Self-adapting mechanism of solid rocket engine nozzle

Abstract

The utility model provides self -adaptation adjusting mechanism of solid rocket engine nozzle relates to rocket engine technical field, include: solid rocket engine propulsion device, the rear end fixed mounting of solid rocket engine propulsion device has the nozzle throat structure, the rear side fixed mounting of nozzle throat structure has the nozzle skirt structure, the rear end of nozzle skirt structure outer wall is provided with module assembly female section. The nozzle can according to the solid rocket altitude, the flexible dress has the adjusting mechanism of the nozzle expansion piece with the adaptive size, thereby avoids the problem that the rocket takes off after the nozzle expansion piece size is insufficient, cannot adjust to the best expansion ratio required to the corresponding height, and further influence engine propulsion efficiency, solved the fixed connection design of nozzle and adjusting mechanism, caused its unable to change according to the rocket altitude, the flexible replacement adjusting mechanism of adapting different height demand, difficult to realize the optimal expansion ratio adaptation in the whole flight section.

Description

Technical Field

[0001] This utility model relates to the field of rocket engine technology, and in particular to an adaptive adjustment mechanism for solid rocket engine nozzles. Background Technology

[0002] The nozzle of a solid rocket engine is one of its core components. Its main function is to efficiently convert the thermal and pressure energy of the high-temperature and high-pressure gas generated in the combustion chamber into kinetic energy, thereby generating thrust to propel the rocket forward. The expansion and adjustment of the nozzle are to adapt to the changes in atmospheric pressure at different flight altitudes, so that the gas can achieve optimal expansion within the nozzle, thereby maximizing the engine's specific impulse. The expansion of the nozzle requires the use of an adjustment mechanism.

[0003] In use, existing solid rocket motor nozzle adjustment mechanisms are usually fixedly connected to the nozzle. Although such adjustment mechanisms can adjust the nozzle expansion ratio within a certain range, their adjustable expansion ratio range is significantly limited due to their own size constraints. At the same time, the fixed connection design between the nozzle and the adjustment mechanism makes it impossible to flexibly replace the adjustment mechanism with one that adapts to different altitude requirements according to changes in the rocket's ascent altitude, making it difficult to achieve optimal expansion ratio adaptation throughout the entire flight phase. Summary of the Invention

[0004] This utility model relates to an adaptive adjustment mechanism for a solid rocket engine nozzle. By using a detachable modular connection between the adjustment mechanism and the nozzle structure, the nozzle can be fitted with an adjustment mechanism featuring a nozzle expander of appropriate size according to the rocket's ascent altitude. This prevents the nozzle expander from being unable to adjust to a suitable expansion ratio after rocket launch, thus avoiding impact on the rocket engine's propulsion efficiency. The adjustment mechanism uses an intelligent adjustment push rod to push the adjustment connection backward, causing it to move the sliding adjustment part and the nozzle expander backward. This backward movement of the nozzle expander increases the expansion ratio of the nozzle skirt structure, allowing the nozzle's expansion ratio to automatically adapt to the rocket's ascent altitude, ensuring appropriate thrust from the solid rocket engine.

[0005] In a first aspect, this utility model provides an adaptive adjustment mechanism for a solid rocket motor nozzle, specifically comprising: a solid rocket motor propulsion device; a nozzle throat structure fixedly mounted at the rear end of the solid rocket motor propulsion device; a nozzle skirt structure fixedly mounted at the rear side of the nozzle throat structure; a module assembly female section provided at the rear end of the outer wall of the nozzle skirt structure; threads formed on the outer wall of the module assembly female section; a module assembly male section threadedly mounted on the outer wall of the module assembly female section; a mounting plate fixedly mounted at the front end of the module assembly male section; a fixing plate fixedly mounted at the top of the mounting plate; a sliding adjustment part slidably mounted on the circumferential outer wall of the module assembly male section; an adjustment connection part fixedly mounted on the circumferential outer wall of the sliding adjustment part; and a nozzle expander fixedly mounted at the rear end of the sliding adjustment part.

[0006] Furthermore, the internal rear end of the module assembly male section has a conical structure, and the internal conical surface of the module assembly male section coincides with the internal conical surface of the module assembly female section.

[0007] Furthermore, the nozzle skirt structure is conical.

[0008] Furthermore, an intelligent adjustment push rod is fixedly installed on the fixed carrier plate.

[0009] Furthermore, the sliding adjustment part is fixedly connected to the output shaft of the intelligent adjustment push rod through the adjustment connection part.

[0010] Furthermore, the nozzle expander has a conical structure.

[0011] Furthermore, when the nozzle expander slides to the tail end of the module assembly section, the internal conical surface of the nozzle expander will coincide with the conical surface of the module assembly section.

