CN117262202A - Wing unfolding mechanism, aircraft and aircraft combination - Google Patents

Abstract

The application discloses a wing unfolding mechanism, an aircraft and an aircraft combination, and relates to the technical field of aircraft wings; the wing unfolding mechanism comprises a driving piece, the action end of the driving piece 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 for rotating around the vertical axis under the driving of the action end of the driving piece, and the tail wing assembly is used for rotating around the horizontal axis under the driving of the action end of the driving piece. The wing unfolding mechanism, the aircraft and the aircraft combination can simultaneously actuate a plurality of wing surfaces of the front wing assembly, the main wing assembly and the tail wing assembly, and effectively solve the problem of simultaneous unfolding of the plurality of wing surfaces.

Description

Wing unfolding mechanism, aircraft and aircraft combination

Technical Field

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

Background

The design difficulty of the wing unfolding mechanism is that the unfolding synchronism, the safety and the symmetry of the unfolded wing are ensured. The wing unfolding mechanism of a general aircraft cannot meet the requirements at the same time, and a simple nacelle does not even need wings and only guides landing by using a parachute. Because of the strict requirements on the throwing precision of some aircrafts and the higher requirements on the control of the flying, a safe and synchronous unfolding mechanism is needed, and in order to meet the aerodynamic performances such as lift-drag ratio and the like in the sliding of the aircrafts, the wings are required to meet the symmetry after being unfolded. The existing partial unfolding mechanism can realize the functions, but at most supports the unfolding of two airfoils, and a plurality of airfoils cannot be unfolded at the same time.

Disclosure of Invention

The utility model provides an object provides a wing expansion mechanism, aircraft and aircraft combination can actuate a plurality of wing surfaces of front wing subassembly, main wing subassembly and fin subassembly simultaneously, has effectively solved the difficult problem that the multiple wing surfaces were expanded simultaneously.

To achieve the above-mentioned purpose, the present application provides a wing deployment mechanism, the wing deployment mechanism includes the driving piece, the action end of driving piece can follow the direction removal of vertical axis, wing deployment mechanism still includes preceding wing subassembly, main wing subassembly and fin subassembly, preceding wing subassembly with main wing subassembly is used for the drive of driving piece action end is rotatory around vertical axis, the fin subassembly is used for the drive of driving piece action end is rotatory around horizontal axis.

In some embodiments, the wing deployment mechanism further comprises a rotating shaft assembly, the rotating shaft assembly is connected with the actuating end of the actuating member, the rotating shaft assembly is used for rotating around a vertical axis under the drive of the actuating end of the actuating member, the rotating shaft assembly is further connected with the main wing assembly and the tail wing assembly so as to drive the main wing assembly to rotate around the vertical axis, and the tail wing assembly rotates around a horizontal axis.

In some embodiments, 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 and arranged in parallel with the vertical axis, the first front wing is connected with the driving piece action end through a first connecting rod, the first front wing is used for rotating forward around the rotation axis of the first front wing under the driving of the driving piece action end, the second front wing is connected with the driving piece action end through a second connecting rod, and the second front wing is used for rotating reversely around the rotation axis of the second front wing under the driving of the driving piece action end.

In some embodiments, the rotating shaft assembly comprises a first rotating shaft member and a second rotating shaft member, the rotating axes of the first rotating shaft member and the second rotating shaft member are overlapped and overlapped with the vertical axis, the first rotating shaft member is connected with the action end of the driving member through a third connecting rod, the second rotating shaft member is connected with the action end of the driving member through a fourth connecting rod, the first rotating shaft member is used for rotating positively around the vertical axis under the driving of the action end of the driving member, and the second rotating shaft member is used for rotating reversely around the vertical axis under the driving of the action end of the driving member;

the main wing assembly comprises a first main wing and a second main wing, the first main wing is connected with the first rotating shaft piece, the first main wing is used for rotating along with the first rotating shaft piece in the forward direction of the vertical axis under the drive of the action end of the driving piece, the second main wing is connected with the second rotating shaft piece, and the second main wing is used for rotating along with the second rotating shaft piece in the reverse direction of the vertical axis under the drive of the action end of the driving piece.

In some embodiments, the fin assembly includes a first fin, a second fin and a fin rotating shaft member, the first fin and the second fin are connected with the fin rotating shaft member, a rotation axis of the fin rotating shaft member coincides with the horizontal axis, the fin rotating shaft member is connected with the first rotating shaft member or the second rotating shaft member through a fifth connecting rod, and the fin rotating shaft member is used for being driven by an action end of the driving member to rotate around the horizontal axis under the action of the first rotating shaft member or the second rotating shaft member.

