JPH05195872A - Ram rocket - Google Patents

Abstract

PURPOSE:To provide a ram rocket which can maintain stable combustion even in case of change of an inflowing quantity and speed of air. CONSTITUTION:This is a ram rocket R with which outside air introduced from a diffuser 5 and ram fuel are mixed together in a combustion chamber 1 so as to continuously burn after taking off and accelerating it by means of a booster, and thrust is obtained by ejecting combustion gas. A plurality of air passages 11, 12 formed in the diffuser 5 are provided, and air introducing ports 17, 18 of respective air passages 11, 12 to open into the combustion chamber 1 are arranged so as to be shifted to each other in the axial direction of the rocket.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a ram rocket used as a flight thrust of a flying object.

[0002]

2. Description of the Related Art FIGS. 4 and 5 are a plan view and a sectional view showing a diffuser portion of a conventional ram rocket.

A ram rocket 100 shown in the figure is a combustion chamber 10
1, a fuel tank and a fuel injector 102 are provided on the head side, a jet nozzle (not shown) is provided on the tail of the combustion chamber 101, and a diffuser 1 for introducing outside air is provided on the side.
It has 03. The diffuser 103 has an air inlet 104 that is open on the head side and is opened on the tail side into the combustion chamber 101.
It is provided in four places.

The above-mentioned ram rocket 100 includes a combustion chamber 10
After starting and accelerating with a booster propellant loaded in No. 1 or another booster rocket, the outside air introduced from the diffuser 103 and the fuel injected from the fuel injector 102 are mixed in the combustion chamber 101 and continuously burned, and the combustion gas Thrust is obtained by ejecting from the jet nozzle.

Such a ram rocket is, for example, 19
The first of “Missile Engineering Encyclopedia” published by Hara Shobo in 1990
40 to 146.

[0006]

However, in the conventional ram rocket 100 as described above, the combustion chamber 10
Since the air introduction port 104 is provided only at the position closer to the head of No. 1, all the air compressed by the diffuser 103 flows uniformly from the head side to the tail side of the combustion chamber 101.

Therefore, the conventional ram rocket 100 is
There is no problem as long as the balance between the air inflow rate and velocity and the fuel is kept constant, but since the air inflow rate and velocity can change due to flight conditions, etc. There is a possibility that the influence is likely to occur and stable combustion is impaired.

[0008]

SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned conventional circumstances, and provides a ram rocket capable of sustaining stable combustion even when the inflow amount or velocity of air changes. The purpose is to do.

[0009]

According to a first aspect of the present invention, a ram rocket according to the present invention is started and accelerated by a booster, and then external air introduced from a diffuser and ram fuel are mixed in a combustion chamber and continuously burned. In a ram rocket that obtains thrust by ejecting combustion gas, a plurality of air flow paths formed by the diffuser are provided, and the air introduction ports of each air flow path that opens into the combustion chamber are arranged in the rocket plane axial direction. A ram rocket that obtains thrust by starting and accelerating by a booster, mixing external air introduced from a diffuser with ram fuel in a combustion chamber and continuously burning the fuel gas, and ejecting the combustion gas. A first partition wall and a second partition wall arranged in the rocket circumferential direction by providing a partition wall in the diffuser.
An air flow path is formed, and the partition walls are provided so as to be movable in the arrangement direction of both air flow paths, and the second air flow path is extended together with the partition walls in the rocket tail direction, and the downstream end parts of both air flow paths are formed. The air introduction port that opens into the combustion chamber is provided in the above, and these configurations are used as means for solving the conventional problems.

[0010]

In the ram rocket according to the present invention, in the first aspect, the air introduction ports of the plurality of air flow passages formed by the diffuser are arranged so as to be displaced in the axial direction of the rocket machine to disperse the introduced air. The combustion area is expanded in the direction of the rocket plane so that changes in the air inflow rate and velocity do not directly affect combustion.

Further, in claim 2, a movable partition wall is provided in the diffuser to form first and second air passages, and the second air passage is extended toward the tail of the rocket, and the first and second air passages are extended. By providing an air inlet at the downstream end of the second air flow path, the introduced air is dispersed to expand the combustion region in the rocket axis direction in the same manner as in claim 1, and the first partition is moved along with the movement of the partition wall. The cross-sectional areas of the first and second air flow paths and the opening area of each air introduction port are changed in inverse proportion to adjust the amount of introduced air from the head side and the tail side in order to stabilize combustion.

[0012]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment according to claims 1 and 2 of the present invention will be described below with reference to FIGS.

The ram rocket R shown in FIG. 3 is provided with a fuel tank 2 and a fuel injector 3 on the head side of the combustion chamber 1, and a jet nozzle 4 on the tail side of the combustion chamber 1 on the side. The part is provided with a plurality of diffusers 5 for introducing outside air. The fuel tank 2 is filled with a solid propellant having an excessive fuel composition or a liquid fuel. A payload mounting portion (not shown) is connected to the head of the fuel tank 2.

As shown in FIGS. 1 and 2, the diffuser 5 is provided with a cowling 6 having a square cross section and a ramp 7 for changing the flow passage area, and also has an air intake port 8 opened on the rocket head side. The movable partition wall 9 is provided inside to form first and second air passages 11 and 12 arranged in the circumferential direction of the rocket. The second air passage 12 is extended in the rocket tail direction together with the partition wall 9 and the cowling 6.

The cowling 6 includes a first segment 13 forming a first air passage 11 and a second air passage 1.
2 and the second segment 1 forming the second half of the cowling
It is composed of 4.

