An engine test device under vibration environment

Abstract

The invention relates to an engine test device under a vibration environment, belonging to the field of engine vibration test; the device comprises a basic platform, a transition platform, a bearing pier, a bearing plate, a buffer bearing seat, a transition bearing seat, a thrust sensor, a transition frame, a left bearing support roller, a right bearing support roller, a front pressure roller unit, a rear pressure roller unit, a pressure roller, an exciting unit, an excitation rod, an arc contact block, a protective cover, an elastic support left unit and an elastic support right unit; the purpose is to provide a test system device that can simulate the free state of an engine flight test to a certain extent, realize the engine ground static test under a vibration environment, and provide technical support for conducting a combustion response study of an engine under a vibration environment.

Description

Technical Field

[0001] The invention belongs to the field of engine vibration test and relates to an engine running test device under a vibration environment. Background Art

[0002] In recent years, solid engines for air defense and anti-missile missiles have adopted large loading, high pressure, and large aspect ratio design conditions to improve performance. Under flight overload conditions, the reliability of the missile is reduced, which easily leads to unstable combustion problems in the engine. Unstable combustion is one of the important basic technical problems that restrict the development of solid engines, and has a negative impact on the guidance and control of missiles.

[0003] In order to analyze the causes of unstable combustion of solid motors and solve the problem of unstable combustion through effective technical improvement measures, it is first necessary to establish the ignition working state of solid motors in a vibration environment, that is, to simulate the free state of flight tests to a certain extent during the ground static test of the engine, and conduct research on the combustion response of the engine in a vibration environment. The study of engine combustion response in a vibration environment is to apply external vibration excitation during the ground ignition of the engine, obtain the actual combustion response results of the engine under the external excitation loading state, obtain the actual combustion response results of the engine by monitoring the thrust and vibration response data during the operation of the engine, and evaluate the impact of external vibration on engine combustion.

[0004] A rocket engine ground dynamic ignition test device and method with application number CN202010294094.3 and announcement date 2020.07.10, the device includes a control unit, a mounting frame, an excitation unit, a thrust bench, an equipment foundation and a power unit. The ground dynamic ignition test device and method of the rocket engine ground dynamic ignition test device proposed in the ground dynamic ignition test device adopts three clamps to completely fasten the engine, fails to give the structure a certain degree of freedom, and it is difficult to simulate the free state of the engine during the flight test. It is not suitable for the study of combustion response under the engine vibration environment. In addition, only the constraint of preventing the loading bench from being pushed away from the excitation position by the engine is considered, and the safety protection requirements of the engine and the test system equipment in the excitation state are not considered.

[0005] Therefore, based on the actual situation and combined with the test site, it is imperative to develop a stable and reliable engine test system device under a vibration environment. Improving the current test status of solid rocket engines will help accelerate the solution to the unstable combustion process of solid engines. Summary of the invention

[0006] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art and to propose an engine test device under a vibration environment, which can simulate the free state of an engine flight test to a certain extent and realize a ground stationary test of the engine under a vibration environment.

[0007] The solution of the present invention is:

[0008] An engine test device under a vibration environment comprises a base platform, a transition platform, a bearing pier, a bearing plate, a buffer bearing seat, a transition bearing seat, a thrust sensor, a transition frame, a left bearing support roller, a right bearing support roller, a front pressure roller unit, a rear pressure roller unit, a pressure roller, an exciting unit, an excitation rod, an arc contact block, a protective cover, an elastic support left unit and an elastic support right unit;

[0009] The base platform is a horizontally placed plate-like structure; the bearing pier is a rectangular parallelepiped structure; the bearing pier is horizontally arranged at the side wall of the base platform and is fixedly connected to the base platform; the transition platform is a horizontally placed plate-like structure; the transition platform is placed on the upper surface of the base platform; a plate-like groove is arranged at the side wall of the bearing pier facing the base platform, and the bearing plate is vertically embedded in the plate-like groove;

