JPH04203256A - Double thrusted type rocket motor - Google Patents

Abstract

PURPOSE:To improve a reliability of ignition by a method wherein an insulator comprising a heat-resistant insulation rubber covering a tip inserted into a communication hole at a surface of a partition wall is adhered to prevent a dropping of the tip caused by vibration and shock, and an ignition lead line is used. CONSTITUTION:An insulator 8 comprised of a heat-resistant insulation rubber is adhered to a surface of the first stage combustion chamber 1 at a partition wall 4 of a rocket motor so as to cover tips 6 inserted into each of communication holes 3 and to prevent dropping of the tips 6. The rocket motor is provided with a safety device. The safety device for the first stage combustion chamber 1 forms the first stage arming rod 9 and a piston 10. The safety device for the second stage combustion chamber 2 is formed by the second stage arming rod 11 and a piston 12. An energy transmitting lead ignition line 14 using an explosive in place of the prior art electrical cable line is disposed from the first stage ignition initiator 13 to the first stage ignition device 15.

Description

[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to a two-stage thrust type I-coggle motor, and more specifically, it is capable of generating 42 thrusts at arbitrary time intervals. This relates to a certain two-stage thrust type rocket motor.

(Prior Art) In order to generate two stages of thrust at arbitrary time intervals, a conventional two-stage thrust type rocket I motor is shown in Fig. 4 and Figs. 5-a, b, and c. As shown in the figure, the combustion chamber 1 for the first stage
A partition wall 4 having a large number of communication holes 3 is provided between the combustion chamber 2 and the combustion chamber 2 for the second stage. In order to prevent the heat and pressure of the combustion gas from being transmitted to the second stage combustion chamber 2 during combustion of the propellant 5 in the first stage combustion chamber 1, the partition wall 4 is provided with a structure shown in Fig. 5-c. A chip 6 like this is attached to each communication hole 3 as shown in FIG. 5-a. This depth 6 or ejection rod (Ejec
tion Rocl) is a rod-shaped phenolic FRf'
Or made of aluminum alloy, each communication hole of the partition wall,
That is, it is inserted into the discharge hole ([1ject, 1-on l1ole). Each rod 6 is completely sealed by an O-ring 17 fitted around the rod.

When the propellant in the second stage combustion chamber is combusted, this thousand knob 6 separates from the corner wall toward the first stage combustion chamber due to the pressure of the combustion gas, and is finally discharged through the nozzle 7 to the outside of the nozzle. [8 IAA (America)
an In5 position of Aero-n
“AIA 8-89-24” published in 1989 by
26 Combustion Te5tof Two-3
"Pulse Rocket Motors"
].

[Problem to be solved by the invention]

However, in the above-mentioned conventional two-stage thrust type four-ket motor, each chip 6 has an O-ring 17 (made of lil rubber, silicone rubber, etc.) fitted into the chip that is in close contact with the communication hole 3. It is fixed to the partition wall 4 only by (Fig. 5-a). Therefore, when vibration, impact force, etc. are applied to the rocket motor, there is a risk that the chip may fall off the partition wall before the rocket I motor is activated.

Further, in the two-stage thrust type Rogent motor described above, in order to start the ignition device 15 in the first-stage combustion chamber, it is necessary to pass the electric cable wire 20 through the outer surface of the combustion chamber. That is, in the case of this structure, since it is necessary to install the electric cable line 20 downstream of the safety device 21 of the LJ motor, there is a possibility that stray currents, induced currents, etc. may occur in the cable line due to the influence of the outside environment. As a result, there is a problem in that there is a risk that the ignition device will be activated inadvertently, leading to immediate and unintentional ignition of the propellant.

[Failure to solve the problem]

With the two-stage thrust type rocket motor according to the present invention, even if an external force such as vibration or impact is applied to the two-stage thrust type rocket motor during storage or storage, the chip taken up in the partition wall part will not fall off. The structure is such that there is no

According to the present invention, an insulating rubber having heat resistance that can withstand the heat during combustion of the propellant for the first stage combustion chamber is attached as an insulator to the surface of the partition wall on the side of the first stage combustion chamber. By attaching insulation rubber so as to cover each chip inserted into the communication hole of the partition wall from the first stage combustion chamber side, it is possible to reliably prevent the chips from falling off.

In addition, the insulation rubber covering the Senbu is the first
The thickness is designed so that the propellant in the stage combustion chamber gradually burns out during combustion, and disappears at the end of combustion.

That is, the present invention provides a two-stage thrust type rocket motor having one nozzle, a first-stage combustion chamber, a second-stage combustion chamber, and a partition partitioning the two combustion chambers, The partition wall has an ignition device for the first-stage combustion chamber and a number of small holes that communicate the first-stage combustion chamber and the second-stage combustion chamber, and the small holes are closed. has a chip attached to
The invention further relates to a two-stage thrust type loget motor characterized in that an indulator is attached to the surface of the partition wall on the side of the first-stage combustion chamber so as to cover the chip.

FIG. 1 is a vertical cross-sectional view of the entire two-stage thrust type logger 1 to the motor of the present invention, and FIG. 2 is a vertical cross-sectional view of the partition wall.

