A solid rocket motor thrust vectoring nozzle based on flexible deformation of expansion section

Abstract

The present invention discloses a solid rocket engine thrust vectoring nozzle based on flexible deformation of an expansion section. The nozzle comprises a rigid base section, a flexible expansion section, and four drive devices. The rigid base section comprises a rigid convergent shell, a composite throat liner, and a rigid expansion shell. The flexible expansion section comprises a plurality of spring steel sheets and an anti-ablation elastic structure. One end of each spring steel sheet is mounted on the end of the rigid expansion shell away from the composite throat liner and arranged in a trumpet shape. The anti-ablation elastic structure is formed by pouring an anti-ablation elastic material onto each spring steel sheet, wrapping and connecting the spring steel sheets. The drive device comprises a servo system and a force transmission disc. The servo system comprises a power source, an actuator, and a transmission. The power source is connected to the actuator, the actuator is connected to the transmission, the transmission is connected to the force transmission disc, and the force transmission disc is connected to the flexible expansion section. The four power sources are evenly distributed around the outer circumference of the rigid base section. The present invention has the advantage of easy control of thrust vectoring.

Description

Technical Field

[0001] The present invention belongs to the technical field of solid rocket engine nozzles, and in particular relates to a solid rocket engine thrust vectoring nozzle based on flexible deformation of an expansion section. Background Art

[0002] The nozzle is a key component in solid rocket engines, converting thermal energy into kinetic energy. The development and application of thrust vectoring control technology is particularly important for improving nozzle performance. Conventional solid rocket engine nozzles often utilize a rigid expansion section, making direct thrust vectoring impossible. Thrust vectoring systems are generally categorized into four types: gas fins, spoilers, lateral nozzles, and oscillating nozzles, depending on the actuators used to generate lateral force. With the continuous advancement of solid rocket engine technology, these lateral force control methods have gradually exposed numerous challenges. For example, gas fins and spoilers require high thermal performance and are prone to erosion during operation. The lateral jet generated by the lateral nozzle significantly interferes with the internal gas flow field, resulting in actual lateral force far below the actual thrust. The oscillating nozzle, in order to ensure a tight seal at the joints, results in high friction. Therefore, developing thrust vectoring control technology for the nozzle itself that overcomes these limitations is crucial.

[0003] The flexible deformation nozzle with expansion section is a nozzle type with great development potential for solving the above-mentioned problems. The nozzle consists of a rigid base section and a flexible expansion section. Due to the deformation characteristics of the flexible expansion section material, the nozzle wall can be asymmetrically deformed through asymmetric outer wall constraints or concave nozzle wall constraints, thereby generating a thrust vector. However, most related research is focused on verifying the feasibility of generating thrust vectors with flexible walls, while there is little description of the control and specific implementation methods of the thrust vector. In addition, the thrust vector of the nozzle itself is still difficult to control.

[0004] Therefore, it is necessary to design a thrust vectoring nozzle for a solid rocket engine based on the flexible deformation of the expansion section. By controlling the deformation shape and size of the expansion section, the flow distribution of the gas in the nozzle can be significantly changed, thereby realizing the thrust vector control of the nozzle. Summary of the Invention

[0005] In order to solve the problem that the thrust vector of the nozzle itself is difficult to control, the present invention provides a solid rocket engine thrust vector nozzle based on flexible deformation of the expansion section.

[0006] The solid rocket engine thrust vector nozzle based on flexible deformation of the expansion section of the present invention comprises a rigid base section, a flexible expansion section and four drive devices;

[0007] The rigid foundation section includes a rigid convergent shell, a composite throat liner and a rigid expansion shell. The rigid convergent shell is fixedly connected to the rigid expansion shell. The composite throat liner is fixed to the inner wall of the rigid convergent shell and overlapped between the convergent section heat-insulating and ablation-resistant layer painted on the inner wall of the rigid convergent shell and the throat downstream heat-insulating and ablation-resistant layer painted on the inner wall of the rigid expansion shell.

