JP2666899B2 - Two-stage thrust rocket motor - Google Patents

Description

Description: BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an improvement of a two-stage thrust type rocket motor having a first stage and a second stage in which two-stage thrust is generated.

[Prior Art] In this type of two-stage thrust type rocket motor, in order to perform flight control utilizing the inertia force of the rocket, it is necessary to burn the second stage without releasing the first stage after combustion is completed. There is.

In order to make the ignition of the second stage independent of the first stage, the combustion power of the first stage is not transmitted to the second stage, and the first stage is burned during the combustion of the second stage. The stage must be used as a mere passage leading to the nozzle and guided to the nozzle without attenuating the combustion power of the second stage.

Therefore, conventionally, as shown in FIG. 7, a central opening is provided between the combustion chamber 1 of the first stage and the combustion chamber 2 of the second stage.
An inner flange-shaped partition 3 having 3a is provided, and this central opening 3a is closed from the first stage side by a dome-shaped port cover 4 having a convex portion directed rearward.

The port cover 4 is formed of cast iron, ceramic, glass, or the like. The dome shape of the port cover 4 withstands the combustion power of the first stage, and is designed to be crushed with the ignition of the second stage to become fine fragments. [AIAA (American Institute of Aeronautics and As
tronautics) published in 1986 by “AIAA-86-1576 The
Dual-Interrupted-Thrust Pulse Motor ".

[Problems to be Solved by the Invention] However, in the above-described conventional two-stage thrust rocket motor, fragments of the port cover that are crushed together with the ignition of the second stage stage cause the nozzles to be compressed by the combustion gas pressure of the second stage. Since it is released to the outside world through the nozzle, there is an inherent danger of collision with and damage to the nozzle.

Further, since the port cover 4 is formed of a brittle material such as ceramic, it is susceptible to vibration, impact, and the like, and may be damaged during the combustion of the first stage.

[Means for Solving the Problems] The present invention has been made in view of the above-described problem, and has a gas flow path that leads to a nozzle without crushing a port cover even during ignition of a second stage. It is another object of the present invention to provide a two-stage thrust type rocket motor having no risk of damage to a nozzle.

In order to achieve this object, a two-stage thrust type rocket motor according to the present invention includes a first stage combustion chamber connected to a rear end nozzle, and a second stage stage located in front of the first stage. And a partition provided in both combustion spaces and having an opening in the center, a port cover provided slidably back and forth in the partition and closing the opening, and locking the port cover at a front position to close the opening. ,
It has a first locking means for releasing the lock when the second stage is burning, and a second locking means for locking the port cover at a position slid backward when the second stage is burning.

[Operation] According to the above configuration, the port cover is locked at the position where the center opening of the partition is closed by the first locking means during the combustion of the first stage. Then, the first locking means is released by the ignition of the second stage, and the port cover slides rearward to open the central opening. Second
The stage stage combustion gas stream is injected from the nozzle through this opening and the first stage combustion chamber. At this time, the port cover is fixed at the position slid backward by the second lock means.

[Example] Hereinafter, the present invention will be described with reference to the drawings. Fig. 1 ~
FIG. 6 shows an embodiment of the present invention.

The rocket motor shown in this example has a first stage combustion chamber (first combustion chamber) 20 communicating with a rear end nozzle 10 as shown in FIG. A second stage combustion chamber (second combustion chamber) 30 arranged in a row; an inner flange-shaped partition wall 40 having a central opening 41 provided between the two combustion chambers; It has a port cover 50 that can slide back and forth to open and close the opening 41.

The smallest position of the opening cross section of the nozzle 10 is the nozzle throat.

This motor has propellants 60, 61 on the inner surfaces of the peripheral walls of the combustion chambers 20, 30.
Adopts an internal combustion type structure fixed in an annular shape. The propellants 60 and 61 are obtained by mixing and solidifying a fuel such as synthetic rubber and an oxidant, and are loaded on the peripheral wall of each combustion chamber via a heat insulating liner.

Igniters 70, 80 for igniting propellants 60, 61 are provided at the center portions on the tip side of the combustion chambers 20, 30, respectively. The igniter is itself a small rocket and the source of ignition is a small amount of gunpowder.

As shown in FIG. 2, the igniter 70 of the first combustion chamber
Are supported by books 21, 21,..., And a firing device 71 and a holder 72 are attached to a cup-shaped member 73 fixed to the column 21 as shown in FIG. A distal end side of a cylindrical sleeve member 74 is fitted into the cup-shaped member 73, and a case 75 having a rear end closed in a hemispherical shape is fitted inside the sleeve member 74 at the rear side. ing.

At four positions in the axial direction of the holder 72, four rows of through holes are formed at a distance of 90 ° from each other, and the main charge 76 in the form of a short columnar pellet is stored and held in the through holes. I have. Further, a ring-shaped stopper 77 described later is screwed to the rear end of the sleeve member 74, and a large number of small nozzles for flame emission are bored in a hemispherical portion of the case 75.

The igniter 70 is provided so as to penetrate the opening 41, and a guide surface 74a that supports the port cover 50 so as to be able to slide back and forth is formed around the sleeve member 74.

The port cover 50 is provided in a shape surrounding the above-described guide surface 74a. In order to ensure heat resistance, for example, the core material is iron and the surface is FRP.

