CN111746783B - Flank structure for aircraft and aircraft - Google Patents

Abstract

Embodiments of the present disclosure provide a flank structure for an aircraft and an aircraft, the flank structure includes at least one multi-link structure, and the multi-link structure is arranged extending from the main body of the aircraft to the wingtip direction, each of which is The multi-link mechanism includes a plurality of links, and the adjacent links are connected by a motor. Embodiments of the present disclosure provide flank structures that feature a widely variable airfoil in both chordwise and spanwise directions, the flank structure having variable airfoil shape, the ability to vary widely in pitch angle, along the wingspan at the distal end portion The ability to twist in the direction, the ability to swing vertically in a large range along the plane where the main body of the vehicle is located, and the ability to swing longitudinally in a large range along the main body of the vehicle, can be adjusted for complex flow fields or environments, and the movement speed can be greatly improved and exercise efficiency, and can achieve high maneuverability.

Description

Flank structure for aircraft and aircraft

technical field

The present disclosure relates to the field of navigation devices, and in particular, to a flank structure for an aircraft and an aircraft.

Background technique

Most of the aircrafts in the prior art adopt a fixed-wing structure or a relatively limited morphingwing structure, which cannot be adjusted for the actual navigation or flight environment or complex flow field, resulting in low navigation or flight speed. The efficiency is not high, the stability is poor, and high maneuverability cannot be achieved.

SUMMARY OF THE INVENTION

The purpose of the embodiments of the present disclosure is to provide a flank structure for an aircraft and an aircraft, so as to solve the problems in the prior art that the navigation or flight speed is low, the efficiency is low, the stability is poor, and the high maneuvering action cannot be realized. .

In order to solve the above-mentioned technical problems, the embodiments of the present disclosure adopt the following technical solutions: a flank structure for an aircraft, comprising at least one multi-link structure, the multi-link structure extending from the main body of the aircraft to the wingtip direction Arrangement, each of the multi-link mechanisms includes a plurality of links, and the adjacent links are connected by a motor.

In some embodiments, the linkage and the motor are interconnected to achieve at least one of the following changes or movements of the flank structure: variable airfoil, variable pitch angle, distal portion along the wingspan It can twist in the direction, swing vertically along the plane where the aircraft body is located, and swing along the longitudinal direction of the aircraft body.

In some embodiments, the aircraft body includes a support link, the support link is consistent with the length direction of the aircraft body, and the first end of the multi-link structure is aligned with the support link connect.

In some embodiments, the second end of the multi-link structure is connected to a tip tab.

In some embodiments, when the number of the multi-link structures is plural, the multi-link structures are sequentially arranged along the aircraft body.

In some embodiments, the lengths of the multi-link structures arranged sequentially from the head to the tail of the aircraft body decrease sequentially.

In some embodiments, multiple sets of fins are sleeved on the multi-link structure, and each set of the fins includes at least one fin unit.

In some embodiments, the number of the fin units in each group of the fins is less than or equal to the number of the multi-link structures.

In some embodiments, in the same group of the fins, the adjacent fin units are connected by means of spherical hinges.

In some embodiments, the front ends or the rear ends of all the fin units sleeved on the same multi-link structure are connected by a fixing part.

In some embodiments, the fixing portion is an elastic fiber filament or a metal filament.

In some embodiments, the fin unit is provided with a conical hole or a chute.

An embodiment of the present disclosure also provides an aircraft, which adopts the flank structure described in any one of the above technical solutions.

Embodiments of the present disclosure provide flank structures that feature widely variable airfoils in both chordwise and spanwise directions, the flank structures having a variable airfoil, the ability to vary the pitch angle over a wide range, and along the span at the distal end portion. The ability to twist in the direction, the ability to swing vertically in a large range along the plane where the main body of the vehicle is located, and the ability to swing longitudinally in a large range along the main body of the vehicle, can be adjusted for complex flow fields or environments, and the movement speed can be greatly improved and exercise efficiency, and can achieve high maneuverability.

