JPH0633731B2 - Ram rocket flame stabilizer - Google Patents

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flame holding device for storing a combustion flame of sustainer fuel in the front portion of a combustion chamber by disposing a baffle at a flame holding space forming position near the air injection port. Regarding

[0002]

2. Description of the Related Art A ram rocket removes outside air pressurized by ram pressure from an air injection port (hereinafter referred to as a port) at the front of a combustion chamber when the rocket is accelerated to a transonic speed after finishing booster propulsion. Since the fuel is injected and the sustainer fuel is injected and burned here, the injected fuel may be disturbed or diluted by the external air flow, and the combustion flame may cause so-called blowout. In order to prevent this, a flame holding space is often formed at the front of the combustion chamber to store the flame. JP-A-56-1
Japanese Patent No. 13032 discloses an example of this type of flame holding device, which will be described with reference to FIG. Reference numeral 1 is a motor case, 2 is a partition wall that divides the motor case into front and rear, and a combustion chamber 4 that doubles as a booster and a sustainer is formed behind the partition (right side in the drawing), and an insulator 3 is formed on the inner surface thereof.
After that, a booster propellant shown by a two-dot chain line is loaded here, and a rocket nozzle (not shown) is attached to the rear end of the combustion chamber 4. 6 is, for example, 4 attached to the outer periphery of the motor case 1.
The two diffusers open the front and communicate the rear end with the front of the combustion chamber 4 through the port 7,
Is initially closed by a port cover 8 indicated by a chain double-dashed line. Further, a sustainer propellant 9 is loaded in front of the partition wall 2, 10 is an igniter for igniting the sustainer propellant, 11 is a nozzle formed in the central portion of the partition wall 2, and 12 is a bowl having many injection holes. The injector has a shape, 13 is a baffle in the shape of a short tube surrounding the injector, and 14 is a flame holding space formed in the baffle.

This ram rocket blows off the port cover 8 by the explosive power or the internal pressure of the diffuser 6 when the booster propellant 5 is burned out, that is, when the booster propellant 5 is burned out and the combustion chamber 4 becomes empty. Is opened, and combustion gas is generated by the igniter 10 almost at the same time. Therefore, this fuel gas mixes with the injected air from the port 7 injected from the surrounding of the injector 12 through the nozzle 11 and burns, but the baffle 13 receives the direct hit of the injected air and enters the space 14. As a result of creating a relatively gentle atmosphere, the combustion flame is continuously stored in the space 14 and blowout can be prevented.

Yet another example is shown in US Pat. No. 2,987,875, which is illustrated by FIG.

Reference numeral 21 is a motor case, 22 is a sustainer fuel case concentrically installed in the motor case, and the diffuser 2 is provided between the cases 21 and 22.
3 is formed, and the rear of the rear end wall 24 of the fuel case 22 is defined as a combustion chamber 25, and the diffuser 23 is annularly opened (port 26) at the front end thereof. 27 is a sustainer propellant, 28 is a nozzle provided at the center of the rear end wall 24, and liquid fuel is also pressure-fed to this nozzle 28 from a fuel tank (not shown) through a pipe 29.

Reference numeral 30 denotes a baffle fixed to the motor case 21, which has annular through windows 31, 32 and a spreader 33 facing the nozzle 28 and forms a flame holding space 34 with the fuel case 24. Further, the diaphragm 35 is brought into contact with the rear surface of the baffle, and the diaphragm 36 can be tilted rearward by connecting the diaphragm 35 with the hinge 36.
A booster propellant 37 is loaded behind the diaphragm 35 to restrain the tilt.

This ram rocket has a booster propellant 37
When is burned, the diaphragm 35 is released from the restraint and tilted, and the transparent windows 31 and 32 are opened. On the other hand, the liquid fuel is mixed in the high temperature fuel gas from the sustainer propellant 27 in the nozzle 28 and ignited, and the flame thereof is spreader 33.
It is preserved in the central portion of the flame holding space 34 while being expanded by.

[0008]

By the way, in such a conventional ram rocket, since the flame holding space is fixedly formed, the loading position of the booster propellant has to be shifted rearward accordingly. In addition, there was a problem that the entire length of the rocket motor extended. Therefore, an object of the present invention is to solve the above problem by making it possible to load the booster propellant also in the flame holding space.

[0009]

Means for Solving the Problems In the present invention, the means for solving the above-mentioned problems is to dispose a baffle at a flame holding space forming position which is a portion in the vicinity of a plurality of air injection ports, thereby forming a front portion of a combustion chamber. In the flame holding device of the ram rocket that forms the flame holding space for holding the combustion flame of the sustainer fuel, the baffle has a plate shape that closes the air injection port, and from the closed position that closes the air injection port. The baffle is rotatably supported to the flame holding space forming position, the booster propellant is filled also in the space that should be the flame holding space with this baffle as the closing position, and the baffle is flame held from the closing position to the flame holding space when burning the sustainer fuel. That is, the flame holding space is formed by rotating to the space forming position.