[0008] The flexible expansion section includes several spring steel sheets and an anti-ablation elastic structure. One end of each spring steel sheet is mounted on the end of the rigid expansion shell away from the composite throat liner and arranged in a trumpet shape as a skeleton. The anti-ablation elastic structure is formed by pouring anti-ablation elastic material on each spring steel sheet and wrapping and connecting the spring steel sheets.

[0009] The driving device includes a servo system and a force transmission disc. The servo system includes a power source, an actuating part and a transmission part. The power source is connected to the actuating part, the actuating part is connected to the transmission part, the transmission part is connected to the force transmission disc, and the force transmission disc is connected to the flexible expansion section. The four power sources are evenly distributed around the outer circumference of the rigid base section.

[0010] Furthermore, the power source is secured via a wedge-shaped platform, the bottom of which is fixed to the outer wall of the rigid convergent housing at the throat. The wedge has a 15° angled wedge, and the power source is fixed to the wedge surface of the wedge. This wedge can greatly prevent the transmission connecting rod from locking when the drive device is operating.

[0011] Furthermore, spring steel sheets are mounted on the rigid expansion shell via a support ring. The thickness of the spring steel sheets decreases as the inner diameter of the nozzle's expansion section increases. The thicker end of the spring steel sheet is fixed to the support ring. The spring steel sheets are evenly distributed on the support ring, which is fixed to the end of the rigid expansion shell away from the composite throat liner. This reduces the overall weight of the component while providing support, thereby improving the overall efficiency of the nozzle.

[0012] Furthermore, the power source is a servo motor, the actuator includes a reduction gear set connected to the servo motor, and an electric push rod connected to the reduction gear set, the transmission unit includes a transmission connecting rod, a driven connecting rod, a flexible connector, and a limit bracket, one end of the transmission connecting rod is hinged to the telescopic end of the electric push rod, and the other end is hinged to the flexible connector, one end of the flexible connector is vertically fixed to the upper disk surface of the force transmission disc, the limit bracket includes a pair of parallel rods and a cross bar connected between the two rods, the bottom of the pair of parallel rods is fixed to the upper disk surface of the force transmission disc, one end of the driven connecting rod is hinged to the cross bar, and the other end is hinged to the middle of the transmission connecting rod, the lower disk surface of the force transmission disc is bonded to the outer wall of the flexible expansion section, and the axis of the force transmission disc is coplanar and perpendicular to the axis of the electric push rod. Because the entire drive device is driven by an electric motor, it has higher reliability, lower manufacturing and installation difficulty, and is simpler to use and maintain than hydraulic and pneumatic systems. Servo technology has also developed to a relatively mature stage and has obvious advantages in harsh operating environments with high temperatures and high speeds.

[0013] Furthermore, both the rigid convergent and expansion shells are constructed from 35CrMnSiA; the composite throat liner is made from a carbon / carbon composite, a high-melting-point metal, graphite, or a translucent material; and the ablation-resistant elastic material is EPDM. These materials are widely used and technically mature in this field, demonstrating stable and reliable performance in practical applications.

[0014] Beneficial effects: (1) Traditional gas rudders and spoilers work in high-temperature, high-speed and highly corrosive gas flows, which brings difficulties to the material selection of the rudders. The present invention installs the drive device on the outer wall of the nozzle, which reduces the material selection requirements. At the same time, the nozzle has thrust vector performance and is easy to control the thrust vector, which is beneficial to actual production; (2) The swing nozzle has high requirements for the sealing of the active surface, which leads to complex design of the internal profile of the nozzle. The present invention simplifies the internal structure of the nozzle and ensures the sealing of the nozzle; (3) The force is dispersed by the force transmission disk, which can make the deformation of the wall of the flexible expansion section more uniform and smooth, which is beneficial to reducing the thrust loss caused by the surface change. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a schematic diagram of the three-dimensional structure of the thrust vectoring nozzle of the solid rocket engine of the present invention;