[0010] The buffer bearing seat is connected to the bearing plate; the transition bearing seat is connected to the buffer bearing seat; the thrust sensor is installed at the center of the side wall of the transition bearing seat; the transition frame is an annular structure, one axial end of the transition frame is connected to the thrust sensor, and the other axial end of the transition frame is coaxially connected to the external solid rocket engine; the left bearing support roller and the right bearing support roller are both arranged at the bottom end of the external solid rocket engine; and the left bearing support roller is close to the thrust sensor, and the right bearing support roller is far away from the right bearing support roller; the front pressure wheel unit and the rear pressure wheel unit are symmetrically arranged on both sides of the external solid rocket engine; the axial ends of the pressure wheel are respectively connected to the top side walls of the front pressure wheel unit and the rear pressure wheel unit; the pressure wheel Pressed on the top of the external solid rocket engine; the excitation unit is axially and vertically fixedly installed on the upper surface of the transition platform; the excitation unit is located below the middle of the external solid rocket engine; the excitation rod is axially and vertically connected to the output end of the excitation unit; the arc contact block is fixedly installed on the top of the excitation rod; the arc contact block is in contact with the bottom of the external solid rocket engine; the protective cover covers the outer wall of the excitation unit; the elastic support left unit and the elastic support right unit are arranged along the axial direction of the external solid rocket engine, the elastic support left unit is located on the upper surface of the transition platform between the left load-bearing support roller and the excitation unit; the elastic support right unit is located on the upper surface of the transition platform between the excitation unit and the right load-bearing support roller.

[0011] In the above-mentioned engine test device under a vibration environment, the arc contact block is an arc plate structure, and the arc of the upper surface of the arc contact block is adapted to the outer wall of the external solid rocket engine.

[0012] In the above-mentioned engine running test device under a vibration environment, the arc-shaped contact block and the pressure wheel correspond in vertical position.

[0013] In the above-mentioned engine test device under a vibration environment, the front pressure roller unit and the rear pressure roller unit have the same structure; the front pressure roller unit includes a front pressure roller frame, support ribs and a support frame; wherein the front pressure roller frame is vertically fixedly installed on the upper surface of the transition platform; the support ribs are arranged on the inner side wall of the front pressure roller frame to strengthen the connection between the front pressure roller frame and the transition platform; the support frame is arranged on the top inner side wall of the front pressure roller frame; the support frame is butt-jointed with one axial end of the pressure roller.

[0014] In the above-mentioned engine test device under a vibration environment, the elastic support left unit and the elastic support right unit have the same structure; the elastic support left unit includes a lower support plate, two protective side plates, a protective upper plate, a balance plate, two guide rods, two groups of lower vibration isolation airbags, two groups of upper vibration isolation airbags, a positioning rod and a protective ring;

[0015] The lower support plate is placed horizontally; the two protective side plates are vertically fixedly installed on both sides of the upper surface of the lower support plate; the protective upper plate is horizontally placed on the top of the two protective side plates; the lower support plate, the two protective side plates and the protective upper plate form a cavity structure; the balance plate is horizontally arranged in the middle of the cavity structure; the positioning rod is vertically fixedly installed at the center of the upper surface of the lower support plate; and the axial top end of the positioning rod extends out of the protective upper plate; the protective collar is fixedly installed on the top of the positioning rod; the two guide rods are both arranged inside the cavity structure, and the two guide rods are symmetrically arranged on both sides of the positioning rod; each guide rod is correspondingly installed with a group of lower vibration isolation airbags and a group of upper vibration isolation airbags; wherein, the lower vibration isolation airbag is arranged in the cavity between the balance plate and the lower support plate, and the upper vibration isolation airbag is arranged in the cavity between the balance plate and the protective upper plate.

