Tooling for solid rocket motor zero position detection and adjustment and its use method

Abstract

The present invention relates to a tool for zero-position detection and adjustment of solid rocket engines, comprising a reference ring suitable for placing a rocket engine and a plurality of reference rods whose length direction is parallel to the axis of the reference ring, and the reference rods are spaced apart in sequence along the circumference of the reference ring; the tool is also provided with two sets of end positioning mechanisms for cooperating with the reference rods to respectively position the two ends of the rocket engine, and at least one zero-position pin for cooperating with the zero-position pin hole on the rocket engine, and a strip-shaped limiting groove for limiting the zero-position pin is provided on the reference rod at the corresponding position. In addition, the invention relates to a method for using the tool. The above-mentioned tool has the functions of qualitative detection, quantitative detection and zero-position adjustment of the zero-position relationship of the rocket engine interface, and can better meet various application requirements; the tool has a simple structure, and can realize zero-position detection and zero-position adjustment of large-sized engines through relatively small-sized parts, and has good application effect and economic benefits.

Description

Technical Field

[0001] The present invention belongs to the field of rocket engines, and in particular relates to a tool for zero-position detection and adjustment of a solid rocket engine and a method for using the tool. Background Art

[0002] In a missile design with a normal layout, the rudders are typically mounted at the rear of the engine, and the wings at the front. The zero-position accuracy of the engine's front and rear interfaces affects the installation accuracy of the missile's wings and rudders, and thus the accuracy of the missile's guidance and control. Therefore, high requirements are generally placed on the zero-position accuracy of the engine's front and rear interfaces. Currently, three-dimensional coordinate measuring machines (CMMs) are commonly used to check the zero-position relationship of the front and rear interfaces during the structural component production phase. However, CMMs are expensive, require a strict testing environment, and are fixed measurement equipment, making them immovable. Furthermore, while this testing method is highly accurate, its single-test efficiency is low, making it unsuitable for testing mass-produced parts. Furthermore, the zero-position relationship of some engine interfaces is determined during final assembly, and using live equipment to test pyrotechnics at this stage poses certain safety risks. Summary of the Invention

[0003] The present invention relates to a tool for zero-position detection and adjustment of a solid rocket engine and a method for using the tool, which can at least solve some of the defects of the prior art.

[0004] The present invention relates to a tool for zero-position detection and adjustment of solid rocket engines, comprising a reference ring and a plurality of reference rods, wherein a rocket engine to be detected is suitable for being placed in the reference ring, and the reference rods are spaced apart in sequence along the circumference of the reference ring, and the reference rods are fixed on the outer wall of the reference ring and the length direction of the rods is parallel to the axial direction of the reference ring; the tool is also provided with two groups of end positioning mechanisms for cooperating with the reference rods to respectively position the two ends of the rocket engine, and at least one zero-position pin for cooperating with the zero-position pin hole on the rocket engine, and a first strip-shaped limiting groove is provided on the reference rod at the corresponding position, the length direction of the first strip-shaped limiting groove is parallel to the axial direction of the reference ring, and the groove width of the first strip-shaped limiting groove matches the pin diameter of the zero-position pin.

[0005] As one of the embodiments, the end positioning mechanism includes a plurality of positioning pins for cooperating with the positioning pin holes on the rocket engine, and a second strip-shaped limiting groove is provided on the reference rod at the corresponding position. The length direction of the second strip-shaped limiting groove is parallel to the axial direction of the reference ring, and the groove width of the second strip-shaped limiting groove matches the pin rod diameter of the positioning pin.

[0006] As one of the implementation modes, the pin rod of the zero position pin and the pin rod of the positioning pin have the same diameter.

[0007] As one of the implementation modes, the positioning pin hole is a threaded hole, and the positioning end of the positioning pin corresponds to a threaded section.

[0008] As one of the implementation modes, a plurality of through holes are provided on the reference ring, and the positioning pins on the corresponding sides sequentially pass through the corresponding second strip-shaped limiting grooves and the corresponding through holes and then extend into the ring cavity of the reference ring.

[0009] As one of the implementation modes, the tooling further includes a fixing ring, one end of each of the reference rods is fixedly connected to the reference ring, and the other end of each of the reference rods is fixedly connected to the fixing ring.

[0010] As one of the embodiments, the reference rod is connected to the reference ring via a plurality of mounting screws.

