JPH0586980A - Liquid ram rocket - Google Patents

Abstract

PURPOSE:To obviate an ignition device and to maintain combustion in an excellent state by providing a combustion gas generating means to generate combustion gas for both ignition and stabilization of flame of fuel-air mixture to feed it in a combustion chamber, in a device having a combustion chamber to burn fuel-air mixture of liquid fuel and air. CONSTITUTION:A liquid ram rocket 1 has a combustion chamber 3 charged with a booster propellant 2. A booster nozzle 4 and a ram rocket nozzle 5 are concentrically arranged to the rear end part of the combustion chamber 3 through a separating coupling 6. The front side of the combustion chamber 3 is filled with liquid fuel 11 and a fuel tank 12 the size of which is reduced through pressurization, a flow rate control device 13, and a fuel injection valve 14 are provided. In this case, a gas generating chamber 17 filled with solid fuel 16 serving as a combustion gas generating means is located on a machine shaft on the front side of the combustion chamber 3. The chamber 17 is provided with an ignition device 18 for solid fuel and a gas injection nozzle 19 for both ignition and stabilization of flame, and combustion gas is injected in the combustion chamber 3 through the nozzle 19 to both ignite fuel-air mixture and stabilize flame.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a liquid ram rocket (ramjet) which produces flight thrust by burning a mixture produced by injecting liquid fuel droplets into the air introduced from the outside in a combustion chamber. Sometimes referred to as).

[0002]

2. Description of the Related Art Conventionally, as this type of liquid ram rocket, for example, there is one shown in FIG.

A liquid ram rocket 101 shown in FIG. 7 is equipped with a combustion chamber 103 for burning an air-fuel mixture produced by injecting droplets into the air introduced through air inlets 102 provided at a plurality of circumferential positions. A ram rocket nozzle 104 is provided at the rear end of the combustion chamber 103.

On the front side of the combustion chamber 103, a reducible tank 106 filled with the liquid fuel 105, a turbo pump 107 for feeding the liquid fuel 105 under pressure, and a liquid fuel 1
A flow rate control device 108 for controlling the flow rate of the fuel gas 05 and an injection valve 109 for injecting the liquid fuel 105 into the air intake 102 are provided, and the tank 106 is provided with the tube 11 for introducing air.
It is housed in a case 111 having 1a.

Further, an air-fuel mixture ignition device 110 is provided on the rear end side of the air intake 102.

Liquid lamb rocket 1 having such a structure
01 causes the liquid fuel 105 to flow out from the tank 106 that is compressed by the air that flows into the case 111 through the tube 111 a and contracts, and the liquid fuel 105 that is pressure-fed through the turbo pump 107 and the flow rate control device 108 is injected by the injection valve 109. To spray.

The ignition device 110 ignites a mixture of the injected droplets of the liquid fuel 105 and the air introduced from the air intake 102, and the combustion gas generated by the combustion of the mixture in the combustion chamber 103. Is generated from the ram rocket nozzle 104 by accelerating and ejecting it.

Regarding this type of ram rocket,
For example, there is a little explanation in "Additional Plate Aerospace Engineering Handbook" edited by the Japan Aerospace Society, April 25, 1983, published by Maruzen, pages 655 to 656.

[0009]

However, in such a conventional liquid ram rocket 101, the air intake 1
Ignition of the air-fuel mixture of the air introduced from 02 and the droplets of the liquid fuel 105 injected from the injection valve 109.
Combustion chamber 103 after ignition, though made by
Since the combustion in the interior is sustained only by the combustion energy of the air-fuel mixture itself, the air-fuel mixture flow velocity in the combustion chamber 103 is large and the pressure is high, especially when high altitude flight is used as the design standard. Since it is low, there is a problem that combustion may not continue due to changes in the amount of inflowing air.

Further, in the above liquid ram rocket 101, the air flowing from the tube 111a is used for the tank 106.
Although the liquid fuel 105 is made to flow out by pressing, the pressing by the inflowing air is not sufficient to pump the liquid fuel 105 to the injection valve 109. There is a problem that the turbo pump 107 that can withstand the conditions must be provided,
Resolving these problems has been a conventional problem.

