An embedded miniaturized attitude and orbit control thrust chamber head structure and its manufacturing method

Abstract

The present invention specifically relates to an internally embedded miniaturized attitude and orbit control thrust chamber head structure and its manufacturing method, addressing the problem that both existing welding and brazing methods of the thrust chamber head are difficult to achieve the miniaturized sealing connection requirements of the thrust chamber head. The internally embedded miniaturized attitude and orbit control thrust chamber head structure includes a flange, an injection plate, and a flexible graphite sealing ring; the flange is provided with an oxidizer chamber and a fuel chamber; an inserted grooving structure is provided between the flange and the injection plate, and a sealed cavity is formed between the flange and the injection plate; the flexible graphite sealing ring is provided within the inserted grooving structure to achieve sealing between the oxidizer chamber and the fuel chamber. This eliminates the need for a reserved welding process section for the attitude and orbit control thrust chamber head, resulting in a lightweight and compact structure and a simple and easy-to-operate process.

Description

Technical Field

[0001] The present invention specifically relates to an internally embedded miniaturized attitude and orbit control thrust chamber head structure and a manufacturing method thereof. Background Art

[0002] The function of the bipropellant attitude and orbit control thrust chamber head is to complete the transportation, flow distribution and injection of oxidizer and fuel. Since a bipropellant hypergolic propellant combination is used, the thrust chamber head structure must first ensure that the oxidizer and fuel are reliably sealed to prevent the two-component propellant from leaking inside the thrust chamber head and exploding in the cavity.

[0003] At present, there are two main sealing connection structures for the thrust chamber head: fusion welding and brazing. Fusion welding connection requires the cooperation of a propellant cover plate structure (or a structure with similar functions) to achieve its function. However, the thrust chamber head involves a large number of parts, and its head structure is relatively bulky. The welding compensation reinforcement required to reserve welding parts is high, making it difficult to achieve miniaturization. The brazing connection structure requires retaining a certain length of brazing section to ensure reliable connection of the brazing seam, and brazing material needs to be reserved to complete the coating open process structure. The miniaturization of this process structure is relatively difficult. At the same time, in order to ensure the quality of brazing, the processing tolerance accuracy of the welding mating surface is required to be high, resulting in greater processing difficulty.

[0004] In summary, both existing methods of welding and brazing of the thrust chamber head are difficult to achieve the demand for miniaturization of the sealing connection of the thrust chamber head. Summary of the Invention

[0005] The purpose of the present invention is to solve the problem that both the existing methods of fusion welding and brazing of the thrust chamber head are difficult to achieve the miniaturization requirement of the thrust chamber head sealing connection, and to provide an embedded miniaturized attitude and trajectory control thrust chamber head structure and a manufacturing method thereof.

[0006] In order to solve the above technical problems, the technical solution adopted by the present invention is:

[0007] An internally embedded miniaturized attitude and orbit control thrust chamber head structure, which is special in that it includes a flange, an injection plate and a flexible graphite sealing ring;

[0008] The flange is provided with an oxidant cavity and a fuel cavity; the flange is fixedly connected to the injection plate; an inserted falcon groove structure is provided between the flange and the injection plate, and an isolated oxidant cavity and fuel cavity are formed between the flange and the injection plate;

[0009] The insertable slot structure includes a slot and a slot that fit together.

[0010] The groove is an annular groove, which is provided at the end of the flange close to the injection plate and is located between the oxidant chamber and the fuel chamber; the flexible graphite sealing ring is provided in the groove;

[0011] The falcon is an annular protrusion, which is arranged on the injection disk and corresponds to the groove. It is used to extend into the groove and squeeze the flexible graphite sealing ring to achieve sealing between the oxidizer cavity and the fuel cavity.

[0012] Furthermore, a first sealing tooth is provided at the bottom of the groove;

[0013] The end portion of the flange corresponding to the groove is provided with a second sealing tooth.

[0014] Furthermore, the flange and the injection plate are welded with titanium alloy.

[0015] Furthermore, the attitude and orbit control thrust chamber head structure satisfies the following relationship:

[0016] 0.65L≤(L3-L1+L2)≤0.8L

[0017] Where, L is the thickness of the flexible graphite sealing ring;

[0018] L1 is the distance from the injection surface of the injection disk to the end face of the falcon;

[0019] L2 is the distance from the bottom surface of the flange groove to the butt joint surface of the fusion weld between the injection plate and the flange;

[0020] L3 is the distance from the injection surface of the injection disk to the butt joint surface of the fusion weld between the injection disk and the flange.

