CN115929506A - Shell assembly of rocket engine and carrier rocket - Google Patents
Shell assembly of rocket engine and carrier rocket Download PDFInfo
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- CN115929506A CN115929506A CN202211058180.XA CN202211058180A CN115929506A CN 115929506 A CN115929506 A CN 115929506A CN 202211058180 A CN202211058180 A CN 202211058180A CN 115929506 A CN115929506 A CN 115929506A
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Abstract
The embodiment of the application provides a shell assembly of a rocket engine and a carrier rocket. The rocket engine housing assembly comprises: the engine comprises an engine shell, a reinforcing piece arranged on the periphery of the engine shell and an outer part connected with the reinforcing piece, wherein the reinforcing piece is provided with a first clamping portion, and the outer part is provided with a second clamping portion. The first clamping portion and the second clamping portion are mutually embedded and in interference connection. The embodiment of the application realizes simple and convenient connection between the outer part and the reinforcing part, is convenient to install, does not need to perform operations such as welding seam flaw detection on the engine shell, has low cost, does not need to weld or modify the engine shell per se, ensures that the installation between the outer part and the engine shell has small influence on the working pressure bearing of the engine shell per se, and ensures the working reliability of the engine shell.
Description
Technical Field
The application relates to the technical field of engines of carrier rockets, in particular to a shell assembly of a rocket engine and a carrier rocket.
Background
In addition to providing the power required for a full projectile, a rocket engine is generally provided with external parts required for the carrier rocket as a whole on the outer surface of an engine shell of the rocket engine, and the external parts are used for installing cables, hanging parts and the like to form an engine shell assembly.
At present, the forming mode of the engine shell assembly mainly comprises an integral machining mode and a welding mode. The integral machining method is to directly integrate the outer part and the engine housing, but this will significantly increase the material preparation and processing costs of the engine housing, which is not favorable for the cost-effective design of the metal housing. The welding mode is to connect the external part containing the organic allowance with the metal engine shell in a fillet weld mode, so that the material preparation cost of raw materials can be reduced, but the later fillet weld flaw detection and the external part finish machining after the solder mask of the engine shell also can cause the increase of the production cost of the shell.
In summary, the current engine housings are expensive to manufacture.
Disclosure of Invention
The application aims at the defects of the prior art and provides a shell assembly of a rocket engine and a carrier rocket, which are used for solving the technical problem that the cost is high in the prior art that an external part is arranged outside an engine shell.
In a first aspect, embodiments of the present application provide a rocket engine case assembly, including: the engine comprises an engine shell, a reinforcing piece arranged on the periphery of the engine shell and an outer part connected with the reinforcing piece;
the reinforcing piece is provided with a first clamping portion, and the outer part is provided with a second clamping portion;
the first clamping portion and the second clamping portion are mutually embedded and in interference connection.
Optionally, the reinforcement comprises a first transition ring, a reinforcement ring and a second transition ring which are arranged around the outer periphery of the engine shell along the first direction in sequence; the first direction is parallel to the axial direction of the engine housing;
the first clamping portion is formed on the reinforcing ring.
Optionally, the first clamping portion includes a first protrusion, and the second clamping portion includes a first groove;
the first bulge is embedded in the first groove and is in interference connection with the first groove;
along the radial direction of the engine shell, the first end of the first bulge is close to the peripheral surface of the engine shell, and the second end of the first bulge is attached to the groove bottom of the first groove; the first end of the first projection has a smaller size than the second end of the first projection in a circumferential direction of the engine case.
Optionally, the first protrusion is a dovetail, and the first groove is a dovetail groove;
the included angle of the tail end of the dovetail groove is 45 degrees to 65 degrees.
Optionally, the first clamping portion further includes a first clamping groove and a second clamping groove formed in the reinforcing ring, and the first protrusion is formed between the first clamping groove and the second clamping groove;
the second clamping part also comprises a first limiting piece and a second limiting piece which are formed on two sides of the first groove;
the first limiting piece and the second limiting piece are respectively embedded into the first clamping groove and the second clamping groove.
Optionally, the depth of the first clamping groove is consistent with that of the second clamping groove and is consistent with the thickness of the reinforcing ring;
the first surface of the first limiting part is attached to the outer surface of the engine shell exposed out of the first clamping groove, and the first surface of the second limiting part is attached to the outer surface of the engine shell exposed out of the second clamping groove.
Optionally, the first transition ring has a first gap for the first limiting member and the second limiting member to move;
and/or the second transition ring is provided with a second gap for the movement of the first limiting piece and the second limiting piece.
