A wing deployment mechanism, an aircraft and an aircraft combination

Abstract

The application discloses a wing unfolding mechanism, an aircraft and an aircraft combination, relates to the technical field of aircraft wings, and discloses the wing unfolding mechanism which comprises a driving element, the action end of the driving element can be moved along the direction of a vertical axis, the wing unfolding mechanism further comprises a front wing assembly, a main wing assembly and a tail wing assembly, the front wing assembly and the main wing assembly are used for rotating around a vertical axis under the driving of the action end of the driving element, and the tail wing assembly is used for rotating around a horizontal axis under the driving of the action end of the driving element. The wing unfolding mechanism, the aircraft and the aircraft combination can simultaneously act on multiple airfoils of the front wing assembly, the main wing assembly and the tail wing assembly, and effectively solve the problem that multiple airfoils are simultaneously unfolded.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft wings, in particular to a wing unfolding mechanism, an aircraft and an aircraft combination. BACKGROUND

[0002] The design difficulty of the wing unfolding mechanism lies in the synchronization, safety and symmetry of the unfolding. The wing unfolding mechanism of a general aircraft cannot simultaneously meet the above requirements. A simple pod does not even need a wing and is guided to land only by a parachute. Some aircraft have more stringent requirements for the deployment accuracy and the control of flight, and thus need a safe and synchronous unfolding mechanism. In order to meet the aerodynamic performance such as the lift-drag ratio of the aircraft during taxiing, the wings need to meet the symmetry after unfolding. Although some existing unfolding mechanisms can achieve the above functions, they can at most support the unfolding of two wing surfaces and cannot simultaneously unfold multiple wing surfaces. SUMMARY

[0003] The purpose of the present application is to provide a wing unfolding mechanism, an aircraft and an aircraft combination, which can simultaneously act on multiple wing surfaces of a front wing assembly, a main wing assembly and a tail wing assembly, effectively solving the problem of simultaneous unfolding of multiple wing surfaces.

[0004] To achieve the above purpose, the present application provides a wing unfolding mechanism, which comprises a driving member, the action end of the driving member being movable in the direction of a vertical axis, the wing unfolding mechanism further comprising a front wing assembly, a main wing assembly and a tail wing assembly, the front wing assembly and the main wing assembly being used to rotate around the vertical axis under the driving of the action end of the driving member, and the tail wing assembly being used to rotate around a horizontal axis under the driving of the action end of the driving member.

[0005] In some embodiments, the wing unfolding mechanism further comprises a rotating shaft assembly, the rotating shaft assembly being connected with the action end of the driving member, the rotating shaft assembly being used to rotate around the vertical axis under the driving of the action end of the driving member, and the rotating shaft assembly being further connected with the main wing assembly and the tail wing assembly to drive the main wing assembly to rotate around the vertical axis and the tail wing assembly to rotate around the horizontal axis.

[0006] In some embodiments, the front wing assembly comprises a first front wing and a second front wing, the rotation axes of the first front wing and the second front wing being spaced apart and parallel to the vertical axis, the first front wing being connected with the action end of the driving member through a first connecting rod, the first front wing being used to rotate forward around the rotation axis of the first front wing under the driving of the action end of the driving member, and the second front wing being connected with the action end of the driving member through a second connecting rod, the second front wing being used to rotate reversely around the rotation axis of the second front wing under the driving of the action end of the driving member.

[0007] In some embodiments, the rotation shaft assembly comprises a first rotation shaft member and a second rotation shaft member, rotation axes of the first rotation shaft member and the second rotation shaft member are arranged in coincidence with the vertical axis, the first rotation shaft member is connected to the driving member action end through a third connecting rod, the second rotation shaft member is connected to the driving member action end through a fourth connecting rod, the first rotation shaft member is used to rotate in a positive direction around the vertical axis under the driving of the driving member action end, and the second rotation shaft member is used to rotate in a reverse direction around the vertical axis under the driving of the driving member action end.

[0008] The main wing assembly comprises a first main wing and a second main wing, the first main wing is connected to the first rotation shaft member, the first main wing is used to rotate in a positive direction around the vertical axis with the first rotation shaft member under the driving of the driving member action end, the second main wing is connected to the second rotation shaft member, and the second main wing is used to rotate in a reverse direction around the vertical axis with the second rotation shaft member under the driving of the driving member action end.

[0009] In some embodiments, the tail wing assembly comprises a first tail wing, a second tail wing and a tail wing rotation shaft member, the first tail wing and the second tail wing are connected to the tail wing rotation shaft member, a rotation axis of the tail wing rotation shaft member is arranged in coincidence with the horizontal axis, the tail wing rotation shaft member is connected to the first rotation shaft member or the second rotation shaft member through a fifth connecting rod, and the tail wing rotation shaft member is used to rotate around the horizontal axis under the driving of the driving member action end and the action of the first rotation shaft member or the second rotation shaft member.

