JP3007174B2 - Ram rocket - 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 rocket used for obtaining a flying thrust of a flying object.

[0002]

2. Description of the Related Art Conventionally, as a ram rocket used for obtaining a flying thrust of a flying object, there is, for example, one having a structure shown in FIG.

A ram rocket 51 shown in FIG. 1 has a ram combustor 52, a booster propellant 53 provided in the ram combustor 52, and a gas generator 54 provided with a booster propellant 53 following combustion. A sustainer propellant 55 that is ignited to generate an over-fueled combustible gas, and a gas nozzle 56 that ejects the combustible gas into the ram combustor 52
An inlet 57 which is connected to a port 52a provided in the ram combustor 52 to take compressed air for burning the combustible gas into the ram combustor 52; and a port at the time of combustion of the booster propellant 53. A port cover 58 for closing the port 52a and opening the port 52a at the end of the combustion of the booster propellant 53, and a high-temperature gas generated by the combustion of the booster propellant 53
And a high-temperature gas generated by burning the compressed air and the combustible gas generated by igniting the sustainer propellant 55 by igniting the compressed air and the sustainer propellant 55 to the outside of the ram combustor 52. A ram nozzle 60 for jetting is provided.

The booster nozzle 59 is provided with an outward flange provided at the rear end (right side in the figure) of the ram combustor 32 in a state of being positioned inside the ram nozzle 60 by a clamp band 61 having a V-shaped groove 61a. This booster nozzle 59 is attached to the ram combustor 52 by operating a separation mechanism (not shown) provided on the clamp band 61 at the end of the combustion of the booster propellant 53 to release the tightening. It is being discharged.

[0005]

However, in such a conventional ram rocket 51, the booster nozzle 59 is removed at the end of the combustion of the booster propellant 53 so that the ram nozzle 60 is exposed. Since the removed booster nozzle 59 is discharged to the outside of the ram combustor 52, for example, when the ram rocket 51 launches a flying object that obtains a flying thrust in the air, the booster nozzle 59 is removed. In order to prevent the vehicle from colliding with the mother machine or the succeeding aircraft, there are restrictions on the operation and design, such as the timing of departure and the length of the combustion time of the booster propellant.

[0006] In order to eliminate such a restriction, the present applicants have developed a polymer material such as polybutadiene (HTPB) having a terminal hydroxyl group and ether (HTPE) having a terminal hydroxyl group which can be consumed by the combustion gas of a booster propellant. The ram rocket has a nozzle structure in which a booster nozzle is disposed inside the ram nozzle (Japanese Utility Model Application Laid-Open No. 63-1682).
No. 47).

[0007] However, these polymer materials have consumption characteristics that are slightly different from the combustion characteristics of the booster propellant, and the consumption can be completed at the intended timing, that is, at the end of the combustion of the booster propellant. Since the design is difficult, there still remains a problem that a large number of man-hours have to be spent for the development of the experiment and the simulation.

[0008]

SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned conventional problems, and can generate a necessary thrust at the time of combustion of a booster propellant. It is an object of the present invention to provide a ram rocket which can form a ram nozzle without discharging a booster nozzle to the outside in accordance with the ram rocket, and can easily design the ram nozzle.

[0009]

Means for Solving the Problems] engagement <br/> Waru ram rocket to claim 1 of this inventions, ram combustor, booster for propellant to the material of the solid fuel disposed on the ram combustor And a sustainer propellant that is ignited following the combustion of the booster propellant to generate flammable gas, and a high temperature gas provided at the rear of the ram combustor and generated by the combustion of the booster propellant. A booster nozzle for injecting to the outside, and a high-temperature gas, which is provided at the rear of the ram combustor and is generated by burning the combustible gas with the compressed air flowing into the ram combustor from the outside, is injected to the outside. And a booster nozzle for the propellant for the booster.
And characterized in that the more formed configurations solid fuel with the same burning characteristics and had the solid fuel, and a means for solving the conventional problems described above the configuration of such a ram rocket.

