JP3109781B2 - Ramjet - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a ramjet used for obtaining a flying thrust of a flying object.

[0002]

2. Description of the Related Art Conventionally, the above-mentioned ram jet includes:
For example, there is one shown in FIG.

A ramjet 51 shown in FIG. 3 has a main combustion chamber 53 loaded with a booster propellant 52, and a combustible gas generation chamber 55 loaded with a sustainer propellant 54. The combustible gas generation chamber 55 has a main combustion chamber 55. Provided in front of the chamber 53,
It communicates with the main combustion chamber 53 via a gas nozzle 56.

[0004] At the outer periphery of the front part of the main combustion chamber 53, air intakes 57 are provided at a plurality of circumferential locations. A port 53a for communicating the air intake 57 with the main combustion chamber 53 is provided with a nozzle / It is closed by a port cover 59 that can be opened by a port cover release mechanism 58.

At the front end of the main combustion chamber 53, there is a built-in combustion delay section 60 whose combustion speed is lower than that of the booster propellant 52. The combustion delay section 60 continuously burns even after the end of combustion of the booster propellant 52. , The combustible gas generated by the combustion of the sustainer propellant 54 and ejected from the gas nozzle 56 and the air intake 5
Combustion of the mixed gas with the external air introduced while being compressed from 7 (so-called secondary combustion) is performed continuously.

Further, a booster nozzle 62 having a booster propellant ignition device 61 is provided at the rear end of the main combustion chamber 53.
The ramjet nozzle 63 is provided concentrically via a separation joint 64 that is separated by the operation of the nozzle / port cover release mechanism 58.

On the other hand, in the gas generating chamber 53 loaded with the sustainer propellant 54, a sustainer propellant igniter 65 is provided.

A ramjet 51 having such a structure
In the above, the booster propellant 52 is burned in the main combustion chamber 53 by the ignition of the booster propellant igniter 61, and the combustion gas is injected from the booster nozzle 62 to obtain a thrust to start and accelerate.

Subsequently, at the end of combustion of the booster propellant 52, the nozzle / port cover releasing mechanism 58 is operated to
The booster nozzle 63 is separated at the separation joint 64 and the port cover 59 is removed.

At this time, the combustion is continued in the combustion delay section 60, while, in the combustible gas generating chamber 55, the sustainer propellant 54 is ignited by the sustainer propellant igniter 65. Combustible gas is generated.

Then, a mixed gas of the combustible gas ejected from the gas nozzle 56 and the air introduced and compressed through the air inlet 57 is ignited by the combustion delay section 60 and burns. The thrust is ejected from 63 to obtain thrust.

The above-described ramjet 51 is described in Japanese Patent Application Laid-Open No. 3-172563.

[0013]

However, in the above-described conventional ramjet 51, although a sufficient flying thrust can be obtained, the combustion delay section 60 is provided with the main combustion chamber 53.
Because the volume of the main combustion chamber 53 in which the booster propellant 52 is loaded must be increased at least by the volume of the combustion delay section 60, the weight increases accordingly. There is a problem that the degree of freedom in designing a flying object on which the ramjet 51 is mounted is narrowed, and solving this problem has been a conventional problem.

[0014]

SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned conventional problems, and is intended to increase the loading ratio of booster propellant, reduce the weight, and increase the degree of freedom in the design of a flying object. The aim is to provide a ramjet that is possible.

[0015]

SUMMARY OF THE INVENTION The present invention comprises a main combustion chamber loaded with a booster propellant, and a sustainer propellant which communicates with the main combustion chamber and burns after the end of the booster propellant combustion. A flammable gas generation chamber having a flammable gas generation chamber, wherein the flammable gas generated by the combustion of the sustainer propellant is mixed with air introduced from the outside in the main combustion chamber to burn the flammable gas. The combustible gas flow passage communicating with the main combustion chamber of the chamber, characterized in that it has a configuration provided with a combustion auxiliary agent that ignites by the combustible gas generated by the combustion of the sustainer propellant and generates a high-temperature gas, The configuration of the ramjet is used as means for solving the above-mentioned conventional problems.

In the ramjet according to the present invention,
The raw material composition of the booster propellant and the sustainer propellant is not particularly limited.

Further, the raw material used for the combustion aid which is ignited by the combustible gas generated by the combustion of the sustainer propellant to generate a high-temperature gas can be selected according to the raw material of the sustainer propellant, required combustion time, combustion energy and the like. For example, a composite propellant that uses aluminum perchlorate as an oxidizing agent while adding aluminum powder can be used.

Further, in some cases, it is possible to increase the loading amount of the sustainer propellant of the vehicle by adopting the same combustion aid as the sustainer propellant.

[0019]

In the ramjet according to the present invention, when the combustion of the booster propellant in the main combustion chamber ends and the sustainer propellant in the combustible gas generation chamber starts burning, the combustion auxiliary is ignited and burns.

Since the combustible gas generated by the combustion of the sustainer propellant and the high-temperature gas generated by the combustion of the combustion auxiliary mix into a mixed gas having high combustion energy, the mixed gas is ejected into the main combustion chamber. Then, combustion (secondary combustion) performed by mixing with compressed air introduced from the outside in the main combustion chamber is connected stably.

Therefore, since only the booster propellant needs to be loaded in the main combustion chamber, the volume of the main combustion chamber only needs to be adjusted to the required amount of the booster propellant, and the loading rate of the booster propellant increases. Thus, the weight can be reduced.

[0022]

DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described below with reference to the drawings.

FIGS. 1 and 2 show an embodiment of a ramjet according to the present invention.