[0010] In some embodiments, the second rotation shaft member is nested in the first rotation shaft member, the first rotation shaft member is provided with a first mounting seat connected to the first main wing, and the second rotation shaft member is provided with a second mounting seat connected to the second main wing.

[0011] In some embodiments, the first rotation shaft member comprises a first rotation shaft sub-member and a second rotation shaft sub-member arranged in a spaced manner in the direction of the vertical axis, the first rotation shaft sub-member is connected to the driving member action end through the third connecting rod, the first rotation shaft sub-member and the second rotation shaft sub-member are connected through a torsion arm, the second rotation shaft member comprises a third rotation shaft sub-member and a fourth rotation shaft sub-member, the third rotation shaft sub-member is nested in the first rotation shaft sub-member, the third rotation shaft sub-member is connected to the driving member action end through the fourth connecting rod, the fourth rotation shaft sub-member is nested in the third rotation shaft sub-member and the second rotation shaft sub-member, the fourth rotation shaft sub-member is connected to the third rotation shaft sub-member through a transmission member, and the fourth rotation shaft sub-member is further connected to a first pull rod, the first pull rod is used to be connected to a fuselage to realize that the fourth rotation shaft sub-member rotates in a reverse direction around the vertical axis and moves along the vertical axis under the driving of the driving member action end, so that the first main wing and the second main wing are located at the same position on the vertical axis.

[0012] In some embodiments, the driving member is a gas spring, which includes a gas spring piston rod and a gas spring outer cylinder sleeved with the gas spring piston rod, the gas spring piston rod is used to be fixed on the fuselage, and the gas spring outer cylinder drives the front wing assembly, the main wing assembly and the tail wing assembly to rotate as the action end of the driving member.

[0013] The application further provides a flying vehicle, which comprises a fuselage and the wing unfolding mechanism.

[0014] The application further provides a flying vehicle combination, which comprises a mother vehicle and the flying vehicle, the flying vehicle is hung on the mother vehicle, and the mother vehicle is provided with a locking device for maintaining the wing unfolding mechanism of the flying vehicle in a folded state.

[0015] With respect to the background art, the wing unfolding mechanism provided by the application comprises a driving member, the action end of the driving member can move along the direction of the vertical axis, the wing unfolding mechanism further comprises a front wing assembly, a main wing assembly and a tail wing assembly, the front wing assembly and the main wing assembly are used to rotate around the vertical axis under the driving of the action end of the driving member, and the tail wing assembly is used to rotate around the horizontal axis under the driving of the action end of the driving member.

[0016] In the use of the wing unfolding mechanism, the action end of the driving member is moved along the direction of the vertical axis, and simultaneously drives the front wing assembly, the main wing assembly and the tail wing assembly to act, so that the front wing assembly and the main wing assembly rotate around the vertical axis, and the tail wing assembly rotates around the horizontal axis, thereby realizing the unfolding of the front wing assembly, the main wing assembly and the tail wing assembly. The wing unfolding mechanism can simultaneously act on multiple airfoils of the front wing assembly, the main wing assembly and the tail wing assembly, and effectively solves the problem of simultaneous unfolding of multiple airfoils. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description are only embodiments of the application, and for those skilled in the art, other drawings can also be obtained without creative labor based on the provided drawings.

[0018] Figure 1 The structural schematic diagram of the wing unfolding mechanism provided by the embodiments of the application is shown in the figure;

[0019] Figure 2 The structural schematic diagram of the wing unfolding mechanism provided by the embodiments of the application is shown in the figure; Figure 1 The structural schematic diagram of the wing unfolding mechanism provided by the embodiments of the application is shown in the figure;

[0020] Figure 3A partial view of a wing unfolding mechanism according to another embodiment of the present application is shown in a first perspective view;

[0021] Figure 4 A partial view of a wing unfolding mechanism according to another embodiment of the present application is shown in a second perspective view;

[0022] Figure 5 A partial view of a wing unfolding mechanism according to another embodiment of the present application is shown in a third perspective view.

[0023] Wherein:

[0024] 1 - driving member, 11 - gas spring piston rod, 12 - gas spring outer cylinder,

[0025] 2 - front wing assembly, 21 - first front wing, 22 - first connecting rod, 23 - second front wing, 24 - second connecting rod,

[0026] 3 - main wing assembly, 31 - first main wing, 32 - second main wing,

[0027] 4 - tail wing assembly, 41 - first tail wing, 42 - second tail wing, 43 - tail wing rotating shaft member, 44 - fifth connecting rod,

[0028] 5 - rotating shaft assembly, 51 - first rotating shaft member, 511 - first rotating shaft sub-member, 512 - second rotating shaft sub-member, 513 - torsion arm, 52 - third connecting rod, 53 - second rotating shaft member, 531 - third rotating shaft sub-member, 532 - fourth rotating shaft sub-member, 533 - transmission member, 534 - first pull rod, 535 - connecting plate, 54 - fourth connecting rod, 55 - first mounting seat, 56 - second mounting seat. DETAILED DESCRIPTION

[0029] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0030] In order for those skilled in the art to better understand the present application, the present application will be further described in detail below with reference to the drawings and specific embodiments.