[0011]

SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned conventional problems. In the invention of claim 1, the mixture can be ignited without the need for an ignition device and the combustion chamber can be ignited. The purpose of the present invention is to provide a liquid ram rocket capable of sustaining the combustion of the air-fuel mixture in a good condition, and particularly capable of sufficiently supporting a liquid ram rocket whose design standard is high altitude flight. According to the invention of Item 2, in the liquid ram rocket provided with the tank that can be reduced by pressurization, the air-fuel mixture can be ignited without the need for an ignition device, and the combustion of the air-fuel mixture in the combustion chamber is excellent. It is possible to maintain the liquid fuel for a long time, and by increasing the pressure applied to the tank, liquid fuel can be injected without using a turbo pump that has been conventionally required. An object of the present invention is to provide a liquid ram rocket capable of being pressure-fed by means of: a liquid ram rocket of the above-mentioned claim 2, wherein the air-fuel mixture is ignited and the air-fuel mixture is burned in the combustion chamber. An object of the present invention is to provide a liquid ram rocket capable of maximizing both the function of sustaining and the function of pressurizing the tank to pump liquid fuel.

[0012]

According to a first aspect of the present invention, in a liquid ram rocket having a combustion chamber for burning a mixture of liquid fuel droplets and air introduced from the outside, the mixture of the mixture is described. A combustion gas generating means for generating combustion gas for ignition and flame holding and supplying the combustion gas to the combustion chamber is provided, and a tank housed in a case so as to be contractible by pressurization is provided, and In a liquid ram rocket provided with a combustion chamber for burning a mixture of liquid fuel droplets filled in a tank and air introduced from the outside, a combustion gas for ignition and flame holding of the mixture is generated to perform the combustion. Combustion gas generating means for supplying the chamber is provided, and part of the combustion gas generated by the combustion gas generating means is introduced into the case so that the tank can be reduced by the pressure of the combustion gas. The combustion gas generating means and the case are communicated with each other, and the combustion gas generating means of the liquid ram rocket according to claim 2 is communicated with the case by a pipe, and the combustion gas in the pipe is discharged. It is characterized in that the pipe body is arranged in a coolable state, and the constitution of each of the liquid ram rockets is a means for solving the problems.

In the liquid ram rocket according to the present invention, the raw material composition of the liquid fuel for generating thrust is not particularly limited.

Further, both solid fuel and liquid fuel can be used for the combustion gas generating means, and as the solid fuel, for example, a small amount of metal is added to polysulfide or polybutadiene material used for high energy binder. Polybutadiene 6 used for inclusion and composite propellant
0 wt% + ammonium perchlorate 30 wt% + RDX1
It is possible to appropriately use a material having a low burning rate in which a small amount of a metal such as Zr is included in a material having a composition of 0% by weight,
On the other hand, as the liquid fuel, for example, hydrazine or ethylene oxide can be used in the case of one liquid, and dinitrogen tetraoxide + hydrazine or dinitrogen tetraoxide + monomethylhydrazine can be used in the case of two liquid.

Further, it is desirable that the combustion gas generating means is provided so as to supply the combustion gas to the front end portion of the combustion chamber near the circulation region of the mixture of the air introduced from the outside and the liquid fuel droplets.

[0016]

Since the liquid ram rocket according to the first aspect of the present invention has the above-mentioned structure, the ignition of the air-fuel mixture of the air introduced from the outside and the liquid fuel droplets can be performed without using an ignition device. In addition, the combustion gas supplied from the combustion gas generation means allows the combustion of the air-fuel mixture to continue favorably. Even if the air-fuel mixture has a high flow velocity and a low pressure in the room, problems such as blowout of combustion of the air-fuel mixture will not occur.

The liquid ram rocket according to claim 2 of the present invention has the above-mentioned structure, and therefore,
The liquid fuel in the tank is delivered at a high pressure because the same action as that of the liquid rocket relating to the above is brought about and a part of the combustion gas generated by the combustion gas generating means is introduced into the case. Therefore, the turbo pump is not required.

Further, since the liquid ram rocket according to claim 3 of the present invention has the above-mentioned structure, the combustion gas generated by the combustion gas generating means is supplied to the combustion chamber at a high temperature. It ensures the function of igniting and flame holding of the air-fuel mixture, while the heat of the combustion gas in the pipe is radiated to the surroundings while part of the combustion gas is introduced into the case through the pipe. Therefore, the combustion gas in the pipe is introduced into the case at a low temperature,
The situation is suitable for pressing the tank.

