A deformable head cone with omnidirectional swing capability

Abstract

The present invention discloses a deformable nose cone with omnidirectional swinging capability, which relates to the field of aircraft technology, and includes: a nose cone body, the nose cone body includes a conical tip, a plurality of conical rings and a plurality of thermal protection structures distributed along the axial direction of the nose cone body, the conical rings and the thermal protection structures are staggered, and a thermal protection structure is arranged between the conical tip and the adjacent conical ring, one end of the nose cone body is a conical tip, and the other end is a conical ring, the conical tip and each conical ring are fixedly connected to the adjacent thermal protection structure; the thermal protection structure includes an inner conical sleeve, an intermediate conical sleeve and an outer conical sleeve distributed in sequence from inside to outside along the radial direction of the nose cone body; a driving mechanism, the driving mechanism is used to drive the nose cone body to swing. On the one hand, the combination of the corrugated plate and the honeycomb structure significantly improves the deformation adaptability and thermal protection performance of the thermal protection structure; on the other hand, the design of the driving mechanism realizes the omnidirectional swinging of the nose cone.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft, in particular to a deformable nose cone with omnidirectional swinging capability. Background Art

[0002] Variable configuration aerospace vehicles can adjust their aerodynamic shape and configuration according to changes in flight environment and mission conditions, and have better flight performance and a wider mission envelope than traditional aircraft. Variable configuration methods of aerospace vehicles include variable wing sweep, variable span, variable chord length, variable curvature, and combined deformation of low-speed flying wings and high-speed waveriders. Exploring new variable configuration methods and their implementation forms has been one of the research hotspots in the aerospace field at home and abroad in recent years.

[0003] On the one hand, the nose cone of an aerospace vehicle plays the role of installing mission payloads; on the other hand, the geometric shape of the nose cone has an important influence on the aerodynamic characteristics and flight attitude of the vehicle. According to simulation analysis and experimental verification, the swing deformation of the nose cone can directly change the aerodynamic distribution of the vehicle and achieve flight control; it also brings additional nose pointing capabilities to the aerospace vehicle, improves the effectiveness of mission payloads, and has the potential to greatly improve the maneuverability and flight performance of the aerospace vehicle. However, aerospace vehicles will produce severe aerodynamic heating effects when flying at high speeds. Therefore, aerospace vehicles all adopt corresponding thermal protection measures, including active, heat sink, ablation and radiation, to ensure the safety of the vehicle and keep the internal load within the allowable temperature and pressure range.

[0004] Although the existing deformable nose cone has certain static and impact resistance, can withstand high temperatures and can achieve nose cone swing, it has the following defects:

[0005] (1) The traditional deformable nose cone thermal protection structure is mainly a sandwich structure, and its surface is directly used as a surface skin structure in the form of a flat plate. However, this structure cannot match the strain generated when the nose cone deforms, which will cause the skin structure to yield and thus fail to meet the deformation requirements of the nose cone;

[0006] (2) At present, most of the design schemes of the nose cone of an aerospace plane cannot realize the omnidirectional swing of the nose cone. The inability to swing the nose cone in all directions limits the range of change of the aerodynamic force distribution of the aerospace plane and limits the flight capability of the aerospace plane. Summary of the invention

[0007] The purpose of the present invention is to provide a deformable nose cone with omnidirectional swinging capability to solve the problems existing in the above-mentioned prior art and realize omnidirectional swinging of the deformable nose cone, thereby facilitating improving the maneuverability and flight performance of aerospace vehicles.

