JPH0742615A - Rotating nozzle holding structure - Google Patents

Abstract

PURPOSE:To operate a rotating nozzle smoothly with small driving torque, and prevent problems such as a slight change in nozzle steering angle, and combustion gas leaking from parts other than the rotating nozzle. CONSTITUTION:A nozzle receiver 7 is mounted on the end part of a rocket 1, a rotating nozzle 10 is fitted into the nozzle receiver 7, the rotating nozzle 10 and the nozzle receiver 7 are pivotally-connected. The nozzle receiver is formed with a high pressure cooling gas introduction port 6A and a gas flow passage 6B which comnunicates the high pressure cooling gas introduction port 6A of the nozzle receiver 7 to a clearance S between the rotating nozzle 10 and the nozzle receiver 7.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a rotary nozzle holding structure used for holding a rotary nozzle (so-called swivel nozzle) which rotates in one plane including a nozzle shaft on a tail portion of a rocket. is there.

[0002]

2. Description of the Related Art Conventionally, as a rotary nozzle holding structure described above, for example, as shown in FIG.
The tail end of the nozzle is provided with a nozzle receiver 105 including an inward annular projection 102a of the insulator 102 mounted inside the combustion chamber case 101, a substantially ring-shaped end plate 103, and a substantially ring-shaped holding metal fitting 104. Receiving 1
05 and the ball-shaped fitting portion 110a of the rotating nozzle 110 are fitted in a spherical pair, and the pressing fitting 104 of the nozzle receiver 105 and the skirt portion 110b of the rotating nozzle 110 are fitted together.
An actuator 106 is provided between the rotary nozzle 110 and the rotary nozzle 110, and the rotary nozzle 110 is arranged in one plane including the nozzle shaft 110c (see FIG.
(In the plane shown in FIG. 2) and the center P of the ball-shaped fitting portion 110a.
There is a holding structure that can be rotated around. In this case, between the holding metal member 104 of the nozzle receiver 105 and the ball-shaped fitting portion 110a of the rotating nozzle 110, and the end plate 103 of the nozzle receiver 105 and the pressing member. O between the metal fittings 104
By interposing the rings 107 and 108, the leakage of the combustion gas from other than the rotating nozzle 110 is prevented.

Regarding this rotary nozzle holding structure, for example, "Second Edition Aerospace Engineering Handbook" edited by the Japan Aerospace Society, September 30, 1992, published by Maruzen, No. 934.
There is some explanation on the page.

[0004]

In the conventional rotary nozzle holding structure described above, however, the internal pressure of the solid rocket 100 causes the rotary nozzle 110 to move toward the holding metal fitting 104 side and be pressed against it, thereby increasing the rotary friction. Therefore, the rotating nozzle 1 requires the actuator 106 having a large driving torque. As described above, the rotating nozzle 110 moves toward the holding metal fitting 104 side, and the rotating nozzle 1 is vibrated.
Since the actuator 106 that regulates the operation of 10 is affected, there is a problem in that there is a possibility that a slight variation may occur in the nozzle steering angle and control may be hindered.

When the propellant of the solid rocket 100 contains aluminum, aluminum oxide is added to the combustion gas, and aluminum oxide is used as the rotary nozzle 110 and the nozzle holder 1.
05, the end plate 103, the holding metal fitting 10
4 and the O-ring 107 are affected by heat, and the rotating nozzle 1
As described above, there is a risk that combustion gas may leak from other than 10, and the rotating nozzle 1
There is a problem that the aluminum oxide that has infiltrated between the nozzle 10 and the nozzle receiver 105 may be gradually deposited, and the operation of the rotary nozzle 110 may be hindered, and these problems can be solved. It was a conventional problem.

[0006]

SUMMARY OF THE INVENTION The present invention has been made by paying attention to the above-mentioned conventional problems. It is possible to smoothly operate a rotating nozzle with a small driving torque and to make a slight change in the nozzle steering angle. It is an object of the present invention to provide a rotating nozzle holding structure capable of preventing the occurrence of troubles and the occurrence of troubles such as leakage of combustion gas from other than the rotating nozzle.

[0007]

A rotary nozzle holding structure according to the present invention is provided with a nozzle receiver at the tail of a rocket, the rotary nozzle is fitted into the nozzle receiver, and the rotary nozzle and the nozzle receiver are connected to each other. The nozzle receiver is pivotally connected to each other, and the nozzle receiver is provided with a high-pressure gas introduction port, and a gas flow passage is provided to connect the high-pressure gas introduction port of the nozzle receiver and the gap between the rotary nozzle and the nozzle receiver. It is characterized in that it has a structure, and the structure of such a rotating nozzle holding structure is a means for solving the above-mentioned conventional problems.