Description of drawings

1 is a schematic structural diagram of a flank structure having three multi-link structures according to an embodiment of the disclosure;

2 is a schematic structural diagram of a flank structure having three multi-link structures according to an embodiment of the present disclosure;

3 is a schematic diagram of a leading edge multi-link structure of a flank structure having three multi-link structures according to an embodiment of the disclosure;

4 is a schematic diagram of a leading edge multi-link structure of a flank structure having three multi-link structures according to an embodiment of the disclosure;

5 is a schematic diagram of a leading edge multi-link structure of a flank structure having three multi-link structures according to an embodiment of the disclosure;

6 is a schematic diagram of a leading edge multi-link structure of a flank structure having three multi-link structures according to an embodiment of the disclosure;

7 is a schematic diagram of a leading edge multi-link structure of a flank structure having three multi-link structures according to an embodiment of the disclosure;

8 is a schematic diagram of a leading edge multi-link structure of a flank structure having three multi-link structures according to an embodiment of the disclosure;

9 is a schematic diagram of a leading edge multi-link structure of a flank structure having three multi-link structures according to an embodiment of the disclosure;

10 is a schematic diagram of a leading edge multi-link structure of a flank structure having three multi-link structures according to an embodiment of the disclosure;

11 is a schematic diagram of a leading edge multi-link structure of a flank structure having three multi-link structures according to an embodiment of the disclosure;

12 is a schematic diagram of a leading edge multi-link structure of a flank structure having three multi-link structures according to an embodiment of the disclosure;

13 is a schematic diagram of the middle multi-link structure of the flank structure with three multi-link structures according to an embodiment of the disclosure;

14 is a schematic diagram of the middle multi-link structure of the flank structure with three multi-link structures according to an embodiment of the disclosure;

15 is a schematic diagram of the middle multi-link structure of the flank structure with three multi-link structures according to an embodiment of the disclosure;

16 is a schematic diagram of the middle multi-link structure of the flank structure with three multi-link structures according to an embodiment of the disclosure;

17 is a schematic diagram of the middle multi-link structure of the flank structure with three multi-link structures according to an embodiment of the disclosure;

18 is a schematic diagram of the middle multi-link structure of the flank structure with three multi-link structures according to an embodiment of the disclosure;

19 is a schematic diagram of the middle multi-link structure of the flank structure with three multi-link structures according to an embodiment of the disclosure;

20 is a schematic diagram of a trailing edge multi-link structure of a flank structure having three multi-link structures according to an embodiment of the disclosure;

21 is a schematic diagram of a trailing edge multi-link structure of a flank structure having three multi-link structures according to an embodiment of the disclosure;

22 is a schematic diagram of a trailing edge multi-link structure of a flank structure having three multi-link structures according to an embodiment of the disclosure;

23 is a schematic diagram of a trailing edge multi-link structure of a flank structure having three multi-link structures according to an embodiment of the disclosure;

24 is a schematic diagram of a trailing edge multi-link structure of a flank structure having three multi-link structures according to an embodiment of the disclosure;

25 is a schematic structural diagram of a wing in a side wing structure with three multi-link structures according to an embodiment of the disclosure;

26 is a schematic structural diagram of a fin unit in a fin of a side fin structure with three multi-link structures according to an embodiment of the disclosure;

27 is a schematic diagram of the connection between the link mechanism and the support structure of the flank structure with three multi-link structures according to an embodiment of the disclosure;

28 is a schematic diagram of the connection between the link mechanism and the support structure of the flank structure with three multi-link structures according to an embodiment of the disclosure;

FIG. 29 is a schematic diagram of the connection between the link mechanism and the support structure of the flank structure with three multi-link structures according to an embodiment of the disclosure;

30 is a schematic diagram of the connection between the link mechanism and the support structure of the flank structure with three multi-link structures according to an embodiment of the disclosure;

31 is a schematic diagram of a flank structure having two multi-link structures according to an embodiment of the disclosure;

32 is a schematic diagram of a flank structure having two multi-link structures according to an embodiment of the disclosure;

