Rocket engine gimbal seat

Abstract

The invention provides a rocket engine gimbal seat which comprises a pair of upper supports used for being connected with a rocket engine rack, a gimbal ring and a pair of lower supports, the bottoms of the pair of upper supports are hinged to the first two opposite side walls of the gimbal ring in a one-to-one correspondence mode, and the bottoms of the pair of upper supports are hinged to the second two opposite side walls of the gimbal ring in a one-to-one correspondence mode. The tops of the pair of lower supports are hinged to the second two opposite side walls of the gimbal ring in a one-to-one correspondence mode, and the middles of the pair of upper supports and the middles of the pair of lower supports make contact with the gimbal ring through cylindrical surfaces.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aerospace equipment, and particularly relates to a rocket engine gimbal. BACKGROUND

[0002] Key role of liquid rocket engine and gimbal Liquid rocket engine is the core power device of space launch vehicle, and its thrust chamber needs to be connected with the vehicle frame through the gimbal to realize the dynamic adjustment of the thrust direction. As the key force transmission component between the engine and the frame, the gimbal needs to maintain high reliability and lightweight characteristics under complex loads such as thrust, vibration and thermal stress.

[0003] With the increasing demand for carrying capacity of space missions (such as deep space exploration and heavy launch rockets), the optimization of engine thrust-to-weight ratio has become a technical focus. The lightweight design of the gimbal directly affects the overall performance of the engine, and the traditional design method has obvious bottlenecks in modeling accuracy, optimization efficiency and automation degree.

[0004] Limitations of traditional gimbal bearing structure Existing gimbals mostly adopt cross shaft or spherical hinge structure (such as a certain engine gimbal adopts cross shaft configuration, and a certain space shuttle main engine SSME adopts spherical hinge design), and its core design features are as follows: Cross shaft type: realize pitch and yaw movement through orthogonal intersecting shaft system, rely on rigid contact between shaft and ear seat to transfer load, and need to improve strength through local reinforcing ribs or thickening structure.

[0005] Spherical hinge type: realize multi-degree-of-freedom motion by using spherical contact surface, but the problem of contact stress concentration is significant, and high-precision machining and surface coating are needed to reduce wear.

[0006] Existing designs generally increase redundant structures (such as reinforcing ribs and redundant bearings) to improve bearing capacity, resulting in weight increase, and it is difficult to balance the lightweight and reliability requirements.

[0007] Defects and deficiencies of existing technology 1. Single bearing structure form, insufficient ultimate load capacity Defects: The shaft-ear seat contact surface of the cross shaft type gimbal is linear contact or small area surface contact, and the local stress concentration is serious, which limits the bearing capacity. It is difficult to meet the needs of new generation heavy liquid rocket engine (such as thrust exceeding 200 tons), which needs to be compensated by significantly increasing the size or strength of the structure, which significantly increases the weight.

[0008] 2. Redundant design leads to structural complexity and weight redundancy defects: In order to improve reliability, the prior art often adds redundant support structures (such as double ear backup and multi-bearing nesting) at key nodes, resulting in an increase in the number of parts, a complex assembly process, and an increase in the proportion of structural weight (in some cases, the redundant structure accounts for more than 15% of the total weight of the gimbal), which directly conflicts with the goal of engine lightweighting. SUMMARY

[0009] The technical problem to be solved by the present application is to overcome the shortcomings of the prior art and provide a rocket engine gimbal.

[0010] The technical solution for solving the above technical problem is as follows: A rocket engine gimbal comprises a pair of upper supports for connecting with a rocket engine rack, a gimbal ring, and a pair of lower supports, the bottom of the pair of upper supports is hinged to the first opposite two side walls of the gimbal ring one by one, the top of the pair of lower supports is hinged to the second opposite two side walls of the gimbal ring one by one, and the middle part of the pair of upper supports and the middle part of the pair of lower supports are in contact with the gimbal ring through a cylindrical surface.