[0021] At the same time, the present invention also provides a method for manufacturing an embedded miniaturized attitude and orbit control thrust chamber head structure, which is special in that it includes the following steps:

[0022] Step 1: The flange and injection plate are machined and the flexible graphite sealing ring is molded;

[0023] Step 2: First place the flexible graphite sealing ring at the bottom of the flange groove, and then insert the injection plate into the flange groove;

[0024] Step 3: Use external tooling to press the flange and the injection plate to compress the flexible graphite sealing ring until the weld seam joint surfaces of the flange and the injection plate are aligned;

[0025] Step 4: After alignment, spot weld the weld seam joint surfaces of the flange and the injection plate and weld the fixed flange and the injection plate. Then weld the injection plate and the flange into one piece to complete the manufacture of the embedded miniaturized attitude and orbit control thrust chamber head structure.

[0026] Furthermore, in step 4, the spot welding is manual argon arc welding; and the welding is laser welding or electron beam welding.

[0027] Compared with the prior art, the technical solution of the present invention has the following beneficial effects:

[0028] (1) The embedded miniaturized attitude and orbit control thrust chamber head structure of the present invention has an inserted grooving structure between the flange and the injection disk, and a flexible graphite sealing ring is arranged inside the inserted grooving structure to achieve a sealed connection between the injection disk and the flange. The sealed connection has low requirements on the processing accuracy of the parts of the attitude and orbit control thrust chamber head, so that the attitude and orbit control thrust chamber head does not need to reserve a welding process section. It has the advantages of light and compact structure, simple process and easy operation, and solves the problem of miniaturization of the attitude and orbit control thrust chamber head structure.

[0029] (2) The embedded miniaturized attitude and orbit control thrust chamber head structure of the present invention consists of only three parts: a flange, an injection plate, and a flexible graphite sealing ring. Compared with the traditional fusion welding structure, it does not require redundant structures such as an injection cover plate and a welding compensation reinforcement height, thereby achieving miniaturization of the head structure.

[0030] (3) The embedded miniaturized attitude and orbit control thrust chamber head structure of the present invention utilizes the compression sealing performance of flexible graphite. By embedding the flexible graphite sealing ring into the inserted falcon groove structure of the flange plate and the injection plate, the sealing function of the head oxidizer chamber and the fuel cavity is realized. Compared with the traditional brazing structure, the processing accuracy requirements for parts are not high and no fine processing is required; at the same time, there is no need to reserve a brazing material coating process table, which is conducive to the miniaturization of the head structure.

[0031] (4) In the embedded miniaturized attitude and orbit control thrust chamber head structure of the present invention, sealing teeth are provided at corresponding positions of the injection plate and the flange plate inserted falcon groove to enhance the sealing performance of the flexible graphite sealing ring.

[0032] (5) The manufacturing method of the head structure of the embedded miniaturized attitude and orbit control thrust chamber of the present invention realizes its sealing function by assembling and extruding the flange and the injection disk to maintain the actual compression of the flexible graphite sealing ring within the range of 25% to 35%. The injection disk and the outer edge of the flange are connected by fusion welding to maintain the compression state of the flexible graphite sealing ring, thereby realizing a tighter seal between the oxidizer chamber and the fuel chamber and miniaturization of the head structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 Schematic diagram of the embedded miniaturized attitude and orbit control thrust chamber head structure in the present invention;

[0034] Figure 2 Schematic diagram of the three-dimensional structure of the flange in the embodiment of the embedded miniaturized attitude and orbit control thrust chamber head structure of the present invention;

[0035] Figure 3 This is a schematic diagram of the three-dimensional structure of the injector in the embodiment of the embedded miniaturized attitude and orbit control thrust chamber head structure of the present invention;

[0036] Figure 4 It is a structural schematic diagram of the flange upper groove and the first sealing tooth in an embodiment of the embedded miniaturized attitude and orbit control thrust chamber head structure of the present invention;

[0037] Figure 5 Schematic diagram of the structure of the upper and second sealing teeth of the injector in the embodiment of the embedded miniaturized attitude and orbit control thrust chamber head structure of the present invention;

[0038] Figure 6 This is a structural schematic diagram of the cooperation between the flange and the injector in an embodiment of the embedded miniaturized attitude and orbit control thrust chamber head structure and its manufacturing method of the present invention.