Optionally, the rocket motor housing assembly further comprises at least one of:
the outer diameter of the reinforcing ring is 1-3 mm larger than that of the engine shell;
along the axial direction of the engine shell, the size of the reinforcing ring is 10-15 mm larger than that of the outer part, and the outer part is located in the middle of the reinforcing ring;
the size of the outer part is 5 mm-20 mm larger than the size of the second end of the first protrusion of the reinforcing ring along the circumferential direction of the reinforcing ring.
Optionally, in a plane parallel to the axial direction of the engine housing, one end of the first transition ring is flush with the outer surface of the engine housing, the other end is flush with the outer circumferential surface of the reinforcement ring, one end of the second transition ring is flush with the outer circumferential surface of the reinforcement ring, and the other end is flush with the outer circumferential surface of the housing.
Optionally, the number of stiffeners is two; the outer member includes: the missile wing support and the cable support;
the first clamping part of one reinforcing piece is in interference connection with the second clamping part of the missile wing support;
the first clamping portion of the other reinforcing piece is in interference connection with the second clamping portion of the cable support.
In a second aspect, embodiments of the present application provide a launch vehicle, including: a housing assembly for a rocket engine as provided in the first preceding aspect.
The beneficial technical effects brought by the technical scheme provided by the embodiment of the application comprise:
in the case assembly of the rocket engine provided by the embodiment of the application, the reinforcing piece is arranged outside the engine case, the outer part is connected with the reinforcing piece, and the strength of the engine case meeting the load requirement of the outer part can be ensured. The reinforcement has first joint portion, and the outer part has second joint portion, and first joint portion and mutual gomphosis of second joint portion and interference are connected for the outer part is connected closely with engine case, can guarantee the reliability of being connected between outer part and the engine case. The connecting structure between the outer part and the reinforcing part is simple, the mounting is convenient, the mounting is simple and reliable, operations such as weld seam flaw detection and the like are not needed to be carried out on the engine shell, the cost is low, the welding or other transformation on the engine shell is not needed, the influence of the mounting between the outer part and the engine shell on the working pressure bearing of the engine shell is small, and the working reliability of the engine shell is ensured. Additional aspects and advantages of the present application will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the present application.
Drawings
The foregoing and/or additional aspects and advantages of the present application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1 is a schematic structural diagram of a housing assembly of an engine according to an embodiment of the present disclosure;
FIG. 2 is a schematic diagram of a connection structure of a housing assembly of an engine according to an embodiment of the present disclosure;
FIG. 3 is a schematic view of a connection structure of a housing assembly of another engine according to an embodiment of the present disclosure;
FIG. 4 is a schematic structural diagram of an outer component of a housing assembly of an engine provided in an embodiment of the present application;
FIG. 5 is a schematic structural diagram of an outer component of a housing assembly of another engine provided in accordance with an embodiment of the present disclosure;
FIG. 6 is a schematic structural diagram illustrating the connection between an engine housing and a reinforcing member of a housing assembly of an engine according to an embodiment of the present disclosure;
FIG. 7 is a dimensional schematic representation of a housing assembly of an engine according to an embodiment of the present disclosure.
Reference numerals:
100-a housing assembly;
10-an engine housing;
20-a reinforcement; 21-a first transition ring; 210-a first gap; 22-a reinforcement ring; 220-a first clamping part; 221-a first projection; 2210-a second end of the first projection 221; 222-a first card slot; 223-a second card slot; 23-a second transition ring; 230-a second gap;
30-an outer part; 310-a second snap-in part; 311-a first groove; 312 — a first stop; 313-a second stop; 301-missile wing support; 302-cable support.
Detailed Description
Embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the embodiments set forth below in connection with the drawings are exemplary descriptions for explaining technical solutions of the embodiments of the present application, and do not limit the technical solutions of the embodiments of the present application.
As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, elements, and/or components, but do not preclude the presence or addition of other features, information, data, steps, operations, elements, components, and/or groups thereof that may be implemented as required by the art. It will be understood that when an element is referred to as being "connected" or "coupled" to another element, it can be directly connected or coupled to the other element or intervening elements may be present. The term "and/or" as used herein means at least one of the items defined by the term, e.g., "a and/or B" may be implemented as "a", or as "B", or as "a and B".
To make the objects, technical solutions and advantages of the present application more clear, embodiments of the present application will be described in further detail below with reference to the accompanying drawings.
The research and development idea of the application comprises: at present, the forming modes of the metal engine shell and the outer part mainly comprise an integral machining mode and a welding mode. The integral machining mode may require designing the machining device, and the machining cost is increased remarkably. If the welding mode is adopted, the welding position needs to be designed in a reinforcing mode, but the structure of the engine can be inevitably influenced, so that the later fillet weld flaw detection and the finish machining of the outer part after the welding resistance of the engine shell can also cause the increase of the production cost of the engine shell assembly.
