected from the through-holes 44 further performs secondary combustion with the combustion gas having excessive fuel, thereby contributing to increasing the combustion efficiency. Further, since the solid fuel rocket 1 is intended for operation only in a vacuum, there is no need to consider air resistance. Therefore, if there is no problem in weight, the volume of the gas tank 43 can be increased. As the gas in the gas tank 43, an inert gas or the like may be used, but a strong oxidizing gas or a flammable gas is not suitable. For this reason, we chose air here not only for secondary combustion, but also as an emergency reserve air reservoir in space.
[0067]
The three fuel units 6 described above are attached to the northern hemisphere 2a, and the ignition unit 7 is attached to the southern hemisphere 2b. The fuel section 6 and the ignition section 7 of each combustion unit 4 are opposed to each other with the center J of the combustion chamber 2 interposed therebetween. The optical axis of the laser L of each combustion unit 4 is along the direction in which the fuel section 6 and the ignition section 7 face each other. The optical axes of the lasers L of the three combustion units 4 intersect each other. The fuel section 6 and the ignition section 7 are arranged on the optical axis of the laser L with the center of the surface 9 a of the solid propellant 9. The optical axis of the laser L is inclined at an appropriate angle with respect to the central axis Q of the combustion chamber 2 (which forms the axis of the nozzle 3 and is indicated by a dashed line in FIG. 3). The combustion units 4 are mounted at positions that are axially symmetric with respect to the central axis Q of the combustion chamber 2.
[0068]
As a result, the combustion gas flowing out of each fuel section 6 is inclined with respect to the central axis Q described above, becomes counter-current, and collides at the center of the combustion chamber 2 to cancel the radial flow velocity component of the combustion chamber 2. Act like so. Therefore, it is possible to prevent the combustion gas from directly colliding with the optical glass window 37 in the cavity 23, and to prevent the combustion products from adhering to the optical glass window 37.
[0069]
In the above-described embodiment, the number of the fuel portions 6 is three. However, if the number of the fuel portions 6 is two, if one of the laser generating portions 28 fails, the combustion gas flow is directly directed toward the other normal optical glass window 37. The disadvantage is that From this point as well, the above-mentioned setting is desirable for the number and arrangement of the fuel portions 6 in the circumferential direction in the spherical combustion chamber 2. When it is desired to increase the number of fuel parts 6, three new fuel parts may be arranged at the center of the combustion chamber 2.
[0070]
As shown in FIG. 6, the water injection unit 50 includes a water tank 51, a water injection nozzle 52, a pipe 53, and a water flow regulator 54. The water tank 51 contains water. The water injection nozzle 52 sprays water from the water tank 51 supplied through the pipe 53 toward the solid propellant 9 of the fuel unit 6.
[0071]
The pipe 53 connects the water tank 51 and the water injection nozzle 52. The water flow regulator 54 changes the flow rate of water to be sprayed from the water tank 51 to the solid propellant 9 through the water injection nozzle 52 and whether or not to spray water in accordance with a command from the control device 47. The water injection unit 50 sprays water toward the solid propellant 9 through the water injection nozzle 52 when stopping the combustion in the combustion chamber 2 as described later. The water injection unit 50 injects water toward the solid propellant 9 based on a command from the control device 47.
[0072]
The water tank 51 is pressurized by the pressure in the gas tank 43 so as to obtain the above-described water injection pressure. This simplifies the structure.
[0073]
The pressure sensor 46 is attached to the wall surface 5, measures the pressure in the combustion chamber 2, and outputs the measured pressure to the control device 47. As the pressure sensor 46, a piezoelectric pressure sensor can be used.
[0074]
The control device 47 is a computer including a known RAM, ROM, CPU, and the like. Information corresponding to the pressure in the combustion chamber 2 is input from the pressure sensor 46 to the control device 47. The control device 47 controls the laser controller 32 of the laser unit 24 based on the pressure in the combustion chamber 2 measured by the pressure sensor 46. The control device 47 controls the flow regulator 48 based on the pressure in the combustion chamber 2 measured by the pressure sensor 46 to control the flow rate of the gas supplied from the gas tank 43 into the cavity 23 through the through hole 44. I do. The control device 47 controls a water flow regulator 54 described later based on the pressure in the combustion chamber 2 measured by the pressure sensor 46 to control the water supplied from the water tank 51 into the cavity 23 through the water injection nozzle 52. Control the flow rate.
[0075]
The control device 47 increases or decreases the intensity of the laser L irradiated by the laser unit 24 to increase or decrease the amount of combustion gas generated, that is, the thrust. At this time, it is needless to say that the laser L is increased or decreased based on the pressure in the combustion chamber 2 measured by the pressure sensor 46. That is, the controller 47 increases or decreases the intensity of the laser L to obtain a desired pressure in the combustion chamber 2, that is, a desired thrust.
