A vertically arranged nozzle reaction force structure with an array distribution

Abstract

The present invention relates to a vertically arranged nozzle reaction thrust structure with an array distribution, which includes a cabin section housing, a reaction thrust engine, a connecting rod, and an ignition system; the reaction thrust engines are symmetrically distributed in a circumferential array along the inner wall surface of the cabin section housing, and are connected to the cabin section housing through a connecting rod and a nozzle housing flanging structure; the ignition system is a non-electrically transmitted explosion ignition system, which includes an igniter and detonating cords. The non-electrically transmitted explosion ignition system is connected to the cabin section cable through the igniter end and is connected to the reaction thrust engines one-to-one through multiple detonating cords; the axis of the nozzle assembly is perpendicular to the axis of the combustion chamber; an adiabatic ring is bonded to the inner wall surface of the combustion chamber housing, and a converging ring is bonded to the interface of the combustion chamber housing; a throat liner is bonded to the inlet of the nozzle assembly. The present invention can adapt to the axial layout space of the projectile body, increase the effective payload, and improve the missile range under the strict limitation of the axial dimension.

Description

Technical Field

[0001] The present invention relates to a vertically arranged nozzle reaction thrust structure with an array distribution, belonging to the technical field of solid rocket engines. Background Art

[0002] To meet the development requirements of the systematization, light weight, and high range of tactical missile weapons, the power system is gradually developing from a single-stage engine to a multi-stage power system. To achieve reliable separation between stages, it is necessary to provide reverse thrust through a reaction engine to eliminate negative loads. The reaction engine is arranged in the inter-stage compartment of the missile. It not only needs to achieve reliable connection with the compartment to meet the overall reaction thrust requirements but also needs to be miniaturized to shorten the axial space and provide necessary space for the payloads of other compartments.

[0003] The existing reaction thrust mainly adopts traditional single layouts, with the combustion chamber and nozzle axes in the same direction or in the same plane.

[0004] The problems with the traditional layout and structure are that the layout form cannot flexibly adapt to the airframe structure layout and occupies a large axial space of the airframe. Summary of the Invention

[0005] The technical problem solved by the present invention is: overcoming the deficiencies of the prior art, providing a vertically arranged nozzle reaction thrust structure with an array distribution, which can adapt to the axial layout space of the airframe, increase the payload, and improve the missile range under strict restrictions on the axial dimension.

[0006] The technical solution adopted by the present invention to solve the problem is:

[0007] A vertically arranged nozzle reaction thrust structure with an array distribution, comprising a compartment housing, a reaction engine, a connecting rod, and an ignition system;

[0008] The reaction engines are symmetrically distributed in a circumferential array along the inner wall surface of the compartment housing and are connected to the compartment housing through a connecting rod and a nozzle housing flanging structure;

[0009] The ignition system is a non-electric detonation ignition system, comprising an igniter and detonating cords. The non-electric detonation ignition system is connected to the compartment cable through the igniter end and is connected to the reaction engines one-to-one through multiple detonating cords;

[0010] The reaction engine includes: a combustion chamber and a nozzle assembly; the axis of the nozzle assembly is perpendicular to the axis of the combustion chamber; an adiabatic ring is bonded to the inner wall surface of the combustion chamber housing, and a converging ring is bonded to the interface of the combustion chamber housing; a throat liner is bonded to the inlet of the nozzle assembly; the outlet of the nozzle assembly forms an angle with the axis, which is an oblique cut outlet structure.

[0011] Furthermore, the outer wall surface of the combustion chamber is fixedly connected with lugs and is connected to the connecting rod through bolts.

[0012] Furthermore, the upper surface of the connecting rod is a cylindrical curved surface, and the diameter of the curved surface is the same as the inner wall diameter of the cabin section shell.

[0013] Furthermore, the upper surface of the nozzle flanging structure is a cylindrical curved surface, and the diameter of the curved surface is the same as the inner wall diameter of the cabin section shell.

[0014] Furthermore, the angle between the nozzle exit plane and the nozzle axis is 30° to 50°.

[0015] Furthermore, the detonating cord contained in the non-electric transmission explosion ignition system is multiple, and the quantity is the same as the number of reverse thrust engines; the detonating cord of the non-electric transmission explosion ignition system is fixed to the cabin section shell or the engine shell by an adhesive bonding method.

[0016] Furthermore, the adiabatic ring has a through-hole structure at the butt joint with the nozzle converging ring, and the aperture of the through-hole is the same as the inner diameter of the converging ring.

[0017] Furthermore, the converging ring is adhesively received inside the combustion chamber shell interface. The material of the converging ring is a carbon fiber / phenolic molded product, the bonding material is a curing adhesive, and the butt joint fit gap between the converging ring and the nozzle is filled with a sealant.

[0018] Furthermore, the adiabatic ring is adhesively bonded to the inner wall surface of the combustion chamber in the butt joint area with the nozzle. The bonding material is a curing adhesive, and the material of the adiabatic ring is high-silica glass-wound steel.

