Test facility unit, engine-following thrust down vibration test system and method

Abstract

The application discloses a test mechanism unit for simulating follow-up thrust generated by an elongated body missile in a flight process; wherein the elongated body missile model comprises an aluminum rod and a test engine; in an initial state, a side column is connected with the second end of the test engine through an explosive bolt, the aluminum rod is bent, and the elongated body missile model is in a deformation state; after the explosive bolt is ignited and separated, the aluminum rod drives the test engine to move to the other side of the support frame, and at the same time, the test engine is ignited to generate follow-up thrust. The application further discloses an engine follow-up thrust vibration test system and method, a camera unit acquires a motion image of the elongated body missile model; a vibration test unit acquires vibration data; and a thrust test unit is used for acquiring the thrust of the elongated body missile model. The application solves the problem that a traditional engine ground static ignition test system cannot generate follow-up thrust, and realizes the simulation of the vibration condition of the elongated body missile after elastic deformation in flight.

Description

Technical Field

[0001] This invention relates to a test mechanism unit for generating follow-up thrust, a vibration test system and method for an engine under follow-up thrust, and particularly to a vibration test system and method for multi-size slender structures of a solid rocket engine under different follow-up thrust conditions, belonging to the field of engine testing technology. Background Technology

[0002] After solid rocket motor ignition, it generates axial thrust, which is generally negligible due to the elastic deformation of the missile body itself. However, with the trend towards larger aspect ratios in missiles, the missile structure becomes more flexible during flight, making it prone to significant elastic deformation. This deformation alters the thrust direction, creating servo thrust. In this case, the elastic deformation cannot be ignored. Therefore, studying the impact of servo thrust on the vibration of slender missile structures is of great significance. Currently, most domestic and international research on the vibration of slender structures under servo thrust does not consider the influence of the lateral component after engine ignition.

[0003] In traditional ground static ignition test systems for solid rocket engines, the engine is typically connected to a load-bearing block via connectors. After assembly and adjustment, the axial direction is not completely fixed, allowing for movement, while the lateral direction is completely fixed. This assembly configuration restricts the thrust generated to the axial direction, preventing the generation of follow-up thrust. For example, the sliding cylinder-type center frame for static testing of solid rocket engines, invented by Lu Junxing et al. (application number 201110321594.2), utilizes a precise dynamic fit between two sleeves and a guide key to achieve precise linear reciprocating motion of the center frame rollers without any wobbling. This easily ensures axis alignment during engine assembly and adjustment. After axis alignment, the engine is laterally fixed, and the thrust generated during static testing remains along the axial direction of the test frame, preventing the generation of follow-up thrust.

[0004] Therefore, it is urgent to develop a stable and reliable test system that can generate follow-up thrust, generate lateral components, and is suitable for the vibration of slender structures under the action of follow-up thrust of solid rocket engines. Summary of the Invention

[0005] The purpose of this invention is to overcome the above-mentioned defects and provide a test mechanism unit that solves the problem that traditional solid rocket engine ground static ignition test systems cannot generate lateral components and follow-up thrust, and can realize the simulation of the follow-up thrust generated by slender missiles during flight.

[0006] Another objective of this invention is to overcome the above-mentioned defects and provide a vibration test system and method under engine follow-up thrust, which solves the problem that traditional tests cannot evaluate the impact of follow-up thrust on missile vibration performance.

[0007] To achieve the above-mentioned objectives, the present invention provides the following technical solution:

[0008] A test mechanism unit for simulating the follow-up thrust generated by a slender missile during flight;

[0009] Includes: load-bearing pier, test stand, support frame, slender missile model, side columns and explosive bolts; the slender missile model includes an aluminum rod and a test engine, with the first end of the aluminum rod connected to the first end of the test engine;

[0010] The load-bearing pier is fixed to the ground; the test stand is fixedly connected to the load-bearing pier; the support frame and side columns are installed on the test stand, with the side columns located on one side of the support frame; the slender missile model is located above the test stand, with the second end of the aluminum rod connected to the load-bearing pier, and the second end of the test engine located on the support frame; in the initial state, the side columns and the second end of the test engine are connected by explosive bolts, the aluminum rod is bent, and the slender missile model is in a deformed state; after the explosive bolts are ignited and separated, the aluminum rod drives the test engine to move to the other side of the support frame, and at the same time the test engine is ignited, and the slender missile model generates a follow-up thrust on the load-bearing pier.