[0010] The booster nozzle must have sufficient strength to withstand the internal pressure of about 50 to 200 atm generated when the booster propellant is burned.

Since it is necessary to burn out the propellant for the booster at the end of combustion, it is preferable that the combustion speed has a value of 4 mm / sec or more.

[0012] order to perform these functions,請of the present invention
The ram rocket according to claim 2, wherein the booster nozzle
The solid fuel used as the raw material is 20 to 30 layers of epoxy resin.
%, 70-80% by weight of ammonium perchlorate
It has to be construed as consisting of, consisting other compositions with the addition of components such as the catalyst is also of using as necessary
It is possible to

[0013]

The ram rocket according to the invention effect of the present invention, since it has a structure described above, the booster nozzle which is more formed on the solid body fuel, solid fuel used in this booster nozzle
The propellant for a booster formed from a solid fuel having the same combustion characteristics as the fuel
As in the prior art that such booster nozzle is discharged to the outside of the ram combustor that disappears, of course, the combustion end of but setting the burning rate is extremely easy solid body fuel therefore booster for propellant In addition, the exposure of the ram nozzle is ensured.

The booster nozzle functions as a nozzle while the booster propellant is burning.
The required thrust is obtained in the combustion stage of the booster propellant.

[0015]

DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described below with reference to the drawings.

FIGS. 1 and 2 illustrate an embodiment of a ram rocket according to the present invention. The ram rocket 1 shown in FIG. 1 is provided with a ram combustor 2 and provided in the ram combustor 2 . the propellant 3 for blanking Suta to the solid fuel as a raw material,
A propellant for a sustainer 5 provided in the gas generator 4 and ignited following combustion of the propellant 3 for the booster to generate a combustible gas with an excess of fuel; and a gas nozzle for injecting the combustible gas into the ram combustor 2 6, an inlet 7 connected to a port 2a provided in the ram combustor 2 to take in the flammable gas into the ram combustor 2 in a compressed state, and a port for burning the booster propellant 3. A port cover 8 for closing the 2a and opening the port 2a in accordance with the end of the combustion of the booster propellant 3, and a booster nozzle for injecting a high-temperature gas generated by the combustion of the booster propellant 3 to the outside of the ram combustor 2; 9 and a high-temperature gas generated by burning the mixture of the compressed air and the combustible gas generated by the ignition of the sustainer propellant 5 to the outside of the ram combustor 2. And a Ramunozuru 10 morphism.

In this case, the booster nozzle 9 is provided inside the ram nozzle 10 and in a state of covering the ram nozzle 10. And this booster nozzle 9 is a booster
Having the same combustion characteristics as the solid fuel used for the propellant 3
In this embodiment, the composition is composed of about 28% by weight of epoxy resin and about 72% by weight of ammonium perchlorate (AP). Since the content ratio of ammonium perchlorate affects the combustion speed, this content ratio is increased or decreased in order to match the timing of burnout with the end of combustion of the booster propellant 3 . When the booster propellant 3 is burned, the booster nozzle 9 itself sufficiently functions as a nozzle while burning, and is burned out as shown in FIG. Thus, the ram nozzle 10 can be formed.

In the ram rocket 1 having such a configuration, first, the propellant 3 for the booster of the ram combustor 2 is ignited to start by obtaining a thrust, and reaches a set Mach number necessary for the operation by the ram pressure. Accelerate until you do.

During the combustion of the booster propellant 3, the booster nozzle 9 generates a thrust necessary for acceleration because the booster nozzle 9 itself sufficiently functions as a nozzle while burning.

[0020] Then, at the stage of combustion is the end of the booster for the propellant 3 to reach the set number of Mach, this booth
Has the same combustion characteristics as the solid fuel used for the propellant 3
For Bed Sutanozuru 9 formed by solid fuel booster
According to the combustion end of the propellant 3 Ramunozuru 10 baked devotion
Is formed. At this time, since the internal pressure of the ram combustor 2 decreases, the port cover 8 is removed by the pressure difference between the internal pressure and the ram pressure on the inlet 7 side, and the port 2
a is released.

