JPH10111100A - Rocket motor separation/rear-end collision prevention apparatus - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide an apparatus with a simplified structure having both functions of separation of a rocket motor and of rear-end collision prevention by producing gas from a gas generator to forwardly thrust a piston up to a stop position, and injecting gas from an opening in a piston side surface. SOLUTION: A flying structure is of a structure where a front flying structure 2 and a rocket motor 4 are separable with a separation surface 1 taken as a boundary (a), and a front end of a piston 6 of a rocket motor separation/ rear-end collision prevention apparatus 3 makes contact with a rear end of the front flying structure 2. The front end of the piston 6 is closed, and a rear end of the same is opened. The piston 6 advances to a dotted position or a position where a stopper engagemen part of the piston 6 is engaged with a stopper of a cylinder 8. Hereby, the rocket motor 4 is separated, and the rocket motor 4 is prevented from colliding the front flying structure 2.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a rocket motor separation and rear-end collision prevention device for a flying object.

[0002]

2. Description of the Related Art FIG. 5 is an explanatory view of rocket motor separation of a conventional flying object by a rocket motor separation device.
(A), (b), and (c) show the separated state of the rocket motor over time. In the figure, 2 is a front projectile, 4 is a rocket motor, 13 is a rocket motor separation device, 11 is a battery, 5 is a steering wing provided at the rear of the rocket motor, and 12 is a center of gravity of the rocket motor. The rocket motor separation device 13 is provided on the rocket motor side of the separation plane between the front projectile 2 and the rocket motor 4 and includes a piston and a gas generator in a cylinder. The gas generated by the gas generator causes the piston to protrude forward, and separates the rocket motor from the front projectile. Thereafter, the steering wing 5 is steered by using the battery 11 mounted on the rocket motor as a power source to deflect the path angle at which the rocket motor travels from the path angle at which the front flying body travels, and the rocket motor turns the front flying body. To prevent rear-end collision. That is, conventionally, in order to separate the rocket motor and prevent the rear-end collision, a rocket motor separating mechanism and a device for steering the steering wing were required.

[0003]

In the conventional method, a device for separating the rocket motor from the front projectile and a means for preventing rear-end collision are independent, and two methods are used for separation and prevention of rear-end collision of the rocket motor. Since a sequence is required, there is a problem that the number of sequences is increased and reliability is reduced.
Further, since a battery for outputting a steering angle command is mounted on the rocket motor side to deflect the steering blade after the rocket motor is separated, the weight of the fuselage is increased. Further, since the ignition ball for activating the battery is a pyrotechnic, there is a problem in that handling risks increase.

[0004] The present invention solves the above-mentioned problems of the prior art,
It is an object of the present invention to provide a rocket motor separation / end collision prevention device having a simple structure and having both functions of separating the rocket motor and preventing rear end collision.

[0005]

SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems, and separates a front flying object of a flying object from a rocket motor during the flight so that the rocket motor collides with the front flying object. In a rocket motor separation / collision prevention device, a cylinder having a stopper at a front end, a tubular shape, a front end closed, a rear end opened, an opening on a side surface, and a stopper engagement portion on a rear end outer surface. Comprising a piston slidably mounted in the cylinder, and a gas generator housed at the rear end of the cylinder,
The present invention relates to a rocket motor separation / collision prevention device characterized in that gas is generated from the gas generator in the cylinder, the piston is protruded forward to a stop position, and the gas is ejected from an opening on the side surface of the piston.

The rocket motor separation / collision prevention device of the present invention is mounted on the front end of the rocket motor in the machine axis direction.
In a state before separation, the piston is in a retracted position in the cylinder, and a front end of the piston is in contact with a rear end of the front flying object. When the gas is generated from the gas generator while the flying object is flying, the piston projects forward while pushing the rear end of the front flying object, and the front flying object and the rocket motor are separated. The piston engages the stopper and stops. When the piston projects forward, the opening on the side surface of the piston is exposed to the atmosphere, and the gas in the piston blows out from the opening to give a moment to the rocket motor. As a result, the traveling direction of the rocket motor is changed, and it is possible to prevent a collision with the front flying object.

[0007]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS FIG. 1 is a diagram of a rocket motor separation / collision prevention device according to an embodiment of the present invention.
(A) is a side view of the whole structure of the flying object which shows the installation position of the same device, (b) is a longitudinal sectional view of the same device. In FIG. 1A, reference numeral 2 denotes a front projectile, reference numeral 4 denotes a rocket motor, reference numeral 1 denotes a dividing surface thereof, and reference numeral 3 denotes a rocket motor separation / collision prevention device installed at the front of the rocket motor. In FIG. 1B, 8 is a cylinder, 6 is a piston provided in the cylinder, and 7 is a gas generator. The projectile has a structure in which the front projectile 2 and the rocket motor 4 can be separated from each other with the separation surface 1 as a boundary as shown in FIG.
The front end of the piston of the rear-end collision prevention device 3 is in contact with the rear end of the front flying object.

