JP3998083B2 - Propulsion rocket - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a propulsion rocket.
[0002]
[Prior art]
FIGS. 6 and 7 show a conventional propulsion rocket. A substantially cylindrical main body 1 contains a propellant and generates a combustion gas when ignited by an ignition device (not shown). The combustion gas is emitted from a gas ejection nozzle port 2. Propulsive force is generated in the direction of the ejection axis C. A lateral drive mechanism Y is provided in the main body 1 in the vicinity of the gas ejection nozzle port 2 in order to generate a driving force having a vertical component with respect to the axial direction. Four drive bodies 3 are attached to the peripheral wall of the main body 1 at equal angular intervals, and have a direction control unit 3a that is driven hydraulically or electrically. In other words, the lateral drive mechanism Y of the conventional example is composed of four drive bodies that are provided near the gas ejection nozzle port 2 and are respectively operated by hydraulic or electric drive units, and the gas ejection nozzle port 2 is operated by the direction control unit 3a. The direction of the gas ejected from is deflected.
[0003]
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 increased.
[0004]
[Problems to be solved by the invention]
The present invention has been made in view of the above-described problems, and an object thereof is to provide a propulsion rocket capable of reliably obtaining a lateral driving force in a desired direction with a simple structure.
[0005]
[Means for Solving the Problems]
The above problems include a main body containing a propellant and a gas outlet provided at one end of the main body, and the combustion gas is ejected to the outer peripheral surface of the main body in a direction substantially perpendicular to the axial direction of the main body. In the propulsion rocket provided with a plurality of gas ejection ports and having a lateral drive mechanism containing a propellant, the lateral drive mechanism is composed of two lateral drive mechanism sections, one of which is the one end portion. The other is provided near the center of gravity of the main body,
The lateral drive mechanism has at least three gas jets provided on a peripheral side wall of a casing forming an annular space, and includes gates that can open and close the gas jets, respectively. It is a plate-like member that is slidably attached on the outer peripheral surface, and is solved by a propulsion rocket that closes the gas jet port when the plate-like member slides.
[0006]
DETAILED DESCRIPTION OF THE INVENTION
FIG. 1 shows a propulsion rocket according to an embodiment of the present invention, but portions corresponding to those in FIG. 6 are given the same reference numerals and detailed description thereof is omitted.
[0007]
A first lateral drive mechanism unit 4 is attached near the gas outlet 2 of the propulsion rocket, and a second lateral drive mechanism unit 5 is attached near the entire center of gravity. Since the first lateral drive mechanism unit 4 and the second lateral drive mechanism unit 5 have substantially the same configuration, only one of them will be described.
[0008]
FIGS. 2 to 5 show details of the first lateral drive mechanism unit 4. In FIGS. 2 and 3, the annular casing 6 is fitted and fixed to the main body 1 through an attachment mechanism. The annular propellant 7 is stored in the annular space 8. As shown in FIG. 3, the propellant 7 has round through holes 7a or holes 7a formed at equal angular intervals.
[0009]
An annular closing member 10 is fitted into the annular opening 9 of the casing 6 with a seal ring g attached thereto. The closing member 10 is fixed to the casing 6 with countersunk screws 12 and 14 on the inner and outer peripheral walls. A casing 11 containing an ignition powder 11a is accommodated in the annular space 15 of the closing member 10. As shown in FIG. 3, holes 6b are formed on the outer peripheral wall of the annular casing 6 at intervals of 90 degrees. A nozzle hole 16 is formed in the closing member 10 in alignment with these holes 6b. The casing 11 containing the ignition powder 11a has an arc shape as shown in FIG. 3, and is provided at two locations facing each other in the radial direction.
[0010]
As shown in FIG. 3, inverted T-shaped grooves 18 are formed in the outer peripheral wall of the casing 6, and the gate plate 13 is slidably fitted in these grooves 18. A nozzle hole 13 a is formed in the gate plate 13. The position shown in FIG. 2 is a closed position, and this nozzle hole 13a is not aligned with the hole 6b of the casing 6, but when it moves rightward, it aligns with the hole 6b and takes an open position. Note that a stopper for positioning is provided without any explicit indication. A drive mechanism for driving the gate plate 13 to the open position is provided in the vicinity, not shown.
