A variable diameter skeleton rope-driven mechanism for the nose cone tip of an aircraft

Abstract

This invention discloses a variable-diameter frame cable-driven mechanism for the nose cone tip of an aircraft, comprising multiple frame branches, a top plate, and a base platform. Each frame branch includes a first frame section, a second frame section, a third frame section, a fourth frame section, a fifth frame section, and a sixth frame section. The base platform is stepped and has three layers of truncated cones, with multiple frame branches evenly distributed in parallel on the base platform. A pulley is provided in the first frame section to fix the end of the steel cable. Two pulleys are provided in the second, third, fourth, fifth, and sixth frame sections for positioning the steel cable around each frame section. A pulley is located below each positioning section of the base platform to ensure that the initial position of the steel cable remains unchanged when controlling the movement of the frame sections. This invention can vary the nose cone diameter according to the different requirements of the aircraft's optimal aerodynamic layout during the ascent and reentry phases.

Description

Technical Field

[0001] This invention belongs to the field of aerospace technology, specifically relating to a variable diameter skeleton rope-driven mechanism at the tip of an aircraft nose cone. Background Technology

[0002] A variable aircraft is a reusable space-to-ground transport vehicle capable of entering space and remaining within the atmosphere for extended periods. It features high speed, strong penetration capabilities, and the ability to rapidly strike predetermined targets, making it a crucial future air-based combat weapon. Traditional fixed-configuration nose cone structures are limited by aerodynamics, aerothermal properties, time windows, and control feedback, failing to meet the performance requirements of multi-mission profiles and complex, variable flight conditions. A variable nose cone mechanism can adjust its shape in real-time according to flight conditions to achieve optimal aerodynamic and thermal characteristics, enabling optimized flight control and significantly improving maneuverability and combat effectiveness. It is an essential choice for aircraft to cope with complex and changing external environments. Existing variable nose cone designs primarily use linkages and other mechanisms to change the nose cone's orientation, allowing for better aerodynamic shapes for different flight environments.

[0003] The optimal aerodynamic configuration requirements for the nose cone differ significantly between the ascent and reentry phases. During ascent, the nose cone needs to have a smaller profile radius to reduce the shock wave intensity at its tip and its length is increased to reduce aerodynamic loads and drag. Conversely, when the aircraft enters the hypersonic region of reentry, the nose cone tip radius needs to be increased to reduce the stagnation heat flux density at the nose cone and thus reduce the peak heat flux.

[0004] Existing designs only involve changing the direction of the nose cone, but not the diameter of its outer surface. However, as the part of the aircraft that first comes into contact with the external environment, the shape of the nose cone has a decisive impact on the overall aerodynamic shape of the aircraft. Furthermore, the optimal nose cone profile diameter differs at different flight stages. During flight, varying the diameter of the nose cone tip's frame can further improve the resistance-reducing and heat-generating capabilities of the modified nose cone in the face of different flight environments. Summary of the Invention

[0005] The purpose of this invention is to provide a variable diameter skeleton rope drive mechanism for the nose cone tip of an aircraft, so as to achieve variable diameter of the nose cone tip.

[0006] This invention provides a variable diameter skeleton cable-driven mechanism for the nose cone tip of an aircraft, comprising multiple skeleton branches, a top plate, and a base platform. Each skeleton branch includes a first skeleton section, a second skeleton section, a third skeleton section, a fourth skeleton section, a fifth skeleton section, and a sixth skeleton section. The first skeleton section, the second skeleton section, the third skeleton section, the fourth skeleton section, the fifth skeleton section, and the sixth skeleton section are connected in series, and each section is hinged to the other by inter-segment hinges.

[0007] The base platform is stepped and has three layers of truncated cones. Multiple skeleton branches are connected in parallel and evenly distributed on the base platform. A rotating joint is formed by hinged connection between the sixth section of the skeleton and the positioning part of the base platform, and a rotating joint is formed by hinged connection between the first section of the skeleton and the positioning part of the top plate. The interior of the top truncated cone of the base platform forms a sliding joint with the top plate to control the deformation of the skeleton branches.

[0008] The first section of the frame is equipped with a pulley for fixing the end of the steel rope; the second, third, fourth, fifth, and sixth sections of the frame each have two pulleys for positioning the steel rope in each frame section; and each positioning part of the base platform has a pulley below it to ensure that the initial position of the steel rope remains unchanged when controlling the movement of the frame sections.