[0076]
The control device 47 stores a change in pressure in the combustion chamber 2 when the solid propellant 9 shown in FIG. 7 is burned. FIG. 7 is obtained by actually burning the solid propellant 9. While the solid propellant 9 in the combustion chamber 2 is burning, as shown by a solid line in FIG. 8A, the pressure, that is, the thrust fluctuates in the combustion chamber 2 (the pressure is high and low, and the thrust increases and decreases). Sometimes. Note that the two-dot chain line in FIG. 8A indicates a state in which the solid propellant 9 burns without causing pressure fluctuation, and indicates an ideal combustion state of the solid propellant 9. The control device 47 first predicts how the pressure in the combustion chamber 2 will change in the future based on the pressure change when the solid propellant 9 shown in FIG. 7 has burned.
[0077]
The control device 47 determines the intensity of the laser L at which the pressure change obtained by prediction as described above becomes a constant pressure (indicated by the two-dot chain line in FIG. 8A) (the one-dot chain line in FIG. 8B). Is calculated). Note that the solid line in FIG. 8B indicates the intensity of the laser L when the pressure fluctuation indicated by the solid line in FIG. 8A occurs. A dashed line in FIG. 8B indicates the intensity of the laser L for reducing the pressure fluctuation indicated by a solid line in FIG. The control device 47 causes the laser unit 24 to irradiate the solid propellant 9 with the laser L at the intensity indicated by the dashed line in FIG. 8B. As described above, when the pressure in the combustion chamber 2 measured by the pressure sensor 46 fluctuates (high or low), the control device 47 causes the laser unit 24 to increase or decrease the intensity of the laser L so that the fluctuation of the pressure decreases.
[0078]
Further, when extinguishing the burning solid propellant 9, the control device 47 irradiates the solid propellant 9 with a laser L having an intensity at which a dynamic quenching phenomenon shown by parallel oblique lines in FIG. 9 occurs. Let it. Then, the pressure and temperature of the flame generated by the burning of the solid propellant 9 rises sharply. The flame described above moves, for example, from a position indicated by a solid line in FIG. 10 to a position indicated by a two-dot chain line in FIG. That is, the above-described flame leaves the solid propellant 9. Then, the temperature near the surface 9a of the solid propellant 9, that is, at the position indicated by the solid line in FIG. 10, rapidly decreases, and the combustion of the solid propellant 9 stops, that is, the solid propellant 9 is extinguished.
[0079]
Further, the control device 47 irradiates the water L to the solid propellant 9 from the water tank 51 through the water injection nozzle 52 after irradiating the laser L having an intensity at which the dynamic quenching phenomenon occurs. Then, water is sprayed on the flame located at the position shown by the two-dot chain line in FIG. 10, and the temperature of the flame decreases. Therefore, it is possible to prevent the flame from approaching the surface 9a of the solid propellant 9 and re-igniting the solid propellant 9. As described above, the control device 47 irradiates the solid propellant 9 with the laser L having an intensity at which the dynamic quenching phenomenon occurs to the laser unit 24, and then causes the water jetting unit 50 to jet water toward the solid propellant 9. .
[0080]
As described above, in the solid fuel rocket 1 having the above-described configuration, the pressure in the combustion chamber 2 during combustion is measured by the pressure sensor 46 having good responsiveness, and the waveform is analyzed in real time by the control device 47. If unstable combustion occurs in the combustion chamber 2, as described above, the semiconductor laser 33 is driven as an actuator by the laser controller 32, and the surface 9 a of the solid propellant 9 is moved so that the laser L cancels the unstable combustion. Is added to
[0081]
In addition, in the solid fuel rocket 1, in order to extinguish the solid propellant 9 during combustion, as described above, a high-intensity laser L is applied to the solid propellant 9 as a square wave pulse or a pulse train, and the solid propellant 9 is fired. The temperature of 9 and the pressure in the combustion chamber 2 are temporarily increased. Thereafter, the temperature of the solid propellant 9 and the pressure in the combustion chamber 2 are suddenly reduced to cause a dynamic extinction phenomenon (Dynamic Extention).
[0082]
Then, the combustion gas burning on the surface 9a of the solid propellant 9 temporarily leaves the surface 9a of the solid propellant 9. At this time, water is injected from the water injection nozzle 52 to the high-temperature combustion gas separated from the surface 9a of the solid propellant 9 to lower the temperature of the combustion gas, thereby suppressing re-ignition of the solid propellant 9. Thus, the burning solid propellant 9 is extinguished.
[0083]
The solid fuel rocket 1 of the embodiment described above irradiates the surface 9a of the solid propellant 9 with the laser L at an intensity between the boundaries S1 and S2 in FIG. Then, even if the irradiation of the laser L is stopped, the solid propellant 9 burns. At this time, the gas is simultaneously blown into the cavity 23 through the through hole 44, the ultrasonic displacement meter 29 measures the distance between the wall 27 and the surface 9 a of the solid propellant 9, and the motor controller 40 controls the zoom unit 36. Controlling. For example, at the position where the surface 9a of the solid propellant 9 is indicated by a solid line in FIG. 4, the spread of the laser L is at an angle θ1, and at the position where the surface 9a of the solid propellant 9 is indicated by a two-dot chain line in FIG. The spread of L is the angle θ2. In this way, the spread of the laser L is gradually reduced as the solid propellant 9 burns.
