阅读说明：本技术 一种安全去除固体火箭发动机喷管堵片的装置和方法 (Device and method for safely removing solid rocket engine nozzle blocking piece ) 是由 朱麟鹏 赵云 李阳 彭吉云 杜秋丽 李彦丽 于 2020-12-02 设计创作，主要内容包括：本发明涉及一种安全去除固体火箭发动机喷管堵片的装置和使用方法,通过采用螺杆传动原理,并搭载缓冲弹簧部件,构建起一套便携式手动打孔作业装置,可以实现操作人员在发动机喷管堵片表面出安全打孔作业的目的,完成打孔作业后,通过采用向特定孔洞施加外力的方式,可以实现对发动机喷管堵片的剥离作业。采用上述装置和方法可以满足发动机堵片安全拆除作业的需求,为固体火箭发动机高空模拟点火试验的顺利开展提供技术支撑。(The invention relates to a device for safely removing a solid rocket engine nozzle blocking piece and a using method thereof. By adopting the device and the method, the requirement of safe removal operation of the engine block can be met, and technical support is provided for the smooth development of the high-altitude simulation ignition test of the solid rocket engine.)

1. The utility model provides a device of solid rocket engine spray tube jam piece is got rid of safely, includes drill bit (1), screw rod (2), sleeve (3), rocking handle (5) and lifting support (6), its characterized in that:

the tail of the screw (2) is connected with the rocking handle (5), the middle of the screw (2) is installed in the sleeve (3), the head of the screw (2) is connected with the drill bit (1), when the rocking handle (5) is rotated, the screw (2) moves along the thread direction and drives the drill bit (1) to rotate forwards, and then the surface of the solid rocket engine nozzle plug is punched; the sleeve (3) is fixed on the lifting bracket (6) through a fixed snap ring (7).

2. The apparatus of claim 1, wherein: the device also comprises a buffer spring (4), wherein the buffer spring (4) is arranged on the tail part of the screw rod (2) between the sleeve (3) and the rocking handle (5) and used for limiting the punching speed.

3. A method for safely removing a solid rocket engine nozzle blocking piece comprises the following specific steps:

the first step is as follows: fixing a solid rocket engine (10) on a workbench (16) by using a fixture (17);

the second step is as follows: planning hole layout and specific punching positions according to the area of the blocking piece (12);

the third step: adjusting the position and height of the lifting support (6) to a position to be punched, cleaning and wiping the surfaces of the spray pipe (11) and the blocking piece (12), observing and confirming that no foreign matter exists on the surfaces of the spray pipe (11) and the blocking piece (12) or other factors possibly influencing punching safety;

the fourth step: rotating the rocking handle (5), punching on the surface of the plug (12), wherein the punching operation is carried out intermittently, the punching depth is observed at any time in the punching process, and residues, scraps and other redundancies generated in the punching process are cleaned in time;

the fifth step: after the punching operation is finished, the central hole (13) is used as a main stress supporting point, and an external force is applied to the direction of the circumferential hole (14) by using a tool to realize the partial stripping operation of the blocking piece (12) and form an irregular partial stripping blocking piece area (15);

a sixth step: determining whether the punching operation needs to be continued or not according to the stripping condition of the blocking piece (12), and if so, stripping the blocking piece (12) after punching is finished at the corresponding position;

a seventh step of: after all stripping operations are finished, the subsequent cleaning of the opening part of the spray pipe (11) is carried out by using a tool, so that the opening part of the spray pipe (11) is smooth and has no residues such as sharp blocking pieces and the like.

4. The method of claim 3, wherein: the layout of the planning holes and the specific punching position at least comprise a central hole (13) and a plurality of symmetrically arranged circumferential holes (14).

Technical Field

The invention relates to a device and a method for safely removing a solid rocket engine nozzle blocking piece, in particular to a solid rocket engine nozzle blocking piece dismounting device constructed based on a screw transmission principle, and belongs to the field of solid rocket engine safety evaluation.

Background

The high-altitude simulation test of the solid rocket engine is an important test means for obtaining the ballistic performance of the engine in a high-altitude ignition state and evaluating the safety of the high-altitude ignition process of the engine. After the engine is ignited at high altitude, the engine is influenced by the dynamic effect of the external low-pressure environment and the high-speed flying of the engine, and a suction phenomenon can be formed at the nozzle of the engine. In order to fully simulate the phenomenon, before the engine carries out a simulated high-altitude ignition test, the plug sheet at the nozzle of the engine nozzle needs to be opened, so that the inner cavity of the engine is communicated with the external low-pressure environment, and a suction phenomenon at the nozzle of the engine nozzle is artificially caused, thereby achieving the purpose of better simulating the high-altitude flight state of the engine. However, in the process of removing the nozzle blockage of the engine, the following technical problems mainly exist: firstly, the area of the nozzle blocking piece is narrow and is close to the throat lining part, and the design shape of the nozzle is usually concave, so the difficulty of the blocking piece removing process is high, and the throat lining is possibly damaged due to improper operation; secondly, in order to guarantee that the nozzle blocking piece can be got rid of completely, need carry out drilling operation on the blocking piece surface, and current drilling tool can't satisfy the demand of nozzle department blocking piece surface drilling operation because the restriction in aspects such as safety reason and structure. Therefore, there is a need to develop a device and a use method capable of meeting the requirement of safely removing the nozzle blocking piece of the solid rocket engine.

