JP2691092B2 - Booster internal ramjet engine - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a booster internal ramjet engine applied to a propulsion device for a supersonic flying vehicle.

[0002]

2. Description of the Related Art FIG. 3 shows a conventional example of a booster-incorporated ramjet engine.

A conventional booster-equipped ramjet engine includes a booster propellant 2, a combustor 3, a ramjet exhaust nozzle 4, a fuel nozzle 5, a ramjet ignition device 6,
It comprises a port cover 7, a booster exhaust nozzle 8 and a booster ignition device 9. The air intake duct 10 and the fuel tank 11 are combined with these components to form a propulsion device,
It is arranged at the rear of the flying body 1.

When the booster propellant 2 is ignited by the booster ignition device 9, the projectile 1 acts as a solid rocket and is accelerated to supersonic speed. When all of the booster propellant 2 is burned out, the pressure of the air that tries to forcefully flow into the air intake duct 10 from the front overcomes the pressure in the combustion chamber that is lowered by the burnout of the booster propellant 2, and the port cover 7 is removed. Automatically separated and air is combustor 3
Begins to flow in. The mounting portion of the booster exhaust nozzle 8 is also blown up and is discharged rearward together with the port cover 7.
After discharge, the fuel nozzle 5 attached to the air intake duct 10
When the liquid fuel is sprayed into the air stream from the ramjet ignition device 6 and ignited by the ramjet ignition device 6, the high-temperature gas generated in the combustor 3 is ejected backward at a high speed through the ramjet exhaust nozzle 4 to move forward. Even if the ramjet ignition device 6 is stopped after that, the ramjet engine operates.

Further, as another example of the port cover, there is also a type of igniting and crushing explosives embedded in a mesh shape on the surface of the port cover and discharging the explosive. As for non-emission type, louver type and butterfly valve type have been studied, but there are many problems to put them into practical use.

[0006]

The conventional booster-internal type ramjet engine has the following problems to be solved.

That is, a flying body 1 equipped with the propulsion device of FIG.
Is launched from an aircraft, the booster propellant 2 burns out after a few seconds and the port cover 7 is released, so that the port cover 7 may collide with the launching mother machine, which is extremely dangerous. In addition, when the mother aircraft flying in a formation are continuously fired, it is difficult to avoid the port cover 7, which further increases the risk.

[0008] In some types of non-emission type port covers that have been studied, it takes time to disturb the flow of air flowing into the combustor, to cause pressure loss, to open, and to reduce the operating time. There were problems such as being slow and affecting the gas flow in the combustor.

In order to solve the above problems, the present invention has an object of providing a booster built-in type ramjet engine in which the port cover portion is formed of a ball valve and no foreign matter is discharged when the valve is opened. .

[0010]

Means for Solving the Problems As a means for solving the above problems, the present invention introduces air from an air intake duct adjacent to the forward side after the combustion of a booster propellant installed in a combustor and finishes combustion. In a ramjet engine with built-in booster that burns fuel and maintains thrust, a ball valve that opens and closes between the air intake duct and the combustor, and the ball valve in the closed state are interlocked by the combustion gas pressure of explosives, etc. It is intended to provide a booster-internal ramjet engine characterized by comprising a valve opening means that opens through the booster.

[0011]

The present invention is configured as described above and has the following effects.

That is, since the ball valve opens and closes the space between the air intake duct and the combustor, nothing is released by opening the valve, and there is no risk of damaging the inside of the combustor or the succeeding mother machine.

Further, there is no obstacle that disturbs the air flow in the air flow path from the air intake duct to the combustor.

[0014]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of the present invention will be described with reference to FIGS. FIG. 1 is a side sectional view of a flying vehicle equipped with a booster internal type ramjet engine according to the present embodiment, and FIG. 2 is a view of the vicinity of the ball valve 16 of FIG. 1 seen from above. The same components as those in FIG. 3 of the conventional example are designated by the same reference numerals, and the description thereof will be omitted.