In some embodiments, the second shaft member is nested in the first shaft member, and the first shaft member is provided with a first mount connected to the first main wing, and the second shaft member is provided with a second mount connected to the second main wing.

In some embodiments, the first rotating shaft piece comprises a first rotating shaft sub-piece and a second rotating shaft sub-piece which are arranged at intervals in the vertical axis direction, the first rotating shaft sub-piece is connected with the action end of the driving piece through the third connecting rod, and the first rotating shaft sub-piece and the second rotating shaft sub-piece are connected through a torque arm; the second rotating shaft part comprises a third rotating shaft part and a fourth rotating shaft part, the third rotating shaft part is nested in the first rotating shaft part, the third rotating shaft part is connected with the action end of the driving part through a fourth connecting rod, the fourth rotating shaft part is nested in the third rotating shaft part and the second rotating shaft part, the fourth rotating shaft part is connected with the third rotating shaft part through a transmission part, the fourth rotating shaft part is further connected with a first pull rod, and the first pull rod is used for being connected to a machine body so as to enable the fourth rotating shaft part to reversely rotate around the vertical axis and move along the vertical axis under the drive of the action end of the driving part, so that the first main wing and the second main wing are located at the same position on the vertical axis.

In some embodiments, the driving piece is a gas spring, the gas spring comprises 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 for being fixed on the machine body, and the gas spring outer cylinder is used as an action end of the driving piece to drive the front wing assembly, the main wing assembly and the tail wing assembly to rotate.

The application also provides an aircraft, which comprises a fuselage and the wing unfolding mechanism, wherein the wing unfolding mechanism is arranged on the fuselage.

The application also provides an aircraft combination, including the host computer and above-mentioned aircraft, the aircraft hang in the host computer, the host computer is provided with and is used for maintaining the wing of aircraft expands the locking device that the mechanism is in the folded state.

For above-mentioned background art, the wing deployment mechanism that this application provided includes the driving piece, and the action end of driving piece can follow the direction of vertical axis and remove, and wing deployment mechanism still includes preceding wing subassembly, main wing subassembly and fin subassembly, and preceding wing subassembly and main wing subassembly are used for rotating around vertical axis under the drive of driving piece action end, and the fin subassembly is used for rotating around horizontal axis under the drive of driving piece action end.

In the use of this wing expansion mechanism, move along the direction of vertical axis through driving piece action end, drive preceding wing subassembly, main wing subassembly and fin subassembly action simultaneously, make preceding wing subassembly and main wing subassembly rotatory around vertical axis, the fin subassembly rotates around horizontal axis, and then realizes the expansion of preceding wing subassembly, main wing subassembly and fin subassembly. The wing unfolding mechanism can simultaneously actuate a plurality of wing surfaces of the front wing assembly, the main wing assembly and the tail wing assembly, and effectively solves the problem of simultaneous unfolding of a plurality of wing surfaces.

Drawings

In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only embodiments of the present application, and that other drawings may be obtained according to the provided drawings without inventive effort to a person skilled in the art.

FIG. 1 is a schematic structural view of a wing deployment mechanism provided in an embodiment of the present application;

FIG. 2 is a schematic view of the transfer assembly of FIG. 1;

FIG. 3 is a partial schematic view of a wing deployment mechanism according to another embodiment of the present application at a first viewing angle;

FIG. 4 is a partial schematic view of a wing deployment mechanism according to another embodiment of the present application at a second viewing angle;

FIG. 5 is a partial schematic view of a wing deployment mechanism according to another embodiment of the present application at a third viewing angle.

Wherein:

1-driving piece, 11-gas spring piston rod, 12-gas spring outer cylinder,

2-front wing assembly, 21-first front wing, 22-first link, 23-second front wing, 24-second link,

3-main wing assembly, 31-first main wing, 32-second main wing,

4-fin assembly, 41-first fin, 42-second fin, 43-fin shaft member, 44-fifth link,

5-spindle assembly, 51-first spindle part, 511-first spindle part, 512-second spindle part, 513-torque arm, 52-third link, 53-second spindle part, 531-third spindle part, 532-fourth spindle part, 533-transmission part, 534-first pull rod, 535-connecting plate, 54-fourth link, 55-first mount, 56-second mount.

Detailed Description

The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all, of the embodiments of the present application. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.

In order to better understand the aspects of the present application, a further detailed description of the present application will be provided below with reference to the accompanying drawings and detailed description.

At present, the air drop supply by using the air drop nacelle is a common air drop supply mode at home and abroad. When the aerial delivery nacelle is hung on the main machine, the wings are in a folded state, and the wings are unfolded after being thrown. The wing of the air drop nacelle is unfolded to influence the aerodynamic performance of the nacelle and the safety of the main aircraft, so that an unfolding mechanism of the air drop nacelle is particularly important.

