An external excitation loading device for simulating the free flight state of a solid rocket engine

Abstract

This invention discloses an external excitation loading device for simulating the free flight state of a solid rocket engine, comprising: a support mechanism, a suspension mechanism, and a vibration excitation mechanism; wherein, the suspension mechanism is installed at the lower part of the support mechanism; and the vibration excitation mechanism is installed at the lower part of the suspension mechanism. This invention changes the rigid clamping state of previous engine flight vibration tests, accurately applying external excitation based on free flight boundary conditions, thereby achieving a realistic simulation of the engine's free flight state and improving the realistic environmental simulation capability of solid rocket engine flight vibration tests.

Description

Technical Field

[0001] This invention belongs to the field of solid rocket engine flight vibration testing technology, and particularly relates to an external excitation loading device for simulating the free flight state of a solid rocket engine. Background Technology

[0002] Flight vibration testing of solid rocket motors is a key verification method for assessing their structural reliability under flight conditions, and the authenticity of the test boundary conditions directly determines the validity of the test data. Currently, the industry commonly uses rigid "clamp-type" fixtures to position and clamp the motors, relying on rigid transition tooling to rigidly connect with the vibration table to achieve the transfer of vibration loads.

[0003] In flight vibration tests, rigid clamps, with their high constraint stiffness and fixed constraint form, significantly alter the engine's dynamic boundary conditions, causing the modal frequencies, mode shapes, and vibration responses to deviate from the free flight state, resulting in inconsistent test results between air and ground. Furthermore, for composite material shells, rigid clamping methods are prone to localized stress concentration and load transfer distortion, potentially leading to damage to the shell, insulation layer, and propellant charge, thus compromising test safety and effectiveness.

[0004] A solid rocket motor elastic weak constraint test rig, with application number CN202011591988.5 and publication date of April 6, 2021, includes a fixed rig, a moving rig, an adjustment device, a test engine, and ground guide rails. This solid rocket motor elastic weak constraint test rig uses a variable frequency spring and gap adjustment ring structure for weak constraint simulation, simulating the transmission process of engine thrust by simulating the elastic deformation of the inter-stage connection device. However, the assembled and adjusted state of this test rig fails to realistically release the structural degrees of freedom, making it difficult to simulate the free state during engine flight testing and unsuitable for state simulation under engine vibration environments.

[0005] In summary, existing rigid and weakly constrained clamping methods are insufficient to meet the requirements of high-precision and high-reliability flight vibration testing. To achieve near-free-state assembly and adjustment support, reduce stress concentration, and improve the realism and safety of the test, it is necessary to use flexible clamps for engine vibration testing. Therefore, based on practical considerations and the engine vibration test site environment, developing a stable and reliable external excitation loading device suitable for simulating the free flight state of solid rocket engines is an urgent task, which will help improve the realistic environmental simulation capabilities of solid rocket engine flight vibration testing. Summary of the Invention

[0006] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide an external excitation loading device for simulating the free flight state of a solid rocket engine. This device changes the rigid clamping state of previous engine flight vibration tests, accurately applies external excitation based on the free flight boundary conditions, realizes the real simulation of the engine's free flight state, and improves the real environment simulation capability of solid rocket engine flight vibration tests.

[0007] The objective of this invention is achieved through the following technical solution: an external excitation loading device for simulating the free flight state of a solid rocket engine, comprising: a support mechanism, a suspension mechanism, and a vibration excitation mechanism; wherein, the suspension mechanism is installed at the lower part of the support mechanism; and the vibration excitation mechanism is installed at the lower part of the suspension mechanism.

[0008] In the aforementioned external excitation loading device for simulating the free flight state of a solid rocket engine, the support mechanism includes a support frame, brake swivel casters, a lifting bracket, a connecting beam, a first-stage sliding T-slot, an inclined support plate, and a lifting unit. The brake swivel casters are located at the bottom of the support frame; the lifting bracket is slidably and vertically mounted on the support frame; the connecting beam is fixedly mounted on the upper part of the lifting bracket; the first-stage sliding T-slot is located at the bottom end of the connecting beam; the inclined support plate is fixed to the side of the support frame; and the lifting unit is mounted on the support frame and fixedly connected to the inclined support plate.