[0011] The present invention also relates to a method for using the above-mentioned tool, which is used to perform qualitative detection of the zero position relationship of the interface of the rocket engine, specifically comprising:

[0012] After assembling the tooling, place the reference end of the rocket engine to be tested into the reference ring, adjust the relative position between the reference end and the reference ring, and maintain a stable relative position between the reference end and the reference ring through the end positioning mechanism on the corresponding side;

[0013] At the reference end, determining whether the zero pin can be inserted from the corresponding first strip-shaped limiting groove into the zero pin hole on the corresponding side; if so, it indicates that the interface structure of the reference end of the rocket engine meets the requirements; otherwise, it does not meet the requirements;

[0014] At the other end of the rocket engine, determine whether the end positioning mechanism on the corresponding side can cooperate with the rocket engine and whether the zero-position pin can be inserted into the zero-position pin hole on the corresponding side from the corresponding first strip limit groove. If so, it indicates that the engine interface structure at this end meets the requirements, otherwise it does not.

[0015] The present invention also relates to a method for using the above-mentioned tool, which is used to quantitatively detect the zero position relationship of the interface of the rocket engine, wherein the reference rod is connected to the reference ring by a plurality of mounting screws, and the quantitative detection method specifically includes:

[0016] Using a mounting screw to preliminarily connect each of the reference rods to the reference ring to form a pre-inspection structure;

[0017] The reference end of the rocket engine to be tested is placed in the reference ring, the relative position between the reference end and the pre-test structure is adjusted, and the reference end is positioned and constrained by the end positioning mechanism on the corresponding side, and it is ensured that the zero pin can be inserted from the corresponding first strip-shaped limiting groove into the zero pin hole on the corresponding side;

[0018] Further adjusting the relative position between the rocket engine and the pre-inspection structure, and positioning and constraining the other end of the rocket engine by the end positioning mechanism on the other side, and ensuring that the zero position pin can be inserted from the corresponding first strip-shaped limiting groove into the zero position pin hole on the corresponding side;

[0019] The reference rods are fixedly connected to the reference rings respectively by the remaining mounting screws;

[0020] The rocket engine is taken out, and the positional relationship between each of the reference rods and the reference ring is detected using a measuring instrument to obtain the zero position deviation value of the interface structure at both ends of the rocket engine.

[0021] The present invention also relates to a method for using the above-mentioned tool, wherein the tool is used to adjust the zero position relationship of the interface of the rocket engine, wherein the zero position of the interface at at least one end of the rocket engine is adjustable, specifically comprising:

[0022] After assembling the tooling, place the reference end of the rocket engine to be tested into the reference ring, adjust the relative position between the reference end and the reference ring, and use the end positioning mechanism on the corresponding side to maintain a stable relative position between the reference end and the reference ring, and ensure that the zero pin can be inserted from the corresponding first strip-shaped limiting groove into the zero pin hole on the corresponding side;

[0023] At the zero-position adjustment end of the rocket engine, the position of the interface structure is adjusted to ensure that the end positioning mechanism on the corresponding side can cooperate with the rocket engine and that the zero-position pin can be inserted from the corresponding first strip-shaped limit groove into the zero-position pin hole on the corresponding side, and then the interface structure on this side is fixed.

[0024] The present invention has at least the following beneficial effects:

[0025] The tooling provided by the present invention utilizes a reference ring and multiple reference rods, along with an end-positioning mechanism and a zero-position pin. This tooling meets these requirements with its simple structure and ease of use, eliminating the need for oversized, overlong, or ultra-thin components that are difficult to manufacture. Zero-position detection and adjustment of large-scale engines can be achieved using relatively small components, resulting in excellent application and economic benefits. The tooling exhibits excellent maintainability and adjustability, with adjustable assembly positions between its components. Regular calibration using a three-dimensional coordinate measuring machine ensures consistent tooling accuracy. Furthermore, if parts wear out due to long-term use, they can simply be replaced and recalibrated, eliminating the need for complete remanufacturing. This significantly reduces manufacturing and maintenance costs.

[0026] The tooling provided by the present invention has the functions of qualitative detection, quantitative detection and zero-position adjustment of the zero-position relationship of the rocket engine interface. It can not only carry out qualitative measurement according to preset accuracy, but also cooperate with measuring equipment to realize quantitative detection of the engine zero-position deviation value. It can better meet various application requirements and can significantly reduce the detection and adjustment equipment required for rocket engine production and application.

[0027] The tooling provided by the present invention is a pure structural component and has good safety when conducting pyrotechnic device testing. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0029] Figure 1 A schematic structural diagram of a tooling provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0030] The following is a clear and complete description of the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts are within the scope of protection of the present invention.