[0016] In the above-mentioned engine test device under a vibration environment, each group of lower vibration isolation airbags includes two lower vibration isolation airbags, and the two lower vibration isolation airbags are placed vertically overlapping; each group of upper vibration isolation airbags includes two upper vibration isolation airbags, and the two upper vibration isolation airbags are placed vertically overlapping.

[0017] In the above-mentioned engine test device under a vibration environment, the inner diameter of the protective ring is larger than the outer wall of the external solid rocket engine, and the protective ring is sleeved on the outer wall of the external solid rocket engine.

[0018] In the engine test device under the above-mentioned vibration environment, the excitation unit drives the excitation rod to perform a vibration test on the external solid rocket engine below the middle part of the external solid rocket engine through the arc contact block.

[0019] In the above-mentioned vibration environment, the engine test device adaptively adjusts the axial displacement of the external solid rocket engine during the vibration test through the left load-bearing support roller and the right load-bearing support roller; and realizes vertical buffering of the external solid rocket engine during the vibration test through the elastic support left unit and the elastic support right unit.

[0020] In the above-mentioned engine test device under a vibration environment, the thrust sensor is used to measure the test force of the external solid rocket engine during the vibration test.

[0021] The beneficial effects of the present invention compared with the prior art are:

[0022] (1) During operation, the present invention can simulate the free state of the engine flight test to a certain extent by providing the left load-bearing support roller, the right load-bearing support roller and the pressure wheel in contact with the engine;

[0023] (2) The present invention avoids the risk of the engine becoming unstable or rolling over under the action of the exciting force during operation by providing elastically supporting the left unit and elastically supporting the right unit protection devices on both sides of the exciting mechanism;

[0024] (3) The present invention provides T-slots on the base platform and the transition platform, which helps to ensure that the thrust test mechanism and the elastic support protection mechanism are adjusted around the center of mass of the engine during installation and adjustment, thereby ensuring the safety of the test. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a side view of the testing device of the present invention;

[0026] Figure 2 This is a front view of the testing device of the present invention;

[0027] Figure 3 A top view of the testing device of the present invention;

[0028] Figure 4 This is a schematic diagram of the structure of the front pressure wheel unit of the present invention;

[0029] Figure 5 This is a schematic diagram of the elastic support left unit structure of the present invention;

[0030] Figure 6 It is a schematic diagram of the top view of the basic platform of the present invention. DETAILED DESCRIPTION

[0031] The present invention will be further described below in conjunction with the embodiments.

[0032] The present invention provides an engine test system device under a vibration environment, which can simulate the free state of an engine flight test to a certain extent and realize a ground static test of the engine under a vibration environment.

[0033] Engine test equipment under vibration environment, such as Figure 1 , Figure 2 , Figure 3As shown, it includes a basic platform body 1-1, a transition platform body 1-2, a load-bearing pier 1-3, a load-bearing plate 1-4, a buffer load-bearing seat 2-1, a transition load-bearing seat 2-2, a thrust sensor 2-4, a transition frame 2-5, a left load-bearing support roller 2-7, a right load-bearing support roller 2-8, a front pressure wheel unit 2-9, a rear pressure wheel unit 2-10, a pressure wheel 2-11, an excitation unit 3-1, an excitation rod 3-2, an arc contact block 3-3, a protective cover 4-1, an elastic support left unit 4-2 and an elastic support right unit 4-3.

[0034] Among them, the base platform 1-1 is a horizontally placed plate-like structure; the load-bearing pier 1-3 is a rectangular structure; the load-bearing pier 1-3 is horizontally arranged at the side wall of the base platform 1-1 and is fixedly connected to the base platform 1-1; the transition platform 1-2 is a horizontally placed plate-like structure; the transition platform 1-2 is placed on the upper surface of the base platform 1-1; the load-bearing pier 1-3 is provided with a plate-like groove at the side wall facing the base platform 1-1, and the load-bearing plate 1-4 is vertically embedded in the plate-like groove.

