Pressure impact insulation skirt ground verification test structure and method

Abstract

The application provides a pressure impact heat-proof tail skirt ground verification test structure and method. The pressure impact heat-proof tail skirt ground verification test structure comprises a cylinder, a pressure relief device, a pressure relief device mounting structure, a pressure tester and a heat-proof tail skirt mounting structure; the pressure relief device is detachably mounted on one end of the cylinder through the pressure relief device mounting structure, and a bottom plate is mounted on the other end of the cylinder; the heat-proof tail skirt mounting structure is used for detachably mounting the heat-proof tail skirt; the heat-proof tail skirt mounting structure and the heat-proof tail skirt divide the cylinder into a first cavity and a second cavity; the first cavity and the second cavity are both provided with the pressure tester; the cylinder is provided with an air inlet, and the air inlet communicates with the first cavity. The simulation system can simulate the stress condition of the heat-proof tail skirt when the stage separation is performed, and simultaneously test the dynamic mechanical properties and the pressure relief rate of the heat-proof tail skirt under the transient pressure impact, and the test process is simple and efficient.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of assembly testing, in particular to a pressure impact heat shield skirt ground verification test structure and method, more particularly to a simulation engine ignition pressure impact heat shield skirt ground verification test system and method, and most particularly to a ground verification test system and method for ground verification of heat shield skirt dynamic mechanical impact characteristics and air tightness characteristics. BACKGROUND

[0002] For a multi-stage aircraft, according to special functional requirements, the structure needs to be separated in a large number of complex states, and the load during the separation process usually has high-pressure transient impact characteristics. The flexible heat shield skirt is arranged at the tail end of the front stage at the stage separation position, which is used to avoid the high-temperature and high-pressure backflow of the high-pressure gas jetted by the front-stage engine into the interior of the front-stage cabin after rebounding through the front end of the rear stage, thereby causing damage to the key components. At the same time, due to the thin air at the stage separation position, there is a pressure difference between the cabin and the outside, and the cabin needs to be rapidly depressurized after high-altitude separation, so the heat shield skirt needs to have dynamic mechanical characteristics of resisting instantaneous pressure impact and the ability of rapid depressurization.

[0003] In order to accurately evaluate the safety and reliability of the structure design, it is most reliable to directly carry out real engine ignition. However, directly carrying out engine ground test is not only expensive, but also has a long cycle, and the safety protection measures for the test site are very high, which cannot meet the current design progress requirements.

[0004] As a new type of heat shield flexible structure, the heat shield skirt has a special shape, and it is difficult to install the general pressure test equipment. In addition, the general pressure test equipment cannot simultaneously simulate the dynamic mechanical performance and rapid depressurization dynamic process of the heat shield skirt under real working conditions after being subjected to pressure impact.

[0005] Therefore, there is an urgent need for a test system that can simulate the backflow pressure characteristics of the product under real separation conditions. SUMMARY

[0006] In view of the defects in the prior art, the purpose of the present application is to provide a pressure impact heat shield skirt ground verification test structure and method.

[0007] According to the pressure impact heat shield skirt ground verification test structure provided by the present application, the pressure impact heat shield skirt ground verification test structure comprises a cylinder, a bottom plate, a pressure relief device, a pressure relief device mounting structure, a pressure test instrument and a heat shield skirt mounting structure.

[0008] The pressure relief device is detachably mounted at one end of the cylinder through the pressure relief device mounting structure, and the bottom plate is mounted at the other end of the cylinder; the heat shield skirt mounting structure is used for detachably mounting the heat shield skirt.

[0009] The heat insulation tail skirt mounting structure and the heat insulation tail skirt divide the cylinder into a first cavity and a second cavity;

[0010] The first cavity and the second cavity are both provided with a pressure tester;

[0011] The cylinder is provided with an air inlet, and the air inlet communicates with the first cavity.

[0012] Preferably, the pressure relief device is a burst disc.

