CN221683083U - Solid rocket engine test fire extinguishing device - Google Patents

Abstract

The utility model relates to the technical field of solid rocket engine simulation test, and provides a solid rocket engine test fire extinguishing device, including a rocker arm and a fire extinguishing nozzle, one end of the rocker arm is connected to a rotary mechanism, and the other end is connected to an extension rod, and the fire extinguishing nozzle is installed at the end of the extension rod away from the rocker arm; a linear telescope, the linear telescope is fixedly connected to the middle part of the rocker arm, and the fire extinguishing nozzle is driven to extend and rotate through the rotary mechanism and the linear telescope. The utility model can facilitate the fire extinguishing nozzle to extend into the engine nozzle for fire extinguishing.

Description

A solid rocket engine test fire extinguishing device

Technical Field

The utility model relates to the technical field of solid rocket engine simulation test, in particular to a solid rocket engine test fire extinguishing device.

Background Art

The high-altitude simulation test is an ignition test of a solid rocket engine conducted in a simulated high-altitude, low-pressure environment. It is an indispensable test method for the development of high-altitude working engines. It mainly assesses the structure and performance of the engine's high-altitude nozzle and verifies the reliability of the engine's operation at high altitudes.

The inner wall of a solid rocket engine works for a long time at a high temperature of more than 3000K and an internal pressure of 5-10MPa or even higher. With the widespread adoption of high-energy propellants, as well as the emergence of advanced charge design and large charge casting technology, the operating temperature and pressure of the combustion chamber will be further increased. Therefore, thermal protection measures have to be taken in the engine structure design, and ablation-resistant composite materials are used as the lining insulation layer. This structural design, including insulation layer ablation, multi-layer composite heat transfer and thermal strength, is called rocket engine thermal structure design.

After the test run, the propellant column has finished burning, and a special fire extinguishing device is needed to cool down and extinguish the engine nozzle and inner shell, so as to recover a relatively complete insulation layer. At present, after the high-altitude simulation test, the engine is extinguished naturally to extinguish the residual fire in the combustion chamber. After the high-altitude test, the internal insulation layer and partition of the engine continue to burn, continuously ablating the engine combustion chamber and nozzle. The structure of the combustion chamber, nozzle and other components is difficult to withstand long-term high-temperature burning. It is difficult to maintain the solidification of the natural flameout at the time when the engine ends, which increases the difficulty of analysis and judgment for designers. Therefore, it is necessary to design a device that is easy to extend into the engine for auxiliary fire extinguishing.

Utility Model Content

The utility model aims to provide a solid rocket engine test fire extinguishing device which can be conveniently extended into the engine nozzle to spray material for fire extinguishing.

The embodiment of the utility model is realized through the following technical scheme: a solid rocket engine test fire extinguishing device, comprising a rocker arm and a fire extinguishing nozzle, one end of the rocker arm is connected to a rotating mechanism, and the other end thereof is connected to an extension rod, and the fire extinguishing nozzle is installed at the end of the extension rod away from the rocker arm; a linear telescope, the linear telescope is fixedly connected to the middle part of the rocker arm, and the fire extinguishing nozzle is driven to retract and rotate through the rotating mechanism and the linear telescope.

Preferably, it also includes a support frame and a mounting frame, the rocker arm passes through the support frame and is fixedly connected thereto, the slewing mechanism is installed at one end of the support frame, and the telescopic end of the linear telescope is connected to the support frame; the linear telescope is arranged in the mounting frame, and the rocker arm passes through the mounting frame, and one side end surface of the support frame is slidably connected to the inner wall of the mounting frame.

Preferably, the slewing mechanism comprises a reducer and a slewing drive motor, the reducer is connected to the tail end of the rocker arm, and the slewing drive motor is connected to the reducer.

Preferably, it further comprises a diaphragm coupling, and two ends of the diaphragm coupling are respectively connected to the reducer and the rocker arm.

Preferably, it further comprises a counterweight block, which is detachably mounted on an end of the support frame away from the fire extinguishing nozzle, and the counterweight block is arranged below the reducer.

Preferably, the linear telescopic device adopts an electric cylinder or a telescopic cylinder, and the telescopic direction of the linear telescopic device is consistent with the length direction of the rocker arm.

Preferably, the extension rod is vertically connected to the rocker arm, and a reinforcing rib plate is provided at the angle between the extension rod and the rocker arm.

Preferably, the fire extinguishing nozzle sprays gas or liquid substances.