The partition 40 and the port cover 50 are respectively connected to the second combustion chamber 30
In the closed state shown in FIG. 1, they are partially overlapped with each other to close the opening 41 and separate both combustion spaces. At this time, the partition wall 40 and the port cover 50 are temporarily fixed by the screws 51. These screws lock the port cover 50 at the position where the opening 41 is closed, and constitute first locking means for releasing the lock when the second stage is burned.

In addition, a taper surface 77a is formed on the outer periphery of the stopper 77 screwed to the rear end of the guide surface 74a of the sleeve member 74, the taper surface 77a having a larger outward protrusion amount toward the rear. When the port cover 50 slides rearward, it constitutes a second locking means for engaging and locking the port cover 50.

As shown in FIG. 5, the igniter 80 of the second combustion chamber 30 is entirely supported by the center of the end plate 31 which closes the front end of the second combustion chamber 30. The internal configuration is the same as the above-described igniter 70 except for the guide surface and the stopper.

Next, the operation of the rocket motor having the above configuration will be described.

First, the main charge 76 of the igniter 70 is electrically detonated by the igniter 71. This is the first stage propellant
60 is ignited and combustion starts from the inner surface of the propellant, generating high-temperature and high-pressure gas.

In this state, since the opening 41 is closed by the port cover 50, only the nozzle 10 is opened, and the generated gas is discharged to the outside via the nozzle 10.

The nozzle 10 expands the high-temperature and high-pressure gas generated from the propellant 60 into an ultrasonic flow, converts heat energy of the gas into velocity energy, and generates thrust.

When the combustion of the propellant 60 in the first stage is completed, the second stage is ignited at a predetermined timing. When the propellant 61 is ignited by the igniter 80 in the second combustion chamber 30, the fixing by the screw 51 is released by the gas pressure generated by the combustion, and the port cover 50 is formed by the tapered surface 77a as shown in FIG. Slide back until locked.

As a result, the first and second combustion chambers communicate with each other at a larger diameter than the throat of the nozzle 10 through the opening 41, and the gas flow generated from the propellant 61 in the second stage passes through the opening 41 and the first combustion chamber 20. Through the nozzle 10 to the outside world.

At this time, since the port cover 50 is locked, the port cover 50 due to the gas flow during the combustion of the second stage is
50 rattling can be prevented, and turbulence in the gas flow can be prevented.

The ignition timing of the second stage may be set by a timer at any time according to the distance to the target, or set by remote control from the ground.

Further, the combustion time and output of each stage for determining the flight pattern can be controlled by changing the shape and the like of the propellant.

By incorporating such a rocket motor into a rocket as shown in FIG. 6, a flight that approaches the target by the combustion of the first stage and reaches the target while further accelerating by the combustion of the second stage A rocket having a pattern can be provided. In FIG. 6, the same members as those in FIG. 5 are denoted by the same reference numerals.

[Effects of the Invention] As described above, according to the two-stage thrust rocket motor according to the present invention, the boat cover only slides backward when the second stage is ignited, and is not broken.

Therefore, there is no possibility of damaging the nozzle by discharging any debris.

In addition, by providing the first rocket means, the opening can be reliably communicated at the time of ignition of the second stage as compared with the case where the port cover itself is crushed, and the reliability is improved.

Further, by fixing the port cover slid rearward by the second locking means, rattling of the port cover can be prevented, and the stability of gas flow during combustion of the second stage can be secured.

[Brief description of the drawings]

1 to 6 show an embodiment of a two-stage thrust rocket motor according to the present invention. FIG. 1 is a partially enlarged sectional view of FIG. 5 showing a partition wall portion, and FIG. Is II- in Fig. 5.
FIG. 3 is a sectional view taken along the line III-III of FIG. 5, FIG.
The figure is a sectional view similar to FIG. 1 showing the sliding state of the port cover, FIG. 5 is a sectional view of the entire rocket motor, and FIG. 6 is a sectional view of a rocket incorporating the rocket motor shown in FIG. . FIG. 7 is a sectional view of a conventional two-stage thrust rocket motor. 10 Nozzle 20 First combustion chamber 30 Second combustion chamber 40 Partition wall 41 Opening 50 Port cover 51 Screw (first locking means) 77a Tapered surface (second lock) means)

 ──────────────────────────────────────────────────続 き Continuing on the front page (72) Inventor Koichi Fukuda 2-2-1 Meguro, Meguro-ku, Tokyo Meguro Germany Dormitory (72) Inventor Chihiro Iwasaki 1-6-1 Sakaemachi, Tachikawa-shi, Tokyo Japan Defense Agency Sha 1054 (72) Inventor Tadao Sasaki 2 Takaracho, Kanagawa-ku, Yokohama, Kanagawa Prefecture Inside Nissan Motor Co., Ltd. Person Kameo Matsumoto 2 Takaracho, Kanagawa-ku, Yokohama, Kanagawa Prefecture, Nissan Motor Co., Ltd. No. 1 Tetsugun-cho, Daicel Chemical Industry Co., Ltd.

Claims (1)

(57) [Claims] A combustion chamber of a first stage connected to a rear end nozzle, a combustion chamber of a second stage located in front of the first stage, and a center provided between the two combustion chambers. A partition having an opening, a port cover that is slidably provided in the partition portion to move back and forth, and closes the opening, and locks the port cover at a front position that closes the opening, and locks the second stage during combustion. First to release
A two-stage thrust rocket motor, comprising: a lock unit; and a second lock unit that locks the port cover at a position where the port cover is slid rearward during combustion of the second stage.