[0035] The buffer bearing seat 2-1 is docked with the bearing plate 1-4; the transition bearing seat 2-2 is docked with the buffer bearing seat 2-1; the thrust sensor 2-4 is installed at the center of the side wall of the transition bearing seat 2-2; the transition frame 2-5 is an annular structure, one axial end of the transition frame 2-5 is docked with the thrust sensor 2-4, and the other axial end of the transition frame 2-5 is coaxially docked with the external solid rocket engine; the left bearing support roller 2-7 and the right bearing support roller 2-8 are both arranged at the bottom end of the external solid rocket engine; and the left bearing support roller 2-7 is close to the thrust sensor 2-4, and the right bearing support roller 2-8 is far away from the right bearing support roller 2-8; the front pressure wheel unit 2-9 and the rear pressure wheel unit 2-10 are symmetrically arranged on the external solid rocket engine. The two sides of the rocket engine; the axial ends of the pressure wheel 2-11 are respectively connected to the top side walls of the front pressure wheel unit 2-9 and the rear pressure wheel unit 2-10; the pressure wheel 2-11 presses on the top of the external solid rocket engine; the excitation unit 3-1 is axially and vertically fixedly installed on the upper surface of the transition platform 1-2; the excitation unit 3-1 is located below the middle of the external solid rocket engine; the excitation rod 3-2 is axially and vertically connected to the output end of the excitation unit 3-1; the arc contact block 3-3 is fixedly installed on the top of the excitation rod 3-2; the arc contact block 3-3 contacts the bottom of the external solid rocket engine; the arc contact block 3-3 is an arc plate-like structure, and the arc of the upper surface of the arc contact block 3-3 is adapted to the outer wall of the external solid rocket engine. The arc contact block 3-3 corresponds to the pressure wheel 2-11 in the vertical direction. The protective cover 4-1 covers the outer wall of the excitation unit 3-1; the elastic support left unit 4-2 and the elastic support right unit 4-3 are arranged along the axial direction of the external solid rocket engine, the elastic support left unit 4-2 is located on the upper surface of the transition platform 1-2 between the left load-bearing support roller 2-7 and the excitation unit 3-1; the elastic support right unit 4-3 is located on the upper surface of the transition platform 1-2 between the excitation unit 3-1 and the right load-bearing support roller 2-8. The thrust sensor 2-4 is used to measure the test force of the external solid rocket engine during the excitation test.

[0036] like Figure 4 As shown, the front pressure wheel unit 2-9 has the same structure as the rear pressure wheel unit 2-10; the front pressure wheel unit 2-9 includes a front pressure wheel frame 2-91, a support rib 2-92 and a support frame 2-93; wherein the front pressure wheel frame 2-91 is vertically fixedly installed on the upper surface of the transition platform 1-2; the support rib 2-92 is arranged on the inner side wall of the front pressure wheel frame 2-91 to strengthen the connection between the front pressure wheel frame 2-91 and the transition platform 1-2; the support frame 2-93 is arranged on the top inner side wall of the front pressure wheel frame 2-91; the support frame 2-93 is connected to one axial end of the pressure wheel 2-11.

[0037] like Figure 5As shown, the elastic support left unit 4-2 and the elastic support right unit 4-3 have the same structure; the elastic support left unit 4-2 includes a lower support plate 4-21, two protective side plates 4-22, a protective upper plate 4-23, a balance plate 4-24, two guide rods 4-25, two groups of lower vibration isolation airbags 4-26, two groups of upper vibration isolation airbags 4-27, a positioning rod 4-28 and a protective ring 4-30;