The application provides a shell assembly of a rocket engine and a carrier rocket, and aims to solve the technical problems in the prior art.
The following describes the technical solutions of the present application and how to solve the above technical problems with specific embodiments. It should be noted that the following embodiments may be referred to, referred to or combined with each other, and the description of the same terms, similar features, similar implementation steps and the like in different embodiments is not repeated.
The embodiment of the application provides a shell assembly 100 of a rocket engine, which comprises: the engine case 10, a reinforcement 20 provided on the outer periphery of the engine case 10, and an outer member 30 connected to the reinforcement 20.
The reinforcement member 20 has a first snap portion 220 and the outer member 30 has a second snap portion 310.
The first engaging portion 220 and the second engaging portion 310 are engaged with each other and connected with each other by interference.
In this embodiment, referring to fig. 1 and 2, the reinforcement member 20 is provided outside the engine housing 10, and the outer member 30 is connected to the reinforcement member 20, so as to ensure that the strength of the engine housing 10 meeting the load requirement of the outer member 30 can be ensured. The reinforcement member 20 has the first clamping portion 220, the outer member 30 has the second clamping portion 310, and the first clamping portion 220 and the second clamping portion 310 are mutually embedded and in interference connection, so that the outer member 30 is tightly connected with the engine shell 10, and the connection reliability between the outer member 30 and the engine shell 10 can be ensured. The connecting structure between the outer part 30 and the reinforcing part 20 is simple, the installation is convenient, the installation is simple and reliable, the operations such as weld seam detection and the like are not needed to be carried out on the engine shell 10, the cost is low, the welding or other transformation on the engine shell 10 is not needed, the influence of the installation between the outer part 30 and the engine shell 10 on the working pressure bearing of the engine shell 10 is small, and the working reliability of the engine shell 10 is ensured. Reference is made to fig. 4 and 5, which show two configurations of the outer part.
It will be appreciated that the outer component 30 is an outer component 30 relative to the engine housing 10, and is a type of structure for mounting or suspending other components from the engine housing 10, rather than an outer component of the housing assembly 100.
Optionally, the reinforcement ring 22 is fixedly connected to the engine housing 10.
In some possible embodiments, referring to fig. 6, the stiffener 20 includes a first transition ring 21, a stiffener ring 22, and a second transition ring 23 arranged in sequence around the outer circumference of the engine case 10 along the first direction. The first direction is parallel to the axial direction of the engine case 10.
The first clamping portion 220 is formed on the reinforcing ring 22.
In this embodiment, the first clamping portion 220 is in interference connection with the reinforcing ring 22, and the first transition ring 21 and the second transition ring 23 are respectively disposed on two sides of the reinforcing ring 22, so that the influence of the strength of the engine case 10 caused by the local stress concentration of the reinforcing ring 22 during the operation of the rocket engine can be reduced, and the operational reliability of the engine case 10 is improved.
In some possible embodiments, referring to fig. 2, the first clip portion 220 includes a first protrusion 221, and the second clip portion 310 includes a first recess 311.
The first protrusion 221 is embedded in the first groove 311 and is in interference connection with the first groove 311.
Along the radial direction of the engine housing 10, a first end of the first protrusion 221 is close to the outer circumferential surface of the engine housing 10, and a second end of the first protrusion 221 is attached to the groove bottom of the first groove 311. The first end of the first projection 221 has a smaller size than the second end of the first projection 221 in the circumferential direction of the engine case 10.
In this embodiment, the size of the first protrusion 221 may be slightly larger than that of the first groove 311 (but within a dimensional tolerance), so that the first protrusion 221 is clamped into the first groove 311 by an external force, and the first protrusion 221 or the first groove 311 deforms to some extent, thereby achieving an interference connection between the first protrusion 221 and the first groove 311. The first protrusion 221 is wider at the top and narrower at the bottom, so that the connection relationship between the first protrusion 221 and the first groove 311 is more reliable.
In some possible embodiments, the first protrusion 221 is a dovetail and the first recess 311 is a dovetail groove.
The included angle of the tail end of the dovetail groove is 45 degrees to 65 degrees.
Dovetail grooves, also known as male and female tongues, refer to two fittings that can be connected in a unique manner, divided into two parts, one of which is fully contained by the other in the connection, the one contained being called male and the other female. In this embodiment, the first protrusion 221 is a dovetail or a male head, which can be regarded as a trapezoidal guide rail, the first groove 311 is a dovetail or a female head, and the shape of the first protrusion 221 and the shape of the first groove 311 are adapted, so that only one form of the first protrusion 221 and the first groove 311 can be connected, and the connection precision is high and stable.
