High-thrust rocket engine full-system test run rack and application thereof

Abstract

The invention relates to a high-thrust rocket engine full-system test run frame and application thereof. The test run rack is used for hot test run of a rocket engine, can bear large thrust, and ensures the stability in the test process and the accuracy of data acquisition. The test run frame comprises a foundation embedded part, a square frame beam supporting structure, a C-shaped support, a movable frame and a pre-tightening force device. The foundation embedded part comprises a plurality of groups of anchor plates, straining beams and connecting bases, the number of the connecting bases is equal to that of the anchor plates, one group of anchor plates and the corresponding group of connecting bases connected to the anchor plates form an anchor pile, the adjacent anchor piles are sequentially connected through the straining beams to form the U-shaped foundation embedded part, and enough pulling resistance can be provided; the square frame beam supporting structure supports the whole test run rack through the stand columns and the force bearing beams, and the detachable stand columns can accurately adjust the height of an engine. And the C-shaped bracket is used for fixing and calibrating a movable frame part of the engine. The structure can bear the axial thrust of 12500 kN, and is stable in structure and easy to disassemble and replace.

Description

Technical Field

[0001] The present invention relates to the technical field of large-scale heavy-load rocket engine test bench structure, and in particular to a large-thrust rocket engine full-system test bench and its application. The device is suitable for testing large-scale, heavy-duty aerospace engines (such as rocket engines) and other large-thrust engines. Background Art

[0002] In recent years, with the rapid development of aerospace technology, the performance and reliability requirements of rocket engines, as an important power source for spacecraft, have been continuously improved. Especially in the research and development of large-thrust rocket engines, testing is a key link to ensure that the performance indicators of the engine meet the standards. Therefore, the engine test bench system has become one of the core equipment in the research and development process.

[0003] During the design and use of traditional rocket engine test benches, they often only test a single function or part of the system, which makes it difficult to cover the full system operation of the entire engine. In actual applications, the thrust, vibration, thermal load and other factors of the rocket engine interact with each other, and the need for comprehensive and integrated testing is becoming increasingly important.

[0004] The existing test frame system has some shortcomings, such as unreasonable structural design, small thrust measurement range, and difficulty in effectively simulating the working state of the whole system, which cannot meet the needs of full system testing of large thrust rocket engines. Therefore, it is of great significance to develop a new test frame that can adapt to complex testing requirements and realize full system testing of rocket engines.

[0005] This test bench should be able to ensure the working stability of the engine at different thrust levels, so as to comprehensively collect data such as thrust, pressure, temperature, vibration, etc., to ensure that the various performance indicators of the engine meet the design requirements. This will provide strong support for the reliability verification and further optimization of rocket engines. Summary of the invention

[0006] Aiming at the demand for full-system test of rocket engines, the present invention provides a full-system test frame device for a large-thrust rocket engine, which can adapt to complex working conditions and can measure large-thrust engines.

[0007] In order to solve the above technical problems, the present invention provides a large-thrust rocket engine full-system test stand device, comprising: The foundation embedded part includes a plurality of anchor plates, tension beams and connection bases with the same number of anchor plates. A group of anchor plates and the corresponding group of connection bases connected thereto constitute an anchor pile. Adjacent anchor piles are sequentially connected by tension beams to form a U-shaped foundation embedded part, which can provide pull-out resistance by fixing to the concrete foundation. A square frame beam support structure, including a column, a load-bearing beam, an upper cross beam, a diagonal brace and a lower cross beam, forming a square frame beam structure with a first accommodation space, used to bear the axial load during engine test; and The C-shaped bracket is connected to the first accommodation space and includes at least two C-shaped columns with gaps, a C-shaped column beam and a support ring. At least two C-shaped columns can enclose a second accommodation space, can bear the load in the test run, and are used to fix the dynamic frame and the calibration system.

[0008] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, there are 4 columns, load-bearing beams, upper crossbeams, diagonal braces and lower crossbeams, the 4 columns are distributed at the four corners of the rectangle, the 4 lower crossbeams are connected in sequence and form a lower rectangle, the four corners of the lower rectangle are respectively connected to the middle and upper parts of the 4 columns through the 4 load-bearing beams, the tops of the 4 columns are formed into an upper rectangle through the 4 upper crossbeams, the tops of the 4 columns are connected to the side close to the lower rectangle with a diagonal brace, the other end of the diagonal brace is connected to the corresponding corner of the lower rectangle, the load-bearing beams, the diagonal braces and the middle and upper parts of the columns form a triangular frame to provide tension to the lower rectangle, and the columns are formed by at least two sections of base columns connected end to end.

