Aircraft nose cone

Abstract

The invention discloses an aircraft nose cone. The aircraft nose cone comprises a cone section, a first connecting part, a second connecting part and a movable part. The plurality of cone sections are connected in sequence to form a nose cone; a plurality of first connecting parts and a plurality of second connecting parts are arranged on every two adjacent cone sections at intervals in the circumferential direction of the cone sections, and the first connecting parts and the second connecting parts are in one-to-one correspondence; one end of the movable part is hinged 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 suitable for deforming to drive the two adjacent cone sections to move relatively so as to drive the nose cone to deform. According to the aircraft nose cone, under the condition that the structure is simplified, the deformation stability and flexibility of the nose cone can be guaranteed, and any-angle deformation of the nose cone is achieved.

Description

Technical Field

[0001] The invention relates to the technical field of aerospace vehicles, and in particular to a nose cone of an aircraft. Background Art

[0002] The rapid development of aerospace technology has placed higher and higher demands on aircraft performance. In order to adapt to different flight environments, aircraft are equipped with variant structures to adjust their own appearance. Among them, the nose cone is a key component for aircraft to achieve variants. In related technologies, the nose cone is driven to deform as a whole by a parallel mechanism, but the flexibility of the structure is poor, and it is impossible to achieve a smaller deformation by partial deformation, and the load of the parallel mechanism is large and the stability is insufficient; or a combination of multiple types of branch chains is used for driving, but the structure is more complex, the control is more difficult, the force is uneven and the stability is limited. Summary of the invention

[0003] The present invention aims to solve at least one of the technical problems existing in the prior art. To this end, one object of the present invention is to provide an aircraft nose cone, which uses distributed drive to achieve nose cone deformation, has low structural complexity, high structural stability and high control flexibility.

[0004] The embodiment of the present invention proposes an aircraft nose cone, which includes a cone section, a first connection part, a second connection part and a movable part. A plurality of cone sections are provided, and the plurality of cone sections are sequentially connected to form a nose cone; a first connection part and a second connection part are respectively provided on two adjacent cone sections, and the first connection part and the second connection part are configured as a plurality of cone sections that are spaced and correspond to each other in the circumferential direction of the cone section; one end of the movable part is hingedly connected to the first connection part, and the other end of the movable part is connected to the second connection part through a universal joint; wherein the movable part is suitable for deformation to drive the two adjacent cone sections to move relative to each other to drive the nose cone to deform.

[0005] According to the aircraft nose cone of the embodiment of the present application, each cone section can move independently relative to the adjacent cone sections, so that the deformation of the nose cone is flexible; each group of movable parts deforms independently and cooperates with each other to drive the cone sections to move, and the driving force is dispersed, which can reduce the load borne by a single structure and increase its service life, making the head cone structure more stable and having a large carrying capacity; hinges and universal joints are used to ensure that adjacent cone sections have the freedom to extend or bend, and to limit the freedom of torsion of the cone sections, so that the structure is streamlined and effective. At the same time, the cone sections are connected by the same branch chain structure, the structure is unified, easy to manufacture and maintain, and the control strategy is simple and efficient. The aircraft nose cone of this embodiment can ensure the stability and flexibility of the nose cone while simplifying the structure, and achieve stable deformation of the nose cone.

[0006] According to some embodiments of the present invention, the universal joint comprises: a first universal joint fork, a second universal joint fork and a cross shaft. The first universal joint fork is arranged at one end of the movable part; the second universal joint fork is arranged 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 is rotatably connected to the first universal joint fork, and the second shaft is rotatably connected to the second universal joint fork.

[0007] According to some embodiments of the present invention, the movable portion is adapted to be extended or shortened 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 hingedly connected to the first connecting part, and a sliding cavity open toward the other end is formed in the outer rod; one end of the inner connecting rod is telescopically accommodated 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 connecting rod is provided with a first locking portion, and the inner connecting rod is provided with a second locking portion, and the first locking portion cooperates with the second locking portion to limit the deformation range of the movable portion.