The included angle of the tail end of the dovetail groove can also be called as the angle (alpha hereinafter) of a slope of the dovetail groove, the included angle is within the range of 45-65 degrees (including 45 degrees and 60 degrees), interference connection is achieved conveniently through external force, the shell assembly 100 of the rocket engine is not prone to sliding under the action of the external force, and reliability of the shell assembly 100 of the rocket engine is high.
During operation of the rocket engine, the outer part 30 is forced substantially in the radial or circumferential direction of the engine housing 10, so that it is not easily slid in the circumferential or radial direction of the engine housing 10 due to the trapezoidal design of the dovetail. In addition, the dovetail joint and the dovetail groove are designed to be in interference fit connection, so that the dovetail joint and the dovetail groove are difficult to slide in the axial direction of the engine housing 10, and the outer part 30 and the reinforcement 20 are ensured to be firmly connected. Simple structure, connection are reliable and easily realize, can reduce the cost of prepareeing material of raw and other materials, satisfy the relevant size of totality and geometric tolerances requirement.
In some possible embodiments, referring to fig. 2 to 5, the first locking portion 220 further includes a first locking groove 222 and a second locking groove 223 opened on the reinforcing ring 22, and the first protrusion 221 is formed between the first locking groove 222 and the second locking groove 223.
The second clamping portion 310 further includes a first limiting member 312 and a second limiting member 313 formed on two sides of the first recess 311.
The first retaining member 312 and the second retaining member 313 are respectively embedded in the first slot 222 and the second slot 223.
In the present embodiment, the first locking groove 222 and the second locking groove 223 are opened on the reinforcing ring 22, and a portion between the first locking groove 222 and the second locking groove 223 forms the first protrusion 221. The first recess 311 is formed by slotting at the middle position of one end of the external element 30, and two sides of the first recess 311 form a first retaining element 312 and a second retaining element 313 protruding from the first recess 311. When the first clamping portion 220 is clamped with the second clamping portion 310, the first limiting member 312 is clamped into the first clamping groove 222 and is in interference fit connection, the second limiting member 313 is clamped into the second clamping groove 223 and is in interference fit connection, and the first protrusion 221 is clamped into the first groove 311 and is in interference fit connection, so that the outer member 30 and the reinforcing ring 22 are in interference fit connection, and the connection reliability between the outer member 30 and the engine housing 10 is ensured.
Optionally, referring to fig. 2, the depth of the first locking groove 222 is the same as the depth of the second locking groove 223 and is smaller than the thickness of the reinforcement ring 22. The entire first locking groove 222 and the second locking groove 223 are opened on the reinforcing ring 22, and have little influence on the engine housing 10.
In some possible embodiments, referring to fig. 3, the depth of the first locking groove 222 is the same as the depth of the second locking groove 223, and is the same as the thickness of the reinforcement ring 22.
The first surface of the first limiting member 312 is attached to the outer surface of the engine housing 10 exposed by the first engaging groove 222, and the first surface of the second limiting member 313 is attached to the outer surface of the engine housing 10 exposed by the second engaging groove 223.
In this embodiment, the depth of the first engaging groove 222 is the same as the depth of the second engaging groove 223, and the depth of the first engaging groove 222 is the same as the thickness of the stiffener 20, that is, the first engaging groove 222 and the second engaging groove 223 are both through grooves, and can expose the outer surface of the engine case 10, and the first protrusion 221 at this time is in the thickest state. After the first limiting member 312 and the second limiting member 313 are respectively clamped into the first clamping groove 222 and the second clamping groove 223, both the first limiting member 312 and the second limiting member 313 contact the engine housing 10, so that the reinforcement ring 22, the engine housing 10, and the outer member 30 can be constrained with each other and are in a relatively stable state.
In some possible embodiments, referring to fig. 6, the first transition ring 21 has a first gap 210 for moving the first limiting member 312 and the second limiting member 313.
Optionally, the second transition ring 23 has a second gap 230 for the movement of the first limiting member 312 and the second limiting member 313.
In this embodiment, the first retaining member 312 and the second retaining member 313 of the outer member 30 can slide into the first locking groove 222 and the second locking groove 223 from the first gap 210 or the second gap 230, respectively, along the axial direction, and the interference connection is realized under the action of the external force. At least one of the first transition ring 21 and the second transition ring 23 may have a gap.
Alternatively, the first gap 210 provided in the present application may be one or more slits cut out from the first transition ring 21, so that the first retaining member 312 and the second retaining member 313 can slide into the first slot 222 and the second slot 223.
Alternatively, the first transition ring 21 may be mounted to the engine casing 10 and then the first transition ring 21 may be cut to facilitate assembly of the entire casing assembly 100.