[0009] In the aforementioned external excitation loading device for simulating the free flight state of a solid rocket engine, the suspension mechanism includes two suspension units; wherein the tops of the two suspension units are fixedly installed on the lower part of the connecting crossbeam through the first-stage sliding T-slot; one end of the test engine is connected to the bottom of one suspension unit, and the other end of the test engine is connected to the bottom of the other suspension unit.

[0010] In the aforementioned external excitation loading device for simulating the free flight state of a solid rocket engine, the excitation mechanism includes two excitation units; wherein, the two excitation units are fixedly installed at the lower part of the suspension mechanism.

[0011] In the aforementioned external excitation loading device for simulating the free flight state of a solid rocket engine, the lifting unit includes a hand-cranked winch, a guide pulley assembly, and a tightening ring; wherein, the hand-cranked winch is mounted on the inclined support plate; the guide pulley assembly is mounted on the support frame and is connected to the hand-cranked winch by a wire rope; the tightening ring is mounted on the tightening ring and is connected to the guide pulley assembly by a wire rope.

[0012] In the aforementioned external excitation loading device for simulating the free flight state of a solid rocket engine, the suspension unit includes a hanger, a secondary transverse T-slot, two guide transition plates, a secondary vertical T-slot, and two elastic clamping units. The hanger is fixedly installed on the lower part of the connecting beam via a primary sliding T-slot. The hanger has the secondary transverse T-slot at its bottom end. Both guide transition plates are fixedly installed on the lower part of the hanger via the secondary transverse T-slots. Both guide transition plates have the secondary vertical T-slots. One elastic clamping unit is fixedly installed on the inner side of one guide transition plate via the secondary vertical T-slot, and the other elastic clamping unit is fixedly installed on the inner side of the other guide transition plate via the secondary vertical T-slot.

[0013] In the aforementioned external excitation loading device for simulating the free flight state of a solid rocket engine, one end of the test engine is positioned between two elastic clamping units of a suspension unit, and the other end of the test engine is positioned between two elastic clamping units of another suspension unit.

[0014] In the aforementioned external excitation loading device for simulating the free flight state of a solid rocket engine, the excitation unit includes an exciter, an excitation rod, an input monitoring unit, and a coupling module; wherein, one end of the excitation rod is connected to the exciter, and the other end of the excitation rod is connected to the input monitoring unit; one end of the coupling module is connected to the input monitoring unit, and the other end of the coupling module is connected to the suspension mechanism.

[0015] In the aforementioned external excitation loading device for simulating the free flight state of a solid rocket engine, the elastic clamping unit includes a mounting base, an elastic matrix, and a flexible clamp; wherein, the mounting base is fixedly connected to a guide adapter plate; one end of the elastic matrix is ​​connected to the mounting base, and the other end of the elastic matrix is ​​connected to the flexible clamp.

[0016] In the aforementioned external excitation loading device for simulating the free flight state of a solid rocket engine, the coupling module is made of resin material, the top surface of the coupling module is an arc-shaped curved surface, and the top surface of the coupling module is connected to the lower end face of the test engine casing by an adhesive; wherein, after uniformly applying the adhesive and undergoing curing for more than 30 minutes, it is bonded to the test engine casing; the elastic matrix is ​​made of vulcanized rubber material.