[0008] To achieve the above object, the present invention provides the following solutions:

[0009] The present invention provides a deformable nose cone with omnidirectional swing capability, comprising:

[0010] A head cone body, wherein the head cone body comprises a conical tip, a plurality of conical rings and a plurality of heat protection structures distributed along the axial direction of the head cone body, the conical rings and the heat protection structures are staggered, and a heat protection structure is arranged between the conical tip and the adjacent conical ring, one end of the head cone body is the conical tip, and the other end is the conical ring, the conical tip and each of the conical rings are fixedly connected to the adjacent heat protection structure; the heat protection structure comprises an inner conical sleeve, an intermediate conical sleeve and an outer conical sleeve distributed in sequence from inside to outside along the radial direction of the head cone body, the side wall of the inner conical sleeve and the side wall of the outer conical sleeve are both made of corrugated plates, the corrugations of the corrugated plates on the side wall of the inner conical sleeve are arranged along the generatrix direction of the inner conical sleeve, the corrugations of the corrugated plates on the side wall of the outer conical sleeve are arranged along the generatrix direction of the outer conical sleeve, and the side wall of the intermediate conical sleeve is made of honeycomb core material;

[0011] The driving mechanism comprises a first driving device, a second driving device, a rocker arm, a sleeve, a driving bevel gear and a driven bevel gear meshing with the driving bevel gear, the first driving device and the second driving device are respectively fixedly connected to the frame of the aircraft on which the head cone body is installed, and when the head cone body is installed on the aircraft, the conical ring in the head cone body farthest from the conical tip is fixedly connected to the frame; the output shaft of the second driving device and the driving bevel gear are coaxial with the conical ring in the head cone body farthest from the conical tip, the first driving device is used to drive the driving bevel gear to rotate, the sleeve is rotatably sleeved on the rotating shaft of the driven bevel gear, the sleeve is fixedly connected to the output shaft of the second driving device, the rotating shaft of the driven bevel gear and the axial direction of the sleeve are both perpendicular to the output shaft of the second driving device, one end of the rocker arm is fixedly connected to the rotating shaft of the driven bevel gear, and the other end is fixedly connected to the conical tip.

[0012] Preferably, the inner diameter of each of the conical rings gradually increases from one end close to the conical tip to the other end; among any two of the conical rings, the minimum inner diameter of the conical ring away from the conical tip is greater than the maximum inner diameter of the other conical ring.

[0013] Preferably, the side wall of the sleeve is provided with an arc-shaped slide groove corresponding to the swing rod, and the swing rod passes through the arc-shaped slide groove and slidably cooperates with the arc-shaped slide groove.

[0014] Preferably, both the first drive device and the second drive device adopt electro-hydraulic drives.

[0015] Preferably, the tapered ring, the tapered tip, the inner tapered sleeve, the middle tapered sleeve and the outer tapered sleeve are all made of metal.

[0016] Preferably, the active bevel gear is coaxial with the output shaft of the first driving device, and the active bevel gear is fixed on the output shaft of the first driving device.

[0017] Preferably, in the same heat protection structure, there are gaps between the inner tapered sleeve, the outer tapered sleeve and the middle tapered sleeve.

[0018] Preferably, the inner tapered sleeve, the middle tapered sleeve and the outer tapered sleeve are all fixedly connected to one tapered ring at one end and fixedly connected to another tapered ring or the tapered tip at the other end.

[0019] Preferably, the first driving device is fixedly connected to the frame via a first fixing bracket, and the second driving device is fixedly connected to the frame via a second fixing bracket.

[0020] Preferably, it further comprises a sleeve, and the rotating shaft of the driven bevel gear is rotatably matched with the sleeve via a bearing.

[0021] Compared with the prior art, the present invention has achieved the following technical effects:

[0022] On the one hand, the deformable nose cone with omnidirectional swinging ability of the present invention significantly improves the deformation adaptability and thermal protection performance of the thermal protection structure through the combination of corrugated plate and honeycomb structure; on the other hand, the design of the driving mechanism realizes the omnidirectional swing of the head cone, expanding the application scenarios of the deformable nose cone, especially in applications requiring high maneuverability and complex environments, such as spacecraft attitude adjustment and aircraft maneuvering flight, showing great potential and advantages.