Alternatively, the mounting position of the first transition ring 21 and the alignment position of the gap 210 may be designed on the housing assembly 20 in advance, the first gap 210 is cut out from the first transition ring 21, and then the first transition ring 21 with the first gap 210 is assembled with the engine housing 10, so as to avoid the influence of the cutting out of the first transition ring 21 on the reliability of the engine housing 10 on the basis of achieving easy assembly.
It is understood that the second transition ring 23 has a similar structure to the first transition ring 21, and the forming process of the second gap 230 is similar to that of the first gap 210, and those skilled in the art can adopt similar implementation means for the second gap 230 based on the forming process of the first gap 210, and details are not repeated herein.
Optionally, the outer diameter of the stiffener ring 22 is 1 mm to 3 mm (this range includes 1 mm and 3 mm) larger than the outer diameter of the engine case 10. Within this data range, the reinforcement ring 22 can provide good reinforcement, strength of the engine case 10 at the mounting of the outer member 30, and does not take up too much space.
Alternatively, the size of the reinforcement ring 22 is 10 mm to 15 mm (the range includes 10 mm and 15 mm) larger than the size of the outer member 30 in the axial direction of the engine case 10, and the outer member 30 is located at the center of the reinforcement ring 22.
In the present embodiment, the width of the reinforcement ring 22 is larger than the width of the outer member 30 in the axial direction of the engine case 10, and the contact area between the reinforcement ring 22 and the engine case 10 is large, which facilitates the stress dispersion. The outer part 30 is located in the middle of the stiffener ring 22 so that the stress can be evenly distributed on both sides of the stiffener ring 22, further ensuring the reliability of the case assembly 100 of the engine.
Optionally, the dimension of the outer member 30 is 5 mm to 20 mm larger than the dimension of the second end 2210 of the first projection 221 of the reinforcement ring 22 in the circumferential direction of the reinforcement ring 22.
In this embodiment, the first protrusion 221 is clamped in the outer member 30, and the size of the outer member 30 is larger than the first protrusion 2215 mm to 20 mm, that is, the first protrusion 221 or the first groove 311 has a certain distance from the edge of the outer member 30, or the first limiting member 312 or the second limiting member 313 has a certain width, so that the first limiting member 312 and the second limiting member 313 have a certain strength, and the connection reliability between the first limiting member 312 and the first card slot 222, and between the second limiting member 313 and the second card slot 223 is ensured.
Optionally, the first surface of the first retaining member 312 and the first surface of the second retaining member 313 of the outer member 30 are both arc-shaped and fit with the outer surface of the engine housing 10. Wherein, the bottom surface of the first groove 311 is also arc-shaped.
In some possible embodiments, in a plane parallel to the axial direction of the engine case 10, one end of the first transition ring 21 is flush with the outer surface of the engine case 10, the other end is flush with the outer circumferential surface of the reinforcement ring 22, and one end of the second transition ring 23 is flush with the outer circumferential surface of the reinforcement ring 22, and the other end is flush with the outer circumferential surface of the case.
In this embodiment, the first transition ring 21 and the second transition ring 23 are respectively disposed on two sides of the stiffener ring 22, and the first transition ring 21 adopts a slope transition structure, a thickness of an end close to the stiffener ring 22 is approximately equal to a thickness of the stiffener ring 22, a thickness of an end far from the stiffener ring 22 is approximately equal to a thickness of the engine housing 10, an inner diameter of the first transition ring 21 is consistent with an inner diameter of the stiffener ring 22, and remains unchanged, and an outer diameter is equivalent to an expansion along an axial direction of the engine housing 10 to be consistent with an outer diameter of the stiffener ring 22.
The second transition ring 23 is a slope transition structure, the thickness of the end close to the reinforcing ring 22 is approximately equal to that of the reinforcing ring 22, the thickness of the end far from the reinforcing ring 22 is approximately equal to that of the engine shell 10, the inner diameter of the second transition ring 23 is consistent with that of the reinforcing ring 22, the inner diameter is kept unchanged, and the outer diameter is equivalent to the outer diameter expanded to be consistent with that of the reinforcing ring 22 along the axial direction of the engine shell 10.
The present embodiment further ensures the operational reliability of the engine case 10 by using the ramp type transition ring structure such that the stress applied to the reinforcement ring 22 is gradually dispersed by the first transition ring 21 and the second transition ring 23.
Optionally, the axial dimension of the first transition ring 21 or the second transition ring 23 is about 10 mm.
In some possible embodiments, please refer to fig. 1, the number of the reinforcing members 20 is two. The outer part 30 comprises: a missile wing support 301 and a cable support 302.