33 is a schematic diagram of a flank structure having two multi-link structures according to an embodiment of the disclosure;

34 is a schematic diagram of a leading edge multi-link structure of a flank structure having two multi-link structures according to an embodiment of the disclosure;

35 is a schematic diagram of a leading edge multi-link structure of a flank structure having two multi-link structures according to an embodiment of the disclosure;

36 is a schematic diagram of a leading edge multi-link structure of a flank structure having two multi-link structures according to an embodiment of the disclosure;

37 is a schematic diagram of a leading edge multi-link structure of a flank structure having two multi-link structures according to an embodiment of the disclosure;

38 is a schematic diagram of a leading edge multi-link structure of a flank structure having two multi-link structures according to an embodiment of the disclosure;

39 is a schematic diagram of a leading edge multi-link structure of a flank structure having two multi-link structures according to an embodiment of the disclosure;

40 is a schematic diagram of a leading edge multi-link structure of a flank structure having two multi-link structures according to an embodiment of the disclosure;

41 is a schematic diagram of a leading edge multi-link structure of a flank structure having two multi-link structures according to an embodiment of the disclosure;

42 is a schematic diagram of a leading edge multi-link structure of a flank structure having two multi-link structures according to an embodiment of the disclosure;

43 is a schematic diagram of a leading edge multi-link structure of a flank structure having two multi-link structures according to an embodiment of the disclosure;

44 is a schematic diagram of the middle multi-link structure of the flank structure with two multi-link structures according to an embodiment of the disclosure;

45 is a schematic diagram of the middle multi-link structure of the flank structure with two multi-link structures according to an embodiment of the disclosure;

46 is a schematic diagram of the middle multi-link structure of the flank structure with two multi-link structures according to an embodiment of the disclosure;

47 is a schematic diagram of the middle multi-link structure of the flank structure with two multi-link structures according to an embodiment of the disclosure;

48 is a schematic diagram of the middle multi-link structure of the flank structure with two multi-link structures according to an embodiment of the disclosure;

49 is a schematic diagram of the middle multi-link structure of the flank structure with two multi-link structures according to an embodiment of the disclosure;

50 is a schematic diagram of the middle multi-link structure of the flank structure with two multi-link structures according to an embodiment of the disclosure;

51 is a schematic structural diagram of a wing in a side wing structure with two multi-link structures according to an embodiment of the disclosure;

52 is a schematic structural diagram of a fin unit in a fin of a side fin structure with two multi-link structures according to an embodiment of the present disclosure;

53 is a schematic diagram of the connection between the link mechanism and the support structure of the flank structure with two multi-link structures according to an embodiment of the disclosure;

54 is a schematic diagram of the connection between the link mechanism and the support structure of the flank structure with two multi-link structures according to an embodiment of the disclosure;

55 is a schematic diagram of the connection between the link mechanism and the support structure of the flank structure with two multi-link structures according to an embodiment of the disclosure;

56 is a schematic diagram of a leading edge multi-link structure of a flank structure having a multi-link structure according to an embodiment of the disclosure;

57 is a schematic structural diagram of a flank structure having a multi-link structure according to an embodiment of the disclosure;

58 is a schematic structural diagram of a flank structure having a multi-link structure according to an embodiment of the disclosure;

59 is a schematic diagram of a leading edge multi-link structure of a flank structure having a multi-link structure according to an embodiment of the disclosure.

60 is a schematic diagram of a leading edge multi-link structure of a flank structure having a multi-link structure according to an embodiment of the disclosure;

61 is a schematic diagram of a leading edge multi-link structure of a flank structure having a multi-link structure according to an embodiment of the disclosure;

62 is a schematic diagram of a leading edge multi-link structure of a flank structure having a multi-link structure according to an embodiment of the disclosure;

63 is a schematic diagram of a leading edge multi-link structure of a flank structure having a multi-link structure according to an embodiment of the disclosure;

64 is a schematic diagram of a leading edge multi-link structure of a flank structure having a multi-link structure according to an embodiment of the disclosure;