The traditional wing unfolding mechanism is mainly realized by a rocker arm and a telescopic mechanism, and the unfolding mechanism has some problems at present, because the left rocker arm and the right rocker arm are positioned on the same horizontal plane in the whole unfolding and folding state, when the chord length of the wing is large, the width of the folded wing is possibly larger than the width of a machine body. And occupies a large space when stored, transported or flown. The other folding mechanism has the same problems, and the special air supply equipment is required to be additionally arranged, so that the mechanism has higher complexity, occupies a certain space, increases the weight of the mechanism and increases the cost. And the traditional unfolding mechanism only relates to the unfolding of the main wings, namely the two wings, and can not simultaneously meet the requirement of synchronous unfolding of 6 wings (two main wings, two front wings and two vertical tails).

In view of the above technical problems, the present application provides a wing deployment mechanism, please refer to fig. 1 and fig. 2, fig. 1 is a schematic structural diagram of the wing deployment mechanism provided in the embodiment of the present application, and fig. 2 is a schematic structural diagram of a rotating shaft assembly in fig. 1.

In the coordinate system illustrated in FIG. 1, an X-axis, a Y-axis, and a Z-axis are included; in some cases, the direction of the X-axis is a horizontal direction, corresponding to a horizontal axis; the direction of the Y axis is a vertical direction and corresponds to the vertical axis; the direction of the Z axis is the vertical direction and corresponds to the vertical axis.

In a specific embodiment, the wing unfolding mechanism mainly comprises a driving piece 1, an action end of the driving piece 1 can move along a direction of a vertical axis, the wing unfolding mechanism further comprises a front wing assembly 2, a main wing assembly 3 and a tail wing assembly 4, the front wing assembly 2 and the main wing assembly 3 are used for rotating around the vertical axis under the driving of the action end of the driving piece 1, and the tail wing assembly 4, namely, a vertical tail is used for rotating around the horizontal axis under the driving of the action end of the driving piece 1.

In the use process of the wing unfolding mechanism, the action end of the driving piece 1 moves along the direction of the vertical axis, and simultaneously drives the front wing assembly 2, the main wing assembly 3 and the tail wing assembly 4 to act, so that the front wing assembly 2 and the main wing assembly 3 rotate around the vertical axis, the tail wing assembly 4 rotates around the horizontal axis, and the front wing assembly 2, the main wing assembly 3 and the tail wing assembly 4 are unfolded. The wing unfolding mechanism can simultaneously actuate a plurality of wing surfaces of the front wing assembly 2, the main wing assembly 3 and the tail wing assembly 4, and effectively solves the problem of simultaneous unfolding of the plurality of wing surfaces.

In a specific embodiment, the wing unfolding mechanism further comprises a rotating shaft assembly 5, the rotating shaft assembly 5 is connected with the action end of the driving piece 1, the rotating shaft assembly 5 is used for rotating around a vertical axis under the drive of the action end of the driving piece 1, the rotating shaft assembly 5 is further connected with the main wing assembly 3 and the tail wing assembly 4 to drive the main wing assembly 3 to rotate around the vertical axis, and the tail wing assembly 4 rotates around a horizontal axis.

With continued reference to fig. 1, the wing deployment mechanism in fig. 1 is in a folded state of the wing, i.e., the wing deployment mechanism has not deployed the wing. As shown in fig. 1, the front wing assembly 2 includes a first front wing 21 and a second front wing 23, the rotation axes of the first front wing 21 and the second front wing 23 are spaced and parallel to the vertical axis, the first front wing 21 is connected with the action end of the driving element 1 through a first link 22, the first front wing 21 is used for rotating forward around the rotation axis of the first front wing 21 under the driving of the action end of the driving element 1, the second front wing 23 is connected with the action end of the driving element 1 through a second link 24, and the second front wing 23 is used for rotating reversely around the rotation axis of the second front wing 23 under the driving of the action end of the driving element 1.

In the present embodiment, the first front wing 21 and the second front wing 23 are symmetrically arranged at both horizontal sides of the driving member 1, 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 realizing the rotation, and the wing unfolding mechanism is arranged on the fuselage during application, so that 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 fixedly in the reference frame of the fuselage. The first connecting rod 22 and the second connecting rod 24 are used for realizing force transmission, and the force transmission should be flexibly set according to actual needs in the connection relationship between the first connecting rod 22 and the components, for example, the first connecting rod 22 is rotationally connected with the first front wing 21 and the action end of the driving piece 1, and the force transmission belongs to an adaptive setting, and will not be repeated here.