The first fastening portion 220 of one reinforcement member 20 is in interference fit with the second fastening portion 310 of the missile wing support 301.
The first clamping portion 220 of the other reinforcement member 20 is in interference fit with the second clamping portion 310 of the cable support 302.
Alternatively, in this embodiment, the outer member 30 may be a missile wing support 301, a cable support 302, etc., and there may be many other outer members 30, which are not listed here, but those skilled in the art can select them according to actual needs. Two stiffeners 20 are located the periphery of engine housing 10 along the axial cover, and outer part 30 all can be connected with beaded finish 22 through the public female tenon mode that this application provided to make outer part 30 and beaded finish 22 interference connection through designing certain error band, need not to reform transform engine housing 10, improve engine housing 10's operational reliability. And the cost is low, the structure is simple, and the realization is easy.
Alternatively, referring to fig. 7, an outer member 30 of a housing assembly 100 of an engine has a missile wing support 301 and a cable support 302, which are connected in a dovetail configuration. The outer diameter R2 of the reinforcement ring 22 at the connection point of the engine housing 10 is 1.5 mm larger than the inner diameter R1, the axial length is larger than the outer part 3010 mm, and the reinforcement ring 22 is transited at both ends by a first transition ring 21 and a second transition ring 23 having slopes, and the axial width of the slopes is 10 mm.
The missile wing holder 301 has a curvature that is adapted to the curvature of the outer surface of the engine casing 10. In the dovetail groove structure of the missile wing support 301, L2 is the length of the missile wing support 301 along the circumferential direction and is 14 mm, L1 is the widest position of the dovetail groove along the circumferential direction and is 10 mm, and α is the angle of the tail end of the dovetail groove, specifically 60 degrees. In the dovetail groove structure of cable holder 302, L2 is that cable holder 302 is along the circumference, and length is 40 millimeters, and L1 length is 25 millimeters, and alpha angle is 60 degrees. The cable support 302 and the missile wing support 301 are connected with the reinforcing ring 22 on the outer surface of the engine shell 10 in an interference mode.
During installation, the finished outer part 30 is inlaid on the reinforcing ring 22 by external force, and the outer part 30 is located in the middle of the casing reinforcing ring 22, namely, the axial edge of the outer part 30 is 5 mm away from the edge of the reinforcing ring 22.
Based on the same inventive concept, the embodiment of the application provides a carrier rocket, which comprises: a housing assembly 100 for a rocket motor as provided in any one of the preceding embodiments.
The carrier rocket provided by the embodiment comprises the shell assembly 100 of the rocket engine provided by the above embodiment, and the implementation principle is similar, and the description is omitted here. Wherein the housing assembly 100 is employed in a power system of a launch vehicle.
By applying the embodiment of the application, the following beneficial effects can be at least realized:
1. in some embodiments, the engine case 10 is externally provided with the reinforcement member 20, and the outer member 30 is connected to the reinforcement member 20, so that the strength of the engine case 10 meeting the load requirement of the outer member 30 can be ensured. The reinforcement member 20 is provided with a first clamping portion 220, the outer member 30 is provided with a second clamping portion 310, and the first clamping portion 220 and the second clamping portion 310 are mutually embedded and in interference connection, so that the outer member 30 is tightly connected with the engine shell 10, and the connection reliability between the outer member 30 and the engine shell 10 can be ensured. The connection structure between the outer part 30 and the reinforcing member 20 is simple, the installation is convenient, the installation is simple and reliable, operations such as weld seam flaw detection and the like are not needed to be carried out on the engine shell 10, the cost is low, welding or other transformation on the engine shell 10 is not needed, the influence of the installation between the outer part 30 and the engine shell 10 on the working pressure bearing of the engine shell 10 is small, and the working reliability of the engine shell 10 is ensured.
2. In some embodiments, the size of the first protrusion 221 may be slightly larger than that of the first groove 311, so that the first protrusion 221 is clamped into the first groove 311 by an external force, and the first protrusion 221 or the first groove 311 deforms to some extent, so as to achieve the interference connection between the first protrusion 221 and the first groove 311. The first protrusion 221 is wider at the top and narrower at the bottom, so that the connection relationship between the first protrusion 221 and the first groove 311 is more reliable.
3. In some embodiments, the first protrusion 221 is a dovetail or a male head, which can be regarded as a trapezoid guide rail, the first groove 311 is a dovetail or a female head, and the first protrusion 221 and the first groove 311 are adapted in shape, so that the first protrusion 221 and the first groove 311 can be connected only in one form, and the connection precision is high and stable.
