aircraft nose cone

Abstract

This invention discloses a nose cone for an aircraft, comprising conical sections, a first connecting portion, a second connecting portion, and a movable portion. Multiple conical sections are sequentially connected to form the nose cone. Adjacent conical sections are respectively provided with a first connecting portion and a second connecting portion, which are configured to be spaced apart and correspond one-to-one in the circumferential direction of the conical sections. One end of the movable portion is hinged to the first connecting portion, and the other end is connected to the second connecting portion via a universal joint. The movable portion is adapted to deform to drive relative movement between adjacent conical sections, thereby driving nose cone deformation. The aircraft nose cone of this invention can ensure the stability and flexibility of nose cone deformation while maintaining a simplified structure, achieving arbitrary angle deformation of the nose cone.

Description

Technical Field

[0001] This invention relates to the field of aerospace vehicle technology, and in particular to a nose cone for an aircraft. Background Technology

[0002] The rapid development of aerospace technology places increasingly higher demands on aircraft performance. To adapt to different flight environments, aircraft incorporate morphing structures to adjust their shape. The nose cone is a key component for achieving this morphing. Related technologies either employ parallel mechanisms for overall deformation drive, but this results in poor structural flexibility, making it impossible to achieve small deformations through partial deformation, and the parallel mechanisms also suffer from high loads and insufficient stability; or they utilize a combination of various types of branches for drive, but this leads to higher structural complexity, greater control difficulty, uneven stress distribution, and limited stability. Summary of the Invention

[0003] This invention aims to at least solve one of the technical problems existing in the prior art. Therefore, one object of this invention is to propose a nose cone for an aircraft that utilizes distributed actuation to achieve a nose cone variant, resulting in low structural complexity, high structural stability, and high control flexibility.

[0004] This invention provides a nose cone for an aircraft, comprising conical sections, a first connecting portion, a second connecting portion, and a movable portion. Multiple conical sections are sequentially connected to form the nose cone. Adjacent conical sections are respectively provided with a first connecting portion and a second connecting portion, which are configured to be spaced apart and correspond one-to-one in the circumferential direction of the conical sections. One end of the movable portion is hinged to the first connecting portion, and the other end is connected to the second connecting portion via a universal joint. The movable portion is adapted to deform to drive relative movement between adjacent conical sections, thereby driving nose cone deformation.

[0005] According to the aircraft nose cone of this application embodiment, each conical segment can move independently relative to adjacent segments, making the nose cone flexible in deformation. Each group of moving parts deforms independently and cooperates to drive the conical segments, dispersing the driving force, which reduces the load on individual structures and increases their service life, making the nose cone structure more stable and with a large load-bearing capacity. Hinges and universal joints ensure the freedom of extension or bending between adjacent conical segments while restricting the freedom of torsion, resulting in a simplified and effective structure. Simultaneously, the conical segments are connected by the same branch structure, making the structure uniform, easy to manufacture and maintain, and the control strategy simple and efficient. The aircraft nose cone of this embodiment can ensure the stability and flexibility of the nose cone while maintaining a simplified structure, achieving stable deformation of the nose cone.

[0006] According to some embodiments of the present invention, the universal joint includes: a first universal joint fork, a second universal joint fork, and a cross shaft. The first universal joint fork is disposed at one end of the movable part; the second universal joint fork is disposed at the second connecting part; the cross shaft is provided with a first shaft and a second shaft connected to each other, the first shaft being rotatably connected to the first universal joint fork, and the second shaft being rotatably connected to the second universal joint fork.

[0007] According to some embodiments of the present invention, the movable portion is adapted to extend or shorten to change the distance between the first connecting portion and the second connecting portion.

[0008] According to some embodiments of the present invention, the movable part includes an outer rod and an inner connecting rod. One end of the outer rod is hinged to a first connecting part, and a sliding cavity open to the other end is formed inside the outer rod; one end of the inner connecting rod is retractably received in the sliding cavity, and the other end of the inner connecting rod is provided with a second universal joint fork.