[0084]
The combustion gas generated from the solid propellant 9 collides at the center of the combustion chamber 2 and is guided toward the nozzle 3. Then, the combustion gas generated by the combustion of the solid propellant 9 in the combustion chamber 2 is ejected through the nozzle 3 to generate thrust.
[0085]
At this time, when increasing the thrust, for example, the laser L is irradiated toward the solid propellant 9 or the laser L applied to the solid propellant 9 is increased. When the pressure in the combustion chamber 2 fluctuates, the fluctuation is measured by the pressure sensor 46, and the intensity of the laser L is changed so as to cancel the fluctuation.
[0086]
Further, when the combustion of the solid propellant is stopped, a high-intensity laser beam is applied to the solid propellant 9 as a square wave pulse or a pulse train to cause a dynamic extinction phenomenon (Dynamic Extension). Then, water is injected from the water injection nozzle 52 to stop the combustion of the solid propellant 9.
[0087]
According to the present embodiment, the solid propellant 9 is ignited by irradiating the laser L, and the self-combustible solid propellant that continues burning even when the solid propellant 9 stops irradiation of the laser L. 22. The pressure sensor 46 for measuring the pressure in the combustion chamber 2 is provided, and the intensity of the laser L is controlled according to the pressure in the combustion chamber 2 measured by the pressure sensor 46. Furthermore, the control unit 47 is provided in the irradiation unit 24 so as to reduce the intensity of the laser L so as to reduce the fluctuation when the pressure in the combustion chamber 2 changes.
[0088]
Further, the solid propellant 9 is irradiated with the laser L having an intensity at which the dynamic quenching phenomenon occurs, and the water jetting unit 50 jets water to the solid propellant 9. For this reason, the solid propellant 9 is irradiated with the laser L having the intensity at which the dynamic quenching phenomenon occurs, so that the flame generated by burning the solid propellant 9 is temporarily separated from the surface 9 a of the solid propellant 9. For this reason, on the surface 9a of the solid propellant 9, the temperature drops rapidly, and the solid propellant 9 is extinguished.
[0089]
Further, the solid propellant 9 is irradiated with the laser L having the intensity at which the dynamic quenching phenomenon occurs, and the water jetting unit 50 jets water to the solid propellant 9. Water is sprayed toward the distant flame. For this reason, the temperature of the above-mentioned flame falls rapidly, and this flame can prevent that the solid propellant 9 reignites.
[0090]
Therefore, by controlling the intensity of the laser L, it is possible to control the combustion of the solid propellant 9 (eg, increase or decrease the thrust). Further, since the intensity of the laser L is controlled so that the fluctuation of the pressure in the combustion chamber 2, that is, the fluctuation of the thrust is reduced, the solid propellant 9 can be stably burned. Furthermore, fire extinguishing of the solid propellant 9 can be performed. Therefore, ignition, combustion and extinguishing of the solid propellant 9 can be performed a plurality of times, and the solid fuel rocket 1 that is easy to handle and can be injected a plurality of times can be obtained.
[0091]
Once the solid propellant 9 is ignited, the combustion continues even if the laser L is turned off because of its self-combustion property. Therefore, the power consumption is greatly reduced even without using the laser L during this time. However, it is necessary to set the mixing ratio of the solid fuel and the solid oxidizer to an appropriate value in advance so as to lower the self-combustibility of the solid propellant 9 in order to perform dynamic quenching by the laser L. On the other hand, if the laser L at the time of ignition is too strong, dynamic quenching may occur even when the laser L is cut off after ignition. Therefore, the intensity of the laser L is kept low by the laser controller 32 to such an extent that it does not extinguish.
[0092]
Since the fuel section 6 is attached to the northern hemisphere 2a of the combustion chamber 2, the flow of the combustion gas passes through the nozzle 3 relatively without stagnating, so that the mechanical loss is small. However, since the cavity 23 is attached to the southern hemisphere 2b of the combustion chamber 2, the possibility of inflow of combustion products into the cavity 23 increases.
[0093]
Further, since the solid propellant 9 is irradiated with the laser L, the solid propellant 9 can be burned by passing the laser L into the combustion chamber 2, so that the pressure in the combustion chamber 2 can be increased. Therefore, the amount of combustion gas generated in the combustion chamber 2 can be increased, and the thrust can be increased.
