A modular grid rudder control device and its assembly method

Abstract

This invention relates to a modular grid fin control device and its assembly method, belonging to the field of liquid propellant rocket technology. The device mainly includes a grid fin body, a hollow assembly mechanism, and a drive mechanism. One end of the grid fin body is hinged to the assembly mechanism, and the drive mechanism is built into the assembly mechanism, including a drive base, a drive telescopic rod, and a drive arm mounted on the grid fin body. The extension and retraction of the drive telescopic rod controls the grid fin body to rotate 90° around the hinge point. The grid fin body consists of an outer frame and an internal 45° angled grid forming a spatial multi-lift surface combination. Its leading edge is P-shaped swept back, and the apex is located at the grid intersection to reduce aerodynamic drag. The device also includes a folding locking block and an unfolding locking mechanism to ensure reliable operation. This invention adopts a modular design, with each component independently disassembling and assembling. The assembly method is clear and allows for rapid maintenance, significantly improving the attitude response efficiency and landing point control accuracy of reusable rockets.

Description

Technical Field

[0001] This invention relates to the field of liquid-fueled rocket technology. In particular, it relates to a modular grid fin control device and its assembly method. Background Technology

[0002] The grid fin assembly is a crucial component of liquid rocket landing and recovery control, typically comprising multiple parts such as aerodynamic control surfaces, deflection mechanisms, folding / deployment mechanisms, and locking mechanisms. During the rocket's ascent phase, the grid fins need to fold and conform to the rocket body surface to reduce aerodynamic drag; during the rocket's return or reentry phase, the grid fins need to deploy and deflect to provide aerodynamic control forces, adjusting the rocket's attitude and landing accuracy.

[0003] Existing grid fin devices generally suffer from the following problems: First, the mechanism is complex, with high coupling between components, leading to difficulties in assembly, testing, and maintenance; second, the locking and unlocking mechanisms lack reliability, especially the locking stability after deployment; third, the linkage logic between the drive mechanism and the locking mechanism is not clear enough, easily causing operational interference. Furthermore, the existing devices have a low degree of modularity, which is not conducive to rapid maintenance and component replacement of reusable rockets. Summary of the Invention

[0004] The purpose of this invention is to provide a modular grid rudder control device and its assembly method to solve one or all of the technical problems existing in the prior art.

[0005] To achieve the above objectives, the present invention provides the following solution: This invention provides a modular grid rudder control device, comprising: Grid rudder body; An assembly mechanism is mounted on the arrow body, and one end of the grid rudder body is hinged to the assembly mechanism. A drive mechanism is provided inside the assembly mechanism. The two ends of the drive mechanism are respectively connected to the grid rudder body and the assembly mechanism. The drive mechanism is used to control the rotation of the grid rudder body at the assembly mechanism. The drive mechanism includes a drive base and a drive telescopic rod. The drive base is fixedly connected to the assembly mechanism. A drive arm is provided on the side of the grid rudder body near the drive mechanism. One end of the drive telescopic rod is hinged to the drive base, and the other end of the drive telescopic rod is hinged to the drive arm. The drive telescopic rod drives the drive arm to move by extending and retracting, so as to control the grid rudder body to rotate axially around the hinge point between it and the assembly mechanism.

[0006] According to one embodiment of the present invention, the grid fin body is provided with a lower locking block, which is used to contact the lower locking mechanism of the rocket body to lock the folded state of the grid fin body; The assembly mechanism is provided with an upper locking mechanism on its inner side, and the grid rudder body is provided with an upper locking block that can engage with the upper locking mechanism. When the grid rudder body is unfolded, the upper locking block engages with the upper locking mechanism and locks.

[0007] According to one embodiment of the present invention, the drive telescopic rod is an electric push rod, a hydraulic cylinder, or a pneumatic push rod.

[0008] According to one embodiment of the present invention, the grid rudder body is hinged to the assembly mechanism via a hinge shaft.

[0009] According to one embodiment of the present invention, the drive arm is fixedly disposed on the side of the grid rudder body near the drive mechanism, and is integrally formed with the grid rudder body or connected by fasteners.

[0010] According to one embodiment of the present invention, the upper locking mechanism is electromagnetic and / or mechanical, and the upper locking block is a metal block.

[0011] According to one embodiment of the present invention, the lower locking block is a metal block, used to cooperate with an electromagnetic and / or mechanical lower locking mechanism on the outside of the rocket body to achieve locking or unlocking.

