CN217180345U

CN217180345U - Ablation-resistant flexible encapsulating material high-pressure impact resistance test device for solid rocket engine

Info

Publication number: CN217180345U
Application number: CN202123038872.1U
Authority: CN
Inventors: 黄驰; 邹毓; 胡铭杰; 车友保; 廖俊
Original assignee: Hubei Hangtai Technology Co ltd
Current assignee: Hubei Hangtai Technology Co ltd
Priority date: 2021-12-06
Filing date: 2021-12-06
Publication date: 2022-08-12
Anticipated expiration: 2031-12-06

Abstract

The invention relates to a high-pressure impact resistance test device for ablation-resistant flexible encapsulating materials of a solid rocket engine. The device comprises a lower die with a cavity, an upper die matched with the lower die and a pressing mechanism for fixing the lower die and the upper die, wherein the lower die is provided with a communicating hole for connecting a high-pressure air pipe. The method has the advantages of being capable of effectively confirming the high-pressure impact resistance of the ablation-resistant flexible encapsulating material for the solid rocket engine, confirming the reliability of the material in use, high in detection accuracy, simple in structure, easy to process and assemble, low in cost, and flexible and convenient to use.

Description

Ablation-resistant flexible encapsulating material high-pressure impact resistance test device for solid rocket engine

Technical Field

The invention relates to the technical field of solid rocket engines, in particular to a high-pressure impact resistance test device for ablation-resistant flexible encapsulating materials of a solid rocket engine.

Background

The ablation-resistant flexible encapsulating material for the solid rocket engine is a key material of the solid rocket engine, is composed of a high polymer material, and has excellent bonding performance, flexibility and ablation resistance. The adhesive is mainly used in the gaps of the explosive blocks of the solid rocket engine, and plays a role in adhering the explosive blocks, isolating high-temperature and high-pressure fuel gas generated during the operation of the engine and enabling the operation of the engine to be more stable. At present, the solid rocket engine is provided with unstable factors due to the lack of a test method and means under the condition of high pressure impact of an ablation-resistant flexible encapsulating material, and the risk of serious consequences such as prolonged product development period caused by experiment failure exists.

Disclosure of Invention

In order to overcome the defects of the prior detection technology, the invention aims to provide a high-pressure impact resistance test device for ablation-resistant flexible encapsulating material of a solid rocket engine.

In order to achieve the purpose, the technical scheme adopted by the invention is as follows:

the ablation-resistant flexible encapsulating material high-pressure impact resistance test device for the solid rocket engine comprises a lower die with a cavity, an upper die matched with the lower die and a pressing mechanism used for fixing the lower die and the upper die, wherein the lower die is provided with a communicating hole connected with a high-pressure air pipe.

Furthermore, the pressing mechanism comprises a plurality of pairs of through holes formed in the edge parts of the lower die and the upper die, and fasteners matched with the through holes for use.

Further, the fastener is a bolt and a nut, and a spring washer and a flat washer used in cooperation with the bolt and the nut.

Furthermore, a plurality of handles are arranged on the periphery of the upper die and the lower die, and the handles are in threaded connection with the upper die and the lower die.

Furthermore, the inner surface of the cavity is adhered with nitrile rubber sheets with uniform thickness.

Furthermore, a groove position is arranged on the periphery of the cavity, and a sealing ring is arranged in the groove position.

The height and the width of the limit stop are consistent with those of the cavity, and the placing position can be adjusted to adjust the space in the cavity so as to control the quantity of the materials poured into the cavity and avoid the overflow of the materials.

Furthermore, a layer of polytetrafluoroethylene gasket is arranged at the position, corresponding to the opening of the cavity, of the upper die, so that the demolding of the device is facilitated.

In summary, the invention includes at least one of the following beneficial technical effects:

1. the high-pressure impact resistance of the ablation-resistant flexible encapsulating material for the solid rocket engine can be effectively confirmed, the use reliability of the material is confirmed, and the detection accuracy is high.

2. Simple structure, easy processing and assembly, low cost and flexible and convenient use.

Drawings

FIG. 1 is a schematic structural diagram of a high pressure impact resistance test device for ablation-resistant flexible potting materials of a solid rocket engine according to the present invention;

FIG. 2 is a cross-sectional side view of the structure of the high pressure impact resistance test device of the ablation-resistant flexible potting material of the solid rocket engine of the present invention;

FIG. 3 is a top view of the lower die of the present invention;

FIG. 4 is a side cross-sectional view of the lower mold of the present invention;

FIG. 5 is a top plan view of the upper die of the present invention;

fig. 6 is a side sectional view of the upper mold of the present invention.

Wherein: 1-lower die, 2-upper die, 3-die cavity, 4-communicating hole, 5-hold-down mechanism, 51-bolt, 52-spring washer, 53-flat washer, 54-through hole, 6-slot position, 7-sealing ring, 8-limit stop, 9-handle and 10-polytetrafluoroethylene gasket.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.