[0094]
Further, three combustion units 4 are provided. The ignition part 7 and the fuel part 6 of each combustion unit 4 are opposed to each other with the center J of the combustion chamber 2 interposed therebetween. For this reason, the combustion gas generated by the combustion of the solid propellant 9 of each fuel unit 6 collides with each other at the center of the combustion chamber 2, and the direction in which the combustion gas flows changes. Therefore, it is possible to prevent the combustion gas generated by the combustion of the solid propellant 9 of each fuel section 6 from being directly blown to the corresponding ignition section 7.
[0095]
Further, since three combustion units 4 are provided, even if one combustion unit 4 is damaged, the combustion gas generated by burning the solid propellant 9 of each fuel unit 6 is generated in the center of the combustion chamber 2. Colliding with each other ensures that the direction of flow of the combustion gas changes. Therefore, it is possible to reliably prevent the combustion gas from being directly blown to the ignition section 7, and to prevent the ignition section 7, that is, the combustion unit 4 from being damaged.
[0096]
A non-combustible solid propellant 21 is provided on the outer edge of the solid propellant 9, and a self-combustible solid propellant 22 is provided inside the non-combustible solid propellant 21. Further, the laser beam L is not irradiated on the cylindrical portion 20 and the like. Therefore, it is possible to prevent the cylinder portion 20 from being heated more than necessary, and to prevent the cylinder portion 20, that is, the combustion unit 4 from being damaged.
[0097]
The cavity 23 to which the optical glass window 37 is attached is concave from the inner surface of the combustion chamber 2 and convex from the outer surface of the combustion chamber 2. Thus, the ignition part 7 is depressed when viewed from inside the combustion chamber 2. Further, gas is blown from the edge 26a into the cylindrical portion 26, that is, into the cavity 23. Therefore, the blown gas flows on the optical glass window 37. Therefore, it is possible to prevent the optical glass window 37 from being heated and to prevent the combustion products from adhering, and it is possible to more reliably prevent the ignition part 7, that is, the combustion unit 4 from being damaged.
[0098]
In the above-described embodiment, the fuel section 6 is attached to the northern hemisphere 2a of the combustion chamber 2. However, in the present invention, as shown in FIGS. 11 and 12, the fuel section 6 may be attached to the southern hemisphere 2b, and the auxiliary fuel section 55 may be attached to the northern hemisphere 2a. The combustion chamber 2 (shown in FIG. 1 and the like) shown in the above-described embodiment is hereinafter referred to as a type A, and the fuel chamber 2 shown in FIG. In FIGS. 11 and 12, the same parts as those in the above-described embodiment are denoted by the same reference numerals, and description thereof will be omitted. The auxiliary fuel section 55 contains a solid oxidant 56. The auxiliary fuel portion 55 faces the nozzle 3 with the center J interposed therebetween.
[0099]
In the type B combustion chamber 2, the fuel-rich combustion gas flow from the solid propellant 9 in the southern hemisphere 2b collides with the surface of the solid oxidant 56 in the auxiliary fuel section 55 in the northern hemisphere 2a, where the opposed jet diffusion flames To form Although the combustion chamber 2 of the type B forms an opposed jet diffusion flame, the combustion efficiency is improved, but the dynamic loss of the flow and the increase of the heat load on the wall of the combustion chamber become problems. In the combustion chamber 2 of the type B, the cavity 23 of the ignition section 7 is installed in the northern hemisphere 2a of the combustion chamber 2, so that there is little risk of inflow of combustion products.
[0100]
In addition, all of the solid propellants 9 of the fuel section 6 of the type A and type B combustion chambers 2 may be non-combustible solid propellants 21 as shown in FIG. If the laser L is turned off during the combustion of the non-combustible solid propellant 21, the combustion cannot be continued, and the combustion can be stopped.
[0101]
Therefore, when only the non-combustible solid propellant 21 shown in FIG. 13 is used for the fuel unit 6, the irradiation of the laser L is stopped to stop the combustion of the solid propellant 9. Therefore, the combustion of the solid propellant 9 can be easily stopped. Further, by controlling the intensity of the laser L, it is possible to control the combustion of the solid propellant 9 (eg, increase or decrease the thrust).
[0102]
In this way, as shown in FIG. 13, when only the non-combustible solid propellant 21 is used for the fuel unit 6, by controlling the irradiation of the laser L, the ignition, combustion, and extinction of the solid propellant 9 can be performed in a plurality. Times can be done. Further, the laser L is increased or decreased to increase or decrease the amount of generated combustion gas, that is, the thrust.
[0103]
Further, a pressure sensor 46 for measuring the pressure in the combustion chamber 2 is provided, and the intensity of the laser L is controlled according to the pressure in the combustion chamber 2 measured by the pressure sensor 46. Since the intensity of the laser L is controlled in accordance with the pressure in the combustion chamber 2, a desired pressure in the combustion chamber 2, that is, a desired thrust can be obtained. Therefore, the reusable solid fuel rocket 1 composed of the solid propellant 9 that is easy to handle and can control the thrust including ignition / stop can be easily obtained.
