A self-deployment structure for extending nozzle of rocket engine

Abstract

The invention relates to a self-deploying structure for an extended nozzle of a rocket engine, belonging to the technical field of rocket engine performance; the structure comprises an extended nozzle, an upper sub-stage, an interstage section, a lower sub-stage and a ball lock; wherein the upper sub-stage, the interstage section and the lower sub-stage are all barrel section structures; the upper sub-stage, the interstage section and the lower sub-stage are coaxially butted in sequence along the axial direction; the extended nozzle is coaxially arranged in the inner cavity of the interstage section; one axial end of the extended nozzle is fixedly connected to the upper sub-stage; the other axial end of the extended nozzle is connected to the lower sub-stage through a ball lock; the extended nozzle is deployed along the axial direction; the invention further reduces the structural mass of the extended nozzle and improves the overall performance advantage of the extended nozzle technology.

Description

Technical Field

[0001] The invention belongs to the technical field of rocket engine performance, and relates to a self-deployment structure for an extended nozzle of a rocket engine. Background Art

[0002] In order to further improve the specific impulse of rocket engines and the overall flight performance of rockets, the current main choice is to design tail nozzles with larger expansion ratios to adapt to the expansion of the jet under high altitude and low ambient pressure. However, the larger expansion ratio further increases the length of the nozzle, which not only increases the difficulty of nozzle manufacturing, but also causes problems such as increased overall size and mass of the rocket.

[0003] The current extended nozzle technology mainly includes the extended nozzle itself, an actuating device, a locking device and an actuating energy source. Its structure is more complicated than that of the traditional nozzle, which leads to an increase in the overall mass and reduces the advantages brought by using the extended nozzle. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art and to propose a self-deployment structure for an extended nozzle of a rocket engine, so as to further reduce the mass of the extended nozzle structure and improve the overall performance advantages of the extended nozzle technology.

[0005] The solution of the present invention is:

[0006] A self-deploying structure for an extended nozzle of a rocket engine, comprising an extended nozzle, an upper sub-stage, an inter-stage section, a lower sub-stage and a ball lock;

[0007] Among them, the upper sub-stage, the interstage section, and the lower sub-stage are all barrel section structures; the upper sub-stage, the interstage section, and the lower sub-stage are coaxially connected in sequence along the axial direction; the extension nozzle is coaxially arranged in the inner cavity of the interstage section; one axial end of the extension nozzle is fixedly connected to the upper sub-stage; the other axial end of the extension nozzle is connected to the lower sub-stage through a ball lock; the extension nozzle is expanded along the axial direction.

[0008] In the above-mentioned self-deployment structure for an extended nozzle of a rocket engine, the extended nozzle comprises an extended cone, a fixed cone, a foam guide mechanism and a self-locking piece;

[0009] The extension cone and the fixed cone are both hollow cone structures placed axially horizontally; the fixed cone is coaxially arranged in the inner cavity of the extension cone; the self-locking sheet is arranged on the outer wall of the large diameter end of the fixed cone; the foam guide mechanism is a cone structure; and the foam guide mechanism is attached to the inner wall of the extension cone.

[0010] In the above-mentioned self-deployment structure for the extended nozzle of a rocket engine, a cylindrical through hole is provided at the axis of the foam guide mechanism; the diameter of the cylindrical through hole is the same as the diameter of the large diameter end of the fixed cone; the fixed cone is arranged in the through hole of the foam guide mechanism, so that when the extension cone is translated axially backward, the through hole of the foam guide mechanism realizes a guiding function.

[0011] In the above-mentioned self-deployment structure for the extended nozzle of a rocket engine, the working process of the self-deployment structure is as follows:

[0012] After the engine in the upper sub-stage cavity is ignited, high pressure is generated to push the lower sub-stage to separate from the interstage section axially; the lower sub-stage pulls the extension cone to translate relative to the fixed cone through the ball lock; after the extension cone translates into place, the ball lock breaks under the continued action of high pressure, and the lower sub-stage separates.