[0009] Furthermore, the mechanism also includes a support structure, which comprises a linear slide rail, a support ring, and a support rod. The support ring includes an upper support ring, a middle support ring, and a lower support ring, and the support rod includes an upper support rod, a middle support rod, and a lower support rod. The linear slide rail is installed on all three truncated cones of the base platform. The upper support rod, the middle support rod, and the lower support rod are respectively hinged to the second segment, the fourth segment, and the sixth segment of the skeleton. The upper support ring, the middle support ring, and the lower support ring are respectively hinged to the upper support rod, the middle support rod, and the lower support rod. The linear slide rail is slidably connected to the upper support ring, the middle support ring, and the lower support ring to realize the linear up-and-down movement of the upper support ring, the middle support ring, and the lower support ring, and then, when the skeleton segments move, the support rod drives the support ring to move up and down.

[0010] Furthermore, the number of skeletal branches is eight.

[0011] Compared with the prior art, the beneficial effects of the present invention are:

[0012] The present invention can vary the nose cone diameter according to the different requirements of the aircraft's optimal aerodynamic layout for the nose cone during the ascent and reentry phases. Attached Figure Description

[0013] Figure 1 This is a frontal view of the large-diameter state of the head cone variable diameter skeleton of the present invention;

[0014] Figure 2 Front view of the small-diameter state of the variable-diameter framework of the nose cone of the present invention;

[0015] Figure 3 Top view of the small-diameter state of the variable-diameter framework of the nose cone of the present invention;

[0016] Figure 4 Schematic structural diagram of the rope drive mechanism of the variable-diameter framework at the tip of the nose cone of the aircraft of the present invention;

[0017] Figure 5 Schematic diagram of the arrangement of steel ropes and pulleys inside the framework sections of the rope drive mechanism of the variable-diameter framework at the tip of the nose cone of the aircraft of the present invention.

[0018] Reference numerals in the figure:

[0019] 1-1, the first framework section; 1-2, the second framework section; 1-3, the third framework section; 1-4, the fourth framework section; 1-5, the fifth framework section; 1-6, the sixth framework section; 2, the inter-joint hinge; 3, the top plate; 4, the bottom platform; 5, the linear slide rail; 6-1, the upper support ring; 6-2, the middle support ring; 6-3, the lower support ring; 7-1, the upper support rod; 7-2, the middle support rod; 7-3, the lower support rod; 8, the pulley; 9, the steel rope. Detailed implementation manners

[0020] The present invention will be described in detail below with reference to the embodiments shown in the drawings. However, it should be noted that these embodiments are not limitations of the present invention, and any equivalent transformation or substitution in terms of function, method, or structure made by those of ordinary skill in the art according to these embodiments shall fall within the protection scope of the present invention.

[0021] Refer Figures 1 to 5As shown, this embodiment provides a variable diameter frame rope-driven mechanism for the nose cone tip of an aircraft, including eight frame branches, a top plate 3, and a base platform 4. Each frame branch includes a first frame segment 1-1, a second frame segment 1-2, a third frame segment 1-3, a fourth frame segment 1-4, a fifth frame segment 1-5, and a sixth frame segment 1-6. The first frame segment 1-1, the second frame segment 1-2, the third frame segment 1-3, the fourth frame segment 1-4, the fifth frame segment 1-5, and the sixth frame segment 1-6 are connected in series, and each segment is hinged to the other by inter-segment hinges 2. The base platform 4 is stepped and has three layers of truncated cones. Multiple frame branches are evenly distributed in parallel on the base platform 4 and are connected by the first frame segment 1-1, the second frame segment 1-2, the third frame segment 1-3, the fourth frame segment 1-4, the fifth frame segment 1-5, and the sixth frame segment 1-6. The six sections 1-6 are hinged to the positioning part of the base platform 4 to form a revolute joint, and are also hinged to the positioning part of the top plate 3 through the first section 1-1 of the skeleton to form a revolute joint; the interior of the top truncated cone of the base platform 4 forms a sliding joint with the top plate 3 to control the deformation of the skeleton branches; a pulley 8 is provided in the first section 1-1 of the skeleton to fix the end of the steel rope 9; the second section 1-2, the third section 1-3, the fourth section 1-4, the fifth section 1-5, and the sixth section 1-6 of the skeleton each have two pulleys 8 for positioning the steel rope 9 for each skeleton section; a pulley 8 is provided below each positioning part of the base platform to ensure that the initial position of the steel rope 9 remains unchanged when controlling the movement of the skeleton sections.

[0022] To drive the nose cone diameter change during different flight phases while maintaining the streamlined shape of the frame, this embodiment divides the frame into segments and employs a cable-driven control method to achieve simultaneous deformation of all six frame segments with a single drive. Specifically, in the large-diameter state, the nose cone changing diameter frame shortens by pulling a steel cable, causing pulleys in adjacent frame segments to move closer, thus rotating the hinges between the segments. Simultaneously, the top plate moves upward. The deformation from a large to a small diameter state is completed when the steel cable is stretched to a straight line. The deformation from a small to a large diameter state occurs when, with the steel cable taut, the top plate moves downward, stretching the steel cable and causing the hinges between the frame segments to rotate.