[0013] Preferably, the pressure relief device mounting structure comprises a disc pressing plate and an upper flange.

[0014] The upper flange is connected to one end of the cylinder, the disc pressing plate is connected to the upper flange through a connecting piece, and the edge of the pressure relief device is located between the disc pressing plate and the upper flange.

[0015] Preferably, the middle part of the disc pressing plate is provided with a hollow structure.

[0016] Preferably, the disc pressing plate and the upper flange are respectively provided with a first groove and a second groove, and the first groove and the second groove form a pressure groove.

[0017] The outermost extension of the pressure relief device is located in the groove and does not contact the disc pressing plate and the upper flange.

[0018] Preferably, the heat insulation tail skirt mounting structure comprises a support beam, a ring rib, an upper support, a lower support, an upper pressing plate and a lower pressing plate.

[0019] The ring rib is located in the second cavity, the support beam is mounted on the ring rib, one end of the heat insulation tail skirt is clamped by the upper support and the upper pressing plate.

[0020] The other end of the heat insulation tail skirt is clamped by the lower support and the lower pressing plate.

[0021] The support beam is connected to the lower support through a connecting piece.

[0022] Preferably, it further comprises a lower flange.

[0023] The bottom plate is connected to the cylinder through the lower flange.

[0024] The bottom plate is provided with a plurality of lugs, and the lugs are used to fix the pressure impact heat insulation tail skirt ground verification test structure to the ground.

[0025] Preferably, it further comprises a sealing ring, which is installed in the groove of the lower flange.

[0026] Preferably, the number of lugs is 4.

[0027] According to the pressure impact heat insulation tail skirt ground verification test method provided by the application, the pressure impact heat insulation tail skirt ground verification test structure is also used, and further comprises the following steps.

[0028] S1, the pressure impact heat insulation tail skirt ground verification test structure is fixed on the ground through the supporting lug on the bottom plate, and the burst diaphragm faces upward.

[0029] S2, the first cavity is continuously inflated through the air inlet, and because the heat insulation tail skirt is not completely sealed, the excess gas enters the second cavity, the pressure difference between the large and small cabins is dynamically detected through the pressure tester 14, and the inflation rate is controlled to ensure that the pressure difference between the large and small cabins does not exceed 0.05 MPa.

[0030] S3, during the continuous inflation process, when the pressure in the second cavity reaches the critical pressure of the pressure relief device, the pressure relief device loses its pressure-bearing capacity and loses its stability, and the second cavity instantaneously completes pressure relief, and the pressure drops to atmospheric pressure.

[0031] S4, when the burst diaphragm breaks, the inflation personnel immediately close the inflation valve, at this time, the transient pressure of the first cavity remains unchanged due to the blocking of the heat insulation tail skirt, the pressure difference between the first cavity and the second cavity is the critical pressure of the pressure relief device, and this moment can simulate the process of the heat insulation tail skirt being subjected to the transient pressure impact when the stage separation occurs, and the heat insulation tail skirt expands freely.

[0032] S5, after the impact process is completed, because there is a pressure difference between the first cavity and the second cavity, the high-pressure gas in the first cavity will dissipate through the gap of the heat insulation tail skirt into the second cavity, and at this time, the pressure relief process of the heat insulation tail skirt can be simulated.

[0033] S6, the pressure change curve is obtained by reading the pressure tester 14, and the pressure relief time and the pressure relief rate of the heat insulation tail skirt can be obtained through calculation.

[0034] Compared with the prior art, the application has the following beneficial effects:

[0035] 1, the simulation system can simulate the stress of the heat insulation tail skirt when the stage separation occurs, and can test the dynamic mechanical properties and the pressure relief rate of the heat insulation tail skirt under the transient pressure impact, and the test process is simple and efficient.

[0036] 2, the pressure relief device is detachably installed, the specification of the pressure relief device can be changed, the size of the transient pressure impact can be changed, and the test requirements of different separation conditions can be met.