[0031] like Figure 1 An embodiment of the present invention provides a tool for zero-position detection and adjustment of a solid rocket engine, comprising a reference ring 11 and a plurality of reference rods 12, wherein a rocket engine 2 to be detected is suitable for being placed in the reference ring 11, and each of the reference rods 12 is spaced apart along the circumference of the reference ring 11, and each of the reference rods 12 is fixed to the outer wall of the reference ring 11, and the length direction of the rod is parallel to the axial direction of the reference ring 11; the tool is further provided with two sets of end positioning mechanisms for cooperating with each of the reference rods 12 to respectively position the two ends of the rocket engine 2, and at least one zero-position pin 14 for cooperating with the zero-position pin hole on the rocket engine 2, and a first strip-shaped limiting groove is provided on the reference rod 12 at the corresponding position, the length direction of the first strip-shaped limiting groove being parallel to the axial direction of the reference ring 11, and the groove width of the first strip-shaped limiting groove matches the pin diameter of the zero-position pin 14.

[0032] In one embodiment, the reference ring 11 is adapted to the front end outer wall of the rocket engine 2, that is, the inner ring diameter of the reference ring 11 is adapted to the front end outer wall diameter of the rocket engine 2. Preferably, there is a clearance fit between the rocket engine 2 and the reference ring 11, and the rocket engine 2 and the reference ring 11 can rotate relative to each other, but radial relative movement between the two is avoided as much as possible.

[0033] In one embodiment, a boss is provided on the inner wall of the reference ring 11. When the rocket engine 2 is placed in, it is placed on the boss, which can improve the positioning accuracy between the rocket engine 2 and the reference ring 11 in the axial direction.

[0034] In one embodiment, the above-mentioned reference rod 12 is in the shape of a plate, and a plurality of notches are formed on the outer wall of the reference ring 11. Each reference rod 12 is arranged on each notch in a one-to-one correspondence. The plate surface of the reference rod 12 is fitted and fixed to the plane of the notch, which can improve the installation structure stability of the reference rod 12 and the relative position accuracy between it and the reference ring 11, for example, ensuring the verticality of the reference rod 12 relative to the reference ring 11 (or ensuring the parallelism of the reference rod 12 relative to the axis of the reference ring 11).

[0035] Preferably, if Figure 1 The reference rod 12 is connected to the reference ring 11 via a plurality of mounting screws 15, which ensures a reliable connection between the reference rod 12 and the reference ring 11. In one embodiment, each mounting screw 15 includes a pre-positioning screw 151 and a plurality of fixing screws 152. The pre-positioning screw 151 enables pre-fixation between the reference rod 12 and the reference ring 11. At this time, the position between the reference rod 12 and the reference ring 11 is basically fixed, but the position of the reference rod 12 relative to the reference ring 11 can still be adjusted; the fixing screws 152 are preferably distributed around the pre-positioning screw 151, which can achieve a reliable fixed connection between the reference rod 12 and the reference ring 11, so that the position between the reference rod 12 and the reference ring 11 remains unchanged.

[0036] Preferably, the number of the reference rods 12 is not less than 3, and the reference rods 12 are preferably evenly distributed in a ring shape along the outer wall of the reference ring 11; specifically, the number and distribution of the reference rods 12 can be determined according to the actual rocket engine interface form.

[0037] In one embodiment, the end positioning mechanism includes a plurality of positioning pins 13 for engaging with positioning pin holes on the rocket engine 2. A second strip-shaped limiting groove is provided on the reference rod 12 at the corresponding position. The length direction of the second strip-shaped limiting groove is parallel to the axial direction of the reference ring 11, and the groove width of the second strip-shaped limiting groove matches the pin diameter of the positioning pin 13. The end positioning mechanism can fix the relative position between the reference rod 12 and the rocket engine 2, and thus the relative position between the corresponding tooling structure and the rocket engine 2, thereby improving the accuracy and reliability of the detection / adjustment operation.

[0038] In one embodiment, the pin rod of the zero position pin 14 has the same diameter as the pin rod of the positioning pin 13, and the specifications of the first strip limit groove and the second strip limit groove are the same. Correspondingly, a strip limit groove is provided at both ends of the reference rod 12. In this way, any reference rod 12 can be used to cooperate with the positioning pin 13 and the zero position pin 14, which can correspondingly improve the flexibility, convenience and reliability of the use of the above-mentioned tooling, and improve the efficiency of detection / adjustment of the rocket engine 2.