[0023] Furthermore, the present invention provides a three-layer thermal protection structure of an inner conical sleeve, an intermediate conical sleeve and an outer conical sleeve, and the side walls of the inner conical sleeve and the outer conical sleeve are both made of corrugated plates, which provide the head cone body with significant anisotropic characteristics, that is, flexibility in the direction of corrugation arrangement, and high rigidity in the direction perpendicular to the corrugated plates, which not only amplifies the deformation effect but also effectively resists external aerodynamic loads. The side wall of the intermediate conical sleeve uses honeycomb core material, which not only reduces the overall weight, but also enhances the heat resistance and aerodynamic load bearing capacity of the structure, achieving a perfect combination of lightweight and high strength.

[0024] Furthermore, the present invention adopts an electro-hydraulic driver as the main driving force source, and efficiently transmits torque to the swing rod through the bevel gear transmission mechanism, which drives the conical tip to swing through the swing rod, thereby realizing the precise swing of the head cone as a whole. The setting of the second drive device can flexibly adjust the circumferential position of the driven bevel gear to ensure smooth swing of the head cone in any direction, meeting the requirements of omnidirectional swing. This unique driving mechanism overcomes the shortcomings of the traditional connecting rod mechanism in achieving omnidirectional swing, and greatly improves the flexibility and applicability of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0026] Figure 1 It is a schematic diagram of the deformable nose cone with omnidirectional swinging capability of the present invention installed on an aircraft;

[0027] Figure 2 It is a schematic structural diagram of a deformable nose cone with omnidirectional swinging capability according to the present invention;

[0028] Figure 3 An exploded view of the deformable nose cone with omnidirectional swinging capability of the present invention;

[0029] Figure 4 It is a schematic structural diagram of a deformable nose cone with omnidirectional swinging capability according to the present invention;

[0030] Figure 5 It is a schematic structural diagram of a sleeve in a deformable nose cone with omnidirectional swinging capability according to the present invention;

[0031] In the figure:

[0032] 100. A deformable nose cone with omnidirectional swinging capability; 200. An aircraft;

[0033] 10. conical tip; 20. conical ring; 30. inner conical sleeve; 40. middle conical sleeve; 50. outer conical sleeve; 60. first driving device; 70. active bevel gear; 80. driven bevel gear; 90. second driving device; 110. sleeve; 111. arc-shaped slide groove; 120. rocker arm. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] The purpose of the present invention is to provide a deformable nose cone with omnidirectional swinging capability to solve the problems existing in the above-mentioned prior art and realize omnidirectional swinging of the deformable nose cone, thereby facilitating improving the maneuverability and flight performance of aerospace vehicles.

[0036] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0037] like Figures 1 to 5 As shown, this embodiment provides a deformable nose cone 100 with omnidirectional swing capability, comprising:

[0038] The head cone body comprises a conical tip 10, a plurality of conical rings 20 and a plurality of heat protection structures distributed along the axial direction of the head cone body, the conical rings 20 and the heat protection structures are staggered, and a heat protection structure is arranged between the conical tip 10 and the adjacent conical ring 20, one end of the head cone body is a conical tip 10, and the other end is a conical ring 20, the conical tip 10 and each conical ring 20 are fixedly connected to the adjacent heat protection structure; the heat protection structure comprises a conical tip 10 and a conical ring 20 along the axial direction of the head cone body; The inner conical sleeve 30, the middle conical sleeve 40 and the outer conical sleeve 50 are sequentially distributed from the inside to the outside of the head cone body in radial direction. The side walls of the inner conical sleeve 30 and the side walls of the outer conical sleeve 50 are both made of corrugated plates. The corrugations of the corrugated plates on the side walls of the inner conical sleeve 30 are arranged along the generatrix direction of the inner conical sleeve 30, and the corrugations of the corrugated plates on the side walls of the outer conical sleeve 50 are arranged along the generatrix direction of the outer conical sleeve 50. The side walls of the middle conical sleeve 40 are made of honeycomb core material.

