JP2000018898A - Propulsion rocket - Google Patents

Abstract

PROBLEM TO BE SOLVED: To drive sideways surely in desired direction through a simple structure. SOLUTION: The propulsion rocket comprises a body 1 incorporating a propellant, a gas ejection opening made at one end part of the body, a plurality of gas ejection openings for ejecting combustion gas substantially perpendicularly to the axial direction of the body 1, and a lateral drive mechanism incorporating a propellant. The lateral drive mechanism is provided with a propellant on the inside of a casing 6 defining an annular space and at least three gas ejection openings in the circumferential side wall and they are opened/closed selectively by means of a gate.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

The present invention relates to a propulsion rocket.

[0002]

2. Description of the Related Art FIGS. 6 and 7 show a conventional propulsion rocket. A substantially cylindrical main body 1 contains a propellant and generates combustion gas when ignited by an igniter (not shown). The combustion gas is ejected from 2 to generate a propulsive force in the direction of the axis C. In order to generate a driving force of a component perpendicular to the axial direction, a horizontal drive mechanism Y is provided in the main body 1 near the gas ejection nozzle port 2. Four driving bodies 3 are attached to the peripheral wall of the main body 1 at equal angular intervals, and include a direction control unit 3a driven hydraulically or electrically. That is, the lateral drive mechanism Y of the conventional example is composed of four driving members provided near the gas ejection nozzle port 2 and each of which is operated by a hydraulic or electric drive unit, and is controlled by the direction control unit 3a. To deflect the direction of the gas ejected from it.

When these are selectively operated, a lateral driving force in a predetermined direction is generated, but the structure is complicated and the deflection angle cannot be made large.

[0004]

SUMMARY OF THE INVENTION The present invention has been made in view of the above problems, and has as its object to provide a propulsion rocket capable of reliably obtaining a lateral driving force in a desired direction with a simple structure.

[0005]

The object of the present invention is to provide a main body containing a propellant and a gas outlet provided at one end of the main body. On the other hand, in a propulsion rocket provided with a plurality of gas ejection ports so as to eject combustion gas in a substantially vertical direction and having a lateral drive mechanism containing a propellant, the lateral drive mechanism is provided around a casing forming an annular space. The side wall is provided with at least three gas jets, each of which is solved by a propulsion rocket having a gate which can be selectively opened and closed.

[0006]

FIG. 1 shows a propulsion rocket according to an embodiment of the present invention. Parts corresponding to those in FIG. 6 are denoted by the same reference numerals, and detailed description thereof will be omitted.

A first lateral drive mechanism 4 is mounted near the gas outlet 2 of the propulsion rocket, and a second lateral drive mechanism 5 is mounted near the center of gravity of the whole. First horizontal drive mechanism 4
Since the second horizontal drive mechanism 5 and the second horizontal drive mechanism 5 have substantially the same configuration, only one of them will be described.

FIGS. 2 to 5 show the details of the first lateral drive mechanism 4, and FIGS.
Is fitted and fixed to the main body 1 via a mounting mechanism. An annular propellant 7 is stored in an annular space 8. As shown in FIG. 3, the propellant 7 has round through holes 7a or holes 7a formed at equal angular intervals.

An annular closing member 10 is fitted in the annular opening 9 of the casing 6 with a seal ring g mounted thereon. The closing member 10 has a countersunk screw 12 on the inner peripheral wall and the outer peripheral wall.
And 14 to the casing 6. In the annular space 15 of the closing member 10, a casing 11 containing an ignition charge 11a is housed. Holes 6b are formed on the outer peripheral wall of the annular casing 6 at intervals of 90 degrees as shown in FIG. The nozzle holes 16 are formed in the closing member 10 in alignment with the holes 6b. The casing 11 containing the igniter 11a has an arc shape as shown in FIG. 3, and is provided at two locations facing each other in the radial direction.

As shown in FIG. 3, an inverted T-shaped groove 18 is formed in the outer peripheral wall of the casing 6, and the gate plate 13 is slidably fitted in the groove 18. A nozzle hole 13a is formed in the gate plate 13. The position shown in FIG. 2 is the closed position, and this nozzle hole 13a is not aligned with the hole 6b of the casing 6, but when moved to the right, it is aligned with the hole 6b and assumes the open position. Note that a stopper for this positioning is provided even if not explicitly shown. A drive mechanism for driving the gate plate 13 to the open position is provided in the vicinity, not shown.