[0017] Compared with the prior art, the present invention has the following advantages: (1) In the process of operation, the present invention can change the rigid clamping state in the previous engine flight vibration test by setting up an elastic clamping unit, providing the flexibility required for the free boundary, and truly simulating the state of free flight of the engine; (2) By setting up a lifting unit and a coupling module, the present invention solves the problems of bonding and curing and stress deviation during the assembly and adjustment process, and can achieve fast and effective bonding and free state leveling, ensuring that the engine is not affected by forces other than external vibration; (3) By setting up an elastic matrix, the present invention enables test engines with different design stiffness to be adapted to different weights, ensuring the safety of flight vibration tests while maintaining the required flexibility of the free boundary. (4) By setting a first-level sliding T-slot and a second-level transverse T-slot, the present invention can adapt to the rapid assembly and adjustment of test engines with multiple structural dimensions, and solve the universality requirements of real flight vibration tests of various solid rocket engines. Attached Figure Description

[0018] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 This is a three-dimensional structural schematic diagram of an external excitation loading device for simulating the free flight state of a solid rocket engine, provided in an embodiment of the present invention. Figure 2 This is a front view structural schematic diagram of an external excitation loading device for simulating the free flight state of a solid rocket engine, provided in an embodiment of the present invention. Figure 3 This is a three-dimensional structural schematic diagram of the support mechanism provided in an embodiment of the present invention; Figure 4 This is a side view structural schematic diagram provided in an embodiment of the present invention; Figure 5 This is a three-dimensional structural schematic diagram of the suspension mechanism provided in an embodiment of the present invention; Figure 6 This is a front view schematic diagram of the excitation mechanism provided in an embodiment of the present invention; Figure 7 This is a three-dimensional structural schematic diagram of the elastic clamping unit provided in an embodiment of the present invention; Figure 8 This is a front view structural schematic diagram of the solid rocket engine provided in an embodiment of the present invention. Detailed Implementation

[0019] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the disclosure to those skilled in the art. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0020] Figure 1 This is a three-dimensional structural schematic diagram of an external excitation loading device for simulating the free flight state of a solid rocket engine, provided in an embodiment of the present invention. Figure 2 This is a front view structural schematic diagram of an external excitation loading device for simulating the free flight state of a solid rocket engine, provided in an embodiment of the present invention. Figure 3 This is a three-dimensional structural schematic diagram of the support mechanism provided in an embodiment of the present invention; Figure 4 This is a side view structural schematic diagram provided in an embodiment of the present invention; Figure 5 This is a three-dimensional structural schematic diagram of the suspension mechanism provided in an embodiment of the present invention; Figure 6 This is a front view schematic diagram of the excitation mechanism provided in an embodiment of the present invention; Figure 7 This is a three-dimensional structural schematic diagram of the elastic clamping unit provided in an embodiment of the present invention; Figure 8 This is a front view structural schematic diagram of the solid rocket engine provided in an embodiment of the present invention.

[0021] like Figure 1 and Figure 2 As shown, an external excitation loading device for simulating the free flight state of a solid rocket engine includes: a support mechanism 1, a suspension mechanism 2, and a vibration mechanism 3; wherein, the suspension mechanism 2 is installed at the lower part of the support mechanism 1; and the vibration mechanism 3 is installed at the lower part of the suspension mechanism 2. The external excitation loading device for simulating the free flight state of a solid rocket engine includes a support mechanism 1 fixed by a support frame 1-1, a suspension mechanism 2 fixedly installed below the support mechanism, and a vibration mechanism 3 fixedly installed below the suspension mechanism.

[0022] like Figure 3As shown, the support mechanism 1 includes a support frame 1-1, a brake swivel caster 1-2, a lifting bracket 1-3, a connecting beam 1-4, a primary sliding T-slot 1-5, an inclined support plate 1-6, and a lifting unit 1-7. The brake swivel caster 1-2 is located at the bottom of the support frame 1-1. The lifting bracket 1-3 is slidably and vertically mounted on the support frame 1-1. The connecting beam 1-4 is fixedly mounted on the upper part of the lifting bracket 1-3. The primary sliding T-slot 1-5 is located at the bottom end of the connecting beam 1-4. The inclined support plate 1-6 is fixed to the side of the support frame 1-1. The lifting unit 1-7 is mounted on the support frame 1-1 and is fixedly connected to the inclined support plate 1-6.

