CN114992331A - Dynamic sealing structure for thin wall of swinging nozzle of solid rocket engine - Google Patents

Abstract

The invention discloses a dynamic sealing structure for a thin-walled swing nozzle of a solid rocket motor, comprising a movable sphere, a sealing sphere seat, a V-shaped metal sealing ring and a sealing sphere cover, wherein the movable sphere is arranged on the sealing sphere seat, The sealing ball seat and the sealing ball cover are connected by screws 5, and a V-shaped metal sealing ring is arranged in the rectangular area formed by the sealing ball seat, the sealing ball cover and the movable ball. The invention has the characteristics of high reliability, good sealing effect, simple results and the like; wherein the V-shaped metal sealing ring can adapt to higher temperatures, and the surface of the sealing ring is sprayed with non-metallic materials, which has better self-lubrication and can bring about smaller high friction coefficient, and ensure its good sealing effect during multiple swings.

Description

Dynamic sealing structure for thin-walled swing nozzle of solid rocket motor

technical field

The invention belongs to the technical field of adjustable nozzles of aerospace solid rocket motors, and in particular relates to a dynamic sealing structure for thin-walled swing nozzles of solid rocket motors.

Background technique

As the power device of the aircraft, the solid rocket motor must carry out thrust control according to the different requirements of the aircraft. The thrust control includes the control of the thrust direction, the thrust magnitude and the thrust termination. The solid rocket motor is mainly implemented through the nozzle of the solid rocket motor, which is technically difficult. At present, flexible nozzles and bearing swing nozzles are the main research directions of adjustable nozzles. In the field of bearing swing nozzle, but restricting the development of adjustable nozzle is dynamic sealing technology.

At present, carbon-phenolic resin sealing rings or polytetrafluoroethylene jackets are mainly used. Due to the characteristics of non-metals, there will be certain hidden dangers in the adjustable nozzles with high temperature, multi-swing, and fast response, which restricts the bearing swinging nozzles. development of technology.

SUMMARY OF THE INVENTION

In view of this, the main purpose of the present invention is to provide a dynamic sealing structure with a thin wall of a swing nozzle of a solid rocket motor.

In order to achieve the above object, the technical scheme of the present invention is achieved in this way:

An embodiment of the present invention provides a dynamic sealing structure for a thin-walled swing nozzle of a solid rocket motor, the structure includes a movable ball, a sealing ball seat, a V-shaped metal sealing ring, and a sealing ball cover, and the movable ball is arranged on the sealing ball On the seat, the sealing ball seat and the sealing ball cover are connected by screws 5, and a V-shaped metal sealing ring is arranged in the rectangular area formed by the sealing ball seat, the sealing ball cover and the movable ball.

In the above solution, a flexible graphite ring is provided at the joint between the sealing ball seat and the sealing ball cover.

In the above solution, the sealing ball seat, the sealing ball cover, and the movable ball are concentric.

In the above solution, the V-shaped metal sealing ring includes a base and a V-shaped corner, a V-shaped corner is arranged on the base, an inner bonding area is arranged on one side of the V-shaped corner, and an outer bonding area is arranged on the other side. Combined area.

In the above solution, the bending radius and wall thickness of the inner bonding area are determined according to space and pressure.

In the above scheme, the bending radius and wall thickness of the inner bonding area are determined according to space and pressure, specifically: according to the formula S=P*2*R/(4*[σ]*θ)+C, wherein, S is the wall thickness, P is the working pressure, R is the bending radius, [σ] is the material allowable stress, θ is the material stress concentration factor, and C is the wall thickness attachment.

In the above solution, the V-shaped angle is calculated to select an appropriate angle, so that the V-shaped metal sealing ring can generate a sufficient amount of compression.

In the above scheme, the V-shaped angle is calculated and selected as an appropriate angle, specifically: determined according to the formula ɑ=2*arctan(2*A*§/h), where A is the area of the sealing ring, and ɑ is the V-shaped angle The angle of the corner, § is the compression ratio of the seal ring, and h is the depth of the V-shaped corner.