[0009] According to some embodiments of the present invention, the outer rod is provided with a first locking part, and the inner connecting rod is provided with a second locking part. The first locking part and the second locking part cooperate to limit the deformation range of the movable part.

[0010] According to a further embodiment of the present invention, the first locking part is configured as a locking groove provided on the inner peripheral wall of the outer sleeve rod, and the locking groove is provided with a first wall and a second wall respectively in the extending direction of the outer sleeve rod; the second locking part is configured as a limiting block provided on the outer peripheral wall of the inner connecting rod, the limiting block is received in the locking groove and abuts against the first wall or the second wall at the extreme position.

[0011] According to some embodiments of the present invention, the aircraft nose cone further includes a drive unit. The drive units are configured as a plurality of units corresponding one-to-one with the movable units, each drive unit being adapted to drive the deformation of the corresponding movable unit.

[0012] According to some embodiments of the present invention, the conical section is constructed as a centrally symmetrical structure, with a plurality of first connecting portions and / or a plurality of second connecting portions arranged symmetrically about the conical section.

[0013] According to some embodiments of the present invention, the distance between the hinge connection point of the first connecting part and the center of the corresponding cone is r1, and the distance between the universal joint connection point of the second connecting part and the center of the corresponding cone is r2, and the following condition is met: r1=r2.

[0014] According to some embodiments of the present invention, the angle between any two adjacent first connecting parts and the center of the corresponding conical segment is α, and satisfies: 60°≤α≤120°.

[0015] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0016] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the description of the embodiments taken in conjunction with the following drawings, in which:

[0017] Figure 1 This is a perspective view of the nose cone of an aircraft according to an embodiment of the present invention;

[0018] Figure 2 This is a front view of the structure of the nose cone of an aircraft according to an embodiment of the present invention;

[0019] Figure 3 This is a left view of the structure of the nose cone of an aircraft according to an embodiment of the present invention;

[0020] Figure 4 This is a cross-sectional view of the nose cone of an aircraft according to an embodiment of the present invention about section line AA;

[0021] Figure 5 This is a schematic diagram of the structure of the second cone section of the nose cone of an aircraft according to an embodiment of the present invention;

[0022] Figure 6 This is an assembly drawing of the movable part of the nose cone of an aircraft according to an embodiment of the present invention;

[0023] Figure 7 This is a schematic diagram of the structure of the movable part of the nose cone of an aircraft according to an embodiment of the present invention;

[0024] Figure 8 This is a schematic diagram of the aircraft nose cone retracted in a state according to an embodiment of the present invention;

[0025] Figure 9 This is a schematic diagram of the nose cone bending state of an aircraft according to an embodiment of the present invention.

[0026] Figure label:

[0027] The aircraft's nose cone is 100mm.

[0028] Conical segment 10; First conical segment 101; Second conical segment 102; Third conical segment 103; Fourth conical segment 104; Fifth conical segment 105; Sixth conical segment 106;

[0029] First connecting part 20; Second connecting part 40;

[0030] Activity section 30; outer rod 31; inner connecting rod 32;

[0031] Universal joint 50; First universal joint fork 53; Second universal joint fork 51; Cross shaft 52. Detailed Implementation

[0032] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0033] The following is for reference. Figures 1-9 A description of an aircraft nose cone 100 according to an embodiment of the present invention.

[0034] like Figures 1-9 As shown, the nose cone 100 of an aircraft according to an embodiment of the present invention includes: a cone segment 10, a first connecting portion 20, a second connecting portion 40, and a movable portion 30. Multiple cone segments 10 are provided, and the multiple cone segments 10 are sequentially connected to form the nose cone 100; a first connecting portion 20 and a second connecting portion 40 are respectively provided on two adjacent cone segments 10, and the first connecting portion 20 and the second connecting portion 40 are configured to be spaced apart and correspond one-to-one in the circumferential direction of the cone segment 10; one end of the movable portion 30 is hingedly connected to the first connecting portion 20, and the other end of the movable portion 30 is connected to the second connecting portion 40 via a universal joint 50; wherein the movable portion 30 is adapted to deform to drive the relative movement of two adjacent cone segments 10 to drive the nose cone 100 to deform.

