JPH10245000A - Emergency separation device of joined part - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide the emergency separation device of a joined part for separating a combustion finished rocket motor from a flying object. SOLUTION: This separation device is composed of an order receiving device 11 for outputting an ignition signal by a separation signal from an antenna 10 by which the separation signal from the earth is received on a flying object and an ignition device 13 which ignites a priming material 13 for emergency operation by an ignition signal from the order receiving device, cuts a combination band unrelatedly to the flying object sequence and separates a front body 4 from a rear body 2 provided on a rocket motor. Thereby, the loading of a great deal of explosive for self explosure is not required and also the front body 4 can be collected surely or the flying object can be returned to a normal sequence from an abnormal state by the non-operation of a separator.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

TECHNICAL FIELD The present invention relates to a space rocket,
A coupling device provided at the fuselage separation section of defense guided missiles or payload projectile rockets (hereinafter referred to as flying vehicles) is provided so that the flying vehicle can follow an abnormal flight path or separate the coupling device. The present invention relates to an emergency separation device for a disconnection unit for urgently cutting and separating when an operation signal of the connection / separation device is not output.

[0002]

2. Description of the Related Art In a projectile such as a defense guided missile, after being fired, in order to reduce the resistance and extend the cruising distance, and to reduce the weight and improve the kinetic performance such as turning performance, The burned-off rocket motor is separated. As shown in FIG. 4, the joint separating device for separating the rocket motor incorporates a rocket motor 03 and generates a propulsion force of the flying vehicle 01 by using a rear fuselage 0.
2 is connected to the rear end of the front fuselage 04 equipped with explosives and other equipment necessary for achieving the mission of the flying object 01, such as guidance devices, and the flying of the flying object 01 It consists of a normal operating pyrotechnic 06 attached to the bonding band 05, which is ignited at a time determined by the shoring sequence, cuts off the bonding band 05 and separates the rear fuselage 02 and the front fuselage 04. . In the figure, 07
Is the rocket motor 0 for ignition of the rocket motor 03.
3 is an igniter provided at the front end of the shaft center.

[0003] However, as described above, such a joint separation device operates according to a predetermined flying sequence, and the rear fuselage 02 and the front fuselage 04 are operated.
As shown in FIG. 5, when the flying object 01 launched from the ground launcher 08 or the like has an abnormal flight, or when the operation of the flying sequence malfunctions, as shown in FIG. Immediately, pyrotechnic for normal operation 0
6 cannot be ignited and separated.

[0004] For this reason, when an abnormality occurs in the flying vehicle 01 or the like, the self-destructive explosive contained in the front fuselage 04 or the rear fuselage 02 is operated to destroy the entire aircraft in the air. Stop flying, damage caused by abnormal flight, or damage caused by flying in a different form from the planned flight course,
In particular, damage caused by falling to the ground is prevented.

[0005] However, the above-mentioned self-destruction method has the following problems. (1) In order to achieve the original mission of the flying vehicle 01 in order to destroy the aircraft, an unnecessary large amount of self-destructive explosives must be mounted inside the aircraft with little space. In addition, there are restrictions on the installation of equipment that must be installed in order to accomplish the mission, and there are significant restrictions on the space and transportation of the launch site and ammunition for handling explosives for self-destruction, which can cause explosions. (2) In addition, after some abnormality has occurred in the flying object 01 and the flying object 01 is self-destructed, no physical data for investigating the cause remains. For this reason, it is difficult to pursue the cause of the abnormal flight that caused the self-destruction.
For rockets to be launched for scientific research, etc., or flying objects such as guided missiles to obtain flight data etc. for grasping aircraft performance, data obtained so far will be lost Not only for these technical surveys or to obtain flight data,
There was a major drawback in that expensive equipment mounted on the aircraft was lost.

[0006] Such abnormalities or malfunctions that occur after the launch are caused by small parts and even though the abnormalities can be eliminated by a simple operation, there is no way to back up, especially from the ground. By activating a normal operation pyrotechnic 06 that did not operate normally at a signal,
The flying object could not be returned to the predetermined flying sequence.

[0007]

SUMMARY OF THE INVENTION The present invention is directed to a method of separating a flight sequence specified in the flight sequence when a malfunction of the above-described conventional joint separation device, that is, when an abnormality or malfunction occurs in the guide bullet 01 or the like. Regardless of time, at any time,
The joints are separated by the signal from the ground, the aircraft is recovered, the data acquired so far, and the equipment for data acquisition can be recovered, and physical data for investigating the cause of abnormal flight etc. The issue is to provide a joint emergency separation device that can be recovered and returned to the flight of a predetermined flight sequence, and that can eliminate the problems associated with mounting a large amount of explosives for self-destruction. I do.