[0012] According to one embodiment of the present invention, the assembly mechanism is a ring structure or a frame structure, wherein the hollow interior is used to accommodate the drive mechanism.

[0013] According to one embodiment of the present invention, the two ends of the drive telescopic rod are respectively hinged to the drive seat and the drive arm via pins.

[0014] The assembly method of the modular grid rudder control device includes the following steps: S1: The upper locking mechanism is connected to the assembly mechanism by bolts. After the upper locking mechanism is assembled, it operates independently and can lock the grid rudder body in the deployed state. S2: The drive mechanism is connected to the assembly mechanism via connecting bolts. After the drive mechanism is assembled, it operates independently and controls the grid rudder body to unfold. S3: The grid rudder body is connected to the assembly mechanism via the flange rotation shaft. After the grid rudder body is assembled, it performs an angular movement under the drive of the assembly mechanism to achieve stability enhancement and attitude adjustment of the aircraft. S4: The lower locking block is connected to the grid rudder body by a bolt. The lower locking block is used to lock the grid rudder body in the retracted state. S5: The grid rudder body and the drive mechanism are connected by a pin to realize the drive relationship for deployment.

[0015] Beneficial effects This invention has at least one of the following technical effects: 1. Through the modular cooperation of the grid fin body, the hollow assembly mechanism, and the drive mechanism located inside the assembly mechanism, 90° axial rotation control of the grid fin body around the hinge point is achieved. Specifically, the drive seat is fixedly connected to the assembly mechanism, and the two ends of the drive telescopic rod are respectively hinged to the drive arms on the drive seat and the grid fin body. When the drive telescopic rod extends or retracts, it can smoothly drive the grid fin body to rotate around the hinge point. This structure avoids motion interference between the drive mechanism and the locking mechanism, the connection relationship between the components is simple, the transmission efficiency is high, and the drive mechanism is built into the assembly mechanism, without occupying additional rocket body space, which is conducive to the compact layout and lightweight design of the rocket.

[0016] 2. The grid fin body adopts a spatial multi-lift surface combination configuration formed by an external frame and an internal grid arrangement. The internal grid is inclined at 45°, which can effectively adjust stability and achieve precise aerodynamic control during rocket reentry. Simultaneously, the leading edge of the grid fin body adopts a P-shaped swept-back design, with its foremost apex located at the grid intersection. This configuration significantly improves the flow obstruction characteristics within the grid and greatly reduces aerodynamic drag. Compared with traditional straight or rectangular grid fins, the aerodynamic shape of this invention can reduce drag by approximately 15% to 20% with the same frontal area, improving the controllability and landing accuracy of the rocket reentry phase. 3. The modular grid fin control device and its assembly method provided in this solution independently connect the upper locking mechanism, drive mechanism, grid fin body, and lower locking block using bolts or pins. There are no coupling interfaces between the modules, allowing for individual disassembly, testing, and replacement. The five steps (S1 to S5) of the assembly method are logically clear, allowing for independent assembly of the upper locking mechanism, drive mechanism, grid fin body, lower locking block, and drive arm connection, ultimately establishing the drive relationship via pins. When a module malfunctions, only the corresponding connector needs to be removed for rapid repair, eliminating the need for complete disassembly. This significantly reduces maintenance costs and time for reusable rockets and improves health management efficiency. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1A three-dimensional structural diagram of the modular grid rudder control device; Figure 2 Side view of the modular grid rudder control unit; Figure 3 This is a structural diagram of the assembly mechanism in a modular grid rudder control device. Figure 4 This is a schematic diagram of the folded state of the grid rudder body in the modular grid rudder control device; Figure 5 This is a schematic diagram of the grid rudder body in the deployed state of the modular grid rudder control device.

[0019] Explanation of reference numerals in the attached figures: 1-Grid rudder body; 11-Drive arm; 12-Upper locking block; 2-Assembly mechanism; 3-Drive mechanism; 31-Drive seat; 32-Drive telescopic rod; 4-Lower locking block; 5-Upper locking mechanism. Detailed Implementation

[0020] The features and exemplary embodiments of various aspects of the present invention will now be described in detail. To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention and to exemplify the principles of the present invention, and are not configured to limit the present invention. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or regions in the drawings may be enlarged for other structural components or regions to aid in the understanding of the embodiments of the present invention.

[0021] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise stated, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the present invention according to the specific circumstances.

[0022] Furthermore, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure or component that includes a list of elements includes not only those elements but also other structural elements that are not expressly listed or inherent to the structure or component. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the article or apparatus that includes the element.