[0035] In an embodiment of the present invention, the first connecting part 20, the movable part 30, and the second connecting part 40 form a branch that connects two adjacent cone sections 10 and drives the two cone sections 10 to move relative to each other.

[0036] According to an embodiment of the present invention, the aircraft nose cone 100, due to the arrangement of multiple sets of branches between two adjacent cone sections 10, allows the corresponding first connecting part 20 and second connecting part 40 to move relative to each other when each movable part 30 deforms. In two adjacent cone sections 10, taking one cone section 10 as a reference, the relative movement of multiple second connecting parts 40 and first connecting parts 20 can drive the other movable cone section 10 to move relative to the reference cone section 10: when the deformation of each movable part 30 is the same, the movable cone section 10 moves parallel to or away from the reference cone section 10; when the deformation of each movable part 30 is different and coordinated, the movable cone section 10 moves relative to the reference cone section 10 and forms a certain angle with it. In a series of sequentially connected conical segments 10, each pair of adjacent segments 10 moves relative to each other, resulting in the superposition and transmission of motion between the first and last segments 10, enabling the head cone 100 to deform flexibly: when adjacent segments 10 move parallel and close together or far apart, the head cone 100 elongates or shortens; when adjacent segments 10 move relative to each other, forming an angle with a unified direction, the head cone 100 bends at any angle; when the relative motion of adjacent segments 10 is not uniform, the head cone 100 undergoes complex deformation. For example... Figure 2 As shown, the head cone 100 is in an extended state; as Figure 8As shown, the head cone 100 is in a bent state; as Figure 9 As shown, the head cone 100 is in the retracted state.

[0037] It should be noted that when the head cone 100 bends or undergoes complex deformation, the angle between each movable part 30 and the two adjacent cone sections 10 will change. This requires that at least one of the connections between the movable part 30 and the first connecting part 20 and the second connecting part 40 be able to rotate relative to each other at any angle. At the same time, since the relative positions of the first connecting part 20, the second connecting part 40 and the corresponding cone section 10 remain unchanged, the deformation of each movable part 30 needs to be coordinated when the two adjacent cone sections 10 move relative to each other.

[0038] Since one end of the movable part 30 is hinged to the first connecting part 20 and the other end is connected to the second connecting part 40 via a universal joint 50, the movable part 30 can rotate relative to the second connecting part 40 around the center of the universal joint 50, and this rotation is arbitrary. Simultaneously, the movable part 30 can rotate relative to the first connecting part 20 around the hinge axis, but this rotation is restricted to a rotation plane perpendicular to the hinge axis. Because the movable part 30 cannot rotate about its own centerline about the first connecting part 20, the mutual constraint of two or more sets of branches can form a common constraint between the movable part 30 and the universal joint 50, preventing adjacent conical sections 10 from rotating parallel to each other (i.e., from torsion), and allowing them to move parallel or at an angle towards or away from each other. The restriction on the torsional freedom of the conical sections 10 can be achieved using only two sets of branches, eliminating the need for additional limiting structures or additional connections between branches, resulting in a simplified structure and a lighter mechanism. At the same time, due to the mutual constraints between the structures, the relative movement of two adjacent cone sections 10 cannot be arbitrarily realized. It can only be driven by the various branches that cooperate with each other, so as to ensure the stability of the connection between the two adjacent cone sections 10 and the flexibility of their relative movement.