[0011] The beneficial effects of the technical solution of the present application are as follows: The upper support is used to fix the gimbal to the rocket engine rack, realizing double-degree-of-freedom swinging. The gimbal ring is in contact with the upper support and the lower support through a cylindrical surface. The load-bearing structure of the gimbal is changed from a rotating shaft to a large contact surface, which is equivalent to a sliding bearing on the contact surface, reducing the structural weight. The load is transmitted through the direct contact between the gimbal ring and the upper and lower supports, and the hinged position mainly plays a limiting role in the swinging process, and no additional bearing is arranged. The shear stress borne by the hinged position is reduced, the size of the hinged structure is reduced, and the bearing structure is simplified, thereby reducing the structural weight and complexity of the gimbal, improving the overall performance of the engine, and improving the swinging stability.

[0012] Further, the top of the first opposite two side walls of the gimbal ring and the bottom of the second opposite two side walls of the gimbal ring are provided with protrusions protruding from the gimbal ring, the protrusions are circular arc structures, the protrusions on the top of the first opposite two side walls of the gimbal ring are provided with upper contact surfaces of the gimbal ring, the protrusions on the bottom of the second opposite two side walls of the gimbal ring are provided with lower contact surfaces of the gimbal ring, the upper contact surfaces of the gimbal ring and the lower contact surfaces of the gimbal ring are convex surfaces, the middle part of the pair of upper supports is provided with first concave surfaces matched with the upper contact surfaces of the gimbal ring, and the middle part of the pair of lower supports is provided with second concave surfaces matched with the lower contact surfaces of the gimbal ring.

[0013] The beneficial effects of the further technical scheme are that the gimbals are in contact with the upper supports and the lower supports through a cylindrical surface. The bearing structure of the gimbals is changed from a rotating shaft to a large contact surface, which is equivalent to a sliding bearing on the contact surface, thereby reducing the structure weight. The load is transmitted through the direct contact between the gimbals and the upper supports and the lower supports, and the load is transmitted through normal pressure. The hinge position mainly plays a limiting role in the swinging process, and no additional bearing is arranged. The shear stress borne by the hinge position is reduced, the size of the hinge structure is reduced, the bearing structure is simplified, the structure weight and complexity of the gimbals are reduced, the overall performance of the engine is improved, and the swinging stability is improved.

[0014] Further, the middle part of the pair of upper supports, the middle part of the pair of lower supports, and the surface of the cylindrical surface contact of the gimbals are all electroplated with a chemical nickel Teflon lubricating coating.

[0015] The beneficial effects of the further technical scheme are that the gimbals, the upper supports, and the lower supports are surface treated on the contact cylindrical surface with a high-strength lubricating coating of electroplated chemical nickel Teflon. The friction of the contact surface is reduced, a friction bearing effect is achieved, and the overall structure quality of the gimbals is further improved.

[0016] Further, the gimbals and the lower supports are based on a topological optimization structure design and are processed and formed by additive manufacturing.

[0017] The beneficial effects of the further technical scheme are that the gimbals and the lower supports are based on a topological optimization structure design and are processed and formed by additive manufacturing, so as to maximize the lightweight structure.

[0018] Further, the top of the pair of upper supports is provided with a first connecting plate for connecting with the rocket engine frame, the first connecting plate is a cuboid structure, and the first connecting plate is provided with a first threaded hole; the bottom of the pair of lower supports is provided with a second connecting plate for connecting with the head of the thrust chamber or the turbine pump, the second connecting plate is an arc-shaped plate body, and the second connecting plate is provided with a second threaded hole.

[0019] The beneficial effects of the further technical scheme are that the first connecting plate and the first threaded hole are arranged to facilitate the connection of the upper supports with the rocket engine frame through bolts. The second connecting plate and the second threaded hole are arranged to facilitate the connection of the lower supports with the head of the thrust chamber or the turbine pump through bolts. The installation and maintenance of the gimbals are facilitated, and the stability and reliability of the gimbals are improved.

[0020] Further, a through hole is arranged at the connection position between the bottom of the lower support and the second connecting plate.

[0021] The beneficial effects of the further technical scheme are that the weight of the lower support is further reduced on the premise of ensuring the overall strength of the lower support.

[0022] Further, the bottom of the upper support is correspondingly hinged to the first opposite two side walls of the gimbaling ring through the rotating shaft assembly, and the top of the lower support is correspondingly hinged to the second opposite two side walls of the gimbaling ring through the rotating shaft assembly.