The technical solution of the embodiments of the utility model has at least the following advantages and beneficial effects: the utility model arranges the device beside the engine nozzle under test. After the test is completed, the linear telescopic device drives the rocker arm and the fire extinguishing nozzle to move forward a distance and then rotate and recover to align with the engine nozzle orifice, and then the fire extinguishing nozzle is extended to spray inert gas to automatically extinguish the fire. The use is convenient and simple.

BRIEF DESCRIPTION OF THE DRAWINGS

In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the utility model and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying creative work.

FIG1 is a schematic structural diagram of a solid rocket engine test fire extinguishing device provided by an embodiment of the utility model;

FIG2 is a schematic diagram of the connection structure of the rocker arm, the rotary mechanism and the linear telescopic device in the utility model;

FIG3 is a schematic diagram of the solid rocket engine test fire extinguishing device of the present invention extending into the engine nozzle to extinguish the fire.

Icons: 1-engine nozzle, 2-rocker arm, 3-fire extinguishing nozzle, 4-extension rod, 41-reinforcement rib plate, 5-slewing mechanism, 51-reducer, 52-slewing drive motor, 53-diaphragm coupling, 6-linear expansion joint, 7-support frame, 8-installation frame, 9-counterweight.

DETAILED DESCRIPTION

In order to make the purpose, technical solution and advantages of the embodiment of the utility model clearer, the technical solution in the embodiment of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiment of the utility model. Obviously, the described embodiment is a part of the embodiment of the utility model, not all of the embodiments. Generally, the components of the embodiment of the utility model described and shown in the drawings here can be arranged and designed in various different configurations.

Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the present invention to be protected, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not require further definition and explanation in the subsequent drawings.

Example

The following is further described in conjunction with a specific embodiment. As shown in Figures 1 to 3, this embodiment is a solid rocket engine test fire extinguishing device, including a rocker arm 2 and a fire extinguishing nozzle 3, one end of the rocker arm 2 is connected to a rotating mechanism 5, and the other end is connected to an extension rod 4, and the fire extinguishing nozzle 3 is installed at the end of the extension rod 4 away from the rocker arm 2; a linear telescope 6, the linear telescope 6 is fixedly connected to the middle part of the rocker arm 2, and the fire extinguishing nozzle 3 is driven to retract and rotate through the rotating mechanism 5 and the linear telescope 6; specifically, the engine nozzle 1 There is a small hole in the middle of the fire extinguishing nozzle 3, and the fire extinguishing nozzle 3 cooperates with the extension rod 4 and the rocker arm 2. The rocker arm 2 has two degrees of freedom under the action of the rotary mechanism 5 and the linear telescopic device 6. The linear telescopic device 6 first drives the rocker arm 2 to extend, and the rotary mechanism 5 drives the rocker arm 2, the extension rod 4 and the fire extinguishing nozzle 3 to rotate and align with the orifice of the engine nozzle 1. The linear telescopic device 6 is then retracted, so that the fire extinguishing nozzle 3 can be connected to the engine nozzle 1. The fire extinguishing nozzle 3 can spray inert gas and other objects to extinguish the fire. The operation is convenient and simple, and the practicality is good.

It is worth noting that a non-contact temperature measuring head can be used to monitor the temperature of the engine nozzle 1 .

As shown in Figure 1, this embodiment also includes a support frame 7 and a mounting frame 8. The rocker arm 2 passes through the support frame 7 and is fixedly connected thereto. The slewing mechanism 5 is installed at one end of the support frame 7, and the telescopic end of the linear telescope 6 is connected to the support frame 7. The linear telescope 6 is arranged in the mounting frame 8, and the rocker arm 2 passes through the mounting frame 8. One side end surface of the support frame 7 is slidably connected to the inner wall of the mounting frame 8. Specifically, when the linear telescope 6 is telescoped, the support frame 7, the rocker arm 2 and the slewing mechanism 5 move linearly synchronously.

The rotary mechanism 5 in this embodiment includes a reducer 51 and a rotary drive motor 52. The reducer 51 is connected to the tail end of the rocker arm 2, and the rotary drive motor 52 is connected to the reducer 51. Specifically, an encoder is also provided at one end of the reducer 51. The rotary drive motor 52 controls the rotation of the rocker arm 2 in combination with the reducer 51. The reducer 51 adopts an RV reducer and has a self-locking characteristic.

As shown in FIG2 , the present embodiment further includes a diaphragm coupling 53, the two ends of which are connected to the reducer 51 and the rocker arm 2 respectively. The diaphragm coupling 53 is composed of several groups of diaphragms (stainless steel sheets) connected to the two half couplings by bolts in an interlaced manner. Each group of diaphragms is composed of several stacked pieces. The diaphragms are divided into connecting rod type and whole piece type of different shapes. The diaphragm coupling 53 compensates the relative displacement of the two connected shafts by the elastic deformation of the diaphragm. It is a high-performance metal strong element flexible coupling, which does not require lubrication, has a compact structure, high strength, long service life, no rotation gap, is not affected by temperature and oil pollution, has the characteristics of acid resistance, alkali resistance and corrosion resistance, and is suitable for shaft transmission in high temperature, high speed and corrosive medium working environment, and compensates for the thermal expansion of the shaft system and equipment in a variable temperature environment.