Disclosure of Invention

The invention aims to provide a device for safely removing a solid rocket engine nozzle blocking piece, which aims to solve the problem of safely removing the solid rocket engine nozzle blocking piece.

In order to solve the existing technical problems, the invention adopts the technical scheme that: a device for safely removing a solid rocket engine nozzle blocking piece comprises a drill bit, a screw, a sleeve, a rocking handle and a lifting support, wherein the tail part of the screw is connected with the rocking handle, the middle part of the screw is arranged in the sleeve, the head part of the screw is connected with the drill bit, and when the rocking handle is rotated, the screw moves along the thread direction and drives the drill bit to rotate forwards, so that the surface of the solid rocket engine nozzle blocking piece is punched; the sleeve is fixed on the lifting bracket through a fixed snap ring.

In order to avoid the drill bit from accidentally damaging the throat insert due to the excessively high drilling speed, the device also comprises a buffer spring, and the buffer spring is arranged on the tail part of the screw rod between the sleeve and the rocking handle and used for limiting the drilling speed.

The invention also discloses a method for safely removing the nozzle blocking piece of the solid rocket engine, which comprises the following specific steps:

the first step is as follows: fixing the solid rocket engine on the workbench by using a fixture;

the second step is as follows: planning hole layout and specific punching positions according to the size of the area of the blocking piece;

the third step: adjusting the position and height of the lifting support to a position to be punched, cleaning and wiping the surfaces of the spray pipe and the blocking piece, observing and confirming that no foreign matter exists on the surfaces of the spray pipe and the blocking piece or other factors possibly influencing punching safety;

the fourth step: rotating the rocking handle to punch on the surface of the plug, wherein the punching operation is carried out intermittently, the punching depth is observed at any time in the punching process, and residues, scraps and other redundancies generated in the punching process are cleaned in time;

the fifth step: after the punching operation is finished, the central hole is taken as a main stress supporting point, and an external force is applied to the direction of the circumferential hole by using a tool, so that the partial stripping operation of the blocking piece is realized, and an irregular region for partially stripping the blocking piece is formed;

a sixth step: determining whether the punching operation needs to be continued or not according to the stripping condition of the blocking piece, and if so, stripping the blocking piece after punching is finished at the corresponding position;

a seventh step of: after all stripping operations are completed, the subsequent cleaning of the nozzle opening is carried out by using a tool, so that the nozzle opening is smooth and has no residues such as sharp blocking pieces and the like.

Generally, a proper hole layout and punching position can be adopted according to the area of the blocking piece, and particularly, the planned hole layout and the specific punching position at least comprise a central hole and a plurality of symmetrically-arranged circumferential holes.

According to the invention, by adopting a screw transmission principle and carrying the spring buffer component, manual punching operation of an operator on the surface of the plug at the engine spray pipe can be realized, electric drilling tools such as an electric drill and the like are avoided, the punching force and depth can be effectively controlled, and accidental damage to the throat insert caused by over-fast or over-deep punching is avoided. After the punching operation is finished, the central hole can be used as a main stress supporting point, and the stripping and removal of the engine spray pipe blocking piece are realized by applying external force to the direction of the circumferential hole. Therefore, the invention adopts a simpler and more convenient and practical method to provide technical support for the safety evaluation test of the high-altitude simulation ignition process of the engine

Advantageous effects

The device is small in size and can be conveniently adjusted according to the placement position and the direction of the engine; the device realizes the forward rotation movement of the drill bit based on the screw transmission principle, and 1 operator can carry out manual operation; the device is provided with the buffer spring, so that the punching progress and depth can be effectively controlled, and the throat insert at the spray pipe is prevented from being damaged by punching operation; the device avoids using an external power supply, is suitable for fixing energetic products such as rocket engines and the like, and improves the intrinsic safety of the operation link.

The invention uses a simpler and more convenient mode, realizes the safe removal operation of the plug sheet at the nozzle of the engine and provides technical support for the development of the high-altitude simulation test of the engine.