[0012] This invention provides an adaptive adjustment mechanism for a solid rocket motor nozzle, which has the following advantages: 1. By designing the adjustment mechanism and nozzle structure as a detachable modular connection, the nozzle can be flexibly replaced with an adjustment mechanism with a nozzle expander of the appropriate size according to the launch altitude of the solid rocket. This avoids the problem that the nozzle expander is not large enough after the rocket is launched, which may prevent it from being adjusted to the optimal expansion ratio required for the corresponding altitude, thus affecting the engine's propulsion efficiency.

[0013] 2. The adjustment mechanism pushes the adjustment connection part backward through the intelligent adjustment push rod, which drives the sliding adjustment part and the nozzle expander to move backward synchronously. This allows the nozzle expander to increase the expansion ratio of the nozzle skirt structure through position change. This design allows the nozzle expansion ratio to be automatically adapted and adjusted with the rocket's altitude, ensuring that the solid rocket engine always maintains a suitable thrust output. Attached Figure Description

[0014] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings of the embodiments will be briefly described below.

[0015] The accompanying drawings described below are only related to some embodiments of the present invention and are not intended to limit the present invention.

[0016] In the attached diagram: Figure 1 A schematic diagram of the installation state of the smaller nozzle expander of this utility model is shown; Figure 2 A schematic diagram of the installation state of the larger nozzle expander of this utility model is shown; Figure 3 A schematic diagram of the nozzle expander of this utility model after adjustment is shown. Figure 4 A schematic diagram of the nozzle skirt structure and the nozzle expander component in a disassembled state is shown. Figure 5 A schematic diagram of the nozzle skirt structure and the nozzle expander of this utility model is shown in half section. List of reference numerals 1. Solid rocket motor propulsion device; 2. Nozzle throat structure; 3. Nozzle skirt structure; 4. Module assembly mother section; 5. Module assembly male section; 6. Mounting plate; 7. Fixed plate; 8. Intelligent adjustment push rod; 9. Sliding adjustment part; 10. Adjustment connection part; 11. Nozzle expansion component. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. Based on the described embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0018] Please refer to Figures 1 to 5 Example 1: This invention proposes an adaptive adjustment mechanism for a solid rocket motor nozzle, comprising: a solid rocket motor propulsion device 1; a nozzle throat structure 2 fixedly mounted at the rear end of the solid rocket motor propulsion device 1; a nozzle skirt structure 3 fixedly mounted at the rear side of the nozzle throat structure 2; a modular assembly female section 4 provided at the rear end of the outer wall of the nozzle skirt structure 3; threads formed on the outer wall of the modular assembly female section 4; and a modular assembly male section 5 threadedly mounted on the outer wall of the modular assembly female section 4. The nozzle can be flexibly fitted with an adjustment mechanism featuring a nozzle expander 11 of appropriate size according to the launch altitude of the solid rocket, thereby preventing the nozzle from being damaged by the nozzle expander after launch. 11. The size is insufficient and cannot be adjusted to the optimal expansion ratio required for the corresponding height; the front end of the module assembly section 5 is fixedly installed with a mounting plate 6; the top of the mounting plate 6 is fixedly installed with a fixing plate 7; a sliding adjustment part 9 is slidably installed on the outer circumference of the module assembly section 5; an adjustment connection part 10 is fixedly installed on the outer circumference of the sliding adjustment part 9; a nozzle expander 11 is fixedly installed at the rear end of the sliding adjustment part 9. The nozzle expander 11 increases the expansion ratio of the nozzle skirt structure 3 by changing its position. This design allows the nozzle expansion ratio to automatically adapt and adjust with the rocket's altitude, ensuring that the solid rocket engine always maintains a suitable thrust output.

[0019] In Example 2, based on Example 1, the internal rear end of the male section 5 of the module assembly is conical, and the internal conical surface of the male section 5 coincides with the internal conical surface of the female section 4 of the module assembly; the nozzle skirt structure 3 is conical; an intelligent adjustment push rod 8 is fixedly installed on the fixed carrier plate 7. During rocket ascent, the intelligent adjustment push rod 8 controls the sliding adjustment part 9 in real time, driving the nozzle expander 11 to move. The nozzle expander 11 changes the expansion ratio of the nozzle structure by moving. By using a detachable modular connection between the adjustment mechanism and the nozzle structure, the nozzle... The tube can be fitted with an adjustment mechanism for the nozzle expander 11 of appropriate size according to the launch altitude of the solid rocket. This avoids the nozzle expander 11 being unable to be adjusted to the appropriate expansion ratio due to insufficient size after the rocket launch, which would affect the propulsion efficiency of the rocket engine. In use, firstly, based on the flight altitude of the solid rocket, select the module assembly male section 5 with the nozzle expander 11 of appropriate size. Then, by threading the module assembly male section 5 onto the module assembly female section 4, the module assembly female section 4 and the module assembly male section 5 are stably connected, thus completing the connection between the nozzle structure and the adjustment mechanism.