At the same time, a flammable gas generated by igniting the propellant for sustainer 5 is injected from the gas nozzle 6 and enters the ram combustor 2, and passes through the flammable gas and the inlet 7 and the port 2a. The inflowing compressed air causes a continuous combustion reaction, and the resulting hot gas is ejected from the already exposed ram nozzle 10 to generate thrust.

[0022] In this way, the booster nozzle 9, a solid body fuel
When the propellant for booster 3 is burned, the booster propellant 3 itself sufficiently functions as a nozzle while burning, so that the thrust required for acceleration can be generated and the propellant for booster 3 can be generated. At the stage of finishing the combustion of the medicine 3, the ram nozzle 10 can be reliably formed by burning out.

[0023]

Since the ram rocket according to the first and second aspects of the present invention has the above-described structure, when the propellant for booster is burned , the solid used in the propellant for booster is used.
The booster nozzle itself formed of a solid fuel having the same combustion characteristics as the fuel performs the function of the nozzle while burning, so that the necessary thrust can be generated and the combustion of the booster propellant since the booster nozzle to burn off in accordance with the completion of the eliminated that components of the booster nozzle as in the prior art is discharged to the outside, of course, physicians use easy solid body fuel setting burn rate
And for which easily can be one Itasa timing of burnout of combustion end and the booster nozzle booster for propellant
Effect is brought about that is.

[Brief description of the drawings]

FIG. 1 is an explanatory longitudinal sectional view showing a schematic configuration of an embodiment of a ram rocket according to the present invention.

FIG. 2 is an enlarged sectional explanatory view showing a state in which a propellant for a booster of the ram rocket in FIG. 1 is burned out to form a ram nozzle.

FIG. 3 is an explanatory longitudinal sectional view showing a schematic configuration of a conventional ram rocket.

[Explanation of symbols]

 REFERENCE SIGNS LIST 1 ram rocket 2 ram combustor 3 booster propellant 5 sustainer propellant 9 booster nozzle 10 ram nozzle

──────────────────────────────────────────────────続 き Continuing on the front page (72) Inventor Takuo Kuwahara Nissan Motor Co., Ltd. Nissan Motor Co., Ltd. (72) Inventor Minoru Minoru 2 Takaracho, Kanagawa-ku, Yokohama, Kanagawa Prefecture Automobile Co., Ltd. (72) Inventor Ichiro Nakagawa Nissan Motor Co., Ltd. 2 Takaracho, Kanagawa-ku, Yokohama-shi, Kanagawa Prefecture (56) References Japanese Utility Model Sho-63-168247 (JP, U) Japanese Patent Publication Sho-36-14771 ( JP, B1) (58) Field surveyed (Int. Cl. ⁷ , DB name) F02K 9/78 F02K 9/97 F02K 7/18

Claims (2)

(57) [Claims] 1. A ram combustor and a ram combustor provided in the ram combustor.
And Bed Suta for propellant to the material of the solid fuel, and Sasutena for propellant to generate combustible gas is ignited following the combustion of the propellant for the booster, the provided on the rear of the ram combustor A booster nozzle for injecting a high-temperature gas generated by the combustion of the booster propellant to the outside, and a mixture of the flammable gas and the compressed air which is provided at a rear portion of the ram combustor and flows into the ram combustor from outside. Equipped with a ram nozzle that injects the high-temperature gas generated by combustion by the outside,
The booster nozzle used for the booster propellant
Ram rocket, characterized in that a more formed into a solid fuel with the same combustion characteristics as body fuel. 2. A solid fuel used as a material for a booster nozzle.
Is 20-30% by weight of epoxy resin, ammonium perchlorate
It is assumed that the composition is 70 to 80% by weight of
The ram rocket according to claim 1.