The present embodiment also includes a counterweight block 9, which is detachably mounted on one end of the support frame 7 away from the fire extinguishing nozzle 3, and the counterweight block 9 is arranged below the reducer 51; specifically, to avoid one end of the rocker arm 2 extending too long, resulting in uneven weighting at both ends of the rocker arm 2, the counterweight block 9 can be used to adjust to ensure smooth linear movement of the rocker arm 2.

It is worth noting that the linear telescopic device 6 adopts an electric cylinder or a telescopic cylinder, and the telescopic direction of the linear telescopic device 6 is consistent with the length direction of the rocker arm 2.

As shown in Figure 2, the extension rod 4 in this embodiment is vertically connected to the rocker arm 2, and a reinforcing rib plate 41 is provided at the angle between the extension rod 4 and the rocker arm 2; specifically, the extension rod 4 and the rocker arm 2 form an L-shaped structure, and the reinforcing rib plate 41 can increase the strength of the connection between the extension rod 4 and the rocker arm 2 to prevent the extension rod 4 from breaking.

The fire extinguishing nozzle 3 sprays gas or liquid substances; specifically, in most cases, gas is used for fire extinguishing, such as carbon dioxide or nitrogen. Compared with using a conventional fire truck spray gun to spray water directly into the diffuser to extinguish the engine fire, cooling water is difficult to spray into the combustion chamber. Most of the cooling water will hit the inner wall of the diffuser and flow into the high-altitude cabin, polluting the test environment and causing energy waste. Carbon dioxide gas fire extinguishing can fully cover the combustion chamber.

The above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims (8)

1. A solid rocket engine test fire extinguishing device is characterized in that: the fire extinguishing device comprises a rocker arm (2) and a fire extinguishing nozzle (3), wherein one end of the rocker arm (2) is connected with a rotary mechanism (5), the other end of the rocker arm is connected with an extension rod (4), and the fire extinguishing nozzle (3) is arranged at one end, far away from the rocker arm (2), of the extension rod (4);

The linear expansion device (6), the linear expansion device (6) is fixedly connected with the middle part of the rocker arm (2), and the fire extinguishing spray head (3) is driven to stretch and rotate through the slewing mechanism (5) and the linear expansion device (6).

2. The solid rocket engine test fire extinguishing apparatus according to claim 1, wherein: the swing mechanism (5) is arranged at one end of the supporting frame (7), and the telescopic end of the linear telescopic device (6) is connected with the supporting frame (7);

The linear expansion device (6) is arranged in the installation frame (8), the rocker arm (2) penetrates through the installation frame (8), and one side end face of the supporting frame (7) is connected with the inner wall of the installation frame (8) in a sliding mode.

3. The solid rocket engine test fire extinguishing apparatus according to claim 2, wherein: the swing mechanism (5) comprises a speed reducer (51) and a swing driving motor (52), the speed reducer (51) is connected with the tail end of the rocker arm (2), and the swing driving motor (52) is connected with the speed reducer (51).

4. A solid rocket engine test fire suppression apparatus according to claim 3, wherein: the speed reducer is characterized by further comprising a diaphragm coupler (53), wherein two ends of the diaphragm coupler (53) are respectively connected with the speed reducer (51) and the rocker arm (2).

5. A solid rocket engine test fire suppression apparatus according to claim 3, wherein: still include balancing weight (9), balancing weight (9) dismantlement install in supporting frame (7) keep away from the one end of shower nozzle (3) that puts out a fire, just balancing weight (9) are located the below of speed reducer (51).

6. The solid rocket engine test fire extinguishing apparatus according to claim 1, wherein: the linear expansion device (6) adopts an electric cylinder or a telescopic cylinder, and the expansion direction of the linear expansion device (6) is consistent with the length direction of the rocker arm (2).

7. The solid rocket engine test fire extinguishing apparatus according to claim 1, wherein: the extension rod (4) is vertically connected with the rocker arm (2), and a reinforcing rib plate (41) is arranged at an included angle between the extension rod (4) and the rocker arm (2).

8. The solid rocket engine test fire extinguishing apparatus according to claim 1, wherein: the spraying material of the fire extinguishing spray head (3) adopts gas or liquid substances.