[0023] To ensure the stability and self-locking of the skeleton structure, the mechanism also includes a follow-up support structure. This support structure includes linear slide rails 5, support rings, and support rods. The support rings include an upper support ring 6-1, a middle support ring 6-2, and a lower support ring 6-3. The support rods include an upper support rod 7-1, a middle support rod 7-2, and a lower support rod 7-3. The linear slide rails 5 are installed on all three layers of the base platform 4. The upper support rods 7-1, middle support rods 7-2, and lower support rods 7-3 are respectively connected to the second segment 1-2 of the skeleton and the first segment 6-3 of the skeleton. The fourth segment 1-4 and the sixth segment 1-6 of the skeleton are hinged together; the upper support ring 6-1, the middle support ring 6-2, and the lower support ring 6-3 are respectively hinged to the upper support rod 7-1, the middle support rod 7-2, and the lower support rod 7-3; the linear slide rail 5 is slidably connected to the upper support ring 6-1, the middle support ring 6-2, and the lower support ring 6-3, and is used to realize the linear up and down movement of the upper support ring 6-1, the middle support ring 6-2, and the lower support ring 6-3, and then drive the support rings to move up and down through the support rods when the skeleton segments move. The support rings move with the movement of each skeleton segment through the support rods. When the head cone diameter skeleton has completed deformation, locking the position of the support rings can achieve self-locking of the skeleton structure.

[0024] The variable-diameter frame rope-driven mechanism at the tip of the aircraft's nose cone can vary the nose cone diameter according to the different requirements of the aircraft's optimal aerodynamic layout during the ascent and reentry phases. Calculations show that this invention can significantly alter the nose cone's surface area; analysis using data with a part 10 diameter of 300mm shows that the nose cone's surface area can increase by 20%, and the effect becomes more pronounced as the actual diameter of the nose cone part 10 increases.

[0025] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within the present invention.

Claims

1. A variable diameter backbone cable actuation mechanism for a nose tip of an aircraft, comprising: The skeleton branch includes a skeleton first section (1-1), a skeleton second section (1-2), a skeleton third section (1-3), a skeleton fourth section (1-4), a skeleton fifth section (1-5), and a skeleton sixth section (1-6); the skeleton first section (1-1), the skeleton second section (1-2), the skeleton third section (1-3), the skeleton fourth section (1-4), the skeleton fifth section (1-5), and the skeleton sixth section (1-6) are sequentially connected in series and are hingedly connected through an inter-section hinge (2); The bottom table (4) is in a stepped shape and is provided with three circular tables; a plurality of skeleton branches are parallelly and uniformly distributed on the bottom table (4) and are hingedly connected with the positioning portions of the bottom table (4) through the skeleton sixth section (1-6) to form a rotating pair and are hingedly connected with the positioning portions of the top disc (3) through the skeleton first section (1-1) to form a rotating pair; the inner portion of the top circular table of the bottom table (4) forms a moving pair with the top disc (3) to control the deformation of the skeleton branch; The skeleton first section (1-1) is internally provided with a pulley (8) for fixing the end of a steel rope (9); the skeleton second section (1-2), the skeleton third section (1-3), the skeleton fourth section (1-4), the skeleton fifth section (1-5), and the skeleton sixth section (1-6) are internally provided with two pulleys (8) for positioning the steel rope (9) to each skeleton section; each positioning portion of the bottom table is provided below with a pulley (8) for ensuring that the initial position of the steel rope (9) is unchanged when the motion of the skeleton section is controlled.

2. The aircraft nose cone tip variable diameter backbone cable drive mechanism of Claim 1, wherein, The support structure includes a linear slide rail (5), a support ring, and a support rod; the support ring includes an upper support ring (6-1), a middle support ring (6-2), and a lower support ring (6-3); the support rod includes an upper support rod (7-1), a middle support rod (7-2), and a lower support rod (7-3); the three circular tables of the bottom table (4) are each provided with the linear slide rail (5); the upper support rod (7-1), the middle support rod (7-2), and the lower support rod (7-3) are respectively hingedly connected with the skeleton second section (1-2), the skeleton fourth section (1-4), and the skeleton sixth section (1-6); the upper support ring (6-1), the middle support ring (6-2), and the lower support ring (6-3) are respectively hingedly connected with the upper support rod (7-1), the middle support rod (7-2), and the lower support rod (7-3); the linear slide rail (5) is slidingly connected with the upper support ring (6-1), the middle support ring (6-2), and the lower support ring (6-3) to realize the linear up-and-down movement of the upper support ring (6-1), the middle support ring (6-2), and the lower support ring (6-3) and then drive the support ring to move up and down through the support rod when the skeleton section moves.

3. The aircraft nose cone tip variable diameter backbone cable drive mechanism of claim 1 or 2, wherein, The number of the skeleton branches is eight.

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