JPH0341079Y2 - - Google Patents

Description

[Detailed description of the invention] [Purpose of the invention] (Industrial application field) This invention is a ram rocket that mixes and burns outside air taken in from a diffuser through an intake port and ram fuel in a combustion chamber. This relates to a port cover for a ram rocket used to temporarily close the mouth.

(Conventional technology) Conventionally, port covers for ram rockets were
For example, “Center-Loaded Duct Integral-
Rocket／Ramjet Transition Testing”
AIAA/SAE 14TH JOINT PROPULSION
CONFERENCE Las Vegas, Nev.／July 25−
27, 1978, and Figure 4~
This will be explained based on FIG.

That is, the ram rocket R shown in FIG.
The head side of the air duct 100 has an air intake port 102a that opens in the direction of flight and an air duct 1.
The combustion chamber 103 is provided on the tail side of the air duct 100. A substantially cylindrical frame 104 is interposed between the ram fuel tank 101 and the combustion chamber 103, which communicates the air duct 100 with the combustion chamber 103, and has a ram fuel injector provided on its inner peripheral surface. There is. A ramjet nozzle 103a is installed at the tail of the fuel chamber 103.
is formed, and a rocket nozzle 105 is attached inside the ramjet nozzle 103a.
A cylindrical solid propellant 106 is loaded inside the air duct 100 and the fuel chamber 103, and the intake port 102b is connected to the port cover 10.
It is blocked at 7.

The port cover 107 is shown in FIGS. 5 and 6.
As shown in the figure, it is disk-shaped, and has a cork disk 109 as an insulating material on one side of a glass disk 108, and a cylinder 110 that holds both disks 108 and 109 around it. provided, the glass disk 108
On the other side, there are two caps 1 containing explosives.
11 and 111 are installed. This port cover 107 closes the intake port 102b by attaching a ring 110 to the intake port 102b with the coil disk 109 facing the air duct 100.

The ram rocket R equipped with the port cover 107 starts and accelerates by igniting the solid propellant 106, and when it reaches a predetermined speed and burns out the solid propellant 106, the rocket nozzle 10
5 and explodes the cap 111 to destroy both the disks 108 and 109. At this time, the fragments of the disks 108 and 109 are
The air duct 100 and the combustion chamber 103 are compressed by the pressure of the outside air compressed through the diff user 102
It passes through and is released to the outside. Thereafter, the ram rocket R continues to fly by mixing the outside air compressed through the diffuser 102 and ram fuel injected from the injector of the frame 104 and continuously burning the mixture in the fuel chamber 103.

(Problem to be solved by the invention) However, the above-mentioned conventional port cover 107
In this case, most of the fragments were composed of a single glass disk 108, and the structure was such that the disk 108 was destroyed by explosion, so the size of the fragments varied, and especially large fragments were found in the combustion chamber 103. There was a problem in that the inner wall of the ramjet nozzle 103a or the inner wall of the ramjet nozzle 103a could be damaged. As ram rockets become larger, it is necessary to increase the thickness of the port cover in order to maintain strength against the pressure during combustion of solid propellants, and as a result, the above-mentioned problems become more pronounced.

This invention was made with attention to such problems, and the purpose is to provide a port cover for a ram rocket that can prevent damage to the combustion chamber and nozzle when the intake port is opened.

[Structure of the invention] (Means for solving the problem) A port cover for a ram rocket according to this invention is a port cover for a ram rocket that mixes outside air taken in from a differential user through an intake port and ram fuel and burns the mixture in a combustion chamber. In a port cover for temporarily closing an intake port, the intake port is provided with a grid body forming a large number of openings, and each opening is provided with a closing member for closing the opening to the outside of the combustion chamber. In the case of the above structure, the closing member is provided so as to be detachable from the grid body by pressure inside the diffuser.

(Example) This invention will be explained below based on the drawings.

FIGS. 1 to 3 are diagrams illustrating an embodiment of this invention.

That is, as shown in FIG. 1, the port cover 1 is a grid body 4 in which a number of rectangular openings 3 are formed by connecting a plurality of crosspieces 2 vertically and horizontally.
and a large number of closing members 5 that individually close each opening 3. The closing member 5 is formed by superimposing a chip 6 and an insulator 7, which are of the same quality as the wall of the combustion chamber, which will be described later, and a stepped portion 6a that engages with the crosspiece 2 is formed at the edge of the chip 6. It can be attached and detached only from one side of the grid body 4 (lower side in FIG. 1).

FIGS. 2 and 3 are diagrams for explaining the ram rocket R, which is equipped with a tank 12 for liquid ram fuel 11 behind a head 10 carrying a payload and the like. Furthermore, the tank 12
A combustion chamber 13 is provided at the rear of the engine. The combustion chamber 1
A substantially cylindrical solid propellant 14 is loaded in the propellant 3 via an insulator 7, and an igniter 15 is attached to the end of the propellant on the head side. Further, a ramjet nozzle 16 is installed at the tail portion of the combustion chamber 13.
is provided, and a rocket nozzle 17 having an opening area smaller than that of the ramjet nozzle 16 is attached inside thereof. this is,
The rocket nozzle 17 is removably attached with a nozzle clamper (not shown) to cope with the pressure increase in the combustion chamber 13 when the ram fuel 11 is later combusted. Furthermore, a plurality of diff users 18 are provided on the outer peripheral side of the combustion chamber 13 in the circumferential direction, each having an air intake port 18a that opens in the flight direction and an intake port 18b that opens at the end of the combustion chamber 13 on the head side. There is.