As shown in FIG. 1, this ramjet 1
Has a main combustion chamber 3 loaded with a booster propellant 2 and a combustible gas generation chamber 5 loaded with a sustainer propellant 4.

The outer periphery of the front part of the main combustion chamber 3 is provided with air intakes 6 at a plurality of circumferential locations, and a port 3a for communicating the air intake 6 with the main combustion chamber 3 is provided with a nozzle 3 /
It is closed by a port cover 8 that can be opened by a port cover release mechanism 7.

At the rear end of the main combustion chamber 3, a booster nozzle 9 and a ram jet nozzle 10 are provided concentrically via a separation joint 11, and the booster nozzle 9 is provided with the nozzle / port cover releasing mechanism. Separation joint 1 by the operation of 7
1 is separated from the ram jet nozzle 10 by being separated in the centrifugal direction. The booster nozzle 9 has a booster propellant ignition device 12 at its center.
The booster propellant ignition device 12 is configured to be removed by combustion gas generated by combustion of the booster propellant 2 after ignition.

On the other hand, the combustible gas generation chamber 5 is provided in front of the main combustion chamber 3, and communicates with the main combustion chamber 3 via a gas flow path 5a. A combustible gas generated by the combustion of the sustainer propellant 4 is supplied to the gas passage 5a.
And a combustion auxiliary agent 13 that ignites and generates high-temperature gas when passing through the main combustion chamber 3. In this embodiment, the combustion adjuvant 13 is composed of an ammonium perchlorate-based composite propellant containing aluminum powder, and the combustion adjuvant 13 is provided in the main combustion chamber 3 of the gas passage 5a.
It is also provided inside the gas nozzle 14 provided on the side.

At the rear end of the combustible gas generating chamber 5, a sustainer propellant ignition device 15 is provided.

In the ramjet 1 having the above-described configuration, first, when the booster propellant 2 in the main combustion chamber 3 is ignited by the booster propellant igniter 12, the booster propellant 2 burns. When the gas is ejected from the booster nozzle 9 while removing the booster propellant ignition device 12, the flying object equipped with the ram jet 1 starts and accelerates until reaching the set Mach number required for the operation by the ram pressure. .

Subsequently, when the set Mach number is reached and the combustion of the booster propellant 2 ends, the separation joint 11 is separated by the operation of the nozzle / port cover releasing mechanism 7 as shown in FIG. The booster nozzle 9 is cut off and the port cover 8 is removed. At the same time, in the combustible gas generation chamber 5, the sustainer propellant 4 is ignited by the sustainer propellant igniter 15.

Next, when the sustainer propellant 4 burns and the combustible gas starts to move toward the main combustion chamber 3 through the gas flow path 5a, the combustion auxiliary 13 ignites and burns.

When the combustible gas generated by the combustion of the sustainer propellant 4 passes through the gas flow path 5a, the high-temperature gas generated by the combustion auxiliary 13 mixes into a mixed gas having high combustion energy. Thus, the mixed gas is injected from the gas nozzle 14 into the main combustion chamber 3, and the combustion (secondary combustion) performed by mixing with the compressed air introduced from the air inlet 6 is performed while being connected in a stable state. That is, the combustion gas generated by the combustion is supplied to the ram jet nozzle 10.
Thrust is generated by jetting from

As described above, the combustion aid 13 for continuously burning the mixed gas of the combustible gas generated by the combustion of the sustainer propellant 4 and the air introduced from the air inlet 6 while compressing the gas is supplied from the gas flow path. 5 a and the gas nozzle 14, the booster propellant 2 is provided inside the main combustion chamber 3.
Therefore, the loading rate of the booster propellant 2 in the main combustion chamber 3 increases, and the weight can be reduced.

The detailed configuration of the ramjet according to the present invention is not limited to the above-described embodiment.

[0035]

As described above, since the ramjet according to the present invention has the above-described structure, the loading rate of the booster propellant in the main combustion chamber is increased, and the weight can be reduced. This provides an extremely excellent effect that the degree of freedom in designing a flying object on which a ramjet is mounted can be increased.

[Brief description of the drawings]

FIG. 1 is an explanatory sectional view of a ramjet according to an embodiment of the present invention before a booster propellant is ignited.

FIG. 2 is an explanatory sectional view of the ramjet shown in FIG. 1 after the end of combustion of a booster propellant.

FIG. 3 is an explanatory sectional view of a conventional ramjet.

[Explanation of symbols]

 REFERENCE SIGNS LIST 1 ramjet 2 booster propellant 3 main combustion chamber 4 sustainer propellant 5 flammable gas generation chamber 5 a gas flow path 13 combustion aid

Continued on the front page (56) References JP-A-4-353250 (JP, A) JP-A-60-142033 (JP, A) JP-A-5-27258 (JP, U) (58) Fields investigated (Int) .Cl. ⁷ , DB name) F02K 9/78 F02K 7/10

Claims (1)

(57) [Claims] 1. A main combustion chamber loaded with a booster propellant;
A combustible gas generating chamber, which is connected to the main combustion chamber and is loaded with a sustainer propellant that burns following the end of the combustion of the booster propellant, wherein a combustible gas generated by combustion of the sustainer propellant in the main combustion chamber; In a ramjet that mixes and burns air introduced from the outside into the flammable gas flow passage that communicates with the main combustion chamber of the flammable gas generating chamber loaded with the sustainer propellant, the flammable gas is generated by combustion of the sustainer propellant. A ramjet characterized by having a combustion aid that ignites with combustible gas to generate high-temperature gas.