It should be noted that the rotation directions of the first front wing 21 and the second front wing 23 are opposite, and the first front wing 21 and the second front wing 23 are juxtaposed on both horizontal sides of the driving member 1 in the state where the first front wing 21 and the second front wing 23 are not unfolded, i.e., in the folded state, for example; when the first front wing 21 and the second front wing 23 are unfolded, the first front wing 21 rotates clockwise under the action of the action end of the driving piece 1 and the rotating shaft of the driving piece, at this time, the first front wing 21 is unfolded clockwise on the left side of the central axis of the machine body, the second front wing 23 rotates anticlockwise, at this time, the second front wing 23 is unfolded anticlockwise on the right side of the central axis of the machine body, and therefore the unfolding of the first front wing 21 and the second front wing 23 is achieved.

Similarly, the main wing assembly 3 comprises a first main wing 31 and a second main wing 32, and the first main wing 31 and the second main wing 32 are driven by the action end of the driving piece 1 to rotate in opposite directions to realize unfolding.

In a specific embodiment, please continue to refer to fig. 1, the rotating shaft assembly 5 includes a first rotating shaft member 51 and a second rotating shaft member 53, the rotation axes of the first rotating shaft member 51 and the second rotating shaft member 53 are overlapped and overlapped with the vertical axis, the first rotating shaft member 51 is connected with the action end of the driving member 1 through a third connecting rod 52, the second rotating shaft member 53 is connected with the action end of the driving member 1 through a fourth connecting rod 54, the first rotating shaft member 51 is used for forward rotating around the vertical axis under the driving of the action end of the driving member 1, and the second rotating shaft member 53 is used for reverse rotating around the vertical axis under the driving of the action end of the driving member 1.

Correspondingly, the first main wing 31 is connected with the first rotating shaft piece 51, the first main wing 31 is used for rotating forward along with the first rotating shaft piece 51 around the vertical axis under the driving of the action end of the driving piece 1, the second main wing 32 is connected with the second rotating shaft piece 53, and the second main wing 32 is used for rotating reversely along with the second rotating shaft piece 53 around the vertical axis under the driving of the action end of the driving piece 1.

In this 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 and the second front wing 23 are located on the right side of the central axis of the fuselage after the first main wing 31 is unfolded, the first main wing 31 is equivalent to the right main wing, the second main wing 32 and the first front wing 21 are located on the left side of the central axis of the fuselage after the second main wing 32 is unfolded, and the second main wing 32 is equivalent to the left main wing. Taking the illustration as an example, in a state that the first main wing 31 and the second main wing 32 are not unfolded, i.e., folded, 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 rotates clockwise to the right side of the central axis of the machine body under the action of the action end of the driving piece 1 and the rotating shaft thereof, and the first main wing 31 rotates anticlockwise to the left side of the central axis of the machine body under the action of the action end of the driving piece 1 and the rotating shaft thereof.

In some cases, the wing deployment mechanism will be mounted on the fuselage in use, the first shaft element 51 of the shaft assembly 5 being connected to the fuselage, the first shaft element 51 and the second shaft element 53 being carried by the fuselage, the first shaft element 51 and the second shaft element 53 being journaled in a frame of reference of the fuselage. The third connecting rod 52 and the fourth connecting rod 54 are used for realizing force transmission, and in the connection relationship between the third connecting rod 52 and the components, the force transmission should be flexibly set according to actual needs, for example, the action ends of the third connecting rod 52, the first rotating shaft element 51 and the driving element 1 are all in rotational connection, and the force transmission belongs to adaptive setting, and will not be repeated here.

It should be noted that the first link 22 and the second link 24 in the front wing assembly 2 described above should be symmetrically disposed on both horizontal sides of the driving member 1, and similarly, the third link 52 and the fourth link 54 in the rotating shaft assembly 5 should be symmetrically disposed on both horizontal sides of the driving member 1.

With continued reference to fig. 1, in some embodiments, the tail assembly 4 includes a first tail 41, a second tail 42, and a tail shaft member 43, where the first tail 41 and the second tail 42 are connected to the tail shaft member 43, the rotation axis of the tail shaft member 43 coincides with the horizontal axis, and the tail shaft member 43 is connected to the first shaft member 51 or the second shaft member 53 through a fifth link 44, and the tail shaft member 43 is used to rotate around the horizontal axis under the action of the first shaft member 51 or the second shaft member 53 under the action of the action end of the driving member 1.

