JPH02211363A - Two-stage driving force type rocket motor - Google Patents

Abstract

PURPOSE:To prevent the breakage of a nozzle and improve reliability and secure stability by installing the first locking means for locking and releasing the lock for a port cover and the second locking means for locking the port cover at a position slid rearward. CONSTITUTION:The propellant in the first stage is ignited, and then combustion is started from the inside surface, and high temperature and high pressure gas is generated. Since, in this state, an opened port 41 is closed by a port cover 50, the generated gas is discharged outside through a nozzle. When the combustion of the propellant in the first stage is completed, the propellant is ignited by an ignitor in the second combustion chamber 30 in a prescribed timing, and the fixation by a machine screw 51 is released by the gas pressure generated by the combustion, and the port cover 50 is slided rearward until it is locked by a tapered surface 77a. Therefore, the first and second combustion chambers 20 and 30 are allowed to communicate through an opened port 41 from the throat of the nozzle having a large diameter, and the generated gas flow is discharged outside through the nozzle, passing through the opened port 41 and the first combustion chamber 20.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an improvement of a two-stage thrust type rocket motor having a first stage and a second stage that generate two stages of thrust.

[Prior Art] In this type of two-stage thrust rocket motor, in order to perform flight control using the inertia of the rocket, it is necessary to burn the second stage without cutting off the first stage that has finished burning. There is.

In order to ignite the second stage independently of the first stage, the combustion power of the first stage is not transmitted to the second stage. The first stage must be used as a mere passageway to the nozzle to direct the combustion power of the second stage to the nozzle without attenuation.

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

The hoard cover 4 is made of cast iron, ceramic, glass, etc., and has a dome shape that allows the first
It is designed to withstand the combustion forces of the second stage and shatter into fine fragments upon ignition of the second stage.
e of Aeronautics and Astr
onautics) published in 1968.
-86-1576Tha Dual-Interrupt
ted-Thrust Pulse Motor”].

[Problems to be Solved by the Invention] However, in the above-mentioned conventional two-stage thrust rocket motor, the fragments of the port cover that are crushed when the second stage ignites are pushed through the nozzle by the combustion gas pressure of the second stage. There is an inherent risk of collision and damage to the nozzle as it is emitted to the outside world through the nozzle.

Furthermore, since the port cover 4 is made of a brittle material such as ceramic, it is susceptible to vibrations, shocks, etc., and may be damaged during combustion in the first stage.

[Means for Solving the Problems] This invention has been made in view of the above-mentioned problems, and it is possible to form a gas flow path leading to the nozzle without crushing the port cover even during ignition of the second stage. It is an object of the present invention to provide a two-stage thrust type rocket motor with no risk of damage to the nozzle.

In order to achieve this object, the two-stage thrust rocket motor according to the present invention has a combustion chamber of the first stage that is continuous with the nozzle at the rear end, and a second stage that is located in front of the first stage. a combustion chamber, a partition wall provided between both combustion chambers and having an opening in the center, a port cover provided on the partition wall so as to be slidable back and forth to close the opening, and a port cover locked in a forward position to close the opening. In addition, the present invention is characterized in that it has a first locking means that releases the lock during second stage combustion, and a second locking means that locks the port cover in a rearwardly slid position during second stage combustion.

[Operation] According to the above configuration, during combustion in the first stage, the port cover is locked by the first locking means at a position where it closes the central opening of the partition wall. Then, the first locking means is released by ignition of the second stage, and the port cover slides tangentially to open the central opening. The second 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 rearward sliding position by the second locking means.

[Example] The present invention will be described below based on the drawings. 1 to 6 show an embodiment of the present invention.

As shown in FIG. 5, the rocket motor shown in this example has a combustion chamber (first combustion chamber) 20 of the first stage that communicates with the nozzle lO at the rear end, and a linear 2nd stage combustion chambers (second combustion chambers) 30 arranged in a row, an inner flange-shaped partition wall 40 having a central opening 41 provided between both combustion chambers, and a central partition wall between the two combustion chambers. A port cover 50 that can freely slide forward and backward to open and close the opening 41
It is equipped with

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

This motor has propellant 6 on the inner surface of the peripheral wall of the combustion chamber 20.30.
It has an internal combustion type structure in which 0.61 is fixed in an annular shape. Propulsion 1Ii80.61 is a mixture of fuel such as synthetic rubber and an oxidizing agent and solidified, and is loaded into the peripheral wall of each combustion chamber via a heat insulating liner.

A propellant 60 is placed in the center of the tip side of each combustion chamber 20, 30.
An igniter 70,80 for igniting at 61° is provided, respectively. The igniter is itself a small rocket, and the source of ignition is a small amount of gunpowder.