[0039] According to the aircraft nose cone 100 of this application embodiment, since multiple sets of branches are provided between every two adjacent cone sections 10, each cone section 10 can move independently relative to its adjacent cone sections 10, making the nose cone 100 flexible in deformation. Furthermore, each set of movable parts 30 deforms independently and cooperates to drive the cone section 10 to move, dispersing the driving force, which reduces the load on a single structure and increases its service life, making the nose cone 100 structure more stable and with a large load-bearing capacity. In addition, the use of hinges and universal joints 50 ensures that adjacent cone sections 10 have the freedom of extension or bending, while also restricting the freedom of torsion of the cone sections 10, resulting in a simplified structure and low mass. Simultaneously, the cone sections 10 are connected by the same branch structure, making the structure uniform, easy to manufacture and maintain, and the control strategy simple and efficient. The aircraft nose cone 100 of this embodiment can ensure the stability and flexibility of the nose cone 100 while maintaining a simplified structure, achieving stable deformation of the nose cone 100.

[0040] In embodiments of the present invention, the number and size of the conical sections 10 can be selected and adjusted according to actual needs. In some embodiments, such as Figures 2-4 As shown, the aircraft nose cone 100 has six sets of conical sections, namely the first conical section 101, the second conical section 102, the third conical section 103, the fourth conical section 104, the fifth conical section 105, and the sixth conical section 106. The first conical section 101 has only a first connecting portion 20, the sixth conical section 106 is constructed as a cone and has only a second connecting portion 40, and the other conical sections have first connecting portions 20 and second connecting portions 40 on both sides, as shown. Figure 5 As shown. In some embodiments, the maximum diameter of the cones decreases sequentially. The maximum diameter of the first cone 101 is 500 mm, and the maximum diameters of the other cones are 500 mm, 478 mm, 448 mm, 403 mm, and 313 mm, respectively. The width of each cone in the connection direction is 90 mm, and the shell thickness of each cone is 10 mm.

[0041] According to some embodiments of the present invention, such as Figure 6 , Figure 7 As shown, the universal joint 50 includes: a first universal joint fork 53, a second universal joint fork 51, and a cross shaft 52. The first universal joint fork 53 is disposed at one end of the movable part 30; the second universal joint fork 51 is disposed at the second connecting part 40; the cross shaft 52 is provided with a first shaft and a second shaft connected to each other, the first shaft being rotatably connected to the first universal joint fork 53, and the second shaft being rotatably connected to the second universal joint fork 51.

[0042] In this embodiment, two universal joint forks are connected by a cross shaft 52, allowing the two universal joint forks to rotate around the two axes of the cross shaft 52 and move relative to each other. Furthermore, when the movable part 30 deforms to drive the two conical sections 10 to move relative to each other, the movable part 30 can perform a compound movement relative to the second connecting part 40, rotating around the two axes, to accommodate any change in the angle between the movable part 30 and the second connecting part 40. In some embodiments, the second universal joint fork 51 is rotatably connected to the second connecting part 40, allowing the movable part 30 to rotate relative to the second connecting part 40 around the centerline of the second universal joint fork 51. This increases the degree of freedom of rotation of the movable part 30 relative to the second connecting part 40, enabling the movable part 30 to perform a compound movement relative to the second connecting part 40 around three centerlines, thus making the relative movement of the two conical sections 10 smoother. Simultaneously, redundant degrees of freedom are provided for the relative movement of the movable part 30 and the second connecting part 40, effectively preventing structural jamming.

[0043] According to some embodiments of the present invention, the movable part 30 is adapted to extend or shorten to change the distance between the first connecting part 20 and the second connecting part 40. When the movable part 30 extends, the first connecting part 20 and the second connecting part 40 move away from each other; when the movable part 30 shortens, the first connecting part 20 and the second connecting part 40 move closer together. Multiple movable parts 30 extend or shorten in coordination, causing the distance between the corresponding first connecting part 20 and the second connecting part 40 to change, thereby achieving relative movement between the two conical sections 10. Changing the length of the movable part 30 to change the distance between the first connecting part 20 and the second connecting part 40 is direct, clear, and easy to control.