In both figures, a ball valve 16 which opens and closes the communication between the air intake duct 10 and the combustor 3 by rotating about an axis 15 is provided between the air intake duct 10 and the combustor 3. It is provided. The ball valve 16 is provided with a shaft 15 protruding from the outer periphery and also serving as a pinion. A rack 14 meshes with the shaft 15 and a cartridge filled with explosives through a cylinder 13 that moves by gas pressure. 12 is connected and supported. The cartridge 12 is fixed to the machine body side. Other configurations are the same as the conventional example.

Next, the operation of the above configuration will be described. After the booster propellant 2 is ignited and the projectile 1 enters the flight, when the booster propellant 2 is burned out, the cartridge 12 is ignited by means not shown, the explosive is instantly burned, and the combustion gas presses the cylinder 13. , Rack 14
Is pushed to the right in FIG. 2, that is, backward. Then, the shaft 15 meshing with the rack 14 rotates in the direction of the arrow in the figure to open the ball valve 16, and the air compressed in the air intake duct 10 by the dynamic pressure of flight changes the air pressure in the combustor 3.
Flows into. After that, fuel is injected from the fuel nozzle 5 as in the conventional case, the ramjet igniter 6 is activated to ignite the fuel, and the fuel is burned in the combustor 3.

In the present embodiment, the shaft 15 and the rack 14 that form a pinion for the rotation of the ball valve 16 are used as the interlocking device, but the interlocking device is not limited to the pinion and the rack. A link device may be provided in which an arm is provided so as to project in the vertical direction and the rack 14 is replaced with a connecting rod of the cylinder 13 to connect the arm and the connecting rod. Any device may be used. The drive source that pushes the rack 14 is not limited to explosives, and a high pressure gas prepared in advance may be used, or a gas generated by another chemical reaction or the like may be used.

As described above, according to the present embodiment, when the air is introduced from the air intake duct 10 into the combustor 3, it is close to the boundary between the air intake duct 10 and the combustor 3 like a conventional port cover. There is nothing released from the
It has the advantage that there is no danger of the emissions colliding with the launching aircraft.

Further, the ball valve 16 fully opens the air flow passage by rotation and does not cause any obstacle in the air flow passage, so that the flow of the air flowing into the combustor 3 is disturbed,
There is an advantage that pressure loss is not caused.

Further, since the ball valve 16 is instantly opened by the operation of the cartridge 12, there is an advantage that a trouble such as a delay in opening the valve does not occur.

[0021]

The present invention has the following effects because it is configured as described above.

That is, since the ball valve is a non-releasing type, the safety of the mother machine is improved and no pressure loss occurs.
As a result, engine performance is better than other non-emission types.
Further, since the flow of air and combustion gas is not disturbed, stable combustion can be obtained. Further, since the port cover of the present invention has almost no area exposed to the combustion gas in the open state, the heat resistance problem is not so severe. When the flying object has a large number of port covers, one cartridge can be driven at the same time, so that the size and weight can be reduced and the flying distance can be increased.

[Brief description of the drawings]

FIG. 1 is a side sectional view of one embodiment of the present invention.

2 is a partially enlarged view of the main part of FIG. 1 seen from above,

FIG. 3 is a side sectional view of a conventional example.

[Explanation of symbols]

 1 Flying Body 2 Booster Propellant 3 Combustor 5 Fuel Nozzle 6 Ramjet Ignition Device 10 Air Intake Duct 11 Fuel Tank 12 Cartridge 13 Cylinder 14 Rack 15 Shaft 16 Ball Valve

Claims (1)

(57) [Claims] 1. A booster-internal ramjet engine for maintaining thrust by taking in air from an air intake duct adjacent to the forward side to burn fuel after the booster propellant inside the combustor has finished burning. A ball valve that opens and closes between the air intake duct and the combustor, and a valve opening means that opens the ball valve in a closed state through an interlocking device by the combustion gas pressure of explosive powder or the like. Ramjet engine with built-in booster.