[0011] Furthermore, in the aforementioned test mechanism unit, the axial direction of the slender missile model in its non-deformed state is assumed to be the horizontal X direction;

[0012] In the initial state, the side column, the explosive bolt, and the second end of the test engine are connected by a steel wire rope. The bending degree of the aluminum rod is adjusted by adjusting the length of the steel wire rope. The direction of the steel wire rope is the horizontal Y direction, which is perpendicular to the X direction.

[0013] The upper surface of the support frame is provided with a horizontal slide rail along the Y direction. The second end of the test engine is installed on the upper surface of the support frame through a slider that cooperates with the horizontal slide rail. After the explosive bolt is ignited and separated, the aluminum rod drives the test engine to move along the horizontal slide rail to the other side of the support frame.

[0014] Furthermore, in the aforementioned test mechanism unit, explosion-proof glass is fixed to the upper surface of the support frame.

[0015] Furthermore, in the aforementioned test mechanism unit, a clamping device is provided at one end of the load-bearing pier. The clamping device is used to clamp the second end of the aluminum rod, and the length-to-diameter ratio of the slender missile model can be adjusted by adjusting the clamping length of the aluminum rod.

[0016] A vibration testing system for an engine under servo thrust includes a control unit, a camera unit, a vibration testing unit, a testing mechanism unit, and a thrust testing unit.

[0017] The test mechanism unit is the aforementioned test mechanism unit;

[0018] The control unit is used to control the ignition of the test engine, the ignition of the explosive bolts, the activation of the camera unit, the activation of the vibration test unit, and the activation of the thrust test unit. After the camera unit, vibration test unit, and thrust test unit are activated, the control unit controls the test engine and the explosive bolts to ignite simultaneously.

[0019] The camera unit is used to acquire motion images of the slender missile model;

[0020] The vibration testing unit is used to acquire vibration data of the slender missile model;

[0021] The thrust test unit is used to obtain the internal pressure of the test engine and the thrust of the slender missile model on the load-bearing pier.

[0022] Furthermore, in the aforementioned vibration test system for engine servo thrust, the test mechanism unit also includes a protective column and a camera frame mounted on the test stand;

[0023] The protective column is located on the outside of the aluminum rod and between the load-bearing pier and the support frame;

[0024] A camera stand is used to support the camera unit on a support frame.

[0025] Furthermore, in a vibration test system under engine servo thrust, the axial direction of the slender missile model in its non-deformation state is set to the horizontal X direction;

[0026] The test bench is equipped with a T-slot along the X direction. The support frame, side columns, protective columns and camera frame are slidably installed in the T-slot using T-bolts.

[0027] Furthermore, in the aforementioned vibration test system for engine servo thrust, the vibration test unit includes an acceleration sensor;

[0028] An accelerometer is fixed on an aluminum rod. The number of accelerometers is ≥1. When the number of accelerometers is >1, multiple accelerometers are distributed along the axial direction of the aluminum rod.

[0029] Furthermore, in the aforementioned vibration test system for engine servo thrust, the thrust test unit includes a pressure sensor for acquiring the internal pressure of the test engine and a thrust sensor for acquiring the thrust of the slender missile model. The pressure sensor is installed on the top cover located at the first end of the test engine, and the thrust sensor is installed at the connection between the aluminum rod and the load-bearing block, or more specifically, between the clamping device and the load-bearing block.

[0030] A vibration test method for an engine under servo thrust, implemented using the aforementioned engine under servo thrust vibration test system, includes:

[0031] In its initial state, the side column is connected to the second end of the test engine by explosive bolts, the aluminum rod is bent, and the slender missile model is in a deformed state;

[0032] After the test begins, the control unit controls the activation of the camera unit, vibration test unit, and thrust test unit. After the camera unit, vibration test unit, and thrust test unit are activated, the test engine and explosive bolts are simultaneously ignited.

[0033] The aluminum rod drives the test engine to move to the other side of the support frame. At the same time, the test engine generates thrust on the aluminum rod, and the slender missile model generates follow-up thrust on the load-bearing pier.

[0034] The camera unit acquires motion images of the slender missile model;

[0035] The vibration testing unit acquires vibration data from the slender missile model;

[0036] The thrust test unit acquires the internal pressure of the test engine and the thrust of the slender missile model on the load-bearing pier.