[0039] The accompanying drawings are denoted as follows:

[0040] 1-flange, 11-groove, 12-first sealing tooth, 2-injection disk, 21-falcon, 22-second sealing tooth, 3-flexible graphite sealing ring. DETAILED DESCRIPTION

[0041] like Figure 1 As shown, the internally embedded miniaturized attitude and orbit control thrust chamber head structure consists of a flange 1, an injector disc 2, and a flexible graphite sealing ring 3. The flange 1 is fixedly connected to the injector disc 2. An oxidizer inlet and a fuel inlet are provided on the two side walls of the flange 1, respectively. The flange 1 is internally provided with an oxidizer chamber and a fuel chamber communicating with the oxidizer inlet and the fuel inlet, respectively. An inserted grove structure is provided between the flange 1 and the injector disc 2, forming an isolated oxidizer chamber and a fuel chamber. The flexible graphite sealing ring 3 is provided within the inserted grove structure to achieve a seal between the oxidizer chamber and the fuel chamber.

[0042] like Figure 2 、 Figure 3 As shown, the inserted slot structure comprises a cooperating slot 11 and protrusion 21. Slot 11 is located at the end of the flange 1 near the injection plate 2 and is a recessed annular groove. Protrusion 21 is located on the end surface of the injection plate 2 and corresponds to slot 11. Protrusion 21 is a protruding annular protrusion that extends into slot 11 and compresses the flexible graphite sealing ring 3, achieving a seal between the oxidizer and fuel chambers. An annular step is provided on the outer wall of the flange 1, and its surface is welded to the outer end surface of the injection plate 2. The flange 1 and the injection plate 2 are welded together using titanium alloy.

[0043] Preferably, the sealing performance of the compressed flexible graphite is utilized to embed the flexible graphite sealing ring 3 in the inserted falcon groove structure provided by the flange 1 and the injection disk 2, and the flexible graphite sealing ring 3 is squeezed and compressed by the flange 1 and the injection disk 2 during the assembly process. The flexible graphite sealing ring 3 is maintained in a compressed state by fusion welding the outermost circles of the flange 1 and the injection disk 2 to achieve sealing between the head oxidizer chamber and the fuel chamber.

[0044] like Figure 4 、 Figure 5 As shown, a first sealing tooth 12 is provided at the bottom of the groove 11; a second sealing tooth 22 is provided at the end of the falcon 21 corresponding to the groove 11. The first sealing tooth 12 and the second sealing tooth 22 are both annular triangular grooves. When the flexible graphite sealing ring 3 is squeezed and compressed, the first sealing tooth 12 and the second sealing tooth 22 are filled with flexible graphite, thereby improving the sealing performance of the flexible graphite sealing ring 3.

[0045] like Figure 6 As shown, in order to obtain good sealing effect and performance, the actual processing dimensions of the groove 11 depth of the flange 1, the height of the injection plate 21 and the thickness of the flexible graphite sealing ring 3 must satisfy the following relationship:

[0046] 0.65L≤(L3-L1+L2)≤0.8L

[0047] Wherein, L is the thickness of the flexible graphite sealing ring 3;

[0048] L1 is the distance from the injection surface of the injection disk 2 to the end surface of the falcon 21;

[0049] L2 is the distance from the bottom surface of the groove 11 of the flange 1 to the butt joint surface of the fusion weld between the injection plate 2 and the flange 1;

[0050] L3 is the distance from the injection surface of the injection plate 2 to the weld joint surface between the injection plate 2 and the flange 1.

[0051] At the same time, the present invention also provides a method for manufacturing an embedded miniaturized attitude and orbit control thrust chamber head structure, comprising the following steps:

[0052] Step 1: The flange 1 and the injection plate 2 are machined and formed, and the flexible graphite sealing ring 3 is molded;

[0053] Step 2: First, place the flexible graphite sealing ring 3 flatly at the bottom of the groove 11 of the flange 1, and then insert the dovetail 21 of the injection plate 2 into the groove 11 of the flange 1;

[0054] Step 3: Use external tooling to press the flange 1 and the injection plate 2 to compress the flexible graphite sealing ring 3 until the weld seam joint surfaces of the flange 1 and the injection plate 2 are aligned;

[0055] Step 4: After alignment, spot welding is performed on the weld seam joint surfaces of flange 1 and injection disk 2 by manual argon arc welding, and then flange 1 and injection disk 2 are fixed by laser welding or electron beam welding. Then, injection disk 2 and flange 1 are welded into one body to complete the manufacture of the embedded miniaturized attitude and orbit control thrust chamber head structure.