[0023] The beneficial effect of the above further technical solution is that the rotating shaft assembly connects the upper support, the lower support and the gimbaling ring. The rotating shaft assembly limits the spatial position of the gimbaling ring in the bidirectional swing process. The rotating shaft assembly is only used for limiting, and the structure weight can be greatly reduced.

[0024] Further, the rotating shaft assembly comprises a pair of shaft covers and a rotating shaft, and the shaft cover is correspondingly installed at the two ends of the rotating shaft.

[0025] The beneficial effect of the above further technical solution is that the shaft cover and the rotating shaft connect the upper support, the lower support and the gimbaling ring. The rotating shaft limits the spatial position of the gimbaling ring in the bidirectional swing process. The rotating shaft is only used for limiting, and the structure weight can be greatly reduced.

[0026] Further, the middle part of the lower support is connected through a plurality of lower support connecting plates.

[0027] The beneficial effect of the above further technical solution is that the lower support connecting plate is used to limit the structural deformation of the lower support under pressure, and improve the structural rigidity.

[0028] Further, the gimbaling ring is a rectangular structure or a square structure, and the middle part of the gimbaling ring is provided with a through hole.

[0029] The beneficial effect of the above further technical solution is that the gimbaling ring is a rectangular structure or a square structure, which is convenient for realizing double-degree-of-freedom swing. The middle part of the gimbaling ring is provided with a through hole, which further reduces the weight of the lower support under the premise of ensuring the overall strength of the gimbaling ring.

[0030] The advantages of the additional aspects of the application will be partially given in the following description, partially become obvious from the following description, or be understood through the practice of the application. BRIEF DESCRIPTION OF DRAWINGS

[0031] In order to more clearly illustrate the technical solutions of the embodiments of the application, the following will briefly introduce the drawings needed to be used in the embodiments. It should be understood that the following drawings only show some embodiments of the application, and therefore should not be regarded as a limitation to the scope. For those skilled in the art, other related drawings can also be obtained without paying creative labor on the premise of the drawings.

[0032] Figure 1Structure schematic view of rocket engine gimbal provided by the embodiment of the present application.

[0033] Figure 2 Structure schematic view of rocket engine gimbal provided by the embodiment of the present application.

[0034] Brief Description of Drawings: 1, upper support; 2, gimbal upper contact surface; 3, gimbal ring; 4, rotating shaft assembly; 5, lower support; 6, lower support connecting plate; 7, gimbal lower contact surface. DETAILED DESCRIPTION

[0035] The principles and features of the present application are described below in conjunction with the accompanying drawings, in which the embodiments are shown for the purpose of explanation only and are not intended to limit the scope of the present application.

[0036] In order to make the objectives, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below in conjunction with the accompanying drawings of the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. The components of the embodiments of the present application described and shown in the accompanying drawings can be arranged and designed in various different configurations.

[0037] Therefore, the detailed description of the embodiments of the present application provided in the accompanying drawings below is not intended to limit the scope of the claimed present application, but only represents selected embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative labor are within the scope of protection of the present application.

[0038] It should be noted that: similar reference numerals and letters represent similar items in the following drawings, therefore, once an item is defined in one drawing, it does not need to be further defined and explained in the subsequent drawings.

[0039] In the description of the embodiments of the present application, it should be noted that, if the orientation or position relationship indicated by the terms “up”, “down”, “horizontal”, “inner” and the like is based on the orientation or position relationship shown in the drawings, or is the orientation or position relationship when the product of the present application is usually placed, which is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the indicated device or element must have a particular orientation, be constructed and operated in a particular orientation, therefore, it cannot be understood as a limitation on the present application.