[0037] The impact of servo thrust on the vibration performance of the slender-body missile was evaluated based on the motion images and vibration data of the slender-body missile model; the combustion state of the propellant surface inside the test engine was monitored based on the internal pressure of the test engine; the thrust of the slender-body missile model on the load-bearing pier was controlled by adjusting the amount of propellant and the combustion rate in the test engine, and test runs of the slender-body missile model under different thrust conditions were carried out.

[0038] Compared with the prior art, the present invention has at least one of the following advantages:

[0039] (1) This invention creatively proposes a test mechanism unit for simulating follow-up thrust. By combining a test engine and an aluminum rod, it simulates a missile with a slender body structure. It fully considers the key features of the slender body structure and performs structural equivalence and simplification, thereby realizing the accurate simulation of the follow-up thrust generated by the slender body missile during flight.

[0040] (2) In the test mechanism unit of the present invention, the lateral component is generated by releasing the slender body structure in a bent state by the explosive bolt, and the axial thrust is generated after the test engine is triggered and ignited. The two are superimposed to form a follow-up thrust, which provides a basis for analyzing the vibration after elastic deformation during the flight of a missile with a large length-to-diameter ratio.

[0041] (3) The present invention can change the thrust by adjusting the amount of propellant and the combustion rate of the engine, change the length-to-diameter ratio by the length of the aluminum rod, and change the lateral component by the initial bending angle of the slender body structure. It is flexible in operation, has a wide range of applications, and has the characteristics of quantitative analysis. Attached Figure Description

[0042] Figure 1 This is a schematic diagram of a test system for engine servo thrust in a preferred embodiment of the present invention;

[0043] Figure 2 This is a three-dimensional structural diagram of the test mechanism unit in a preferred embodiment of the present invention;

[0044] Figure 3 This is a schematic diagram of the front view of the test mechanism unit in a preferred embodiment of the present invention;

[0045] Figure 4 This is a top view of the test mechanism unit in a preferred embodiment of the present invention.

[0046] Figure 5 This is a top view of the experimental mechanism unit in one state according to a preferred embodiment of the present invention;

[0047] Figure 6 This is a top view of the test mechanism unit in another state according to a preferred embodiment of the present invention;

[0048] In the diagram, 1-control unit, 2-camera unit, 3-vibration test unit, 4-test mechanism unit, 5-thrust test unit, 2-1-high-speed camera, 3-1-accelerometer sensor, 4-1-test bench, 4-2-support frame, 4-3-explosion-proof glass, 4-4-test engine, 4-5-camera stand, 4-6-protective cover, 4-7-aluminum rod, 4-8-clamping device, 4-9-load-bearing block, 4-10-protective column, 4-11-side column, 4-12-explosion bolt, 4-13-slider, 5-1-pressure sensor, 5-2-thrust sensor. Detailed Implementation

[0049] The features and advantages of the present invention will become clearer and more apparent from the following detailed description.

[0050] The term “exemplary” as used herein means “serving as an example, embodiment, or illustration.” Any embodiment illustrated herein as “exemplary” is not necessarily to be construed as superior to or better than other embodiments. Although various aspects of embodiments are shown in the accompanying drawings, the drawings are not necessarily drawn to scale unless specifically indicated otherwise.

[0051] This invention provides a vibration testing system for slender structures under the action of engine follow-up thrust. This system can generate follow-up thrust after engine ignition to test the vibration of slender structures.

[0052] Specifically, such as Figure 1As shown, the present invention provides a vibration test system for a slender body structure under the action of engine follow-up thrust, comprising a control unit 1, a camera unit 2, a vibration test unit 3, a test mechanism unit 4, and a thrust test unit 5.

[0053] Control unit 1 is used to control the entire test process and set the test sequence.

[0054] The camera unit 2 includes a computer with high-speed camera software installed and a high-speed camera 2-1. The high-speed camera needs to be higher than 500 frames per second.

[0055] The vibration testing unit 3 includes a computer with vibration testing software installed, a vibration data acquisition instrument, and an acceleration sensor 3-1.