[0019]

【Example】

[First Embodiment] FIGS. 1 and 2 show an embodiment of a liquid ram rocket according to claims 1 and 2 of the present invention. The liquid ram rocket 1 is a combustion chamber loaded with a booster propellant 2. 3, a booster nozzle 4 and a ram rocket nozzle 5 are concentrically provided at the rear end of the combustion chamber 3 via a separation joint 6, and the booster nozzle 4 has an ignition device 7 for booster propellant. Is provided.

On the outer periphery of the front end side of the combustion chamber 3, there are provided air intakes 8 arranged at a plurality of positions in the circumferential direction, and a port cover 9 for closing the air intakes 8 is provided with a port cover release mechanism 10. It is supposed to be released by.

On the front side of the combustion chamber 3, the liquid fuel 1
1 and a fuel tank 12 that can be reduced by pressurization, and a flow rate control device 1 that controls the flow rate of the liquid fuel 11.
3 and an injection valve 1 for injecting liquid fuel 11 into the air intake 8
4, the fuel tank 12 is housed in a case 15 having a tube 15a for introducing air.

In this case, on the axle on the front side of the combustion chamber 3, there is provided a gas generating chamber 17 filled with the solid fuel 16 as a combustion gas generating means. This gas generation chamber 17
Is provided with an ignition device 18 for solid fuel that ignites the solid fuel 16, and an ignition / flame holding gas injection nozzle 19 provided integrally with the gas generation chamber 17 The flame holding gas injection nozzle 19 includes a partition wall 20.
So as to project into the combustion chamber 3.

A gas supply device 21 is provided in the gas generation chamber 17 adjacent to the case 15, and a part of the combustion gas generated by the combustion of the solid fuel 16 is supplied to the case via the gas supply device 21. It is designed to be installed in 15.

In the liquid ram rocket 1 having such a structure, when the booster propellant 2 is ignited by the booster propellant ignition device 7, the booster propellant 2 is burned in the combustion chamber 3 and the combustion gas is boosted. It starts and accelerates by jetting from the nozzle 4.

Subsequently, at the end of combustion of the booster propellant 2, the booster nozzle 4 is separated at the separation joint 6 and the port cover 9 of the air intake 8 is removed by the port cover release mechanism 10 as shown in FIG. The liquid fuel 11 is ejected from the injection valve 14 in the form of liquid droplets.

At the same time, the solid fuel 16 is ignited by the solid fuel igniter 18, and a mixture of the air introduced from the air inlet 8 and the droplets of the liquid fuel 11 injected from the injection valve 14 is mixed. The ignition gas is ignited by the combustion gas generated by the combustion of the solid fuel 16 ejected from the ignition and flame holding gas injection nozzle 19, and the combustion gas for generating the thrust generated by the combustion of the air-fuel mixture in the combustion chamber 3 is ram rocket. Thrust is obtained by accelerating and ejecting from the nozzle 5.

At this time, since the combustion gas generated by the combustion of the solid fuel 16 is continuously ejected from the ignition and flame holding gas injection nozzle 19 to the front end portion of the combustion chamber 3, the air and the liquid are discharged. Even after the initial ignition of the air-fuel mixture with the liquid droplets of the fuel 11, the air-fuel mixture is burned not only by its combustion energy but also by the combustion gas ejected from the ignition / flame holding gas injection nozzle 19. Is maintained well, and even when the gas flow velocity in the combustion chamber 3 is high and the pressure is low as in the case where high-altitude flight is used as the design standard, the air-fuel mixture is not blown out and the like. Combustion will be well sustained.

Further, since a part of the combustion gas generated by the combustion of the solid fuel 16 is introduced into the case 15 by the gas supply device 21, the fuel tank 12 is pressed at a high pressure, and the fuel tank 12 is pressed. Liquid fuel in 12
Will be pumped to the injection valve 14 without the need for a turbo pump.

