JPH0357867A - Ram rocket - Google Patents

Abstract

PURPOSE:To suppress a change of shape in a machine body barrel part total unit at the time of opening and closing an air intake port by providing a port cover, which closes the air intake port of a diffuser before a predetermined ram pressure is obtained, and a hinge-opening and closing cover plate which constitutes a ramp part of a machine body barrel part wall surface. CONSTITUTION:A ram rocket 1 has a ram combustion chamber 3 in a motor case 2 and takes in air through an air introducing path 7 and a supply air port 8 from an air intake port 4. Here the supply air port 8, which connects the air introducing path 7 to the ram combustion chamber 3, is closed by a crushing type port cover 9, while a cover plate 10, corresponding to the air intake port 4, is turnably mounted through a hinge pin 11 to a ram part 6 which partitions the air introducing path 7. This cover plate 10 is held to an air intake port closing position by a crushing type strut 12. The port cover 9 and the strut 12 are broken by a crushing system ignition device 13, when a predetermined ram pressure is obtained, and operated so as to open the supply air port 8 and the air intake port 4.

Description

DETAILED DESCRIPTION OF THE INVENTION Field of the Invention The present invention relates to a ram rocket, and more particularly to a structure in which the air intake port of a diffuser is closed until a predetermined ram pressure is obtained.

Conventional technology This type of ramrocket is known, for example, from Japanese Patent Application Laid-Open No. 57-13.
As disclosed in Japanese Patent No. 1845, there is a diffuser in which the diffuser itself forming the air intake port is movable.

More specifically, as shown in FIGS. 7 and 8, the air intake 3
The diffcoser 34 that forms part 3 is configured to be openable and closable by a hinge bin 35, and during booster flight until a predetermined ram pressure is obtained (while the booster propellant 38 is being combusted), the air intake port is opened as shown in Fig. 7. The diffuser 34 is held in the closed position to close the air filter 33.

On the other hand, after a predetermined ram pressure has been obtained, the transition to sustain flight is performed, as shown in FIG. is formed with an opening, air compressed by ram pressure is taken into the combustion chamber 37, and thrust is obtained by secondary combustion of the flammable gas of the sustainer propellant in the tank 39.

According to this structure, unnecessary air resistance exerted by the diffuser 34 can be eliminated at least until transition to sustain flight, and the flight performance of the flying object is improved.

Problems to be Solved by the Invention However, when the movable diffuser structure as described above is adopted, the relatively large diffuser 34 has to be moved from the base, so the diffuser a4 is in the closed position and in the expanded position. There is a large change in the shape of the entire fuselage body compared to when it is in the open position, and there is concern that it will affect flight performance. That is, if the diffuser 34 is expanded all at once when transitioning to sustain flight, the impact will be applied to the aircraft body as a disturbance, and there is a risk that the flight performance will deteriorate on the contrary.

The present invention was made in view of the above problems.
The objective is to provide a structure in which the member blocking the air intake port of the diffcoser is made as small as possible to achieve the intended purpose while suppressing the influence on flight performance.

Means for Solving the Problems The present invention provides a ram rocket equipped with a diffuser on the outer periphery of the fuselage body, the front of which is opened as an air intake D.
In addition to the port force bar, which closes the air inlet connecting the diffuser and the combustion chamber until a predetermined ram pressure is obtained, the air intake port is also blocked until a predetermined ram pressure is obtained. , and after a predetermined ram pressure is obtained, the air intake port is opened and at the same time a hinged cover plate is provided, which forms a ramp section on the wall surface of the fuselage body.

Here, the above-mentioned lamp section serves to determine the position of the throat section of the diffuser and at the same time to control the generation position of the shock wave.

According to this structure, during booster flight, not only the air supply port connecting the diffuser and the combustion chamber but also the air intake port of the diffuser remain closed by the cover plate. Therefore, the air resistance during flight is reduced by the amount that air is not taken in by the diffuser.

