JPH06193510A - Impulse jet injector - Google Patents

Abstract

PURPOSE:To burn a plurality of rocket motor of an impulse jet injector sequentially at time intervals by means of an electric circuit having a simple structure and a light weight. CONSTITUTION:In an impulse jet injector for burning sequentially a plurality of rocket motor 5 each of which burns for a short time at arbitrary time intervals, temperature relays 6 which are closed by their operation caused by rise accompanying the combustion of the rocket, motors are installed on respective rocket motors 5, and those temperature relays 6 are arranged in respective ignition circuits of the rocket motors burning subsequently.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an impulse jet injector used for motion control of a flying object.

[0002]

2. Description of the Related Art FIG. 6 shows an electric circuit of a conventional projectile impulse jet injector equipped with a plurality of conventional micro rocket motors that burn for a short period of time. In this conventional impulse jet injector, the corresponding control relays 9 are used to activate the respective micro rocket motors 5. In FIG. 6, 8 indicates an ignition device for the micro rocket motor 5, and 10 indicates a battery which is a common power source.

[0003]

In the above-mentioned conventional impulse jet injector, since several amperes of current have to be passed in order to start the ultra-small rocket motor 5, the control relay 9 has a large size to some extent. (So-called power relay) is required, and the circuit itself for controlling this relay also becomes large. Moreover, the number of relays required is the same as the number of rocket motors, increasing mass and volume.

The present invention is intended to provide an impulse jet injector which can solve the above problems.

[0005]

The impulse jet injector of the present invention is an impulse jet injector that sequentially burns a plurality of small rocket motors that burn for a short period of time at arbitrary time intervals. A temperature relay that operates and closes due to a temperature rise due to is attached, and the temperature relay is arranged in an ignition circuit of a rocket motor that burns next.

[0006]

In the present invention, a plurality of small rocket motors are used to generate jet jets and burn at a time interval from each other.

The temperature relay attached to each rocket motor operates and closes when the temperature of the rocket motor that has ignited increases due to combustion, and closes the rocket motor ignition circuit for the next combustion. Therefore, when one of the rocket motors burns and the temperature rises, the next rocket motor is ignited and starts burning.

[0008]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A first embodiment of the present invention will be described with reference to FIGS. FIG. 3 is an external view of a wingless vehicle equipped with the impulse jet injection amount according to the embodiment. A plurality of jet ports 2 are provided on the front surface of the flying body 1. By jetting a jet jet 3 from this jet port 2 in a direction orthogonal to the aircraft axis,
The attitude of the flying body 1 is controlled by generating a moment around the center of gravity G.

This system has a high responsiveness because it directly generates a moment, as compared with the system by steering which controls the attitude by generating aerodynamic force by taking a steering angle.

FIG. 1 is a sectional view of an impulse jet injector according to this embodiment mounted on an outer plate. The outer plate 4 of the flying body is provided with a plurality of injection holes 2 arranged side by side in the circumferential direction and the machine axis direction. Inside the respective injection ports 2, the outer plate 4 has a cylindrical microminiature rocket motor. 5 is attached. The diameter of the injection port 2 is φ5 mm, the diameter of the ultra-small rocket motor 5 is φ10 mm, the length is 20 mm, and the mass is 1
Assuming 0 g, the thrust of the jet jet 3 jetted from the jet port 2 by the microminiature rocket motor 5 is about 20.
A thrust force of 00N can be generated for about 0.2 ms.

A temperature relay 6 whose contacts are closed when the temperature rises is attached to the side surface of the micro rocket motor 5. The temperature relay 6 is
A shape memory alloy or the like is used to prevent the contact from opening even if the temperature drops once it is closed.

The electrical circuit of a plurality of micro rocket motors 5 is shown in FIG. The battery 10, which is a power source, is connected to the wiring 7 via the control relay 9. The ignition device 8 of the one A which is first ignited among the plurality of micro rocket motors 5 is adapted to be supplied with an electric current through the wiring 7 a connected to the wiring 7. The rocket motor B, which is ignited next to the rocket motor A, is connected to the ignition device 8 of the rocket motor B via the temperature relay 6 of the rocket motor A, and is also connected to the ignition device 8 of the rocket motor B. An electric current is supplied by the wiring 7b. Similarly, the ignition device 8 of the rocket motors C and D to be ignited next passes through the temperature relays 6 of the rocket motors B and C ignited immediately before from the wirings 7c and 7d connected to the wiring 7. Each is supplied with an electric current.