[0038] The lower support plate 4-21 is placed horizontally; the two protective side plates 4-22 are vertically fixedly installed on the two sides of the upper surface of the lower support plate 4-21; the protective upper plate 4-23 is horizontally placed on the top of the two protective side plates 4-22; the lower support plate 4-21, the two protective side plates 4-22, and the protective upper plate 4-23 form a cavity structure; the balance plate 4-24 is horizontally arranged in the middle of the cavity structure; the positioning rod 4-28 is vertically fixedly installed at the center of the upper surface of the lower support plate 4-21; and the axial top end of the positioning rod 4-28 extends out of the protective upper plate 4- 23; the protective collar 4-30 is fixedly installed on the top of the positioning rod 4-28; the two guide rods 4-25 are both arranged inside the cavity structure, and the two guide rods 4-25 are symmetrically arranged on both sides of the positioning rod 4-28; each guide rod 4-25 is correspondingly installed with a group of lower vibration isolation airbags 4-26 and a group of upper vibration isolation airbags 4-27; wherein, the lower vibration isolation airbag 4-26 is arranged in the cavity between the balance plate 4-24 and the lower support plate 4-21, and the upper vibration isolation airbag 4-27 is arranged in the cavity between the balance plate 4-24 and the protective upper plate 4-23.

[0039] Each group of lower vibration isolation airbags 4-26 includes two lower vibration isolation airbags 4-26, and the two lower vibration isolation airbags 4-26 are placed vertically overlapping; each group of upper vibration isolation airbags 4-27 includes two upper vibration isolation airbags 4-27, and the two upper vibration isolation airbags 4-27 are placed vertically overlapping. The inner diameter of the protective ring 4-30 is larger than the outer wall of the external solid rocket engine, and the protective ring 4-30 is sleeved on the outer wall of the external solid rocket engine.

[0040] The excitation unit 3-1 drives the excitation rod 3-2 to perform an excitation test on the external solid rocket motor below the middle of the external solid rocket motor through the arc contact block 3-3.

[0041] The axial displacement of the external solid rocket engine during the vibration test is adaptively adjusted by the left load-bearing support roller 2-7 and the right load-bearing support roller 2-8; and the vertical buffering of the external solid rocket engine during the vibration test is achieved by the elastic support left unit 4-2 and the elastic support right unit 4-3.

[0042] like Figure 6As shown, the upper surface of the base body 1-1 is provided with a transverse T-slot 1-11 and a vertical T-slot 1-12; the transverse T-slot 1-11 and a plurality of vertical T-slots 1-12 are provided on the base body 1-1 at a certain distance. The relative position of the transition body 1-2 on the base body 1-1 is adjusted by the transverse T-slot 1-11 and the vertical T-slot 1-12 to adapt to external solid rocket engines of different sizes.

[0043] The working principle of the present invention is: when working, Figure 1-Figure 6 As shown, firstly, the transition frame 2-5 is bolted with conventional parts, and the head of the solid engine is omitted in the figure; the relative position of the transition platform 1-2 on the base platform 1-1 is adjusted by the transverse T-slot 1-11 to adjust the position of the left load-bearing support roller 2-7 on the transition platform 1-2, so that the left load-bearing support roller 2-7 is installed below the front group position of the engine; according to the length of the engine casing section, the position of the right load-bearing support roller 2-8 on the transition platform 1-2 is adjusted so that the symmetrical center plane of the left and right support rollers is located at the center of mass of the engine; the elastic support left unit 4-2 and the elastic support right unit 4-3 are symmetrically installed so that the symmetry of the two elastic support units The center plane is located at the center of mass of the engine; the protective collar 4-30 is opened to the front and rear sides by hinges, and the conventional driving equipment is operated. The solid engine is hoisted onto two supporting rollers, and the protective collar is closed and the protective collar 4-30 is tightened and locked by bolts; the excitation mechanism 3 is installed so that the arc contact block 3-3 is located at the center of mass of the engine and fits the arc surface of the engine casing; the positions of the front pressure wheel unit 2-9 and the rear pressure wheel unit 2-10 on the transition platform are adjusted, and they are installed symmetrically on both sides of the excitation mechanism, and the pressure wheel 2-11 is installed on the front and rear pressure wheel units through the support frame 2-93, so that the pressure wheel installation position is slightly higher than the solid engine but does not contact it.