[0019] Furthermore, the throat liner is adhesively bonded to the nozzle inlet. The bonding material is a curing adhesive, the material of the throat liner is a felt carbon / carbon composite material, the material of the nozzle shell is 30Cr3SiNiMoVA, and the material of the combustion chamber shell is 30Cr3SiNiMoVA.

[0020] The beneficial effects of the present invention compared with the prior art are as follows:

[0021] (1) Under the strict limitation of the axial dimension, the present invention has a flexible layout form, can be disassembled into parts, and multiple reverse thrust engines are dispersedly arranged outside the nozzle and in the circumferential space inside the cabin section shell;

[0022] (2) The axis of the nozzle of the present invention is perpendicular to the axis of the combustion chamber, and the total axial length of the engine is significantly shortened. Description of the Drawings

[0023] Figure 1 Schematic layout diagram of the reverse thrust system provided by the present invention;

[0024] Figure 2 Schematic assembly diagram of the reverse thrust engine and the connecting rod provided by the present invention;

[0025] Figure 3Schematic diagram of the beveled exit structure of the nozzle provided by the present invention;

[0026] Where 10 - beveled exit of the nozzle;

[0027] Figure 4 Schematic diagram of the connecting rod structure provided by the present invention;

[0028] Figure 5 Schematic diagram of the flanging structure of the nozzle housing provided by the present invention;

[0029] Figure 6 Schematic diagram of the assembly of the nozzle and the combustion chamber provided by the present invention. Detailed implementation manners

[0030] The present invention will be further described below in conjunction with embodiments.

[0031] The following further details the anti - thrust force structure of an array - type distributed synchronous ignition vertical beveled nozzle provided by the embodiments of the present application in conjunction with the accompanying drawings of the specification. The specific implementation manners may include (as Figures 1 to 6 shown):

[0032] In the solution provided by the embodiments of the present application, Figure 1 is the layout schematic diagram of the anti - thrust force system. As Figure 1 shown, the anti - thrust force structure of the array - type distributed synchronous ignition vertical beveled nozzle provided by the present invention includes: a cabin section housing 1, a thrust - reversing engine 2, a connecting rod 3, and an ignition system 4; the thrust - reversing engine 2 includes: a combustion chamber 21, a nozzle assembly 22; the multiple thrust - reversing engines are circumferentially arrayed symmetrically along the inner wall surface of the cabin section housing, and are connected to the cabin section housing 1 through the connecting rod 11, the flanging structure 12 of the nozzle housing 9, etc.; the ignition system 4 is a non - electric detonating ignition system, including an igniter 41 and a detonating cord 42. The non - electric detonating ignition system is connected to the cabin section cable through the igniter end and is connected to the thrust - reversing engine one - to - one through multiple detonating cords; the axis of the nozzle assembly is perpendicular to the axis of the combustion chamber; an adiabatic ring 5 is bonded to the inner wall surface of the combustion chamber housing, and a converging ring 6 is bonded to the interface 8 of the combustion chamber housing; a throat liner 7 is bonded to the inlet of the nozzle assembly; the outlet of the nozzle assembly forms a certain angle with the axis, which is a beveled exit structure.

[0033] In the embodiments provided by the present application, the specific structural dimensions of the cabin section housing are determined according to the mechanical interface of the overall missile design.

[0034] Furthermore, the connecting rod is connected to the cabin section by 3 M8 screws, and the nozzle flanging is connected to the cabin section by 4 M4 screws;

[0035] Furthermore, two lugs are welded on the outer wall surface of the combustion chamber and are connected to the connecting rod by 2 M8 single - end bolts;

[0036] Further, the ignition system is threadedly connected to the section housing by 4 M4 screws;

[0037] Further, the upper surface of the connecting rod is a cylindrical curved surface, and the curved surface radius and the inner wall diameter of the section housing are both Φ510mm;

[0038] Further, the upper surface of the nozzle flanging structure is a cylindrical curved surface, and the diameter is Φ510mm;

[0039] Further, the included angle between the nozzle outlet plane and the nozzle axis is 35°;

[0040] Further, the non-electric detonating ignition system contains 4 detonating cords and 4 engines;

[0041] Further, the detonating cords of the non-electric detonating ignition system are fixed to the section housing or the engine housing by adhesive tape bonding;

[0042] Further, the nozzle is connected to the combustion chamber by 6 M4 screws, positioned by pins, and sealed by an O-ring;

[0043] Further, a converging ring is adhesively received inside the interface of the combustion chamber housing. The material of the converging ring is carbon fiber / phenolic molded product, the adhesive material is curing glue, and the gap between the converging ring and the nozzle butt joint is filled with sealant;

[0044] Further, an adiabatic ring is adhesively bonded to the inner wall surface of the combustion chamber in the area where it is butted with the nozzle. The adhesive material is curing glue, and the material of the adiabatic ring is high silica glass-wound steel;

[0045] Further, the adiabatic ring has a through-hole structure at the butt joint with the nozzle converging ring, and the through-hole diameter and the inner diameter of the converging ring are both Φ13mm;

[0046] Further, a throat liner is adhesively bonded to the nozzle inlet. The adhesive material is curing glue, the material of the throat liner is felt carbon / carbon composite material, the material of the nozzle housing is 30Cr3SiNiMoVA, and the material of the combustion chamber housing is 30Cr3SiNiMoVA.

