JPH06299903A - Nozzle for ram rocket - Google Patents

Abstract

PURPOSE:To provide a nozzle for ram rocket which can eliminate danger for an own aircraft and following aircraft in the air and relax the restrictions on operation and design of the nozzle and the whole ram rocket. CONSTITUTION:In a nozzle for ram rocket which is provided with a booster nozzle which jets out combustion gas at the time of booster operation on the inner side of a ram nozzle which jets out combustion gas at the time of ram jet operation, the booster nozzle 22 is formed by high temperature dissipation material which dissipates after it is melted or burned out due to heat of combustion gas and a flow passage 33 which flows a cooling fluid is provided in the booster nozzle 22.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a ram rocket nozzle for use in a ram rocket which is operated by a propellant loaded in a ram combustor and then transferred to ramjet operation.

[0002]

2. Description of the Related Art As a nozzle for a ram rocket of this type, for example, there is one shown in FIG.

The illustrated ram rocket nozzle 100 is a ramjet nozzle 101 provided at the tail of a ram combustor.
A booster nozzle 104 is provided on the inner side of the booster by using a pyrotechnic-operated separating device 102 and other fixing members 103.
Is attached. The booster nozzle 10
4 is configured by combining various members in consideration of the strength and heat resistance of each part such as the convergent part C, the throat part T, and the divergent part D.

The above-mentioned ram rocket nozzle 100 is used in a ram rocket in which a solid propellant is loaded in a ram fuel device, and the combustion gas is ejected from the booster nozzle 104 during the operation of the booster for burning the solid propellant. . Upon completion of combustion of the solid propellant, the booster nozzle 104 is disengaged, and the introduced outside air and ram fuel are mixed and continuously burned by the ram combustor. During ram operation, the combustion gas is ejected from the ram nozzle 101. It will be.

Ram rocket nozzle 101 as described above
Are described, for example, in US Pat. No. 4,022,129.

[0006]

However, in the conventional ram rocket nozzle 100 as described above, since the booster nozzle 104 is disengaged after the booster is activated, for example, when the ram rocket is launched in the air, There is a risk that the booster nozzle 104 in the block state discharged to the vehicle will collide with its own aircraft and the following aircraft. In order to prevent this, the timing of the launch, the length of the combustion time of the booster propellant, etc. There were many restrictions on operation and design.

The conventional nozzle 100 for a ram rocket is also provided.
In addition, the booster nozzle 104 to be removed is required to have high heat resistance performance, and such a requirement is one of the factors that limit the design.

[0008]

SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned conventional circumstances, and eliminates the danger to the aircraft itself and the following aircraft in the air, and the operation and design of the nozzle and the ram rocket as a whole. It is an object of the present invention to provide a nozzle for a ram rocket that can relax the above restrictions.

[0009]

A ram rocket nozzle according to the present invention is provided with a booster nozzle for ejecting combustion gas during booster operation inside a ram nozzle for ejecting combustion gas during ramjet operation. In the nozzle for use, the booster nozzle is formed of a high temperature extinguishing material that disappears by melting or burning out due to the heat of the combustion gas, and the booster nozzle is provided with a flow path for circulating a cooling fluid, The above configuration is used as means for solving the problem.

[0010]

The nozzle for a ram rocket according to the present invention is provided with a cooling fluid passage in a booster nozzle formed of a high-temperature extinguishing material, so that the cooling fluid passage is cooled during the booster operation. A booster nozzle is cooled by circulating a fluid. Therefore, the booster nozzle can prevent burnout due to heat of the combustion gas without using a material having sufficient heat resistance.

Further, in the above-mentioned ram rocket nozzle, when the flow of the cooling fluid is stopped at the end of the booster operation, the heat of the combustion gas causes the booster nozzle to melt or burn out and disappear. Do not scatter in a blocked state.

[0012]

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

The ram rocket nozzle 1 is provided at the tail of the ram rocket R shown in FIG.

The ram rocket R is provided with a gas generator 4 on the head side of a ram combustor 3 formed by the outer cylinder 2, and a plurality of diffusers 5 for introducing outside air on the side part of the outer cylinder 2. The ram rocket nozzle 1 is provided inside the tail of the outer cylinder 2.

Inside the ram combustor 3, a solid booster propellant 6 is loaded. The gas generator 3 is
A payload mounting section (not shown) is connected to the head side, and an injection nozzle 7 is provided in the tail section.
It is loaded with a solid sustainer propellant 8 having an overburning composition. A partition wall 9 made of a burnable material is provided between the ram combustor 3 and the injection nozzle 7.

The diffuser 5 has an air intake port 10 that is open to the head side and communicates with the head-side portion of the ram combustor 3. The communication part between the diffuser 5 and the ram combustor 3 is temporarily closed by a port cover 11. Further, on the tail side of the diffuser 5, there is provided a storage section 12 for mounting a release device for the port cover 11 and a cooling fluid supply device described later.

The ram rocket nozzle 1 is, as shown in FIG. 1, a ram nozzle 2 fixed to the inside of the tail of an outer cylinder 2.
1 and a booster nozzle 22 provided inside thereof. The ram nozzle 21 is formed of a composite material or the like having sufficient heat resistance against combustion gas.

The booster nozzle 22 includes a nozzle body 31 forming a convergent portion C, a throat portion T and a divergent portion D, and a fixing block 32 which is fitted between the nozzle body 31 and the ram nozzle 21. It is made of plastic, which is a high-temperature extinguishing material that melts or burns out by the heat of combustion gas and disappears.

