JPH079216B2 - Ram rocket - Google Patents

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a ram rocket, and more particularly to a structure in which an air intake of a diffuser is closed until a predetermined ram pressure is obtained.

2. Description of the Related Art As a ram rocket of this type, for example, JP-A-57-131845 is used.
As disclosed in the publication, there is a diffuser that forms an air intake port itself. More specifically, as shown in FIG. 7 and FIG. 8, a diffuser 34 that forms an air intake 33 with a ramp 32 that is a part of the fuselage body 31 can be opened and closed by a hinge pin 35. During the booster flight until the predetermined ram pressure is obtained (during combustion of the booster propellant 38), the diffuser 34 is held at the closed position so as to close the air intake 33 as shown in FIG.

On the other hand, when transitioning to the sustainer flight after the predetermined ram pressure is obtained, as shown in FIG.
At the same time, the diffuser 34 is expanded to form the air intake 33, the air compressed by the ram pressure is taken into the combustion chamber 37, and the combustible gas of the sustainer propellant in the tank 39 is secondarily burned. The thrust is obtained by making it.

With this structure, unnecessary air resistance received by the diffuser 34 can be eliminated at least until the flight to the sustainer flight, and the flight performance as a flying object is improved.

However, in the case of adopting the movable diffuser structure as described above, since the relatively large diffuser 34 is moved from the root portion, it is different from the case where the diffuser 34 is in the closed position. The shape of the entire fuselage changes greatly when it is in the open position, which may affect flight performance. In other words, if the diffuser 34 is expanded at a stretch during the flight to Sustainer flight, the impact may be applied to the airframe as a disturbance, which may rather reduce the flight performance.

The present invention has been made in view of the above problems,
It is an object of the present invention to provide a structure in which a member that closes an air intake of a diffuser is made as small as possible and an intended purpose can be achieved while suppressing an influence on flight performance.

Means for Solving the Problems The present invention provides a ram rocket provided with a diffuser, the front of which is opened as an air intake, on the outer periphery of a fuselage body,
Aside from the port cover that closes the air supply port that connects the diffuser and the combustion chamber until a predetermined ram pressure is obtained, the air intake port is also closed until a predetermined ram pressure is obtained, Further, after the predetermined ram pressure is obtained, the air intake opening is opened, and at the same time, a hinge opening / closing type cover plate which constitutes a ramp portion on the wall surface of the body is provided.

Here, the ramp part serves to determine the position of the throat part of the diffuser and at the same time control the generation position of the shock wave.

Function According to this structure, during booster flight, the air inlet connecting the diffuser and the combustion chamber as well as the air inlet of the diffuser flies while being blocked by the cover plate. Therefore, the air resistance during flight is reduced to the extent that air is not taken in by the diffuser.

On the other hand, when transitioning to Sustainer flight, the port cover that previously blocked the air inlet was crushed and removed by, for example, explosives, and at the same time, the cover plate was held at the air inlet closed position until then. The struts that had been used are crushed by the same means as above. As a result, the cover plate rotates and the air intake of the diffuser is opened for the first time, and at the same time, the cover plate aligns with the ramp portion forming the wall surface of the diffuser to form a part of the ramp portion. Then, the air compressed by the ram pressure is taken into the combustion chamber.

Embodiment FIG. 1 is an explanatory view of the configuration of the essential part showing an embodiment of the present invention, in which 2 is a motor case which is the body of the ram rocket 1 and 3 is a ram formed inside the motor case 2. It is a combustion chamber (container). A diffuser 5 whose front is opened as an air intake 4 is integrally formed on the outer surface of the motor case 2, and an air introduction path 7 is defined by the diffuser 5 and the ramp portion 6 on the motor case 2 side. ing. The air introduction passage 7 is connected to the combustion chamber 3 via the air supply port 8.
Is in communication with.

While the ramp portion 6 constitutes a part of the wall surface of the motor case 2, the ramp portion 6 determines the position of the throat portion of the air introduction path 7 and at the same time controls the generation position of the shock wave accompanying flight, and is shown in FIG. As described above, the ramp portion 6 is formed in a mountain shape along the longitudinal direction of the air introduction passage 7.

The air supply port 8 connecting the air introduction path 7 and the ram combustion chamber 3 is closed by a crush type port cover 9, and the ramp portion 6 is provided with a cover plate 10 corresponding to the air intake port 4 via a hinge pin 11. It is movably attached. The cover plate 10 is provided with a crushable support column 12 so that the air intake 4
Is held in a closed position, which allows the air intake 4
Is sealed. And the port cover 9 and the support
Both 12 are connected to a crushing system ignition device 13.

Further, a concave plate receiving portion 14 corresponding to the shape of the cover plate 10 is formed on the side of the lamp portion 6, and as shown in FIG. 6 when the supporting force of the cover plate 10 by the support column 12 is released, as will be described later. As also shown, the cover plate 10 is rotated and stored in the plate receiving portion 14,
Reference numeral 10 substantially forms a part of the ramp portion 6 by being aligned with the wall surface of the ramp portion 6. Reference numeral 15 is a seal member that seals the gap between the diffuser 5 and the cover plate 10.