[0009] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, the load-bearing beams, diagonal braces and the upper and middle parts of the columns form an isosceles right-angled triangle frame, and the diagonal braces form an angle of 45° with the horizontal plane.

[0010] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, the dynamic frame is connected to the C-shaped bracket through a constraint and limit device, the constraint and limit device includes a spring steel bottom plate, an outer support plate, an inner support plate and a support seat, a third accommodating space is opened on the support seat, one side of the outer support plate is connected to the support seat, and the other side is connected to the inner notch of the C-shaped column, one side of the inner support plate is located in the third accommodating space and connected to the spring steel bottom plate, and the other side is connected to the dynamic frame, and there is a gap between the inner support plate and the bottom of the third accommodating space to provide a clearance space for the vertical deformation of the spring steel bottom plate; the dynamic frame includes a load-bearing ring beam, a main load-bearing bracket and an annular transition frame, and the load-bearing ring beam and the annular transition frame are respectively connected to the top and bottom of the main load-bearing bracket.

[0011] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, the lower parts of adjacent C-type columns are connected by C-type column cross beams, and the top is connected to a support ring to support the dynamic frame.

[0012] Furthermore, in the above-mentioned large-thrust rocket engine full-system test bench, two support rods are cross-connected in the middle of the support ring through the center of the circle, and the two support rods coincide with the connecting line of the tops of two opposite C-shaped columns.

[0013] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, the C-type column is connected to the preload device, the second accommodating space is connected to the dynamic frame, and the preload device is used to provide preload to the dynamic frame; a force sensor is connected between the notch of the C-type column and the top surface of the dynamic frame, and there is a gap between the force sensor and the C-type column or the top surface of the dynamic frame.

[0014] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, a first slot structure is provided on the side of the C-shaped column away from the notch, and a connecting piece with a second slot structure is connected to the inner side of the overlapping part of the lower cross beam and the load-bearing beam, the first slot structure and the second slot structure are matched in a concave-convex manner, and the C-shaped column is detachably connected to the square frame beam support structure through the first slot structure and the second slot structure.

[0015] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, each group of anchor plates adopts a partition structure connected in series up and down, and is fixed in the concrete foundation with reinforcing ribs and screws to improve the pull-out resistance.

[0016] Furthermore, in the above-mentioned high-thrust rocket engine full-system test bench, the preload device includes a pull rod, a support, a lever, a servo motor, a bevel gear, a weight rod and a weight.

[0017] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, the dynamic frame includes a load-bearing ring beam and a constraint and limit device, the dynamic frame includes a load-bearing ring beam and a constraint and limit device, the load-bearing ring beam includes a main load-bearing bracket and an annular transition frame, and the constraint and limit device includes a spring steel bottom plate, an outer support plate and an inner support plate.

[0018] Furthermore, in the above-mentioned high-thrust rocket engine full-system test bench, the preload device includes a pull rod, a support, a lever, a servo motor, a bevel gear, a weight rod and a weight.

[0019] Furthermore, the above-mentioned large-thrust rocket engine full-system test bench is detachable because the columns are composed of at least two base columns connected end to end. The full-system test bench can lift the engine to different installation heights by adjusting the height of the columns, providing sufficient test space, and is therefore suitable for engines of different models.

[0020] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, the column is formed by two sections of base columns connected end to end, and the two sections are connected by flanges, which can also facilitate transportation and on-site installation.

[0021] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, there are four C-type columns, the four C-type columns are 90 degrees to each other, the four C-type column cross beams connect adjacent C-type columns, and the support ring is on the top of the C-type column, connecting the four C-type columns and the preload device above.

[0022] The lower cross beam and the upper cross beam are connected to adjacent load-bearing beams to control the deformation of the load-bearing beams.

[0023] The test frame limits the position and transfers the load to the moving frame part through the central C-shaped bracket.

[0024] The C-shaped column as a whole adopts a box-type structure, which can not only accommodate components such as a moving frame and a sensor, but also effectively bear the thrust load in the vertical direction.