In one embodiment, the high pressure cooling gas is used as the high pressure gas.

[0009]

Since the rotary nozzle holding structure according to the present invention has the above-mentioned structure, the rotary nozzle moves to the tail end side of the nozzle receiver due to the internal pressure of the rocket, and the rotary nozzle vibrates. Therefore, the rotating nozzle operates with a small driving torque without causing a slight change in the nozzle rudder angle.

Even when the propellant contains aluminum, the high-pressure gas is supplied from the high-pressure gas introduction port to the gap between the rotary nozzle and the nozzle receiver through the gas passage. As a result, the invasion of combustion gas and aluminum oxide into this gap is prevented, and the airtightness between the rotating nozzle and the nozzle receiver is broken, and aluminum oxide accumulates in the gap between the rotating nozzle and the nozzle receiver. Therefore, the rotating nozzle can operate smoothly without any trouble.

[0011]

DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described below with reference to the drawings.

1 to 3 show an embodiment of a rotary nozzle holding structure according to the present invention.

As shown in FIGS. 1 and 2, the solid rocket 1 has, at its tail, an inward annular projection 3a of an insulator 3 provided on the inner surface of the combustion chamber case 2 and an inward annular projection of the insulator 3. The nozzle receiving hole 4a of the end plate 4 which is in contact with the end plate 3a and the nozzle receiving hole 6a of the holding metal fitting 6 which holds the end plate 4 together with the insulator 3 and is fixed to the end plate 4 by the bolt 5 are provided. The nozzle receiver 7 holds the rotary nozzle 10.

The rotary nozzle 10 has a ball-shaped fitting portion 12 on the head side of a skirt portion 11, and a nozzle body 13 made of a heat-resistant material such as carbon fiber reinforced plastic (CFRP) is made of metal. It is configured to be covered with the shell 14.

The rotary nozzle 10 is adapted to be held by the nozzle receiver 7 by fitting the nozzle receiver 7 and the ball-shaped fitting portion 12 thereof. By providing the actuator 8 for pushing and pulling between the skirt portion 11 and the skirt portion 11, the actuator 8 is rotated in one plane including the nozzle shaft 10a (in the plane shown in FIG. 2) and around the center A of the ball-shaped fitting portion 12. It can be moved.

In this case, support shafts 15 and 15 projecting from the metal shell 14 in the upward direction and downward direction in FIG. 1 are provided on the rotating shaft passing through the center A of the rotating nozzle 10. In addition, bearings 9 and 9 are provided between the end plate 4 of the nozzle holder 7 and the holding metal fitting 6 and on the rotating shafts that also pass through the center A, and support shafts for the rotating nozzle 10 are provided. By fitting and connecting the bearings 15 and 15 to the bearings 9 and 9 on the side of the nozzle receiver 7, the rotating nozzle 10 can be moved and pressed toward the holding metal fitting 6 side of the nozzle receiver 7 by the internal pressure of the solid rocket 1. I try not to.

Further, the press fitting 6 of the nozzle receiver 7 is provided with a high pressure cooling gas introduction port (high pressure gas introduction port) 6A which is connected to a high pressure cooling gas supply source (not shown) through a pipe 20. A gas flow path 6B is provided that connects the high-pressure cooling gas introduction port 6A and the gap S between the metal shell 14 of the rotary nozzle 10 and the nozzle receiver 7. This gas flow path 6
B is a linear flow path 6a that directly communicates with the high-pressure cooling gas introduction port 6A, and a circumferential flow path 6b that communicates with this linear flow path 6a.
And a plurality of radial flow passages 6c arranged at equal intervals in the circumferential direction that communicate the annular flow passage 6b and the gap S, and the high pressure cooling gas from the high pressure cooling gas supply source is made of metal. By jetting out into the space S between the shell 14 and the nozzle receiver 7 over the entire circumference, aluminum oxide is prevented from entering this space S when the combustion gas and the propellant contain aluminum. I am trying.

Further, between the pressing metal fitting 6 of the nozzle receiver 7 and the ball-shaped fitting portion 12 of the rotary nozzle 10, and the nozzle receiver 7
By interposing O-rings 16 and 17 between the end plate 4 and the pressing plate 6 of the combustion gas rotating nozzle 10
Prevents leaks from other sources.

In this embodiment, the rotating nozzle 10 is
As shown in FIG. 3, four solid rockets 1 are provided at intervals of 90 ° in the circumferential direction around the axis of the solid rocket 1.
The upper rotary nozzle 10 (the rotary nozzle 10 shown in FIGS. 1 and 2) and the lower rotary nozzle 10 in FIG. 3 rotate in the horizontal direction in FIG. The thrusting direction control around the yaw axis is performed, and the turning nozzle 10 on the left side of FIG. 3 and the turning nozzle 10 on the right side of FIG. 3 turn in the vertical direction of FIG. 3 to perform the thrusting direction control around the yaw axis. There is. Also,
The thrust direction control about the roll axis is performed by simultaneously rotating the rotary nozzles 10 so as to be rotationally symmetrical with respect to the axis of the solid rocket 1.