[0104]
Further, in the case shown in FIG. 13 as well, when the pressure in the combustion chamber 2 measured by the pressure sensor 46 fluctuates, the laser unit 24 makes the laser L more or less intense so that the fluctuation of the pressure decreases.
[0105]
In the above-described embodiment, the spread θ1 and θ2 of the laser L are controlled in order to appropriately irradiate the solid propellant 9 with the laser L. However, as shown in FIG. 14, the distance between the probe 27a of the wall 27, that is, the probe 29a of the ultrasonic displacement meter 29 and the surface 9a of the solid propellant 9, is kept constant, and the laser L is applied to the outer edge of the solid propellant 9. Irradiation to the cylinder portion 20 may be restricted.
[0106]
In FIG. 14, the same parts as those in the above-described embodiment are denoted by the same reference numerals, and description thereof will be omitted. In the case shown in FIG. 14, the inner case 11 is slidable along the radial direction of the combustion chamber 2 with respect to the outer case 10. The combustion unit 4 includes the above-described ultrasonic displacement meter 29, a moving unit 57 as a moving unit, and a control unit 58.
[0107]
The moving section 57 includes a rack 59 attached to the inner case 11, a motor 60 fixed to the combustion chamber 2, and the like. A pinion 61 that meshes with the rack 59 is attached to the output shaft of the motor 60. The moving section 57 can move the solid propellant 9 toward the inside of the combustion chamber 2 by rotating the output shaft of the motor 60.
[0108]
The control unit 58 includes a motor controller 62 connected to the ultrasonic displacement meter 29, a driver 63, and the like. The motor controller 62 is connected to the motor 60 via the driver 63. The motor controller 62 irradiates the laser L to the outer edge of the surface 9a of the solid propellant 9 based on the distance between the wall 27 and the surface 9a of the solid propellant 9 measured by the ultrasonic displacement meter 29. In addition, the motor 60 is controlled via the driver 63 so as to prevent the irradiation of the cylindrical portion 20. The motor controller 62 moves the solid propellant 9 gradually toward the inside of the combustion chamber 2 as the solid propellant 9 is burned. In the case shown in FIG. 14, the laser L is not applied to the cylinder 20, so that the cylinder 20 can be prevented from being heated more than necessary, and the cylinder 20, that is, the combustion unit 4 can be prevented from being damaged.
[0109]
Further, in the present invention, as shown in FIG. 15, a secondary combustion chamber 64 may be further attached to the combustion chamber 2 to increase the thrust. The secondary combustion chamber 64 includes a cylindrical main body 65 attached to the nozzle 3 and the like, a second nozzle 66, and a secondary solid propellant 67 accommodated in the main body 65. One end of the main body 65 is attached to the nozzle 3 of the combustion chamber 2. The combustion gas in the combustion chamber 2 is blown into the main body 65 through the nozzle 3. The second nozzle 66 is attached to the other end of the main body 65 on the side remote from the nozzle 3. The second nozzle 66 guides the combustion gas passing through the inside of the main body 65 to the outside of the main body 65.
[0110]
The secondary solid propellant 67 is formed in an annular shape and is filled in the main body 65. The secondary solid propellant 67 has a through hole 67a formed at the center thereof, through which the combustion gas blown into the main body 65 passes.
[0111]
The nozzle 3, the main body 65, the second nozzle 66, and the secondary solid propellant 67 are coaxially arranged.
[0112]
A plurality of secondary solid propellants 67 are provided in the main body 65. The secondary solid propellant 67 is provided with the solid oxidant 56, the non-combustible solid propellant 21, and the solid oxidant 56 in the order close to the nozzle 3. Thus, the solid oxidizer 56 and the non-combustible solid propellant 21 are provided alternately. Although polytetrafluoroethylene (PTFE) is used as the solid oxidant 56, a pressure-formed body of ammonium perchlorate alone may be used as another solid oxidant 56. Further, only one type of solid propellant 67 may be provided in the main body 65.
[0113]
In the case shown in FIG. 15, the combustion gas that has passed through the nozzle 3 from the combustion chamber 2 flows into the secondary combustion chamber 64. Since the combustion gas at this time still contains unburned fuel components, it burns with the solid oxidant 56 charged in the secondary combustion chamber 64. This improves combustion efficiency and increases propulsion performance. Further, the fuel burns with the non-combustible solid propellant 21, burns with the solid oxidant 56 and the like, and is ejected from the second nozzle 66. Thus, the amount of gas generated increases, and the thrust increases.
[0114]
In the case shown in FIG. 15, the target of combustion control by the laser L is the self-combustible solid propellant 22, and the solid oxidant 56 is disposed in the secondary combustion chamber 64. However, in the present invention, conversely, the solid oxidant 56 may be thermally decomposed by laser heating to cause a combustion reaction with the self-combustible propellant 22 loaded in the secondary combustion chamber 64. In the case shown in FIG. 15, when the combustion gas generated from the combustion chamber 2 is excessive in oxidant, the non-combustible solid propellant 21 and the solid oxidant 56 May be arranged alternately.