[0044] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. An engine test device under vibration environment, characterized in that: It comprises a base platform (1-1), a transition platform (1-2), a bearing pier (1-3), a bearing plate (1-4), a buffer bearing seat (2-1), a transition bearing seat (2-2), a thrust sensor (2-4), a transition frame (2-5), a left bearing support roller (2-7), a right bearing support roller (2-8), a front pressure wheel unit (2-9), a rear pressure wheel unit (2-10), a pressure wheel (2-11), an excitation unit (3-1), an excitation rod (3-2), an arc contact block (3-3), a protective cover (4-1), an elastic support left unit (4-2) and an elastic support right unit (4-3); The base platform (1-1) is a horizontally placed plate-like structure; the load-bearing pier (1-3) is a rectangular parallelepiped structure; the load-bearing pier (1-3) is horizontally arranged at the side wall of the base platform (1-1) and is fixedly connected to the base platform (1-1); the transition platform (1-2) is a horizontally placed plate-like structure; the transition platform (1-2) is placed on the upper surface of the base platform (1-1); a plate-like groove is arranged at the side wall of the load-bearing pier (1-3) facing the base platform (1-1), and the load-bearing plate (1-4) is vertically embedded in the plate-like groove; The buffer bearing seat (2-1) is butt-jointed with the bearing plate (1-4); the transition bearing seat (2-2) is butt-jointed with the buffer bearing seat (2-1); the thrust sensor (2-4) is installed at the center of the side wall of the transition bearing seat (2-2); the transition frame (2-5) is an annular structure, one axial end of the transition frame (2-5) is butt-jointed with the thrust sensor (2-4), and the other axial end of the transition frame (2-5) is coaxially butt-jointed with the external solid rocket engine; the left bearing support roller (2-7) and the right bearing support roller (2-8) are connected to the thrust sensor (2-4) and the thrust sensor (2-4) respectively. The support rollers (2-8) are all arranged at the bottom end of the external solid rocket engine; the left load-bearing support roller (2-7) is close to the thrust sensor (2-4), and the right load-bearing support roller (2-8) is far away from the right load-bearing support roller (2-8); the front pressure wheel unit (2-9) and the rear pressure wheel unit (2-10) are symmetrically arranged on both sides of the external solid rocket engine; the axial ends of the pressure wheel (2-11) are respectively connected to the top side walls of the front pressure wheel unit (2-9) and the rear pressure wheel unit (2-10); The wheel (2-11) is pressed on the top of the external solid rocket engine; the excitation unit (3-1) is axially and vertically fixedly installed on the upper surface of the transition platform (1-2); the excitation unit (3-1) is located below the middle of the external solid rocket engine; the excitation rod (3-2) is axially and vertically connected to the output end of the excitation unit (3-1); the arc contact block (3-3) is fixedly installed on the top of the excitation rod (3-2); the arc contact block (3-3) is in contact with the bottom of the external solid rocket engine; the protective cover (4-1) covers the outer wall of the excitation unit (3-1); the elastic support left unit (4-2) and the elastic support right unit (4-3) are arranged along the axial direction of the external solid rocket engine, the elastic support left unit (4-2) is located on the upper surface of the transition platform (1-2) between the left load-bearing support roller (2-7) and the excitation unit (3-1); the elastic support right unit (4-3) is located on the upper surface of the transition platform (1-2) between the excitation unit (3-1) and the right load-bearing support roller (2-8); The elastic support left unit (4-2) and the elastic support right unit (4-3) have the same structure; the elastic support left unit (4-2) comprises a lower support plate (4-21), two protective side plates (4-22), a protective upper plate (4-23), a balance plate (4-24), two guide rods (4-25), two groups of lower vibration isolation airbags (4-26), two groups of upper vibration isolation airbags (4-27), a positioning rod (4-28) and a protective ring (4-30); The lower support plate (4-21) is placed horizontally; the two protective side plates (4-22) are vertically fixedly installed at the two side edges of the upper surface of the lower support plate (4-21); the protective upper plate (4-23) is horizontally placed at the top of the two protective side plates (4-22); the lower support plate (4-21), the two protective side plates (4-22), and the protective upper plate (4-23) form a cavity structure; the balance plate (4-24) is horizontally arranged in the middle of the cavity structure; the positioning rod (4-28) is vertically fixedly installed at the center of the upper surface of the lower support plate (4-21); and the axial top end of the positioning rod (4-28) extends out of the protective upper plate (4-23). ); the protective collar (4-30) is fixedly installed on the top of the positioning rod (4-28); the two guide rods (4-25) are both arranged inside the cavity structure, and the two guide rods (4-25) are symmetrically arranged on both sides of the positioning rod (4-28); each guide rod (4-25) is correspondingly installed with a group of lower vibration isolation airbags (4-26) and a group of upper vibration isolation airbags (4-27); wherein the lower vibration isolation airbag (4-26) is arranged in the cavity between the balance plate (4-24) and the lower support plate (4-21), and the upper vibration isolation airbag (4-27) is arranged in the cavity between the balance plate (4-24) and the protective upper plate (4-23).