[0037] 3, the pressure relief device adopts a burst diaphragm, the sealing structure of the burst diaphragm is simple, the sealing effect is good, and the reliability is high. BRIEF DESCRIPTION OF DRAWINGS

[0038] Other features, objects, and advantages of the application will become more apparent from the following detailed description of non-limiting embodiments thereof, when read in conjunction with the accompanying drawings:

[0039] Figure 1 is a structural schematic diagram of the application;

[0040] Figure 2 is a sectional view of the application;

[0041] Figure 3 is a schematic diagram of the installation of the burst disc;

[0042] Figure 4 is a structural schematic diagram of the heat shield skirt.

[0043] The drawings show:

[0044]

[0045] DETAILED DESCRIPTION

[0046] The application will be described in detail below with specific embodiments. The following examples will help those skilled in the art to further understand the application, but do not limit the application in any form. It should be noted that for those skilled in the art, without departing from the concept of the application, a number of changes and improvements can be made. These are within the scope of the application.

[0047] The application provides a pressure impact heat shield skirt ground verification test structure, as shown in Figures 1-2 including a cylinder 3, a pressure relief device, a pressure relief device mounting structure, a pressure tester 14, a bottom plate 5, and a heat shield skirt mounting structure;

[0048] In a preferred embodiment, the cylinder 3 is a cylinder, the pressure tester 14 is a pressure sensor, and the pressure relief device is a burst disc 10.

[0049] The pressure relief device is detachably mounted on one end of the cylinder 3 through the pressure relief device mounting structure, and the bottom plate 5 is mounted on the other end of the cylinder 3; the heat shield skirt mounting structure is used for detachable installation of the heat shield skirt 7; the heat shield skirt mounting structure and the heat shield skirt 7 divide the cylinder 3 into a first cavity 18 and a second cavity 19, in a preferred embodiment, the first cavity 18 is a large cavity, and the second cavity 19 is a small cavity; the first cavity 18 and the second cavity 19 are both provided with a pressure tester 14; the cylinder 3 is provided with an air inlet 21, and the air inlet 21 communicates with the first cavity 18.

[0050] The pressure relief device installation structure includes a diaphragm pressure plate 1 and an upper flange 2; the diaphragm pressure plate 1 has a hollow structure in the middle, and one side of the bursting diaphragm 10 is connected to the outside atmosphere through the hollow structure.

[0051] The upper flange 2 is connected to one end of the cylinder 3, and the diaphragm pressure plate 1 is connected to the upper flange 2 by a connector. In a preferred embodiment, the connector is a screw 16 and a nut 17 mating structure; the edge of the pressure relief device is located between the diaphragm pressure plate 1 and the upper flange 2. Preferably, as shown... Figure 3 As shown, the diaphragm plate 1 and the upper flange 2 are respectively provided with a first groove and a second groove, which are directly opposite each other to form a pressure groove 22. The outermost extension of the pressure relief device is located in the groove 22 and does not contact the diaphragm plate 1 and the upper flange 2. The pressure groove 22 is used to reduce the contact area. Specifically, after the screws on the upper flange 2 are tightened, the upper flange undergoes a slight bending deformation. At this time, the pressure between the diaphragm plate 1 and the upper flange 2 is concentrated at the contact position 23 between the upper end of the pressure groove 22 and the burst diaphragm 10, thus achieving a sealing function. This sealing method does not require additional sealing components and has a good sealing effect.

[0052] like Figure 4 As shown, the heat-insulating tail skirt 7 is a spatial lantern-shaped structure with different radii at both ends. Each end of the heat-insulating tail skirt 7 has a large-radius ring and a small-radius ring. The ring with the larger radius is defined as the first ring 71, and the ring with the smaller radius is defined as the second ring 72. Both the first ring 71 and the second ring 72 have multiple circumferentially distributed through holes through which screws 16 can pass for fixing the heat-insulating tail skirt 7. In a preferred embodiment, the heat-insulating tail skirt 7 can be made of aramid fiber or silicone rubber.