[0040] In the description of the embodiments of the present application, it also needs to be explained that, unless explicitly specified and limited, if the terms "arrange", "install", "connect", "connect" appear, they should be understood in a broad sense, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected, it can be mechanically connected, or it can be electrically connected, it can be directly connected, or indirectly connected through an intermediate medium, it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0041] As shown in Figure 1 and Figure 2 The embodiment of the present application provides a rocket engine gimbal, which comprises a pair of upper supports 1 connected with a rocket engine frame, a gimbal ring 3 and a pair of lower supports 5, the bottom of the pair of upper supports 1 is hinged with the first opposite two side walls of the gimbal ring 3 in one-to-one correspondence, the top of the pair of lower supports 5 is hinged with the second opposite two side walls of the gimbal ring 3 in one-to-one correspondence, and the middle part of the pair of upper supports 1 and the middle part of the pair of lower supports 5 are in contact with the gimbal ring 3 through a cylindrical surface.

[0042] The beneficial effects of the technical scheme of the present application are that the upper support is used to fix the gimbal on the rocket engine frame, two degrees of freedom are realized, the gimbal ring is in contact with the upper support and the lower support through a cylindrical surface, the load bearing structure of the gimbal is changed from a rotating shaft to a large contact surface, which is equivalent to a sliding bearing on the contact surface, the structure weight is reduced, the load is transmitted through the normal pressure, the hinge position mainly plays a limiting role in the swinging process, and no additional bearing is arranged, the shear stress borne by the hinge position is reduced, the hinge structure size is reduced, the bearing structure is simplified, the structure weight and complexity of the gimbal are reduced, the overall performance of the engine is improved, and the swinging stability is improved.

[0043] Wherein, the cylindrical surface is a curved surface formed by a straight line moving along a fixed curve in parallel.

[0044] As shown in Figure 1 and Figure 2 The technical problem to be solved by the present application is to realize a high-load gimbal (rocket engine gimbal) with two degrees of freedom 15° swinging under the condition of 200t and above large thrust of liquid rocket engine. The gimbal (rocket engine gimbal) comprises a gimbal ring 3, an upper support 1, a lower support 5, a rotating shaft assembly 4 and a lower support connecting plate 6.

[0045] The upper support 1 is used for fixing the gimbals on the rocket engine frame. The shaft cover and the rotating shaft connect the upper support 1 and the lower support 5 with the gimbals 3. The lower support connecting plate 6 connects the two lower supports 5. The gimbals 3 are in contact with the upper support 1 and the lower support 5 through a cylindrical surface. The gimbals 3, the upper support 1 and the lower support 5 need to be surface treated on the contact cylindrical surface, and are coated with a high-strength lubricating coating of electroplated chemical nickel Teflon. The common gimbals bearing structure currently in use is connected with a rotating shaft, and the size of the rotating shaft needs to be increased with the increase of the engine thrust, which will result in a bulky structure and a large weight. The gimbals bearing structure (rocket engine gimbals) of the embodiment of the present application changes the rotating shaft into a large contact surface, which is equivalent to directly playing the role of a sliding bearing on the contact surface, and the rotating shaft is only used for limiting, so that the structure weight can be greatly reduced. The lower support connecting plate 6 is used for limiting the structural deformation of the lower support 5 under pressure, and the number and position of the connecting plate (lower support connecting plate 6) can be adjusted according to the actual engine thrust, so that better structural rigidity can be achieved.

[0046] As shown in Figure 1 and Figure 2 Further, the top of the first opposite two side walls of the gimbals 3 and the bottom of the second opposite two side walls of the gimbals 3 are provided with protrusions protruding from the gimbals 3, the protrusions are in a circular arc structure, the protrusions on the top of the first opposite two side walls of the gimbals 3 are provided with upper gimbals contact surfaces 2, the protrusions on the bottom of the second opposite two side walls of the gimbals 3 are provided with lower gimbals contact surfaces 7, the upper gimbals contact surfaces 2 and the lower gimbals contact surfaces 7 are convex surfaces, the middle part of the pair of upper supports 1 is provided with first concave surfaces matched with the upper gimbals contact surfaces 2, and the middle part of the pair of lower supports 5 is provided with second concave surfaces matched with the lower gimbals contact surfaces 7.