[0025] A large-thrust rocket engine full-system test frame described in any of the above items is used for sub-stage test or single-machine test. The maximum axial bearing capacity of the test frame is 12,500 kN, and the dynamic load coefficient is 2.5. It can meet the hot test requirements of different types of rocket engines and has the function of switching between sub-stage test and single-machine test. The entire full-system test frame can be used for single-machine test. The C-shaped bracket and internal related structures are removed, and only the external square frame beam support structure is retained. The sub-stage is connected to the square frame beam support structure through a ring connector, and the sub-stage test can be carried out.

[0026] Compared with the prior art, the present invention has the following beneficial effects: Compared with traditional rocket engine test frames, this test frame is modular in design, and key components such as columns and C-shaped brackets can be removed and replaced, which is convenient for maintenance and subsequent upgrades; the test frame can bear a maximum axial load of 12,500 kN, and the dynamic load coefficient is 2.5, ensuring structural stability under various thrust conditions; the constraint and limit device of the C-shaped bracket can have an axial displacement of 3-5mm due to the elasticity of the spring steel base plate, which can adjust the thrust direction and ensure the accuracy of the engine performance test.

[0027] The C-shaped column is detachably connected to the square frame beam support structure through the first slot structure and the second slot structure, so that the test frame can remove the C-shaped bracket and internal related structures, and only retain the external square frame beam support structure for sub-level test running.

[0028] The restraining and limiting device provides space for the vertical deformation of the spring steel bottom plate through the elastic spring steel bottom plate and the gap between the inner support plate and the bottom of the third accommodating space, so that the movable frame can move axially by 3-5mm, thereby measuring the engine thrust. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0030] Figure 1 It is a schematic diagram of the overall structure of a large-thrust rocket engine full-system test stand provided by an embodiment of the present invention; Figure 2 The embodiment of the present invention provides Figure 1 Schematic diagram of the foundation embedded parts structure; Figure 3 The embodiment of the present invention provides Figure 1 Schematic diagram of the square frame beam support structure in FIG. Figure 4 The embodiment of the present invention provides Figure 1 Schematic diagram of the C-shaped bracket structure; Figure 5 The embodiment of the present invention provides Figure 1 The structural diagram of the moving frame in FIG. Figure 6 The embodiment of the present invention provides Figure 1 Schematic diagram of the C-shaped bracket and preload device and their related structures; Figure 7 The embodiment of the present invention provides Figure 5 A schematic diagram of the structure of the restraining and limiting device in FIG. Figure 8 The embodiment of the present invention provides Figure 5 A schematic structural diagram of the restraining and limiting device from another perspective; Fig. 9 The embodiment of the present invention provides Figure 6 Schematic diagram of the structure of the preload device.

[0031] In the accompanying drawings, the same reference numerals are used to denote the same components or structures, wherein: 1-connecting base; 2-anchor plate; 3-pull beam; 4-upper cross beam; 5-load-bearing beam; 6-column; 7-lower cross beam; 8-support ring; 9-C-type column; 10-C-type column cross beam; 11-diagonal brace; 12-support rod; 13-restraint limit device; 14-load-bearing ring beam; 15-annular transition frame; 16-outer support plate; 17-spring steel bottom plate; 18-inner support plate; 19-pull rod; 20-support; 21-lever; 22-servo motor; 23-bevel gear; 24-weight rod; 25-weight; 26-moving frame; 27-preload device; 28-main load-bearing bracket; 29-force sensor; 30-support seat; 31-first slot structure; 32-second slot structure. DETAILED DESCRIPTION

[0032] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0033] In the description of the present invention, the terms "inside", "outside", "under", "below", "below", "below", "under", "above", "above", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, which are only for the convenience of describing the present invention and do not require that the present invention must be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention. In addition, the technical features involved in each embodiment of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0034] A large-thrust rocket engine full-system test stand device, comprising: The foundation embedded part includes a plurality of groups of anchor plates 2, tension beams 3 and connection bases 1 having the same number as the groups of anchor plates 2. A group of anchor plates and a corresponding group of connection bases connected thereto form an anchor pile. Adjacent anchor piles are sequentially connected by tension beams to form a U-shaped foundation embedded part, which can provide pull-out resistance by being fixed to the concrete foundation. The square frame beam support structure includes a column 6, a load-bearing beam 5, an upper cross beam 4, a diagonal brace 11 and a lower cross beam 7, forming a square frame beam structure with a first accommodation space, which is used to bear the axial load during the engine test; and The C-shaped bracket is connected to the first accommodation space and includes at least two C-shaped columns 9 with notches, a C-shaped column crossbeam 10 and a support ring 8. At least two C-shaped columns 9 can enclose a second accommodation space, can bear the load in the test run, and are used to fix the movable frame 26 and the calibration system.