4. In some embodiments, the depth of the first engaging groove 222 is the same as the depth of the second engaging groove 223, and the thickness of the reinforcing member 20 is the same, that is, the first engaging groove 222 and the second engaging groove 223 are through grooves, and can expose the outer surface of the engine case 10, when the first protrusion 221 is in the thickest state. After the first limiting member 312 and the second limiting member 313 are respectively clamped into the first clamping groove 222 and the second clamping groove 223, the first limiting member 312 and the second limiting member 313 are both in contact with the engine case 10, so that the stiffener ring 22, the engine case 10, and the outer member 30 can be constrained with each other and are in a relatively stable state.
5. In some embodiments, the first retaining member 312 and the second retaining member 313 of the outer member 30 can slide into the first locking groove 222 and the second locking groove 223 from the first gap 210 or the second gap 230, respectively, in the axial direction, and the interference connection is realized under the action of the external force. At least one of the first transition ring 21 and the second transition ring 23 may have a gap.
6. In some embodiments, the first transition ring 21 adopts a slope transition structure, the thickness of the end close to the reinforcing ring 22 is approximately equal to the thickness of the reinforcing ring 22, the thickness of the end far from the reinforcing ring 22 approaches the thickness of the engine casing 10, the inner diameter of the first transition ring 21 is consistent with the inner diameter of the reinforcing ring 22, the inner diameter is kept constant, and the outer diameter is equivalent to expand to be consistent with the outer diameter of the reinforcing ring 22 along the axial direction of the engine casing 10. The second transition ring 23 is a slope transition structure, the thickness of the end close to the reinforcing ring 22 is approximately equal to that of the reinforcing ring 22, the thickness of the end far from the reinforcing ring 22 is approximately equal to that of the engine shell 10, the inner diameter of the second transition ring 23 is consistent with that of the reinforcing ring 22, the inner diameter is kept unchanged, and the outer diameter is equivalent to the outer diameter expanded to be consistent with that of the reinforcing ring 22 along the axial direction of the engine shell 10. The present embodiment further ensures the operational reliability of the engine case 10 by using the ramp type transition ring structure, such that the stress applied to the reinforcement ring 22 is gradually dispersed by the first transition ring 21 and the second transition ring 23.
In the description of the present application, the directions or positional relationships indicated by the words "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like are for convenience of description or simplicity of describing the embodiments of the present application based on the exemplary directions or positional relationships shown in the drawings, and do not indicate or imply that the devices or components referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, are not to be construed as limiting the present application.
The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, the meaning of "a plurality" is two or more unless otherwise specified.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
In the description herein, particular features, structures, materials, or characteristics may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing is only a part of the embodiments of the present application, and it should be noted that it is within the scope of the embodiments of the present application that other similar implementation means based on the technical idea of the present application can be adopted by those skilled in the art without departing from the technical idea of the present application.
Claims (11)
1. A rocket engine housing assembly, comprising: an engine case, a reinforcement provided on an outer periphery of the engine case, and an outer member connected to the reinforcement;
the reinforcement has a first snap-in portion and the outer member has a second snap-in portion;
the first clamping portion and the second clamping portion are mutually embedded and in interference connection.
2. A rocket engine housing assembly as recited in claim 1, wherein said stiffener comprises a first transition ring, a stiffener ring, and a second transition ring arranged in sequence about an outer periphery of said engine housing in a first direction; the first direction is parallel to an axial direction of the engine case;
the first clamping portion is formed on the reinforcing ring.
3. A rocket engine housing assembly as recited in claim 2, wherein said first catch portion comprises a first projection, and said second catch portion comprises a first recess;
the first protrusion is embedded in the first groove and is in interference connection with the first groove;
along the radial direction of the engine shell, the first end of the first bulge is close to the outer peripheral surface of the engine shell, and the second end of the first bulge is attached to the groove bottom of the first groove; the first end of the first projection has a size smaller than a size of the second end of the first projection in a circumferential direction of the engine case.
4. A rocket engine housing assembly according to claim 3 wherein said first protrusion is a dovetail and said first groove is a dovetail groove;
the included angle of the tail end of the dovetail groove is 45-65 degrees.
5. A rocket engine housing assembly according to claim 3, wherein said first clip portion further comprises a first clip groove and a second clip groove opening on said reinforcing ring, said first projection being formed between said first clip groove and said second clip groove;
the second clamping part also comprises a first limiting piece and a second limiting piece which are formed at two sides of the first groove;
the first limiting piece and the second limiting piece are respectively embedded into the first clamping groove and the second clamping groove.
6. A rocket engine housing assembly according to claim 5, wherein the depth of said first slot corresponds to the depth of said second slot and corresponds to the thickness of said reinforcing ring;
the first surface of the first limiting part is attached to the outer surface of the engine shell, exposed out of the first clamping groove, and the first surface of the second limiting part is attached to the outer surface of the engine shell, exposed out of the second clamping groove.