[0016] Figure 2 This is a front view schematic diagram of the thrust vectoring nozzle of the solid rocket engine of the present invention;

[0017] Figure 3 for Figure 2 NN cross-section half-section diagram;

[0018] Figure 4 This is a schematic diagram of the structure of the spring steel sheet inside the flexible expansion section of the present invention;

[0019] Figure 5 Schematic diagram of the structure of the driving device in the present invention;

[0020] In the figure: 1. Thermal insulation and ablation-resistant layer of the convergent section; 2. Rigid convergent shell; 3. Drive device; 31. Servo motor; 32. Reduction gear set; 33. Electric push rod; 34. Transmission connecting rod; 35. Rotating shaft; 36. Driven connecting rod; 37. Limit bracket; 38. Flexible connector; 39. Force transmission disc; 4. Rigid expansion shell; 5. Anti-ablation elastic structure; 6. Spring steel sheet; 61. Support ring; 7. Composite throat liner; 8. Thermal insulation and ablation-resistant layer downstream of the throat. DETAILED DESCRIPTION

[0021] The present invention will now be further described in detail by way of embodiments with reference to the accompanying drawings, but the present invention is not limited to the embodiments.

[0022] like Figure 1-3 As shown, the present invention is a solid rocket engine thrust vector nozzle based on flexible deformation of the expansion section, which includes a rigid base section, a flexible expansion section and four identical drive devices 3.

[0023] The rigid foundation section includes a rigid convergent shell 2, a composite throat liner 7 and a rigid expansion shell 4. The rigid convergent shell 2 and the rigid expansion shell 4 are both made of 35CrMnSiA and are fixed by threaded connection. The composite throat liner 7 is fixed to the inner wall of the rigid convergent shell 2 and overlapped between the convergent section insulation and ablation-resistant layer 1 brushed on the inner wall of the rigid convergent shell 2 and the throat downstream insulation and ablation-resistant layer 8 brushed on the inner wall of the rigid expansion shell 4. Figure 3 shown.

[0024] The flexible expansion section includes four identical spring steel sheets 6, a support ring 61 and an anti-ablation elastic structure 5. The thickness of each spring steel sheet 6 decreases as the inner diameter of the nozzle expansion section increases, reaching the thinnest at the tail of the spring steel sheet 6. The head (thick end) of the spring steel sheet 6 is fixed on the support ring 61. The spring steel sheets 6 are evenly distributed on the support ring 61 and arranged in a trumpet shape, such as Figure 4 As shown. The support ring 61 is fixed to the end of the rigid expansion shell 4 away from the composite throat liner 7. The anti-ablation elastic structure 5 is formed by pouring an anti-ablation elastic material (such as anti-ablation EPDM rubber) on each spring steel sheet 6 and wrapping and connecting each spring steel sheet 6. The inner surface of the nozzle is complete without gaps, and the above-mentioned spring steel sheets 6 play the role of a skeleton. Specifically, a plurality of evenly distributed screw holes are provided along the circumference of the end of the rigid expansion shell 4 away from the composite throat liner 7, and corresponding mounting holes are provided on the support ring 61. Screws are used to fasten the rigid expansion shell 4 and the support ring 61; a mounting hole is provided on the head of the spring steel sheet 6, and corresponding screw holes are also provided on the support ring 61. Screws are used to fasten the spring steel sheet 6 and the support ring 61.

[0025] The driving device 3 includes a servo system and a force transmission disc 39. The servo system includes a power source, an actuating part and a transmission part. The power source is connected to the actuating part, the actuating part is connected to the transmission part, the transmission part is connected to the force transmission disc 39, and the force transmission disc 39 is connected to the flexible expansion section. The four power sources are evenly distributed around the outer circumference of the rigid base section.