[0039] The driving mechanism includes a first driving device 60, a second driving device 90, a swing rod 120, a sleeve 110, a driving bevel gear 70 and a driven bevel gear 80 meshing with the driving bevel gear 70. The first driving device 60 and the second driving device 90 are respectively fixedly connected to the frame of the aircraft 200 on which the head cone body is installed. When the head cone body is installed on the aircraft 200, the conical ring 20 farthest from the conical tip 10 in the head cone body is fixedly connected to the frame; the output shaft of the second driving device 90 and the driving bevel gear 70 are connected to the driven bevel gear 80 meshing with the driving bevel gear 70. The bevel gears 70 are all coaxial with the conical ring 20 farthest from the conical tip 10 in the head cone body. The first drive device 60 is used to drive the active bevel gear 70 to rotate. The sleeve 110 is rotatably sleeved on the rotating shaft of the driven bevel gear 80. The sleeve 110 is fixedly connected to the output shaft of the second drive device 90. The rotating shaft of the driven bevel gear 80 and the axial direction of the sleeve 110 are both perpendicular to the output shaft of the second drive device 90. One end of the rocker arm 120 is fixedly connected to the rotating shaft of the driven bevel gear 80, and the other end is fixedly connected to the conical tip 10.

[0040] It should be noted that the honeycomb core material is an existing material well known in the art, and when the technicians use the honeycomb core material to make the intermediate conical sleeve 40, they can adaptively select the thickness of the honeycomb core material according to the performance requirements of the intermediate conical sleeve 40; the rotating shaft of the driven bevel gear 80 can only rotate relative to the sleeve 110, and the rotating shaft of the driven bevel gear 80 and the sleeve 110 are relatively fixed in the axial direction, and the implementation method can be to choose to set a limiting step or other types of limiting members on the rotating shaft of the driven bevel gear 80; in this embodiment, the rotating shaft of the driven bevel gear 80 is rotatably matched with the sleeve 110 through a bearing, the inner ring of the bearing is fixedly connected to the inner wall of the rotating shaft of the driven bevel gear 80, and the outer ring of the bearing is fixedly connected to the inner wall of the sleeve 110.

[0041] The principle of deformation of the nose cone body in the deformable nose cone 100 with omnidirectional swinging capability of this embodiment is as follows:

[0042] The side walls of the inner conical sleeve 30 and the outer conical sleeve 50 are both made of corrugated plates, which can be bent along the direction of the corrugation arrangement. The corrugations of the corrugated plates on the side walls of the inner conical sleeve 30 are arranged along the generatrix direction of the inner conical sleeve 30, and the corrugations of the corrugated plates on the side walls of the outer conical sleeve 50 are arranged along the generatrix direction of the outer conical sleeve 50. This results in that both the inner conical sleeve 30 and the outer conical sleeve 50 can be bent in all directions on the cross section, providing a significant anisotropic feature for the head cone body, that is, flexibility in the direction of the corrugation arrangement, and high rigidity in the direction perpendicular to the corrugated plates, which both amplifies the deformation effect and effectively resists external aerodynamic loads. The side walls of the middle conical sleeve 40 are made of honeycomb core material, so that the middle conical sleeve 40 also has good deformation performance.

[0043] Each conical ring 20 and conical tip 10 is rigid and will not deform, but because the inner conical sleeve 30, the middle conical sleeve 40 and the outer conical sleeve 50 in the thermal protection structure have significant anisotropy, each thermal protection structure can deform under the action of external force; during operation, the first drive device 60 drives the active bevel gear 70 to rotate, and the active bevel gear 70 drives the driven bevel gear 80 to rotate, and the rotating shaft of the driven bevel gear 80 drives the rocker arm 120 to swing, and when the rocker arm 120 swings, it drives the conical tip 10 to swing, thereby applying a bending force to the head cone body, thereby realizing the deformation and bending of the head cone body as a whole; it should be noted that the deformation and bending of the head cone body as a whole is realized by each thermal protection structure, and the conical tip 10 in the head cone body and each conical ring 20 itself will not deform.