[0023] Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for descriptive convenience to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device, in addition to those different from those shown in the figure. Furthermore, phrases such as "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first" and "second" are also used to describe individual elements, areas, parts, etc., without specifically indicating order or sequence, and should not be considered restrictive. Similar terms are used throughout the description to represent similar elements.

[0024] It will be apparent to those skilled in the art that the present invention can be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention.

[0025] In the following embodiments, there may be descriptions such as "this device". Those skilled in the art should understand that "this device" refers to a modular grid rudder control device and its assembly method provided by the present invention.

[0026] like Figure 1-5 As shown, Figure 1 A three-dimensional structural diagram of the modular grid rudder control device; Figure 2 Side view of the modular grid rudder control unit; Figure 3 This is a structural diagram of the assembly mechanism in a modular grid rudder control device. Figure 4 This is a schematic diagram of the folded state of the grid rudder body in the modular grid rudder control device; Figure 5 This is a schematic diagram of the grid rudder body in the deployed state of the modular grid rudder control device; It mainly includes the grid rudder body 1, the assembly mechanism 2, and the drive mechanism 3.

[0027] The assembly mechanism 2 is a hollow structure, specifically a ring-shaped or frame-shaped structure, with its internal hollow area used to accommodate the drive mechanism 3. The assembly mechanism 2 is fixedly installed on the rocket body or interstage section.

[0028] One end of the grid rudder body 1 is hinged to the assembly mechanism 2 via a hinge shaft or flange rotation shaft, so that the grid rudder body 1 can rotate relative to the assembly mechanism 2 around the hinge point.

[0029] The drive mechanism 3 is integrally disposed inside the assembly mechanism 2. The drive mechanism 3 includes a drive base 31 and a drive telescopic rod 32. The drive base 31 is fixedly connected to the inner wall of the assembly mechanism 2. A drive arm 11 is fixedly disposed on the side of the grid rudder body 1 near the drive mechanism 3. The drive arm 11 can be integrally formed with the grid rudder body 1 or connected by fasteners. One end of the drive telescopic rod 32 is hinged to the drive base 31, and the other end is hinged to the drive arm 11. The drive telescopic rod 32 can be an electric push rod, a hydraulic cylinder, or a pneumatic push rod. The two ends of the drive telescopic rod 32 are respectively hinged to the drive base 31 and the drive arm 11 by pins.

[0030] When the drive telescopic rod 32 extends, it pushes the drive arm 11, causing the grid rudder body 1 to rotate around the hinge point in the unfolding direction; when the drive telescopic rod 32 retracts, it pulls the drive arm 11, causing the grid rudder body 1 to rotate in the folding direction. By controlling the stroke of the drive telescopic rod 32, the adjustment of the grid rudder body 1 in the unfolded and folded states can be controlled.

[0031] To achieve reliable locking, this device is also equipped with a folding locking structure and an unfolding locking structure.

[0032] Folding Locking Structure: A lower locking block 4, which is a metal block, is provided on the grid fin body 1. An independent lower locking mechanism is provided at a corresponding position on the rocket body or interstage section. The lower locking mechanism can be an electromagnet or a mechanical latch. When the grid fin body 1 is in the folded state, the lower locking block 4 contacts the lower locking mechanism. After the lower locking mechanism is energized or activated, it locks the lower locking block 4, thereby preventing the grid fin body 1 from unfolding without command.

[0033] Deployment locking structure: An upper locking mechanism 5 is fixedly installed inside the assembly mechanism 2. The upper locking mechanism 5 can be an electromagnet or a mechanical spring locking pin. An upper locking block 12 is installed at a corresponding position on the grid rudder body 1. The upper locking block 12 is a metal block or a component with a slot. When the grid rudder body 1 is deployed to the 90° position, the upper locking block 12 is exactly engaged with the upper locking mechanism 5, and the upper locking mechanism 5 is activated to lock the grid rudder body 1 in the deployed state, ensuring that it will not fold accidentally under aerodynamic loads.

[0034] In some embodiments, the grid fin body 1 is a spatial multi-lift surface combination configuration formed by an outer frame and an internal grid arrangement. The internal grid of the grid fin body 1 is arranged at a 45° angle to adjust rocket stability and achieve aerodynamic control. The leading edge of the grid fin body 1 adopts a P-shaped sweepback, with the foremost vertex appearing at the intersection of the grids of the grid fin body 1. This structure can effectively improve the flow obstruction performance inside the grid and significantly reduce the aerodynamic drag of the grid fin body 1.