[0031] At present, the glide air supply by air-drop pod is a common air-drop supply method at home and abroad. When the air-drop pod is hung on the mother plane, the wings are in a folded state, and the wings are unfolded after being dropped. The wing unfolding of the air-drop pod affects the aerodynamic performance of the pod and the safety of the mother plane, so the unfolding mechanism is particularly important.

[0032] Traditional wing deployment mechanisms primarily utilize rocker arms and telescopic mechanisms. However, these mechanisms have several drawbacks. Because the left and right rocker arms remain on the same horizontal plane throughout the folded state, the folded wing width can exceed the fuselage width when the wing chord is large. This results in significant space requirements during storage, transport, and flight. Another folding mechanism suffers from similar issues and requires specialized air supply equipment, increasing its complexity, space consumption, weight, and cost. Furthermore, traditional deployment mechanisms only involve the main wing, i.e., the deployment of two wing surfaces, and cannot simultaneously deploy all six wing surfaces (two main wings, two canards, and two vertical stabilizers).

[0033] To address the aforementioned technical problems, this application provides a wing deployment mechanism, please refer to... Figure 1 and Figure 2 , Figure 1 This is a schematic diagram of the wing deployment mechanism provided in an embodiment of this application. Figure 2 for Figure 1 A schematic diagram of the central axis assembly.

[0034] exist Figure 1 The illustrated coordinate system includes the X-axis, Y-axis, and Z-axis; in some cases, the X-axis is horizontal, corresponding to the horizontal axis; the Y-axis is vertical, corresponding to the vertical axis; and the Z-axis is vertical, corresponding to the vertical axis.

[0035] In one specific embodiment, the wing deployment mechanism mainly includes a drive member 1, the actuating end of the drive member 1 can move along the direction of the vertical axis. The wing deployment mechanism also includes a canard assembly 2, a main wing assembly 3 and a tail assembly 4. The canard assembly 2 and the main wing assembly 3 are used to rotate around the vertical axis under the drive of the actuating end of the drive member 1, and the tail assembly 4, i.e., the vertical tail, is used to rotate around the horizontal axis under the drive of the actuating end of the drive member 1.

[0036] During the operation of this wing deployment mechanism, the moving end of the drive component 1 moves along the vertical axis, simultaneously driving the canard assembly 2, main wing assembly 3, and tail assembly 4 to rotate. This causes the canard assembly 2 and main wing assembly 3 to rotate around the vertical axis, and the tail assembly 4 to rotate around the horizontal axis, thereby achieving the deployment of the canard assembly 2, main wing assembly 3, and tail assembly 4. This wing deployment mechanism can simultaneously actuate multiple wing surfaces of the canard assembly 2, main wing assembly 3, and tail assembly 4, effectively solving the problem of simultaneous deployment of multiple wing surfaces.

[0037] In a specific embodiment, the wing unfolding mechanism further comprises a rotating shaft assembly 5, which is connected with the driving member 1 and rotates around a vertical axis under the driving of the driving member 1, and is connected with the main wing assembly 3 and the tail wing assembly 4 to drive the main wing assembly 3 to rotate around a vertical axis and the tail wing assembly 4 to rotate around a horizontal axis.

[0038] Please continue to refer to Figure 1 , Figure 1 The wing unfolding mechanism in the above-mentioned specific embodiment is in a folded state of the wing, i.e., the wing unfolding mechanism has not unfolded the wing. As shown in Figure 1 , the front wing assembly 2 comprises a first front wing 21 and a second front wing 23, and the rotating axes of the first front wing 21 and the second front wing 23 are arranged in parallel with the vertical axis and are spaced apart, the first front wing 21 is connected with the driving member 1 through a first connecting rod 22 and rotates forward around the rotating axis of the first front wing 21 under the driving of the driving member 1, and the second front wing 23 is connected with the driving member 1 through a second connecting rod 24 and rotates reversely around the rotating axis of the second front wing 23 under the driving of the driving member 1.

[0039] In the embodiment, the first front wing 21 and the second front wing 23 are symmetrically arranged on the horizontal two sides of the driving member 1, and the first front wing 21 is equivalent to a left front wing and the second front wing 23 is equivalent to a right front wing. The first front wing 21 and the second front wing 23 are provided with rotating shafts for rotation, and the rotating shafts of the front wings are connected with the fuselage, and the first front wing 21 and the second front wing 23 rotate around the axes in the reference system of the fuselage. The first connecting rod 22 and the second connecting rod 24 are used to realize force transmission, and the connection relationship thereof with the components can be flexibly set according to actual needs, such as the rotating connection of the first connecting rod 22 with the first front wing 21 and the driving member 1, which is an adaptive setting and will not be described herein.