[0013] In the above-mentioned self-deployment structure for an extended nozzle of a rocket engine, the extension cone has the same taper as the fixed cone, and the diameter of the small diameter end of the extension cone is the same as the diameter of the large diameter end of the fixed cone; after the extension cone is translated into position relative to the fixed cone, the small diameter end of the extension cone docks with the large diameter end of the fixed cone.

[0014] In the above-mentioned self-deployment structure for the extended nozzle of a rocket engine, after the extended cone is translated into position relative to the fixed cone, the extended cone and the fixed cone are locked by a self-locking piece to achieve locking of the extended nozzle.

[0015] In the above-mentioned self-deployment structure for the extended nozzle of a rocket engine, after the extension cone is translated into position, the foam guide mechanism is burned and removed under the action of the high-temperature combustion gas of the engine in the upper sub-stage.

[0016] In the above-mentioned self-deployment structure for the extended nozzle of a rocket engine, the built-in pressure time in the interstage section is controlled by designing an optimized timing, so as to adjust the deployment speed of the extended nozzle and prevent collision damage and deployment failure between the extended cone and the fixed cone caused by the extension cone moving too fast or too slow.

[0017] In the above-mentioned self-deployment structure for the extended nozzle of a rocket engine, after design, the pressure build-up time in the interstage is 10-50ms.

[0018] In the above-mentioned self-deployment structure for the extended nozzle of a rocket engine, it is characterized in that: after design, the deployment time of the extended nozzle is 20ms.

[0019] The beneficial effects of the present invention compared with the prior art are:

[0020] (1) The extended nozzle self-deployment scheme of the present invention greatly simplifies the entire set of extended nozzle separation, unlocking, deployment and locking devices, reduces the weight of the entire system structure, and improves the overall performance indicators of the rocket;

[0021] (2) The extended nozzle self-deployment scheme of the present invention can further shorten the length of the interstage, thereby further shortening the overall length of the rocket;

[0022] (3) The extended nozzle self-deployment scheme of the present invention can greatly simplify the extended nozzle deployment sequence and improve the reliability of the entire system. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is an overall schematic diagram of the self-deployment structure of the extended nozzle of the rocket engine of the present invention;

[0024] Figure 2 It is a schematic diagram of the extended nozzle retracted state of the present invention;

[0025] Figure 3 It is a schematic diagram of the extended nozzle of the present invention in the expanded state. DETAILED DESCRIPTION

[0026] The present invention will be further described below in conjunction with the embodiments.

[0027] The present invention provides a self-deployment structure for an extended nozzle of a rocket engine, which can be used to improve the specific impulse of the rocket engine, shorten the length of the rocket, and reduce the fuel consumption of the rocket. The self-deployment technology based on the extended nozzle can further reduce the mass of the extended nozzle structure and improve the overall performance advantage of the extended nozzle technology.

[0028] Used in rocket engine extended nozzle self-deployment structure, such as Figure 1 As shown, it specifically includes an extended nozzle, an upper sub-stage 3, an inter-stage section 4, a lower sub-stage 5 and a ball lock 6. The specific assembly relationship is:

[0029] The upper sub-stage 3, the interstage section 4, and the lower sub-stage 5 are all barrel section structures; the upper sub-stage 3, the interstage section 4, and the lower sub-stage 5 are coaxially connected in sequence along the axial direction; the extension nozzle is coaxially arranged in the inner cavity of the interstage section 4; one axial end of the extension nozzle is fixedly connected to the upper sub-stage 3; the other axial end of the extension nozzle is connected to the lower sub-stage 5 through a ball lock 6; the extension nozzle is expanded along the axial direction.