On the other hand, when transitioning to sustain flight, the boat cover that had previously blocked the air intake is shattered and removed, for example by explosives, and at the same time the cover plate is held in the air intake blocking position until then. The struts that were in use are crushed by the same means as above. As a result, when the cover plate rotates and the air intake port of the diffuser is opened for the first time, the cover plate 9 aligns with the ramp section that forms the wall surface of the diffuser and forms part of the ramp section. The air compressed by the ram pressure is drawn into the combustion chamber.

Embodiment FIG. 1 is an explanatory diagram of the main parts of an embodiment of the present invention, in which 2 is a motor case that becomes the fuselage body of the ram rocket L, and 3 is a ram formed inside the motor case 2. It is a combustion chamber. A diffuser 5 having an open front end as an air intake port 4 is integrally formed on the outer surface of the motor case 2, and an air introduction path 7 is defined by this diffuser 5 and a ramp portion 6 on the side of the motor case 2. ing. The air introduction passage 7 is connected to the combustion chamber 3 through the air supply port 8.
is connected to.

The ramp section 6 constitutes a part of the wall surface of the motor case 2, and also serves to determine the position of the throat section of the air introduction passage 7 and at the same time to control the position where shock waves are generated during flight, as shown in Fig. 1. As shown, the ramp portion 6 is formed in a mountain shape along the longitudinal direction of the air introduction path 7.

An air supply port 8 connecting the air introduction passage 7 and the ram combustion chamber 3 is closed by a crushable port cover 9, and a cover plate 10 corresponding to the air intake port 4 is connected to the ramp portion 6 via a hinge bin 1l. movably mounted. This cover plate 10 is held in a position where it closes the air intake port 4 by a collapsible strut l2, thereby sealing the air intake port 4. Both the boat cover 9 and the strut 12 are connected to a crushing system ignition device (3).

Further, a concave plate receiving part 14 corresponding to the shape of the cover plate 10 is formed on the lamp part 6 side, and when the supporting force of the cover plate 1-10 by the support column 12 is released, as will be described later, the sixth As shown in the figure, the cover plate IO is rotated and stored in the plate receiving part 14,
The cover plate 10 substantially aligns with the wall surface of the ramp part 6 and forms a part of the ramp part 6. 15 is a sealing member that seals the gap between the diffuser 5 and the cover plate 10.

As shown in Figs. 2 to 5, the above-mentioned support column 12 has a two-layered structure consisting of a main body part l6 made of tempered glass and an acrylic plate l7, and is supported by the rotational biasing force given by a torsion recoil spring l8. The cover plate 10 is pushed up, and the tip of the cover plate 10 is brought into pressure contact with the inner wall surface of the diffuser 5 as shown in FIG. 19 is a receiving plate provided at a part of the cover plate 10 in pressure contact with the support column I2;
20 is a frame supporting the torsion coil spring 18.

A meandering explosive groove 2l and a plurality of straight shock wave absorbing grooves 22 are formed on the surface of the acrylic plate 17, and the explosive groove 21 is filled with a semi-mixed explosive 23 for crushing the strut l2. embedded. As shown in FIG. 4, a detonator 24 is mounted on the surface of the acrylic plate 17 at a position that bisects the entire length of the explosive groove 2l. This detonator 24 is connected to the crushing system igniter 13 shown in FIG.
It functions to ignite and detonate the explosive 23 buried in the explosive groove 2L.

On the other hand, the shock wave absorption groove 22 prevents the shock wave generated by the ignition and detonation of the detonator 24 from reaching the explosive 23 before the explosion propagation of the explosive 23 buried in the explosive groove 21 and damaging the explosive 23. work.

In addition, the boat cover 9 described above also basically supports the support l2.
It has the same structure as , and is crushed and removed from the air supply port 8 by the action of the crushing system igniter 13 shared with the support column l2.

Next, the operation of the ram rocket constructed as described above will be explained.