[0044] According to some embodiments of the present invention, such as Figure 7 As shown, the movable part 30 includes an outer rod 31 and an inner connecting rod 32. One end of the outer rod 31 is hinged to the first connecting part 20, and a sliding cavity open to the other end is formed inside the outer rod 31. One end of the inner connecting rod 32 is retractably housed in the sliding cavity, and the other end of the inner connecting rod 32 is provided with a second universal joint fork 51. One end of the inner connecting rod 32 can slide within the sliding cavity of the outer rod 31 to achieve the extension or shortening of the movable part 30. In this embodiment, the use of an inner and outer rod 31 facilitates the driving of the deformation of the movable part 30. In some embodiments, a pneumatic pump or similar device can be used to drive the extension and retraction of the movable part 30.

[0045] It should be noted that the deformation of the movable part 30 is not arbitrary. In some cases, such as when the movable part 30 shrinks to a length that is too small, it may cause two adjacent cone sections 10 to collide. In other cases, such as when the movable part 30 elongates too much, it may cause the inner connecting rod 32 to slip off the outer rod 31, causing the structure to become unstable.

[0046] To address the aforementioned potential problems, according to some embodiments of the present invention, the outer rod 31 is provided with a first locking part (not shown in the figure), and the inner connecting rod 32 is provided with a second locking part (not shown in the figure). The first locking part and the second locking part cooperate to limit the deformation range of the movable part 30. In this embodiment, when the inner connecting rod 32 moves relative to the outer rod 31 to the minimum and maximum length positions allowed by the movable part 30, the first locking part and the second locking part cooperate to lock, thereby preventing the inner connecting rod 32 from continuing to move relative to the outer rod 31, thus ensuring the stability of the structure.

[0047] In some embodiments of the present invention, the first locking part is constructed as a locking groove disposed on the inner peripheral wall of the outer sleeve rod 31, and the locking groove is provided with a first wall and a second wall respectively in the extending direction of the outer sleeve rod 31; the second locking part is constructed as a limiting block disposed on the outer peripheral wall of the inner connecting rod 32, the limiting block being received in the locking groove and abutting against the first wall or the second wall at the extreme position. In this embodiment, the limiting block slides relative to the outer sleeve rod 31 with the inner connecting rod 32 in the locking groove. When the limiting block abuts against the first wall or the second wall, the movement of the inner connecting rod 32 in the moving direction is restricted and stopped. Therefore, the inner connecting rod 32 can only move relative to the outer sleeve rod 31 within the range limited by the first wall and the second wall, avoiding structural collisions or slippage, and ensuring the stability of the structure.

[0048] According to some embodiments of the present invention, the aircraft nose cone 100 further includes a drive unit (not shown in the figure). The drive unit is configured as a plurality of units corresponding one-to-one with the movable parts 30, each drive unit being adapted to drive the deformation of its corresponding movable part 30. This embodiment employs a distributed drive, with each drive unit corresponding one-to-one with the movable parts 30, enabling each movable part 30 to be independently driven by the drive unit for deformation. This distinguishes the deformation amounts of each movable part 30, improving the flexibility of relative movement between adjacent cone sections 10. Simultaneously, this distributed drive helps reduce the load borne by each set of branches, improves drive efficiency, reduces the requirements on the drive unit, and extends the service life of the branches. Furthermore, the distributed drive can also be redundantly designed, ensuring overall reliability in the event of partial drive failure, and ensuring that the deformation of the nose cone 100 is not affected. In some embodiments, the drive unit can be configured to drive the deformation of the movable part 30 using air pressure, or it can be integrally constructed with the movable part 30 as an electrically driven telescopic cylinder, etc., achieving structural simplification as much as possible based on the distributed drive.

[0049] According to some embodiments of the present invention, the cone 10 is constructed as a centrally symmetrical structure, with multiple first connecting portions 20 and / or multiple second connecting portions 40 arranged symmetrically about the cone 10. Through the centrally symmetrical design of the cone 10 and the first connecting portions 20 and second connecting portions 40 about the cone 10, the head cone 100 of this embodiment is constructed as a centrally symmetrical structure, which enables a more uniform distribution of the driving force of each movable portion 30 on the cone 10, thus increasing the stability of the head cone 100 structure.