[Second Embodiment] FIG. 3 shows another embodiment of the liquid ram rocket according to claims 1 and 2 of the present invention, and a liquid ram rocket 31 according to this embodiment.
However, the difference from the liquid ram rocket 1 according to the first embodiment is that the liquid fuel 32 filled in the tank 33 is used as the combustion gas generating means.

Therefore, in this liquid ram rocket 31 in which the rear end side of the combustion chamber 3 is omitted in FIG. 3, after the combustion of the booster propellant (2) is completed, the air and the fuel tank introduced from the outside are supplied. Ignition of an air-fuel mixture with droplets of the liquid fuel 11 fed from 12 is performed by the combustion gas generated by the combustion of the liquid fuel 32 as the combustion gas generation means that has flowed out from the tank 33, and further initial ignition is performed. Since this combustion gas is also injected from the ignition / flame holding gas injection nozzle 19 after that, the combustion of the air-fuel mixture is favorably maintained.

Further, since a part of the combustion gas is introduced into the case 15 by the gas supply device 21, the fuel tank 12 is pressed with a high pressure, and the liquid fuel 11 in the fuel tank 12 is It will be pumped to the injection valve 14 without the need for a turbo pump.

[Third Embodiment] FIG. 4 shows claims 1 and 2 of the present invention.
1 shows an embodiment of a liquid ram rocket according to claims 2 and 3, and this liquid ram rocket shows a modification of the liquid ram rocket 1 shown in FIGS. 1 and 2, and has the same function. The same reference numerals are attached to the parts.

The liquid ram rocket 41 shown in FIG.
A gas generation chamber 43, which is filled with the solid fuel 42 as a combustion gas generation means and has an ignition device 46 for the solid fuel, is provided at the rear end side of the air intake 8, and the gas generation chamber 43 is integrally provided with the ignition and The flame holding gas injection nozzle 44 is projected near the rear end of the air intake 8, and the gas generation chamber 43 and the case 4 are
7 and 7 are communicated with each other through a gas supply pipe 45 arranged outside the outer shell 48.

In this liquid ram rocket 41, the solid fuel 42 is ignited by the solid fuel igniter 46 at the end of the combustion of the booster propellant (2), and the air and the liquid fuel 11 introduced from the outside are ignited. The mixture gas with the liquid droplets is ignited by the combustion gas generated by the combustion of the solid fuel 42 injected from the ignition and flame holding gas injection nozzle 44, and the mixture gas is burned in the combustion chamber 3.

Also in this case, since the combustion gas generated by the combustion of the solid fuel 42 continues to be ejected from the ignition and flame holding gas injection nozzle 44 to the portion near the front end of the combustion chamber 3, Even after the initial ignition of the air-fuel mixture, the air-fuel mixture is well connected not only with its own combustion energy but also with the combustion gas ejected from the ignition / flame holding gas injection nozzle 44.

Further, since a part of the combustion gas generated by the combustion of the solid fuel 42 is introduced into the case 47 through the gas supply pipe 45, a high pressure is applied to the fuel tank 12 and the liquid The fuel 11 is pressure-fed to the injection valve 14 without using a turbo pump.

At this time, since the gas supply pipe 45 is exposed to the outside, the high temperature combustion gas passing through the gas supply pipe 45 is cooled by the ambient air, so that the combustion gas is stored in the case 47. When it is introduced into the case 47, it becomes a low-temperature gas, so that it becomes a more preferable condition to press the fuel tank 12 in the case 47.

In the liquid ram rocket 41 according to this embodiment, since the gas generating chamber 43 is provided on the rear end side of the air intake port 8, the fuel tank 12 can be filled with more liquid fuel 11.

[Fourth Embodiment] FIG. 5 shows claims 1 and 2 of the present invention.
Another embodiment of the liquid ram rocket according to claims 2 and 3 is shown, and this liquid ram rocket also shows a modification of the liquid ram rocket shown in FIGS. 1 and 2. In this case as well, parts having the same functions are assigned the same reference numerals and explanations thereof are omitted.

In the liquid ram rocket 51 shown in FIG. 5 with the rear end side of the combustion chamber 3 omitted, a tank 56 filled with the liquid fuel 52 as a combustion gas generating means is provided at the rear end side of the air intake port 8. The liquid fuel 52 in the tank 56 is supplied to the gas generating chamber 53 via the tube 54, and the gas generating chamber 53 and the case 57 are arranged outside the outer shell 58. It is configured to communicate via.