[0035] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, there are 4 columns 6, load-bearing beams 5, upper cross beams 4, diagonal braces 11 and lower cross beams 7, the 4 columns are distributed at the four corners of the rectangle, the 4 lower cross beams 7 are connected in sequence and surround a lower rectangle, the four corners of the lower rectangle are respectively connected to the middle and upper parts of the 4 columns 6 through the 4 load-bearing beams 5, the tops of the 4 columns 6 are surrounded by the 4 upper cross beams 4 to form an upper rectangle, the tops of the 4 columns 6 are connected to the side close to the lower rectangle with a diagonal brace 11, the other end of the diagonal brace 11 is connected to a corner corresponding to it on the lower rectangle, the load-bearing beams 5, the diagonal braces 11 and the middle and upper parts of the columns 6 form a triangular frame to provide tension to the lower rectangle, and the columns 6 are formed by at least two sections of base columns connected end to end.

[0036] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, the load-bearing beam 5, the diagonal brace 11 and the upper and middle parts of the columns 6 form an isosceles right-angled triangle frame, and the diagonal brace forms an angle of 45° with the horizontal plane.

[0037] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, the movable frame 26 is connected to the C-shaped bracket through a constraint and limit device 13, and the constraint and limit device 13 includes a spring steel bottom plate 17, an outer support plate 16, an inner support plate 18 and a support seat 30. A third accommodating space is opened on the support seat 30, one side of the outer support plate 16 is connected to the support seat 30, and the other side is connected to the inner notch of the C-shaped column 9, one side of the inner support plate 18 is located in the third accommodating space and connected to the spring steel bottom plate 17, and the other side is connected to the movable frame 26, and there is a gap between the inner support plate 18 and the bottom of the third accommodating space to provide a clearance space for the vertical deformation of the spring steel bottom plate 17; the movable frame includes a load-bearing ring beam 14, a main load-bearing bracket 28 and an annular transition frame 15, and the load-bearing ring beam 14 and the annular transition frame 15 are respectively connected to the top and bottom of the main load-bearing bracket 28.

[0038] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, the lower parts of the adjacent C-type columns 9 are connected by C-type column cross beams 10, and the top is connected to the support ring 8 to support the dynamic frame 26.

[0039] Furthermore, in the above-mentioned large-thrust rocket engine full-system test bench, the two support rods 12 are cross-connected in the middle of the support ring 8 through the center of the circle, and the two support rods 12 coincide with the connecting line of the tops of the two opposite C-shaped columns 9.

[0040] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, the C-type column 9 is connected to the preload device 27, the second accommodating space is connected to the movable frame 26, and the preload device 27 is used to provide preload force to the movable frame; a force sensor 29 is connected between the notch of the C-type column 9 and the top surface of the movable frame, and there is a gap between the force sensor 29 and the C-type column 9 or the top surface of the movable frame.

[0041] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, a first slot structure 31 is provided on the side of the C-shaped column 9 away from the notch, and a connecting piece with a second slot structure 32 is connected to the inner side of the overlapping part of the lower cross beam 7 and the load-bearing beam 5, and the first slot structure 31 and the second slot structure 32 are matched in a concave-convex manner, and the C-shaped column 9 is detachably connected to the square frame beam support structure through the first slot structure 31 and the second slot structure 32.

[0042] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, each group of the anchor plates 2 adopts a partition structure connected in series up and down, and is fixed in the concrete foundation with reinforcing ribs and screws to improve the pull-out resistance.

[0043] Furthermore, in the above-mentioned large-thrust rocket engine full-system test bench, the preload device 27 includes a pull rod 19, a support 20, a lever 21, a servo motor 22, a bevel gear 23, a weight rod 24 and a weight 25.

[0044] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, the dynamic frame includes a load-bearing ring beam and a constraint and limit device, the dynamic frame includes a load-bearing ring beam and a constraint and limit device, the load-bearing ring beam includes a main load-bearing bracket and an annular transition frame, and the constraint and limit device includes a spring steel bottom plate, an outer support plate and an inner support plate.