2. The engine running test device under vibration environment according to claim 1, characterized in that: The arc-shaped contact block (3-3) is an arc-shaped plate-shaped structure, and the arc shape of the upper surface of the arc-shaped contact block (3-3) is adapted to the outer wall of the external solid rocket engine.

3. The engine running test device under vibration environment according to claim 1, characterized in that: The arc-shaped contact block (3-3) and the pressing wheel (2-11) correspond in position in the vertical direction.

4. The engine running test device under vibration environment according to claim 1, characterized in that: The front pressure wheel unit (2-9) has the same structure as the rear pressure wheel unit (2-10); the front pressure wheel unit (2-9) comprises a front pressure wheel frame (2-91), a support rib (2-92) and a support frame (2-93); wherein the front pressure wheel frame (2-91) is vertically fixedly installed on the upper surface of the transition platform (1-2); the support rib (2-92) is arranged on the inner side wall of the front pressure wheel frame (2-91) to strengthen the connection between the front pressure wheel frame (2-91) and the transition platform (1-2); the support frame (2-93) is arranged on the top inner side wall of the front pressure wheel frame (2-91); the support frame (2-93) is butt-jointed with one axial end of the pressure wheel (2-11).

5. The engine running test device under vibration environment according to claim 1, characterized in that: Each group of lower vibration isolation airbags (4-26) includes two lower vibration isolation airbags (4-26), and the two lower vibration isolation airbags (4-26) are placed in an overlapping manner in a vertical direction; each group of upper vibration isolation airbags (4-27) includes two upper vibration isolation airbags (4-27), and the two upper vibration isolation airbags (4-27) are placed in an overlapping manner in a vertical direction.

6. The engine running test device under vibration environment according to claim 5, characterized in that: The inner diameter of the protective collar (4-30) is larger than the outer wall of the external solid rocket motor, and the protective collar (4-30) is sleeved on the outer wall of the external solid rocket motor.

7. The engine running test device under vibration environment according to claim 1, characterized in that: The vibration excitation unit (3-1) drives the excitation rod (3-2) to perform a vibration excitation test on the external solid rocket motor below the middle of the external solid rocket motor through the arc-shaped contact block (3-3).

8. The engine running test device under vibration environment according to claim 1, characterized in that: The axial displacement of the external solid rocket engine during the vibration test is adaptively adjusted by the left load-bearing support roller (2-7) and the right load-bearing support roller (2-8); and the vertical direction of the external solid rocket engine is buffered during the vibration test by the elastic support left unit (4-2) and the elastic support right unit (4-3).

9. The engine running test device under vibration environment according to claim 1, characterized in that: The thrust sensor (2-4) is used to measure the test force of the external solid rocket engine during the vibration test.

Images