In the above solution, the base is in close contact with the bottom surface of the sealed ball seat, and the inner and outer abutment regions are closely fitted with the sealed ball seat and the nozzle.

Compared with the prior art, the invention has the characteristics of high reliability, good sealing effect, simple results, etc.; wherein the V-shaped metal sealing ring can adapt to higher temperature, and the surface of the sealing ring is sprayed with non-metallic materials, and has better self-lubrication. It can bring a smaller friction coefficient and ensure its good sealing effect during multiple swings.

Description of drawings

The accompanying drawings described herein are used to disclose further understanding of the present invention and constitute a part of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the attached image:

1 is a schematic structural diagram of an embodiment of the present invention;

2 is a structural diagram of a V-shaped metal sealing ring according to an embodiment of the present invention;

3 is a structural diagram of a flexible graphite ring according to an embodiment of the present invention;

Detailed ways

In order to make the objectives, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention, but not to limit the present invention.

The same or similar numbers in the drawings of this embodiment correspond to the same or similar components; in the description of the present invention, it should be understood that the terms "upper", "lower", "left", "right", "inner" The orientation or positional relationship indicated by ", "outside", etc. is based on the orientation or positional relationship shown in the accompanying drawings, which is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the indicated device or element must have a specific Orientation, construction and operation in a specific orientation, so the terms describing the positional relationship in the accompanying drawings are only used for exemplary illustration, and should not be construed as a limitation on this patent. The specific meaning of the term.

It should be noted that, herein, the terms "comprising", "comprising" or any other variation thereof are intended to encompass non-exclusive inclusion, such that a process, article or device comprising a series of elements includes not only those elements, but also Include other elements not expressly listed, or which are inherent to such a process, article or apparatus. Without further limitation, an element qualified by the phrase "comprising a..." does not preclude the presence of additional identical elements in the process, article, or device that includes the element.

An embodiment of the present invention provides a wear-resistant, high-temperature-resistant thin-walled dynamic sealing structure for a solid rocket motor swing nozzle, as shown in Figures 1-3, the structure includes a movable ball 1, a sealing ball seat 2, and a V-shaped metal The sealing ring 3, the sealing ball cover 6, the movable ball 1 is arranged on the sealing ball seat 2, the sealing ball seat 2 and the sealing ball cover 6 are connected by screws 5, the sealing ball seat 2, the sealing ball cover 6 and A V-shaped metal sealing ring 3 is arranged in the rectangular area formed by the movable sphere 1 .

A flexible graphite ring 4 is provided at the connection between the sealing ball seat 2 and the sealing ball cover 6 .

The outer side of the V-shaped metal seal 3 is provided with a non-metallic coating, which can ensure the sealing performance during the rotation process.

Install the V-shaped metal sealing ring 3, with the opening facing the intake side; during the working process, the V-shaped metal sealing ring 3 is opened to a certain opening by pressure to ensure the tightness.

The V-shaped metal sealing ring 3 includes a base 31 and a V-shaped corner 32. The base 31 is provided with a V-shaped corner 32. The V-shaped corner 32 is provided with an inner bonding area 33 on one side and a V-shaped corner 32 on the other side. Outer conformation area 34 .

The bending radius and wall thickness of the inner fitting area 33 are determined according to space and pressure.

Specifically, the bending radius and wall thickness of the inner bonding area 33 are determined according to the space and pressure, specifically: determined according to the formula S=P*2*R/(4*[σ]*θ)+C, wherein, S is the wall thickness, P is the working pressure, R is the bending radius, [σ] is the material allowable stress, θ is the material stress concentration factor, and C is the wall thickness attachment.

The V-shaped angle 32 is calculated to select an appropriate angle so that the V-shaped metal sealing ring 3 can generate a sufficient amount of compression. Specifically, the V-shaped angle 32 is calculated to select an appropriate angle, specifically: determined according to the formula ɑ=2*arc tan(2*A*§/h), where A is the area of the seal ring, and ɑ is V The angle of the type angle 32, § is the compression ratio of the seal ring, and h is the depth of the V-shaped angle 32.

