JPS599744B2 - rocket engine - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a rocket engine suitable for use as a high-altitude flying object.

As is well known, in order to effectively launch a projectile to a high altitude, there is an optimal combination of the thrust of the rocket engine and the operating time of the thrust (normal operating time).

(Patent Application Publication No. 1976-762, Patent Application Publication No. 1972)
-6762).

Most conventional rockets were of the internal combustion type, which did not provide the optimal combination of thrust and time.

There is also a special end-combustion type in which a high-burning-rate propellant, etc. is embedded on the shaft, as disclosed in some of the above-mentioned patent applications, but it is not widely used.

In order to obtain a rocket engine that can achieve an optimal combination of thrust and operating time using only grains with a burning rate that can be easily obtained at present, the present inventor has conducted various studies, and found that grains are placed in the rocket chamber alternately inward from the inner wall. This objective is achieved by arranging a plurality of flat combustion restricting materials that protrude from the grain and extend in parallel to each other to divide the dalein and bend the direction of combustion of the grains into a lightning bolt shape.

That is, in the present invention, a rocket chamber is loaded with grains, and the grains are partitioned by a plurality of flat combustion restricting materials that extend parallel to each other in the direction of the rocket's central axis. They are arranged symmetrically with respect to the imaginary plane of the longitudinal section through which they pass, and in the cross section, one end is fixed to the inner periphery of the rocket chamber and the other end is arranged away from the inner periphery, so that the direction of grain combustion is symmetrical to the combustion direction. The present invention provides a rocket engine characterized in that the restricting member is bent at the other end thereof.

In the case of internal combustion type rockets, the distance that the grains burn (hereinafter referred to as the web) is usually 25 to 30% of the diameter of the grains, but in the rocket engine of the present invention, two combustion restriction materials are used. Even if one is placed on each side and the direction of grain combustion is refracted once, a web twice the diameter of the grain is essentially obtained; if two are placed on each side and refracted twice. A web four times the diameter of the grain, or even more if refracted three or more times, can be obtained.

When multiple combustion restriction materials are arranged on the left and right sides, one end of the material is fixed alternately above and below the inner periphery of the rocket chamber in cross section, and the other end separated from the inner periphery is fixed in the direction of combustion. Of course, they are arranged so that they are sequentially refracted in the shape of a lightning bolt.

An embodiment of the present invention will be described below based on the drawings.

A thrust pattern having the shape shown in FIG. 3, which is an embodiment of the present invention, is shown in FIG. 2b.

The thrust pattern shown in Figure 2a is a typical example of the internal combustion type shown in Figure 1, but it is similar to the thrust pattern shown in Figure 3 when the dimensions, type of grain 1, and combustion pressure are the same. It is something.

In the case of this embodiment, since it is of the twice-bending type, the actual web is about 8 times as large, and therefore the thrust is about 1/8.

The progress state of combustion in the double refraction type of the embodiment is as shown in the combustion progress plane A in FIG.

With this shape, there is a sharp increase in the combustion area in the vicinity where the direction of combustion is bent, but in order to prevent this, another embodiment of the outer circumferential restrictor 4 of the engine 2 as shown in FIG. There is a method of installing a combustion restricting material 3 in the shape of a slightly triangular prism on an inner wall or the like.

Note that 1a in FIG. 4 shows the initial surface of grain combustion.

FIG. 5 shows an example of calculating the operating time as a parameter when the altitude reached and the thrust x time are constant.

This was calculated using vertical ascent, assuming that the rocket diameter was 110mm, the length of the rocket engine was 2400mm, and the structural weight and instrument weight were constant.

The operating time is shown in d on the horizontal axis of Fig. 5. For a rocket of this size, e is the required combustion speed of grain 1 when the internal combustion type is used, and f is the required combustion speed when the end combustion type is used.
, the format of the present invention is also shown in g.

Incidentally, the combustion speed that can be easily achieved at present is approximately 3 mm/see.
Since it is about 15 to 16 degrees/sec, the range is e,
Indicated by diagonal lines above f and g.

According to this, the end combustion type is completely inefficient due to the lack of thrust, and the internal combustion type has an altitude of approximately 60%, which is the optimum design altitude.
% is the highest.

However, according to the two-fold refraction method of the present invention, it is found that an optimal design can be easily achieved using the existing grain 1.

Other examples include a one-time refraction type as shown in FIG. 8, a three-time refraction type as shown in FIG. 9, and more refraction types are easily possible.

That is, according to the present invention, it has become possible to design a thrust pattern that is intermediate between the thrust pattern obtained by the conventional internal combustion type and the thrust pattern obtained by the end face combustion type.

When launching with the rocket engine 2 of the present invention, if the initial thrust is not sufficient, consideration should be given to supplementing the speed at the time of launcher separation by using it together with an internal combustion type booster grain 5 as shown in Fig. 6. Good.

In addition, 6 in FIG. 6 indicates a nozzle.

[Brief explanation of the drawing]

1 and 2 show a conventional example according to the present invention, FIG. 1 is a sectional view of a conventional internal combustion type rocket, FIG. 2 is a graph of the thrust F1 time t curve, and a is a 1, b is a graph in the format of FIG. 3, FIGS. 3 to 6 show an embodiment of the present invention, and FIG. 4 is an enlarged view of main parts showing the progress of combustion, FIG. 5 is a graph showing the relationship between operating time t1 burning speed r reached altitude Z in one embodiment, C is t r r s A graph of the c curve, d is a graph of the t curve, e is a graph of the required burning rate r curve for internal combustion, f is r for end combustion.
A curve graph diagram, g is an r curve graph diagram when the two-fold refraction type of the present invention is used, FIG. 6 is a vertical cross-sectional view of an embodiment of a rocket engine when applied to an actual rocket, and FIG. 7 9 to 9 show other embodiments of the present invention, and I-I in FIG.
FIG. 3 is a cross-sectional view of the rocket along a line. A... Burning progress surface, 1... Grain,
1a... Grain combustion initial surface, 2... Cap engine, 3... Combustion restriction material, 4...
...Perimeter restrictor, 5...Booster grain, 6...Nozzle.

Claims (1)

[Claims] 1 Grain is loaded into the rocket chamber, and the grain is partitioned by a plurality of flat combustion restricting materials that extend parallel to each other in the direction of the rocket's central axis, and these combustion restricting materials have a vertical cross section passing through the rocket's central axis. They are arranged symmetrically with respect to an imaginary plane, and in a cross section, one end is fixed to the inner periphery of the rocket chamber and the other end is arranged away from the inner periphery, so that the direction of combustion of the grains is aligned with the combustion restriction material. A rocket engine characterized by being bent at the other end.