[0010] According to a further embodiment of the present invention, the first locking portion is constructed as a locking groove arranged on the inner peripheral wall of the outer rod, and the locking groove is respectively provided with a first wall and a second wall in the extension direction of the outer rod; the second locking portion is constructed as a limit block arranged on the outer peripheral wall of the inner connecting rod, and the limit block is accommodated in the locking groove and stops 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 comprises: a driving part. The driving parts are configured to be multiple and arranged in one-to-one correspondence with the movable parts, and each driving part is adapted to drive the corresponding movable part to deform.

[0012] According to some embodiments of the present invention, the cone section is configured as a centrally symmetrical structure, and the plurality of first connecting portions and / or the plurality of second connecting portions are symmetrically arranged about the symmetry center of the cone section.

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

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

[0015] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0017] Figure 1 is a structural stereogram of an aircraft nose cone according to an embodiment of the present invention;

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

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

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

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

[0022] Figure 6 is an assembly diagram of the movable portion of the aircraft nose cone according to one embodiment of the present invention;

[0023] Figure 7 is a schematic structural diagram of the movable portion of the aircraft nose cone according to one embodiment of the present invention;

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

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

[0026] Reference numerals:

[0027] Aircraft nose cone 100;

[0028] Cone section 10; first cone section 101; second cone section 102; third cone section 103; fourth cone section 104; fifth cone section 105; sixth cone section 106;

[0029] A first connection portion 20; a second connection portion 40;

[0030] Active part 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 DESCRIPTION

[0032] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0033] Reference below Figure 1-Figure 9 An aircraft nose cone 100 according to an embodiment of the present invention is described.

[0034] like Figure 1-Figure 9 As shown, the aircraft nose cone 100 according to an embodiment of the present invention comprises: a cone section 10, a first connection part 20, a second connection part 40 and a movable part 30. A plurality of cone sections 10 are provided, and the plurality of cone sections 10 are sequentially connected to form the nose cone 100; the first connection part 20 and the second connection part 40 are respectively provided on two adjacent cone sections 10, and the first connection part 20 and the second connection part 40 are configured to be arranged at intervals and one-to-one in the circumferential direction of the cone section 10; one end of the movable part 30 is hingedly connected to the first connection part 20, and the other end of the movable part 30 is connected to the second connection part 40 through a universal joint 50; wherein the movable part 30 is suitable for deformation to drive the two adjacent cone sections 10 to move relative to each other to drive the nose cone 100 to deform.

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

[0036] According to the aircraft nose cone 100 of the embodiment of the present invention, since multiple groups of branches are arranged between two adjacent cone sections 10, when each movable part 30 is deformed, the corresponding first connection part 20 and the second connection part 40 can be relatively moved. In two adjacent cone sections 10, taking one of the cone sections 10 as a reference, the relative movement of the multiple second connection parts 40 and the first connection part 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 approaches or moves away from the reference cone section 10 in parallel; 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. Among the multiple cone sections 10 connected in sequence, each two adjacent cone sections 10 move relative to each other, so that the motion between the first cone section 10 and the last cone section 10 is superimposed and transmitted, so that the head cone 100 can be flexibly deformed: when the two adjacent cone sections 10 are parallel and close to or away from each other, the head cone 100 can be extended or shortened; when the two adjacent cone sections 10 move relative to each other to form an angle and the directions are unified, the head cone 100 can be directional bent toward any angle; when the relative motion forms of the adjacent cone sections 10 are not unified, the head cone 100 can be deformed in a complex manner. Figure 2 As shown, the nose cone 100 is in an extended state; Figure 8As shown, the nose cone 100 is in a bent state; Fig. 9 As shown, the nose cone 100 is in a retracted state.