[0030] The extension nozzle includes an extension cone 1, a fixed cone 2, a foam guide mechanism 7 and a self-locking plate 8. The extension cone 1 and the fixed cone 2 are both hollow cone structures placed axially horizontally; the fixed cone 2 is coaxially arranged in the inner cavity of the extension cone 1, such as Figure 2 As shown, the self-locking piece 8 is arranged on the outer wall of the large diameter end of the fixed cone 2; the foam guide mechanism 7 is a cone structure; and the foam guide mechanism 7 is attached to the inner wall of the extension cone 1.

[0031] A cylindrical through hole is provided at the axis of the foam guide mechanism 7; the diameter of the cylindrical through hole is the same as the diameter of the large diameter end of the fixed cone 2; the fixed cone 2 is arranged in the through hole of the foam guide mechanism 7, so that when the extension cone 1 is translated axially backward, the through hole of the foam guide mechanism 7 realizes a guiding function.

[0032] The working process of the self-expanding structure is:

[0033] After the engine in the inner cavity of the upper sub-stage 3 is ignited, high pressure is generated to push the lower sub-stage 5 to separate from the interstage section 4 along the axial direction; the lower sub-stage 5 pulls the extension cone 1 to translate relative to the fixed cone 2 through the ball lock 6, as shown in FIG. Figure 3 As shown. After the extension cone 1 is translated into position, the ball lock 6 breaks under the continued action of high pressure, and the lower sub-stage 5 is separated. The extension cone 1 has the same taper as the fixed cone 2, and the diameter of the small diameter end of the extension cone 1 is the same as the diameter of the large diameter end of the fixed cone 2; after the extension cone 1 is translated into position relative to the fixed cone 2, the small diameter end of the extension cone 1 is butted against the large diameter end of the fixed cone 2.

[0034] After the extension cone 1 is translated relative to the fixed cone 2, the extension cone 1 and the fixed cone 2 are locked by the self-locking piece 8 to achieve the locking of the extension nozzle. After the extension cone 1 is translated, the foam guide mechanism 7 is burned and removed under the action of the high-temperature combustion gas of the engine in the upper sub-stage 3.

[0035] By designing an optimized timing, the built-in pressure time of the interstage section 4 is controlled, and the deployment speed of the extension nozzle is adjusted to prevent collision damage and deployment failure between the extension cone 1 and the fixed cone 2 caused by the extension cone 1 moving too fast or too slow.

[0036] Specifically, after design, the built-up pressure time of the interstage 4 is 10-50ms, and the deployment time of the extended nozzle is 20ms.

[0037] The present invention mainly utilizes the kinetic energy of the lower substage during the separation process as the kinetic energy source for the extension nozzle to be deployed, and utilizes the lower substage to move backward to pull the extension nozzle to be deployed. The lower substage is connected to the extension nozzle by a special ball lock 6, which can fix the extension cone in the initial stage, provide pulling force during the deployment process, and finally automatically unlock after the extension nozzle is deployed in place. The deployment direction is ensured by a foam guide mechanism 7 during the deployment process. And after the deployment is completed, the extension cone is locked by a self-locking piece 8.

[0038] The extended nozzle self-deployment timing design is as follows: after the upper stage engine ignites, the pressure in the interstage begins to build up, the interstage shell separates, the lower stage moves backward and the extended nozzle is deployed, and after it is deployed in place, the extended nozzle is unlocked from the lower stage, and the extended nozzle is deployed and locked. By adjusting and optimizing the timing design, the pressure build-up time in the interstage can be controlled, and then the speed at which the extended nozzle is deployed in place can be adjusted to prevent problems such as collision damage between the extended cone and the fixed cone and deployment failure caused by too fast or too slow speed.

[0039] The extended nozzle self-deployment scheme of the present invention greatly simplifies the entire set of separation, unlocking, deployment and locking devices of the extended nozzle, reduces the structural weight of the entire system, and improves the overall performance indicators of the rocket; and the extended nozzle self-deployment scheme can further shorten the length of the interstage section, thereby further shortening the overall length of the rocket; the extended nozzle self-deployment scheme can greatly simplify the extended nozzle deployment timing and improve the reliability of the entire system.

