A plug-type vector nozzle structure for a solid rocket motor

Abstract

A plug-type vector nozzle structure for a solid rocket engine, which is used to solve the problems existing in the thrust vector control of plug nozzles. The existing plug nozzle structures and forms are all aimed at aeroengines or liquid rocket engines, without considering the application situation on solid rocket engines and are not applicable to the technical problems of solid rocket engines. The plug-type vector nozzle includes a plug cone, a ring throat shroud, and a combustion chamber, which realizes the adjustment of the nozzle profile inside the plug nozzle to achieve the purpose of thrust vector control. It has a simple structure, high reliability, a wide working range, high nozzle efficiency, a large lateral force, and a strong deflection ability.

Description

Technical Field

[0001] The present invention relates to a plug-type vector nozzle structure for a solid rocket motor, belonging to the field of solid rocket motors. Background Art

[0002] A nozzle is an energy conversion device of a jet engine, which generates thrust by converting high-temperature gas into the kinetic energy of the gas, and is an important factor affecting the performance of the engine. The plug nozzle has an automatic altitude compensation characteristic and can maintain a high nozzle efficiency within a large operating altitude range. The existing plug nozzle vector technology is mainly realized by using the secondary jet thrust vector technology, which has the disadvantages of low efficiency, complex thermal protection structure, and large weight, restricting the application of the plug nozzle in solid rocket motors. Summary of the Invention

[0003] The technical problem solved by the present invention is: aiming at the problem that the existing plug nozzle structure in the current prior art is not applicable to solid rocket motors, a plug-type vector nozzle structure for a solid rocket motor is proposed.

[0004] The present invention solves the above technical problem by the following technical solutions:

[0005] A plug-type vector nozzle structure for a solid rocket motor includes a plug cone and a ring throat shroud. The ring throat shroud is disposed around the outside of the plug cone. The plug cone, the ring throat shroud, and the combustion chamber together form a plug-type vector nozzle. The outer profile surface of the plug cone and the inner profile surface of the ring throat shroud together constitute the aerodynamic profile of the plug-type vector nozzle.

[0006] The ring throat shroud is a variable profile structure, including a ring throat housing, an adiabatic layer, an elastic layer, a rigid layer, and servo lugs. The adiabatic layer and the ring throat housing are a fixed structure, and the elastic layer, the rigid layer, and the servo lugs are variable structures.

[0007] The elastic layer and the rigid layer are alternately combined into a flat plate structure. Two servo lugs are circumferentially connected at 90° on the outermost rigid layer and move along the radial direction of the engine under the drive of an external servo motor to complete the deformation of the inner profile surface.

[0008] The elastic layer and the rigid layer of the ring throat shroud form a variable profile, which is the expansion section of the plug-type vector nozzle, and the gas flows supersonically in the expansion section.

[0009] The combustion chamber includes a combustion chamber housing, a combustion chamber adiabatic layer, and a combustion chamber charge. The inner side of the combustion chamber housing is the combustion chamber adiabatic layer, and the combustion chamber charge is disposed in the combustion chamber adiabatic layer. Both the plug cone and the ring throat shroud are detachably connected to the combustion chamber housing.

[0010] The annular throat insulation layer is made of ablative and erosion-resistant carbon-carbon material, the elastic layer is made of ablative-resistant silicone rubber material, and the rigid layer is made of carbon fiber / epoxy resin or high-silica fiberglass cloth / epoxy resin material.

[0011] The elastic layer and the rigid layer are adhesively bonded to the insulation layer and the annular throat housing after being formed by thermal adhesion vulcanization.

[0012] In the plug-type vector nozzle, after the combustion chamber charge is ignited to generate gas, the annular throat cover deforms as required. The change in the area on both sides of the gas outlet of the annular throat cover after deformation causes a change in the gas Mach number, and the change in the side wave system of the plug cone leads to uneven pressure distribution to generate a lateral force.

[0013] The plug-type vector nozzle controls the thrust vector of the plug-type vector nozzle by controlling the deformation degree of the variable profile to control the lateral force on the plug cone wall surface.

[0014] The flow channel cross-sectional area of the variable profile of the annular throat cover is greater than 1.4 times the annular throat area.

[0015] The advantages of the present invention compared with the prior art are as follows:

[0016] A plug-type vector nozzle structure of a solid rocket engine provided by the present invention adopts an annular throat cover structure with a variable profile. Two servo lugs are circumferentially connected at 90° to the outermost rigid layer and can move radially along the engine under the drive of a servo motor to realize the deformation of the inner profile. The adjustment of the nozzle profile inside the plug-type nozzle can be achieved by controlling the profile of the annular throat cover, achieving the purpose of thrust vector control. The structure is simple, highly reliable, has a wide working range, high nozzle efficiency, large lateral force, and strong deflection ability. Brief Description of the Drawings

[0017] Figure 1 It is a schematic structural diagram of the plug-type vector nozzle of the solid rocket engine provided by the invention;

[0018] Figure 2 It is a schematic structural diagram of the annular throat cover provided by the invention;

[0019] Figure 3 It is a schematic diagram of the comparison of the aerodynamic profiles after the adjustment of the plug-type vector nozzle annular throat cover provided by the invention;