In the present embodiment, unlike the first and second front wings 21 and 23 and the first and second main wings 31 and 32 described above, the first and second tail wings 41 and 42 are rotated in synchronization and in the same direction when the first and second tail wings 41 and 42 are unfolded. Taking the illustration as an example, the first tail 41 rotates on the left side of the central axis of the machine body under the action of the action end of the driving element 1 and the tail rotating shaft element 43, and the second tail 42 rotates on the right side of the central axis of the machine body under the action of the action end of the driving element 1 and the tail rotating shaft element 43. The fifth link 44 is used for realizing force transmission, and in the connection relationship between the fifth link 44 and the components, the force should be flexibly set according to actual needs, for example, the fifth link 44 is rotationally connected with the first rotating shaft member 51 and the tail rotating shaft member 43, which belongs to an adaptive setting and is not described herein. In addition, the fifth link 44 and the second shaft member 53 may be provided in the same manner as described in the present embodiment.

Preferably, when the first tail 41 and the second tail 42 are in the folded state, the first tail 41 and the second tail 42 rotate to a horizontal plane similar to the plane where the front wing assembly 2 and the main wing assembly 3 are located, and when the first tail 41 and the second tail 42 are unfolded, the first tail 41 and the second tail 42 rotate to a vertical position, so that the space occupied by the wing unfolding mechanism in the fuselage can be saved.

With continued reference to fig. 2, in some embodiments, the second shaft member 53 is nested in the first shaft member 51, and the first shaft member 51 is provided with a first mounting seat 55 connected to the first main wing 31, where the motion of the first main wing 31, i.e. the right main wing, is implemented by the first shaft member 51 and the fourth link 54, and the second shaft member 53 is provided with a second mounting seat 56 connected to the second main wing 32, where the motion of the second main wing 32, i.e. the left main wing, is implemented by the second shaft member 53 and the third link 52.

Fig. 3 to 5 are schematic diagrams of a wing deployment mechanism according to another embodiment of the present application in a first view, fig. 4 is a schematic diagram of a wing deployment mechanism according to another embodiment of the present application in a second view, and fig. 5 is a schematic diagram of a wing deployment mechanism according to another embodiment of the present application in a third view.

It should be noted that fig. 3 to 5 are another embodiment of the present application, and are slightly different from the embodiments of fig. 1 and 2 in structure, but all fall within the scope of the technical solutions provided in the present application.

In a specific embodiment, the main wing is unfolded by rotating the inner sleeve and the outer sleeve which are nested inside each other. The inner sleeve can move in the vertical direction, and when the inner sleeve is folded, the inner sleeve descends to give up space for the two wing surfaces to be folded at the lower part of the aircraft; when the wing is unfolded, the inner sleeve ascends, so that after the wing is unfolded, the left main wing and the right main wing are positioned on the same horizontal plane, and the symmetry after the wing is unfolded is ensured.

It should be noted that the present embodiment is not limited to the specific structure of the two sleeves, i.e., the first shaft member 51 and the second shaft member 53, and may be separate components or may be combined components, which shall fall within the scope of the present embodiment; for example, when separate components are employed, the form of threads may be employed in order to achieve dual movement of rotation and translation.

Specifically, the first shaft member 51 includes a first shaft member 511 and a second shaft member 512 that are disposed at intervals in the vertical axis direction, the first shaft member 511 is connected to the action end of the driving member 1 through a third link 52, at this time, the first shaft member 511 rotates under the drive of the action end of the driving member 1, the first shaft member 511 and the second shaft member 512 are connected through a torque arm 513, at this time, the first shaft member 511 and the second shaft member 512 rotate synchronously without movement in the vertical axis direction. The first mounting seat 55 connected to the first main wing 31 is disposed at the end of the second rotating shaft component 512, and the second rotating shaft component 512 drives the first main wing 31, i.e. the right main wing, to act.

The second rotating shaft piece 53 includes a third rotating shaft piece 531 and a fourth rotating shaft piece 532, the third rotating shaft piece 531 is nested in the first rotating shaft piece 511, the third rotating shaft piece 531 is connected with the action end of the driving piece 1 through the fourth connecting rod 54, at this time, the third rotating shaft piece 531 rotates under the drive of the action end of the driving piece 1 and is opposite to the rotation direction of the first rotating shaft piece 511, the fourth rotating shaft piece 532 is nested in the third rotating shaft piece 531 and the second rotating shaft piece 512, the fourth rotating shaft piece 532 is connected with the third rotating shaft piece 531 through the transmission piece 533, at this time, the fourth rotating shaft piece 532 can be driven by the transmission piece 533 to rotate together with the third rotating shaft piece 531, the fourth rotating shaft piece 532 is also connected with the first pull rod 534, the first pull rod 534 is used for being connected to the fuselage, the effect of the first pull rod 534 is to drive the fourth rotating shaft piece 532 to move along the vertical axis relative to the third rotating shaft piece 511 when the fourth rotating shaft piece 532 rotates, thereby enabling the fourth rotating shaft piece 532 to reversely rotate around the vertical axis to move along the vertical main axis, so that the first wing 31 and the second wing 31 are located at the same vertical position on the vertical main axis 32. The second mounting seat 56 connected to the second main wing 32 is disposed at the end of the fourth rotating shaft component 532, and the end of the fourth rotating shaft component 532 passes through the end of the second rotating shaft component 512, and the fourth rotating shaft component 532 drives the second main wing 32, i.e. the left main wing, to act.