In the liquid ram rocket 51, after the combustion of the booster propellant (2) is completed, the combustion gas generated by the combustion of the liquid fuel 52 fed from the tank 56 through the tube 54 is ignited and flame-retarded. By injecting from the gas injection nozzle 19, the mixture of the air introduced from the outside and the droplets of the liquid fuel 11 fed from the fuel tank 12 is ignited.

At this time, since the pre-combustion gas is continuously ejected from the ignition and flame holding gas injection nozzle 19 even after the initial ignition, the combustion of the air-fuel mixture in the combustion chamber 3 is well connected. It will be.

Since a part of the combustion gas is introduced into the case 57 through the gas supply pipe 55, the fuel tank 12 is pressed at a high pressure, and the liquid fuel 11 is a turbo pump. The fuel is delivered to the injection valve 14 without using it.

In addition, also in this embodiment, since the gas supply pipe 55 is exposed to the outside, the combustion gas introduced into the case 57 becomes a low temperature gas, and the fuel tank 12 in the case 57 has a low temperature. Pressurization will be performed in a more suitable state.

The liquid ram rocket 51 of this embodiment is also used.
Then, since the tank 56 filled with the liquid fuel 52 is provided on the rear end side of the air intake port 8, the fuel filling rate of the fuel tank 12 becomes excellent.

[Fifth Embodiment] FIG. 6 shows claims 1 and 2 of the present invention.
It shows still another embodiment of the liquid ram rocket according to claims 2 and 3, and shows a modified example of the liquid ram rocket 1 shown in FIGS. 1 and 2, which has the same function. The same reference numerals are given to the parts and the description thereof will be omitted.

In the liquid ram rocket 61 shown in FIG. 6, a filter 62 is provided in the gas generating chamber 17 filled with the solid fuel 16 as a combustion gas generating means, and the filter 6 is also provided.
The second portion and the case 67 for accommodating the fuel tank 12 are communicated with each other through a gas supply pipe 65 arranged outside the outer shell 68, and further, a delivery device provided between the flow rate control device 13 and the injection valve 14. A portion of the gas feed pipe 65 located inside the outer shell 68 is wound around the feed pipe 64 a plurality of times.

In the liquid ram rocket 61 having such a configuration, the ignition of the air-fuel mixture of the air introduced from the outside and the droplets of the liquid fuel 11 fed from the fuel tank 12 is caused by the combustion of the solid fuel 16. Done by burning combustion gas.

Since the combustion gas continues to be injected from the ignition and flame holding gas injection nozzle 19 to the air-fuel mixture after the initial ignition, the air-fuel mixture is satisfactorily connected.

In this case, the gas injection nozzle 1 for ignition and flame holding
Since the combustion gas injected from 9 has a high temperature, ignition and flame holding of the air-fuel mixture by this combustion gas can be reliably performed.

Further, since a part of the combustion gas is introduced into the case 67 through the gas supply pipe 65, a high pressure is applied to the fuel tank 12 and the liquid fuel 1
1 will be pumped to the injection valve 14 without the need for a turbo pump.

At this time, a part of the gas supply pipe 65 is wound around the feed pipe 64, and the gas supply pipe 6
Since the other parts of 5 are exposed to the outside,
The combustion gas passing through the gas supply pipe 65 at a high temperature is cooled by the liquid fuel 11 fed through the feed pipe 64, and is also cooled outside by the air. When introduced into the case 67, the gas becomes a low temperature gas, and therefore, the state is more suitable for pressing the fuel tank 12 in the case 67.

In the liquid ram rocket 61 according to this embodiment, the gas generating chamber 17 is provided with the filter 62, but the invention is not limited to this.
The filter 62 may not be provided depending on the raw material used for No. 6.

[0054]

As described above, in the liquid ram rocket according to the first aspect of the present invention, the combustion gas for igniting and holding flame of the air-fuel mixture with the air in which the liquid fuel droplets are introduced from the outside is used. Since the combustion gas generating means for generating and supplying the mixture to the combustion chamber is provided, the mixture can be ignited without using an ignition device, and the combustion of the mixture in the combustion chamber is well connected. It is possible to carry out the above-mentioned operation, and particularly, it is possible to sufficiently cope with a liquid ram rocket whose design standard is high-altitude flight.