[0008]

For this reason, an emergency separation device for a joint according to the present invention has the following means. Regardless of the flight sequence predetermined for the flying object,
In order to cut and separate the joint band that joins the rear fuselage equipped with the rocket motor and the front fuselage equipped with measuring equipment, in addition to the conventional joint separation equipment, (1) abnormal flight An antenna has been provided so that a separated signal transmitted from the ground can be received by a flying object at a time that cannot be predicted in advance, such as time. In order to guide the flying object, the antenna may be configured to receive a signal transmitted from the ground, and may also be used as an antenna normally mounted on the flying object. (2) A command receiving device for inputting a separated signal from the ground received by the antenna and transmitting an ignition signal based on the separated signal is provided. (3) Receiving an ignition signal from the command receiving device, attached to a connecting band connecting the rear body and the front body, and cutting the connecting band connecting the rear body and the front body by its explosive force. An ignition device is provided to ignite the emergency operating pyrotechnic. The emergency operation pyrotechnic that ignites with the igniter has a normal operation attached to the connecting band to separate the rear fuselage from the front fuselage at the predetermined flight time. A pyrotechnic product may also be used.

According to the above-mentioned means (1) to (3), the connecting part emergency separation device of the present invention can be used when the guidance device for flying breaks down and the flying object causes abnormal flying. If the pyrotechnic for normal operation does not operate and the predetermined rocket motor separation is not performed at the predetermined time predetermined in the flight sequence, the operator monitoring from the ground or an automatic measuring device, By transmitting the separation signal to the flying vehicle, the joint separation device provided to separate the rear fuselage equipped with the rocket motor is forcibly operated, and the rocket motor is moved to the front fuselage. Can be separated from

As a result, the front fuselage loses thrust and the flight stops, and thereafter, the front fuselage can be decelerated with a parachute or the like to land on water, thereby preventing damage caused by falling and preventing the occurrence of damage. , Physical data for investigating the cause of the abnormal flight can be collected, the cause can be easily identified, or data acquired so far, or expensive equipment mounted on the aircraft to acquire the data Can be recovered.

If the pyrotechnic for normal operation is simply a trouble due to malfunction due to disconnection or lack of explosive, the flying body is separated into a rear body and a front body by a signal from the ground, The flight can be continued by returning to a predetermined normal sequence.

In addition, the emergency actuating pyrotechnic need only have an amount of explosive charge that can cut the bonding band connecting the rear fuselage and the front fuselage, instead of destroying the entire fuselage.
In addition, by making the pyrotechnic for emergency operation also usable as the pyrotechnic for normal operation, a particularly large mounting space can be eliminated, and the equipment required for achieving the original mission of the flying object can be installed. Ample space can be ensured, and the launch site and ammunition space or transportation constraints associated with handling large volumes of self-destructive explosives can be eliminated.

[0013]

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a perspective view showing an embodiment of an emergency separation device for a joint according to the present invention. FIG. 1 is a view showing a first embodiment of a joint emergency separation device of the present invention,
FIG. 1A is an overall view, and FIG.
FIG. 2 is a block diagram of the emergency-separation device for the joint shown in FIG. 1 (a).

As shown in the drawing, the joint emergency separation device according to the present embodiment has a built-in rocket motor 3 and a tip of a rear fuselage 2 for generating a propulsive force of the flying object 1, For separating the rear fuselage 2 and the front fuselage 4 by cutting the coupling band 5 that couples the rear end of the front fuselage 4 on which guidance equipment, measuring equipment, explosives, etc. necessary for accomplishing the mission are mounted. This is provided in addition to the normal operation pyrotechnic 6, which separates the rear fuselage and the front fuselage 4 in a normal flying sequence.

When the igniter 7 provided at the front end of the shaft center of the rocket motor 3 is ignited, the rocket motor 3 burns and, as shown in FIG.
The flying object 1 is fired. After launch, flying object 1
Flying on the normal flight path N and operating normally, the control device mounted on the front fuselage 4 will operate normally for a predetermined time in the flight sequence previously input. The pyrotechnic 6 is activated to cut the bonding band 5.

As a result, the rear fuselage 2 containing the rocket motor 3 is cut off from the front fuselage 4 and falls into a predetermined, safe water area that does not cause damage by falling. Move to the sequence after the flight sequence, achieve the specified mission, and finally, parachute 1
6 allows safe recovery to the ground.

