JP2009013944A - Ram rocket - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To remove a port cover from a port with a lighter and simpler structure, with improving reliability without mounting a port cover removing device using an explosive device. <P>SOLUTION: In a ram rocket having a primary combustor 30 including an injection nozzle 31 jetting fuel gas and a secondary combustor 40 filled with a propellant and having a port 41 for taking in compressed air from an outside into an inside opened and formed thereon and loading propellant for a booster arranged mutually back and forth in a flying direction (a), and blocking the port 41 by the port cover 47 until completion of combustion of the propellant 44 for the booster in the secondary combustor 40, the port 41 is formed at a position opposing to an injection nozzle of the primary combustor 30 and the port cover 47 blocking the port 41 is attached to the port 41 in such a manner that the same is removed by fuel gas jetted out from the injection nozzle 31. <P>COPYRIGHT: (C)2009,JPO&INPIT

Description

  The present invention relates to a ram rocket having a structure in which a port formed in a secondary combustor loaded with a booster propellant is closed by a port cover.

Conventionally, there exists a thing of the structure described in the nonpatent literature 1 as this kind of ram rocket. FIG. 6 is a cross-sectional view schematically showing an entire conventional ram rocket.
As shown in FIG. 6, the ram rocket described in Non-Patent Document 1 includes a primary combustor 3 provided with an injection nozzle 2 for injecting a fuel gas of a filled ramjet fuel 1, Ports 4 and 4 for taking in compressed air from the outside are formed in openings and a secondary combustor 6 loaded with a booster propellant 5 is arranged back and forth in the flight direction a. In addition, the ports 4 and 4 are closed by the port covers 7 and 7 until the combustion of the booster propellant 5 in the secondary combustor 6 is completed.

The ram rocket having the above configuration flies while accelerating by burning the booster propellant 5 loaded in the secondary combustor 6, and following the completion of the combustion of the booster propellant 5,
By removing the port covers 7 and 7 that have previously blocked the ports 4 and 4 by the removal devices 8 and 8, compressed air is introduced from the outside into the secondary combustor 6, and the compressed air and the ramjet The flight is continued by mixing and burning the fuel 1 for fuel.
Japan Aerospace Society, "Aerospace Engineering Handbook", 2nd edition, Maruzen Co., Ltd., September 30, 1992, p. 735

  The above-mentioned removal device 8 generally uses the explosive energy of pyrotechnics to crush the port covers 7 and 7 to open the ports 4 and 4, but has a lighter and simpler structure. Requested to remove the port cover.

  Therefore, the present invention provides a ram rocket that can improve reliability without mounting a port cover removal device using pyrotechnics, and can remove the port cover from the port with a lighter and simpler configuration. It is aimed.

  In order to achieve the above object, the present invention provides a primary combustor having an injection nozzle for injecting a fuel gas of a ramjet fuel filled, an opening for taking in compressed air from the outside, and a booster The secondary combustor to which the propellant is loaded is arranged back and forth in the flight direction, and the port covers the port by the port cover until the combustion of the booster propellant in the secondary combustor is completed. The port is formed at a position facing the injection nozzle of the primary combustor, and a port cover for closing the port is injected from the injection nozzle. It is characterized by being attached to the port so as to be removed by the fuel gas.

  According to the present invention, when the combustion of the booster propellant in the secondary combustor is completed, the port cover closing the port is removed by the fuel gas injected from the injection nozzle. Without mounting a port cover removal device using pyrotechnics, the reliability can be improved and the port cover can be removed from the port with a lighter and simpler configuration.

  The best mode for carrying out the present invention will be described below with reference to the drawings. 1 is a schematic sectional view of a ram rocket according to an embodiment of the present invention, FIG. 2A is an enlarged view of a portion indicated by an encircling line I in FIG. 1, and FIG. It is.

  A ram rocket (also referred to as an integral ram rocket) A according to an embodiment of the present invention includes an air intake 20, a primary combustor 30, and a secondary combustor 40 that coincide with the axis O1 and from the front side in the flight direction a. It is configured to be sequentially arranged toward the rear side.

  The secondary combustor 40 is formed in a substantially cylindrical shape that is elongated along the axis O1, and a port 41 is formed in the front end 40a so as to coincide with the axis O1, and in the rear end 40b. A ram nozzle 42 and a booster nozzle 43 are provided, and an integral booster propellant (hereinafter simply referred to as “booster propellant”) 44 is loaded therein.

The ram nozzle 42 is used during ram combustion, and the booster nozzle 43 is used during combustion of the booster propellant 44.
The booster nozzle 43 is attached to the inside of the ram nozzle 42 by a clamp or the like (not shown), and an igniter 45 used for ignition of the booster propellant 44 is attached to the inside of the booster nozzle 43.

The port 41 and the injection nozzle 31 have an arrangement relationship in which an opening 46 for taking compressed air into the secondary combustor 40 is defined.
In the present embodiment, the port 41 is formed in a circular shape having an outer diameter larger than the outer diameter of the injection nozzle 31 of the primary combustor 30 described in detail later. An opening 46 for taking in the next combustor 40 is formed in a ring shape as shown in FIG.