[0023] Brake swivel casters 1-2 are located at the bottom of the support frame; lifting brackets 1-3 are slidably and vertically installed on the support frame; connecting beams 1-4 are installed and fixed above the lifting brackets; a first-stage sliding T-slot 1-5 is located at the bottom of the connecting beam; inclined support plates 1-6 are fixed to the side of the support frame; and lifting units 1-7 are located on the support frame and are fixedly connected to the inclined support plates.

[0024] like Figure 2 As shown, the suspension mechanism 2 includes two suspension units, namely the first suspension unit 2-1 and the second suspension unit 2-2. The tops of the two suspension units are fixedly mounted on the lower part of the connecting beam 1-4 via a primary sliding T-slot 1-5. One end of the test engine is connected to the bottom of one suspension unit, and the other end of the test engine is connected to the bottom of the other suspension unit. The two suspension units are fixedly mounted below the connecting beam via the primary sliding T-slot, and are arranged symmetrically and identically within the support mechanism.

[0025] like Figure 2 As shown, the excitation mechanism 3 includes two excitation units, namely the first excitation unit 3-1 and the second excitation unit 3-2; wherein, the two excitation units are fixedly installed at the lower part of the suspension mechanism 2. The two excitation units are arranged inside the support mechanism and fixed below the suspension mechanism, and are symmetrically arranged at the left and right ends of the suspension mechanism with the same structure.

[0026] like Figure 3 As shown, the lifting unit 1-7 includes a hand-cranked winch 1-71, a guide pulley assembly 1-72, and a tightening ring 1-73; wherein, the hand-cranked winch 1-71 is mounted on the inclined support plate 1-6; the guide pulley assembly 1-72 is mounted on the support frame 1-1, and the guide pulley assembly 1-72 is connected to the hand-cranked winch 1-71 by a wire rope; the tightening ring 1-73 is mounted on the guide pulley assembly 1-72, and the tightening ring 1-73 is connected to the guide pulley assembly 1-72 by a wire rope.

[0027] The hand-cranked winch 1-71 is fixed to the inclined support plate; the guide pulley block 1-72 is connected to the hand-cranked winch by a steel wire rope and fixed to the support frame; the tightening ring 1-73 is connected to the guide pulley block by a steel wire rope and is set on the lifting bracket.

[0028] like Figure 4 As shown, the suspension unit includes a bracket 2-11, a secondary transverse T-slot 2-12, two guide transition plates 2-13, a secondary vertical T-slot 2-14, and two elastic clamping units 2-15. The bracket 2-11 is fixedly installed on the lower part of the connecting beam 1-4 via a primary sliding T-slot 1-5. The bottom end of the bracket 2-11 has a secondary transverse T-slot 2-12. Both guide transition plates 2-13 are fixedly installed via the secondary transverse T-slot 2-12. At the lower part of the bracket 2-11, both guide transition plates 2-13 are provided with secondary vertical T-slots 2-14; one elastic clamping unit 2-15 is fixedly installed on the inner side of one guide transition plate 2-13 through the secondary vertical T-slot 2-14 of one guide transition plate 2-13, and the other elastic clamping unit 2-15 is fixedly installed on the inner side of the other guide transition plate 2-13 through the secondary vertical T-slot 2-14 of the other guide transition plate 2-13.

[0029] Hanger 2-11 is fixedly installed below the connecting beam via a primary sliding T-slot; secondary horizontal T-slot 2-12 is located at the bottom of the hanger; guide transition plate 2-13 is fixedly installed below the hanger via a secondary horizontal T-slot; secondary vertical T-slot 2-14 is located on the guide transition plate; elastic clamping unit 2-15 is fixedly installed inside the guide transition plate via a secondary vertical T-slot.

[0030] One end of the test engine is positioned between two elastic clamping units 2-15 of one suspension unit, and the other end of the test engine is positioned between two elastic clamping units 2-15 of another suspension unit.

