JP2999276B2 - Ram rocket - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION The present invention relates to the combustion of a booster propellant in a ram combustion chamber, the combustion of a sustainer propellant in a combustible gas generator, and an excess amount of combustible gas and air introduced from the outside. And a ram rocket (also referred to as a ram jet) having a structure in which a thrust is obtained by combustion in the ram combustion chamber.

[0002]

2. Description of the Related Art Conventionally, as a ram rocket of this kind,
For example, there is one having a structure as shown in FIG. 2 (however, shows a state after the booster propellant has burned).

A ram rocket 51 shown in FIG. 2 has a ram combustion chamber 53 loaded with a booster propellant 52 shown by a virtual line for after combustion, and a rear end of the ram combustion chamber 53 is provided after separation. A booster nozzle 54 and a ram nozzle 55 indicated by phantom lines are provided concentrically via a separation joint, and the booster nozzle 54 is provided with a booster propellant ignition device.

A plurality of air inlets 56 are provided at a plurality of circumferential locations on the outer periphery of the front side of the ram combustion chamber 53, and a port cover 57 for closing the air inlet 56 is not shown. Can be canceled by

Further, a flammable gas generator 62 loaded with a sustainer propellant 61 containing excess fuel is provided at the front end of the ram combustion chamber 53. The flammable gas generator 62 and the ram combustion chamber 53 A flammable gas igniter 64 for igniting the flammable gas generated by the flammable gas generator 62 is provided in communication with the flammable gas nozzle 63, and a flammable gas flow control mechanism 65 is provided. It is provided.

[0006] In the ram rocket 51 having such a structure, the booster propellant 52 burns in the ram combustion chamber 53 by igniting the booster propellant igniter.
The combustion gas is launched from the booster nozzle 54 to obtain thrust by starting, and accelerates.

Subsequently, at the end of combustion of the booster propellant 52, the booster nozzle 54 is separated at the separation joint, and the port cover 57 of the air inlet 56 is opened by the port cover release mechanism, and the fuel is ejected from the combustible gas nozzle 63. A mixed gas of combustible gas and air introduced through the air inlet 56 is ignited by a combustible gas igniter 64, and the combustion gas is ejected from a ram nozzle 55 to obtain thrust.

Incidentally, regarding this type of ram rocket,
For example, there is a slight explanation in “Enhanced Aerospace Engineering Handbook” edited by The Japan Society of Aeronautics and Astronautics, pages 655 to 656, published by Maruzen on April 25, 1983.

In the sustainer propellant 61, a low oxidant propellant containing a metal fuel such as boron has been used as a gas generating agent.

[0010] Regarding this kind of gas generating agent containing boron, "Ignition and Combust" is used.
ion of Boron Particlesand
Clouds, J.A. SPACERAFT VOL.
19, no. 4 (AIAA 82-4174) P294
To P306 have a detailed description.

[0011]

However, in such a conventional ram rocket 51, since a gas generating agent containing a metal fuel is used as the sustainer propellant 61, the flammability is, for example, like boron. If it is not so good, when it is mixed with air in the ram combustion chamber 53, it may be released to the outside without sufficiently burning. In this case, the original performance of the metal fuel must be exhibited. There was a problem that can not be. Then, the particle size may be reduced in order to enhance the flammability of the metal. However, when the particle size is reduced to 1 to 3 μm or less, there is a problem that the productivity is inferior. It was an issue to solve it.

[0012]

SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned conventional problems. Even when a gas generating agent containing a metal fuel is used as a sustainer propellant, combustion by mixing with air can be sufficiently performed. It is possible to prevent the metal fuel from being released to the outside without burning, and to realize the original performance of the metal fuel sufficiently to realize an increase in the specific thrust. .

[0013]

SUMMARY OF THE INVENTION The present invention comprises a sustainer propellant containing a metal fuel, and combusts by mixing a fuel-rich combustible gas generated by combustion of the sustainer propellant with air introduced from the outside. In a ram rocket provided with a ram combustion chamber, a front side of the ram combustion chamber is provided.
Provided with a intake air, are characterized in that a configuration in which a gas generating agent to flow out a high-temperature gas to ram the combustion chamber through the air inlet during combustion of Sa Sutena propellant, such ram The configuration of the rocket is used as means for solving the above-mentioned conventional problems.

The ram rocket according to the present invention is provided with a gas generating agent for causing hot gas to flow into the ram combustion chamber when the sustainer propellant is burned (when the ram is burning). It is desirable that high-temperature gas be allowed to flow out to the upstream side in the ram combustion chamber, and for example, it can be provided near the air intake.

As the gas generating agent, an ordinary aluminum-containing composite propellant can be used, and a propellant containing a relatively large amount of metal fuel is used as a small gas generating agent in order to further increase the specific thrust. It is also possible to use as.

[0016]

[Effect of the invention] In the ram rocket relating to the present invention, above
From what has been a configuration noted, it has a Sasutena propellant containing a metal fuel, combustion difficult situations when due to the high ignition temperature ambient temperature is low excess air state of the metal fuel is even impossible conventionally, in this invention <br/>, during combustion of Sasutena propellant, ram combustion chamber
Flows into the ram combustion chamber through the air intake provided on the front side of the
Depending on the high-temperature gas from the upper SL gas generating agent, and a this high temperature region above flow side of the ram combustion chamber is formed, the metal fuel combustion is promoted combustion becomes sufficient to The residual fuel is not released to the outside, so that the performance inherent in the metal fuel is sufficiently exhibited, and the specific thrust at the time of secondary combustion of the sustainer propellant is increased.

[0017]

FIG. 1 shows an embodiment of a ram rocket according to the present invention. The ram rocket 1 shown in FIG. 1 shows a state after a booster propellant is burned.