First, during booster flight (generally during combustion of solid booster propellant) until a predetermined ram pressure is obtained, the first
As shown in the figure, an air supply port 8 connecting the air introduction passage 7 and the ram combustion chamber 3 is closed by a port cover 9, and the air intake port 4 is also closed by a cover brake 10.

Therefore, no air is taken into the diffuser 5 itself as well as the ram combustion chamber 3. At this time, the pressure applied to the cover plate 10 is borne by the struts 12, while the port cover 9 functions to prevent the flame from flowing back from the ram combustion chamber 3 side to the diffuser 5 side.

On the other hand, when the speed of the ram rocket 1 reaches a speed sufficient to obtain ram pressure, the solid sustainer propellant is ignited following the completion of combustion of the booster propellant (not shown), and the rocket shifts to sustainer flight. Concurrently with this, the crushing system igniter l3 is activated, and the boat cover 9 and the support column l2 are crushed by the explosive 23.

When the port cover 9 is crushed and removed, the air supply port 8 opens, while the crushing of the support column 12 releases the supporting force that had previously supported the cover plate 10 in the closed position of the air intake port 4. As a result, the cover plate 10 falls inward due to air pressure and is stored in the plate receiving portion 14, and the air intake port 4 of the diffuser 5 is opened. Therefore, air is introduced into the ram combustion chamber 3 through the diffuser 5 for the first time at this point.

In the ram combustion chamber 3, the combustion gas of the sustainer propellant (not shown) and the air taken in through the diffuser 5 are intensely mixed to cause so-called ram combustion, and this combustion gas is injected from a nozzle (not shown) to generate thrust. With this, we will be able to perform sustain flight.

Here, during sustain flight, the cover plate 10 remains stored in the plate receiving portion l4 by air pressure, so that it aligns with the ramp portion 6 and constitutes a part of the ramp portion 6.

Effects of the Invention As described above, according to the present invention, in addition to the boat cover that closes the air supply port until a predetermined ram pressure is obtained, the air intake port of the diffuser is closed until a predetermined ram pressure is obtained. After the air intake is closed and a predetermined ram pressure is obtained, the air intake is opened and at the same time a hinged cover plate that forms the ramp section on the fuselage wall is installed. Since there is little change in the shape of the entire body of the fuselage between when the booster is closed and when it is closed, it has the effect of reducing air resistance during booster flight, which is the intended purpose, while minimizing the impact on flight performance.

[Brief explanation of drawings]

Fig. 1 is a diagram showing an embodiment of the present invention, and is an enlarged explanatory view of the main part during flight of Pusta, Fig. 2 is an enlarged view of the main part of Fig. 1, and Fig. 3 is an eight-directional view of Fig. 2. , Figure 4 is IV-IV of Figure 3.
Figure 5 is a cross-sectional view along the line ■-■ in Figure 3, Figure 6 is an enlarged explanatory view of the main parts showing the state transitioned from the state in Figure 1 to sustain flight, Figure 7 8 is a cross-sectional explanatory view showing an example of a conventional ram location during booster flight, and FIG. 8 is a cross-sectional explanatory view during sustainer flight. 1... Ram rocket, 2... Motor carrier case as fuselage body, 3... Ram combustion chamber, 4... Air intake port,
5... Diffuser, 6... Lamp part, 8... Air supply port, 9... Port cover IO... Cover plate,
12... Strut, 13... Crushing system ignition device, 14...
・Plate receiving part, 2l... Explosive groove. Figure 2 18 18

Claims (1)

[Claims] (1) In a ram rocket equipped with a diffuser on the outer periphery of the fuselage fuselage with an opening at the front as an air intake port, the air supply port connecting the diffuser and the combustion chamber should be closed until the specified ram pressure is obtained. Apart from the port cover, the air intake port is also closed until a predetermined ram pressure is obtained, and once the predetermined ram pressure is obtained, the air intake port is opened and a lamp on the fuselage body wall is closed. A ram rocket characterized by having a cover plate that can be opened and closed by a hinge.