It should be noted that, unlike the torque arm 513 described above, the torque arm 513 merely rotates the first and second shaft members 511 and 512 synchronously without moving in the vertical axis direction, and the transmission member 533 can rotate the third and fourth shaft members 531 and 532 synchronously and can move the fourth shaft member 532 in the vertical axis direction relative to the third shaft member 531.

Further, a connection plate 535 is provided on the fourth rotating shaft component 532, the connection plate 535 is connected to the first pull rod 534, and the first pull rod 534 is connected to the machine body; in addition, the connection plate 535 is connected to the transmission member 533, and the transmission member 533 is further connected to the third rotation shaft sub 531.

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, and under the action of the torque arm 513, the first rotating shaft sub-member 511 and the second rotating shaft sub-member 512 are enabled to rotate forward around the vertical axis, so as to drive the first main wing 31 to rotate forward around the vertical axis, and at this time, the first main wing 31 does not move along the vertical axis direction; for the second rotating shaft piece 53, the fourth connecting rod 54 drives the third rotating shaft piece 531 to move, so that the third rotating shaft piece 531 reversely rotates around the vertical axis, under the action of the transmission piece 533, the fourth rotating shaft piece 532 reversely rotates around the vertical axis, and further, the first main wing 31 is reversely rotated around the vertical axis, meanwhile, the first pull rod 534 is connected between the machine body and the connecting plate 535, when the connecting plate 535 rotates together with the fourth rotating shaft piece 532, the connecting plate 535 moves along the vertical axis under the limiting condition of the length of the first pull rod 534, so that the fourth rotating shaft piece 532 moves along the vertical axis, and further, the second main wing 32 moves along the vertical axis while reversely rotating, which is equivalent to that the second main wing 32 moves in the lower direction of the first main wing 31 when being unfolded, and 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 folded in a staggered manner along the vertical axis.

In a specific embodiment, the driving piece 1 is a gas spring, and on the one hand, the gas spring is used as a driving source of the unfolding mechanism, so that the device has the advantages of simplicity and convenience and high cost performance; on the other hand, the gas spring has the characteristic of time delay, the unfolding time of the gas spring driving mechanism is controllable, the delivered objects are ensured to be unfolded for a certain time after leaving the main machine, and the separation safety is ensured. In addition, the full unfolding time of the airfoil can be controlled by adjusting the opening of the valve in the gas spring or selecting different types of gas springs, so that the time delay is achieved, and the separation safety is ensured.

In this embodiment, the air spring includes an air spring piston rod 11 and an air spring outer cylinder 12 sleeved with the air spring piston rod 11, the air spring piston rod 11 is fixed on the machine body, and the air spring outer cylinder 12 is used as an actuating end of the driving element 1 to drive the front wing assembly 2, the main wing assembly 3 and the tail wing assembly 4 to rotate.

In summary, the present application is designed to comprehensively consider the characteristics that the deployment mechanism needs to satisfy, with respect to the shortcomings of the existing wing deployment mechanisms. According to the novel unfolding mechanism, the characteristics of the existing wing unfolding mechanism are analyzed, the requirements of separation safety and throwing accuracy of a certain type of aircraft are combined, a mechanism capable of delaying and guaranteeing simultaneous unfolding of the front wing, the main wing and the vertical tail is provided, the novel unfolding mechanism can better solve some problems existing in the existing unfolding mechanism, in addition, the mechanism can further guarantee symmetry of the wing after unfolding, and aerodynamic performance is guaranteed not to be lost.

The application also provides an aircraft, which comprises a fuselage and the wing unfolding mechanism, wherein the wing unfolding mechanism is arranged on the fuselage.

The aircraft should have all the beneficial effects of the wing deployment mechanism described above and will not be described in detail herein.

The application also provides an aircraft combination, including the host computer and above-mentioned aircraft, the aircraft is hung in the host computer, and the host computer is provided with the locking device that is used for maintaining the wing expansion mechanism of aircraft in the folded state.

The aircraft assembly should have all the beneficial effects of the aircraft and wing deployment mechanism, and will not be described in detail herein.