65 is a schematic diagram of a leading edge multi-link structure of a flank structure having a multi-link structure according to an embodiment of the disclosure;

66 is a schematic diagram of a leading edge multi-link structure of a flank structure having a multi-link structure according to an embodiment of the disclosure;

67 is a schematic diagram of a leading edge multi-link structure of a flank structure having a multi-link structure according to an embodiment of the disclosure;

68 is a schematic diagram of a leading edge multi-link structure of a flank structure having a multi-link structure according to an embodiment of the disclosure;

69 is a schematic structural diagram of a wing in a side wing structure with a multi-link structure according to an embodiment of the disclosure;

70 is a schematic structural diagram of a fin unit in a fin of a side fin structure with a multi-link structure according to an embodiment of the disclosure;

71 is a schematic diagram of the connection between the link mechanism and the support structure of the flank structure with a multi-link structure according to an embodiment of the disclosure;

72 is a schematic diagram of the connection between the link mechanism and the support structure of the flank structure with a multi-link structure according to an embodiment of the disclosure;

Reference number:

1- leading edge multi-link structure; 2- middle multi-link structure; 3- trailing edge multi-link structure; 8- leading edge end wing; 9- middle end wing; 10- support link;

101-first leading edge link; 102-second leading edge link; 103-third leading edge link; 104-fourth leading edge link; 105-fifth leading edge link; 106-first front link 107-Second leading edge connector; 108-Third leading edge connector; 109-Fourth leading edge connector; 111-First leading edge motor; 1111-First leading edge motor rotor; 1112- The first leading edge motor stator; 112 - the second leading edge motor; 1121 - the second leading edge motor stator; 1122 - the second leading edge motor rotor; 113 - the third leading edge motor; 1131 - The third leading edge motor stator; 1132 - the third leading edge motor rotor; 114 - the fourth leading edge motor; 1141 - the fourth leading edge motor stator; 1142 - the fourth leading edge motor rotor; 115 - the fifth leading edge motor; 1151 - the fifth leading edge motor Stator; 1152-5th leading edge motor rotor; 116-sixth leading edge motor; 1161-sixth leading edge motor rotor; 1162-sixth leading edge motor stator; 117-seventh leading edge motor; 1171-seventh front 1172-seventh leading-edge motor rotor; 118-fifth leading-edge connecting piece 119-sixth leading-edge connecting piece; 120-seventh leading-edge connecting piece;

201-first middle link; 202-second middle link; 203-third middle link; 204-first middle link; 205-second middle link; 206-third middle link; 207- Fourth middle connecting piece; 208-fifth middle connecting piece 209-sixth middle connecting piece; 211-first middle motor; 2111-first middle motor rotor; 2112-first middle motor stator; 212-second middle motor ; 2121 - the second middle motor stator; 2122 - the second middle motor rotor; 213 - the third middle motor; 2131 - the third middle motor stator; 2132 - the third middle motor rotor; 214 - the fourth middle motor; 2141 - the first Four middle motor stator; 2142-fourth middle motor rotor;

301-first trailing edge link; 302-second trailing edge link; 303-first trailing edge link; 304-second trailing edge link; 305-third trailing edge link; 306-fourth rear link edge connector; 311-first trailing edge motor; 3111-first trailing edge motor rotor; 3112-first trailing edge motor stator; 312-second trailing edge motor; 3121-second trailing edge motor stator; 3122-th Two trailing edge motor rotors; 313 - third trailing edge motor; 3131 - third trailing edge motor stator; 3132 - third trailing edge motor rotor.

Detailed ways

Various aspects and features of the present disclosure are described herein with reference to the accompanying drawings.

It should be understood that various modifications may be made to the embodiments claimed herein. Therefore, the above description should not be regarded as limiting, but merely as exemplifications of embodiments. Those skilled in the art will envision other modifications within the scope and spirit of this disclosure.

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the present disclosure and, together with the general description of the disclosure given above and the detailed description of the embodiments given below, serve to explain the principles of the disclosure. principle.