[0053] The heat-insulating tail skirt installation structure includes a support beam 6, a ring rib 11, an upper bracket 8, a lower bracket 9, an upper pressure plate 12, and a lower pressure plate 13. The ring rib 11 is located inside the second cavity 19, and the support beam 6 is installed on the ring rib 11. One end of the heat-insulating tail skirt 7 is held by the upper bracket 8 and the upper pressure plate 12; the other end of the heat-insulating tail skirt 7 is held by the lower bracket 9 and the lower pressure plate 13. The support beam 6 is connected to the lower bracket 9 through a connector. Specifically, the upper bracket 8, the lower bracket 9, the upper pressure plate 12, the lower pressure plate 13, and the heat-insulating tail skirt 7 together divide the cylinder 3 into a first cavity 18 and a second cavity 19.

[0054] The pressure impact heat insulation tail skirt ground verification test structure further comprises a lower flange 4 and a sealing ring 15; the bottom plate 5 is connected to the cylinder 3 through the lower flange 4, preferably, the lower flange 4 and the bottom plate 5 are connected through fasteners; a plurality of supporting ears 20 are arranged on the bottom plate 5, and the supporting ears 20 are used for fixing the pressure impact heat insulation tail skirt ground verification test structure to the ground, preferably, the number of the supporting ears 20 is four. The sealing ring 15 is installed in a groove of the lower flange 4. In a preferred embodiment, the fasteners are screw 16 and nut 17 matching structures.

[0055] The assembly of the pressure impact heat insulation tail skirt ground verification test structure is as follows: first, the upper flange 2, the lower flange 4, the upper support 8 and the ring rib 11 are connected at corresponding positions of the cylinder through welding. The support beam 6 is welded and fixed at the ring rib groove. After welding is completed, the O-shaped sealing ring 15 is installed at the lower flange groove, and the bottom plate 5 is connected and clamped through the screw 16 and the nut 17. Then, the heat insulation tail skirt 7 is installed, specifically, the first ring is clamped by the upper support 8 and the upper pressing plate 12 and is clamped and fixed through the screw 16 and the nut 17, and the second ring is clamped by the lower support 9 and the lower pressing plate 13 and is clamped and fixed through the screw 16 and the nut 17. Then, the blasting membrane 10 is installed, and the membrane pressing plate 1 and the upper flange 2 are clamped and fixed through the screw 16 and the nut 17. Finally, two pressure testers 14 are installed at the reserved positions of the cylinder.

[0056] The application further provides a pressure impact heat insulation tail skirt ground verification test method, which adopts the pressure impact heat insulation tail skirt ground verification test structure and further comprises the following steps.

[0057] S1, the pressure impact heat insulation tail skirt ground verification test structure is fixed to the ground through the supporting ears 20 on the bottom plate 5, and the blasting membrane faces upward.

[0058] S2, the first cavity 18 is continuously inflated through the air inlet 21, because the heat insulation tail skirt 7 is not completely sealed, the excess gas enters the second cavity 19, the pressure difference between the large cabin and the small cabin is dynamically detected through the pressure tester 14, the inflation rate is controlled to ensure that the pressure difference between the large cabin and the small cabin does not exceed 0.05 MPa, and at this time, it can be considered that the pressures of the large cabin and the small cabin are approximately the same.

[0059] S3, in the process of continuous inflation, when the pressure in the second cavity 19 reaches the critical pressure of the pressure relief device, the pressure relief device loses stability and is damaged, loses the pressure bearing capacity, and appears large-area tearing, and the second cavity 19 instantaneously completes pressure release and the pressure drops to atmospheric pressure.