In the synchronous design, the parts to be driven of the nacelle are considered to be provided with a left wing, a right wing, a left wing, a right wing and a left wing, 6 wings are driven by a single air spring, the left wing and the right wing are connected to an air spring outer cylinder through two connecting rods, a left wing rotating shaft and a right wing rotating shaft are connected to the air spring outer cylinder through connecting rods after being transmitted from the bottom of the nacelle to the top of the nacelle, the left wing and the right wing are fixed coaxially with the rotating shafts, and a rocker arm is arranged at the position of the wing rotating shaft and is connected with the right main wing rotating shaft through the connecting rods. Therefore, the driving of the 6 airfoils drives the gas spring outer cylinder through the single movement, the piston rod end of the gas spring is fixed on the machine body, the gas spring outer cylinder is connected with the driving of the 6 airfoils, the radial displacement of the gas spring is limited through the middle through hole of the lifting lug, and the mechanical synchronization of the movement of the mechanism can be realized for the 6 airfoils of the machine as long as the gas spring is laterally free of displacement.

In the aspect of safety design, the time for opening the machine span in place can be controlled by controlling the gas spring reset time. Meanwhile, in order to avoid accidental unfolding in the hanging and flying folding process, the whole aircraft is designed with a three-level locking device, and the separation safety is met in the aircraft throwing process by matching with the unfolding mechanism.

In the symmetrical design, the two main wing surfaces are lifting, the left wing and the right wing are highly symmetrical in the wing unfolding state, and the left wing and the right wing are highly staggered and folded in the fuselage enveloping body in the folding state. The right wing rotating shaft is divided into two parts, the middle part is connected with torque through a torque arm to drive the wing to rotate, a rocker arm is additionally arranged in the middle of the left wing rotating shaft and is connected with the machine body through a pull rod, in the rotating process of the left wing, the pull rod swings to generate a height difference to drive the left wing to move in the height direction, so that the unfolding state of the left wing and the right wing are horizontally symmetrical, and the folding state is staggered in height.

In the process of the unfolding mechanism, simulation means such as structural design, strength design and the like are fully utilized to evaluate the performance of the unfolding mechanism so as to design the delay synchronous unfolding mechanism meeting the requirements. Meanwhile, the fact that the aircraft is thrown at high altitude is considered to be a low-temperature condition, so that multiple rounds of constant and low-temperature test verification is carried out on key components such as a gas spring, and the reliability of a mechanism is ensured.

In practical use, the locking and unfolding process of the aircraft wing is divided into 3 steps, and the present application is further described below with reference to examples.

Aerial mount (wing fold) state: the aircraft is hung on the main aircraft through the hanging frame, the vertical direction is limited through the hanging lugs, and the lateral direction is clamped with the locking pins on the main wing of the aircraft through the hanging frame clamping mechanism to limit the lateral swing of the nacelle. At this time, the 6 wing surfaces are in a folded state, and the front wing of the aircraft is limited by the mechanical limiting device, so that the unfolding mechanism is prevented from being unfolded by mistake.

Deployment state after release: after the aircraft is put in, the clamping mechanism on the hanging frame loses the locking function of the rear wing of the nacelle, but at the moment, the main wing surface is still mechanically locked, the hanging frame is put in until the main wing surface is completely and safely separated from the aircraft, and the flying control gives instructions to control the swing of the aileron, so that the mechanical lock arranged below the side of the aircraft body is unlocked, the whole 6 wings lose mechanical limit, and the main wing is unfolded under the driving of the gas spring.

After the mechanism is fully unfolded, the flying state is as follows: and after the wing is unfolded in place, the wing is provided with a spring pin brake, and the spring pin automatically stretches and is inserted into the rocker arm hole to stop.

Therefore, the application provides a delay unfolding mechanism capable of synchronously unfolding wings, the unfolding mechanism can overcome some defects of a traditional unfolding mechanism, symmetry of the wings can be guaranteed, and good aerodynamic performance of an aircraft is guaranteed.

It should be noted that many of the components mentioned in this application are common standard components or components known to those skilled in the art, and the structures and principles thereof are known to those skilled in the art from technical manuals or by routine experimental methods.

It should be noted that in this specification relational terms such as first and second are used solely to distinguish one entity from another entity without necessarily requiring or implying any actual such relationship or order between such entities.

The wing deployment mechanism, aircraft and aircraft combination provided by the present application are described in detail above. Specific examples are set forth herein to illustrate the principles and embodiments of the present application, and the description of the examples above is only intended to assist in understanding the methods of the present application and their core ideas. It should be noted that it would be obvious to those skilled in the art that various improvements and modifications can be made to the present application without departing from the principles of the present application, and such improvements and modifications fall within the scope of the claims of the present application.