These and other features of the present disclosure will become apparent from the following description of preferred forms of embodiment, given as non-limiting examples, with reference to the accompanying drawings.

It is also to be understood that although the present disclosure has been described with reference to some specific examples, those skilled in the art will be able to realize many other equivalents of the present disclosure with certainty, which have the features as claimed in the claims and are therefore situated therein. within the limited scope of protection.

The above and other aspects, features and advantages of the present disclosure will become more apparent in view of the following detailed description when taken in conjunction with the accompanying drawings.

Specific embodiments of the present disclosure are hereinafter described with reference to the accompanying drawings; however, it is to be understood that the claimed embodiments are merely examples of the present disclosure, which may be embodied in various ways. Well-known and/or repeated functions and constructions have not been described in detail to avoid obscuring the present disclosure with unnecessary or redundant detail. Therefore, specific structural and functional details claimed herein are not intended to be limiting, but merely serve as a basis for the claims and a representative basis for teaching one skilled in the art to variously employ the present invention in substantially any suitable detailed structure. public.

This specification may use the phrases "in one embodiment," "in another embodiment," "in yet another embodiment," or "in other embodiments," which may all refer to the same in accordance with the present disclosure or one or more of different embodiments.

The embodiments of the present disclosure relate to a flank structure suitable for an aircraft. Here, the aircraft can achieve sailing or flying, gliding and high maneuvering actions based on movements such as swinging of the flank structure in the air or in the water. The structure of the aircraft here can be Similar bionic structures such as bionic birds, bionic fish, etc., may also be structures such as aircraft-type biplane aircraft, and the present disclosure does not limit the specific structure of the aircraft. The flank structure here can also be called "flapping wings", which are arranged at any position on the main body of the aircraft. , the present disclosure also does not limit the setting position of the flank structure.

In the embodiment of the present disclosure, the flank structure here can have a wide range of variable pitch angles, so as to achieve the effects of up and down flapping and forward and backward swinging, and the flank structure can achieve a large amount of twisting and curling in the spanwise direction. To this end, the flank structure can be realized by a multi-link structure and a combination of motor drive, and the twisting and curling of the flank structure can be realized through the cooperation of the multi-link structure and the motor. According to the number of the multi-link structures used in the flank structure, different flank structure forms can be realized, so as to realize different swing attitudes and degrees. The motor here can be an outer rotor motor or an inner rotor motor, and generally includes a stator and a rotor.

The multi-link structure is sleeved with fins to achieve a certain airfoil, and the airfoil changes in real time during movement; the overall flank structure is covered with a membrane material, which constitutes the flexible skin of the flank structure.

In the following first embodiment, the implementation of the flank structure through three multi-link structures is described in detail.

Figures 1 and 2 show a schematic structural diagram of a flank structure with three multi-link structures. In this flank structure, the leading edge, the middle and the trailing edge of the flank extend from the main body of the aircraft to the tip of the wing, respectively. The three multi-link structures are respectively the leading edge multi-link structure 1, the middle multi-link structure 2 and the trailing edge multi-link structure, which are arranged in sequence from the head to the tail of the main body of the aircraft, and the total length decreases in turn. Rod structure 3, the first ends of these three multi-link structures are all connected with the support link 10 located on the main body of the aircraft, where the support link 10 belongs to the part on the skeleton of the main body of the aircraft, and the support link 10 The direction can be consistent with the length direction of the main body of the aircraft. The three multi-link structures perform independent movements according to the control instructions, so as to better simulate the movement of the creature. A fin is set between the above-mentioned multi-link mechanisms, and the fin is composed of fin units. The fin unit can be made of rigid material. Preferably, the fin unit near the tail of the aircraft can be made of flexible material completely, or made of half rigid and half flexible material, so that the fin unit located near the tail of the aircraft has The ability to passively deform flexibly. The flank structure in the embodiment of the present disclosure has the characteristics of a widely variable airfoil in both the chordwise and spanwise directions, and has the capability of variable airfoil shape and wide range of pitch angle, and the far end of the flank structure away from the main body of the aircraft. Parts have the ability to twist in the spanwise direction, the ability to swing in a large vertical range along the plane of the aircraft body, and the ability to swing widely in the longitudinal direction of the aircraft body.