[0047] The beneficial effects of the above further technical solutions are that the gimbals are in contact with the upper support and the lower support through a cylindrical surface. The gimbals bearing structure is changed from a rotating shaft into a large contact surface, which is equivalent to directly playing the role of a sliding bearing on the contact surface, and the structure weight is reduced. The load is transmitted through the gimbals and the upper and lower supports, the load is transmitted through the normal pressure, the hinge position mainly plays a limiting role in the swinging process, and no additional bearing is arranged. The shear stress borne by the hinge position is reduced, the size of the hinge structure is reduced, the bearing structure is simplified, the structure weight and complexity of the gimbals are reduced, the overall performance of the engine is improved, and the swinging stability is improved.

[0048] Further, the middle part of the pair of upper supports 1, the middle part of the pair of lower supports 5 and the surface of the cylindrical surface contact of the gimbals 3 are all coated with a lubricating coating of electroplated chemical nickel Teflon.

[0049] The beneficial effects of the further technical solutions are that the gimbal ring, the upper support and the lower support are surface treated on the contact column, and are electroplated with chemical nickel Teflon high-strength lubricating coating. The contact surface friction is reduced, the friction bearing effect is achieved, and the overall structural quality of the gimbal is further improved.

[0050] Nickel Teflon electroplating, also known as Ni-Teflon or Ni-PTFE electroplating, is a composite electroplating technology that combines nickel and polytetrafluoroethylene (PTFE).

[0051] Chemical nickel plating is a currentless plating method that relies on the redox reaction occurring in the same solution to reduce metal ions and deposit them on the surface of the part. This method uses a solution containing nickel ions and a reducing agent to deposit a nickel coating on the metal surface through a self-catalytic chemical reaction.

[0052] Nickel Teflon plating is a process in which the workpiece is immersed in an electroless nickel plating solution containing Teflon, and Teflon PTFE and Ni-P nickel-phosphorus alloy are uniformly plated on the surface of the workpiece through chemical deposition. This composite coating combines the corrosion resistance of nickel with the lubricity, wear resistance and hydrophobicity of Teflon.

[0053] Composite coating properties: Teflon PTFE in the composite coating is distributed in the chemical nickel-phosphorus coating without affecting its corrosion resistance, while effectively reducing the friction coefficient. The thickness of the composite coating usually includes a Ni-P (nickel-phosphorus alloy) layer of more than 3 μm and a Ni-PTFE layer of more than 2 μm.

[0054] Preparation process: First, the surface of the substrate is treated, including cleaning, degreasing and grinding operations, to ensure that the adhesion strength between the coating and the substrate is strong enough. Then, Teflon polymer is sprayed on the surface of the substrate to form a uniform coating. The main component of the Teflon coating is tetrafluoroethylene resin, which becomes viscous after melting at high temperature to form a coating. Finally, after spraying the Teflon polymer, the surface is electroplated or physically plated with nickel, and the coated nickel alloy has excellent corrosion resistance and scrub resistance.

[0055] Surface treatment is a process method that artificially forms a layer on the surface of the base material, which is different from the mechanical, physical and chemical properties of the base. The purpose of surface treatment is to meet the requirements of corrosion resistance, wear resistance, decoration or other special functional requirements of the product.

[0056] Further, the gimbal ring 3 and the lower support 5 are designed based on topological optimization and are formed by additive manufacturing.

[0057] The beneficial effects of the further technical solutions are that the gimbal ring and the lower support are designed based on topological optimization and are formed by additive manufacturing to maximize the lightweight structure.

[0058] Topology optimization is a mathematical method for optimizing material distribution in a given area according to given load conditions, constraint conditions and performance indicators. By taking material distribution as the optimization object, topology optimization can find the best distribution scheme in a design space with uniformly distributed materials.

[0059] Additive manufacturing, commonly known as 3D printing, is a manufacturing technology that integrates computer-aided design, material processing and forming technology, and uses digital model files as the basis to manufacture solid objects through software and numerical control system by means of extrusion, sintering, melting, light curing and spraying.

[0060] As shown in Figure 1 and Figure 2 , further, the top of each of the pair of upper supports 1 is provided with a first connecting plate for connecting with the rocket engine frame, the first connecting plate being a cuboid structure, and the first connecting plate is provided with a first threaded hole; the bottom of each of the pair of lower supports 5 is provided with a second connecting plate for connecting with the thrust chamber head or turbine pump, the second connecting plate being an arc-shaped plate body, and the second connecting plate is provided with a second threaded hole.