[0056] like Figure 2 As shown, in a preferred embodiment, the test mechanism unit 4 includes a load-bearing block 4-9 fixed to the ground, a test bench 4-1 connected to the load-bearing block 4-9, a thrust sensor 5-2 installed on the right side of the load-bearing block 4-9, a clamping device 4-8 fixedly connected to the thrust sensor 5-2, an aluminum rod 4-7 installed on the clamping device 4-8, a protective column 4-10 located on the test bench 4-1 and spanning both sides of the aluminum rod 4-7, a support frame 4-2 installed on the test bench 4-1 and located on the right side of the protective column 4-10, and a support frame 4-2 fixed to the upper surface of the support frame 4-2. The invention comprises: explosion-proof glass 4-3; a test engine 4-4 connected to aluminum rod 4-7 and located above the explosion-proof glass 4-3; a circular slider 4-13 fixed below the test engine 4-4 and sliding on the explosion-proof glass 4-3; a camera frame 4-5 fixed on the test stand 4-1 and spanning both sides of the test engine 4-4; a protective cover 4-6 installed at the center of the camera frame 4-5; a side column 4-11 fixed to the test stand 4-1 and located in front of the support frame 4-2; and explosion bolts 4-12 connecting the test engine 4-4 and the side column 4-11. The reason for using aluminum rods in this invention is that aluminum rods are rust-resistant and highly flexible, primarily to simulate the slender design of an engine. It would be difficult to achieve this flexible state under static ignition testing conditions using a real engine.

[0057] The thrust test unit 5 includes a computer with thrust test software installed, a thrust data acquisition instrument, and pressure sensor 5-1 and thrust sensor 5-2.

[0058] Optionally, the test timing set by the control unit 1 includes signal triggering B of the high-speed camera unit 2, signal triggering E of the explosive bolt 4-12, signal triggering A of the vibration test unit 3, signal triggering C of the thrust test unit 5, and ignition triggering D of the test engine 4-4, with the triggering order being ABC followed by DE.

[0059] Optionally, a high-speed camera 2-1 is installed inside a protective housing 4-6 and connected to a computer with high-speed camera software installed to record the entire test process.

[0060] Optionally, the number of accelerometers 3-1 is determined according to the test requirements, and they are installed on aluminum rods 4-7 and connected to the vibration data acquisition instrument via connecting cables. The vibration data acquisition instrument is connected to a computer with the vibration testing software installed.

[0061] Optionally, the test bench 4-1 is equipped with a T-slot, and several T-bolts are used to fix the protective column 4-10, camera frame 4-5, support frame 4-2, and side column 4-11 respectively, and the positions of these parts can be adjusted; the side column 4-11 and the explosive bolt 4-12 are connected to the engine by a steel wire rope, and the steel wire rope is kept horizontal. The bending angle of the aluminum rod 4-7 is adjusted by controlling the length of the steel wire rope; the clamping device 4-8 is equipped with 5 pairs of clamping bolts, which can adjust the clamping length of the aluminum rod 4-7; the center of gravity of the test engine 4-4, the center of gravity of the aluminum rod 4-7, and the center of gravity of the explosive bolt 4-12 are on the same horizontal plane, and the connection and combination of the test engine 4-4 and the aluminum rod 4-7 is used to simulate the slender structure of the engine.

[0062] Optionally, two pressure sensors 5-1 are symmetrically mounted on the top cover of the test engine 4-4, and a thrust sensor 5-2 is mounted between the clamping device 4-8 and the load-bearing block 4-9, both connected to the force data acquisition instrument via connecting cables. The force data acquisition instrument is connected to a computer with the force testing software installed.

[0063] This invention proposes a vibration testing system for a slender structure under the action of engine-driven thrust. It simulates a missile with a slender structure using a combination of a test engine and an aluminum rod. After the explosive bolt is triggered and ignited by the control unit, the slender structure, which is in a bent state, is released. After release, the test engine slides horizontally laterally on the upper surface of the support frame, supported by a slider. Simultaneously, the test engine generates thrust after being triggered and ignited. This thrust becomes a driven thrust as the engine continues to slide. The camera unit, vibration testing unit, and thrust testing unit record relevant test data after being triggered. This invention can apply a lateral component to the thrust, which is always maintained in one direction in traditional tests, simulating the vibration of a large aspect ratio missile after elastic deformation during flight. Furthermore, this invention can change the thrust by adjusting the engine propellant charge, change the aspect ratio by adjusting the length of the aluminum rod, and change the magnitude of the lateral component by adjusting the initial bending angle of the slender structure, providing quantitative analysis capabilities. Pressure measurement is used to monitor the combustion of the propellant surface within the engine and confirm that it is in a normal combustion state.