[0035] In some embodiments, the assembly mechanism 2 is axially rotatable and mounted on the rocket body. Optionally, a drive device that can be precisely timed and angle-adjusted, such as a drive servo motor or reducer, which is already disclosed in the prior art, is set accordingly. The drive device is connected to the assembly mechanism 2 in a transmission connection. In this way, the assembly mechanism 2 can be controlled by the drive device to drive the grid fin body 1 to deflect at a certain angle, thereby realizing the attitude control and adjustment of the rocket.

[0036] The modular grid rudder control device of the present invention is assembled according to the following steps, which enables independent installation and quick replacement of each module, including the following steps: S1: The upper locking mechanism 5 is fixed to the designated position inside the assembly mechanism 2 by bolt connection. Check whether the operation of the upper locking mechanism 5 is normal, and ensure that it can operate independently and lock the grid rudder body 1 in the unfolded state. S2: The drive mechanism 3 is fixed to the inside of the assembly mechanism 2 by connecting bolts, ensuring that the drive seat 31 is firmly positioned with the assembly mechanism 2, the drive telescopic rod 32 moves smoothly, the drive mechanism 3 operates independently and can control the deployment of the grid rudder body 1. S3: The grid rudder body 1 is hinged to the assembly mechanism 2 via a flange rotation shaft or hinge shaft to ensure rotational freedom and complete the assembly of the grid rudder body 1; the grid rudder body 1 can perform yaw motion under the drive of the assembly mechanism 2 to achieve stability enhancement and attitude adjustment of the aircraft. S4: The lower locking block 4 is fixed to the corresponding position of the grid fin body 1 by bolt connection, ensuring that the lower locking block 4 can contact and lock with the external fixing structure set on the rocket body when the grid fin body 1 is retracted. S5: Connect the drive arm 11 on the grid rudder body 1 to the end of the drive telescopic rod 32 through a pin to establish a drive relationship, so that the telescopic motion of the drive telescopic rod 32 can be converted into the rotational motion of the grid rudder body 1.

[0037] The above five steps are independent of each other. If any step fails, the corresponding module's connector can be removed for individual replacement or repair without overall disassembly, which greatly improves maintainability.

[0038] The operation and use method of the modular grid rudder control device includes the following steps. Initial state: The grid rudder body 1 is in a folded state, close to the surface of the arrow body, and the lower locking block 4 is in contact with and locked to the external lower locking mechanism. At this time, the upper locking mechanism 5 is separated from the upper locking block 12, and the drive telescopic rod 32 is in the retracted position.

[0039] Y1: Lower Unlock. When the rocket returns or the reentry vehicle needs to deploy the grid fins, the control system sends an unlocking command to the external lower locking mechanism. If the lower locking mechanism is an electromagnet, its power is cut off, the electromagnet is demagnetized, and the lower locking block 4 is released; if it is a mechanical lock, the locking pin is driven out by an electromagnet or a micro motor. The lower locking block 4 disengages from the lower locking mechanism, and the grid fin body 1 gains the ability to rotate freely.

[0040] Y2: The deployment control system sends a deployment command to the drive mechanism 3. The drive telescopic rod 32 begins to retract, pulling the drive arm 11 and causing the grid rudder body 1 to rotate around the hinge point from 0° to 90°. Throughout the deployment process, the drive telescopic rod 32 retracts at a constant speed, and the angular velocity of the grid rudder body is stable and controllable. At the same time, the upper locking block 12 moves together with the grid rudder body 1, gradually approaching the upper locking mechanism 5.

[0041] Y3: Upper Locking. When the grid rudder body 1 rotates to near 0°, the upper locking block 12 enters the effective range of the upper locking mechanism 5. The control system then issues a locking command to the upper locking mechanism 5. If the upper locking mechanism 5 is an electromagnet, it is immediately energized, generating a magnetic force to attract the upper locking block 12; if it is a mechanical lock, the spring-driven locking pin pops out and engages in the slot of the upper locking block 12. The upper locking mechanism 5 and the upper locking block 12 are tightly engaged, reliably locking the grid rudder body 1 in the extended position. At this time, the drive telescopic rod 32 can continue to be extended or unloaded, and the upper locking mechanism 5 independently undertakes the locking and holding function.

[0042] Y4: When the grid rudder needs to be folded again, first unlock the upper locking mechanism 5, then drive the telescopic rod 32 to extend and push the grid rudder body 1 back to the 90° folding position. The lower locking block 4 will then contact the external lower locking mechanism again, and the lower locking mechanism will activate to achieve folding and locking.