[0045] Furthermore, in the above-mentioned high-thrust rocket engine full-system test bench, the preload device includes a pull rod, a support, a lever, a servo motor, a bevel gear, a weight rod and a weight.

[0046] Furthermore, the above-mentioned large-thrust rocket engine full-system test bench is detachable because the columns are composed of at least two base columns connected end to end. The full-system test bench can lift the engine to different installation heights by adjusting the height of the columns, providing sufficient test space, and is therefore suitable for engines of different models.

[0047] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, the column is formed by two sections of base columns connected end to end, and the two sections are connected by flanges, which can also facilitate transportation and on-site installation.

[0048] Furthermore, in the above-mentioned large-thrust rocket engine full-system test frame, there are four C-type columns, the four C-type columns are 90 degrees to each other, the four C-type column cross beams connect adjacent C-type columns, and the support ring is on the top of the C-type column, connecting the four C-type columns and the preload device above.

[0049] The lower cross beam and the upper cross beam are connected to adjacent load-bearing beams to control the deformation of the load-bearing beams.

[0050] The test frame limits the position and transfers the load to the moving frame part through the central C-shaped bracket.

[0051] The C-shaped column as a whole adopts a box-type structure, which can not only accommodate components such as a moving frame and a sensor, but also effectively bear the thrust load in the vertical direction.

[0052] A large-thrust rocket engine full-system test frame described in any of the above items is used for sub-stage test or single-machine test. The maximum axial bearing capacity of the test frame is 12,500 kN, and the dynamic load coefficient is 2.5. It can meet the hot test requirements of different types of rocket engines and has the function of switching between sub-stage test and single-machine test. The entire full-system test frame can be used for single-machine test. The C-shaped bracket and internal related structures are removed, and only the external square frame beam support structure is retained. The sub-stage is connected to the square frame beam support structure through a ring connector, and the sub-stage test can be carried out.

[0053] Example 1 Overall structural design: The test frame consists of foundation embedded parts, square frame beam support structure and C-shaped bracket.

[0054] The foundation embedded parts are used to fix the test frame on the concrete foundation to ensure that no displacement occurs during the test. The foundation embedded parts mainly include four groups of anchor plates 2, three tension beams 3 and four groups of connecting bases 1. One group of anchor plates and the corresponding group of connecting bases connected thereto form an anchor pile, and the four anchor piles are connected in sequence through tension beams to form a U-shaped foundation embedded part. Specifically, each group of anchor plates 2 adopts a three-layer partition structure arranged in an upper and lower interval, and is connected to the corresponding connecting base connected thereto through 16 M90 screws. The bottom plate and top plate of the same group of connecting bases (the bottom plate is in contact with the ground, and the top plate is in contact with the column) are fixed in the concrete foundation by welding reinforcement bars. The tension beam 3 is used to connect and reinforce the anchor piles of adjacent groups to ensure that the anchor piles will not be displaced when loaded. The screw is made of 30CrMnSiA high-strength material with excellent tensile properties to ensure that it can withstand a vertical upward thrust of 12500 kN.

[0055] The square frame beam support structure is composed of 4 columns 6 with a height of 6.7 meters, 4 load-bearing beams 5, 4 upper beams 4, 4 diagonal braces 11 and 4 lower beams 7. The 4 columns are distributed at the four corners of the rectangle, and the 4 lower beams 7 are connected in sequence to form a lower rectangle. The four corners of the lower rectangle are connected to the upper and middle parts of the 4 columns 6 through the 4 load-bearing beams 5, respectively. The tops of the 4 columns 6 are surrounded by the 4 upper beams 4 to form an upper rectangle. The tops of the 4 columns 6 are connected to the side close to the lower rectangle with diagonal braces 11, and the other end of the diagonal brace 11 is connected to the corresponding corner of the lower rectangle. The load-bearing beams 5, diagonal braces 11 and the upper and middle parts of the columns 6 form a triangular frame to provide tension to the lower rectangle. The square frame beam support structure evenly distributes the force of the test frame to the foundation through the columns 6 and the triangular frame. The C-shaped bracket is used to fix the dynamic frame part of the engine and to connect the load and calibration system required during the test. The column 6 is designed with a rectangular cross section of 1.2 meters by 0.9 meters, and is connected to the foundation embedded parts through a flange. A reinforcing rib plate is provided at the flange to reduce stress concentration. The span of the isosceles right triangle frame is 11 meters. The upper crossbeam 4 and the column 6 together form a closed square frame structure, which can evenly disperse the load generated during the test.