[0040] It should be noted that the rotating directions of the first front wing 21 and the second front wing 23 are opposite. For example, in the folded state of the first front wing 21 and the second front wing 23, the first front wing 21 and the second front wing 23 are placed side by side on the horizontal two sides of the driving member 1; when the first front wing 21 and the second front wing 23 are unfolded, the first front wing 21 rotates clockwise under the driving of the driving member 1 and the action of the rotating shaft thereof, and at this time, the first front wing 21 is unfolded clockwise on the left side of the central axis of the fuselage, and the second front wing 23 rotates counterclockwise, and at this time, the second front wing 23 is unfolded counterclockwise on the right side of the central axis of the fuselage, so as to realize the unfolding of the first front wing 21 and the second front wing 23.

[0041] Similarly, the main wing assembly 3 comprises a first main wing 31 and a second main wing 32, which are also rotated in opposite directions to be unfolded under the driving of the action end of the driving member 1.

[0042] In a specific embodiment, please continue to refer to Figure 1 , the rotation shaft assembly 5 comprises a first rotation shaft member 51 and a second rotation shaft member 53, the rotation axes of the first rotation shaft member 51 and the second rotation shaft member 53 are arranged to coincide with the vertical axis, the first rotation shaft member 51 is connected with the action end of the driving member 1 through a third connecting rod 52, the second rotation shaft member 53 is connected with the action end of the driving member 1 through a fourth connecting rod 54, the first rotation shaft member 51 is used to rotate forward around the vertical axis under the driving of the action end of the driving member 1, and the second rotation shaft member 53 is used to rotate reversely around the vertical axis under the driving of the action end of the driving member 1.

[0043] Correspondingly, the first main wing 31 is connected with the first rotation shaft member 51, and the first main wing 31 is used to rotate forward around the vertical axis with the first rotation shaft member 51 under the driving of the action end of the driving member 1, the second main wing 32 is connected with the second rotation shaft member 53, and the second main wing 32 is used to rotate reversely around the vertical axis with the second rotation shaft member 53 under the driving of the action end of the driving member 1.

[0044] In the embodiment, the first main wing 31 and the second main wing 32 are located below the first front wing 21 and the second front wing 23, the first main wing 31 is located on the right side of the fuselage central axis after being unfolded with the second front wing 23, and the first main wing 31 is equivalent to a right main wing, the second main wing 32 is located on the left side of the fuselage central axis after being unfolded with the first front wing 21, and the second main wing 32 is equivalent to a left main wing. For example, in the folded state of the first main wing 31 and the second main wing 32, the first main wing 31 and the second main wing 32 are located on the central axis of the fuselage, when the first main wing 31 and the second main wing 32 are unfolded, the first main wing 31 is rotated clockwise to the right side of the fuselage central axis under the driving of the action end of the driving member 1 and the action of its rotation shaft, and the first main wing 31 is rotated counterclockwise to the left side of the fuselage central axis under the driving of the action end of the driving member 1 and the action of its rotation shaft.

[0045] In some cases, the wing unfolding mechanism is installed on the fuselage when applied, the first rotation shaft member 51 in the rotation shaft assembly 5 is connected with the fuselage, and the first rotation shaft member 51 and the second rotation shaft member 53 are carried by the fuselage, in the reference system of the fuselage, the first rotation shaft member 51 and the second rotation shaft member 53 rotate around the axis. The functions of the third connecting rod 52 and the fourth connecting rod 54 are to realize force transmission, and in their connection relationship with the components, they should be flexibly set according to actual needs, such as the rotary connection between the third connecting rod 52 and the first rotation shaft member 51 and the action end of the driving member 1, which belongs to adaptive setting, and will not be described here.

[0046] It should be noted that the first connecting rod 22 and the second connecting rod 24 in the above-mentioned front wing assembly 2 should be symmetrically arranged on the horizontal two sides of the driving member 1, and similarly, the third connecting rod 52 and the fourth connecting rod 54 in the rotation shaft assembly 5 should also be symmetrically arranged on the horizontal two sides of the driving member 1.

[0047] Please continue to refer to Figure 1 In some embodiments, the tail wing assembly 4 includes a first tail wing 41, a second tail wing 42, and a tail wing rotation shaft member 43, the first tail wing 41 and the second tail wing 42 are connected with the tail wing rotation shaft member 43, the rotation axis of the tail wing rotation shaft member 43 coincides with the horizontal axis, the tail wing rotation shaft member 43 is connected with the first rotation shaft member 51 or the second rotation shaft member 53 through a fifth connecting rod 44, and the tail wing rotation shaft member 43 is used to rotate around the horizontal axis under the driving of the action end of the driving member 1 and the action of the first rotation shaft member 51 or the second rotation shaft member 53.