[0037] It should be noted that when the head cone 100 is bent or deformed in a complex manner, the angle between each movable part 30 and the two adjacent cone sections 10 will change, which 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 constructed to 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 amounts of each movable part 30 need to cooperate with each other 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 connection part 20, and the other end is connected to the second connection part 40 through a universal joint 50, the movable part 30 can rotate relative to the second connection part 40 around the center of the universal joint 50, and the rotation is arbitrary; at the same time, the movable part 30 can rotate relative to the first connection part 20 around the hinge axis, and the rotation is limited to a rotation plane perpendicular to the hinge axis. Since the movable part 30 cannot rotate around its own center line with respect to the first connection part 20, two or more groups of branches constrain each other, that is, they can form a common constraint between the movable part 30 and the universal joint 50, so that the two adjacent cone sections 10 cannot rotate relative to each other in parallel, that is, they cannot twist, and can only approach or move away in parallel or at an angle. The restriction of the torsional freedom of the cone section 10 can be achieved by using two groups of branches, without the need to set up a separate limit structure, and without establishing a separate association relationship between the branches. The structure is simple and the weight of the mechanism is small. At the same time, due to the mutual constraints between the structures, the relative movement of two adjacent cone sections 10 cannot be realized arbitrarily, and can only be driven by the mutually coordinated branch chains, thereby ensuring the stability of the connection between the two adjacent cone sections 10 and the flexibility of relative movement.

[0039] According to the aircraft nose cone 100 of the embodiment of the present application, since multiple groups of branches are arranged between every two adjacent cone sections 10, each cone section 10 can move independently relative to the adjacent cone section 10, so that the nose cone 100 can be deformed flexibly; and each group of movable parts 30 can be deformed independently and cooperate with each other to drive the cone section 10 to move, and the driving force is dispersed, which can reduce the load borne by a single structure and increase its service life, so that the structure of the nose cone 100 is more stable and has a large bearing capacity; in addition, the use of hinges and universal joints 50 can ensure that there is freedom of extension or bending between adjacent cone sections 10, and can also limit the freedom of torsion of the cone section 10, and the structure is simple and the mass is small. At the same time, the cone sections 10 are connected by the same branch chain structure, the structure is unified, easy to manufacture and maintain, and the control strategy is simple and efficient. The aircraft nose cone 100 of this embodiment can ensure the stability and flexibility of the nose cone 100 while simplifying the structure, and realize the stable deformation of the nose cone 100.

[0040] In the embodiment of the present invention, the number and size of the cone segments 10 can be selected and adjusted according to actual needs. Figure 2-Figure 4 As shown, the aircraft nose cone 100 is provided with six groups of cone sections, namely the first cone section 101, the second cone section 102, the third cone section 103, the fourth cone section 104, the fifth cone section 105 and the sixth cone section 106. Among them, the first cone section 101 is only provided with the first connection part 20, the sixth cone section 106 is constructed as a cone head and is only provided with the second connection part 40, and the first connection part 20 and the second connection part 40 are respectively provided on both sides of the other cone sections. Figure 5 In some embodiments, the maximum diameters of the cone segments decrease in sequence, the maximum diameter of the first cone segment 101 is 500 mm, the maximum diameters of the other cone segments are 500 mm, 478 mm, 448 mm, 403 mm, and 313 mm in sequence, the width of each cone segment in the connection direction is 90 mm, and the shell thickness of each cone segment is 10 mm.

[0041] According to some embodiments of the present invention, 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 arranged at one end of the movable part 30; the second universal joint fork 51 is arranged 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 is rotatably connected to the first universal joint fork 53, and the second shaft is rotatably connected to the second universal joint fork 51.

[0042] In this embodiment, two universal joint forks are connected by a cross shaft 52, so that the two universal joint forks can rotate around the two axes of the cross shaft 52 and move relative to each other; and then when the movable part 30 deforms and drives the two cone sections 10 to move relative to each other, the movable part 30 can perform a compound movement of rotating around two axes relative to the second connecting part 40 to adapt to 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 and the second connecting part 40 are rotatably connected, so that the movable part 30 can rotate relative to the second connecting part 40 around the center line of the second universal joint fork 51, increasing the degree of freedom of the movable part 30 to rotate relative to the second connecting part 40, so that the movable part 30 can perform a compound movement of rotating around three center lines relative to the second connecting part 40, and thus the relative movement of the two cone sections 10 can be smoother; at the same time, redundant degrees of freedom for the relative movement of the movable part 30 and the second connecting part 40 are provided, which can effectively avoid structural jamming.