FIG. 3 shows the leading edge multi-link structure 1 located at the leading edge of the flank, which includes a first leading edge link 101 , a second leading edge link 102 , a third leading edge link 103 , and a fourth leading edge link 103 connected in sequence. The edge link 104 and the fifth leading edge link 105 , wherein the first leading edge link 101 is connected with the support link 10 , and the fifth leading edge link 105 is connected with the leading edge end flap 8 .

In order to enable the leading edge multi-link structure 1 of the leading edge of the side wing to swing with multiple degrees of freedom, the leading edge link and the support link and the adjacent leading edge links are connected by a motor. A leading edge link 101 and the support link 10 are connected by a first leading edge motor 111 and a second leading edge motor 112, and between the first leading edge link 101 and the second leading edge link 102 are connected by a third leading edge link The second leading edge link 102 and the third leading edge link 103 are connected through the fourth leading edge motor 114 and the fifth leading edge motor 115, and the third leading edge link 103 and the fourth leading edge The connecting rods 104 are connected through a sixth leading edge motor 116 , and the fourth leading edge connecting rod 104 and the fifth leading edge connecting rod 105 are connected through a seventh leading edge motor 117 . The first leading edge motor 111 and the sixth leading edge motor 116 are outer rotor motors, the second leading edge motor 112 , the third leading edge motor 113 , the fourth leading edge motor 114 , the fifth leading edge motor 115 and the seventh leading edge motor 112 The leading edge motor 117 is an inner rotor motor.

It should be noted that, in the embodiment of the present disclosure, the number of the connecting rods and the arrangement of the motors between the connecting rods can be adjusted and set according to the actual situation, and are not limited to the arrangement in the embodiment.

Further, as described above, the first leading edge link 101 and the support link 10 are connected by the first leading edge motor 111 and the second leading edge motor 112 , wherein the first leading edge motor 111 and the second leading edge motor 111 The mutual cooperation of the motors 112 can enable the flank structure to achieve the vertical swing capability along the plane where the aircraft body is located, and at the same time also enable the flank structure to achieve the longitudinal swing capability along the aircraft main body. Specifically, as shown in FIG. 4 and FIG. 5 , The first leading edge motor 111 includes a first leading edge motor rotor 1111 and a first leading edge motor stator 1112, and the second leading edge motor 112 includes a second leading edge motor stator 1121 and a second leading edge motor rotor 1122, wherein the first leading edge motor 1121 The leading edge motor stator 1112 is located in the first leading edge motor rotor 1111, the second leading edge motor rotor 1122 is located in the second leading edge motor stator 1121, and the first leading edge motor stator 1112 is connected with the support link 10, so that the first leading edge motor stator 1112 is The edge motor stator 1112 and the supporting link 10 are coaxially arranged, and the first leading edge motor rotor 1111 is connected to the second leading edge motor stator 1121 through the first leading edge connecting piece 106 , so that the first leading edge motor stator 1112 and the second leading edge motor stator 1112 are connected to each other. The directions of the motor rotors 1122 are perpendicular to each other, and a second front edge connecting member 107 is provided at the first end of the first front edge connecting rod 101 . The edge link 101 is connected, for example, the first leading edge connecting piece 106 and the second leading edge connecting piece 107 may be U-shaped connecting pieces, and the first leading edge motor rotor 1111 is fixedly arranged on two of the first leading edge connecting piece 106 Between the sides, the bottom edge of the first front edge connecting piece 106 is connected with the side surface of the second leading edge motor stator 1121 , and the second leading edge motor rotor 1122 is rotatably connected with the two sides of the second leading edge connecting piece 107 . , the bottom edge of the second leading edge connecting member 107 is connected with the first end of the first leading edge connecting rod 101 .