[0060] S4, when hearing the burst diaphragm rupture sound, the inflator personnel immediately closes the inflator valve, at this time, the first cavity 18 remains unchanged due to the blocking of the heat shield tail skirt 7, the pressure difference between the first cavity 18 and the second cavity 19 is the critical pressure of the pressure relief device, at this time, the process of the heat shield tail skirt being impacted by the transient pressure when the stage separation is simulated, and the heat shield tail skirt 7 expands freely.

[0061] S5, after the impact process is over, due to the pressure difference between the first cavity 18 and the second cavity 19, the high-pressure gas in the first cavity 18 will dissipate into the second cavity 19 through the gap of the heat shield tail skirt 7, at this time, the pressure relief process of the heat shield tail skirt can be simulated.

[0062] S6, by reading the pressure change curve of the pressure tester 14, the pressure relief time and the pressure relief rate of the heat shield tail skirt 7 can be obtained through calculation.

[0063] After the test is completed, the diaphragm pressing plate 1 can be removed to replace the burst diaphragm 10, and the upper pressing plate 12 and the lower pressing plate 13 can be removed to replace the heat shield tail skirt 7, the present application can carry out transient pressure impact and pressure relief tests on other heat shield tail skirts under different initial pressures, and the heat shield tail skirt can be replaced conveniently and quickly.

[0064] The working principle of the present application is as follows: during the test implementation process, by continuously inflating the inside of the tool, the burst diaphragm is used to simulate the process of the flexible heat shield tail skirt structure being impacted by the backflow of the front-stage engine and the pressure release in the cabin under actual separation conditions, and the pressure tester 14 is used to record the pressure change in the cabin to examine the dynamic mechanical properties and air tightness of the heat shield tail skirt.

[0065] In addition, the present application adopts the combination structure of the pressing plate and the screw to fix the heat shield tail skirt 7 and the burst diaphragm 10, after the test is completed, the new heat shield tail skirt 7 and the burst diaphragm 10 of different specifications can be quickly replaced for the next test, and the test efficiency is high.

[0066] In summary, the present application can measure the dynamic mechanical properties and the pressure relief rate of the heat shield tail skirt under the transient pressure impact, so as to meet the examination and test requirements of the dynamic strength properties and the dynamic sealing properties of the flexible structure heat shield tail skirt in the development process of different models.

[0067] In the description of the present application, it should be understood that the orientations or positional relationships indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0068] The specific embodiments of the present application have been described. It is to be understood that the application is not limited to particular details described herein and that various modifications can be made therein without departing from the scope of the claimed application. Embodiments and features disclosed in this document, including in the examples, can be combined with each other, unless specifically contradicted by or inconsistent with each other.

Claims

1. A pressure-impingement heat shield aft skirt ground verification test structure, characterized by, The pressure impact heat insulation tail skirt ground verification test structure comprises a cylinder (3), a pressure relief device, a pressure relief device mounting structure, a bottom plate (5), a pressure tester (14), and a heat insulation tail skirt mounting structure. The pressure relief device is detachably mounted on one end of the cylinder (3) through the pressure relief device mounting structure, and the bottom plate (5) is mounted on the other end of the cylinder (3); the heat insulation tail skirt mounting structure is used for detachably mounting a heat insulation tail skirt (7). The heat insulation tail skirt mounting structure and the heat insulation tail skirt (7) divide the cylinder (3) into a first cavity (18) and a second cavity (19). The first cavity (18) and the second cavity (19) are both provided with a pressure tester (14). An air inlet (21) is arranged on the cylinder (3), and the air inlet (21) communicates with the first cavity (18). The pressure relief device is a burst diaphragm (10).

2. The pressure-impingement insulation-tail-skirt ground-verification test structure of claim 1, wherein, The pressure relief device mounting structure comprises a diaphragm pressing plate (1) and an upper flange (2). One end of the upper flange (2) is connected with the cylinder (3), and the diaphragm pressing plate (1) is connected with the upper flange (2) through a connecting piece; the edge of the pressure relief device is located between the diaphragm pressing plate (1) and the upper flange (2).

