JPH078832Y2 - Ducted rocket airport opening device - Google Patents

Description

[Detailed Description of the Invention] [Industrial field of application] The present invention relates to an air port opening device for a ducted rocket, and more specifically, when the rocket transitions to sustain propulsion, its air intake air port is blocked. The present invention relates to an air port opening device for removing a port cover.

[Prior Art] A ducted rocket is one aspect of a ram rocket.
It has multiple diffusers around the hull so that the outside air pushed into these diffusers can be taken in from the air ports.At the beginning, these air ports were blocked by a port cover and the rocket was boosted at most by boost propulsion. After accelerating to high speed, open the airport and proceed to sustain propulsion.

Conventionally, as such an air port opening device, a hinge type port cover that rotates the port cover in the opening direction by a pyrotechnic actuator or the like, and a port cover attached to the air port are provided with the pressure of the outside air pushed from the diffuser. A detachment type in which it is utilized to detach inward is mainly known (see Japanese Patent Laid-Open No. 61-126361). And the latter departure method is applicable to medium-sized or smaller ducted rockets due to its simple structure.

FIG. 3 shows a configuration of a ducted rocket (hereinafter referred to as a rocket) provided with the above-mentioned release-type opening device, which is the subject of the present invention. The rocket 1 has a ram combustor 3 on the rear side of a shell 2 forming the outer shell of the rocket motor and a gas generator 20 on the front side.

The ram combustor 3 includes a ram combustion chamber 5 formed by partitioning the inside of the shell 2 with a partition wall 4, a sustainer nozzle 6 fitted at the rear end of the combustion chamber, and, for example, four diffusers 7, and each diffuser. Is a center body 8 fixed to the shell 2, and four cowlings 9 fixed to the surroundings in an equiangular relationship,
Mainly composed of a curved guide wall 10 for partitioning the inside of the cowling, each of them is opened toward the front, and its rear end portion communicates with the ram combustion chamber 5 by an air port 11.

FIG. 4 is an enlarged view of the rear end portion. The shell 2 is divided into a rear shell 2a and a front shell 2b, which are joined together by a screw portion 2c. Airport 11 is the rear hull
Step 11a is opened near the front end of 2a and faces outward in the middle.
Provide. An aeroglit 12 is fitted into the air port from the outside and positioned by the step 11a, and the center body 8 and cowling 9 of the diffuser 7 are attached to the rear shell.
The outer edge of the aerogrid 12 is sandwiched between the mouth of the rear end of the 2a and the step 11a. Then, from the inside of the air port 11 through the seal ring 14, the port cover
15 is fitted to close the port 11 airtightly. Code 16
Is a heat-resistant insulator attached to the inner surface of the shell 2 (2a, 2b). The aero grid 12 is omitted and the airport 11
There is a case where only the port cover is fitted in, and in this case, for example, the stepped portion 11a is formed inward and the port cover is engaged with the stepped portion 11a to prevent the detachment from the outside.

Returning to FIG. 3, the gas generator 20 is an end-face combustion type sustainer propellant 22 loaded between the partition wall 4 and the partition wall 21 in front of the partition wall 4,
It has a sustainer igniter 23 mounted on the partition wall 4 and a gas nozzle 24 formed on this partition wall. When the sustainer igniter 23 is ignited to ignite the sustainer propellant, the propellant 22 self-combusts and a large amount of unburned fuel components. The fuel gas containing is generated, and this is ejected from the gas nozzle 24.

The ram combustion chamber 5 is initially loaded with a booster propellant 25, and the sustainer nozzle 6 is fitted with a booster nozzle 26, which is fastened to the gun shell rupture type nozzle clamp 27 on the ascending shell 2. Gas nozzle 24 has a booster igniter 28
Is detachably attached. In this state, the port cover 15 is irremovably restrained by the outer peripheral surface of the booster propellant 25.