[0048] In the present embodiment, unlike the first front wing 21 and the second front wing 23, and the first main wing 31 and the second main wing 32, the first tail wing 41 and the second tail wing 42 are synchronously and synchronously rotated when they are unfolded. For example, the first tail wing 41 rotates on the left side of the fuselage central axis under the driving of the action end of the driving member 1 and the action of the tail wing rotation shaft member 43, and the second tail wing 42 rotates on the right side of the fuselage central axis under the driving of the action end of the driving member 1 and the action of the tail wing rotation shaft member 43. The function of the fifth connecting rod 44 is to realize force transmission, and its connection relationship with the components should be flexibly set according to actual needs, such as the fifth connecting rod 44 being rotatably connected with the first rotation shaft member 51 and the tail wing rotation shaft member 43, which belongs to adaptive setting and will not be described here. In addition, it can also be the fifth connecting rod 44 connected with the second rotation shaft member 53, which also belongs to the scope of the present embodiment.

[0049] As a preferred, when the first tail wing 41 and the second tail wing 42 are in a folded state, the first tail wing 41 and the second tail wing 42 are rotated to a horizontal plane similar to the plane where the front wing assembly 2 and the main wing assembly 3 are located, and then rotated to a position similar to vertical when the first tail wing 41 and the second tail wing 42 are unfolded. In this way, the occupied space of the wing unfolding mechanism in the fuselage can be saved.

[0050] Please continue to refer to Figure 2 In some embodiments, the second rotation shaft member 53 is nested in the first rotation shaft member 51, and the first rotation shaft member 51 is provided with a first mounting seat 55 connected with the first main wing 31, so that the action of the first main wing 31, i.e. the right main wing, is realized by the first rotation shaft member 51 and the fourth connecting rod 54, and the second rotation shaft member 53 is provided with a second mounting seat 56 connected with the second main wing 32, so that the action of the second main wing 32, i.e. the left main wing, is realized by the second rotation shaft member 53 and the third connecting rod 52.

[0051] Please referFigures 3 to 5 wherein, Figure 3 a partial view of a wing unfolding mechanism according to another embodiment of the present application from a first perspective, Figure 4 a partial view of a wing unfolding mechanism according to another embodiment of the present application from a second perspective, Figure 5 a partial view of a wing unfolding mechanism according to another embodiment of the present application from a third perspective.

[0052] It should be noted that, Figures 3 to 5 as another embodiment of the present application, which is slightly different in structure from Figure 1 and Figure 2 embodiments, but all belong to the scope of the technical solutions provided by the present application.

[0053] In a specific embodiment, the unfolding of the main wing is driven by the rotation of two nested sleeves. The inner sleeve can move vertically. When folding, the inner sleeve moves downward to provide space for the two wings to fold under the aircraft. When unfolding, the inner sleeve moves upward to ensure that the left and right main wings are in the same horizontal plane after unfolding, ensuring symmetry after unfolding. This symmetrical unfolding method avoids the tendency of the wings to slide or roll due to uneven aerodynamic forces after unfolding.

[0054] It should be noted that the specific structure of the two sleeves, i.e., the first rotating shaft member 51 and the second rotating shaft member 53, is not limited in this embodiment. They can be separate components or combined components, and should belong to the scope of this embodiment. For example, when using separate components, a threaded form can be used to achieve both rotation and movement.

[0055] Specifically, the first rotating shaft member 51 includes a first rotating shaft sub-member 511 and a second rotating shaft sub-member 512 arranged vertically. The first rotating shaft sub-member 511 is connected to the driving member 1 through a third connecting rod 52. At this time, the first rotating shaft sub-member 511 is driven to rotate by the driving member 1. The first rotating shaft sub-member 511 and the second rotating shaft sub-member 512 are connected by a torsion arm 513. At this time, the first rotating shaft sub-member 511 and the second rotating shaft sub-member 512 rotate synchronously and have no movement along the vertical axis. The first mounting seat 55 connected to the first main wing 31 is arranged at the end of the second rotating shaft sub-member 512. The first main wing 31, i.e., the right main wing, is driven by the second rotating shaft sub-member 512.

[0056] The second rotating shaft member 53 comprises a third rotating shaft sub-member 531 and a fourth rotating shaft sub-member 532. The third rotating shaft sub-member 531 is nested in the first rotating shaft sub-member 511 and is connected to the driving member 1 through a fourth connecting rod 54. At this time, the third rotating shaft sub-member 531 rotates in the opposite direction of the first rotating shaft sub-member 511 under the driving of the driving member 1. The fourth rotating shaft sub-member 532 is nested in the third rotating shaft sub-member 531 and the second rotating shaft sub-member 512 and is connected to the third rotating shaft sub-member 531 through a transmission member 533. At this time, the fourth rotating shaft sub-member 532 rotates together with the third rotating shaft sub-member 531 under the driving of the transmission member 533. The fourth rotating shaft sub-member 532 is also connected to a first pull rod 534, which is used to be connected to the fuselage. The first pull rod 534 is used to drive the fourth rotating shaft sub-member 532 to move along the vertical axis relative to the third rotating shaft sub-member 531 when the fourth rotating shaft sub-member 532 rotates, so that the fourth rotating shaft sub-member 532 rotates in the opposite direction around the vertical axis and moves along the vertical axis, so that the first main wing 31 and the second main wing 32 are located at the same position on the vertical axis. A second mounting seat 56 connected to the second main wing 32 is arranged at the end of the fourth rotating shaft sub-member 532, and the end of the fourth rotating shaft sub-member 532 passes through the end of the second rotating shaft sub-member 512. The second main wing 32, i.e. the left main wing, is driven by the fourth rotating shaft sub-member 532.

