JP4619814B2 - Two-stage thrust rocket motor - Google Patents

Description

  TECHNICAL FIELD The present invention relates to a two-stage thrust rocket motor used in a portable guided bullet system that obtains flight thrust by firing a main rocket after a predetermined delay time after being launched from an injection mechanism with thrust of the injection rocket. It is.

A portable rocket motor that obtains flight thrust by igniting the main rocket after being launched from the injection mechanism with the thrust of the conventional injection rocket has a structure in which an injection rocket motor is arranged behind the main rocket motor axis. It is.
From the viewpoint of ensuring safety for the shooter, the rocket motor of this type, when launched from the injection mechanism, the injection rocket completes combustion in the injection mechanism, and after the inertial flight over a certain distance, the main rocket is ignited. It is desirable to obtain flight thrust.
For this reason, the performance of the injection rocket is required to generate high thrust and complete combustion in a short time, and to have a certain delay time from injection to ignition of the main rocket.

In addition, considering that personnel are carried, it is desirable to be small and light, but when the main rocket motor and the injection rocket motor are arranged in series in the axial direction, in order to further reduce the size and weight, especially in the axial direction There was a limit to the shortening.
In addition, although it is a rocket used for other applications, as a rocket structure having two combustion chambers, for example, a sub-combustion chamber is inserted into a main combustion chamber as disclosed in Patent Document 1, and the sub-combustion chamber is used as a bleed motor. A method characterized by use has also been devised.
Further, in Patent Document 2, a method is also devised in which a rocket motor is further provided on the outer periphery of the central rocket motor, and the gas jet of the central rocket and the gas jet of the outer peripheral rocket are used in combination.

As described above, after launching from the injection mechanism with the thrust of the injection rocket, the rocket motor that ignites the main rocket has a limit in reducing the length in the axial direction in order to further reduce the size and weight. there were.
If the structure that separates the sub-combustion chamber is used in the main combustion chambers found in Patent Document 1 and Patent Document 2, the length in the axial direction can be shortened. Since it is inserted into the main combustion chamber, it is expected that the combustion gas in the main combustion chamber enters the space ahead of the sub-combustion chamber and the sub-combustion chamber buckles due to the combustion gas pressure. In order to prevent buckling, it is necessary to increase the wall thickness of the auxiliary combustion chamber, and there is a problem that the length in the machine axis direction can be reduced while the mass is increased.
Japanese Patent Laid-Open No. 61-218756 Japanese Patent Publication No.33-8704

  The present invention provides a two-stage thrust rocket motor for use in a portable guided rocket system that obtains flight thrust by firing a main rocket after a predetermined delay time after launching from the injection mechanism with thrust of the injection rocket. The purpose is to become smaller and lighter.

  As a result of diligent research in consideration of the above-mentioned problems, the present inventor has divided a cylindrical sub motor case into the main motor case in a state where the front is opened, and is divided into two spaces, and one front end plate By sealing both the motor cases at the same time, two independent combustion chambers are formed, and at the same time, there is obtained a structure that does not create a space for the combustion gas of the main combustion chamber to enter the front axis of the auxiliary combustion chamber. The present invention has been achieved by discovering that it is possible to reduce the direction and reduce the weight at the same time.

That is, the present invention is as follows.
1. After launching from the injection mechanism with the thrust of the injection rocket, in the two-stage thrust rocket motor that obtains flight thrust by igniting the main rocket, insert the inner cylinder motor case with the front end open inside the main motor case, By sealing the outer main motor case and inner cylinder motor case with one front end plate, one combustion chamber is concentrically divided into two combustion chambers, one combustion chamber being an injection rocket combustion chamber, and the other combustion A two-chamber type two-stage thrust rocket motor characterized in that the chamber is a main rocket combustion chamber.
2. 1. The main rocket ignition device is operated after a certain delay time is provided from the operation of the injection rocket ignition device by one ignition signal by providing the main rocket ignition mechanism with a delay function. The two-stage thrust rocket motor described in 1.
3. 1. By using a perforated plate on the nozzle side of the injection rocket combustion chamber, it has an injection rocket motor using at least one small-diameter propellant as the injection rocket propellant. Or 2. The two-stage thrust rocket motor described in 1.

  According to the present invention, a small and light two-stage thrust used in a portable guided bullet system that obtains a flying thrust by igniting the main rocket after a predetermined delay time after being launched from the ejection mechanism with the thrust of the ejection rocket A rocket motor can be obtained.