In the above structure, when the booster propellant 25 is ignited and the rocket 1 is launched, the rocket 1 is accelerated to the transonic speed and reaches the high altitude, where the booster propellant 25 is burned down and the boost propulsion ends. At this time, the port cover 15 is released from the above constraint due to the burning of the propellant.
Due to the high pressure of the outside air pushed in, the air is separated from the air port 11 and blown inward, whereby the outside air is injected from the opened air port and is taken into the empty ram combustion chamber 5. Then, after the air port 11 is opened, the controller of the rocket 1 issues a break signal to the nozzle clamp 27 and an ignition signal to the sustainer igniter 23. Based on these signals, the booster nozzle 26 separates and the sustainer propellant is released. 22 is ignited to generate the fuel gas. This fuel gas blows off the booster igniter 28 and is ejected from the gas nozzle 24, and then is mixed with the outside air taken in and burned. At this time, the aerogrid 12 rectifies the injected outside air to stabilize the combustion flame. The high-temperature combustion gas generated in this way is injected from the sustainer nozzle 6 and the rocket 1
Will continue to promote sustainability.

[Problems to be solved by the invention]

By the way, in such a conventional apparatus, there is a problem in that some of the air ports are erroneously opened.

This is because in the release device of the port cover release system, the release force is obtained by the pressure difference between the external pressure of the outside air pushed from the diffuser and the internal pressure of the empty ram combustion chamber. If the start of the port cover departure is delayed or if it twists into the air port, the pressure in the ram combustion chamber is increased by the outside air injected from another air port and the above pressure difference decreases. This is because a part of the port cover remains in the air port while being fitted or twisted together.

Therefore, an object of the present invention is to prevent the port cover from remaining even if the separation due to the pressure difference fails.

[Means for solving problems]

Means of the present invention for solving this problem are an explosive-actuated pusher fixed to the outside of the port cover and facing the port cover, and an operation command transmission for issuing an operation command to the pusher at the time of transition to sustain propulsion. It is a means of providing means.

[Action]

According to this means, an operation command is issued from the operation command transmission means at the time of transition to sustain propulsion, and each pusher operates in unison with this command, so there is a port cover remaining at the air port at this time. Also push this from the outside and separate it.

〔Example〕

An embodiment of the present invention will be described with reference to FIG. Since the main part of the ducted rocket to which this embodiment is applied has the same structure as the rocket 1 of FIG. 3, FIG. 1 shows only the main part thereof. That is, the rear shell 2a and the front shell 2b of the shell 2 are joined together by the screw portion 2c, and the insulator 16 is attached to the inner surface thereof.
The air port 11 is opened at four positions near the front end of 2a, and the port cover 15 is airtightly fitted from the inside of the air port through a seal ring 14.

The diffuser 30 has a center body 31, a cowling 32 and a guide wall 33 in the same manner as that of the rocket 1, and is fixed to the rear rear shell 2a by mounting bolts 17 and 18.
In this state, the front end of the diffuser is opened forward and the rear end faces the air port 11. The cowling 32 is formed with a screw boss 34 facing the center of the air port 11 and having a female screw hole therethrough. Further, the aerogrid 35 is inserted into the air port 11 from the outside so that the outer edge portion is the stepped portion.
It is sandwiched between 11a and the diffuser 30, and this aero grid has the above-mentioned through hole 36 for rectifying the injected outside air,
Another through hole 37 is formed so as to face the screw boss 34. In the same manner as in the past, the port cover 15 is brought into close contact with the aerogrid 35, and the booster propellant 25 is held by the outer periphery of the booster propellant 25 so that it cannot be removed. Then, a powder-operated pusher 40 is fastened to the screw boss 34, and its push plunger 41 is inserted into the through hole 37 of the aerogrid 35 so as to face the port cover 15. Of course, as described above, when the aero grid 35 is omitted, the push plunger 41 directly faces the port cover.

