JPS602512B2 - rocket ignition system - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to an ignition device for a rocket that has an ignition charge ignited by a heating element (igniter) that generates heat by external energy in the body, and is flown by a propellant burned by the ignition charge.

An actual perspective view of an example of a conventional rocket ignition system of this kind is shown in Fig. 1, and its schematic circuit diagram is shown in Fig. 2. In the figure, 1 is a rocket, 2 is a propellant, and 3 is a dot. Gunpowder, 4 is igniter,
5 is a wire cutter, 6 is a launch controller, 7 is a DC power supply, 8
9 is a launch switch, 9 is a crab pad, 21 is a launch pad, and 22 is a wire.

Note that the same reference numerals indicate corresponding parts throughout the drawings. In FIGS. 1 and 2, a storage battery 9 is used as the DC power source 7 because the rocket ignition device is generally moved and quietness is required in special applications. The electric energy of the DC power supply 7 consisting of the storage battery 9 is supplied to the igniter 4 inside the rocket 1 via the launch switch 8 of the launch controller 6 and the wire cutter 5 of the launch pad 21 . To launch this rocket 1, when the launch switch 8 is set to 〃〃〭〭, the igniter 4 generates heat due to the electric energy of the storage battery 9, the ignition charge 3 is ignited by the heat energy, and the propellant 2 burns and Rocket 1 takes flight. Note that the electric power required to generate heat from the igniter 4 is usually about several watts, and the wire 22 for transmitting electric energy is cut by the wire cutter 5 when the rocket 1 is launched. However, with this conventional device, it is difficult to cut the wire 22, and the wire 22 may be cut and the wire 22 may be cut, especially when firing 20 to 3 hammers one after another.
It was troublesome to dispose of the wire remaining on the 1 side. More specifically, since the DC power source 7 is used and the negative electrode side is generally grounded, there is a problem that the DC power source 7 will be short-circuited if the cut wire is grounded. Another 20-3
When a firing eagle is required to be fired according to a certain sequence, broken wires that are grounded or short circuits between wires may generate electrical noise that may cause the sequence circuit to malfunction. be. Also, as a countermeasure,
It is also possible to remove the cause of the malfunction by installing a malfunction prevention device on the electric circuit side or by improving the wire cutter 5, but in reality, the former makes the electric circuit complicated and is not a complete preventive measure. However, the latter is difficult due to the nature of utilizing the pulling force of the wire 22 at the point where the rocket 1 launches. Furthermore, in this way, each rocket has 22 wires.
There was a drawback in that it was very inconvenient to insert a lotus into a launch pad that had a lotus bag of 20 to 3 digits. Therefore, as a solution to these problems, a device that sends an ignition signal to the rocket 1 wirelessly is being considered.

An actual perspective view of a conventional wireless rocket ignition system of this type is shown in Fig. 3, and its electrical circuit diagram is illustrated in Fig. 4, where 6A is a launch controller, 10G is an ignition mechanism (
11 is a pulse generator, 12 is a pulse transformer, 13 is a thyristor, and 14 is a battery. 3rd, 4th
In the figure, a battery is built into the body of the rocket as an energy source for igniting an igniter 4, and an ignition mechanism (ignition control circuit) 10 is provided that supplies energy to the igniter 4 using, for example, a thyristor 13 as a switch. −
On the other hand, the thyristor 13 is fired by an ignition signal that instructs ignition, but this signal is magnetically coupled to the launch controller 6A outside the rocket 1 by the pulse transformer 12, and is connected to the pulse transformer by the pulse generator 11. 12 as a pulse signal. Therefore, if the input of the pulse generator 11 is controlled by the launch switch 8, the rocket can be launched. However, while this device eliminates causes of malfunctions such as wire grounding, it is expensive because it requires an ignition energy source inside the rocket 1, and it is difficult to store energy stably for a long time. In addition, it is structurally difficult to incorporate the ignition mechanism (ignition control circuit) for controlling ignition into the rocket body, and furthermore, since it is magnetically coupled to the outside by a pulse transformer, it is difficult to incorporate the ignition mechanism (ignition control circuit) into the rocket's launch pad. This method had drawbacks such as inconvenience due to restrictions on structural interrelationships.

An object of the present invention is to eliminate the above-mentioned drawbacks of the prior art, and to create a simple and low-cost wireless rocket that can be easily and accurately ignited from the outside without providing an ignition mechanism including an energy source inside the rocket. Located in providing ignition system.