[0043] According to some embodiments of the present invention, the movable portion 30 is adapted to be extended or shortened to change the distance between the first connection portion 20 and the second connection portion 40. When the movable portion 30 is extended, the first connection portion 20 and the second connection portion 40 are moved away from each other; when the movable portion 30 is shortened, the first connection portion 20 and the second connection portion 40 are moved closer to each other; a plurality of movable portions 30 are extended or shortened in coordination with each other, so that the spacing between the corresponding first connection portion 20 and the second connection portion 40 changes, so as to realize the relative movement of the two cone sections 10. The spacing between the first connection portion 20 and the second connection portion 40 is changed by changing the length of the movable portion 30, which is direct and clear, and has low control difficulty.

[0044] According to some embodiments of the present invention, 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 hingedly connected to the first connecting part 20, and a sliding cavity open toward the other end is formed in the outer rod 31; one end of the inner connecting rod 32 is telescopically accommodated 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 in the sliding cavity of the outer rod 31 to achieve the extension or shortening of the movable part 30. In this embodiment, the inner and outer rods 31 are used to facilitate the drive for the deformation of the movable part 30. In some embodiments, an air pump or the like can be used to drive the movable part 30 to extend and retract with air pressure.

[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 too small length, it may cause the two adjacent cone sections 10 to collide. In some cases, such as when the movable part 30 is extended too much, it may cause the inner connecting rod 32 and the outer connecting rod 31 to slip, making the structure unstable.

[0046] In view of the above-mentioned possible problems, according to some embodiments of the present invention, the outer rod 31 is provided with a first locking portion (not shown in the figure), and the inner connecting rod 32 is provided with a second locking portion (not shown in the figure), and the first locking portion cooperates with the second locking portion to limit the deformation range of the movable part 30. When the inner connecting rod 32 of this embodiment moves relative to the outer rod 31 to the minimum length and maximum length position allowed by the movable part 30, the first locking portion cooperates with the second locking portion to achieve locking, so as to prevent the inner connecting rod 32 from continuing to move relative to the outer rod 31, thereby ensuring the stability of the structure.

[0047] In some embodiments of the present invention, the first locking portion is configured as a locking groove provided on the inner peripheral wall of the outer rod 31, and the locking groove is provided with a first wall and a second wall respectively in the extension direction of the outer rod 31; the second locking portion is configured as a limit block provided on the outer peripheral wall of the inner connecting rod 32, and the limit block is received in the locking groove and abuts against the first wall or the second wall at the limit position. The limit block of this embodiment slides relative to the outer rod 31 in the locking groove along with the inner connecting rod 32, and when the limit 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 stops, so that the inner connecting rod 32 can only move relative to the outer rod 31 within the range limited by the first wall and the second wall, avoiding the occurrence of structural collision or slippage, so as to ensure the stability of the structure.

[0048] According to some embodiments of the present invention, the aircraft nose cone 100 further includes: a driving unit (not shown in the figure). The driving unit is configured to correspond to the movable part 30 in a one-to-one manner, and each driving unit is suitable for driving the corresponding movable part 30 to deform. This embodiment adopts a distributed drive, and the driving unit corresponds to the movable part 30 in a one-to-one manner, so that each movable part 30 can be independently driven by the driving unit to deform, so that the deformation amount of each movable part 30 can be distinguished, and the flexibility of the relative movement of adjacent cone sections 10 can be improved; at the same time, this distributed drive helps to reduce the load borne by each group of branches, improve the driving efficiency, reduce the requirements for the driving unit, and increase the service life of the branches; further, the distributed drive can also be designed with redundancy, and the overall reliability can be guaranteed when some drives fail, ensuring that the deformation of the nose cone 100 is not affected. In some embodiments, the driving unit can be configured to use air pressure to drive the movable part 30 to deform, or it can be integrally configured with the movable part 30 as an electrically driven telescopic cylinder, etc., to simplify the structure as much as possible on the basis of distributed drive.