On the other hand, after the launch, the flying object 1 does not become normal, and if the pyrotechnic 6 for normal operation does not operate due to a trouble of the electronic device or the pyrotechnic 6 for normal operation, or it is expected that When a flight is started on the unusual flight path A, the rear fuselage 2 and the front fuselage 4 are separated by a signal from the ground. For this reason, the front fuselage 4 is provided with an antenna 10 for receiving a separated signal transmitted from the transmitting equipment 9 on the ground so as to operate independently of the flight sequence,
The ground separated signal received by the antenna 10 is input,
On the basis of this separation signal, a command receiving device 11 for transmitting an ignition signal, an ignition signal from the command receiving device 11, and an attachment for a joint band 5 connecting the rear body 2 and the front body 4 for emergency operation An ignition device 13 for igniting the pyrotechnic 12 is provided.

Note that the antenna 10 may also serve as an antenna normally provided on the flying object 1, and the emergency operating pyrotechnic 12 is predetermined on the flying object 1. In order to separate the rear fuselage 2 and the front fuselage 4 in the flying sequence, the above-mentioned normal operation pyrotechnic 6 attached to the connecting band 5 may be combined.

As described above, since the flying body 1 is provided with the joint emergency separation device for separating the front fuselage 4 and the rear fuselage 2 in an emergency, after the flying body 1 is fired, If an abnormality was found in the guidance control or flight route due to a trouble of some component, or the pyrotechnic 6 for normal operation did not operate, and the separation was not performed at the time set in the flight sequence. In this case, as shown in FIG. 3, the separated signal transmitted from the transmitting device 9 on the ground is transmitted to the antenna 10 mounted on the flying object 1, and operates by receiving power supply from the battery 10 from the antenna 10. It is sent to the command receiving device 11. The command receiving device 12 sends an ignition signal command to the ignition device 13 based on the reception of the separation signal.

The ignition device 13 which has received the ignition signal
Is supplied with power from the battery 15 and has a pyrotechnic 1 for emergency operation.
An ignition current is applied to the fuselage 2 to ignite the pyrotechnic 12 for emergency operation, and the explosive force cuts the bonding band 5 to separate the front body 2 from the rear body 4.

After the front fuselage 2 is separated, the flying body 1 is fired, and guidance control is performed by some trouble.
Or, if an abnormality is confirmed in the flight path, the payload including the payload mounted on the front fuselage 2 or the measurement device including the measurement data is safely recovered to the ground with the parachute 16, and a pyrotechnic for normal operation is used. If the product 6 does not operate and the separation is not performed, the normal sequence of the separated front body 4 determined in the flight sequence is returned to the normal sequence of the forebody 4, and the aircraft is made to fly and collected on the ground. Do.

[0022]

As described above, according to the joint urgent separation device of the present invention, the constitution shown in the claims makes it possible to (1) reduce the amount of explosive as compared with the conventional self-destruction method. And the number of devices required to accomplish the mission is not restricted, and restrictions on handling and transportation are reduced. (2) The aircraft that flew abnormally can be recovered, and physical data for investigating the cause remains. In addition, the acquired data can be reliably collected, and the loss of equipment required for data acquisition can be prevented. (3) The normal operation pyrotechnic that should operate normally is disconnected.
When the rocket motor cannot be separated due to failure to operate due to explosive failure, the front fuselage can be returned to the almost normal sequence defined in the flight sequence.

[Brief description of the drawings]

FIG. 1 is a view showing a first embodiment of a joint emergency separation device according to the present invention, wherein FIG. 1 (a) is an overall view and FIG. 1 (b) is FIG.
Partial sectional view of part A shown in FIG.

FIG. 2 is a block diagram of a joint emergency separation device shown in FIG.

FIG. 3 is a diagram showing an operation status of the embodiment shown in FIG. 1,

FIG. 4 is a sectional view showing a conventional joint separation device,

FIG. 5 is a diagram showing an operation state of a conventional joint separation device at the time of malfunction.

[Explanation of symbols]

 1,01 Flying vehicle 2,02 Rear fuselage 3,03 Rocket motor 4,04 Front fuselage 5,05 Coupling band 6,06 Pyrotechnic for normal operation 7,07 Igniter 8,08 Launcher 9 Transmission equipment 10 Antenna 11 Command receiving device 12 Emergency pyrotechnic 13 Ignition device 14, 15 Battery 16 Parachute

Claims (1)

[Claims] 1. A connecting band for connecting a rear fuselage equipped with a rocket motor for generating propulsion and a front fuselage equipped with equipment for accomplishing a mission, at a time determined by a flight sequence, An antenna for receiving a separation signal transmitted from the ground, comprising: an antenna for receiving a separation signal transmitted from the ground; and A command receiving device that receives a separation signal from the device and transmits an ignition signal, and receives an ignition signal from the command receiving device, ignites an emergency operation pyrotechnic attached to the coupling band, and performs a flying sequence. An emergency disconnecting device for a joint portion, comprising: an ignition device that cuts the joint band independently of the rear body and separates the rear body and the front body.