3. The pressure-impingement insulation-tail-skirt ground-verification test structure of claim 2, wherein, The middle part of the diaphragm pressing plate (1) is provided with a hollow structure.

4. The pressure-impingement insulation-tail-skirt ground-verification test structure of claim 2, wherein, First and second recesses are respectively arranged on the diaphragm pressing plate (1) and the upper flange (2), and the first and second recesses form a pressure recess (22). The outermost edge of the pressure relief device is located in the pressure recess (22) and does not contact the diaphragm pressing plate (1) and the upper flange (2).

5. The pressure-impingement insulation-tail-skirt ground-verification test structure of claim 1, wherein, The heat insulation tail skirt mounting structure comprises a support beam (6), a ring rib (11), an upper support (8), a lower support (9), an upper pressing plate (12), and a lower pressing plate (13). The ring rib (11) is located in the second cavity (19), the support beam (6) is mounted on the ring rib (11), one end of the heat insulation tail skirt (7) is clamped by the upper support (8) and the upper pressing plate (12); The other end of the heat insulation tail skirt (7) is clamped by the lower support (9) and the lower pressing plate (13); The support beam (6) is connected with the lower support (9) through a connecting piece.

6. The pressure-impingement insulation-tail-skirt ground-verification test structure of claim 1, wherein, It also comprises a lower flange (4). The bottom plate (5) is connected with the cylinder (3) through the lower flange (4). A plurality of lugs (20) are arranged on the bottom plate (5), and the lugs (20) are used for fixing the pressure impact heat insulation tail skirt ground verification test structure to the ground.

7. The pressure-impingement insulation-tail-skirt ground-verification test structure of claim 6, wherein, A sealing ring (15) is mounted in the recess of the lower flange (4).

8. The pressure-impingement insulation-tail-skirt ground-verification test structure of claim 6, wherein, The number of lugs is four.

9. A method of ground verification testing of a pressure-impingement heat shield aft skirt, characterized by, The pressure impact heat insulation tail skirt ground verification test structure of any one of claims 1 to 8 further comprises the following steps: S1, fixing the pressure impact heat insulation tail skirt ground verification test structure to the ground through the lugs (20) on the bottom plate (5), and the burst diaphragm faces upward. S2, continuously filling the first cavity (18) through the air inlet (21), due to the non-fully sealed heat shield tail skirt (7), the excess gas will enter the second cavity (19), the pressure difference between the large and small cabins is dynamically detected through the pressure tester (14), and the pressure difference between the large and small cabins is ensured to be not more than 0.05 MPa by controlling the filling rate; S3, during the continuous filling process, when the pressure in the second cavity (19) reaches the critical pressure of the pressure relief device, the pressure relief device loses its pressure-bearing capacity and loses its stability, and the second cavity (19) instantaneously completes pressure relief, and the pressure drops to atmospheric pressure; S4, when the sound of the burst diaphragm is heard, the inflator immediately closes the inflation valve, at this time the first cavity (18) is blocked by the heat shield tail skirt (7) and the transient pressure remains unchanged, the pressure difference between the first cavity (18) and the second cavity (19) is the critical pressure of the pressure relief device, which can simulate the process of the heat shield tail skirt being impacted by the transient pressure when the stage separation occurs, and the heat shield tail skirt (7) expands freely; S5, after the impact process is completed, due to the pressure difference between the first cavity (18) and the second cavity (19), the high-pressure gas in the first cavity (18) will dissipate through the gap of the heat shield tail skirt (7) to the second cavity (19), at this time the pressure relief process of the heat shield tail skirt can be simulated; S6, by reading the pressure change curve of the pressure tester (14), the pressure relief time and pressure relief rate of the heat shield tail skirt (7) can be obtained through calculation.

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