[0026] Specifically, the four power sources are fixed by four wedge-shaped platforms. The bottom of the wedge-shaped platform is fixed to the outer wall of the rigid convergent shell 2 at the throat. The wedge-shaped platform has an angle of 15°. The wedge surface is provided with screw holes. The power source is fixed to the wedge surface of the wedge by screws. Figure 5 As shown, the power source is a servo motor 31; the actuating part includes a reduction gear set 32 ​​connected to the servo motor 31, and an electric push rod 33 connected to the reduction gear set 32; the transmission part includes a transmission connecting rod 34, a driven connecting rod 36, a flexible connecting member 38 and a limiting bracket 37; one end of the transmission connecting rod 34 is hinged to the telescopic end of the electric push rod 33, and the other end is hinged to the flexible connecting member 38, one end of the flexible connecting member 38 is vertically fixed to the upper disk surface of the force transmission disc 39; the limiting bracket 37 includes a pair of parallel rods and a cross bar connected between the two rods, the cross bar serves as a rotating shaft 35, the bottom of the pair of parallel rods is vertically bonded to the upper disk surface of the force transmission disc 39, one end of the driven connecting rod 36 is hinged on the cross bar, and the other end is hinged to the middle part of the transmission connecting rod 34, the lower disk surface of the force transmission disc 39 is bonded to the outer wall of the flexible expansion section, and the axis of the force transmission disc 39 is coplanar and perpendicular to the axis of the electric push rod 33.

[0027] More specifically, one end of the transmission link 34 is connected to the non-rotating rod eye of the telescopic end of the electric push rod 33 through a joint bearing. There are two driven links 36, which are located on both sides of the transmission link 34. One end of the two driven links 36 is hinged to the transmission link 34, and the other end is hinged to the cross bar of the limit bracket 37. The other end of the transmission link 34 is also hinged to the flexible connector 38 through a joint bearing. The flexible connector 38 is located between the two parallel rods of the limit bracket 37.

[0028] The above-mentioned servo motor 31, reduction gear set 32, electric push rod 33, transmission connecting rod 34, and flexible connecting member 38 form a branch chain. There are four such branch chains in total, and the size structure and connection method of the four branch chains are completely consistent, and are evenly distributed around the circumference. Each branch chain can be driven by the servo motor 31 to perform reciprocating linear motion under the limitation of the electric push rod 33 and the limiting bracket 37.

[0029] The composite throat liner 7 is made of any one of carbon / carbon composite materials, high melting point metals, graphite materials, and sweat-inducing materials.

[0030] The operating principle of the present invention is as follows: When the solid rocket motor does not require lateral control force, the drive unit 3 is in its zero position (neutral), and the nozzle axis has no angle of attack relative to the gas flow, thus generating no lateral force. When the solid rocket motor requires lateral control force, the drive unit 3 is powered by a servo motor 31. The control system transmits commands to the servo motor 31, which then rotates, undergoes deceleration and reversal through a reduction gear set 32, and transmits torque to an electric push rod 33, driving the electric push rod 33 in reciprocating linear motion. This in turn drives a transmission connecting rod 34 and a flexible connector 38, applying a force load to a force transmission disk 39. The force transmission disk 39 applies uniform pressure to the flexible expansion section, causing it to deform in a controlled manner. The deformation of the flexible expansion section forces the gas flow to produce an angular deviation relative to the nozzle axis, thereby achieving pitch and yaw control of the solid rocket motor. The control system indirectly adjusts the deformation shape and size of the flexible expansion section by controlling the output torque of the servo motor 31. The four drive units 3 work together to adjust the attitude of the solid rocket motor, thereby achieving thrust vector control.

[0031] The technologies not specifically mentioned above are all referenced to the existing technologies.

[0032] Based on the above-mentioned ideal embodiment of the present invention, and through the above description, relevant personnel can make various changes and modifications without departing from the scope of the technical concept of the present invention. The technical scope of the present invention is not limited to the contents of the specification.