When in use, the base 31 is in close contact with the bottom surface of the sealing ball seat 2, and the inner abutting area 33 and the outer abutting area 34 are in close contact with the sealing ball seat 2 and the nozzle; The fitting area 34 is closely fitted and provides a good seal by pressure, and the inner fitting area 33 is fitted with the curved surface of the nozzle, with the rotation of the nozzle, a good fitting effect is ensured by pressure, thereby providing a good sealing effect .

Since one side of the V-shaped sealing ring 3 is a metal surface and the other side is a non-metallic curved surface, it is necessary to ensure the bonding force and bonding area on both sides during the working process. It can be seen from Figure 2 that the V-shaped sealing ring 3 has a thinner end during the working process, and is in point contact when the pressure is low, and has a sealing effect. The sealing effect ensures that the greater the pressure, the better the sealing effect.

The above descriptions are only preferred embodiments of the present invention, and are not intended to limit the protection scope of the present invention.

Claims (9)

1. The dynamic sealing structure for the thin wall of the swinging nozzle of the solid rocket engine is characterized by comprising a movable ball body, a sealing ball seat, a V-shaped metal sealing ring and a sealing ball cover, wherein the movable ball body is arranged on the sealing ball seat, the sealing ball seat is connected with the sealing ball cover through a screw 5, and the V-shaped metal sealing ring is arranged in a rectangular area formed by the sealing ball seat, the sealing ball cover and the movable ball body.

2. The dynamic seal structure for the thin wall of the swinging nozzle of the solid rocket engine according to claim 1, wherein a flexible graphite ring is arranged at the joint of the sealing ball seat and the sealing ball cover.

3. The dynamic seal structure for the thin wall of the swinging nozzle of the solid rocket engine according to claim 1 or 2, wherein the seal ball seat, the seal ball cover and the movable ball body are concentric.

4. The dynamic sealing structure for the thin wall of the pendular nozzle of a solid rocket engine as recited in claim 3, wherein said V-shaped metal sealing ring comprises a base and a V-shaped corner, said base is provided with a V-shaped corner, one side of said V-shaped corner is provided with an inner side bonding region, and the other side of said V-shaped corner is provided with an outer side bonding region.

5. The dynamic seal structure for the thin wall of the pendular nozzle of a solid rocket engine as recited in claim 4, wherein the bending radius and the wall thickness of said inboard landing zone are determined by space and pressure.

6. The dynamic seal structure for the thin wall of the oscillating nozzle of the solid rocket engine according to claim 5, wherein the bending radius and the wall thickness of the inner bonding area are determined according to space and pressure, and specifically: the material stress concentration coefficient is determined according to the formula S ═ P ^ 2 ^ R/(4 ^ sigma ^ theta) + C, wherein S is the wall thickness, P is the working pressure, R is the bending radius, [ sigma ] is the material allowable stress, theta is the material stress concentration coefficient, and C is the wall thickness accessory quantity.

7. The dynamic seal structure for a thin wall of a solid rocket engine pendular nozzle of claim 5 wherein said V-shaped angle is calculated and selected to be an appropriate angle to allow a sufficient amount of compression of the V-shaped metal seal ring.

8. The dynamic seal structure for the thin wall of the pendular nozzle of a solid rocket engine as recited in claim 7, wherein said V-shaped angle is calculated by selecting a suitable angle, specifically: the sealing ring compression ratio is determined according to a formula of a ═ 2 § arctan (2 § a § h), wherein a is the sealing ring area, a is the angle of the V-shaped angle, a is the sealing ring compression ratio, and h is the depth of the V-shaped angle.

9. The dynamic seal structure for the thin wall of the pendular nozzle of a solid rocket engine as recited in claim 8, wherein said base is attached to the bottom surface of said sealing ball seat, and said inner and outer attachment areas are both closely attached to said sealing ball seat and said nozzle.

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