[0047] In one embodiment, the diameter of the reverse thrust engine combustion chamber is Φ70mm, the length is 150mm, the length of the reverse thrust engine nozzle is 123mm. Through the perpendicular design of the combustion chamber and the nozzle axis, the reverse thrust engine occupies an axial length of 177mm in the missile body, and the axial space is reduced by 35%.

[0048] Under the condition of strict axial dimension limitation, the present invention has a flexible layout form and can be disassembled from the whole into parts. Multiple reverse thrust engines are dispersedly arranged in the circumferential space inside the cabin section shell outside the nozzle. The axis of the nozzle of the present invention is perpendicular to the axis of the combustion chamber, and the total axial length of the engine is significantly shortened.

[0049] This structure has been applied in this model, and the product processability and producibility have been verified. It has passed multiple ground and flight tests, with reliable structure and meeting the overall requirements.

[0050] 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 based on the technical essence of the present invention without departing from the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A vertically arranged nozzle reaction force structure with an array distribution, characterized in that, It includes a cabin section shell, a thrust reverser engine, a connecting rod, and an ignition system; The thrust reverser engines are symmetrically distributed in a circumferential array along the inner wall surface of the cabin section shell, and are connected to the cabin section shell through a connecting rod and a nozzle shell flanging structure; The ignition system is a non-electrically transmitted explosion ignition system, including an igniter and detonating cords. The non-electrically transmitted explosion ignition system is connected to the cabin section cable through the igniter end and is connected to the thrust reverser engines one-to-one through multiple detonating cords; The thrust reverser engine includes: a combustion chamber and a nozzle assembly; the axis of the nozzle assembly is perpendicular to the axis of the combustion chamber; an adiabatic ring is bonded to the inner wall surface of the combustion chamber shell, and a converging ring is bonded to the interface of the combustion chamber shell; a throat liner is bonded to the inlet of the nozzle assembly; the outlet of the nozzle assembly forms a certain angle with the axis, which is an oblique cut outlet structure.

2. The vertical nozzle reaction force structure with an array distribution according to claim 1, characterized in that Lugs are fixedly connected to the outer wall surface of the combustion chamber and are connected to the connecting rod through bolts.

3. The vertical nozzle reaction force structure with array distribution according to claim 1, characterized in that, The upper surface of the connecting rod is a cylindrical curved surface, and the diameter of the curved surface is the same as the diameter of the inner wall surface of the cabin section shell.

4. The vertical nozzle reaction force structure with an array distribution according to claim 1, characterized in that, The upper surface of the nozzle flanging structure is a cylindrical curved surface, and the diameter of the curved surface is the same as the diameter of the inner wall surface of the cabin section shell.

5. The vertical nozzle reaction force structure with array distribution according to claim 1, characterized in that, The angle between the nozzle outlet plane and the nozzle axis is 30° to 50°.

6. The vertical nozzle reaction force structure with an array distribution according to claim 1, characterized in that, The non-electrically transmitted explosion ignition system contains multiple detonating cords, and the number is the same as the number of thrust reverser engines; the detonating cords of the non-electrically transmitted explosion ignition system are fixed to the cabin section shell or the engine shell by bonding.

7. The vertical nozzle reaction thrust structure with an array distribution according to claim 1, characterized in that, The adiabatic ring has a through-hole structure at the butt joint with the nozzle converging ring, and the aperture of the through-hole is the same as the inner diameter of the converging ring.

8. A vertically arranged nozzle reaction force structure with an array distribution according to claim 1, characterized in that, A converging ring is adhesively received inside the interface of the combustion chamber shell. The material of the converging ring is a carbon fiber / phenolic molded product, the bonding material is a curing adhesive, and the gap between the converging ring and the nozzle is filled with a sealant.

9. The vertical nozzle reaction force structure with array distribution according to claim 1, characterized in that, An adiabatic ring is bonded to the inner wall surface of the combustion chamber in the butt joint area with the nozzle. The bonding material is a curing adhesive, and the material of the adiabatic ring is high-silica glass-wound steel.

10. The vertical nozzle reaction force structure with an array distribution according to claim 1, characterized in that, A throat liner is bonded to the inlet of the nozzle. The bonding material is a curing adhesive, the material of the throat liner is felt carbon / carbon composite material, the material of the nozzle shell is 30Cr3SiNiMoVA, and the material of the combustion chamber shell is 30Cr3SiNiMoVA.

Images