Claims

1. A solid rocket engine thrust vectoring nozzle based on flexible deformation of the expansion section, characterized in that: It includes a rigid base section, a flexible expansion section and four drive devices (3); The rigid base section includes a rigid convergent shell (2), a composite throat liner (7) and a rigid expansion shell (4); the rigid convergent shell (2) is fixedly connected to the rigid expansion shell (4); the composite throat liner (7) is fixed to the inner wall of the rigid convergent shell (2) and overlapped between the convergent section heat-insulating and ablation-resistant layer (1) brushed on the inner wall of the rigid convergent shell (2) and the throat downstream heat-insulating and ablation-resistant layer (8) brushed on the inner wall of the rigid expansion shell (4); The flexible expansion section includes a plurality of spring steel sheets (6) and an anti-ablation elastic structure (5), one end of each spring steel sheet (6) is mounted on an end of the rigid expansion shell (4) away from the composite throat liner (7) and arranged in a trumpet shape as a skeleton, and the anti-ablation elastic structure (5) is formed by pouring an anti-ablation elastic material on each spring steel sheet (6) and wrapping and connecting each spring steel sheet (6); The driving device (3) includes a servo system and a force transmission disc (39). The servo system includes a power source, an actuating part, and a transmission part. The power source is connected to the actuating part, the actuating part is connected to the transmission part, the transmission part is connected to the force transmission disc (39), and the force transmission disc (39) is connected to the flexible expansion section. The four power sources are evenly distributed around the outer circumference of the rigid base section.

2. The solid rocket engine thrust vector nozzle based on flexible deformation of the expansion section according to claim 1, characterized in that: The power source is fixed through a wedge-shaped platform, the bottom of the wedge-shaped platform is fixed on the outer wall of the rigid convergent shell (2) at the throat, the wedge-shaped platform has an inclined wedge with an angle of 15 degrees, and the power source is fixed on the inclined wedge surface of the wedge-shaped platform.

3. The solid rocket engine thrust vector nozzle based on flexible deformation of the expansion section according to claim 2, characterized in that: The spring steel sheet (6) is mounted on the rigid expansion shell (4) through a support ring (61). The thickness of the spring steel sheet (6) decreases as the inner diameter of the nozzle expansion section increases. The thick end of the spring steel sheet (6) is fixed on the support ring (61). The spring steel sheets (6) are evenly distributed on the support ring (61). The support ring (61) is fixed to one end of the rigid expansion shell (4) away from the composite throat liner (7).

4. The solid rocket engine thrust vector nozzle based on flexible deformation of the expansion section according to claim 3, characterized in that: The power source is a servo motor (31), the actuating part includes a reduction gear set (32) connected to the servo motor (31), and an electric push rod (33) connected to the reduction gear set (32), the transmission part includes a transmission connecting rod (34), a driven connecting rod (36), a flexible connecting member (38) and a limit bracket (37), one end of the transmission connecting rod (34) is hinged to the telescopic end of the electric push rod (33), and the other end is hinged to the flexible connecting member (38), one end of the flexible connecting member (38) is hinged to the telescopic end of the electric push rod (33), and the other end is hinged to the flexible connecting member (38). The limiting bracket (37) is vertically fixed to the upper disk surface of the force transmission disc (39), and includes a pair of parallel rods and a cross bar connected between the two rods. The bottom of the pair of parallel rods is fixed to the upper disk surface of the force transmission disc (39). One end of the driven connecting rod (36) is hinged to the cross bar, and the other end is hinged to the middle of the transmission connecting rod (34). The lower disk surface of the force transmission disc (39) is bonded to the outer wall of the flexible expansion section. The axis of the force transmission disc (39) is coplanar and perpendicular to the axis of the electric push rod (33).

5. The solid rocket engine thrust vector nozzle based on flexible deformation of the expansion section according to claim 4, characterized in that: The rigid convergent shell (2) and the rigid expansion shell (4) are both made of 35CrMnSiA; the composite throat liner (7) is made of any one selected from carbon / carbon composite materials, high melting point metals, graphite materials, and sweating materials; and the anti-ablation elastic material is anti-ablation EPDM rubber.

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