7. A rocket engine housing assembly as recited in claim 5, wherein said first transition ring has a first gap for movement of said first retaining member and said second retaining member;
and/or the second transition ring is provided with a second gap for the movement of the first limiting piece and the second limiting piece.
8. A rocket engine housing assembly as recited in claim 2, comprising at least one of:
the outer diameter of the reinforcing ring is 1-3 mm larger than that of the engine shell;
the size of the reinforcing ring is 10-15 mm larger than that of the outer part along the axial direction of the engine shell, and the outer part is located in the middle of the reinforcing ring;
the size of the outer part is 5-20 mm larger than the size of the second end of the first protrusion of the reinforcing ring along the circumferential direction of the reinforcing ring.
9. A rocket engine housing assembly as recited in claim 2, wherein said first transition ring has one end flush with an outer surface of said engine housing and another end flush with an outer peripheral surface of said reinforcing ring, and said second transition ring has one end flush with an outer peripheral surface of said reinforcing ring and another end flush with an outer peripheral surface of said housing, in a plane parallel to an axial direction of said engine housing.
10. A rocket engine case assembly according to claim 1 wherein the number of said reinforcing members is two; the outer part comprises: a missile wing support and a cable support;
the first clamping part of the reinforcing piece is in interference connection with the second clamping part of the missile wing support;
and the other first clamping part of the reinforcing part is in interference connection with the second clamping part of the cable support.
11. A launch vehicle, comprising: a rocket motor housing assembly according to any one of claims 1-10.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211058180.XA CN115929506B (en) | 2022-08-30 | 2022-08-30 | Rocket engine shell assembly and carrier rocket |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211058180.XA CN115929506B (en) | 2022-08-30 | 2022-08-30 | Rocket engine shell assembly and carrier rocket |
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| CN115929506A true CN115929506A (en) | 2023-04-07 |
| CN115929506B CN115929506B (en) | 2023-09-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202211058180.XA Active CN115929506B (en) | 2022-08-30 | 2022-08-30 | Rocket engine shell assembly and carrier rocket |
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| JPH07260400A (en) * | 1994-03-18 | 1995-10-13 | Mitsubishi Heavy Ind Ltd | Mounting device |
| US20120234967A1 (en) * | 2011-03-16 | 2012-09-20 | Christou Kyriakos C | Low-heat-transfer interface between metal parts |
| CN203196330U (en) * | 2013-03-14 | 2013-09-18 | 梁伟基 | Water rocket nozzle with tail wing mechanism |
| CN104696103A (en) * | 2013-12-10 | 2015-06-10 | 上海新力动力设备研究所 | Welding structure of missile wing support of solid rocket engine |
| CN209386907U (en) * | 2018-11-23 | 2019-09-13 | 江西洪都航空工业集团有限责任公司 | Fixed missile wing connection member |
| KR102184614B1 (en) * | 2019-07-26 | 2020-11-30 | 국방과학연구소 | Fin using dissimilar materials and projectile comprising thereof |
| CN214950929U (en) * | 2021-04-25 | 2021-11-30 | 杭州中天模型有限公司 | Base of water rocket and water rocket |
| CN217303753U (en) * | 2022-06-23 | 2022-08-26 | 北京星途探索科技有限公司 | Missile wing mounting structure suitable for composite material engine shell |
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2022
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07260400A (en) * | 1994-03-18 | 1995-10-13 | Mitsubishi Heavy Ind Ltd | Mounting device |
| US20120234967A1 (en) * | 2011-03-16 | 2012-09-20 | Christou Kyriakos C | Low-heat-transfer interface between metal parts |
| CN203196330U (en) * | 2013-03-14 | 2013-09-18 | 梁伟基 | Water rocket nozzle with tail wing mechanism |
| CN104696103A (en) * | 2013-12-10 | 2015-06-10 | 上海新力动力设备研究所 | Welding structure of missile wing support of solid rocket engine |
| CN209386907U (en) * | 2018-11-23 | 2019-09-13 | 江西洪都航空工业集团有限责任公司 | Fixed missile wing connection member |
| KR102184614B1 (en) * | 2019-07-26 | 2020-11-30 | 국방과학연구소 | Fin using dissimilar materials and projectile comprising thereof |
| CN214950929U (en) * | 2021-04-25 | 2021-11-30 | 杭州中天模型有限公司 | Base of water rocket and water rocket |
| CN217303753U (en) * | 2022-06-23 | 2022-08-26 | 北京星途探索科技有限公司 | Missile wing mounting structure suitable for composite material engine shell |
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| CN115929506B (en) | 2023-09-05 |
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