Hereinafter, the present invention will be described with a focus on preferred embodiments.
The main motor case used in the present invention is preferably formed of a high-strength metal such as high-strength steel, high-strength aluminum, or high-tension titanium, and is preferably a substantially cylindrical structure. In addition, it has at least one or more nozzles for discharging combustion gas generated in the combustion chamber behind the axle, but at least one or more nozzles for the main combustion chamber and at least one or more nozzles for the auxiliary combustion chamber. It is desirable to have each nozzle. More desirably, the main combustion chamber nozzle and the sub-combustion chamber nozzle may be symmetrical with respect to the machine axis.

  The auxiliary motor case is preferably a substantially cylindrical structure with a front opening formed of a high-strength metal such as high-strength steel, high-strength aluminum, or high-strength titanium. After the insulator is installed on the surface of the main motor case, the main motor case and the center axis are inserted together to insert the main combustion chamber in the space between the main motor case and the sub motor case. Form. In the following description, the outer ring main combustion chamber is the main rocket combustion chamber, and the central auxiliary combustion chamber is the injection rocket combustion chamber, but the outer annular main combustion chamber is the injection rocket combustion chamber and the central auxiliary combustion chamber is the main. It can also be used as a rocket combustion chamber.

In the main rocket combustion chamber, for example, considering the concealment of the launch point and flight route, the inner hole surface with a high combustion speed and high specific thrust and the rear end surface as the combustion surface are sufficiently larger than the outer diameter of the secondary motor case Although a cylindrical double-base main rocket propellant having a large inner hole is disposed at the center, a composite main rocket propellant having similar characteristics can also be used unless confidentiality is particularly required.
In the injection rocket combustion chamber, for example, in order to achieve the high thrust and complete the combustion in a short time in consideration of the secrecy of the launch point, a full combustion type inner hole having a high combustion speed and a high specific thrust is provided. A rod-shaped double-base injection rocket propellant is arranged, but a composite injection rocket propellant having the same characteristics can also be used when confidentiality is not particularly required.

When a small-diameter propellant is placed in the combustion chamber without fixing such as bonding, the perforated plate is placed on the nozzle side of the motor case to prevent the propellant during combustion from scattering outside the nozzle. Inserted. The perforated plate is, for example, a metal disc having at least one or more holes, but can also be formed integrally with the motor case.
The front end plate is attached in front of the axle so as to seal both the main motor case and the sub motor case, and an ignition device is incorporated therein.

  The ignition device, for example, ignites the main igniting agent with an insensitive ignition squib on each of the main rocket and the injection rocket, and further ignites the propellant. By providing a delay function by using a delay agent or the like between ignition agents, the main rocket propellant can be ignited after a certain delay time after the ignition rocket propellant is ignited by one ignition signal.

It is possible to arbitrarily design the ignition delay time of the main rocket propellant by selecting the material and designing the shape, and combining it with the grain design of the injected rocket propellant, the combustion of the injected rocket propellant and the main It is possible to arbitrarily design the relative time with the rocket propellant combustion. For example, it is possible to ignite the main rocket propellant after a certain delay time after the injection rocket propellant combustion ends, and it is also possible to ignite the main rocket propellant immediately before the injection propellant combustion ends, for example. .
Needless to say, according to the present invention, a small and light two-stage thrust rocket motor used in a portable guided bullet system having a diameter of 150 mm or less, an axle length of 300 mm or less, and a mass of 2 kg or less, a diameter of 50 mm or less, an axle length of 200 mm or less, and a mass of 1 kg. The following smaller and lighter two-stage thrust rocket motor can also be obtained.

Examples of the present invention will be described below with reference to FIGS. 1 and 2, but the present invention is not limited to these examples.
FIG. 1 is a sectional view in the direction of the axis of a rocket motor according to the present invention, FIG. 2 is a sectional view in the direction perpendicular to the axis of the rocket motor, 1 is a main rocket motor, 2 is an injection rocket motor, 3 is a nozzle part, 4 is an ignition device.

  The main motor case 10 is a cylindrical structure made of high-strength steel having a diameter of 40 mm and a length of 130 mm formed integrally with the nozzle portion 3. The nozzle portion 3 includes a nozzle block 30, a main rocket nozzle 31 and a main rocket nozzle 31. An injection rocket nozzle 36 is formed. The injection rocket nozzle 36 is arranged in the center of the nozzle block 30, and the main rocket nozzle 31 is arranged symmetrically with the injection rocket nozzle 36 in between so as to be centered on the machine axis. The nozzle 31 and the nozzle 36 are respectively nozzles. It is sealed with a closure 32 and a nozzle closure 37.