[0039] Regarding the above-mentioned "the width of the first strip limit groove matches the pin rod diameter of the zero position pin 14" and "the width of the second strip limit groove matches the pin rod diameter of the positioning pin 13", it is preferred that there is a clearance fit relationship between the zero position pin 14 and the first strip limit groove, and a clearance fit relationship between the positioning pin 13 and the second strip limit groove. It can generally be regarded as that the pin can only move along the slot length direction of the strip limit groove, which can improve the accuracy of the detection / adjustment operation.

[0040] Among them, the above-mentioned first strip-shaped limiting groove and the second strip-shaped limiting groove can be a waist-shaped groove or a U-shaped groove; in this embodiment, the U-shaped groove structure is adopted to facilitate the installation of pins and other operations, wherein the notch of the U-shaped groove is preferably facing the other end of the corresponding reference rod 12.

[0041] In one embodiment, the positioning pin hole is a threaded hole, and the positioning end of the positioning pin 13 corresponds to a threaded section. The two are matched in a threaded connection manner, which can effectively ensure the positioning accuracy of the rocket engine 2 and ensure the relative position stability between the rocket engine 2 and the tooling after positioning.

[0042] In one embodiment, the positioning end of the zero position pin 14 is a polished rod section, and the zero position pin hole is a polished hole, which facilitates the insertion and removal of the zero position pin 14 and can improve the convenience and efficiency of the detection / adjustment operation.

[0043] Among them, the zero-position pin hole and the positioning pin hole on the rocket engine 2 can be the interface structure of the rocket engine 2 itself. For example, the positioning pin hole at the front end of the rocket engine 2 is used to connect with the wing compartment, and the positioning pin hole at the rear end is used to connect with the servo compartment; it can also be a pin hole set separately for detection / adjustment operations.

[0044] Preferably, if Figure 1 The reference ring 11 is provided with a plurality of through-holes. The positioning pin 13 on the corresponding side sequentially passes through the corresponding second strip-shaped limiting groove and the corresponding through-hole and then extends into the annular cavity of the reference ring 11. That is, the positioning pin 13 on this side must pass through the second strip-shaped limiting groove on the reference rod 12 and the through-hole on the reference ring 11 before being inserted into the positioning pin hole of the rocket engine 2. In this way, the reference ring 11 and the reference rod 12 can be used as a reference to position the rocket engine 2, which can further improve the positioning accuracy and the accuracy of the detection / adjustment operation. Among them, the aperture of the through-hole matches the pin diameter of the positioning pin 13, for example, there is a clearance fit between the pin and the through-hole. Similarly, the zero pin 14 on this side is also preferably passed through the first strip-shaped limiting groove on the reference rod 12 and the through-hole on the reference ring 11 before being inserted into the zero pin hole of the rocket engine 2. The number of through-holes needs to be configured accordingly, for example, the same as the number of reference rods 12.

[0045] Further optimize the above tooling, such as Figure 1 The tooling also includes a fixing ring 16. One end of each reference rod 12 is fixedly connected to the reference ring 11, and the other end of each reference rod 12 is fixedly connected to the fixing ring 16. By providing the fixing ring 16, the accuracy and stability of the position of each reference rod 12 can be further improved, thereby improving the reliability of the detection / adjustment operation.

[0046] The embodiment of the present invention further provides a method for using the above-mentioned tool, including at least one of the following specific methods of use:

[0047] (1) The tooling is used to perform qualitative detection of the zero position relationship of the interface of the rocket engine 2, specifically including:

[0048] After assembling the tooling, place the reference end of the rocket engine 2 to be tested into the reference ring 11, adjust the relative position between the reference end and the reference ring 11, and keep the relative position between the reference end and the reference ring 11 stable through the end positioning mechanism on the corresponding side;

[0049] At the reference end, determine whether the zero pin 14 can be inserted from the corresponding first strip-shaped limiting groove into the zero pin hole on the corresponding side. If so, it indicates that the interface structure of the reference end of the rocket engine 2 meets the requirements, otherwise it does not meet the requirements.

[0050] At the other end of the rocket engine 2, determine whether the end positioning mechanism on the corresponding side can cooperate with the rocket engine 2 and whether the zero-position pin 14 can be inserted into the zero-position pin hole on the corresponding side from the corresponding first strip limit groove. If so, it indicates that the engine interface structure at this end meets the requirements, otherwise it does not.