The nozzle body 31 is formed with a flow path 33 for circulating a cooling fluid. This flow path 33 is formed in a spiral shape from the inlet side to the outlet side of the nozzle, as shown by a part of the dotted line in FIG.

Further, connectors 34 and 35, which communicate with the flow path 33, are provided at the respective ends of the nozzle body 31 on the nozzle inlet side and the outlet side, and the connector 34 on the nozzle inlet side has a cooling fluid. Is connected to the nozzle outlet side connector 35, and a cooling fluid recovery pipe 37 is connected to the connector 35 on the nozzle outlet side.

Each of the pipes 36 and 37 has a heat-resistant coating on the outside, and is guided from the nozzle outlet to the outside of the outer cylinder 2 as shown in FIG. 2 to cool the inside of the housing portion 12 as described above. It is connected to a working fluid supply device.

As shown in FIG. 3, the above-mentioned supply device comprises a pressure vessel 41 filled with a pressurizing gas and a tank 43 filled with a cooling fluid 42. By pushing the piston 44 of
The cooling fluid 42 is pressurized and supplied to the supply pipe 36 side.
As the pressurizing gas, for example, nitrogen gas is used,
Liquid nitrogen, for example, is used as the cooling fluid. Further, the above-mentioned supply device naturally includes other control devices such as a valve mechanism.

Next, the operation of the ram rocket nozzle 1 will be described together with the motion of the ram rocket R.

The ram rocket R starts and accelerates by igniting the booster propellant 6. During this booster operation, the ram rocket nozzle 1 ejects the combustion gas generated by the combustion of the booster propellant 6 from the booster nozzle 22, while allowing the cooling fluid 42 to flow through the flow passage 33 to increase the booster nozzle 22. To prevent the booster nozzle 22 from being burnt out by the combustion gas.

Here, the cooling fluid 42 supply device collects the gas vaporized and expanded by the heat of the combustion gas in the pressure vessel 41 through the recovery pipe 37, and the actuators used in the ram rocket R ( It is designed to be used as the power source of A).

Then, when the combustion of the booster propellant 6 is completed, the ram rocket R burns the partition wall 9 of the head of the ram combustor, ignites the sustainer propellant 8, and removes the port cover 11. To do. As a result, the ram rocket R and the outside air introduced from the diffuser 5
Combustible gas as ram fuel produced by combustion of sustainer propellant 8 is mixed and continuously burned in ram combustor 3,
The ramjet is in operation.

At this time, in the nozzle 1 for the ram rocket,
When the combustion of the booster propellant 6 is completed, the supply of the cooling fluid 42 is stopped. As a result, in the ram rocket nozzle 1, the booster nozzle 22 made of a high temperature extinguishing material is melted and removed by the heat of the combustion gas, and the combustion gas during the ramjet operation is ejected from the ram nozzle 21.

As described above, in the ram rocket nozzle 1 of the above-described embodiment, the plastic booster nozzle 22 can be sufficiently adapted to the booster operation, and moreover, when the operation is changed to the ramjet operation. Since the booster nozzle 22 is melted and removed, there is almost nothing that scatters in the air in a block state, and there is no danger of causing danger to the own machine that fired the ram rocket R or the succeeding machine.

In the ram rocket nozzle according to the present invention, the material of the booster nozzle, the shape of the flow passage, etc. are not limited to those in the above-mentioned embodiment. In the case of forming in a shape, it is also possible to provide a plurality of the flow paths so as to enhance the cooling effect.

[0030]

As described above, according to the ram rocket nozzle of the present invention, when the booster operation is changed to the ramjet operation, the booster nozzle is extinguished at a high temperature by melting or burning out. There is almost nothing that scatters in a block state, and it is possible to eliminate the danger to the aircraft that launched the ram rocket and the following aircraft.

Further, since it is possible to sufficiently cope with the operation of the booster nozzle without using a material having sufficient heat resistance for the booster nozzle, it is possible to expand the kinds of materials applicable to the booster nozzle and to block the block. In order to avoid the danger of the booster nozzle discharged in the state, it is not necessary to take measures for the ram rocket itself (for example, adjusting the firing timing and the combustion time of the booster propellant), so that the operation of the nozzle and the ram rocket as a whole is eliminated. And design constraints can be greatly relaxed.

[Brief description of drawings]

FIG. 1 is a cross-sectional view illustrating a ram rocket nozzle according to an embodiment of the present invention.

FIG. 2 is a perspective view showing a part of an outlet side of a ram rocket nozzle.

FIG. 3 is a schematic explanatory view showing a cooling fluid supply device.

FIG. 4 is a cross-sectional view illustrating a ram rocket provided with the ram rocket nozzle shown in FIG. 1.

FIG. 5 is a cross-sectional view illustrating a conventional ram rocket nozzle.

[Explanation of symbols]

 R Ram rocket 1 Nozzle for Ram rocket 21 Ram nozzle 22 Booster nozzle 33 Flow path

 ─────────────────────────────────────────────────── ─── Continued Front Page (72) Inventor Akihiro Nakamura 3-5-1 Momoi, Suginami-ku, Tokyo Nissan Aerospace Engineering Co., Ltd.

Claims (1)

[Claims] 1. A nozzle for a ram rocket having a booster nozzle for ejecting combustion gas during booster operation inside a ram nozzle for ejecting combustion gas during ramjet operation, such as melting or burning due to heat of combustion gas. A nozzle for a ram rocket, characterized in that the booster nozzle is formed of a high-temperature extinguishing material that disappears as a result, and a channel for circulating a cooling fluid is provided in the booster nozzle.