[0061] The beneficial effects of the above further technical solutions are: the first connecting plate and the first threaded hole are provided to facilitate the connection of the upper support with the rocket engine frame through bolts. The second connecting plate and the second threaded hole are provided to facilitate the connection of the lower support with the thrust chamber head or turbine pump through bolts. This facilitates the installation and maintenance of the gimbals, and improves the stability and reliability of the gimbals.

[0062] As shown in Figure 1 and Figure 2 , further, the bottom of the lower support 5 is provided with a through hole at the connection position of the second connecting plate.

[0063] The beneficial effects of the above further technical solutions are: to further reduce the weight of the lower support while ensuring the overall strength of the lower support.

[0064] As shown in Figure 1 and Figure 2 , further, the bottom of each of the pair of upper supports 1 is hingedly connected to the first opposite two side walls of the gimbals ring 3 through a shaft assembly, and the top of each of the pair of lower supports 5 is hingedly connected to the second opposite two side walls of the gimbals ring 3 through a shaft assembly.

[0065] The beneficial effect of the further technical scheme is that the rotating shaft assembly connects the upper support, the lower support and the gimbaling ring. The rotating shaft assembly limits the spatial position of the gimbaling ring during bidirectional swinging. The rotating shaft assembly only serves as a limiting function, and the structure weight can be greatly reduced.

[0066] As shown in Figure 1 and Figure 2 , further, the rotating shaft assembly comprises a pair of shaft covers and a rotating shaft, and the pair of shaft covers are installed at both ends of the rotating shaft one by one.

[0067] The beneficial effect of the further technical scheme is that the shaft cover and the rotating shaft connect the upper support, the lower support and the gimbaling ring. The rotating shaft limits the spatial position of the gimbaling ring during bidirectional swinging. The rotating shaft only serves as a limiting function, and the structure weight can be greatly reduced.

[0068] The two ends of the rotating shaft can be provided with threaded holes for installing bolts, and the shaft cover is installed at the two ends of the rotating shaft through the bolts. The diameter of the shaft cover is greater than the diameter of the rotating shaft. The shaft cover can be a circular structure.

[0069] The rotating shaft passes through the upper support 1 and the gimbaling ring 3, so that the upper support 1 and the gimbaling ring 3 are hinged, and a pair of shaft covers are located on both sides of the hinged position of the upper support 1 and the gimbaling ring 3 one by one. Similarly, the rotating shaft passes through the lower support 5 and the gimbaling ring 3, so that the lower support 5 and the gimbaling ring 3 are hinged, and a pair of shaft covers are located on both sides of the hinged position of the lower support 5 and the gimbaling ring 3 one by one.

[0070] As shown in Figure 1 and Figure 2 , further, the middle part of the pair of lower supports 5 is connected through a plurality of lower support connecting plates 6.

[0071] The beneficial effect of the further technical scheme is that the lower support connecting plate is used to limit the structural deformation of the lower support under pressure and improve the structural rigidity.

[0072] As shown in Figure 1 and Figure 2 , further, the gimbaling ring 3 is a rectangular structure or a square structure, and the middle part of the gimbaling ring 3 is provided with a through hole.

[0073] The beneficial effect of the further technical scheme is that the gimbaling ring is a rectangular structure or a square structure, which is convenient for realizing double-degree-of-freedom swinging. The middle part of the gimbaling ring is provided with a through hole, which further reduces the weight of the lower support under the premise of ensuring the overall strength of the gimbaling ring.

[0074] The gimbal (a gimbal of a rocket engine) provided by the embodiment of the application is composed of two upper supports 1, a gimbal ring 3, two lower supports 5, four pivot assemblies 4 and two lower support connecting plates 6.

[0075] As shown in Figure 1 and Figure 2 The gimbal (a gimbal of a rocket engine) provided by the embodiment of the application is composed of two upper supports 1, a gimbal ring 3, two lower supports 5, four pivot assemblies 4 and two lower support connecting plates 6.

[0076] The upper support 1 is connected with the engine frame through bolts, and the lower support 5 is connected with the head of the thrust chamber or the turbine pump through bolts. The pivot assembly 4 limits the spatial position of the gimbal in the bidirectional swing process. The lower support connecting plate 6 is used to connect the two lower supports 5, so as to improve the overall strength of the gimbal structure.

