JP2933289B2 - Gas generating agent - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a ram for combusting a booster propellant in a ram combustion chamber and a combustible gas generated by burning a sustainer propellant in a combustible gas generator and air introduced from the outside. The present invention relates to an improvement in a gas generating agent used as a sustainer propellant in a ram rocket (also referred to as a ram jet) having a structure in which a thrust is obtained by combustion in a 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. 1 (however, shows a state after the booster propellant has 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.

A plurality of air inlets 6 are provided at a plurality of circumferential locations on the outer periphery of the front side of the ram combustion chamber 3, and a port cover 7 that closes the air inlet 6 is released by a port cover releasing mechanism 8. I can do it.

Further, at the front end of the ram combustion chamber 3, there is provided a combustible gas generator 12 loaded with a sustainer propellant 11 containing an excessive amount of fuel. The combustible gas generator 12 and the ram combustion chamber 3 Combustible gas nozzle 1
3 and a flammable gas generator 12
A flammable gas igniter 14 for igniting the flammable gas generated in step 1 is provided, and a flammable gas flow control mechanism 15 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 booster propellant igniter, 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 at the separation joint, and the port cover 7 of the air inlet 6 is opened by the port cover release mechanism 8, and the combustible gas nozzle 13 blows out. The mixed gas of the combustible gas and the air introduced from the air inlet 6 is ignited by the combustible gas igniter 14, and the combustion gas is ejected from the ram nozzle 5 to obtain thrust.

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

In the sustainer propellant 11, a low oxidant propellant containing boron or magnalium as a metal fuel 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 1, a gas generating agent containing boron or magnalium as a metal fuel is used for the sustainer propellant 11, so that boron or magnalium is not used. Since the flammability is not so good, when mixed with air in the ram combustion chamber 3, the flammability may be released to the outside without sufficiently burning. In this case, the original performance of the metal fuel is exhibited. There was a problem that it was not possible. The particle size may be reduced in order to enhance the flammability of boron and magnalium. However, when the particle size is reduced to 1 to 3 μm or less, there is a problem that the productivity is deteriorated. Solving the problem was a challenge.

[0012]

SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned problems, and has been made in consideration of the fact that even when a gas generating agent containing boron or magnalium as a metal fuel is used as a sustainer propellant, mixing with air can be performed. Combustion can be sufficient, and it is not released to the outside without burning, so that the original performance of the metal fuel can be fully exhibited and the specific thrust can be increased. It is intended to be.

[0013]

According to the present invention, there is provided a gas generating agent for a solid ram rocket containing at least one of boron and magnalium or a mixture thereof as a metal fuel, the titanium powder having an average particle diameter of 20 μm or less. Is contained in an amount of 1 to 5% by weight, and the configuration of such a gas generating agent is a means for solving the above-mentioned conventional problems.

In the gas generating agent according to the present invention,
If the blending ratio of titanium powder to be contained is small, the effect of blending titanium powder is not sufficiently obtained, and the residual performance of boron or magnalium is generated and released to the outside, so that the original performance of metal fuel is obtained. Therefore, the mixing ratio of the titanium powder was set to 1% by weight or more.

However, if the mixing ratio of the titanium powder is too large, the effect is not so much increased, but rather the specific thrust is lowered.

If the particle size of the titanium powder is too large,
Since the effect of adding the titanium powder cannot be sufficiently obtained, the average particle diameter of the titanium powder needs to be 20 μm or less.

[0017]

The gas generating agent according to the present invention contains at least one of boron and magnalium or a mixture of both, and has an average particle diameter of 20 μm.
m or less of titanium powder is contained, so that even when the above-mentioned boron or magnalium is contained as a metal fuel, the combustion thereof becomes sufficient, and the combustion residue may be released to the outside. As a result, the inherent performance of the metal fuel is sufficiently exhibited, and the specific thrust of the gas generating agent is increased.

[0018]

EXAMPLE A gas generating agent having a compounding ratio shown in Table 1 and containing titanium powder was used as a gas generating agent having a changed average particle size. The gas generation equivalence ratio and the specific thrust were measured, and no. The increase rate of the specific advancing force based on the specific thrust of No. 1 was examined.

The results are also shown in Table 1.

[0020]

[Table 1]

As shown in Table 1, the content of titanium powder was kept constant at 5.0% by weight, and the average particle size of titanium powder was changed. In Nos. 2 to 6, of the invention examples in which the average particle size of the titanium powder was 20 μm or less, the particles of No. 1 to No. 3 of the invention examples. In any of 2 to 5, the rate of increase of the specific advancing force exceeds 1.00 and the specific thrust is increased as compared with the case where no titanium powder is added.
The average particle size of the titanium powder was too large at 30 μm. In Comparative Example No. 6, no titanium powder was added. 1
It was an unfavorable result that the specific thrust was rather lower.

Further, the average particle size of the titanium powder was kept constant at 20 μm, and the content of the titanium powder was changed. 7 ~
12, the content of titanium powder is 1.0 to 4.8% by weight. In Nos. 8 to 11, the rate of increase in the specific thrust exceeded 1.00, whereas the content of the titanium powder was too small at 0.8% by weight.
No. 7 cannot provide the effect of adding titanium powder, and if the content of titanium powder is too large as 5.5% by weight, N
o. In No. 12, improvement in specific thrust could not be obtained.

In this embodiment, No. 1 is an example of the invention. The thrust of the thirteen gas generants was the largest.

[0024]

The gas generating agent according to the present invention is a gas generating agent for a solid ram rocket containing at least one of boron and magnalium as a metal fuel,
Since titanium powder having an average particle diameter of 20 μm or less is contained in an amount of 1 to 5% by weight, even when the above-mentioned boron or magnalium is contained as a metal fuel, it is possible to sufficiently perform the combustion. However, unlike the conventional case, there is no possibility that the residual combustion is generated and released to the outside, so that the original performance of the metal fuel can be sufficiently exhibited, and the specific thrust of the gas generating agent increases. As a result, a remarkably excellent effect that it is possible to increase the projecting distance or reduce the weight of the flying object is provided.

[Brief description of the drawings]

FIG. 1 is an explanatory sectional view showing a state after a booster propellant is burned in a ram rocket using a gas generating agent according to the present invention.

[Explanation of symbols]

 1 Ram rocket 2 Booster propellant 11 Sustainer propellant (gas generating agent)

──────────────────────────────────────────────────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) References JP-A-1-192787 (JP, A) JP-A-61- 127692 (JP, A) (58) Fields investigated (Int. Cl. ⁶ , DB name) C06D 5/00 C06D 5/06

Claims (1)

(57) [Claims] 1. A gas generating agent for a solid ram rocket containing at least one of boron and magnalium as a metal fuel, comprising 1 to 5% by weight of titanium powder having an average particle size of 20 μm or less. Gas generating agent.