[0064] Figure 1The schematic diagram shown illustrates a vibration testing system for a slender structure under the action of engine-driven thrust. It includes a control unit 1, a high-speed camera unit 2, a vibration testing unit 3, a testing mechanism unit 4, and a thrust testing unit 5. The control unit 1 controls the entire testing process and sets the testing sequence. The high-speed camera unit 2 includes a computer with installed high-speed camera software and a high-speed camera 2-1. The vibration testing unit 3 includes a computer with installed vibration testing software, a vibration data acquisition device, and an acceleration sensor 3-1. The thrust testing unit 5 includes a computer with installed thrust testing software, a thrust data acquisition device, and a pressure sensor 5-1.

[0065] The control unit, high-speed camera unit, vibration testing unit, test mechanism unit, and thrust testing unit of the present invention are, respectively, a control mechanism, a high-speed camera mechanism, a vibration testing mechanism, a test mechanism, and a thrust testing mechanism.

[0066] Example:

[0067] This embodiment will combine Figures 1-6 The technical solution of the present invention will be described in detail below.

[0068] like Figure 1 As shown, the test sequence includes signal triggering B of high-speed camera unit 2, signal triggering E of explosive bolt 4-12, signal triggering A of vibration test unit 3, signal triggering C of thrust test unit 5, and ignition triggering D of engine 4-4. The triggering order is ABC followed by DE.

[0069] like Figure 2As shown, the test mechanism unit 4 includes a load-bearing pier 4-9 fixed to the ground, a test bench 4-1 connected to the load-bearing pier 4-9, a clamping device 4-8 installed on the right side of the load-bearing pier 4-9, an aluminum rod 4-7 installed on the clamping device 4-8, protective columns 4-10 located on the test bench 4-1 and spanning both sides of the aluminum rod 4-7, a support frame 4-2 installed on the test bench 4-1 and located on the right side of the protective column 4-10, explosion-proof glass 4-3 fixed to the upper surface of the support frame 4-2, and a connection to the aluminum rod 4-7. The test engine 4-4 is located above the explosion-proof glass 4-3; a circular slider 4-13 is fixed below the test engine 4-4 and can slide on the explosion-proof glass 4-3; a camera frame 4-5 is fixed on the test bench 4-1 and spans both sides of the engine 4-4; a protective cover 4-6 is installed at the center position above the camera frame 4-5; a side column 4-11 is fixed on the test bench 4-1 and located in front of the support frame 4-2; and an explosion bolt 4-12 connects the test engine 4-4 and the side column 4-11. The test stand 4-1 is equipped with T-slots, and several T-bolts are used to fix the protective column 4-10, camera frame 4-5, support frame 4-2, and side column 4-11 respectively, and the positions of these parts can be adjusted. The side column 4-11, explosive bolt 4-12 and test engine 4-4 are connected by steel wire rope, and the steel wire rope is kept horizontal. The bending angle of aluminum rod 4-7 is adjusted by controlling the length of the steel wire rope. The clamping device 4-8 is equipped with 5 pairs of clamping bolts, which can adjust the clamping length of aluminum rod 4-7. The center of gravity of test engine 4-4, center of gravity of aluminum rod 4-7 and center of gravity of explosive bolt 4-12 are on the same horizontal plane. The connection and combination of test engine 4-4 and aluminum rod 4-7 simulates the slender structure of missile.

[0070] like Figure 3 and Figure 1 As shown, the number of accelerometers 3-1 is determined according to the test requirements, and they are installed on the side surface of aluminum rod 4-7, and connected to the vibration data acquisition instrument via connecting cables. The vibration data acquisition instrument is connected to a computer with the vibration testing software installed.

[0071] like Figure 4 and Figure 1 As shown, two pressure sensors 5-1 are symmetrically mounted on the top cover of the test engine 4-4, and a thrust sensor 5-2 is mounted between the clamping device 4-8 and the load-bearing block 4-9. Both are connected to the force data acquisition instrument via connecting cables. The force data acquisition instrument is connected to a computer with the force testing software installed.

[0072] like Figure 4 As shown, the high-speed camera 2-1 is installed inside the protective housing 4-6 and connected to a computer with high-speed camera software installed, used to film the entire test process.