As shown in FIGS. 2 to 5, the column 12 has a two-layer structure of a main body 16 made of tempered glass and an acrylic plate 17, and is covered by a rotational biasing force given by a torsion coil spring 18. Push plate 10 up, cover plate
The tip of 10 is pressed against the inner wall surface of the diffuser 5 as shown in FIG. 19 is a pillar of the cover plate 10
A receiving plate provided at a pressure contact portion with 12 and a frame 20 supporting a torsion coil spring 18.

A meandering explosive groove 21 and a plurality of linear shock wave absorbing grooves 22 are engraved on the surface of the acrylic plate 17, respectively, and a semi-mixed explosive 23 for crushing the support column 12 is formed in the explosive groove 21. It is embedded. Then, as shown in FIG.
Is installed. This detonator 24 is connected to the crushing system ignition device 13 shown in FIG. 1, and serves to ignite and detonate the explosive 23 embedded in the explosive groove 21.

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

The above-mentioned port cover 9 also has basically the same structure as the column 12, and is crushed by the action of the crushing system ignition device 13 shared with the column 12 and removed from the air supply port 8.

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

First, during booster flight (generally during combustion of solid booster propellant) until a predetermined ram pressure is obtained,
As shown in the figure, the 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 plate 10. Therefore, no air is taken into the diffuser 5 itself as well as the ram combustion chamber 3. At this time,
The support plate 12 bears the pressure received by the cover plate 10, while the port cover 9 functions to prevent the flame from flowing backward 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 the ram pressure, the solid sustainer propellant is ignited following the end of combustion of the booster propellant (not shown), and the flight shifts to sustainer flight. Around this time, the crushing system ignition device 13 operates, and the explosive 23 crushes the port cover 9 and the column 12. When the port cover 9 is crushed and removed, the air supply port 8 is opened, while the crushing of the support column 12 releases the supporting force that has supported the cover plate 10 at the closed position of the air intake port 4 until then. As a result, the cover plate 10 is collapsed inward by the air pressure and stored in the plate receiving portion 14, and the air intake port 4 of the diffuser 5 is opened. Therefore, at this point, air is introduced into the ram combustion chamber 3 through the diffuser 5 for the first time.

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 vigorously mixed and so-called ram combustion is performed, and this combustion gas is injected from a nozzle (not shown) to generate thrust. You will be able to fly sustainably.

Here, during the Sustainer flight, the cover plate
Since 10 remains stored in the plate receiving part 14 by air pressure, it will be aligned with the ramp part 6 and form part of the ramp part 6.

As described above, according to the present invention, apart from the port cover that closes the air supply port until a predetermined ram pressure is obtained, the air intake port of the diffuser until a predetermined ram pressure is obtained. When the air intake is opened, the air intake is opened and the hinge opening / closing type cover plate that forms the ramp part of the machine body wall is provided at the same time after the specified ram pressure is obtained. Since the shape change of the entire fuselage between the closed state and the closed state is small, there is an effect that the air resistance during the booster flight, which is the intended purpose, can be reduced while the influence on the flight performance is minimized.

[Brief description of drawings]

FIG. 1 is a view showing an embodiment of the present invention, and is an enlarged explanatory view of a main part during a booster flight, FIG. 2 is an enlarged view of a main part of FIG. 1, and FIG. 4 is a sectional view taken along line IV-IV of FIG. 3, FIG. 5 is a sectional view taken along line VV of FIG. 3,
FIG. 6 is an enlarged explanatory view of an essential part showing a state where the state of FIG. 1 is shifted to the sustainer flight, FIG. 7 is an example of a conventional ram rocket, a sectional explanatory view at the time of booster flight, and FIG. 8 is Similarly, it is a cross-sectional explanatory diagram at the time of a Sustainer flight. 1 ... Ram rocket, 2 ... Motor case as fuselage body, 3 ... Ram combustion chamber, 4 ... Air intake port, 5 ... Diffuser, 6 ... Lamp, 8 ... Air supply port, 9 ... Port cover, 10 ...
Cover plate, 12 ... Support, 13 ... Crushing system ignition device, 14 ...
Plate receiving part, 21 ... Explosive groove.

 ─────────────────────────────────────────────────── ─── Continuation of the front page (56) References JP-A-57-131845 (JP, A)

Claims (1)

[Claims] 1. A ram rocket equipped with a diffuser having a front opening as an air intake on the outer periphery of a fuselage body, in which a supply port connecting a diffuser and a combustion chamber is closed until a predetermined ram pressure is obtained. Separately from the port cover, the air intake is closed until the specified ram pressure is obtained, and after the specified ram pressure is obtained, the air intake is opened and the fuselage body wall surface is opened at the same time. A ram rocket that is provided with a hinged cover plate that constitutes the ramp part of the ram rocket.