[0056] Preferably, in step 4, an external tool is used to compress the flange 1 and the injection disc 2 to compress the flexible graphite sealing ring 3 until the welding parts of the flange 1 and the injection disc 2 are aligned. The compression process requires that the flexible graphite sealing ring 3 is compressed and formed in one step, and the flexible graphite sealing ring 3 is not allowed to loosen. After compression, the flange 1 and the injection disc 2 are fixed at the butt joint of the fusion weld by manual argon arc spot welding, and then the injection disc 2 and the flange 1 are welded into one body to form a head by fusion welding. The fusion welding method can be laser welding or electron beam welding.

Claims

1. An internally embedded miniaturized attitude and orbit control thrust chamber head structure, characterized by: It includes a flange (1), an injection plate (2) and a flexible graphite sealing ring (3); An oxidant cavity and a fuel cavity are provided on the flange (1); the flange (1) is fixedly connected to the injection disk (2); an inserted falcon groove structure is provided between the flange (1) and the injection disk (2), and an isolated oxidant cavity and a fuel cavity are formed between the flange (1) and the injection disk (2); The inserted falcon slot structure comprises a slot (11) and a falcon (21) that cooperate with each other; The groove (11) is an annular groove, which is arranged at the end of the flange (1) close to the injection plate (2) and is located between the oxidant chamber and the fuel chamber; the flexible graphite sealing ring (3) is arranged in the groove (11); The falcon (21) is an annular protrusion, which is arranged on the injection disk (2) and corresponds to the groove (11), and is used to extend into the groove (11) and squeeze the flexible graphite sealing ring (3) to achieve sealing between the oxidant cavity and the fuel cavity; The attitude and orbit control thrust chamber head structure satisfies the following relationship: 0.65L≤(L3-L1+L2)≤0.8L Where, L is the thickness of the flexible graphite sealing ring (3); L1 is the distance from the injection surface of the injection disk (2) to the end surface of the falcon (21); L2 is the distance from the bottom surface of the groove (11) of the flange (1) to the butt joint surface of the fusion weld between the injection plate (2) and the flange (1); L3 is the distance from the injection surface of the injection disc (2) to the butt joint surface of the fusion weld between the injection disc (2) and the flange (1).

2. The embedded miniaturized attitude and orbit control thrust chamber head structure according to claim 1 is characterized by: A first sealing tooth (12) is provided at the bottom of the groove (11); The end of the falcon (21) corresponding to the groove (11) is provided with a second sealing tooth (22).

3. The embedded miniaturized attitude and orbit control thrust chamber head structure according to claim 1 is characterized by: The flange (1) and the injection plate (2) are welded using titanium alloy.

4. A method for manufacturing the embedded miniaturized attitude and orbit control thrust chamber head structure according to any one of claims 1 to 3, characterized in that: The following steps are involved: Step 1: The flange (1) and the injection plate (2) are formed by mechanical processing, and the flexible graphite sealing ring (3) is formed by mold processing; Step 2: First, place the flexible graphite sealing ring (3) at the bottom of the groove (11) of the flange (1), and then insert the falcon (21) of the injection plate (2) into the groove (11) of the flange (1); Step 3: Use external tooling to press the flange (1) and the injection plate (2) to compress the flexible graphite sealing ring (3) until the weld seam butt surfaces of the flange (1) and the injection plate (2) are aligned; Step 4: After alignment, spot welding is performed on the weld seam butt surfaces of the flange (1) and the injection plate (2), and the flange (1) and the injection plate (2) are fixed by welding, and then the injection plate (2) and the flange (1) are welded into one piece, thereby completing the manufacture of the internally embedded miniaturized attitude and orbit control thrust chamber head structure.

5. The method for manufacturing an embedded miniaturized attitude and orbit control thrust chamber head structure according to claim 4, characterized in that: In step 4, the spot welding is manual argon arc welding; and the welding is laser welding or electron beam welding.

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