[0073] The working process of this invention is as follows: according to Figure 1 The schematic diagram of the test system shown illustrates the installation and debugging of each unit, with the test sequence recorded in control unit 1. After the test begins, control unit 1 simultaneously triggers camera unit 2, vibration test unit 3, and thrust test unit 5, and then simultaneously triggers the explosive bolt 4-12 and test engine 4-4. After the explosive bolt 4-12 separates, the test engine 4-4 is released and slides horizontally across the upper surface of the explosion-proof glass 4-3 via the circular slider 4-13, reaching... Figure 5 and Figure 6 The two states shown. Figure 5 The image shows the test engine 4-4 positioned exactly at the center axial position of the test stand 4-1. Figure 6 The image shows the farthest position of the test engine 4-4 as it slides to the other side. The ignition of the explosive bolt 4-12 simultaneously triggers the ignition of the test engine 4-4, superimposing the horizontal sliding process of the test engine 4-4 with the axial thrust generated by combustion, thus producing the required follow-up thrust. During this process, the aluminum rod 4-7 continuously undergoes dynamic bending deformation, and all test units are operational. Once all the propellant in the test engine 4-4 has ignited and the test engine 4-4 stops sliding, all test units are stopped and the data is saved. During the test, the thrust output amplitude can be controlled by adjusting the amount of propellant and the burning rate in the test engine 4-4, allowing for test runs of the slender missile model under different thrust conditions.

[0074] Finally, the collected data or images are analyzed and processed using their respective testing software to generate a test report, thus completing the test. Specifically, the impact of servo thrust on the vibration performance of slender missiles can be evaluated based on images and vibration data.

[0075] The present invention has been described in detail above with reference to specific embodiments and exemplary examples; however, these descriptions should not be construed as limiting the present invention. Those skilled in the art will understand that various equivalent substitutions, modifications, or improvements can be made to the technical solutions and embodiments of the present invention without departing from the spirit and scope of the invention, and all such modifications and improvements fall within the scope of the present invention. The scope of protection of the present invention is defined by the appended claims.

[0076] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A test rig unit, characterized by The application relates to a device for simulating the follow-up thrust generated by an elongated body missile during flight. The device comprises a supporting pier (4-9), a testbed (4-1), a support frame (4-2), an elongated body missile model, a side column (4-11) and an explosive bolt (4-12); the elongated body missile model comprises an aluminum rod (4-7) and a test engine (4-4), and the first end of the aluminum rod (4-7) is connected with the first end of the test engine (4-4); The supporting pier (4-9) is fixed to the ground; the testbed (4-1) is fixedly connected with the supporting pier (4-9); the support frame (4-2) and the side column (4-11) are installed on the testbed (4-1), and the side column (4-11) is arranged on one side of the support frame (4-2); the elongated body missile model is located above the testbed (4-1), the second end of the aluminum rod (4-7) is connected with the supporting pier (4-9), and the second end of the test engine (4-4) is located on the support frame (4-2); in the initial state, the side column (4-11) and the second end of the test engine (4-4) are connected through the explosive bolt (4-12), the aluminum rod (4-7) is bent, and the elongated body missile model is in a deformed state; after the explosive bolt (4-12) is ignited and separated, the aluminum rod (4-7) drives the test engine (4-4) to move to the other side of the support frame (4-2), meanwhile, the test engine (4-4) is ignited, and the elongated body missile model generates follow-up thrust on the supporting pier (4-9); The axial direction of the elongated body missile model in a non-deformed state is the horizontal X direction; In the initial state, the side column (4-11) and the explosive bolt (4-12) and the explosive bolt (4-12) and the second end of the test engine (4-4) are connected through steel wires, and the bending degree of the aluminum rod (4-7) is adjusted by adjusting the length of the steel wires; the direction of the steel wires is the horizontal Y direction, and the Y direction is perpendicular to the X direction; A horizontal slide rail along the Y direction is arranged on the upper surface of the support frame (4-2), the second end of the test engine (4-4) is installed on the upper surface of the support frame (4-2) through a sliding block (4-13) matched with the horizontal slide rail, and after the explosive bolt (4-12) is ignited and separated, the aluminum rod (4-7) drives the test engine (4-4) to move along the horizontal slide rail to the other side of the support frame (4-2); An explosion-proof glass (4-3) is fixed to the upper surface of the support frame (4-2).

2. A test mechanism unit according to claim 1, characterized in that One end of the supporting pier (4-9) is provided with a clamping device (4-8) for clamping the second end of the aluminum rod (4-7), and the length-diameter ratio of the elongated body missile model is adjusted by adjusting the clamping length of the aluminum rod (4-7).