A port cover 47 having the same contour as this is attached to the port 41 with a required adhesive. The adhesive force is such that the port cover 47 can be removed from the port 41 by the fuel gas injected from the injection nozzle 31 of the primary combustor 30. In addition, since the port cover 47 is attached with an adhesive, a simple configuration can be achieved.
On the front side surface 47a of the port cover 47, as shown in FIG. 2 (A), a ring-shaped nozzle fitting portion 47b that fits the injection nozzle 31 is projected.

In the present embodiment, the air intake 20 is formed in a cylindrical shape having substantially the same diameter as the secondary combustor 40, and the primary combustor 30 filled with the ramjet fuel 32 is supported in the latter half of the air intake 20. ing.
The air intake is not necessarily limited to a cylindrical shape, and can be formed in other shapes as necessary.

The primary combustor 30 is supported so as to coincide with the axis O1 by being attached to the bridging members 21 and 21 installed between the inner wall 20a of the air intake 20 and the rear end portion of the primary combustor 30 is An injection nozzle 31 for injecting fuel gas of the ramjet fuel 32 is provided.
Further, by supporting the primary combustor 30 so as to coincide with the axis O1, a flow path of compressed air is formed around the primary combustor 30.

The injection nozzle 31 and the port 41 are arranged with the injection port 31 a of the injection nozzle 31 facing the port 41. In the present embodiment, the port cover 47 is brought into contact with the injection port 31a of the injection nozzle 31 so that the energy of the fuel gas injected from the injection nozzle 31 can be used effectively and secondary combustion is performed. The port cover 47 can be held until the combustion of the booster propellant 44 in the vessel 40 is completed.
The port cover 47 is not limited to being brought into contact with the injection port 31a of the injection nozzle 31 and may be arranged slightly apart.

  The operation of the ram rocket A having the above configuration will be described with reference to FIGS. 3 to 5 show the process up to ram combustion (secondary combustion), FIG. 3 is an explanatory view showing a state in which the booster propellant is burning, and FIG. 4 shows the port cover from the port. FIG. 5 is an explanatory diagram showing a state of ram combustion.

  As shown in FIG. 3, the booster propellant 44 in the secondary combustor 40 is ignited and fired by ejecting high temperature gas generated by the combustion through the booster nozzle 43 to the outside. Accelerate until the set Mach number required for operation is reached.

  Next, when the combustion of the booster propellant 44 ends when the set Mach number is approached, as shown in FIG. 4, a separation mechanism (not shown) is operated to discharge the booster nozzle 43 from the secondary combustor 40 to the outside, The ramjet fuel 32 in the primary combustor 30 is ignited and the fuel gas 33 is injected from the injection nozzle 31.

The port cover 47 bonded to the port 41 is removed from the port 41 by the fuel gas 33 injected from the injection nozzle 31, thereby opening the port 41.
By opening the port 41, the compressed air is taken into the secondary combustor 40 through the opening 46 formed around the injection nozzle 31, and the fuel gas 33 is injected into the secondary combustor 40.
The fuel gas 33 and the compressed air taken in are mixed to cause a continuous combustion reaction (ram combustion) in the secondary combustor 40, and through the ram nozzle 42 in which the high-temperature gas generated thereby is already exposed. Further thrust is obtained by jetting outside.

It is a schematic sectional drawing of the ram rocket which concerns on one Embodiment of this invention. (A) is an enlarged view of a portion indicated by an encircling line I in FIG. 1, and (B) is a II-II sectional view thereof. It is explanatory drawing which shows the state which the propellant for boosters is burning. It is explanatory drawing which shows a mode that a port cover is removed from a port. It is explanatory drawing which shows the state which is carrying out ram combustion. It is sectional drawing which shows the whole of the conventional ram rocket schematically.

Explanation of symbols

30 Primary Combustor 31 Injection Nozzle 40 Secondary Combustor 41 Port 44 Booster Propellant 46 Opening 47 Port Cover a Flight Direction

Claims (4)

A primary combustor having an injection nozzle for injecting a fuel gas of a ramjet fuel that is filled, and a secondary combustor having an opening for taking in compressed air from the outside and loading a booster propellant The ram rocket is arranged so that the ports are closed by the port cover until the combustion of the booster propellant in the secondary combustor is completed. And
The port is formed at a position facing the injection nozzle of the primary combustor,
A ram rocket, wherein a port cover for closing the port is attached to the port so as to be removed by the fuel gas injected from the injection nozzle.   The ram rocket according to claim 1, wherein the port cover is attached to the port by an adhesive.   The ram rocket according to claim 1 or 2, wherein the injection nozzle and the port are arranged so that an opening for taking compressed air into the secondary combustor is defined therebetween.   The ram rocket according to any one of claims 1 to 3, wherein an injection nozzle of the primary combustor is brought into contact with a port cover attached to the port.

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