[0020] Figure 4 It is a schematic diagram of the CFD analysis result of the plug-type vector nozzle provided by the invention - the pressure distribution on the plug cone wall surface; Detailed Description of the Invention

[0021] A plug-type vector nozzle structure for a solid rocket engine, which is used to solve the problems existing in the thrust vector control of plug nozzles. The existing plug nozzle structures and forms are all for aeroengines or liquid rocket engines, without considering the application situation on solid rocket engines and are not applicable to the technical problems of solid rocket engines. The plug-type vector nozzle includes a plug cone, an annular throat shroud, and a combustion chamber, where:

[0022] The annular throat shroud is arranged around the outside of the plug cone. The plug cone, the annular throat shroud, and the combustion chamber together form the plug-type vector nozzle. The outer contour surface of the plug cone and the inner contour surface of the annular throat shroud together form the aerodynamic contour surface of the plug-type vector nozzle;

[0023] The annular throat shroud is a variable contour surface structure, including an annular throat shell, an insulation layer, an elastic layer, a rigid layer, and servo lugs. The insulation layer and the annular throat shell are fixed structures, and the elastic layer, the rigid layer, and the servo lugs are variable structures;

[0024] The elastic layer and the rigid layer are alternately combined into a flat plate structure. Two servo lugs are circumferentially connected at 90° on the outermost rigid layer and move along the radial direction of the engine under the drive of an external servo motor to complete the deformation of the inner contour surface;

[0025] The elastic layer and the rigid layer of the annular throat shroud form a variable contour surface, which is the expansion section of the plug-type vector nozzle. The gas flows supersonically in the expansion section;

[0026] The combustion chamber includes a combustion chamber shell, a combustion chamber insulation layer, and a combustion chamber charge. The inner side of the combustion chamber shell is the combustion chamber insulation layer, and the combustion chamber charge is arranged in the combustion chamber insulation layer. Both the plug cone and the annular throat shroud are detachably connected to the combustion chamber shell;

[0027] The annular throat insulation layer is made of a carbon-carbon material resistant to ablation and erosion. The elastic layer is made of an ablation-resistant silicone rubber material, and the rigid layer is made of a carbon fiber / epoxy resin or high-silica glass cloth / epoxy resin material;

[0028] The elastic layer and the rigid layer are bonded to the insulation layer and the annular throat shell after being formed by thermo-vulcanization;

[0029] In the plug-type vector nozzle, after the combustion chamber charge is ignited, gas is generated. The annular throat shroud deforms as required. After deformation, the change in the area on both sides of the gas outlet of the annular throat shroud causes a change in the gas Mach number, and the change in the side wave system of the plug cone causes uneven pressure distribution to generate a lateral force;

[0030] The plug-type vector nozzle controls the thrust vector of the plug-type vector nozzle by controlling the deformation degree of the variable contour surface and controlling the lateral force on the wall surface of the plug cone.

[0031] The following is further described in conjunction with the accompanying drawings of the specification and the preferred embodiments:

[0032] In the current embodiment, as Figures 1 to 4As shown, the reference numerals are specifically: 1 - plug cone; 2 - annular throat shroud; 3 - combustion chamber housing; 4 - combustion chamber thermal insulation layer; 5 - combustion chamber charge; 21 - annular throat thermal insulation layer; 22 - annular throat housing; 23 - elastic layer; 24 - rigid layer; 25 - servo lug, where:

[0033] Embodiment 1:

[0034] As Figure 1 shown, it is a schematic structural diagram of the plug-type vector nozzle of the solid rocket engine provided by this Embodiment 1; as Figure 2 shown, it is a schematic structural diagram of the annular throat shroud provided by this Embodiment 1; as Figure 3 shown, it is Figure 2 the comparison of the aerodynamic profile after the adjustment of the annular throat shroud; as Figure 4 shown, it is the CFD analysis result of the plug-type vector nozzle provided by this Embodiment 1 - the wall pressure of the plug cone.

[0035] Refer to Figure 1 shown, the plug-type vector nozzle of the solid rocket engine provided by the present invention includes a plug cone 1 and an annular throat shroud 2, and the outer profile of the plug cone and the inner profile of the annular throat shroud together constitute the aerodynamic profile of the plug-type vector nozzle.

[0036] Refer to Figure 2 shown, the annular throat shroud 2 is a variable-profile structure, where the annular throat thermal insulation layer 21 and the annular throat housing 22 are fixed structures, and the elastic layer 23, the rigid layer 24 and the servo lug 25 are variable structures. The elastic layer 23 and the rigid layer 24 are a multi-layer flat structure formed by alternating combinations. Two servo lugs 25 are circumferentially connected to the outermost rigid layer at 90°, and move along the radial direction of the engine under the drive of the servo motor to realize the deformation of the inner profile.

[0037] Refer to Figure 1 shown, the plug cone 1 and the annular throat shroud 2 are respectively detachably connected to the combustion chamber housing 3.