Therefore, when the internal pressure rises due to the operation of the solid rocket 1, the rotary nozzle 10 has its supporting shaft 1
The bearings 9 and 9 fitted with the bearings 5 and 15 are
Since the moving nozzle 10 is prevented from moving toward the holding metal fitting 6, the rotating nozzle 10 is pressed against the holding metal fitting 6 and
No vibration occurs at 0, and as a result, the operation of the rotary nozzle 10 is performed without causing a slight change in the nozzle steering angle and without requiring a large driving torque.

During operation of the solid rocket 1,
The high-pressure cooling gas from the high-pressure cooling gas supply source, which has a pressure higher than that of the combustion gas, is supplied to the high-pressure cooling gas introduction port 6A and the gas flow path B, the straight flow path 6a, the circumferential flow path 6b, and the radial flow path 6
Since it is ejected over the entire circumference of the gap S between the metal outer shell 14 and the nozzle receiver 7 via c, when the combustion gas and the propellant contain aluminum, the infiltration of aluminum oxide occurs. Will be blocked,
Since the airtightness between the rotary nozzle 10 and the nozzle receiver 7 is not broken and aluminum oxide is not deposited in the gap S, the rotary nozzle 10 operates smoothly.

In this embodiment, the metal shell 14 of the rotary nozzle 10 forming the gap S and the O-ring 16 for preventing the leakage of the combustion gas from the gap S are exposed to the high-pressure cooling gas, so that the heat resistance of these components is improved. In addition to the requirement for heat resistance, it becomes possible to select an inexpensive material, and when the high-pressure cooling gas flows out along with the combustion gas, it flows along the surface of the nozzle body 13.
It is advantageous in preventing erosion.

The detailed structure of the rotary nozzle holding structure according to the present invention is not limited to the above-mentioned embodiment.

[0024]

As described above, since the rotary nozzle holding structure according to the present invention has the above-described structure, the rotary nozzle moves to the tail end side of the nozzle receiver due to the internal pressure of the rocket, or the rotary nozzle. In addition to the fact that vibration does not occur, the infiltration of combustion gas and aluminum oxide into the gap between the rotating nozzle and the nozzle receiver is prevented even when the propellant contains aluminum. Since the rotation nozzle can be prevented, the rotation nozzle can be operated smoothly with a small driving torque, and a slight variation in the nozzle rudder angle or a problem that combustion gas leaks from other than the rotation nozzle occurs. Can be prevented
As a result, a very excellent effect that the thrust direction control can be performed without any hindrance is brought about, and in a more preferable embodiment, by using the high pressure cooling gas as the high pressure gas, the rotation nozzle and the nozzle receiver are Since each facing surface is exposed to the high-pressure cooling gas, the heat resistance requirement is relaxed and inexpensive materials can be used for these parts. In addition, the high-pressure cooling gas flows along the inner wall of the rotating nozzle. Since it flows as a result of this, it also has an effect of acting advantageously in preventing the erosion of the inner wall material of the nozzle by the combustion gas.

[Brief description of drawings]

FIG. 1 is a partial vertical cross-sectional explanatory view of a solid rocket tail portion showing an embodiment of a rotating nozzle holding structure according to the present invention.

FIG. 2 is a partial horizontal cross-sectional explanatory view of the solid rocket tail portion shown in FIG.

3 is a partial perspective explanatory view of the solid rocket tail shown in FIG. 1. FIG.

FIG. 4 is a partial cross-sectional explanatory view of a solid rocket tail portion showing a conventional rotating nozzle holding structure.

[Explanation of symbols]

 1 Solid Rocket 6A High Pressure Cooling Gas Introduction Port (High Pressure Gas Introduction Port) 6B Gas Flow Path 7 Nozzle Receiver 10 Rotating Nozzle S Gap

Claims (2)

[Claims] 1. A rocket tail is provided with a nozzle receiver, a rotary nozzle is fitted into the nozzle receiver, and the rotary nozzle and the nozzle receiver are pivotally connected to each other, and the high pressure gas introduction port is provided in the nozzle receiver. The rotary nozzle holding structure is characterized in that a gas flow path that connects the high pressure gas introduction port of the nozzle receiver and the gap between the rotary nozzle and the nozzle receiver is provided. 2. The rotating nozzle holding structure according to claim 1, wherein a high-pressure cooling gas is used as the high-pressure gas.