[0051] Among them, for the assembly of the tooling, preferably, the reference rod 12 is first connected to the reference ring 11 using the pre-positioning screw 151, and the verticality of the reference rod 12 relative to the reference ring 11 is detected using measuring equipment. When the verticality does not meet the requirements, the position of the reference rod 12 is fine-tuned until the verticality meets the requirements, that is, the relative position of the reference rod 12 and the reference ring 11 meets the requirements; then the reference rod 12 is fixedly connected to the reference ring 11 using the fixing screw 152.

[0052] (2) The tooling is used to quantitatively detect the zero position relationship of the interface of the rocket engine 2, wherein the reference rod 12 is connected to the reference ring 11 by a plurality of mounting screws 15. The quantitative detection method specifically includes:

[0053] A mounting screw 15 (i.e., the aforementioned pre-positioning screw 151) is used to preliminarily connect each of the reference rods 12 to the reference ring 11 to form a pre-inspection structure;

[0054] Place the reference end of the rocket engine 2 to be tested into the reference ring 11, adjust the relative position between the reference end and the pre-test structure, and constrain the reference end by the end positioning mechanism on the corresponding side, and ensure that the zero pin 14 can be inserted from the corresponding first strip-shaped limiting groove into the zero pin hole on the corresponding side;

[0055] Further adjust the relative position between the rocket engine 2 and the pre-inspection structure, and position and constrain the other end of the rocket engine 2 through the end positioning mechanism on the other side, and ensure that the zero position pin 14 can be inserted from the corresponding first strip-shaped limiting groove into the zero position pin hole on the corresponding side;

[0056] Each of the reference rods 12 is fixedly connected to the reference ring 11 by the remaining mounting screws 15 (i.e., the aforementioned fixing screws 152);

[0057] The rocket engine 2 is taken out, and the positional relationship between each of the reference rods 12 and the reference ring 11 is detected using a measuring instrument to obtain the zero position deviation value of the interface structure at both ends of the rocket engine 2.

[0058] (3) The tooling is used to adjust the zero position relationship of the interface of the rocket engine 2, wherein the zero position of the interface at at least one end of the rocket engine 2 is adjustable, specifically including:

[0059] After assembling the tooling, place the reference end of the rocket engine 2 to be tested into the reference ring 11, adjust the relative position between the reference end and the reference ring 11, and use the end positioning mechanism on the corresponding side to keep the relative position of the reference end and the reference ring 11 stable, and ensure that the zero pin 14 can be inserted from the corresponding first strip-shaped limiting groove into the zero pin hole on the corresponding side;

[0060] At the zero-position adjustment end of the rocket engine 2, adjust the position of the interface structure to ensure that the end positioning mechanism on the corresponding side can cooperate with the rocket engine 2 and that the zero-position pin 14 can be inserted into the zero-position pin hole on the corresponding side from the corresponding first strip-shaped limit groove, and then fix the interface structure on this side.

[0061] Among them, for the adjustment of the zero position of the interface of the rocket engine 2, a connecting ring can be used to achieve zero position adjustment. The connecting ring can be rotatably mounted on the engine 2, and a zero position pin hole and a positioning pin hole can be set on the connecting ring.

[0062] The measuring instrument may be a three-coordinate measuring machine.

[0063] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A tool for zero-position detection and adjustment of solid rocket motors, characterized by: The tool comprises a reference ring and a plurality of reference rods, wherein the rocket engine to be tested is suitable for being placed in the reference ring, and the reference rods are spaced apart in sequence along the circumference of the reference ring, and are fixed to the outer wall of the reference ring, with the length direction of the rods parallel to the axial direction of the reference ring; the tool is further provided with two sets of end positioning mechanisms for cooperating with the reference rods to respectively position the two ends of the rocket engine, and at least one zero position pin for cooperating with the zero position pin hole on the rocket engine, and a first strip-shaped limiting groove is provided on the reference rod at the corresponding position, the length direction of the first strip-shaped limiting groove being parallel to the axial direction of the reference ring, and the groove width of the first strip-shaped limiting groove matches the pin diameter of the zero position pin; The reference rod is connected to the reference ring by a plurality of mounting screws, each mounting screw including a pre-positioning screw and a plurality of fixing screws. The pre-positioning screw is used to realize the pre-fixation between the reference rod and the reference ring. The pre-fixation between the reference rod and the reference ring is specifically that the position between the reference rod and the reference ring is basically fixed, but the position of the reference rod can still be adjusted relative to the reference ring.