[0057] It should be noted that the transmission member 533 is different from the torsion arm 513 described above. The torsion arm 513 is only used to synchronize the rotation of the first rotating shaft sub-member 511 and the second rotating shaft sub-member 512 without moving along the vertical axis. The transmission member 533 can synchronize the rotation of the third rotating shaft sub-member 531 and the fourth rotating shaft sub-member 532 and can also move the fourth rotating shaft sub-member 532 along the vertical axis relative to the third rotating shaft sub-member 531.

[0058] Further, a connecting plate 535 is arranged on the fourth rotating shaft sub-member 532. The connecting plate 535 is connected to the first pull rod 534, and the first pull rod 534 is connected to the fuselage. In addition, the connecting plate 535 is connected to the transmission member 533, and the transmission member 533 is connected to the third rotating shaft sub-member 531.

[0059] When the driving member 1 is actuated, for the first rotating shaft member 51, the third connecting rod 52 drives the first rotating shaft sub-member 511 to move, under the action of the torsion arm 513, to make the first rotating shaft sub-member 511 and the second rotating shaft sub-member 512 rotate forward around the vertical axis, and further drive the first main wing 31 to rotate forward around the vertical axis, at this time, the first main wing 31 has no movement along the vertical axis; for the second rotating shaft member 53, the fourth connecting rod 54 drives the third rotating shaft sub-member 531 to move, to make the third rotating shaft sub-member 531 rotate reversely around the vertical axis, under the action of the transmission member 533, to make the fourth rotating shaft sub-member 532 rotate reversely around the vertical axis, and further drive the first main wing 31 to rotate reversely around the vertical axis, at the same time, the first pull rod 534 is connected between the fuselage and the connecting plate 535, when the connecting plate 535 rotates with the fourth rotating shaft sub-member 532, the connecting plate 535 moves along the vertical axis under the restriction of the length of the first pull rod 534, so as to make the fourth rotating shaft sub-member 532 move along the vertical axis, and further make the second main wing 32 move along the vertical axis while rotating reversely, which is equivalent to that the second main wing 32 moves upward from the lower side of the first main wing 31 when the second main wing 32 is unfolded, when the first main wing 31 and the second main wing 32 are unfolded, the first main wing 31 and the second main wing 32 are located at the same position on the vertical axis; conversely, when the first main wing 31 and the second main wing 32 are folded, the first main wing 31 and the second main wing 32 are staggered to be folded along the vertical axis.

[0060] In a specific embodiment, the driving member 1 is a gas spring, which has the advantages of simplicity and cost-effectiveness as the driving source of the unfolding mechanism, and has the characteristic of time delay, so that the unfolding time of the gas spring driving mechanism is controllable, ensuring that the delivery object is unfolded after a certain time after leaving the mother machine, and ensuring the separation safety. In addition, by adjusting the opening degree of the valve in the gas spring or selecting different types of gas springs, the complete unfolding time of the wing surface can be controlled to achieve time delay and ensure the separation safety.

[0061] In the embodiment, the gas spring includes a gas spring piston rod 11 and a gas spring outer cylinder 12 sleeving the gas spring piston rod 11, the gas spring piston rod 11 is used to be fixed to the fuselage, and the gas spring outer cylinder 12 drives the front wing assembly 2, the main wing assembly 3 and the tail wing assembly 4 to rotate as the action end of the driving member 1.

[0062] In summary, in view of the shortcomings of the existing wing unfolding mechanism, the present application comprehensively considers the characteristics that the unfolding mechanism needs to meet, and is designed. By analyzing the characteristics of the existing wing unfolding mechanism, and combining the requirements of the separation safety and the delivery accuracy of a certain type of aircraft, the present application proposes a mechanism that can delay and ensure the simultaneous unfolding of the front wing, the main wing and the vertical tail. This new type of unfolding mechanism can better solve some problems existing in the existing unfolding mechanism, and in addition, the mechanism can also ensure the symmetry of the unfolded wing, and ensure that the aerodynamic performance is not lost.

[0063] The application further provides an aircraft, comprising a fuselage and the wing unfolding mechanism.