[0011]
The embodiment of the present invention is configured as described above. Next, the operation thereof will be described.
[0012]
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 it is now desired to bend the rocket to the right with respect to the propulsion direction, the first lateral drive mechanism 4 is actuated. That is, the igniter 11 is ignited, the propellant 7 is ignited, and combustion gas is generated. The right gate plate 13 is driven to the open position with respect to the propulsion direction of the lateral drive mechanism unit 4. The main body 1 receives a lateral driving force to the left at the end and turns to the right. Similarly, when it is desired to turn leftward, the left gate plate 13 is opened in FIG.
[0013]
In the state where the explosive in the main body 1 is burned out and the propelling force in the axial direction C is lost, the second lateral drive mechanism 5 mounted at the center of gravity is operated. That is, the igniter 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 it is desired to drive the rocket 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 laterally, the upper or lower gate plate 13 in FIG. 3 is also opened. The same applies to the driving of the gate plate 13 of the lateral driving mechanism 4 when there is a propulsion driving force. 4 and 5 are development views showing selective opening and closing of the gate plate 13. FIG.
[0014]
According to the present invention, since a plurality of holes 16 are formed so as to communicate with one annular space 8, the same combustion pressure is released outward when two or more openings 6b are simultaneously opened, and the desired direction. A conversion can be made. Moreover, since the through-hole 7a is formed in the explosive 7, the surface area can be increased and the combustion rate can be increased.
[0015]
The embodiment of the present invention has been described above. Of course, the present invention is not limited to this, and various modifications can be made based on the technical idea of the present invention.
[0016]
For example, according to the embodiment described above, two lateral drive mechanism portions are provided, but one of them may be provided. In particular, a plurality of lateral drive mechanism portions may be provided, and the trajectory can be corrected with a fine time. Further, the number of holes 6b is not limited to four, and a larger number may be formed. It is sufficient 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. Further, the propellant 7 may be arranged in an annular shape in a circular shape instead of an annular shape. Furthermore, although the through-hole 7a or the hole 7a penetrates, it does not need to penetrate with a bottom (hole). A plurality of holes may be formed in the diameter direction.
[0017]
【The invention's effect】
According to the propulsion rocket of the present invention, it can be reliably driven 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 the present embodiment.
FIG. 2 is a fragmentary front view of a main part.
FIG. 3 is a cutaway side view of a main part.
FIG. 4 is an exploded plan view of a main part.
FIG. 5 is an exploded plan view of the main part for 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 Lateral drive mechanism part 5 Lateral drive mechanism part 6 Casing 6b Nozzle opening 7 Propellant 13 Gate board 13a Hole

Claims (2)

A lateral drive provided with a main body containing a propellant and a gas outlet provided at one end of the main body, and causing the outer peripheral surface of the main body to eject combustion gas in a direction transverse to the axial direction of the main body In the propulsion rocket provided with a mechanism, the lateral drive mechanism is composed of two lateral drive mechanism parts, one of which is provided near the one end and the other is provided at the center of gravity of the main body,
The lateral drive mechanism has at least three gas jets provided on a peripheral side wall of a casing forming an annular space, and includes gates that can open and close the gas jets, respectively. It is a plate-like member attached slidably on the outer peripheral surface,
The propulsion rocket characterized in that the gas outlet is closed by sliding the plate-like member. A nozzle hole is formed in the plate-shaped member, and a position where the nozzle hole and the gas outlet are aligned is an open position, and the combustion gas is ejected at the open position. The propulsion rocket according to 1.

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