2. The tool for zero-position detection and adjustment of a solid rocket motor according to claim 1, characterized in that: The end positioning mechanism includes a plurality of positioning pins for cooperating with the positioning pin holes on the rocket engine, and a second strip-shaped limiting groove is provided on the reference rod at the corresponding position. The length direction of the second strip-shaped limiting groove is parallel to the axial direction of the reference ring, and the groove width of the second strip-shaped limiting groove matches the pin rod diameter of the positioning pin.

3. The tool for zero-position detection and adjustment of a solid rocket motor according to claim 2, characterized in that: The pin rod of the zero position pin has the same diameter as that of the positioning pin.

4. The tool for zero-position detection and adjustment of a solid rocket motor according to claim 2, characterized in that: The positioning pin hole is a threaded hole, and the positioning end of the positioning pin corresponds to a threaded section.

5. The tool for zero-position detection and adjustment of a solid rocket motor according to claim 2, characterized in that: The reference ring is provided with a plurality of through holes, and the positioning pins on the corresponding sides sequentially pass through the corresponding second strip-shaped limiting grooves and the corresponding through holes and then extend into the ring cavity of the reference ring.

6. The tool for zero-position detection and adjustment of a solid rocket motor according to claim 1, characterized in that: It also includes a fixing ring, one end of each reference rod is fixedly connected to the reference ring, and the other end of each reference rod is fixedly connected to the fixing ring.

7. The method for using the tool according to any one of claims 1 to 6, characterized in that: The tool is used to perform qualitative detection of the zero position relationship of the interface of the rocket engine, specifically including: After assembling the tooling, place the reference end of the rocket engine to be tested into the reference ring, adjust the relative position between the reference end and the reference ring, and maintain a stable relative position between the reference end and the reference ring through the end positioning mechanism on the corresponding side; At the reference end, determining whether the zero pin can be inserted from the corresponding first strip-shaped limiting groove into the zero pin hole on the corresponding side; if so, it indicates that the interface structure of the reference end of the rocket engine meets the requirements; otherwise, it does not meet the requirements; At the other end of the rocket engine, determine whether the end positioning mechanism on the corresponding side can cooperate with the rocket engine and whether the zero-position pin can be inserted into the zero-position pin hole on the corresponding side from the corresponding first strip limit groove. If so, it indicates that the engine interface structure at this end meets the requirements, otherwise it does not.

8. The method for using the tool according to any one of claims 1 to 6, characterized in that: The tool is used to quantitatively detect the zero position relationship of the interface of the rocket engine, wherein the reference rod is connected to the reference ring by a plurality of mounting screws, and the quantitative detection method specifically includes: Using pre-positioning screws to preliminarily connect each of the reference rods to the reference ring to form a pre-inspection structure; The reference end of the rocket engine to be tested is placed in the reference ring, the relative position between the reference end and the pre-test structure is adjusted, and the reference end is positioned and constrained by the end positioning mechanism on the corresponding side, and it is ensured that the zero pin can be inserted from the corresponding first strip-shaped limiting groove into the zero pin hole on the corresponding side; Further adjusting the relative position between the rocket engine and the pre-inspection structure, and positioning and constraining the other end of the rocket engine by the end positioning mechanism on the other side, and ensuring that the zero position pin can be inserted from the corresponding first strip-shaped limiting groove into the zero position pin hole on the corresponding side; The reference rods are fixedly connected to the reference rings by fixing screws; The rocket engine is taken out, and the positional relationship between each of the reference rods and the reference ring is detected using a measuring instrument to obtain the zero position deviation value of the interface structure at both ends of the rocket engine.

9. The method for using the tool according to any one of claims 1 to 6, characterized in that: The tool is used to adjust the zero position relationship of the interface of the rocket engine, wherein the zero position of the interface at at least one end of the rocket engine is adjustable, specifically including: After assembling the tooling, place the reference end of the rocket engine to be tested into the reference ring, adjust the relative position between the reference end and the reference ring, and use the end positioning mechanism on the corresponding side to maintain a stable relative position between the reference end and the reference ring, and ensure that the zero pin can be inserted from the corresponding first strip-shaped limiting groove into the zero pin hole on the corresponding side; At the zero-position adjustment end of the rocket engine, the position of the interface structure is adjusted to ensure that the end positioning mechanism on the corresponding side can cooperate with the rocket engine and that the zero-position pin can be inserted from the corresponding first strip-shaped limit groove into the zero-position pin hole on the corresponding side, and then the interface structure on this side is fixed.

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