[0020] In Example 3, based on Example 2, the sliding adjustment part 9 is fixedly connected to the output shaft of the intelligent adjustment push rod 8 via the adjustment connection part 10; the nozzle expander 11 has a conical structure; when the nozzle expander 11 slides to the tail end of the module assembly section 5, the inner conical surface of the nozzle expander 11 will coincide with the conical surface of the module assembly section 5. This adjustment mechanism pushes the adjustment connection part 10 backward via the intelligent adjustment push rod 8, causing it to move backward along with the sliding adjustment part 9 and the nozzle expander 11. This allows the nozzle expander 11 to increase the expansion ratio of the nozzle skirt structure 3 by moving backward, thereby enabling the nozzle expansion ratio to automatically adapt and adjust according to the rocket's altitude, ensuring that the thrust of the solid rocket engine is appropriate. After connection, it can be put into rocket launch operation. During launch, the intelligent adjustment push rod 8 can control the sliding adjustment part 9 to move along with the nozzle expander 11 in real time, causing the nozzle expander 11 to change the expansion ratio of the nozzle structure by moving, thereby using the change in expansion ratio to ensure that the thrust of the rocket engine is appropriate, playing an adaptive adjustment role for the solid rocket engine.

[0021] Working principle: During use, the operator needs to pre-calculate and select the appropriate nozzle expander module 11 based on the flight trajectory parameters of the mission, such as the target orbital altitude and atmospheric density change curve. Then, the male module assembly section 5 is installed on the female module assembly section 4 by thread, so that the female module assembly section 4 and the male module assembly section 5 form a stable connection, thereby completing the connection between the nozzle structure and the adjustment mechanism. After the connection is completed, the rocket can be put into the air for launch. During the rocket launch, the intelligent adjustment push rod 8 will control the sliding adjustment part 9 in real time, driving the nozzle expander 11 to move. The nozzle expander 11 changes the expansion ratio of the nozzle structure by moving, and uses the change in expansion ratio to ensure that the thrust of the rocket engine is in a suitable state, thereby realizing the adaptive adjustment of the solid rocket engine.

[0022] The following points should be noted in this article: 1. The accompanying drawings of this utility model embodiment only involve the structure involved in this utility model embodiment; other structures can refer to general designs.

[0023] 2. Where there is no conflict, the embodiments of this utility model and the features in the embodiments can be combined with each other to obtain new embodiments.

[0024] The above are merely specific embodiments of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the scope of the claims.

Claims

1. An adaptive adjustment mechanism for a solid rocket motor nozzle, comprising: A solid rocket motor propulsion device (1) is provided with a nozzle throat structure (2) fixedly installed at its rear end; a nozzle skirt structure (3) is fixedly installed on the rear side of the nozzle throat structure (2); characterized in that a module assembly mother section (4) is provided at the rear end of the outer wall of the nozzle skirt structure (3); a thread is provided on the outer wall of the module assembly mother section (4); a module assembly male section (5) is installed on the outer wall of the module assembly mother section (4) by thread; a mounting plate (6) is fixedly installed at the front end of the module assembly male section (5); a fixing plate (7) is fixedly installed on the top of the mounting plate (6); a sliding adjustment part (9) is slidably installed on the outer circumferential wall of the module assembly male section (5); an adjustment connection part (10) is fixedly installed on the outer circumferential wall of the sliding adjustment part (9); and a nozzle expansion part (11) is fixedly installed at the rear end of the sliding adjustment part (9).

2. The adaptive adjustment mechanism for the solid rocket motor nozzle according to claim 1, characterized in that, The internal rear end of the module assembly male section (5) has a conical structure, and the internal conical surface of the module assembly male section (5) coincides with the internal conical surface of the module assembly female section (4).

3. The adaptive adjustment mechanism for the solid rocket motor nozzle according to claim 1, characterized in that, The nozzle skirt structure (3) is conical.

4. The adaptive adjustment mechanism for the solid rocket motor nozzle according to claim 1, characterized in that, A smart adjustment push rod (8) is fixedly installed on the fixed carrier plate (7).

5. The adaptive adjustment mechanism for the solid rocket motor nozzle according to claim 1, characterized in that, The sliding adjustment part (9) is fixedly connected to the output shaft of the intelligent adjustment push rod (8) through the adjustment connection part (10).

6. The adaptive adjustment mechanism for the solid rocket motor nozzle according to claim 1, characterized in that, The nozzle expander (11) has a conical structure.

7. The adaptive adjustment mechanism for the solid rocket motor nozzle according to claim 1, characterized in that, When the nozzle expander (11) slides to the tail end of the module assembly section (5), the inner conical surface of the nozzle expander (11) will coincide with the conical surface of the module assembly section (5).

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