[0115]
According to the case shown in FIG. 15, the secondary combustion chamber 64 through which the combustion gas in the combustion chamber 2 passes is provided. A secondary solid propellant 67 is provided in the main body 65 of the secondary combustion chamber 64. Therefore, the combustion gas passed through the main body 65 of the secondary combustion chamber 64 burns the secondary solid propellant 67. Therefore, the amount of gas generated from the secondary nozzle 66 of the secondary combustion chamber 64 can be increased, and the thrust can be increased.
[0116]
In the case shown in FIG. 15, some of the solid propellants 21 and 22 are those in which the combustion gas is optically opaque and the laser L does not reach the surface of the solid propellant 9 or the solid propellant that easily flows into the cavity 23. Some produce combustion products. In such a case, the combustion chamber 2 is preferably made of only the solid oxidant 56 that generates an optically transparent gas, and the solid propellants 21 and 22 are preferably placed in the secondary combustion chamber 64.
[0117]
As described above, the difference between the solid fuel rocket 1 according to the type of the combustion chamber 2, the presence or absence of the secondary combustion chamber 64, and the type of the solid propellants 21 and 22 has been roughly described. 1 and Table 2 may be used.
[0118]
[Table 1]

[0119]
[Table 2]

Here, in addition to the above, an auxiliary fuel section 55 made of a solid oxidant 56 or the like is attached to the northern hemisphere 2a of the combustion chamber 2 in the type B combustion chamber 2.
[0120]
Next, a solid fuel rocket 1 according to a second embodiment of the present invention will be described with reference to FIG. In the solid fuel rocket 1 shown in FIG. 16, the entire propulsion chamber 2 is filled with the solid propellant 9 without providing the outer case 10. Further, in the present embodiment, the solid propellant 9 is burned by irradiating the solid propellant 9 with the laser L from the ignition unit 7 as in the first embodiment described above.
[0121]
Further, in the present embodiment, similarly to the above-described first embodiment, the solid propellant 9 is ignited by irradiating the laser L, and the intensity of the combustion gas, that is, the thrust is reduced by weakening the laser L. Increase or decrease. Further, in the present embodiment, the solid propellant 9 may be composed of a self-combustible solid propellant 22 or may be composed of a non-combustible solid propellant 21.
[0122]
When the solid propellant 9 is composed of the non-combustible solid propellant 21, the irradiation of the laser L is stopped and the solid propellant 9 is extinguished. Further, also in the present embodiment, when the pressure in the combustion chamber 2 measured by the pressure sensor 46 fluctuates, the laser unit 24 makes the laser L more or less intense so that the fluctuation of the pressure decreases.
[0123]
According to the present embodiment, similarly to the first embodiment described above, in the case of the non-combustible solid propellant 9, ignition, combustion, and fire extinguishing can be performed a plurality of times, and handling is easy and injection can be performed a plurality of times. The solid fuel rocket 1 can be obtained.
[0124]
Further, in the present invention, as the light source of the laser L, a high-output solid-state laser such as an Nd: YAG laser or a glass laser can be used in addition to the semiconductor laser 33.
[0125]
【The invention's effect】
As described above, according to the present invention, the solid propellant is ignited by irradiating the solid propellant with a laser, and the solid propellant stops the laser irradiation. Are also self-combustible to continue burning. Further, a measuring means for measuring the pressure in the combustion chamber is provided, and the intensity of the laser is controlled in accordance with the pressure in the combustion chamber measured by the measuring means. Further, when the pressure in the combustion chamber fluctuates, the irradiation means is provided with a control means for increasing or decreasing the intensity of the laser so as to reduce the fluctuation.
[0126]
For this reason, by controlling the intensity of the laser, it is possible to control the combustion of the solid propellant (eg, increase or decrease the thrust). Further, since the laser intensity is controlled so that the fluctuation of the pressure in the combustion chamber, that is, the fluctuation of the thrust is reduced, the solid propellant can be stably burned.
[0127]
According to the present invention as set forth in claim 2, the solid propellant is ignited by irradiating the solid propellant with a laser, and the solid propellant continues burning even when the laser irradiation is stopped. Sex. Further, a measuring means for measuring the pressure in the combustion chamber is provided, and the intensity of the laser is controlled in accordance with the pressure in the combustion chamber measured by the measuring means. Further, the solid propellant is irradiated with a laser having a strength at which the dynamic quenching phenomenon occurs, and the injection means injects water into the solid propellant.
[0128]
For this reason, by controlling the intensity of the laser, it is possible to control the combustion of the solid propellant (eg, increase or decrease the thrust). In addition, since the solid propellant is irradiated with a laser having an intensity at which the dynamic quenching phenomenon occurs, the flame generated by burning the solid propellant temporarily leaves the surface of the solid propellant. Therefore, on the surface of the solid propellant, the temperature rapidly decreases and the pressure decreases, and the solid propellant is extinguished.