[0077] The gimbal ring 3 and the lower support 5 are designed based on topological optimization and are processed by additive manufacturing, so as to maximize the light weight of the structure. In the embodiment of the application, the high-strength lubricating coating of electroplated chemical nickel Teflon is coated on the upper contact surface 2 and the lower contact surface 7 of the gimbal ring, so as to reduce the friction of the contact surface, play the role of a friction bearing, and further improve the overall structural quality of the gimbal.

[0078] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the application, and not to limit them; although the application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the application.

Claims

1. A rocket engine gimbal, characterized in that: include: A pair of upper supports (1), a gimbal (3) and a pair of lower supports (5) for connecting to a rocket engine frame, wherein the bottoms of the pair of upper supports (1) are hinged to the first two opposite side walls of the gimbal (3) in a one-to-one correspondence, the tops of the pair of lower supports (5) are hinged to the second two opposite side walls of the gimbal (3) in a one-to-one correspondence, and the middle parts of the pair of upper supports (1) and the middle parts of the pair of lower supports (5) are in contact with the gimbal (3) through a cylindrical surface.

2. A rocket engine gimbal according to claim 1, characterized in that: The top of the first two opposite side walls of the gimbal ring (3) and the bottom of the second two opposite side walls of the gimbal ring (3) are both provided with protrusions protruding from the gimbal ring (3), and the protrusions are arc-shaped structures. The protrusions at the top of the first two opposite side walls of the gimbal ring (3) are provided with a gimbal ring upper contact surface (2), and the protrusions at the bottom of the second two opposite side walls of the gimbal ring (3) are provided with a gimbal ring lower contact surface (7). The gimbal ring upper contact surface (2) and the gimbal ring lower contact surface (7) are both convex surfaces. The middle parts of a pair of upper supports (1) are both provided with a first concave surface adapted to the gimbal ring upper contact surface (2), and the middle parts of a pair of lower supports (5) are both provided with a second concave surface adapted to the gimbal ring lower contact surface (7).

3. A rocket engine gimbal according to claim 1, characterized in that: The middle parts of the pair of upper supports (1), the middle parts of the pair of lower supports (5) and the surfaces in contact with the cylindrical surface of the gimbal ring (3) are all electroplated with a chemical nickel Teflon lubricating coating.

4. A rocket engine gimbal according to claim 1, characterized in that: The gimbal ring (3) and the lower support (5) are both designed based on topological optimization structures and are formed by additive manufacturing.

5. The rocket engine gimbal according to claim 1, characterized in that: The tops of a pair of upper supports (1) are each provided with a first connecting plate for connecting to a rocket engine frame, the first connecting plate is a rectangular parallelepiped structure, and a first threaded hole is provided on the first connecting plate; the bottoms of a pair of lower supports (5) are each provided with a second connecting plate for connecting to a thrust chamber head or a turbine pump, the second connecting plate is an arc-shaped plate body, and a second threaded hole is provided on the second connecting plate.

6. A rocket engine gimbal according to claim 5, characterized in that: A through hole is provided at the connection position between the bottom of the lower support (5) and the second connecting plate.

7. The rocket engine gimbal according to claim 1, characterized in that: The bottoms of a pair of upper supports (1) are hinged to the first two opposite side walls of the gimbal ring (3) through a rotating shaft assembly, and the tops of a pair of lower supports (5) are hinged to the second two opposite side walls of the gimbal ring (3) through a rotating shaft assembly.

8. A rocket engine gimbal according to claim 7, characterized in that: The rotating shaft assembly includes a pair of shaft covers and a rotating shaft, wherein the pair of shaft covers are mounted on both ends of the rotating shaft in a one-to-one correspondence.

9. The rocket engine gimbal according to claim 1, characterized in that: The middle parts of a pair of lower supports (5) are connected via a plurality of lower support connecting plates (6).

10. The rocket engine gimbal according to claim 1, characterized in that: The gimbal ring (3) is a rectangular structure or a square structure, and a through hole is provided in the middle of the gimbal ring (3).

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