The present invention provides a heating element (
In an ignition system for a rocket that has an ignition charge that is ignited by an igniter (igniter) and that flies with a propellant combusted by the ignition charge, external energy is converted from electric energy to magnetic energy by electromagnetic induction and applied to a heating element, The device is characterized in that the ignition charge is ignited by the heat generated by the eddy current flowing through the heating element, and according to the present invention, the rocket and the launch controller are connected by magnetic energy, so that the rocket is not connected to the launch controller. This not only eliminates problems caused by wire ground faults, but also eliminates the need to incorporate an ignition mechanism that includes a power source into the rocket, as magnetic energy is directly converted into thermal energy and ignited within the rocket. In addition to this, magnetic energy can directly transmit large amounts of energy through electromagnetic induction, and the use of high frequencies allows for a large degree of freedom in the mechanical interrelationships of the transmission parts.

Embodiments of the present invention will be described below with reference to the drawings.

FIG. 5 is an actual perspective view showing an embodiment of a rocket ignition system according to the present invention, and FIG. 6 is an electrical circuit diagram thereof. In the figure, 6C is a launch controller, 16 is a high frequency generator, and 17 is a 18 is a solenoid, 18 is a magnetic flux 0, 19 is a heating element, and 2 rivers are a magnetic flux generator. In FIGS. 5 and 6, the ignition charge 3 is the heating element 19
covered by. The heating element 19 is made of an electrical conductor, and is made of a metal material such as aluminum that easily generates heat due to an eddy current flowing in response to high frequency magnetic energy. Launch pad 21 (first
A magnetic flux generator 20 is provided on top of the figure. This magnetic flux generator consists of two solenoids 17. The launch controller 6C has a built-in high-frequency generator 16 that converts the direct current of the direct-current power supply 7 into high-frequency alternating current. With this configuration, during the launch of the rocket 1, the DC power from the battery 9 of the DC power source 7 is supplied to the high frequency generator 16 via the launch switch 8 of the launch controller 6C.
The magnetic flux is converted into high frequency alternating current by the solenoid 17 of the magnetic flux generator 20, and converted into high frequency alternating magnetic flux 18 by the solenoid 17 of the magnetic flux generator 20.

This alternating magnetic flux enters the rocket 1 and generates an eddy current in the heating element 19. As a result of the heating element 19 being heated by this eddy current, the ignition charge 3 is ignited, thereby causing the propellant 2
burns, and the rocket is launched. As mentioned above, the energy required for ignition is usually about several watts, so the heating element 19 and the magnetic flux generator 20 do not need to be very large devices, and therefore the DC power source 7 can be of a conventional capacity. . In this way, without making major changes to conventional rockets and DC power sources, it is not only possible to eliminate the causes of malfunctions caused by short circuits in wires, which were the drawbacks of conventional rockets, but also to eliminate Since there is no need to incorporate an ignition mechanism including a power source inside the rocket, the price can be lowered and reliability can be improved.As there is no need for an ignition mechanism inside the rocket, it is easier to store the rocket, and the rocket can be easily stored. It has the advantage that the equipment can be easily operated, maintained, and inspected outside the system.

In addition, FIG. 7 is an electrical circuit diagram showing another embodiment of the rocket ignition system according to the present invention, in which 6B is a launch controller, 15 is a converter, and 23 is a transformer.

In FIG. 7, the energetic coupling between the rocket and launch controller 6B is provided by a transformer 23. In this case, it is not necessary to incorporate the ignition mechanism 10 (FIG. 3) into the rocket 1, but the mechanical interrelationship of the connecting parts is severely restricted. As explained above, according to the wireless rocket ignition device of the present invention.

A simple, reliable, and economical device that can easily supply energy from the outside of the barrel and reliably ignite it can be obtained, and can be particularly effectively used in multiple rocket launchers.

[Brief explanation of drawings]

FIG. 1 and FIG. 2 are conventional. FIGS. 3 and 4 are perspective views and electrical circuit diagrams showing another example of the ignition device of the igniter; FIGS. 5 and 6 are diagrams illustrating the present invention Fig. 7 is an electrical circuit diagram showing another embodiment of the rocket ignition system according to the present invention. Explanation of symbols, 1...Rocket, 2...Propellant, 3...Ignition powder, 6C...
...Launching controller, 7...DC power supply, 8...
Emission switch, 16... High frequency generator, 19...
- Heating element, 20...Magnetic flux generator. Hair Figure 2 Figure 3 Figure 4 Figure 0 Figure 7

Claims (1)

[Claims] 1. Includes a heating element that generates heat by receiving energy from the outside, an ignition powder that ignites due to the heat generated by the heating element, and a propellant that burns and generates thrust by ignition of the ignition powder, and the thrust of the propellant 1. An ignition device for a rocket flying in flight, wherein the heating element receives energy from the outside through electromagnetic induction and generates heat by an eddy current flowing through itself.