[0064] The aircraft should have all the beneficial effects of the wing unfolding mechanism described above, which will not be repeated here.

[0065] The application further provides an aircraft combination, comprising a mother aircraft and the aircraft, the aircraft being mounted on the mother aircraft, and the mother aircraft being provided with a locking device for maintaining the wing unfolding mechanism of the aircraft in a folded state.

[0066] The aircraft combination should have all the beneficial effects of the aircraft and the wing unfolding mechanism, which will not be repeated here.

[0067] In terms of synchronization design, considering that the components that need to be driven by the pod include the left and right front wings, the left and right rear wings, and the left and right vertical tails, six wing surfaces are driven by a single air spring, the left and right front wings are connected to the outer cylinder of the air spring through two connecting rods, the left and right rear wings are connected to the outer cylinder of the air spring through connecting rods after the rotation shafts pass through the bottom of the fuselage to the top of the fuselage, and the left and right vertical tails are coaxial with the rotation shafts and have a rocker arm at the rotation shaft of the vertical tail, which is connected to the rotation shaft of the right main wing surface through a connecting rod. Therefore, the driving of the six wing surfaces is realized through the unique movement of the air spring outer cylinder, the air spring piston rod end is fixed on the fuselage, the air spring outer cylinder drives the six wing surfaces, and the radial displacement of the air spring is limited through the middle through hole of the lifting lug. As long as there is no lateral displacement of the air spring, the six wing surfaces of the whole machine can realize mechanical synchronization of the mechanism movement.

[0068] In terms of safety design, the time for the wings to unfold in place can be controlled by controlling the reset time of the air spring. At the same time, in order to avoid accidental unfolding during the folding process, the whole aircraft is designed with three levels of locking devices to cooperate with the unfolding mechanism to meet the safety of separation during the aircraft launching process.

[0069] In terms of symmetry design, the two main wings are lifting type, and in the unfolded state, the left and right wings are height-symmetric, and in the folded state, the left and right wings are staggered in height and folded into the fuselage envelope. The right wing rotation shaft is disconnected into two parts, and the middle part is connected through a torsion arm to transmit torque and drive the wing rotation. The left wing rotation shaft is increased with a rocker arm, which is connected to the fuselage through a pull rod. During the rotation of the left wing, the pull rod swings to generate a height difference, which drives the left wing to move in the height direction, so that the left and right wings are horizontally symmetric in the unfolded state and are staggered in height in the folded state.

[0070] In the unfolding mechanism process, the performance is evaluated by fully utilizing simulation means such as structural design and strength design, so as to design a delay synchronous unfolding mechanism that meets the requirements. At the same time, considering that the aircraft is usually launched at high altitude, the low-temperature condition is considered, and therefore, the key components such as the air spring are subjected to multiple normal and low-temperature test verifications to ensure the reliability of the mechanism.

[0071] In practical applications, the locking and unfolding process of the aircraft wing is divided into three steps, which are further described below with examples.

[0072] Airborne mounting (wing folding) state: the aircraft is suspended on the mother plane through the suspension rack, the vertical direction is limited through the lifting lug, and the lateral direction is limited through the clamping mechanism of the suspension rack and the locking pin on the main wing of the aircraft to clamp and limit the lateral swing of the hanging cabin. At this time, the six wing surfaces are in a folded state, and the front wing of the aircraft is limited by a mechanical limiting device to prevent the unfolding mechanism from being mis-unfolded.

[0073] Unfolding state after being dropped: after the aircraft is dropped, the clamping mechanism on the suspension rack loses the locking function of the rear wing of the hanging cabin, but at this time the main wing surface is still mechanically locked, the suspension rack is dropped until it is completely and safely separated from the plane, and the flight control gives a command to swing the aileron to unlock the mechanical lock installed on the side of the fuselage. The lower, the entire six wings lose mechanical limiting, and begin to unfold under the action of the gas spring.

[0074] Flight state after the mechanism is completely unfolded: after unfolding, the mechanical stop limiting mechanism continues to move and is kept in the unfolded state under the action of the gas spring force, and at the same time, after the wing is unfolded, a spring pin brake is set, and the spring pin shaft automatically extends and inserts into the rocker arm hole to stop.

[0075] Therefore, the present application proposes an unfolding mechanism that can delay and synchronously unfold the wings, which can make up for some shortcomings of traditional unfolding mechanisms and ensure the symmetry behind the wings and the good aerodynamic performance of the aircraft.

[0076] It should be noted that many components mentioned in the present application are general standard components or components known to those skilled in the art, and their structure and principle can be known by technical personnel through technical manuals or through conventional experimental methods.

[0077] It should be noted that in the present specification, relationship terms such as first and second are only used to distinguish one entity from another entity, and do not necessarily require or imply any actual relationship or order between the entities.