[0129]
In addition, the solid propellant is irradiated with a laser having an intensity that causes a dynamic quenching phenomenon, and the jetting means jets water onto the solid propellant, so that the water is directed toward a flame temporarily separated from the surface of the solid propellant. Is injected. For this reason, the temperature of the above-mentioned flame falls sharply, and this flame can be prevented from re-igniting the solid propellant.
[0130]
Therefore, by controlling the intensity of the laser, it is possible to control the combustion of the solid propellant (such as increasing or decreasing the thrust). In the case of a non-combustible solid propellant, the fire can be extinguished. Therefore, the solid propellant can be ignited, burned and extinguished a plurality of times, and a solid fuel rocket that is easy to handle and can be injected a plurality of times can be obtained.
[0131]
According to the third aspect of the present invention, the solid propellant is ignited by irradiating the solid propellant with a laser, and the solid propellant continues burning even when the laser irradiation is stopped. Sex. Further, a measuring means for measuring the pressure in the combustion chamber is provided, and the intensity of the laser is controlled in accordance with the pressure in the combustion chamber measured by the measuring means. Further, when the pressure in the combustion chamber fluctuates, the irradiation means is provided with a control means for increasing or decreasing the intensity of the laser so as to reduce the fluctuation.
[0132]
Further, the solid propellant is irradiated with a laser having an intensity at which the dynamic quenching phenomenon occurs, and the jetting means jets water to the solid propellant. For this reason, the solid propellant is irradiated with a laser having an intensity that causes the dynamic quenching phenomenon, so that the flame generated by burning the solid propellant is temporarily separated from the surface of the solid propellant. Therefore, on the surface of the solid propellant, the temperature rapidly decreases and the pressure decreases, and the solid propellant is extinguished.
[0133]
In addition, the solid propellant is irradiated with a laser having an intensity that causes a dynamic quenching phenomenon, and the jetting means jets water onto the solid propellant, so that the water is directed toward a flame temporarily separated from the surface of the solid propellant. Is injected. For this reason, the temperature of the above-mentioned flame falls sharply, and this flame can be prevented from re-igniting the solid propellant.
[0134]
Therefore, by controlling the intensity of the laser, it is possible to control the combustion of the solid propellant (such as increasing or decreasing the thrust). Further, since the laser intensity is controlled so that the fluctuation of the pressure in the combustion chamber, that is, the fluctuation of the thrust is reduced, the solid propellant can be stably burned. Furthermore, fire extinguishing of the solid propellant can be performed. Therefore, the solid propellant can be ignited, burned and extinguished a plurality of times, and a solid fuel rocket that is easy to handle and can be injected a plurality of times can be obtained.
[0135]
According to the invention as set forth in claim 4, thrust is generated by irradiating the solid propellant with a laser, and the solid propellant becomes non-self-combustible to stop burning when the laser irradiation is stopped. ing. Therefore, by controlling the irradiation of the laser, ignition, combustion and extinguishing of the solid propellant can be performed a plurality of times. Therefore, it is possible to obtain a solid fuel rocket that is easy to handle and can be injected a plurality of times. Further, by controlling the intensity of the laser, combustion control of the solid propellant (increase or decrease in thrust) can be performed.
[0136]
According to the fifth aspect of the present invention, a measuring means for measuring the pressure in the combustion chamber is provided, and the intensity of the laser is controlled according to the pressure in the combustion chamber measured by the measuring means. Since the intensity of the laser is controlled in accordance with the pressure in the combustion chamber, a desired pressure in the combustion chamber, that is, a desired thrust can be obtained.
[Brief description of the drawings]
FIG. 1 is a plan view of a solid fuel rocket according to a first embodiment of the present invention.
FIG. 2 is a side view of the solid fuel rocket shown in FIG. 1 as viewed from the direction of arrow II.
FIG. 3 is a cross-sectional view taken along a line ABCDCEFHI in FIG. 1;
FIG. 4 is an explanatory diagram showing a configuration of an ignition portion and the like of the solid fuel rocket shown in FIG. 1;
FIG. 5 is a sectional view of a fuel part of the solid fuel rocket shown in FIG. 1;
FIG. 6 is an explanatory diagram illustrating a configuration of a gas supply unit and the like of the solid fuel rocket illustrated in FIG. 1;
FIG. 7 is an explanatory diagram showing a change in pressure when the solid propellant of the solid fuel rocket shown in FIG. 1 is burned.
FIG. 8A is an explanatory diagram showing a state in which a pressure fluctuation has occurred when the solid propellant of the solid fuel rocket shown in FIG. 1 is burned. FIG. 8B is an explanatory diagram illustrating the intensity of the laser that reduces the fluctuation at the time of FIG.
9 is an explanatory diagram showing conditions and the like when the solid propellant of the solid fuel rocket shown in FIG. 1 generates ignition, combustion, dynamic quenching, and the like.