3. An engine follow-up thrust down vibration test system characterized by, The device comprises a control unit (1), a camera unit (2), a vibration test unit (3), a test mechanism unit (4) and a thrust test unit (5); The test mechanism unit (4) is the test mechanism unit in claim 1 or 2; The test mechanism unit (4) is the test mechanism unit in claim 1 or 2. The control unit (1) is used for controlling ignition of the test engine (4-4), ignition of the explosion bolt (4-12), opening of the camera unit (2), opening of the vibration test unit (3) and opening of the thrust test unit (5), and the test engine (4-4) and the explosion bolt (4-12) are ignited simultaneously after the camera unit (2), the vibration test unit (3) and the thrust test unit (5) are opened; The camera unit (2) is used for acquiring a motion image of the slender body missile model; The vibration test unit (3) is used for acquiring vibration data of the slender body missile model; The thrust test unit (5) is used for acquiring internal pressure of the test engine (4-4) and thrust of the slender body missile model on the bearing pier (4-9); The thrust test unit (5) comprises a pressure sensor (5-1) used for acquiring the internal pressure of the test engine (4-4) and a thrust sensor (5-2) used for acquiring the thrust of the slender body missile model, the pressure sensor (5-1) is installed on a top cover located at a first end of the test engine (4-4), and the thrust sensor (5-2) is installed at a connection position of the aluminum rod (4-7) and the bearing pier (4-9).

4. The engine follow-up thrust down vibration test system according to claim 3, characterized in that, The test mechanism unit (4) further comprises a protective column (4-10) and a camera frame (4-5) installed on the test bed (4-1); The protective column (4-10) is arranged outside the aluminum rod (4-7) and between the bearing pier (4-9) and the support frame (4-2); The camera frame (4-5) is used for supporting the camera unit (2) above the support frame (4-2).

5. The engine follow-up thrust down vibration test system according to claim 4, characterized in that, The axial direction of the slender body missile model in a non-deformation state is the horizontal X direction; The test bed (4-1) is provided with a T-shaped groove in the X direction, and the support frame (4-2), the side column (4-11), the protective column (4-10) and the camera frame (4-5) are slidably installed in the T-shaped groove by using T-shaped bolts.

6. The engine follow-up thrust down vibration test system according to claim 3, wherein The vibration test unit (3) comprises an acceleration sensor (3-1); The acceleration sensor (3-1) is fixed on the aluminum rod (4-7), and the number of the acceleration sensor (3-1) is greater than or equal to 1, and when the number of the acceleration sensor (3-1) is greater than 1, the plurality of acceleration sensors (3-1) are distributed along the axial direction of the aluminum rod (4-7).

7. An engine follow-up thrust down vibration test method characterized by, The engine follow-up thrust vibration test system is realized by using the engine of any one of claims 3-6, comprising: In an initial state, the side column (4-11) is connected with the second end of the test engine (4-4) through the explosion bolt (4-12), the aluminum rod (4-7) is bent, and the slender body missile model is in a deformation state; After the test starts, the control unit (1) controls the opening of the camera unit (2), the vibration test unit (3) and the thrust test unit (5), and the test engine (4-4) and the explosion bolt (4-12) are ignited simultaneously after the camera unit (2), the vibration test unit (3) and the thrust test unit (5) are opened; The aluminum rod (4-7) drives the test engine (4-4) to move to the other side of the support frame (4-2), and at the same time, the test engine (4-4) generates a thrust on the aluminum rod (4-7), and the slender body missile model generates a follow-up thrust on the bearing pier (4-9); The camera unit (2) acquires the motion image of the slender body missile model; The vibration test unit (3) acquires the vibration data of the slender body missile model; The thrust test unit (5) acquires the internal pressure of the test engine (4-4) and the thrust of the slender body missile model on the bearing pier (4-9); According to the motion image of the slender body missile model and the vibration data of the slender body missile model, the influence of the follow-up thrust on the vibration performance of the slender body missile is evaluated; according to the internal pressure of the test engine (4-4), the burning state of the propellant surface in the test engine (4-4) is monitored; by adjusting the amount of propellant and the burning rate in the test engine (4-4), the thrust of the slender body missile model on the bearing pier (4-9) is controlled, and the test run test of the slender body missile model under different thrust conditions is carried out.

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