[0078] The wing unfolding mechanism, aircraft and aircraft combination provided by the present application are described in detail above. The principles and implementation modes of the present application are described in this paper by applying specific examples, and the above example description is only used to help understand the method and core idea of the present application. It should be pointed out that for ordinary skilled personnel in the technical field, some improvements and modifications can be made to the present application without departing from the principles of the present application, and these improvements and modifications also fall within the protection scope of the claims of the present application.

Claims

1. A wing deployment mechanism, characterized in that, The wing deployment mechanism includes a drive member, the actuating end of which can move along the vertical axis. The wing deployment mechanism also includes a canard assembly, a main wing assembly, and a tail assembly. The canard assembly and the main wing assembly are used to rotate around the vertical axis under the drive of the actuating end of the drive member, and the tail assembly is used to rotate around the horizontal axis under the drive of the actuating end of the drive member. The wing deployment mechanism also includes a pivot assembly, which is connected to the actuating end of the drive component. The pivot assembly is used to rotate around a vertical axis under the drive of the actuating end of the drive component. The pivot assembly is also connected to the main wing assembly and the tail assembly to drive the main wing assembly to rotate around a vertical axis and the tail assembly to rotate around a horizontal axis. The front wing assembly includes a first front wing and a second front wing. The rotation axes of the first front wing and the second front wing are spaced apart and are both parallel to the vertical axis. The first front wing is connected to the actuating end of the drive member through a first link. The first front wing is used to rotate in the forward direction around the rotation axis of the first front wing under the drive of the actuating end of the drive member. The second front wing is connected to the actuating end of the drive member through a second link. The second front wing is used to rotate in the reverse direction around the rotation axis of the second front wing under the drive of the actuating end of the drive member. The rotating shaft assembly includes a first rotating shaft and a second rotating shaft. The rotation axes of the first rotating shaft and the second rotating shaft are coincident and coincident with the vertical axis. The first rotating shaft is connected to the actuating end of the driving member through a third link, and the second rotating shaft is connected to the actuating end of the driving member through a fourth link. The first rotating shaft is used to rotate in the forward direction around the vertical axis under the drive of the actuating end of the driving member, and the second rotating shaft is used to rotate in the reverse direction around the vertical axis under the drive of the actuating end of the driving member. The main wing assembly includes a first main wing and a second main wing. The first main wing is connected to the first rotating shaft and is used to rotate in the forward direction around the vertical axis under the drive of the actuating end of the drive member. The second main wing is connected to the second rotating shaft and is used to rotate in the reverse direction around the vertical axis under the drive of the actuating end of the drive member.

2. The wing deployment mechanism according to claim 1, characterized in that, The tail fin assembly includes a first tail fin, a second tail fin, and a tail fin pivot. The first tail fin and the second tail fin are connected to the tail fin pivot. The rotation axis of the tail fin pivot coincides with the horizontal axis. The tail fin pivot is connected to the first pivot or the second pivot via a fifth link. The tail fin pivot is used to rotate around the horizontal axis under the action of the first pivot or the second pivot under the drive of the actuating end of the drive member.

3. The wing deployment mechanism according to claim 1, characterized in that, The second pivot member is nested within the first pivot member, and the first pivot member is provided with a first mounting seat connected to the first main wing, and the second pivot member is provided with a second mounting seat connected to the second main wing.

4. The wing deployment mechanism according to claim 3, characterized in that, The first pivot component includes a first pivot segment and a second pivot segment spaced apart along the vertical axis. The first pivot segment is connected to the actuating end of the drive component via the third link, and the first pivot segment and the second pivot segment are connected by a torque arm. The second pivot component includes a third pivot segment and a fourth pivot segment. The third pivot segment is nested within the first pivot segment and is connected to the actuating end of the drive component via the fourth link. The fourth pivot segment is nested within the third pivot segment and the second pivot segment, and is connected to the third pivot segment via a transmission component. The fourth pivot segment is also connected to a first pull rod, which is used to connect to the fuselage. This allows the fourth pivot segment to rotate in the opposite direction around the vertical axis and move along the vertical axis under the drive of the actuating end of the drive component, so that the first main wing and the second main wing are located at the same position on the vertical axis.

5. The wing deployment mechanism according to any one of claims 1 to 4, characterized in that, The driving component is a gas spring, which includes a gas spring piston rod and a gas spring outer cylinder that houses the gas spring piston rod. The gas spring piston rod is used to fix the fuselage, and the gas spring outer cylinder serves as the actuating end of the driving component to drive the forewing assembly, the main wing assembly, and the tail assembly to rotate.

6. An aircraft, characterized in that, It includes a fuselage and a wing deployment mechanism as described in any one of claims 1 to 5, wherein the wing deployment mechanism is mounted on the fuselage.

7. An aircraft assembly, characterized in that, It includes a mother aircraft and an aircraft as described in claim 6, the aircraft being mounted on the mother aircraft, the mother aircraft being provided with a locking device for maintaining the wing deployment mechanism of the aircraft in a folded state.

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