[0031] like Figure 5 As shown, the excitation unit includes an exciter 3-11, an excitation rod 3-12, an input monitoring unit 3-13, and a coupling module 3-14; wherein, one end of the excitation rod 3-12 is connected to the exciter 3-11, and the other end of the excitation rod 3-12 is connected to the input monitoring unit 3-13; one end of the coupling module 3-14 is connected to the input monitoring unit 3-13, and the other end of the coupling module 3-14 is connected to the suspension mechanism 2.

[0032] The vibrator 3-11 is fixed on the ground and arranged below the suspension mechanism; the excitation rod 3-12 is installed on the vibrator by a threaded connection; the input monitoring unit 3-13 is located at the top of the excitation rod and is threadedly connected to it; the coupling module 3-14 is located at the top of the input monitoring unit and is threadedly connected to it.

[0033] like Figure 3 and Figure 4 As shown, the lifting support can be raised and lowered within the support frame under the synchronous traction force of the two lifting units, and maintain a self-locking fixed state.

[0034] like Figure 7 As shown, the elastic clamping unit 2-15 includes a mounting base 2-151, an elastic substrate 2-152, and a flexible clamp 2-153; wherein, the mounting base 2-151 is fixedly connected to the guide adapter plate 2-13; one end of the elastic substrate 2-152 is connected to the mounting base 2-151, and the other end of the elastic substrate 2-152 is connected to the flexible clamp 2-153.

[0035] Mounting base 2-151 is fixedly connected to guide adapter plate; elastic base 2-152 is fixedly connected to the side of mounting base; flexible clamp 2-153 is set at the end of elastic base and fixedly connected to it.

[0036] The coupling module 3-14 is made of resin, and its top surface is an arc-shaped curved surface. The top surface of the coupling module 3-14 is connected to the lower end face of the test engine housing via an adhesive; specifically, the adhesive is uniformly applied and cured for at least 30 minutes before bonding to the test engine housing. Figure 6 As shown, the coupling module is made of lightweight resin material. Its top surface is an arc-shaped curved surface that contacts the lower end surface of the test engine housing. After being uniformly coated with adhesive and cured for more than 30 minutes, it can be firmly bonded to the test engine housing.

[0037] The elastic matrix 2-152 is a vulcanized rubber material. For example... Figure 2 and 7 As shown, the elastic matrix is ​​a vulcanized rubber material, which is prone to elastic deformation under external excitation force. Different design stiffnesses are adapted to test engines of different weights to maintain the flexibility required for the free boundary.

[0038] At work, such as Figure 1 and Figure 3 As shown, push the support mechanism 1 directly above the vibration mechanism 3, control the brake casters 1-2, and fix the support mechanism; as shown Figure 2 and Figure 5 As shown, the mounting bracket 2-11 is pre-installed below the connecting crossbeam 1-4. The mounting bracket can slide left and right along the first-stage sliding T-slot on the connecting crossbeam, depending on the test engine (e.g., Figure 8 (As shown) Adjust the length of the sliding position and lock it in place; as shown Figure 5 As shown, the guide adapter plate 2-13 is pre-installed below the connecting crossbeam. Along the secondary transverse T-slot 2-1, the guide adapter plate is slid outwards to its maximum position; as shown... Figure 1 and Figure 5As shown, the test engine is hoisted using lifting equipment. The engine hoisting height is lower than the ground clearance of the mounting bracket. Based on the weight of the test engine, elastic clamping units 2-15 with appropriate stiffness are designed and selected. Two pairs of elastic clamping units are fixed at the modal node positions of the test engine. The test engine, with the elastic clamping units 2-15 connected, is hoisted and transported to the underside of the mounting bracket. The guide adapter plate is slowly slid inward along the secondary transverse T-slot, so that the mounting base 2-151 of the elastic clamping unit fits against the guide adapter plate and is fixed with bolts. Figure 1 and Figure 6 As shown, adhesive is uniformly applied to the arc-shaped surface at the top of coupling module 3-14. Based on the height of the external excitation position of the test engine above the ground, the two lifting units 1-7 are synchronously controlled to slowly descend. The lifting bracket 1-3, under the synchronous traction of the two lifting units, descends within the support frame 1-1 until the test engine casing is tightly fitted to the arc-shaped surface at the top of the coupling module. Because the hand-cranked winch 1-71 of the lifting unit uses a ratchet structure, it can self-lock after descending to the correct position and cure for more than 30 minutes. The two lifting units are then synchronously controlled to slowly rise. After the input monitoring unit 3-13 is connected to the test equipment, the current test force value is observed, ensuring that the moving coil plane of the vibrator 3-11 is in a natural state (neither pulled upwards nor pressed downwards by external forces). Figure 1 and Figure 2 As shown, the vibration controller controls the excitation unit. Two identical and symmetrically arranged excitation units generate vertical vibration displacement. Since the coupling module 3-14 and the test engine are rigid integrated structures after bonding and curing, and the elastic matrix 2-152 of the elastic clamping unit is made of vulcanized rubber, it is easy to generate elastic deformation under the action of external excitation force, and has vertical and horizontal degrees of freedom. Under the excitation of the external flight vibration test spectrum, the test engine generates forced vertical vibration displacement, which changes the rigid clamping state of the previous engine flight vibration test. Based on the free flight boundary conditions, it realizes the real simulation of the engine free flight state.