As shown in FIG. 2, an insulation 8 made of heat-resistant insulation rubber is adhered to the surface of the partition wall 4 on the side of the first stage combustion chamber 1 of the rocket motor of the present invention, and is inserted into each communication hole 3. This is to cover the tip 6 and prevent the chip 6 from falling off.

Additionally, most rocket motors newly developed in recent years have safety devices attached to their ignition devices. In the two-stage thrust rocket motor that is the subject of the present invention, safety devices are required for both the ignition device for the first-stage combustion chamber and the ignition device for the second-stage combustion chamber.
A stage thrust type rocket motor is provided with a safety device 22 designated at 22 in FIG. Details of this safety device are shown in Figure 3. That is, the safety device for the first stage combustion chamber consists of the first stage arming rod 9 and the piston 10, and the safety device for the second stage combustion chamber consists of the second stage arming rod 11 and the piston 12. ′ζ is there. Furthermore, these are integrally attached as shown in Figures 3-, I and 3-1).

In the present invention, from the first stage ignition inshake 13 to the first stage ignition device 15, a gA bomb wire 14 for energy transmission using explosives is arranged in place of the conventional electric cable wire, and the first By adopting a structure that transmits ignition energy to the ignition charge of the stage ignition device, it is possible to create an ignition device that does not place electrical cable lines downstream of the safety device that are susceptible to the influence of external environments such as electromagnetic waves. .

[Operation] The two-stage thrust type Roken motor of the present invention having the above structure operates according to the following sequence.

First, the arming slot 9 of the safety device of the ignition device 15 for the first stage combustion chamber 1 is moved to release the safety device, and the rocket motor is prepared for operation.

Next, when an ignition signal is sent to the inishake 13 and ignited, the flame is transmitted to the detonating wire 14, igniting the ignition device 150 for the first stage combustion chamber, and then the igniter for the first stage combustion chamber 1. The propellant 5 ignites and generates the first thrust.

During the combustion of the propellant 5, the insulation rubber 8 covering the knob 6 of the bulkhead 4 decomposes due to heat, and the tip 6
The retained state is released.

In addition, at this time, the safety device of the ignition device for the second stage combustion chamber 2 is
As shown in FIG. 3-a, the second stage arming rod 11 moves due to the generated acceleration detected by the acceleration detection device 23, thereby entering the released state.

Next, after an arbitrary period of time has elapsed, an ignition signal is sent to the initiator 24 for the second stage combustion chamber 2, and the ignition charge 1G of the ignition device for the second stage combustion chamber 2 is ignited.

At this time, the propellant 25 in the second stage combustion chamber is ignited, and due to the pressure of the gas, it falls off from the tip No. 6 of the partition wall 4 toward the first stage combustion chamber 1 and is removed through the nozzle 7.

[Effects of the Invention] According to the present invention, by pasting an insulator made of heat-resistant insulation rubber that covers the chip inserted into the communication hole on the surface of the partition wall, it is possible to prevent the chip from falling off due to vibration or impact.

In addition, by using a detonating wire as the energy transmission means from the first-stage ignition initiator installed in the safety device to the first-stage ignition device, there is no need to place an electric cable line downstream of the safety device. This makes it possible to prevent stray currents, induced currents, etc. from occurring in cable lines due to the influence of the outside environment.

[Brief explanation of the drawing]

FIG. 1 is an overall vertical cross-sectional view of a two-stage thrust rocket motor according to the present invention, and FIG. 2 is an enlarged vertical cross-sectional view showing a partition wall thereof.
3-a and 3-b are respectively a front view and a side view of a safety device for a two-stage thrust rocket motor according to the present invention, FIG. 4 is an overall vertical sectional view of a conventional two-stage thrust type rocket motor, and FIG.
-a, b. Figure 0 is a vertical cross-sectional view of a partition wall of a conventional two-stage thrust motor [motor], a front view, and a vertical cross-sectional view of a chip, respectively. 1. 1st stage combustion chamber 2. 2nd stage combustion chamber 3. Partition wall 6. Chip 8. Insulation rubber 15. 1st stage ignition device

Claims (1)

[Scope of Claims] 1. A two-stage thrust rocket motor having one nozzle, a first-stage combustion chamber, a second-stage combustion chamber, and a partition partitioning the two combustion chambers. , the partition wall has an ignition device for the first-stage combustion chamber and a number of small holes that communicate the first-stage combustion chamber and the second-stage combustion chamber, and these small holes include the small holes. A two-stage thrust type rocket motor, characterized in that it has a tip attached to close the first stage combustion chamber, and further includes an insulator attached to the surface of a partition wall on the side of the first stage combustion chamber so as to cover the tip. 2. A two-stage thrust type rocket motor having one nozzle, a first-stage combustion chamber, a second-stage combustion chamber, and a partition separating the two combustion chambers, the first-stage combustion chamber A two-stage thrust type rocket motor, characterized in that the means for transmitting energy from the ignition initiator of the ignition device to the ignition device for the first stage combustion chamber is a detonating cord or the like.