[0010]

According to the above construction, the baffle at the closed position is supported by the booster propellant behind it, and its rotation is restricted.
When the propellant is burned out, the restraint is released, and the propellant rotates to the flame-holding space forming position. Therefore, the flame-holding space is formed only when the sustainer is propelled, which requires the booster space. It can be used as a propellant field loading space.

[0011]

1 and 2 show an embodiment of the present invention. In the drawing, 51 is a motor case, 52 is a partition wall, 54 is a combustion chamber, and 56 is four diffusers, and these constituent parts have substantially the same relationship as those of the same name in FIG.

Next, reference numeral 58 denotes a port cover which is integral with the motor case 51 and is formed by notching a portion for opening the port (57) by a notch 59. Reference numeral 60 denotes a baffle provided so as to correspond to each port cover 58. As shown in FIG. 2, a blade 61, a hinge arm 62, a hinge boss 63, and a blade 61 which are curved and formed so as to match the inner surfaces of the motor case 51 and the port cover 58. It consists of a stopper 64 standing upright from the hinge arm and hinge pin 65.
And the seal ring 66 are used to rotatably support the housing 67 provided at the rear of the diffuser. When the baffle 60 rotates from the position shown by the solid line to the position shown by the two-dot chain line 60 ', the stopper 64 comes into contact with the motor case 51 to prevent further rotation, and in this state the blade 61
Are exposed to the combustion chamber 54 from all directions, these blades 6
A flame holding space 68 is formed between the partition wall 1 and the partition wall 52. Then pull down the baffle (60 ') to remove the port cover 58.
When it is rotated until it comes into contact with the booster propellant 6
That is, 9 loading spaces are secured.

Reference numeral 70 denotes an insulator adhered as described above prior to the loading of the booster propellant 69, which is also applied to the inner surface of the baffle 60 in series so as to partition the operating portion with a notch, or as shown in FIG. As described above, it is desirable that another insulator 71 is attached to the baffle 60 so that the portion can be easily separated from the mother insulator.
This ram rocket uses liquid fuel for the sustainer. 75 is a fuel tank which stores this sustainer fuel under pressure, 76 is a nozzle for spraying the fuel into the diffuser 56, and 77 is the center of the partition wall 52. An igniter holder attached to the portion, 78 is a igniter for a booster which is detachably fixed to the rear portion of the holder by using a shear pin, 79 is an annular explosive for releasing the igniter 78, and 80 is an ignition for a sustainer. Reference numeral 81 is a flame injection hole of the igniter 80.

In the above structure, the booster propellant 69
Is burned off, the baffle 60 and the port cover 58 supported by the baffle 60 are released from the restraint by the propellant.
The port cover 58 is broken by the internal pressure of the diffuser 56 from the notch 59 to open the port 57, and the baffle 60 is caused by the air injected from this port to form the flame holding space 68 as described above. . Almost at the same time, the annular explosive 79 is detonated, the booster igniter 78 is released, and the flame injection hole 81 is opened.
Further, the sustainer fuel is sprayed from the nozzle 76 to form a mixture with the intake air, and then the sustainer igniter is operated to ignite the mixture.

[0015]

As described above, according to the present invention, the booster propellant can be loaded also in the flame holding space to be formed in the front portion of the combustion chamber, so that the amount of the propellant can be secured and the amount of the propellant can be increased. The total length can be shortened.

[Brief description of drawings]

FIG. 1 is a sectional view of an essential part of a ram rocket showing an embodiment of the present invention.

FIG. 2 is a perspective view of the baffle in the embodiment shown in FIG.

FIG. 3 is a sectional view of a main part of a conventional ram rocket.

FIG. 4 is a sectional view of a main part of a conventional ram rocket.

[Explanation of symbols]

 54 Combustion Chamber 57 Air Injection Port 60 Baffle 68 Flame Retaining Space 69 Booster Propellant 75 Liquid Sustainer Fuel Tank

 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Hajime Yamawaki 3-5-1 Momoi, Suginami-ku, Tokyo Nissan Motor Co., Ltd. Ogikubo office

Claims (1)

[Claims] 1. A ram rocket having a flame holding space for holding a combustion flame of a sustainer fuel formed in a front portion of a combustion chamber by arranging a baffle at a flame holding space forming position near a plurality of air injection ports. In the flame holding device, the baffle is formed into a plate shape that closes the air injection port, and is pivotally supported rotatably from the closed position where the air injection port is closed to the flame holding space forming position, and the baffle is closed. The flame-holding space of the ram rocket that forms a flame-holding space by filling the space that should be the flame-holding space with booster propellant and rotating the baffle from the closed position to the flame-holding space forming position during sustainer fuel combustion. apparatus.