The ram rocket 1 shown in FIG. 1 has a ram combustion chamber 3 loaded with a booster propellant 2 indicated by a virtual line for after combustion, and a rear end of the ram combustion chamber 3 is provided after separation. A booster nozzle 4 and a ram nozzle 5 indicated by phantom lines are provided concentrically via a separation joint, and the booster nozzle 4 is provided with a booster propellant ignition device.

Further, the ram combustion chamber 3 is provided with air intake ports 6 at a plurality of circumferential locations on the outer periphery on the front side thereof, and a port cover 7 for closing the air intake port 6 is provided by a port cover release mechanism (not shown). It can be released.

On the rear side of the port cover 7, a gas generating agent 8 for injecting a high-temperature gas into the ram combustion chamber 3 at the time of secondary combustion of sustainer propellant described later (at the time of ram combustion) is provided. An igniter 9 for igniting the gas generating agent 8 is provided. Also, reference numeral 10 in the figure denotes a nozzle that opens to the air inlet 6, and high-temperature gas from the gas generating agent 8 is injected into the air inlet 6 through the nozzle 10.
And flows out into the ram combustion chamber 3 through the air intake 6 .
The pressure of the compressed air at the air inlet 6 is about 6 atm.
Therefore, the gas generating agent 8 is designed so as to have a gas pressure that can overcome this atmospheric pressure. In the figure, reference numeral 11 denotes a nozzle closure, which is separated from the nozzle 10 by the gas pressure of the gas generating agent 8.

Further, at the front end of the ram combustion chamber 3, there is provided a combustible gas generator 13 loaded with a sustainer propellant 12 containing a metal fuel composed of boron. 3 is provided through a flammable gas nozzle 14 and a flammable gas igniter 15 for igniting the flammable gas generated by the flammable gas generator 13 is provided. A mechanism 16 is provided.

In the ram rocket 1 having such a structure, the booster propellant 2 is burned in the ram combustion chamber 3 by igniting the igniter for the booster propellant, and the combustion gas is ejected from the booster nozzle 4. Start and accelerate by gaining thrust.

Subsequently, at the end of combustion of the booster propellant 2, the booster nozzle 4 is separated and discharged at the separation joint, and the port cover 7 of the air inlet 6 is opened by the port cover releasing mechanism, and the combustible gas nozzle is opened. A flammable gas igniter 15 ignites a mixed gas of the flammable gas ejected from 14 and the air introduced from the air intake 6, and the combustion gas is ejected from the ram nozzle 5 to obtain thrust. .

[0024] At this time, the by igniter 9 in accordance with the ignition of the combustible gas to generate a hot gas by igniting the gas generating agent 8, Roh nozzle 1 0 The hot gas Contact
Since as make injection into the air intake port portion of the inlet 6 which is upstream of the ram combustion chamber 3 through an air inlet 6 and the region of high temperature is formed on the upstream side of the ram combustion chamber 3
Will be .

Therefore, even when the sustainer propellant 12 contains boron, which is particularly difficult to burn as a metal fuel, it is possible to promote the combustion of this boron to improve its combustion efficiency, and to reduce the remaining combustion of boron. The metal fuel is not discharged to the outside, so that the characteristics of the metal fuel can be sufficiently exhibited, and the specific thrust by the combustion of the sustainer propellant 12 is further improved.

In one embodiment, when a sustainer propellant 12 containing boron is used as a metal fuel, a small gas generating agent 8 is provided so that high-temperature gas is injected into the ram combustion chamber 3 during ram combustion. If spilled,
It was possible to obtain a considerable increase in specific thrust as compared with the case where the small gas generating agent (8) was not provided.

[0027]

According to the present invention ram rocket relating to the present invention, the above-mentioned
Because was the a configuration, it becomes possible to perform sufficient to promote the combustion even when containing the metal fuel Sasutena propellant, which caused the combustion remainder as in the prior art emitted to the outside The propulsion performance of the metal fuel can be fully exhibited, and the specific thrust by the combustion of the Sustainer propellant increases, thereby increasing the projectile distance or reducing the weight of the projectile. A remarkably excellent effect that it can be realized is brought about.

[Brief description of the drawings]

FIG. 1 is an explanatory sectional view showing a state after a booster propellant is burned by a ram rocket according to the present invention.

FIG. 2 is an explanatory sectional view showing a state after a conventional booster propellant is burned in a ram rocket.

[Explanation of symbols]

 1 Ram rocket 2 Booster propellant 3 Ram combustion chamber6 air intake  8 Gas generating agent 12 Sustainer propellant

──────────────────────────────────────────────────続 き Continuing on the front page (72) Inventor Takuo Kuwahara Nissan Motor Co., Ltd. Nissan Motor Co., Ltd. (72) Inventor Minoru Mitono 2 Takaracho 2 Kanagawa-ku, Yokohama, Kanagawa Prefecture Automobile Co., Ltd. (72) Inventor Ichiro Nagagawa 2 Takaracho, Kanagawa-ku, Yokohama-shi, Kanagawa Nissan Motor Co., Ltd. (56) Reference JP-A-59-203855 (JP, A) JP-A-55- 75553 (JP, A) (58) Field surveyed (Int. Cl. ⁷ , DB name) F02K 7/18 F02K 9/78 F02K 9/26-9/28

Claims (1)

(57) [Claims] 1. A ram having a sustainer propellant containing a metal fuel and having a ram combustion chamber for burning by mixing a fuel-rich combustible gas generated by combustion of the sustainer propellant with air introduced from the outside. in rocket, co the prior SL provided an air inlet on the front side of the ram combustion chamber
To, through the inlet before Symbol air during the combustion of support Sutena propellant
Setting a gas generating agent to flow out a high-temperature gas to ram the combustion chamber Te
A ram rocket characterized by the fact that