[0049] According to some embodiments of the present invention, the cone section 10 is constructed as a centrally symmetrical structure, and the plurality of first connecting parts 20 and / or the plurality of second connecting parts 40 are symmetrically arranged about the symmetry center of the cone section 10. By designing that the cone section 10 and the first connecting parts 20 and the second connecting parts 40 are symmetrical about the center of the cone section 10, the head cone 100 of this embodiment is constructed as a centrally symmetrical structure as a whole, which can make the driving force of each movable part 30 on the cone section 10 more evenly distributed, and make the stability of the head cone 100 structure higher.

[0050] According to some embodiments of the present invention, the distance between the hinge connection point of the first connection part 20 and the center of the corresponding cone section 10 is r1, and the distance between the universal joint 50 connection point of the second connection part 40 and the center of the corresponding cone section 10 is r2, and the following condition is satisfied: r1=r2. In this embodiment, since the head cone 100 is a centrally symmetrical structure as a whole, the center lines of each cone section 10 coincide, and when the spacing between the hinge point, the universal joint 50 connection point and the corresponding cone section 10 is equal, the spacing between the centers of the two ends of the movable part 30 and the center lines of the two adjacent cone sections 10 is also equal. Therefore, when the head cone 100 is elongated or shortened, that is, when the two adjacent cone sections 10 are parallel to each other or move away from each other, the movable part 30 is parallel to the center line of the head cone 100, such as Figure 4 As shown, on the basis of uniform force on the cone segment 10, the force exerted by the movable part 30 on the cone segment 10 is concentrated in the moving direction of the cone segment 10, thereby reducing the radial force and effectively improving the 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 cone section 10 is α, and satisfies: 60°≤α≤120°. Since the first connecting parts 20 are arranged along the circumference of the cone section 10, the angle α between the two adjacent first connecting parts 20 and the center of the corresponding cone section 10 determines the number of branches between the two cone sections 10. When the angle between any two adjacent first connecting parts 20 and the center of the corresponding cone section 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 portion 40 and the movable portion 30 can be changed arbitrarily, at least three connecting points are required to achieve the relative fixation of adjacent cone segments 10 , so the number of the branch chains is at least three groups.

[0053] In some embodiments of the present invention, Figure 1-Figure 9 As shown, there are four groups of branches between adjacent cone sections 10. The branches include a first connecting portion 20, a movable portion 30, and a second connecting portion 40. The movable portion 30 is constructed as a telescopic structure including an inner connecting rod 32 and an outer connecting rod 31. The first connecting portion 20 is hinged to the outer connecting rod 31, and the second connecting portion 40 is connected to the inner connecting rod 32 through a universal joint 50. Therefore, the branch includes a rotating pair R, a moving pair P, and a universal joint U. When the four groups of RPU branches drive the adjacent cone sections 10 to move, only three groups of drives are required. The other group serves as a driven branch to maintain the stability of the movement and limit the freedom of the mechanism. At the same time, one group of branches can be used as a spare group. When any group of branches fails, it is guaranteed that there are three groups of branches that can normally drive the cone section 10 to move, thereby ensuring the stability and reliability of the head cone 100 variant. As shown Figure 4As shown, the four groups of branches are arranged in a central symmetric manner, and when driven together, the force on the cone section 10 can be more uniform and stable; further, when the adjacent cone sections 10 are parallel as the initial adjustment state, if the head cone 100 is extended or bent toward a certain active part 30, such as Fig. 9 As shown, the head cone 100 bends to the lower right, and only two RPU branches opposite to each other in the horizontal direction provide two sets of driving forces, and the other two passively deform to maintain the stability of movement and limit the freedom of the mechanism. This embodiment can reduce the number of drives, reduce the control difficulty, and improve the driving 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 be driven together to further disperse the stress points of the cone section 10 to make 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 weight of the nose cone 100, increase the load of each structure, and reduce the stability of the structure, which may do more harm than good.