[0039] The purpose of this embodiment is to change the rigid clamping state of previous engine flight vibration tests, and to accurately apply external excitation based on free flight boundary conditions to achieve a true simulation of the engine's free flight state.

[0040] In this embodiment, by setting up an elastic clamping unit, the rigid clamping state of previous engine flight vibration tests can be changed, providing the flexibility required for the free boundary and realistically simulating the free flight state of the engine. By setting up a lifting unit and a coupling module, the process problems of bonding curing and stress deviation during assembly and adjustment are solved, enabling rapid and effective bonding and free state leveling, ensuring that the engine is not affected by forces other than external vibrations. By setting up an elastic matrix, test engines of different weights with different design stiffness can be adapted, ensuring the safety of flight vibration tests while maintaining the flexibility required for the free boundary. By setting up a primary sliding T-slot and a secondary transverse T-slot, it can adapt to the rapid assembly and adjustment of test engines with multiple structural sizes, solving the universal needs of real flight vibration tests for various solid rocket motors.

[0041] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. An external excitation loading device for simulating the free flight state of a solid rocket motor, characterized in that... include: The structure comprises a support mechanism (1), a suspension mechanism (2), and a vibration excitation mechanism (3); among which, The suspension mechanism (2) is installed at the lower part of the support mechanism (1); The excitation mechanism (3) is installed at the lower part of the suspension mechanism (2).

2. The external excitation loading device for simulating the free flight state of a solid rocket engine according to claim 1, characterized in that: The support mechanism (1) includes a support frame (1-1), brake swivel casters (1-2), a lifting bracket (1-3), a connecting beam (1-4), a primary sliding T-slot (1-5), an inclined support plate (1-6), and a lifting unit (1-7); wherein, The brake swivel caster (1-2) is located at the bottom of the support frame (1-1); The lifting bracket (1-3) is slidably and vertically installed on the support frame (1-1); The connecting beam (1-4) is installed and fixed on the upper part of the lifting bracket (1-3); The first-stage sliding T-slot (1-5) is provided at the bottom end of the connecting crossbeam (1-4); The inclined support plate (1-6) is fixed to the side of the support frame (1-1); The lifting unit (1-7) is mounted on the support frame (1-1) and is fixedly connected to the inclined support plate (1-6).

3. The external excitation loading device for simulating the free flight state of a solid rocket engine according to claim 2, characterized in that: The suspension mechanism (2) includes two suspension units; wherein, The tops of the two suspension units are fixedly installed on the lower part of the connecting crossbeam (1-4) via the first-stage sliding T-slot (1-5); One end of the test engine is connected to the bottom of a suspension unit, and the other end of the test engine is connected to the bottom of another suspension unit.