As shown in fig. 1 and 2, the ablation-resistant flexible potting material high-pressure impact resistance test device for the solid rocket engine comprises a lower die with a cavity, an upper die matched with the lower die and a pressing mechanism for fixing the lower die and the upper die, wherein the ablation-resistant flexible potting material is poured into the cavity for testing, the pressing mechanism prevents the upper die and the lower die from moving transversely and longitudinally to ensure the stability of the test device, as shown in fig. 4, a communication hole connected with a high-pressure gas pipe is formed in the lower die, and after the high-pressure gas pipe is connected to the communication hole, high-pressure gas can be injected into the cavity through the communication hole.

As a preferred scheme of the invention, the pressing mechanism comprises a plurality of pairs of through holes arranged at the edge parts of the lower die and the upper die and fasteners matched with the through holes for use.

The fastener adopts a bolt and a nut and is matched with a spring washer and a flat washer, so that the contact surface is enlarged, the pressure is reduced, the connection is firmer, and the parts and the bolt can be protected.

In order to facilitate the transfer of the tool, the upper die and the lower die are all provided with a plurality of handles, and the handles are connected with the upper die and the lower die through threads, so that the tool is convenient to disassemble.

In order to facilitate the observation and comparison of test results, the inner surface of the cavity is adhered with the nitrile rubber sheet with uniform thickness.

As shown in fig. 3, as a preferred scheme of the present invention, slots are disposed around the cavity, and sealing rings are disposed in the slots, so as to increase the sealing performance of the cavity and prevent air leakage during the test.

As a preferable scheme of the present invention, the present invention further comprises a limit stopper which can be placed in the cavity, wherein the height and width of the limit stopper are the same as those of the cavity, and the placement position can be adjusted to adjust the space in the cavity, so as to control the amount of the material poured into the cavity, and simultaneously, the overflow of the material can be avoided, and the material can be prevented from flowing out from the communicating hole during pouring.

As shown in fig. 5 and 6, as a preferred embodiment of the present invention, a layer of teflon gasket is disposed at a position of the upper mold corresponding to the opening of the cavity, so that the flexible potting material in the cavity does not produce an adhesive effect when contacting the upper mold, thereby facilitating the demolding of the device.

The implementation principle of the invention is that firstly, the ablation-resistant flexible encapsulating material of the solid rocket engine is poured into a cavity of a lower die, a limit stop block is used for controlling the pouring amount, after the pouring is finished, an upper die is closed, a pressing mechanism is used for pressing the upper die and the lower die, the cavity is closed, then a high-pressure gas pipe is connected to a communication hole and releases high-pressure gas, the high-pressure gas acts on the flexible encapsulating material in the cavity, after a period of time, whether the pressure of the high-pressure gas is in a reasonable range is preliminarily detected, if the pressure is in the reasonable range, the airtightness is good, the subsequent steps can be carried out, and then the high-pressure gas source is closed, and the pressure in the cavity is discharged. And at the moment, the upper die can be opened, the change of the bonding state of the flexible encapsulating material and the nitrile rubber sheet in the cavity after the action of the high-pressure gas is observed, if the bonding state is changed within a certain range, the high-pressure impact test is qualified, otherwise, the high-pressure impact test is unqualified.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present application, and not to limit the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present application.

Claims

1. The device is characterized by comprising a lower die with a cavity, an upper die matched with the lower die and a pressing mechanism used for fixing the lower die and the upper die, wherein the lower die is provided with a communicating hole connected with a high-pressure air pipe.

2. The device for testing the high pressure impact resistance of the ablation-resistant flexible potting material of the solid-rocket engine as recited in claim 1, wherein said pressing mechanism comprises a plurality of pairs of through holes formed at the edge portions of said lower mold and said upper mold, and fasteners used in cooperation with said through holes.

3. The solid-rocket engine ablation-resistant flexible potting material high-pressure impact resistance test device of claim 2, the fasteners being bolts and nuts and spring washers and flat washers used in cooperation with the bolts and nuts.

4. The solid-rocket engine ablation-resistant flexible potting material high-pressure impact resistance test device of claim 1, wherein a plurality of handles are arranged around the upper die and the lower die, and the handles are in threaded connection with the upper die and the lower die.

5. The device for testing the ablation resistance and high pressure impact resistance of the solid rocket engine flexible encapsulating material according to claim 1, wherein a nitrile rubber sheet with uniform thickness is adhered to the inner surface of the cavity.

6. The device for testing the ablation resistance and the high pressure impact resistance of the flexible encapsulating material of the solid rocket engine according to claim 1, wherein slots are arranged around the cavity, and sealing rings are arranged in the slots.

7. The apparatus for testing high pressure impact resistance of ablation-resistant flexible potting material of a solid rocket engine as recited in claim 1, further comprising a limit stop capable of being placed in said cavity, wherein the height and width of said limit stop are identical to the height and width of said cavity, and the placement position can be adjusted to adjust the space in said cavity, so as to control the amount of material poured into said cavity and avoid the overflow of the material.

8. The ablation-resistant flexible potting material high-pressure impact resistance test device for the solid rocket engine according to claim 1, wherein a polytetrafluoroethylene gasket is arranged at a position of the upper die corresponding to the opening of the cavity, so that the device can be conveniently demoulded.