FIG. 10 is an explanatory view schematically showing a state where a dynamic quenching phenomenon or the like has occurred in the solid fuel rocket shown in FIG. 1;
FIG. 11 is a plan view showing a modification of the combustion chamber of the solid fuel rocket shown in FIG.
12 is a cross-sectional view taken along the line abcdcefghhi in FIG.
FIG. 13 is a cross-sectional view showing a modified example of the fuel section of the solid fuel rocket shown in FIG.
FIG. 14 is a cross-sectional view showing another modified example of the solid fuel rocket shown in FIG. 1, such as a fuel section.
15 is a sectional view showing a secondary combustion chamber and the like attached to the solid fuel rocket shown in FIG.
FIG. 16 is a sectional view of a solid fuel rocket according to a second embodiment of the present invention.
[Explanation of symbols]
1 solid fuel rocket
2 Combustion chamber
3 nozzles
9 solid propellants
21 Non-combustible solid propellant
22 Self-combustible solid propellant
24 Laser unit (irradiation means)
46 Pressure sensor (measuring means)
47 control device (control means)
50 Water injection unit (injection means)

Claims (5)

A hollow combustion chamber,
A solid propellant positioned in the combustion chamber;
Irradiating means for irradiating the solid propellant with a laser to burn the solid propellant and generate combustion gas,
A nozzle that penetrates a wall surface of the combustion chamber and guides a combustion gas in the combustion chamber to outside the combustion chamber.
The solid propellant is a self-combustible solid propellant that continues burning even after stopping laser irradiation,
Measuring means for measuring the pressure in the combustion chamber,
Control means for controlling the irradiation means in accordance with the pressure in the combustion chamber measured by the measurement means,
The control means increases or decreases the intensity of the laser irradiated by the irradiation means to increase or decrease the generation amount of the combustion gas, and when the pressure in the combustion chamber measured by the measurement means fluctuates, the fluctuation of the pressure changes. A solid fuel rocket wherein the intensity of the laser is increased or decreased by the irradiation means so as to decrease the intensity. A hollow combustion chamber,
A solid propellant positioned in the combustion chamber;
Irradiating means for irradiating the solid propellant with a laser to burn the solid propellant and generate combustion gas,
A nozzle that penetrates a wall surface of the combustion chamber and guides a combustion gas in the combustion chamber to outside the combustion chamber.
The solid propellant is a self-combustible solid propellant that continues burning even after stopping laser irradiation,
Injection means for injecting water toward the solid propellant,
Control means for controlling the irradiation means and the injection means,
The control means increases or decreases the intensity of the combustion gas by increasing or decreasing the intensity of the laser irradiated by the irradiation means, and the control means sets the laser having the intensity at which the dynamic quenching phenomenon occurs in the irradiation means. A solid fuel rocket characterized in that after irradiating the solid propellant, water is jetted toward the solid propellant by the injection means. A hollow combustion chamber,
A solid propellant positioned in the combustion chamber;
Irradiating means for irradiating the solid propellant with a laser to burn the solid propellant and generate combustion gas,
A nozzle that penetrates a wall surface of the combustion chamber and guides a combustion gas in the combustion chamber to outside the combustion chamber.
The solid propellant is a self-combustible solid propellant that continues burning even after stopping laser irradiation,
Measuring means for measuring the pressure in the combustion chamber,
Injection means for injecting water toward the solid propellant,
Controlling the irradiation means according to the pressure in the combustion chamber measured by the measurement means, and control means for controlling the injection means,
The control means increases or decreases the intensity of the laser irradiated by the irradiation means to increase or decrease the generation amount of the combustion gas, and the fluctuation in the pressure decreases when the pressure in the combustion chamber measured by the measurement means fluctuates. After increasing or decreasing the intensity of the laser to the irradiating means, the control means irradiates the solid propellant with a laser having an intensity at which a dynamic quenching phenomenon occurs in the irradiating means, and then water is applied to the injecting means. A solid fuel rocket characterized by being ejected toward a solid propellant. A hollow combustion chamber,
A solid propellant positioned in the combustion chamber;
Irradiating means for irradiating the solid propellant with a laser to burn the solid propellant and generate combustion gas,
A nozzle that penetrates a wall surface of the combustion chamber and guides a combustion gas in the combustion chamber to outside the combustion chamber.
A solid fuel rocket, wherein the solid propellant is a non-combustible solid propellant that stops burning when the laser irradiation is stopped. Measuring means for measuring the pressure in the combustion chamber,
Control means for controlling the irradiation means in accordance with the pressure in the combustion chamber measured by the measurement means,
The control means increases or decreases the intensity of the laser irradiated by the irradiation means to increase or decrease the generation amount of the combustion gas, and stops the irradiation of the laser to the irradiation means to stop the combustion of the solid propellant. The solid fuel rocket according to claim 4, wherein

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