[0044] In addition, the second drive device 90 is provided to flexibly adjust the position of the driven bevel gear 80. Specifically, when the second drive device 90 is working, the drive sleeve 110 rotates, and the sleeve 110 drives the driven bevel gear 80 to rotate, ensuring the smooth swing of the head cone in any direction, meeting the requirements of omnidirectional swing; while adjusting the position of the driven bevel gear 80 through the second drive device 90, the first drive device 60 drives the active bevel gear 70 to rotate, so that the driven bevel gear 80 rotates with the output shaft of the second drive device 90 as the central axis, and the active bevel gear 70 rotates, thereby preventing the driven bevel gear 80 from rotating when the driven bevel gear 80 rotates with the output shaft of the second drive device 90 as the central axis. This unique driving mechanism overcomes the shortcomings of the traditional connecting rod mechanism in achieving omnidirectional swing, and greatly improves the flexibility and scope of application of the system.

[0045] In this embodiment, the head cone body is in a conical shape as a whole; the inner diameter of each conical ring 20 gradually increases from one end close to the conical tip 10 to the other end; among any two conical rings 20, the minimum inner diameter of the conical ring 20 far away from the conical tip 10 is greater than the maximum inner diameter of the other conical ring 20. Since the inner conical sleeve 30, the middle conical sleeve 40 and the outer conical sleeve 50 in each heat protection structure are fixedly connected to one conical ring 20 at one end and fixedly connected to another conical ring 20 or the conical tip 10 at the other end, it is easy to understand that the inner diameters of the inner conical sleeve 30, the middle conical sleeve 40 and the outer conical sleeve 50 also gradually increase from one end close to the conical tip 10 to the other end; and among any two heat protection structures, the minimum inner diameter of the heat protection structure far away from the conical tip 10 is greater than the maximum inner diameter of the other heat protection structure.

[0046] In the optional scheme of this embodiment, it is more preferred that the side wall of the sleeve 110 is provided with an arc-shaped groove 111 corresponding to the rocker arm 120, and the rocker arm 120 passes through the arc-shaped groove 111 and slides with the arc-shaped groove 111; and the axis of the rocker arm 120 is located on the longitudinal section of the head cone body; when the head cone body is not bent, the rocker arm 120 is coaxial with the head cone body.

[0047] In the optional solution of this embodiment, it is more preferred that both the first drive device 60 and the second drive device 90 adopt electro-hydraulic drives.

[0048] In an optional solution of the present embodiment, it is more preferred that the materials of the tapered ring 20, the tapered tip 10, the inner tapered sleeve 30, the middle tapered sleeve 40 and the outer tapered sleeve 50 are all metal.

[0049] In an optional solution of the present embodiment, it is more preferred that the driving bevel gear 70 is coaxial with the output shaft of the first driving device 60 , and the driving bevel gear 70 is fixed on the output shaft of the first driving device 60 .

[0050] In an optional solution of the present embodiment, it is more preferred that in the same heat protection structure, there are gaps between the inner tapered sleeve 30 and the outer tapered sleeve 50 and the middle tapered sleeve 40 .

[0051] In the optional scheme of this embodiment, it is more preferred that the first driving device 60 is fixedly connected to the frame through a first fixed bracket (not shown in the figure), and the second driving device 90 is fixedly connected to the frame through a second fixed bracket (not shown in the figure).