The first and second air flow passages 11 and 12 have curved portions 15 provided at the tails of the respective segments 13 and 14.
The direction of the air is changed by about 16 degrees by 16 and the air introduction port 1 which opens into the combustion chamber 1 is provided at the downstream end thereof.
7, 18 are provided. As a result, the two air introduction ports 17 and 18 are displaced from each other in the rocket machine axial direction.

The partition wall 9 has a first air passage 11 at the rear half thereof.
The air flow is blocked to the guide portions 19 and 20 and the air introduction ports 17 and 18 along the inner circumferences of the curved portions 15 and 16 of the segments 13 and 14 while forming a slightly bent side. The first and second air flow paths 1 are provided by a drive mechanism (not shown).
It can be moved in the arrangement direction of 1 and 12 (vertical direction in FIG. 2).

Here, the first and second air passages 11, 1
2 has a curved downstream end as described above,
The slope of the slope continuous to the downstream side of the ramp 7 is different,
The gradient of the air passage 11 is larger than that of the second passage 12. The partition wall 9 has a first shape different in this way.
-Move with the second air passages 11 and 12 separated from each other.

That is, in this embodiment, the first air passage 1
By extending the cross-sectional shape of 1 from the center of the diffuser 5 to the second air flow path 12 side, the partition wall 9 can be moved by the extended amount.

Further, when the partition wall 9 is located at the center as shown in FIG.
Since it is exposed inside and may disturb the air flow, the partition wall 9
In this case, a closing plate 23 for the recess is attached so as to match the slope of the second air flow path 2.

The ram rocket R having the above structure starts and accelerates by using the solid propellant loaded in the combustion chamber 1 or another solid rocket as a booster. When the solid propellant is used, the air inlets 17 and 18 are closed by detachable port covers, and detachable rocket nozzles are mounted inside the jet nozzle 4.

After the boost flight is completed, the ram rocket R injects ram fuel such as combustible gas or liquid fuel from the fuel injector 3 to mix the outside air introduced from the diffuser 5 with the ram fuel in the combustion chamber 1. Thrusting is obtained by ejecting the combustion gas from the jet nozzle 4 continuously.

Here, the ram rocket R compresses air in the first and second air passages 11 and 12 of the diffuser 5, respectively, and the air is introduced from the air inlet 17 on the head side and the air inlet 18 on the tail side. Since air is introduced into the combustion chamber 1 and the combustion region is expanded in the axial direction by dispersing the introduced air in this way, even if the inflow amount or velocity of air changes due to the flying state, The direct impact of these changes on combustion is extremely small.

Further, in the ram rocket R, by moving the partition wall 9, the partition wall 9 and each opening adjustment section 2 are moved.
1 and 22, the cross-sectional areas of the first and second air flow paths 11 and 12 and the opening areas of the air introduction ports 17 and 18 are changed in inverse proportion to each other, and the introduced air from the head side and the tail side is changed. Adjust the amount. As a result, combustion in the expanded combustion region becomes more stable.

In the case of a ram rocket provided with a plurality of diffusers, the air inlets of the air passages formed by the diffusers, that is, the air inlets of the diffusers may be arranged so as to be displaced in the rocket machine axial direction. Such a configuration is included in the scope of claim 1, and the above-described expansion of the combustion range can be realized.

[0026]

As described above, according to the ram rocket of the present invention, the combustion area in the combustion chamber can be expanded in the axial direction of the rocket by the structure of claim 1, so that the air condition can be increased depending on the flight condition. Even if there is a change in the inflow amount or speed, the direct effect of these changes on combustion can be minimized and stable combustion can be maintained.

Further, the ram rocket of the present invention is defined by claim 2.
With the above configuration, it is possible to adjust the amount of air introduced to the head side and the tail side together with the expansion of the combustion range described above, and it is possible to control so that the optimum air amount is obtained according to the flight state. Therefore, it is possible to further stabilize the combustion.

[Brief description of drawings]

FIG. 1 is a side sectional view showing a diffuser portion of a ram rocket in an embodiment of the present invention.

FIG. 2 is a horizontal sectional view of the diffuser shown in FIG.

FIG. 3 is a cross-sectional view illustrating the entire ram rocket.

FIG. 4 is a plan view of a diffuser portion of a conventional ram rocket.

5 is a side sectional view of the diffuser shown in FIG.

[Explanation of symbols]

 R Ram rocket 1 Combustion chamber 5 Diffuser 9 Partition wall 11 First air flow path 12 Second air flow path 17, 18 Air inlet

Claims (2)

[Claims] 1. In a ram rocket, after starting and accelerating by a booster, the outside air introduced from a diffuser and ram fuel are mixed in a combustion chamber for continuous combustion, and thrust is produced by ejecting the combustion gas, in the diffuser. A ram rocket characterized by comprising a plurality of air flow paths to be formed, and arranging the air introduction ports of each air flow path opening into the combustion chamber so as to be shifted in the axial direction of the rocket machine. 2. A ram rocket in which after propelling and accelerating by a booster, external air introduced from a diffuser and ram fuel are mixed in a combustion chamber for continuous combustion, and thrust is generated by ejecting the combustion gas, in the diffuser A partition wall to form first and second air passages arranged in the rocket circumferential direction, and the partition wall is movably provided in the arrangement direction of both air passages, and the second air passage is formed together with the partition wall. A ram rocket extending in the direction of the tail of the rocket and having an air inlet opening into the combustion chamber at the downstream end of both air flow paths.