[0050] According to some embodiments of the present invention, the distance between the hinge connection point of the first connecting part 20 and the center of the corresponding cone 10 is r1, and the distance between the universal joint 50 connection point of the second connecting part 40 and the center of the corresponding cone 10 is r2, satisfying: r1 = r2. In this embodiment, since the head cone 100 is a centrally symmetrical structure, the center lines of each cone 10 coincide, and the distances between the hinge point, the universal joint 50 connection point and the corresponding cone 10 are equal, the distances between the centers of both ends of the movable part 30 and the center lines of the two adjacent cones 10 are also equal. Therefore, when the head cone 100 undergoes elongation or shortening deformation, that is, when the two adjacent cones 10 are parallel and approaching or moving away, the movable part 30 is parallel to the center line of the head cone 100, such as... Figure 4 As shown, by concentrating the force exerted by the movable part 30 on the cone 10 in the direction of movement of the cone 10 on the basis of uniform force distribution on the cone 10, the radial force is reduced, which can effectively improve the load-bearing capacity of the head cone 100 structure.

[0051] According to some embodiments of the present invention, the angle between any two adjacent first connecting parts 20 and the center of the corresponding conical segment 10 is α, and satisfies: 60°≤α≤120°. Since the first connecting parts 20 are arranged circumferentially along the conical segment 10, the size of the angle α between any two adjacent first connecting parts 20 and the center of the corresponding conical segment 10 determines the number of branches between the two conical segments 10. When the angle between any two adjacent first connecting parts 20 and the center of the corresponding conical segment 10 satisfies 60°≤α≤120°, the number of branches can be set to three, four, five, or six.

[0052] Since the angle between the second connecting part 40 and the movable part 30 can vary arbitrarily, at least three connecting points are required to achieve relative fixation of adjacent conical sections 10. Therefore, at least three sets of branches are selected.

[0053] In some embodiments of the present invention, such as Figures 1-9 As shown, four sets of branches are provided between adjacent cone sections 10. Each branch includes a first connecting part 20, a movable part 30, and a second connecting part 40. The movable part 30 is a telescopic structure including an inner connecting rod 32 and an outer connecting rod 31. The first connecting part 20 is hinged to the outer connecting rod 31, and the second connecting part 40 is connected to the inner connecting rod 32 via a universal joint 50. Therefore, this branch includes a revolute joint R, a prismatic joint P, and a universal joint U. When driving adjacent cone sections 10, only three sets of RPU branches are needed to drive the movement; the other set acts as a driven branch, maintaining motion stability and limiting the degree of freedom of the mechanism. Simultaneously, one set of branches can serve as a backup, ensuring that three sets of branches can normally drive the cone section 10 to move in the event of a failure in any set, thus guaranteeing the stability and reliability of the head cone 100 variant. Figure 4As shown, the four sets of branches are arranged in a centrally symmetrical manner, which can make the force on the cone 10 more uniform and stable when driven together; furthermore, when the initial adjustment state is that the adjacent cones 10 are parallel, if the head cone 100 extends or bends or deforms in the direction of a certain movable part 30, such as Figure 9 As shown, the head cone 100 bends downwards and to the right, which can be achieved by only two horizontally opposite RPU branches providing two sets of driving forces. The other two branches passively deform to maintain motion stability and restrict the degree of freedom of the mechanism. This embodiment can reduce the number of drives, simplify control, and improve drive efficiency.

[0054] In some embodiments, the number of branches can also be set to five or six groups to provide more spare branches and improve the reliability of the head cone 100; at the same time, they can work together to further disperse the stress points of the cone 10, making the structure more stable.

[0055] In some embodiments, the number of branches may be set to more than six groups, but too many branches will increase the load on the head cone 100, increase the load on each structure, and reduce the stability of the structure, which does more harm than good.

[0056] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0057] In the description of this invention, "first feature" and "second feature" may include one or more of the features.

[0058] In the description of this invention, "a plurality of" means two or more.

[0059] In the description of this invention, the first feature being "above" or "below" the second feature may include the first and second features being in direct contact, or it may include the first and second features not being in direct contact but being in contact through another feature between them.