[0052] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only used to help understand the method and core ideas of the present invention. At the same time, for those skilled in the art, according to the ideas of the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. A deformable nose cone with omnidirectional swing capability, characterized in that: include: A head cone body, wherein the head cone body comprises a conical tip, a plurality of conical rings and a plurality of heat protection structures distributed along the axial direction of the head cone body, the conical rings and the heat protection structures are staggered, and a heat protection structure is arranged between the conical tip and the adjacent conical ring, one end of the head cone body is the conical tip, and the other end is the conical ring, the conical tip and each of the conical rings are fixedly connected to the adjacent heat protection structure; the heat protection structure comprises an inner conical sleeve, an intermediate conical sleeve and an outer conical sleeve distributed in sequence from inside to outside along the radial direction of the head cone body, the side wall of the inner conical sleeve and the side wall of the outer conical sleeve are both made of corrugated plates, the corrugations of the corrugated plates on the side wall of the inner conical sleeve are arranged along the generatrix direction of the inner conical sleeve, the corrugations of the corrugated plates on the side wall of the outer conical sleeve are arranged along the generatrix direction of the outer conical sleeve, and the side wall of the intermediate conical sleeve is made of honeycomb core material; The driving mechanism comprises a first driving device, a second driving device, a rocker arm, a sleeve, a driving bevel gear and a driven bevel gear meshing with the driving bevel gear, the first driving device and the second driving device are respectively fixedly connected to the frame of the aircraft on which the head cone body is installed, and when the head cone body is installed on the aircraft, the conical ring in the head cone body farthest from the conical tip is fixedly connected to the frame; the output shaft of the second driving device and the driving bevel gear are coaxial with the conical ring in the head cone body farthest from the conical tip, the first driving device is used to drive the driving bevel gear to rotate, the sleeve is rotatably sleeved on the rotating shaft of the driven bevel gear, the sleeve is fixedly connected to the output shaft of the second driving device, the rotating shaft of the driven bevel gear and the axial direction of the sleeve are both perpendicular to the output shaft of the second driving device, one end of the rocker arm is fixedly connected to the rotating shaft of the driven bevel gear, and the other end is fixedly connected to the conical tip.

2. The deformable nose cone with omnidirectional swinging capability according to claim 1, characterized in that: The inner diameter of each conical ring gradually increases from one end close to the conical tip to the other end; among any two conical rings, the minimum inner diameter of the conical ring far away from the conical tip is greater than the maximum inner diameter of the other conical ring.

3. The deformable nose cone with omnidirectional swinging capability according to claim 1, characterized in that: The side wall of the sleeve is provided with an arc-shaped slide groove corresponding to the swing rod, and the swing rod passes through the arc-shaped slide groove and is slidably matched with the arc-shaped slide groove.

4. The deformable nose cone with omnidirectional swinging capability according to claim 1, characterized in that: The first driving device and the second driving device both adopt electro-hydraulic drivers.

5. The deformable nose cone with omnidirectional swinging capability according to claim 1, characterized in that: The materials of the tapered ring, the tapered tip, the inner tapered sleeve, the middle tapered sleeve and the outer tapered sleeve are all metal.

6. The deformable nose cone with omnidirectional swinging capability according to claim 1, characterized in that: The active bevel gear is coaxial with the output shaft of the first driving device, and the active bevel gear is fixed on the output shaft of the first driving device.

7. The deformable nose cone with omnidirectional swinging capability according to claim 1, characterized in that: In the same heat protection structure, there are spaces between the inner tapered sleeve, the outer tapered sleeve and the middle tapered sleeve.

8. The deformable nose cone with omnidirectional swinging capability according to claim 1, characterized in that: The inner tapered sleeve, the middle tapered sleeve and the outer tapered sleeve are all fixedly connected to one tapered ring at one end and fixedly connected to another tapered ring or the tapered tip at the other end.

9. The deformable nose cone with omnidirectional swinging capability according to claim 1, characterized in that: The first driving device is fixedly connected to the frame via a first fixing bracket, and the second driving device is fixedly connected to the frame via a second fixing bracket.

10. The deformable nose cone with omnidirectional swinging capability according to claim 1, characterized in that: The rotating shaft of the driven bevel gear is rotationally matched with the sleeve through a bearing.

Images