4. The external excitation loading device for simulating the free flight state of a solid rocket engine according to claim 1, characterized in that: The excitation mechanism (3) includes two excitation units; wherein, Two vibration units are fixedly installed on the lower part of the suspension mechanism (2).

5. The external excitation loading device for simulating the free flight state of a solid rocket engine according to claim 2, characterized in that: The lifting unit (1-7) includes a hand-cranked winch (1-71), a guide pulley block (1-72), and a tightening ring (1-73); wherein, The hand-cranked winch (1-71) is mounted on the inclined support plate (1-6); The guide pulley assembly (1-72) is mounted on the support frame (1-1), and the guide pulley assembly (1-72) is connected to the hand-cranked winch (1-71) by a steel wire rope. The tightening ring (1-73) is disposed on the tightening ring (1-73), and the tightening ring (1-73) is connected to the guide pulley block (1-72) by a steel wire rope.

6. The external excitation loading device for simulating the free flight state of a solid rocket motor according to claim 3, characterized in that: The suspension unit includes a hanger (2-11), a secondary horizontal T-slot (2-12), two guide transition plates (2-13), a secondary vertical T-slot (2-14), and two elastic clamping units (2-15); wherein, The bracket (2-11) is fixedly installed on the lower part of the connecting beam (1-4) through a primary sliding T-slot (1-5); The bottom end of the bracket (2-11) is provided with the secondary transverse T-slot (2-12). Both guide transition plates (2-13) are fixedly installed on the lower part of the bracket (2-11) through the secondary transverse T-slot (2-12); Both guide transition plates (2-13) are provided with the aforementioned secondary vertical T-slots (2-14); One elastic clamping unit (2-15) is fixedly installed on the inner side of a guide transition plate (2-13) through a secondary vertical T-slot (2-14) of a guide transition plate (2-13), and another elastic clamping unit (2-15) is fixedly installed on the inner side of another guide transition plate (2-13) through a secondary vertical T-slot (2-14) of another guide transition plate (2-13).

7. The external excitation loading device for simulating the free flight state of a solid rocket engine according to claim 6, characterized in that: One end of the test engine is positioned between two elastic clamping units (2-15) of a suspension unit, and the other end of the test engine is positioned between two elastic clamping units (2-15) of another suspension unit.

8. The external excitation loading device for simulating the free flight state of a solid rocket engine according to claim 4, characterized in that: The excitation unit includes an exciter (3-11), an excitation rod (3-12), an input monitoring unit (3-13), and a coupling module (3-14); wherein, One end of the excitation rod (3-12) is connected to the vibrator (3-11), and the other end of the excitation rod (3-12) is connected to the input monitoring unit (3-13). One end of the coupling module (3-14) is connected to the input monitoring unit (3-13), and the other end of the coupling module (3-14) is connected to the suspension mechanism (2).

9. The external excitation loading device for simulating the free flight state of a solid rocket engine according to claim 6, characterized in that: The elastic clamping unit (2-15) includes a mounting base (2-151), an elastic substrate (2-152), and a flexible clamp (2-153); wherein, The mounting base (2-151) is fixedly connected to the guide adapter plate (2-13); One end of the elastic substrate (2-152) is connected to the mounting base (2-151), and the other end of the elastic substrate (2-152) is connected to the flexible clamp (2-153).

10. The external excitation loading device for simulating the free flight state of a solid rocket motor according to claim 8, characterized in that: The coupling module (3-14) is made of resin material, and the top surface of the coupling module (3-14) is an arc-shaped curved surface. The top surface of the coupling module (3-14) is connected to the lower end face of the test engine housing by an adhesive. The adhesive is uniformly applied and cured for more than 30 minutes before being bonded to the test engine housing. The elastic matrix (2-152) is a vulcanized rubber material.

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