The pusher 40 has a cylindrical housing as shown in FIG.
The push plunger is assembled by using 42 as a base.
41 is airtightly fitted to a cylinder 43 formed by expanding the inner surface of the housing near the inner end via an O-ring 44, and movement thereof is restricted by a shear pin 45. Further, a holder 47 is airtightly screwed to the outer end side of the housing 42 via an O-ring 46,
A threaded portion 48 for fastening to the threaded boss 34 is formed at the outer end of the holder, and a cartridge 49 is provided inside the threaded portion 48.
Is fitted. The cartridge 49 has a cylindrical casing 50 with an open inner end, in which an ignition ball 51, a point explosive 52, and a pusher charge 53 are loaded, and a leg wire 54 of the ignition ball 51 is pulled to an insulating sleeve 55 fitted in a holder 47. It is pulled out to the outside of the holder through this, and this pulled-out portion is sealed with a potting material 56.

Therefore, when an electric signal is sent to the ignition ball 51 through the leg 54, the ignition ball is ignited and the pusher charge 53 is detonated via the point explosive 52. As a result, the push plunger 41 is strongly pressed, so that the plunger shears the shear pin 45 and projects inward. The electric signal is issued as an operation command S from the operation command transmitting means 60.

The operation command transmitting means 60 is housed behind the guide wall 33 in one cowling 32 as shown in FIG. 1, for example, and a transition timing detector 61, a power supply battery 64 and a switching circuit 65 for the sustain propulsion are provided. It has a connector 66. The transition timing detector 61 in this example includes a fuse unit 62 and a timer 63. The fuse unit 62 is arranged in contact with the outer periphery of the booster propellant 25, and a minute electric current is supplied to the temperature fuse contained therein. Therefore, when the time to burn out the booster propellant 25 approaches, the temperature fuse receives the heat of combustion and melts, and after a short time, the propellant 25 burns out. The timer 63 issues a booster propellant burnout signal, that is, a transition timing signal to sustain propulsion, when the above-mentioned short time has elapsed from the time when the above current was cut off due to the melting of the temperature fuse, and the switching circuit.
65 receives this signal and closes the power supply circuit from the battery 64, thereby issuing the operation command S. This operation command is simultaneously transmitted to each pusher 40 via the connector 66.

The embodiment is configured as described above. Therefore, when the ducted rocket has completed boost propulsion and the booster propellant 25 is burned out, the port cover will be treated in the same manner as in the conventional case.
15 loses the restraint by the propellant 25 and disengages from the air port 11 inward, and an operation command S is issued from the operation command transmitting means 60 almost at the same time as the burning. Therefore, each pusher 40 operates immediately in response to this command S, and the push plungers 41 are simultaneously projected to the mark where the port cover 15 has separated. Therefore, if there is a port cover that can be removed, the inner end of the plunger 41 hits the center part of the outer surface of the port 41 and pushes it inward during the projecting process of the plunger 41. All the airports are opened by being forced.

After that, the breaking signal is sent to the nozzle clamp 27 shown in FIG. 3 and the ignition signal is sent to the sustainer igniter 23 to shift the ducted rocket to the sustain propulsion as in the conventional case. At this time, the melting point of the fuse unit 62 can be used as a starting point for calculating the transmission timing of the break signal or ignition signal.

〔effect〕

As described above, according to the present invention, even if the disengagement of the port cover due to the pressure difference ends abnormally, the explosive actuated pusher once again performs the forced disengagement action, thus avoiding a situation in which an air port opening error occurs. To be done.

[Brief description of drawings]

FIG. 1 is a cross-sectional view of an essential part of a rocket showing an embodiment of the present invention, FIG. 2 is a partially enlarged cross-sectional view of FIG. 1, and FIG. 3 is a cross-sectional view of a ducted rocket equipped with a conventional device. FIG. 4 is a partially enlarged sectional view of FIG. 11 …… Air port 15 …… Port cover 40 …… Pusher 60 …… Actuation command sending means 61 …… Sensor transition timing detector S …… Actuation command

 ─────────────────────────────────────────────────── ─── Continuation of the front page (56) Bibliography SHO 62-126544 (JP, U)

Claims (1)

[Scope of utility model registration request] Claim: What is claimed is: 1. A device for opening an air port by opening a port cover that has closed the air port when the ducted rocket shifts to sustain propulsion, and is fixed outside the port cover to face the port cover. An air port opening device for ducted rockets that has a gunpowder-operated pusher and operation command transmission means that issues an operation command to the pusher at the time of transition to sustain propulsion.