A liquid ram rocket according to a second aspect of the present invention is provided with a tank housed in a case so as to be contractible by pressurization, and liquid fuel droplets filled in the tank and air introduced from the outside. And a combustion gas generating means for generating combustion gas for ignition and flame holding of the air-fuel mixture and feeding the mixture gas into the combustion chamber, and the combustion gas generating means and the case being in communication with each other. In addition to being able to satisfactorily ignite air and hold flames, it is possible to press the tank at a high pressure, so that liquid fuel can be pumped without using a turbo pump, which was conventionally required. It has a very good effect that it can.

Further, in the liquid ram rocket according to claim 3 of the present invention, the combustion gas generating means of the liquid ram rocket according to claim 2 and the case are connected by a pipe, and the combustion gas in the pipe can be cooled. Since this pipe is arranged, the ignition and flame holding of the mixture can be reliably performed by the combustion gas generated by the combustion gas generating means, and a low temperature gas can be stored in the case. Since it can be introduced, there is an extremely excellent effect that the pressurization of the fuel tank can be performed in a more suitable state.

[Brief description of drawings]

FIG. 1 is a sectional explanatory view showing an embodiment of a liquid ram rocket according to claim 1 and claim 2 of the present invention.

FIG. 2 is a cross-sectional explanatory view showing a state of a booster propellant combustion end stage of the liquid ram rocket of FIG.

FIG. 3 is a cross-sectional explanatory view showing the state of the final stage of combustion of booster propellant in a liquid ram rocket according to another embodiment of claims 1 and 2 of the present invention.

FIG. 4 is a cross-sectional explanatory view showing the state of the final stage of combustion of booster propellant in a liquid ram rocket according to an embodiment of claim 1, claim 2 and claim 3 of the present invention.

FIG. 5 is a cross-sectional explanatory view showing the state of the final stage of combustion of booster propellant in a liquid ram rocket according to another embodiment of claim 1, claim 2 and claim 3 of the present invention.

FIG. 6 is a cross-sectional explanatory view showing a final stage of combustion of booster propellant in a liquid ram rocket according to still another embodiment of claims 1, 2 and 3 of the present invention.

FIG. 7 is a cross-sectional explanatory view of a conventional liquid ram rocket.

[Explanation of symbols]

 1 31 41 51 61 Liquid Lamb Rocket 3 Combustion Chamber 11 Liquid Fuel 12 Fuel Tank 15 47 57 67 Case 16 42 Solid Fuel (Combustion Gas Generation Means) 32 52 Liquid Fuel (Combustion Gas Generation Means) 45 55 65 Gas Supply Pipe (Pipe) body)

Front page continued (72) Inventor Minoru Mitsuno 2 Takaracho, Kanagawa-ku, Yokohama, Kanagawa Nissan Motor Co., Ltd. (72) Takao Kuwahara, 2 Takara-cho, Kanagawa-ku, Yokohama, Kanagawa Nissan Motor Co., Ltd.

Claims (3)

[Claims] 1. A liquid ram rocket provided with a combustion chamber for burning a mixture of liquid fuel droplets and air introduced from the outside, in which a combustion gas for igniting and holding flame of the mixture is generated. A liquid ram rocket, characterized in that it is provided with a combustion gas generating means for supplying it into the combustion chamber. 2. A liquid comprising a tank housed in a case so as to be contractible by pressurization, and a combustion chamber for burning a mixture of liquid fuel droplets filled in the tank and air introduced from the outside. In the ram rocket, a combustion gas generating means for generating combustion gas for ignition and flame holding of the air-fuel mixture and supplying the combustion gas to the combustion chamber is provided, and part of the combustion gas generated by the combustion gas generating means is provided in the case A liquid ram rocket, characterized in that the combustion gas generating means and the case are communicated with each other so that the tank can be reduced by the pressure of the combustion gas by being introduced into. 3. The liquid ram rocket according to claim 2, wherein the combustion gas generating means and the case are connected by a pipe, and the combustion gas in the pipe can be cooled so that the pipe is arranged. Characteristic liquid ram rocket.