[0038] Refer to Figure 2 shown, the annular throat thermal insulation layer 21 is made of carbon-carbon material resistant to ablation and erosion, the annular throat housing 22 is made of high-strength steel material, the elastic member 23 is made of ablation-resistant silicone rubber material, and the rigid member 24 is made of carbon fiber / epoxy resin or high-silica glass cloth / epoxy resin material.

[0039] Refer to Figure 4 shown, after the annular throat shroud is deformed, the area on one side of the outlet becomes larger, the gas Mach number increases while the area on the other side of the outlet becomes smaller, the gas Mach number decreases, resulting in uneven distribution of the wall pressure of the plug cone and thus obtaining a lateral force to realize the thrust vector control of the plug nozzle.

[0040] As a preferred implementation, the elastic member 23 and the rigid member 24 are formed by thermo-vulcanizing adhesion and then bonded to the annular throat thermal insulation layer 21 and the annular throat housing 22.

[0041] As a preferred embodiment, the variable profile of the annular throat shroud 2 is the divergent section of the inner nozzle of the plug nozzle, where the combustion gas is in supersonic flow. Preferably, the ratio of the cross-sectional area of the variable part of the flow path of the annular throat shroud 2 to the throat area should be greater than 1.4.

[0042] As a preferred embodiment, the plug cone profile is designed by the Angelino method and then truncated by 40% - 60%.

[0043] As a preferred embodiment, the single-layer thickness of the elastic member 23 should be between 0.8 mm and 1.5 mm, and the single-layer thickness of the rigid member 24 should be between 2.0 mm and 4.0 mm.

[0044] The servo lug 25 moves radially along the engine under the drive of the servo motor to deform the variable profile, and the degree of deformation is controllable. At the same time, the combustion chamber charge is ignited to generate combustion gas, and the Mach number of the combustion gas is controlled by the degree of deformation to generate a lateral force on the wall surface, realizing the thrust vector control of the plug vector nozzle.

[0045] Although the present invention has been disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the technical solution of the present invention all fall within the protection scope of the technical solution of the present invention.

[0046] The content not described in detail in the specification of the present invention belongs to the well-known technology of those skilled in the art.

Claims

1. A plug-type vector nozzle structure for a solid rocket engine, characterized in that: It includes a plug cone and an annular throat shroud. The annular throat shroud is arranged around the outside of the plug cone. The plug cone, the annular throat shroud, and the combustion chamber together form a plug-type vector nozzle. The outer profile surface of the plug cone and the inner profile surface of the annular throat shroud together constitute the aerodynamic profile of the plug-type vector nozzle; The annular throat shroud is a variable-profile structure, including an annular throat housing, an insulating layer, an elastic layer, a rigid layer, and servo lugs. The insulating layer and the annular throat housing are fixed structures, and the elastic layer, the rigid layer, and the servo lugs are variable structures; The elastic layer and the rigid layer are flat structures formed by alternating combinations. Two servo lugs are circumferentially connected at 90° on the outermost rigid layer and move along the radial direction of the engine under the drive of an external servo motor to complete the deformation of the inner profile surface.

2. A plug-type vector nozzle structure for a solid rocket engine according to claim 1, characterized in that: The elastic layer and the rigid layer of the annular throat shroud form a variable profile, which is the expansion section of the plug-type vector nozzle, and the gas flows supersonically in the expansion section.

3. A plug-type vector nozzle structure for a solid rocket engine according to claim 2, characterized in that: The combustion chamber includes a combustion chamber housing, a combustion chamber insulating layer, and a combustion chamber charge. The inner side of the combustion chamber housing is the combustion chamber insulating layer, and the combustion chamber charge is arranged in the combustion chamber insulating layer. Both the plug cone and the annular throat shroud are detachably connected to the combustion chamber housing.

4. A plug-type vector nozzle structure for a solid rocket engine according to claim 3, characterized in that: The insulating layer of the annular throat shroud is made of a carbon-carbon material resistant to ablation and erosion, the elastic layer is made of a silicone rubber material resistant to ablation, and the rigid layer is made of a carbon fiber / epoxy resin or high-silica glass cloth / epoxy resin material.

5. A plug-type vector nozzle structure for a solid rocket engine according to claim 4, characterized in that: The elastic layer and the rigid layer are bonded to the insulating layer and the annular throat housing after being formed by thermal adhesion vulcanization.

6. A plug-type vector nozzle structure for a solid rocket engine according to claim 5, characterized in that: In the plug-type vector nozzle, after the combustion chamber charge is ignited to generate gas, the annular throat shroud deforms as required. The change in the area on both sides of the gas outlet of the annular throat shroud after deformation causes a change in the gas Mach number, and the change in the side wave system of the plug cone causes uneven pressure distribution to generate a lateral force.

7. A plug-type vector nozzle structure for a solid rocket engine according to claim 6, characterized in that: The plug-type vector nozzle controls the thrust vector of the plug-type vector nozzle by controlling the deformation degree of the variable profile and controlling the lateral force on the wall of the plug cone.

8. A plug-type vector nozzle structure for a solid rocket engine according to claim 7, characterized in that: The ratio of the flow channel cross-sectional area of the variable profile of the annular throat shroud to the annular throat area is greater than 1.4.

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