[0056] The C-shaped bracket is composed of 4 C-shaped columns 9 with notches, 4 C-shaped column beams 10 and 1 support ring 8. The lower parts of adjacent C-shaped columns 9 are connected by C-shaped column beams 10, and the tops are connected to the support ring 8 to support the movable frame. Two crossed support rods 12 are radially connected in the middle of the support ring 8, and the two support rods 12 coincide with the connecting line of the tops of the two opposite C-shaped columns 9. The notch of the C-shaped column 9 has a large cavity space for accommodating the movable frame. A first slot structure is provided on the side of the C-shaped column 9 away from the notch, and the first slot structure is connected to the square frame beam support structure through a connector.

[0057] The movable frame 26 is connected to the C-shaped bracket through the restraining and limiting device 13, and the restraining and limiting device 13 includes a spring steel bottom plate 17, an outer support plate 16, an inner support plate 18 and a support seat 30. A third accommodating space is opened on the support seat 30. One side of the outer support plate 16 is connected to the support seat 30, and the other side is connected to the inner notch of the C-shaped column 9. One side of the inner support plate 18 is located in the third accommodating space and connected to the spring steel bottom plate 17, and the other side is connected to the movable frame 26. There is a gap between the inner support plate 18 and the bottom of the third accommodating space to provide a clearance space for the vertical deformation of the spring steel bottom plate 17. The dynamic frame is a key component for supporting the engine, and includes a load-bearing ring beam 14, a main load-bearing support 28 and an annular transition frame 15. The load-bearing ring beam 14 and the annular transition frame 15 are respectively connected to the top and bottom of the main load-bearing support 28.

[0058] The C-type column 9 is connected to the preload device 27, which can adopt one of the existing technologies, such as the existing technology with application number CN202211277944.4 and title "A preload adjustment device for thrust measurement of a large thrust rocket engine", which can include a pull rod 19, a support 20, a lever 21, a servo motor 22, a bevel gear 23, a weight rod 24 and a weight 25. The preload device is used to overcome the reverse thrust generated by the pipeline connection and liquid flow and the gravity of the dynamic frame and the engine, eliminate the gap between the force sensor and the C-type column 9, and make the sensor bear the same load direction before and after the test.

[0059] The dynamic frame is precisely calibrated through the restraint limit device and preload device connected to the C-shaped bracket to ensure that the thrust direction of the engine is aligned with the central axis of the test frame. The preload device ensures the stability of the dynamic frame during the test and reduces the impact of load changes on the test results.

[0060] Materials and manufacturing: The main load-bearing components of the test frame are made of Q355D material, which has excellent mechanical properties. In order to reduce the weight and cost of the structure, some connecting parts such as flanges are made of forgings, and other main structural parts are welded from plates.

[0061] Fastener connection and verification: All connection parts of the test frame use high-strength fasteners, and the bolts and studs are made of 8.8 grade materials to ensure their reliability under high loads. The fasteners at the main connection parts are verified and analyzed to confirm that they can withstand an axial load of 12,500 kN and a maximum working stress of 383 MPa, which meets the standard requirements.

[0062] 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 principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A large-thrust rocket engine full-system test bench, characterized in that: include: A foundation embedded part, comprising a plurality of groups of anchor plates (2), tension beams (3) and connection bases (1) equal in number to the number of groups of anchor plates (2), wherein a group of anchor plates and a corresponding group of connection bases connected thereto form an anchor pile, and adjacent anchor piles are sequentially connected by tension beams to form a U-shaped foundation embedded part, which can provide pull-out resistance by being fixed to a concrete foundation; A square frame beam support structure, comprising a column (6), a load-bearing beam (5), an upper cross beam (4), a diagonal brace (11) and a lower cross beam (7), forming a square frame beam structure with a first accommodation space, and used for bearing an axial load during engine test; and The C-shaped bracket is connected to the first accommodation space and comprises at least two C-shaped columns (9) with notches, a C-shaped column crossbeam (10) and a support ring (8). The at least two C-shaped columns (9) can enclose a second accommodation space, can bear the load during the test run, and are used to fix the moving frame (26) and the calibration system.