An injector 19 connected to the tank 12 is provided between the tank 12 and the combustion chamber 13, and the injector 19 includes an injection nozzle 19a that opens near the intake port 18a in the diffuser 18. There is. Also, behind the differential user 18,
A housing section 20 is formed by extending the outer wall of the differential user 18 in the tail direction, and an igniter 21 whose tip protrudes near the intake port 18a in the differential user 18 is housed within the housing section 20. The port cover 1 described above is arranged so that the grid body 4 is attached to the intake port 1 with the closing member 5 facing the combustion chamber 13 side.
By fixing it to the inner periphery of the intake port 8b, the intake port 1
8b is blocked. Each of the closing members 5 is attached using an adhesive with a relatively small bonding force in order to improve airtightness, and is prevented from detaching by the solid propellant 14.

Ramrocket R equipped with the above port cover 1
starts and accelerates by igniting the solid propellant 14 with the igniter 15. At this time, since the closing member 5 is formed with a stepped portion 6a that engages with the crosspiece 2 of the grid body 4, the closing member 5 is not blown away toward the diff user 18 by the pressure inside the combustion chamber 13. Thereafter, when the solid propellant 14 undergoes final sliver combustion and the pressure inside the combustion chamber 13 becomes lower than the pressure inside the diffuser 18, the closing member 5 separates from the grid body 4 due to the pressure difference.
The closing member 5 passes through the combustion chamber 13 and is discharged to the outside. At this time, since each closing member 5 is small and closes each opening 3 individually,
There is no fear of damaging the inner wall of the combustion chamber 13. Also, when the solid propellant 14 is burned out, the nozzle clamp (not shown) is released and the rocket nozzle 1 is
Separate 7. Then, the ram rocket R uses the compressed outside air via the diffuser 18 and the injector 19.
By mixing the mixture with the ram fuel 11 injected from the injection nozzle 19a and igniting it with the igniter 21, the fuel continues to fly while being continuously combusted in the combustion chamber 13. Here, the grid body 4 is held at the intake port 18b and supplies compressed air into the combustion chamber 13 in a rectified state.

Note that the port cover 1 can of course be applied to ram rockets whose structures differ depending on the type of ram fuel, but as explained in the above embodiment, the ram fuel 11
If applied to Ram Rocket R, which injects
The grid body 4 can be used as a flame holder. Furthermore, the form of the port cover and the shape of the opening are not limited to the above embodiments.
For example, the grid body may be provided with an engaging portion that allows the closing member to be removed only toward the combustion chamber. Furthermore, since the port cover uses a large number of relatively small closing members of a constant shape regardless of the overall size, it can easily cope with the need to increase the strength of the port cover as the ram rocket increases in size. .

[Effects of the invention] As explained above, according to the port cover for a ram rocket of this invention, the intake air of the ram rocket mixes the outside air taken in from the differential user through the intake port and the ram fuel and burns the mixture in the combustion chamber. In a port cover for temporarily closing a port, a grid body forming a large number of openings is provided at the intake port, and a closing member for closing the opening is placed in each of the openings toward the combustion chamber side. Since the port cover is configured so that only the blockage member can be removed, compared to the conventional case where a single member is detonated, the port cover allows the blockage member to be released as small fragments of a certain size, and the port cover When the port cover is opened, damage to the combustion chamber and nozzle caused by the components of the port cover can be prevented.

[Brief explanation of the drawing]

Fig. 1 is a perspective view illustrating a port cover according to an embodiment of the invention, Fig. 2 is a sectional view illustrating a ram rocket equipped with the port cover shown in Fig. 1, and Fig. 3 is a ram rocket shown in Fig. 2. FIG. 4 is an enlarged sectional view of the differential user part of the ram rocket, and FIG. 4 is a sectional view illustrating a ram rocket equipped with a conventional port cover.
Figure 5 is a front view illustrating a conventional port cover.
FIG. 6 is a sectional view of the port cover shown in FIG. 5. DESCRIPTION OF SYMBOLS 1...Port cover, 3...Opening part, 4...Grid body, 5...Closing member, 11...Ram fuel,
13... Combustion chamber, 18... Defuser, 18b
...Intake port, R...Ram rocket.

Claims (1)

[Scope of utility model registration request] In a port cover for temporarily closing the intake port of a ram rocket that mixes outside air taken in from a diff user through an intake port and ram fuel and burns the mixture in a combustion chamber, the intake port is provided with a large number of openings. A port cover for a ram rocket, characterized in that a grid body is provided, and a closing member for closing the opening is provided in each of the openings so as to be removable only toward the combustion chamber side.