[0043] It should be noted that the modular grid fin control device and its assembly method provided by this invention can be widely applied to the recovery system of liquid-fueled launch vehicles and the attitude control system of reusable aircraft. Its modular design helps reduce production costs, improve assembly and testing efficiency, and significantly enhances the reliability and maintainability of flight missions, thus possessing clear industrial practical value.

[0044] It should be understood that the above-described embodiments or examples of the present invention can be combined with each other and have corresponding technical effects.

[0045] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for assembling a modular grid fin device for rocket attitude control, characterized in that, The modular grid rudder device includes: Grid rudder body (1); Assembly mechanism (2) is set on the arrow body, and one end of the grid rudder body (1) is hinged to the assembly mechanism (2). A drive mechanism (3) is provided inside the assembly mechanism (2). The two ends of the drive mechanism (3) are respectively connected to the grid rudder body (1) and the assembly mechanism (2). The drive mechanism (3) is used to control the rotation of the grid rudder body (1) at the assembly mechanism (2). The drive mechanism (3) includes a drive seat (31) and a drive telescopic rod (32). The drive seat (31) is fixedly connected to the assembly mechanism (2). The grid rudder body (1) is provided with a drive arm (11) on the side close to the drive mechanism (3). One end of the drive telescopic rod (32) is hinged to the drive seat (31), and the other end of the drive telescopic rod (32) is hinged to the drive arm (11). The drive telescopic rod (32) drives the drive arm (11) to move by extending and retracting, so as to control the grid rudder body (1) to rotate axially around the hinge point between it and the assembly mechanism (2). The grid fin body (1) is provided with a lower locking block (4), which is used to contact the lower locking mechanism of the rocket body to lock the grid fin body (1) in the folded state. The assembly mechanism (2) is provided with an upper locking mechanism (5) on its inner side. The grid rudder body (1) is provided with an upper locking block (12) that can engage with the upper locking mechanism (5). When the grid rudder body (1) is unfolded, the upper locking block (12) engages with the upper locking mechanism (5) and locks. The grid rudder body (1) is hinged to the assembly mechanism (2) via a hinge shaft; The drive arm (11) is fixedly disposed on the side of the grid rudder body (1) near the drive mechanism (3), and is integrally formed with the grid rudder body (1) or connected by fasteners. The method includes the following steps: S1: The upper locking mechanism (5) and the assembly mechanism (2) are connected by bolts. After the upper locking mechanism (5) is assembled, the upper locking mechanism (5) operates independently and locks the grid rudder body (1) in the unfolded state. S2: The drive mechanism (3) is connected to the assembly mechanism (2) by connecting bolts. After the drive mechanism (3) is assembled, the drive mechanism (3) operates independently and controls the grid rudder body (1) to unfold. S3: The grid rudder body (1) is connected to the assembly mechanism (2) through the flange rotation shaft. After the grid rudder body (1) is assembled, the grid rudder body (1) performs an angle swing under the drive of the assembly mechanism (2) to achieve stability enhancement and attitude adjustment of the aircraft. S4: The lower locking block (4) is connected to the grid rudder body (1) by bolts. The lower locking block (4) is used to lock the grid rudder body (1) in the retracted state. S5: The grid rudder body (1) and the drive mechanism (3) are connected by a pin to realize the drive relationship for deployment.

2. The method of assembling a modular girdle rudder device for attitude control of a rocket as claimed in claim 1, wherein, The drive telescopic rod (32) includes an electric push rod, a hydraulic cylinder, or a pneumatic push rod.

3. The assembly method of the modular grid fin device for rocket attitude control according to claim 1, characterized in that, The upper locking mechanism (5) includes electromagnetic and / or mechanical types, and the upper locking block (12) includes a metal block.

4. The assembly method of the modular grid fin device for rocket attitude control according to claim 1, characterized in that, The lower locking block (4) includes a metal block for use in conjunction with an electromagnetic and / or mechanical lower locking mechanism of the rocket body to achieve locking or unlocking.

5. The assembly method of the modular grid fin device for rocket attitude control according to claim 1, characterized in that, The assembly mechanism (2) includes a ring structure or a frame structure, the hollow interior of which is used to accommodate the drive mechanism (3).

6. The assembly method of the modular grid fin device for rocket attitude control according to claim 1, characterized in that, The two ends of the drive telescopic rod (32) are respectively hinged to the drive seat (31) and the drive arm (11) by pins.

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