[0060] In the description of this invention, the terms "above," "over," and "on top" for the first feature and the second feature include the first feature being directly above or diagonally above the second feature, or simply indicating that the first feature is at a higher horizontal level than the second feature.

[0061] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "illustrative embodiment," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0062] Although embodiments of the invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. An aircraft nose cone, characterized by, The application relates to a cone joint, which comprises: a plurality of taper joints, which are sequentially connected to form a head taper; a first connecting part and a second connecting part are respectively arranged on two adjacent taper joints, the first connecting part and the second connecting part are configured as a plurality of parts which are arranged in a circumferential direction of the taper joints and one-to-one corresponding; a movable part, one end of the movable part is hingedly connected with the first connecting part, and the other end of the movable part is connected with the second connecting part through a universal joint; wherein the movable part is adapted to deform to drive the relative movement of the two adjacent taper joints to drive the deformation of the head taper; one end of the movable part is hingedly connected with the first connecting part, and the other end of the movable part is connected with the second connecting part through the universal joint, the movable part rotates relative to the second connecting part around the center of the universal joint, and the rotation is arbitrary; meanwhile, the movable part rotates relative to the first connecting part around the hinged shaft, and the rotation is limited in a rotation plane perpendicular to the hinged shaft; the movable part cannot rotate around the center line thereof relative to the first connecting part, and two or more groups of branched chains restrict each other to form common restriction between the movable part and the universal joint, so that the two adjacent taper joints cannot rotate in parallel and cannot be twisted, and can only approach or move away in parallel or at an angle.

2. The aircraft nose cone of Claim 1, wherein, The universal joint comprises: a first universal joint fork arranged at one end of the movable part; a second universal joint fork arranged at the second connecting part; a cross shaft provided with a first shaft and a second shaft connected with each other, the first shaft being rotatably connected with the first universal joint fork, and the second shaft being rotatably connected with the second universal joint fork.

3. The aircraft nose cone of Claim 2, wherein, The movable part is adapted to elongate or shorten to change the distance between the first connecting part and the second connecting part.

4. The aircraft nose cone of Claim 3, wherein, The movable part comprises: an outer sleeve rod, one end of the outer sleeve rod being hingedly connected with the first connecting part, and a sliding cavity being formed in the outer sleeve rod and being open towards the other end; an inner connecting rod, one end of the inner connecting rod being telescopically accommodated in the sliding cavity, and the other end of the inner connecting rod being provided with the second universal joint fork.

5. The aircraft nose cone of Claim 4, wherein, The outer sleeve rod is provided with a first locking part, and the inner connecting rod is provided with a second locking part, the first locking part and the second locking part being matched to limit the deformation range of the movable part.

6. The aircraft nose cone of Claim 5, wherein, The first locking part is configured as a locking groove arranged on an inner circumferential wall of the outer sleeve rod, and the locking groove is respectively provided with a first wall and a second wall in the extension direction of the outer sleeve rod; the second locking part is configured as a limiting block arranged on an outer circumferential wall of the inner connecting rod, the limiting block being accommodated in the locking groove and being abutted with the first wall or the second wall at a limit position.

7. The aircraft nose cone of Claim 1, wherein, The application further comprises: a driving part, which is configured as a plurality of parts corresponding to the movable parts, and each driving part is adapted to drive the deformation of the corresponding movable part.

8. The aircraft nose cone of Claim 1, wherein, The taper joint is configured as a central symmetric structure, and the plurality of first connecting parts and / or the plurality of second connecting parts are symmetrically arranged about the symmetry center of the taper joint.

9. The aircraft nose cone of Claim 8, wherein, The distance between the hinge connection point of the first connection part and the corresponding taper joint center is r1, the distance between the universal joint connection point of the second connection part and the corresponding taper joint center is r2, and the following is satisfied: r1=r2.

10. The aircraft nose cone of Claim 1, wherein, The included angle between any two adjacent first connection parts and the corresponding taper joint center is α, and the following is satisfied: 60°≤α≤120°.

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