FIG. 2 is a detailed vertical sectional view of the rocket motor separating / collision preventing device 3. As shown in FIG. In the figure, reference numeral 8 denotes a cylinder, and 8a denotes a stopper provided inside the front end of the cylinder, which is an annular inwardly projecting portion. 8b is an O-ring. Numeral 6 denotes a cylindrical piston slidably held in the cylinder, and numeral 6a denotes a stopper engaging portion provided on the outer surface of the rear end of the piston, which has a flange shape. 6b is an O-ring. Reference numeral 7 denotes a gas generator housed at the inner rear end of the cylinder 8, and 9 denotes an opening provided on a side surface of the piston 6. The front end of the piston is closed and the rear end is open. The piston can be advanced to the position shown by the dotted line, that is, the position where the stopper engaging portion of the piston engages the stopper of the cylinder.

FIG. 3 is a view of the piston 6, and FIG.
FIG. 2B is a side view, and FIG. 2B is a sectional view taken along the line AA in FIG. An opening 9 is provided on a side surface of the piston 6. The piston 6 is driven by the pressure of the gas generated by the gas generator 7.
Project forward to the position shown by the dotted line in FIG.
Is pushed, and the front flying object 2 and the rocket motor 4 are separated by the separation surface 1. The opening 9 of the piston 6 corresponds to the cylinder 8
Moved to the outside and exposed to the outside air. The gas generated by the gas generator 7 blows out to the side through the opening 9.

FIG. 4 is a view for explaining the operation of the rocket motor separation / back-end collision prevention device. (A), (b), (c) in the figure
Indicates the separated state of the rocket motor over time. In the figure, reference numeral 10 denotes a jet jetting from the opening 9 to the side. The jet 10 causes the rocket motor 4 to rotate about the rocket motor center of gravity 12, and the traveling path angle is deflected from the traveling path angle of the front flying object 3. This can prevent the rocket motor 4 from colliding with the front flying object 3.

In this apparatus, the operation of separating the rocket motor from the front flying object and the operation of preventing the rocket motor from hitting the front flying object can be executed in one sequence. Therefore, the number of sequences can be reduced, and the reliability can be improved. Further, since the battery provided for steering the steering wing after the rocket motor is separated becomes unnecessary, the weight of the fuselage is reduced. Furthermore, since the ignition ball provided in the battery is not required, pyrotechnics are reduced, and handling risks are reduced.

[0012]

According to the rocket motor separation / collision prevention device of the present invention, the rocket motor includes a cylinder, a piston, and a gas generator. The gas is generated from the gas generator in the cylinder, and the piston is forwardly projected to a stop position. Since the gas is ejected from the opening on the side surface of the piston, the rocket motor can be separated and the rocket motor can be prevented from colliding with the front flying object.

[Brief description of the drawings]

1A and 1B are diagrams of a rocket motor separation / collision prevention device according to an embodiment of the present invention, wherein FIG. 1A is a side view of a flying object showing an installation position of the device, and FIG. Area view.

FIG. 2 is a detailed vertical cross-sectional view of the rocket motor separation / collision prevention device.

3A and 3B are diagrams of a piston of the same device, in which FIG. 3A is a side view, and FIG. 3B is a sectional view taken along line AA of FIG. 3A.

FIG. 4 is an explanatory diagram of the operation of the rocket motor separation / collision prevention device.

FIG. 5 is an explanatory view of rocket motor separation by a conventional flying object rocket motor separation device.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Separation surface 2 Front flying object 3 Rocket motor separation / collision prevention device 4 Rocket motor 5 Steering blade 6 Piston 6a Stopper engaging portion 6b O-ring 7 Gas generator 8 Cylinder 8a Stopper 8b O-ring 9 Opening 10 Jet 11 Battery 12 Rocket motor center of gravity 13 Rocket motor separation device (conventional)

Claims (1)

[Claims] 1. A rocket motor separation / collision prevention device for separating a rocket motor from a front projectile of a flying object and a rocket motor during the flight so as to prevent the rocket motor from colliding with the front projectile. Cylinder with stopper,
A piston having a tubular shape, a front end closed, a rear end opened, a side opening, a rear end outer surface provided with a stopper engaging portion, a piston slidably mounted in the cylinder, and a rear end in the cylinder A rocket motor separation device comprising: a gas generator housed in a cylinder; generating gas from the gas generator in the cylinder; projecting the piston forward to a stop position; and ejecting the gas from an opening in a side surface of the piston. -Rear-end collision prevention device.