Claims (10)

1. The wing unfolding mechanism is characterized by comprising a driving piece, wherein the action end of the driving piece can move 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 the vertical axis under the driving of the action end of the driving piece, and the tail wing assembly is used for rotating around the horizontal axis under the driving of the action end of the driving piece.

2. The wing deployment mechanism of claim 1, further comprising a shaft assembly coupled to the actuator actuating end, the shaft assembly configured to rotate about a vertical axis under the drive of the actuator actuating end, the shaft assembly further coupled to the main wing assembly and the tail assembly to rotate about a vertical axis and the tail assembly about a horizontal axis.

3. The wing deployment mechanism of claim 1, wherein 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 are arranged at intervals and are parallel to the vertical axis, the first front wing is connected with the actuating end of the actuating element through a first connecting rod, the first front wing is used for rotating forward around the rotation axis of the first front wing under the driving of the actuating end of the actuating element, the second front wing is connected with the actuating end of the actuating element through a second connecting rod, and the second front wing is used for rotating reversely around the rotation axis of the second front wing under the driving of the actuating end of the actuating element.

4. The wing deployment mechanism of claim 2, wherein the shaft assembly comprises a first shaft member and a second shaft member, the rotation axes of the first shaft member and the second shaft member are coincident with each other and coincident with the vertical axis, the first shaft member is connected with the driving member actuating end through a third connecting rod, the second shaft member is connected with the driving member actuating end through a fourth connecting rod, the first shaft member is used for rotating forward around the vertical axis under the drive of the driving member actuating end, and the second shaft member is used for rotating reversely around the vertical axis under the drive of the driving member actuating end;

the main wing assembly comprises a first main wing and a second main wing, the first main wing is connected with the first rotating shaft piece, the first main wing is used for rotating along with the first rotating shaft piece in the forward direction of the vertical axis under the drive of the action end of the driving piece, the second main wing is connected with the second rotating shaft piece, and the second main wing is used for rotating along with the second rotating shaft piece in the reverse direction of the vertical axis under the drive of the action end of the driving piece.

5. The wing deployment mechanism of claim 4, wherein the tail assembly comprises a first tail, a second tail and a tail rotating shaft member, the first tail and the second tail are connected with the tail rotating shaft member, the rotating axis of the tail rotating shaft member coincides with the horizontal axis, the tail rotating shaft member is connected with the first rotating shaft member or the second rotating shaft member through a fifth connecting rod, and the tail rotating shaft member is used for being driven by the action end of the driving member to rotate around the horizontal axis under the action of the first rotating shaft member or the second rotating shaft member.

6. The wing deployment mechanism of claim 4, wherein the second shaft member is nested within the first shaft member and the first shaft member is provided with a first mount to which the first main wing is coupled and the second shaft member is provided with a second mount to which the second main wing is coupled.

7. The wing deployment mechanism of claim 6, wherein the first shaft member comprises a first shaft member and a second shaft member arranged at intervals in the vertical axis direction, the first shaft member and the actuating end of the driving member are connected by the third link, and the first shaft member and the second shaft member are connected by a torque arm; the second rotating shaft part comprises a third rotating shaft part and a fourth rotating shaft part, the third rotating shaft part is nested in the first rotating shaft part, the third rotating shaft part is connected with the action end of the driving part through a fourth connecting rod, the fourth rotating shaft part is nested in the third rotating shaft part and the second rotating shaft part, the fourth rotating shaft part is connected with the third rotating shaft part through a transmission part, the fourth rotating shaft part is further connected with a first pull rod, and the first pull rod is used for being connected to a machine body so as to enable the fourth rotating shaft part to reversely rotate around the vertical axis and move along the vertical axis under the drive of the action end of the driving part, so that the first main wing and the second main wing are located at the same position on the vertical axis.

8. The wing deployment mechanism of any one of claims 1 to 7, wherein the driving member is a gas spring, the gas spring includes a gas spring piston rod and a gas spring outer cylinder that is sleeved on the gas spring piston rod, the gas spring piston rod is fixed on the fuselage, and the gas spring outer cylinder is used as an actuating end of the driving member to rotate the front wing assembly, the main wing assembly and the tail wing assembly.

9. An aircraft comprising a fuselage and a wing deployment mechanism as claimed in any one of claims 1 to 8, the wing deployment mechanism being mounted to the fuselage.

10. An aircraft assembly comprising a parent aircraft and an aircraft as claimed in claim 9, the aircraft being mounted on the parent aircraft, the parent aircraft being provided with a locking device for maintaining a wing deployment mechanism of the aircraft in a folded condition.