The injection motor case 20 is a cylindrical structure made of high-tensile steel having a diameter of 20 mm and a length of 110 mm, with a porous plate 22 formed integrally at the rear end and an opening at the front end, and an insulator 23 on the inner surface and an insulator on the outer surface. Then, the injection rocket combustion chamber 25 is formed on the inner side of the main rocket combustion chamber 13 by being fitted to the inner central portion of the nozzle block 30, that is, the inlet side of the injection rocket nozzle 36.
A double-base main propellant 11 is inserted into the main rocket combustion chamber 13 and has a cylindrical shape with a round hole and has a restrictor 12 on the outer surface and the front end surface. In order to obtain a high thrust in a short time, seven rod-like full combustion type double-base injection propellants 21 having round holes are inserted into the injection rocket combustion chamber 25.

The ignition device 4 includes an insensitive ignition squib 46 for injection rockets and a main igniting agent 47 in the center of the front end panel 40, and an insensitive ignition squib 41 for main rockets and an annular principal point in the periphery. An explosive 42 is arranged, and a delay charge 43 is loaded between an ignition squib 41 for the main rocket and the main igniter 42. Further, the rear surface of the front end plate 40 is processed so as to be fitted to the open end of the injection motor case 20.
The ignition device 4 is fitted in each motor case and sealed in front of the main motor case 10 and the injection motor case 20 so that the main rocket motor 1 has the injection rocket motor 2 and has a diameter of 40 mm and a length. A two-chamber two-stage thrust rocket motor with a mass of 145 mm and a mass of 500 g can be obtained.

Subsequently, the operation of the rocket motor according to the present embodiment will be described with reference to FIG.
The ignition squib 41 for the main rocket and the ignition squib 46 for the injection rocket are ignited by one external ignition signal and ignition power (not shown). The ignition squib 46 for the injection rocket ignites the main igniter 47 for the injection rocket, and further ignites the injection propellant 21. At the same time, the ignition squib 41 for the main rocket ignites the delay charge 43.
The injection rocket 2 opens the nozzle closure 32 for the injection rocket by the pressure of the combustion gas generated by the combustion of the injection propellant 21, and generates a thrust by discharging the combustion gas from the injection rocket nozzle 36. Is fired from an injection mechanism (not shown).

After firing from an unillustrated injection mechanism, while the rocket continues inertial flight, the delay charge 43 is the main ignition charge for the main rocket when the combustion of the delay charge 43 is completed, that is, after a certain delay time has elapsed from the ignition signal. 42 is ignited, and the main propellant 11 is further ignited.
The main rocket 1 opens the nozzle closure 37 for the main rocket by the pressure of the combustion gas generated by the combustion of the main propellant 11 and discharges the combustion gas from the nozzle 31 for the main rocket, thereby generating a thrust. Will fly.
FIG. 3 is a time-thrust curve showing one of the performances of the rocket, and it can be seen that the flight thrust of the main rocket is obtained after a certain delay time has elapsed after obtaining the injection thrust of the injection rocket.

  The present invention can be suitably used as a small and light two-stage thrust rocket motor used in a portable guided bullet system.

1 is a sectional view in the axial direction of a two-chamber two-stage thrust rocket motor according to an embodiment of the present invention. 1 is a cross-sectional view perpendicular to the axis of a two-chamber two-stage thrust rocket motor body according to an embodiment of the present invention. It is a time-thrust curve which shows one of the performance of the two-chamber two-stage thrust rocket motor by one Example of this invention.

Explanation of symbols

1 .... Main rocket motor 2 .... Injection rocket motor 3 .... Nozzle part 4 .... Ignition device 10 .... Main Motor case 11 ... Main propellant 12 ... Restrictor 13 ... Main combustion chamber 20 ... Injection motor case 21 ... Injection propellant 22 .... Perforated plate 23, 24 ... Insulator 25 ...... Injection combustion chamber 30 ...... Nozzle block 31,36 ... Nozzle 32, 37 ... Nozzle closure 40 ··· Front panel 41, 46 ··· Ignition squib 42, 47 · · · Main ignition agent 43 ···

Claims (3)

  After launching from the injection mechanism with the thrust of the injection rocket, in the two-stage thrust rocket motor that obtains flight thrust by igniting the main rocket, insert the inner cylinder motor case with the front end open inside the main motor case, By sealing the outer main motor case and inner cylinder motor case with one front end plate, one combustion chamber is concentrically divided into two combustion chambers, one combustion chamber being an injection rocket combustion chamber, and the other combustion A two-chamber type two-stage thrust rocket motor characterized in that the chamber is a main rocket combustion chamber.   2. The main rocket ignition device is operated after a certain delay time is provided from the operation of the injection rocket ignition device by one ignition signal by providing the main rocket ignition mechanism with a delay function. Two-stage thrust rocket motor.   3. An injection rocket motor using at least one small-diameter propellant as an injection rocket propellant by using a perforated plate on the nozzle side of the injection rocket combustion chamber. The described two-stage thrust rocket motor.