The igniter 70 of the first combustion chamber has three
It is supported by book columns 21, 21, . The distal end side of a cylindrical sleeve member 74 is fitted into this cup-shaped member 73, and a case 7 whose rear end is closed in a hemispherical shape is located inside the sleeve member 74.
5 is inserted.

At four positions in the axial direction of the holder 72, there are
Four rows of through holes are formed spaced apart from each other, and a main charge 76 in the form of a short cylindrical pellet is accommodated and held in the through holes. Further, a ring-shaped stopper 77, which will be described later, is screwed onto the rear end of the sleeve member 74, and the case 7
A large number of small nozzles for emitting flames are perforated in the hemispherical part of 5.

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

The port cover 50 is provided in a shape surrounding the above-mentioned guide surface 74a, and has a core made of iron and a surface made of FRP, for example, to ensure heat resistance.

The partition wall 40 and the port cover 50 are each formed in a curved shape convex toward the second combustion chamber 30 side, and in the closed state shown in FIG. 1, they partially overlap each other to close the opening 41. Separate the two combustion chambers. At this time, the partition wall 40 and the port cover 50 are temporarily fixed with screws 51. This screw 51 locks the port cover 50 in a position that closes the opening 41, and constitutes a first locking means that releases the lock during combustion in the second stage.

Further, a tapered surface 77a is formed on the outer periphery of the stopper 77 that is screwed onto the rear end of the guide surface 74a of the sleeve member 74, and the amount of outward protrusion becomes larger toward the rear. A second part that engages and locks the port cover 50 when it slides backward.
It constitutes a locking means.

The igniter 80 of the second combustion chamber 30 is supported at the center of the front mirror plate 31 that closes the front end of the second combustion chamber 30, as shown in FIG. The internal configuration is similar to the above-described igniter 70 except for the guide surface and stopper.

Next, the operation of the rocket motor with the above configuration will be explained.

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

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

The nozzle 10 converts the high-temperature, high-pressure gas generated from the propellant 60 into a supersonic flow 1151, converts the thermal 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 of the second combustion chamber 30, the gas generated by the combustion Screw 51 due to pressure
The port cover 50 slides rearward until it is locked by the tapered surface TTa as shown in FIG. 4.

With this, the first. The second combustion chambers communicate with each other through an opening 41 with a diameter larger than the throat of the nozzle 10 , and the gas flow generated from the propellant 61 of the second stage passes through the opening 41 and the first combustion chamber 20 into the nozzle 10 . is released to the outside world through

At this time, by locking the port cover 50, it is possible to prevent the port cover 50 from shaking due to the gas flow during second stage combustion.

This can prevent turbulence in the gas flow.

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

Furthermore, the combustion time, output, etc. of each stage that determines the flight pattern can be controlled by changing the shape of the propellant, etc.

By incorporating such a rocket motor into a rocket as shown in Figure 6, a flight can be achieved in which the first stage burns to approach the target, and the second stage burns to further accelerate the flight and reach the target. Rockets with patterns can be provided. In FIG. 6, the same members as in FIG. 5 are given the same reference numerals.

[Effects of the Invention] As explained above, according to the two-stage thrust type rocket motor according to the present invention, the port cover only slides rearward even when the second stage is ignited, and is not destroyed.

Therefore, there is no possibility of damaging the nozzle due to the ejection of any debris.

Further, by providing the tenth kettle means, the opening can be reliably communicated during ignition of the second stage, and reliability is improved, compared to the case where the port cover itself is crushed.

Further, by fixing the port cover that has slid rearward with the second locking means, it is possible to prevent the port cover from shaking, and it is possible to ensure the stability of the gas flow during the second stage combustion.

[Brief explanation of the drawing]

1 to 6 show an embodiment of a two-stage thrust type rocket motor according to the present invention, and FIG. 1 is a partially enlarged cross-sectional view of FIG. 5 showing a bulkhead portion, and FIG. is ■− in Figure 5.
The sectional view taken along the line II, Figure 3 is the sectional view taken along the mm line in Figure 5, and the 4th
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. 5. . FIG. 7 is a sectional view of a conventional two-stage thrust type 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)

Claims (1)

[Claims] A combustion chamber of a first stage continuous to a nozzle at the rear end, a combustion chamber of a second stage located in front of the first stage, and a partition wall provided between the two combustion chambers and having an opening in the center. , a port cover provided on the partition wall so as to be slidable back and forth to close the opening; and a first port cover that locks the port cover in a forward position that closes the opening and releases the lock during the second stage combustion. locking means;
A two-stage thrust type rocket motor, comprising: a second locking means for locking the port cover in a rearwardly slid position when the second stage is in combustion.