[0040] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A self-deploying structure for an extended nozzle of a rocket engine, characterized in that: It includes an extended nozzle, an upper sub-stage (3), an inter-stage section (4), a lower sub-stage (5) and a ball lock (6); The upper substage (3), the interstage section (4), and the lower substage (5) are all barrel-section structures; the upper substage (3), the interstage section (4), and the lower substage (5) are coaxially connected in sequence along the axial direction; the extension nozzle is coaxially arranged in the inner cavity of the interstage section (4); one axial end of the extension nozzle is fixedly connected to the upper substage (3); the other axial end of the extension nozzle is connected to the lower substage (5) via a ball lock (6); and the extension nozzle is expanded along the axial direction; The extension nozzle comprises an extension cone (1), a fixed cone (2), a foam guide mechanism (7) and a self-locking sheet (8); The extension cone (1) and the fixed cone (2) are both hollow cone structures placed axially horizontally; the fixed cone (2) is coaxially arranged in the inner cavity of the extension cone (1); the self-locking sheet (8) is arranged on the outer wall of the large diameter end of the fixed cone (2); the foam guide mechanism (7) is a cone structure; the foam guide mechanism (7) is attached to the inner wall of the extension cone (1); The foam guide mechanism (7) is provided with a cylindrical through hole at the axis thereof; the diameter of the cylindrical through hole is the same as the diameter of the large diameter end of the fixed cone (2); the fixed cone (2) is arranged in the through hole of the foam guide mechanism (7), so that when the extension cone (1) is translated backward along the axial direction, the through hole of the foam guide mechanism (7) realizes a guiding function; The working process of the self-expanding structure is: After the engine in the inner cavity of the upper sub-stage (3) is ignited, high pressure is generated to push the lower sub-stage (5) to separate from the interstage section (4) along the axial direction; the lower sub-stage (5) pulls the extension cone (1) to translate relative to the fixed cone (2) through the ball lock (6); after the extension cone (1) translates into place, the ball lock (6) breaks under the continued action of high pressure, and the lower sub-stage (5) is separated.

2. The self-deploying structure for the extended nozzle of a rocket engine according to claim 1, characterized in that: The extension cone (1) and the fixed cone (2) have the same taper, and the diameter of the small diameter end of the extension cone (1) is the same as the diameter of the large diameter end of the fixed cone (2); after the extension cone (1) is translated into position relative to the fixed cone (2), the small diameter end of the extension cone (1) is butted against the large diameter end of the fixed cone (2).

3. The self-deploying structure for the extended nozzle of a rocket engine according to claim 2, characterized in that: After the extension cone (1) is translated into position relative to the fixed cone (2), the extension cone (1) and the fixed cone (2) are locked by means of a self-locking sheet (8), thereby achieving locking of the extension nozzle.

4. The self-deploying structure for the extended nozzle of a rocket engine according to claim 1, characterized in that: After the extension cone (1) is translated into position, the foam guide mechanism (7) is burned and removed under the action of the high temperature combustion gas of the engine in the upper sub-stage (3).

5. The self-deploying structure for the extended nozzle of a rocket engine according to claim 1, characterized in that: By designing an optimized timing sequence, the built-in pressure time of the interstage section (4) is controlled, and the deployment speed of the extension nozzle is adjusted, thereby preventing the extension cone (1) (1) and the fixed cone (2) from being damaged by collision and deployment failure due to the extension cone (1) moving too fast or too slow.

6. The self-deploying structure for the extended nozzle of a rocket engine according to claim 5, characterized in that: After design, the built-in pressure duration of the interstage section (4) is 10-50ms.

7. The self-deploying structure for the extended nozzle of a rocket engine according to claim 5, characterized in that: After design, the deployment time of the extended nozzle is 20ms.

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