[0056] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

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

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

[0059] In the description of the present invention, a first feature being “on” or “under” a second feature may include that the first and second features are directly in contact with each other, or may include that the first and second features are not in direct contact with each other but are in contact with each other via another feature therebetween.

[0060] In the description of the present invention, "above", "over" and "on" a first feature includes the first feature being directly above and obliquely above the second feature, or simply means that the first feature is horizontally higher than the second feature.

[0061] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "illustrative embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

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

Claims

1. An aircraft nose cone, characterized in that: include: Cone section, wherein a plurality of cone sections are provided, and a plurality of cone sections are sequentially connected to form the head cone; A first connection portion and a second connection portion are respectively provided on two adjacent cone sections, and the first connection portion and the second connection portion are configured as a plurality of portions which are spaced apart and correspond to each other in a circumferential direction of the cone section; A movable part, one end of which is hingedly connected to the first connecting part, and the other end of which is connected to the second connecting part via a universal joint; The movable portion is suitable for deformation to drive two adjacent cone sections to move relative to each other to drive the head cone to deform.

2. The aircraft nose cone according to claim 1, characterized in that: The universal joint comprises: a first universal joint fork, the first universal joint fork being arranged at one end of the movable part; a second universal joint fork, the second universal joint fork being arranged at the second connecting portion; A cross shaft is provided with a first shaft and a second shaft connected to each other, the first shaft is rotatably connected to the first universal joint fork, and the second shaft is rotatably connected to the second universal joint fork.

3. The aircraft nose cone according to claim 2, characterized in that: The movable portion is suitable for extending or shortening to change the distance between the first connecting portion and the second connecting portion.

4. The aircraft nose cone according to claim 3, characterized in that: The activities include: an outer sleeve rod, one end of which is hingedly connected to the first connecting portion, and a sliding cavity opened toward the other end is formed in the outer sleeve rod; An inner connecting rod, one end of which is telescopically accommodated in the sliding cavity, and the other end of which is provided with the second universal joint fork.

5. The aircraft nose cone according to claim 4, characterized in that: The outer rod is provided with a first locking portion, and the inner connecting rod is provided with a second locking portion, and the first locking portion cooperates with the second locking portion to limit the deformation range of the movable portion.

6. The aircraft nose cone according to claim 5, characterized in that: The first locking portion is configured as a locking groove provided on the inner peripheral wall of the outer rod, and the locking groove is provided with a first wall and a second wall in the extending direction of the outer rod respectively; The second locking portion is configured as a limit block disposed on the outer peripheral wall of the inner connecting rod. The limit block is received in the locking groove and abuts against the first wall or the second wall at an extreme position.

7. The aircraft nose cone according to claim 1, characterized in that: Also includes: The driving part is structured to be a plurality of driving parts arranged in a one-to-one correspondence with the movable parts, and each of the driving parts is suitable for driving the corresponding movable part to deform.

8. The aircraft nose cone according to claim 1, characterized in that: The cone section is configured as a centrally symmetrical structure, and the plurality of first connecting portions and / or the plurality of second connecting portions are symmetrically arranged about the symmetry center of the cone section.

9. The aircraft nose cone according to claim 8, characterized in that: The distance between the hinge connection point of the first connection part and the center of the corresponding cone section is r1, the distance between the universal joint connection point of the second connection part and the center of the corresponding cone section is r2, and the following condition is satisfied: r1=r2.

10. The aircraft nose cone according to claim 1, characterized in that: The included angle between any two adjacent first connecting parts and the center of the corresponding cone segment is α, and satisfies: 60°≤α≤120°.

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