Drawings

Fig. 1 is a schematic view of a punching apparatus, which includes: the drill bit 1, the screw rod 2, the sleeve 3, the buffer spring 4, the rocking handle 5, the lifting support 6 and the fixed clamping ring 7.

Fig. 2 is a schematic diagram of a punching apparatus, which includes: the drill bit 1, the screw rod 2, the sleeve 3, the buffer spring 4, the rocking handle 5, the lifting support 6, the fixed clamping ring 7, the nut 8 and the screw 9.

FIG. 3 is a schematic illustration of a nozzle vane removal process, including: the solid rocket engine 10, a nozzle 11, a blocking piece 12, a central hole 13, a circumferential hole 14, a region 15 for stripping part of the blocking piece, a workbench 16 and a clamp 17.

Detailed Description

The present invention will be further described with reference to the accompanying drawings and with reference to specific embodiments of the removal operation of the nozzle plate of a solid rocket engine of a certain type.

As shown in fig. 1-2, a device for safely removing a nozzle plate of an engine based on a screw driving principle comprises: the drill bit 1, the screw rod 2, the sleeve 3, the buffer spring 4, the rocking handle 5, the lifting support 6, the fixed snap ring 7 and the like. The size of the drill bit 1 is properly selected according to the area of the engine nozzle blocking piece; the screw 2 is connected with the rocking handle 5 and fixed by the nut 8, the screw 2 is connected with the drill bit 1 through the sleeve 3, when an operator rotates the rocking handle 5, the screw 2 moves along the thread direction and drives the drill bit 1 to rotate forwards, and therefore the purpose of punching on the surface of the engine nozzle plug is achieved; the buffer spring 4 is arranged on the tail part of the screw rod 2 between the sleeve 3 and the rocking handle 5, and is mainly used for realizing the purposes of limiting the punching speed and effectively controlling the punching depth and avoiding the accidental damage of the throat insert caused by too fast or too deep punching of the drill bit 1; drill bit 1, screw rod 2, sleeve 3, buffer spring 4, rocking handle 5 constitute manual drilling equipment's main part jointly to on being fixed in elevating bracket 6 with manual drilling equipment main part through fixed snap ring 7, fixed snap ring 7 passes through the screw 9 to be fixed on elevating bracket 6, and then can make things convenient for operating personnel to punch the operation according to engine spray tube position and the altitude mixture control perforating device to suitable position that needs the position of punching.

As shown in fig. 3, after the solid rocket engine 10 is fixed on a workbench 16 through a fixture 17 and the engine nozzle is exposed to a proper position, the height of the perforating device is adjusted to perform perforating operation, and after the perforating operation is completed, the stripping and removing operation of the nozzle plug can be performed by using tools such as sharp-nose pliers.

The specific steps of the operation for safely removing the nozzle blocking piece of the solid rocket engine are as follows:

the first step is as follows: the solid rocket engine 10 is fixed on the workbench 16 by using the fixture 17, and the engine nozzle 11 is exposed at a proper position, so that the subsequent nozzle plug piece removing operation is convenient for an operator;

the second step is as follows: planning hole layout and specific punching positions according to the area of the blocking piece 12, wherein the hole layout and the specific punching positions at least comprise a central hole 13 and a plurality of symmetrically arranged circumferential holes 14;

the third step: adjusting the position and the height of the lifting support 6 to a position to be punched according to the position of the nozzle plugging piece, cleaning and wiping the surfaces of the nozzle 11 and the plugging piece 12, observing and confirming that no foreign matters exist on the surfaces of the nozzle 11 and the plugging piece 12 or other factors possibly influencing punching safety;

the fourth step: rotating the rocking handle 5, punching the surface of the plug 12 intermittently, observing the punching depth at any time during punching, and timely cleaning residues, scraps and other redundancies generated during punching;

the fifth step: after the punching operation is finished, the central hole 13 is taken as a main stress supporting point, and external force is applied to the direction of the circumferential hole 14 by using tools such as sharp-nose pliers and the like, so that the partial stripping operation of the blocking piece 12 is realized, and an irregular partial stripping blocking piece area 15 is formed;

a sixth step: determining whether the punching operation needs to be continued or not according to the stripping condition of the blocking piece 12, and if so, continuing to perform the stripping operation of the blocking piece 12 after the punching operation is finished at the corresponding position;

a seventh step of: after all stripping operations are completed, subsequent cleaning of the nozzle 11 opening is performed by using tools such as sharp-nose pliers and the like, so that the nozzle opening is smooth and has no residues such as sharp-pointed blocking pieces and the like.

The device and the method for safely removing the solid rocket engine nozzle blocking piece can solve the problem of safely removing the engine nozzle blocking piece and provide technical support for a test run test of simulating the high-altitude environment on the ground of the solid rocket engine.