The embodiment of the present invention is configured as described above. Next, the operation thereof will be described.

When the propellant in the main body 1 is ignited, combustion gas is injected from the gas injection port 2 and the rocket generates a propulsive force in the axial direction C. If the rocket is to be bent rightward in the propulsion direction, the first lateral drive mechanism 4 is operated.
That is, the ignition charge 11 is ignited, the propellant 7 is ignited,
Generates combustion gas. The right gate plate 13 with respect to the propulsion direction of the lateral drive mechanism 4 is driven to the open position. The main body 1 receives the lateral driving force to the left at the end and turns to the right. Similarly, when it is desired to turn left, the left gate plate 13 in FIG. 3 is opened.

The explosive in the main body 1 has been burned out, and the
When the propulsion force is no longer present, the second lateral drive mechanism 5 mounted at the position of the center of gravity is operated. That is, the ignition charge 11 is ignited, and the propellant 7 is ignited. In this case, when it is desired to drive the rocket laterally to the right, the gate plate 13 on the left side of the lateral drive mechanism 5 is opened. When the rocket is to be driven laterally to the left, the gate plate 13 on the right side of the lateral drive mechanism 5 is opened. When it is desired to drive obliquely horizontally, both the upper and lower gate plates 13 in FIG. 3 are opened. Gate plate 1 of lateral drive mechanism 4 when there is a propulsion drive force
The same applies to the driving of No. 3. 4 and 5 are development views showing selective opening and closing of the gate plate 13. FIG.

According to the present invention, since a plurality of holes 16 are formed so as to communicate with one annular space 8, when two or more openings 6b are simultaneously opened, the same combustion pressure is released outwardly, and Change direction. Also,
Since the through holes 7a are formed in the explosive 7, the surface area can be increased and the combustion rate can be increased.

Although the embodiment of the present invention has been described above, the present invention is, of course, not limited to this, and various modifications can be made based on the technical idea of the present invention.

For example, according to the above-described embodiment, two lateral drive mechanisms are provided, but either one may be provided. In particular, a plurality of lateral drive mechanisms may be provided at the position of the center of gravity, and the trajectory may be corrected at a timely interval. I can do it. Also, the number of holes 6b may be more than four. What is necessary is just to form at least three. In driving a plurality of gate plates, the direction of deflection or lateral movement can be finely adjusted by providing a difference in opening time. The propellant 7 may be a plurality of arcs instead of a ring and may be arranged in a ring. Furthermore, the through hole 7a or the hole 7
a penetrates but does not have to penetrate with a bottom (hole). A plurality of holes may be formed in the diameter direction.

[0017]

According to the propulsion rocket of the present invention, it is possible to reliably drive the rocket laterally in a desired direction. Moreover, it has a simple structure.

[Brief description of the drawings]

FIG. 1 is a side view of a propulsion rocket according to an embodiment.

FIG. 2 is a fragmentary front view of a relevant part.

FIG. 3 is a cutaway side view of a main part.

FIG. 4 is a developed plan view of a main part.

FIG. 5 is a developed plan view of the main part, showing opening and closing of the gate plate.

FIG. 6 is a side view of a conventional propulsion rocket.

FIG. 7 is a rear view of the same.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Main body 2 Gas ejection nozzle port 4 Horizontal drive mechanism 5 Horizontal drive mechanism 6 Casing 6b Nozzle port 7 Propellant 13 Gate plate 13a Hole

Claims (4)

[Claims] 1. A main body containing a propellant and a gas outlet provided at one end of the main body, and a combustion gas is jetted to an outer peripheral surface of the main body in a direction transverse to an axial direction of the main body. In the propulsion rocket equipped with the lateral drive mechanism,
The lateral drive mechanism is provided with at least three gas ejection ports on a peripheral side wall of a casing forming an annular space, and each of these gas ejection ports is provided with a gate that can be selectively opened and closed. Propulsion rocket. 2. The propulsion rocket according to claim 1, wherein the casing contains one annular propellant or a plurality of annularly disposed propellants. 3. The propulsion rocket according to claim 2, wherein a plurality of holes or holes are formed in a thickness direction or a diameter direction of the propellant. 4. The horizontal drive mechanism comprises two horizontal drive mechanisms, one of which is provided near the one end and the other is provided substantially corresponding to the center of gravity of the whole. A propulsion rocket according to any one of claims 1 to 3.