In the present embodiment constructed as described above, by closing the control relay 9 for a short time, a current is supplied to the ignition device 8 of the rocket motor A which is first ignited first among the micro rocket motors 5. When the rocket motor A is supplied, the rocket motor A is ignited to start combustion, and a jet jet 3 is jetted from the jet port 2 corresponding to the rocket motor as shown in FIG.

At this time, after a lapse of some time, the temperature of the temperature relay 6 rises due to the heat generation of the rocket motor A that is ignited, whereby the temperature relay 6 is actuated and its contacts are closed. Therefore, when the control relay 9 is closed again, the ignition device 8 of the rocket motor B to be ignited next time
To the rocket motor B to generate a jet jet. Similarly, the rocket motor C,
D is sequentially ignited at time intervals to generate jet jets.

FIG. 4 is a time chart showing an example of the operation of this embodiment. By closing the control relay 9 for about 0.5 ms, the ignition device 8 of the rocket motor A operates. By the operation of the ignition device 8, the thrust of the rocket motor A is generated for about 0.2 ms.

When the rocket motor A operates, the temperature of the outer cylinder rises, and after a certain time delay, the temperature relay 6 operates and the contacts are closed.

When the control relay 9 is closed again after the temperature relay 6 is activated, the next rocket motor B is activated. Similarly, the rocket motors C and D are sequentially operated thereafter.

FIG. 5 shows a second embodiment of the present invention. In this embodiment, the temperature relay 6 of each micro rocket motor 5 is used.
Is mounted between the rocket motor 5 and the outer plate 5 so that the temperature relay 6 is directly exposed to the jet jet flow 3.

In this embodiment, a micro rocket motor 5 is used.
Although the mounting of the temperature relay 6 becomes complicated, the time delay of the temperature relay 6 can be reduced by directly exposing the temperature relay 6 to the jet jet flow 3.

As described above, in the first and second embodiments, the temperature relay 6 attached to the micro rocket motor is heated and closed as the rocket motor burns. By sending an electric current to the ignition device 8 of the rocket motor to be ignited,
The jet jets 3 can be generated by sequentially operating a plurality of rocket motors at time intervals.

Further, since the control relay is not provided in the electric circuit of each rocket motor but one is provided in the common wiring 7, the electric circuit can be downsized, and its mass and volume can be reduced. it can.

[0022]

In the impulse jet injector according to the present invention, each rocket motor is equipped with a temperature relay that operates and closes due to a temperature rise associated with combustion of the rocket motor. By arranging them in the circuit, it is possible to eject jet jets one after another with a simple control circuit.

Further, since it is not necessary to provide a control relay in the electric circuit of each rocket motor, the circuit can be downsized, and its mass and volume can be reduced.

[Brief description of drawings]

FIG. 1 is a cross-sectional view of a first embodiment of the present invention.

FIG. 2 is an electric circuit diagram of the embodiment.

FIG. 3 is an external view of a flying vehicle equipped with the impulse jet injector according to the embodiment.

FIG. 4 is a time chart showing an example of the operation of the same embodiment.

FIG. 5 is a sectional view of the second embodiment of the present invention.

FIG. 6 is an electric circuit diagram of a conventional impulse jet injector.

[Explanation of symbols]

 1 Flying body 2 Jet port 3 Jet jet 4 Outer plate 5 Micro rocket motor 6 Temperature relay 7, 7a, 7b, 7c, 7d Wiring 8 Ignition device 9 Control relay 10 Battery

Claims (1)

[Claims] 1. In an impulse jet injector that sequentially burns a plurality of small rocket motors that burn for a short period of time at arbitrary time intervals, a temperature relay that operates and closes due to the temperature rise associated with each rocket motor. And the temperature relay is arranged in the ignition circuit of a rocket motor for subsequent combustion.