2. A large thrust rocket engine full system test stand according to claim 1, characterized in that: The columns (6), the load-bearing beams (5), the upper cross beams (4), the diagonal braces (11) and the lower cross beams (7) are each provided with four columns. The four columns are distributed at the four corners of the rectangle. The four lower cross beams (7) are connected in sequence to form a lower rectangle. The four corners of the lower rectangle are respectively connected to the upper and middle parts of the four columns (6) through the four load-bearing beams (5). The tops of the four columns (6) are formed into an upper rectangle through the four upper cross beams (4). The tops of the four columns (6) are connected to a diagonal brace (11) on one side close to the lower rectangle. The other end of the diagonal brace (11) is connected to a corresponding corner of the lower rectangle. The load-bearing beams (5), the diagonal brace (11) and the upper and middle parts of the columns (6) form a triangular frame to provide tension to the lower rectangle. The columns (6) are formed by connecting at least two sections of base columns end to end.

3. A large thrust rocket engine full system test stand according to claim 1, characterized in that: The movable frame (26) is connected to the C-shaped bracket via a restraining and limiting device (13). The restraining and limiting device (13) comprises a spring steel bottom plate (17), an outer support plate (16), an inner support plate (18) and a support seat (30). A third accommodating space is provided on the support seat (30). One side of the outer support plate (16) is connected to the support seat (30), and the other side is connected to the inner notch of the C-shaped column (9). One side of the inner support plate (18) is located in the third accommodating space and is connected to the spring steel bottom plate (17), and the other side is connected to the movable frame (26). A gap is provided between the inner support plate (18) and the bottom of the third accommodating space to provide clearance space for the vertical deformation of the spring steel bottom plate (17). The movable frame comprises a load-bearing ring beam (14), a main load-bearing bracket (28) and an annular transition frame (15). The load-bearing ring beam (14) and the annular transition frame (15) are respectively connected to the top and bottom of the main load-bearing bracket (28).

4. A large thrust rocket engine full system test stand according to claim 1, characterized in that: The lower parts of adjacent C-shaped columns (9) are connected by a C-shaped column crossbeam (10), and the top parts are connected to a support ring (8) to support the movable frame (26).

5. A large thrust rocket engine full system test stand according to claim 4, characterized in that: Two support rods (12) are cross-connected in the middle of the support ring (8) through the center of the circle, and the connection line between the two support rods (12) and the tops of the two opposite C-shaped columns (9) coincides.

6. A large thrust rocket engine full system test stand according to claim 1, characterized in that: The C-shaped column (9) is connected to a pre-tightening device (27), the second accommodating space is connected to a movable frame (26), and the pre-tightening device (27) is used to provide a pre-tightening force to the movable frame; A force sensor (29) is connected between the notch of the C-shaped column (9) and the top surface of the moving frame, and a gap is provided between the force sensor (29) and the C-shaped column (9) or the top surface of the moving frame.

7. A large thrust rocket engine full system test stand according to claim 1, characterized in that: A first slot structure (31) is provided on a side of the C-shaped column (9) facing away from the notch, and a connecting piece having a second slot structure (32) is connected to the inner side of the overlap between the lower cross beam (7) and the load-bearing beam (5), the first slot structure and the second slot structure being matched in a concave-convex manner, and the C-shaped column is detachably connected to the square frame beam support structure via the first slot structure and the second slot structure.

8. A large thrust rocket engine full system test stand according to claim 1, characterized in that: Each group of anchor plates (2) adopts a partition structure connected in series up and down, and is fixed in the concrete foundation with reinforcing ribs and screws to improve the pull-out resistance.

9. A large thrust rocket engine full system test stand according to claim 6, characterized in that: The preload device (27) comprises a pull rod (19), a support (20), a lever (21), a servo motor (22), a bevel gear (23), a weight rod (24) and a weight (25).

10. Application of a large-thrust rocket engine full-system test bench according to any one of claims 1 to 9, characterized in that: Used for sub-stage testing or single-machine testing, the test frame has a maximum axial bearing capacity of 12,500 kN and a dynamic load coefficient of 2.5, which can meet the hot test requirements of different types of rocket engines.

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