As described above, the first leading edge link 101 and the second leading edge link 102 are connected through the third leading edge motor 113 . Specifically, as shown in FIGS. 6 and 7 , the third leading edge motor 113 includes the first leading edge motor 113 Three leading edge motor stators 1131 and third leading edge motor rotors 1132 , wherein the third leading edge motor rotor 1132 is located in the third leading edge motor stator 1131 , and a third leading edge motor rotor 1132 is provided at the second end of the first leading edge connecting rod 101 . Leading edge connecting piece 108 , the first leading edge connecting piece 101 is connected with the third leading edge motor stator 1131 through the third leading edge connecting piece 108 , and a fourth leading edge connecting piece is provided at the first end of the second leading edge connecting piece 102 109, the third leading edge motor rotor 1132 is connected to the second leading edge link 102 through the fourth leading edge connecting piece 109, for example, the fourth leading edge connecting piece 109 is a U-shaped connecting piece, and the third leading edge motor rotor 1132 It is rotatably connected with the two sides of the fourth leading edge connecting piece 109 , and the bottom edge of the fourth leading edge connecting piece 109 is connected with the first end of the second leading edge connecting piece 102 .

As described above, the second leading edge link 102 and the third leading edge link 103 are connected through the fourth leading edge motor 114 and the fifth leading edge motor 115 , wherein the fourth leading edge motor 114 and the fifth leading edge motor The motors 115 cooperate with each other so that the distal part of the wing structure away from the aircraft body can achieve the ability to swing vertically along the plane of the wing body near the trunk end of the wing, and can also make the distal part of the wing structure away from the aircraft body to have a twist in the spanwise direction ability to swing. Specifically, as shown in FIGS. 8 and 9 , the fourth leading edge motor 114 includes a fourth leading edge motor stator 1141 and a fourth leading edge motor rotor 1142 , and the fifth leading edge motor 115 includes a fifth leading edge motor stator 1151 and a fourth leading edge motor rotor 1142 . The fifth leading edge motor rotor 1152, wherein the fourth leading edge motor rotor 1142 is located in the fourth leading edge motor stator 1141, the fifth leading edge motor rotor 1152 is located in the fifth leading edge motor stator 1151, and the second leading edge connecting rod 102 is coaxially connected to the fourth leading edge motor rotor 1142 , the fourth leading edge motor stator 1141 and the fifth leading edge motor stator 1151 are vertically connected to each other, and a fifth leading edge is provided at the first end of the third leading edge connecting rod 103 The connecting piece 118 and the fifth leading edge motor rotor 1152 are connected with the third leading edge connecting rod 103 through the fifth leading edge connecting piece 118 , so that the fifth leading edge motor 115 can make the wing structure realize the torsion action in the spanwise direction For example, the fifth leading edge connecting piece 118 is a U-shaped connecting piece, the fifth leading edge motor rotor 1152 and the two sides of the fifth leading edge connecting piece 118 are rotatably connected, and the bottom edge of the fifth leading edge connecting piece 110 Connected with the first end of the third leading edge link 103 .

As mentioned above, the third leading edge link 103 and the fourth leading edge link 104 are connected by the sixth leading edge motor 116, wherein the sixth leading edge motor 116 can make the distal part of the flank structure have a pitching motion. Specifically, as shown in FIG. 10 , the sixth leading edge motor 116 includes a sixth leading edge motor rotor 1161 and a sixth leading edge motor stator 1162 , wherein the sixth leading edge motor stator 1162 is located on the sixth leading edge motor rotor In 1161, the third leading edge link 103 is coaxially connected to the first end of the sixth leading edge motor stator 1162, and the second end of the sixth leading edge motor stator 1162 is coaxially connected to the fourth leading edge link 104 .

As described above, the fourth leading edge link 104 and the fifth leading edge link 105 are connected through the seventh leading edge motor 117 . Specifically, as shown in FIGS. 11 and 12 , the seventh leading edge motor 117 includes a Seven leading edge motor stators 1171 and seventh leading edge motor rotors 1172 , wherein the seventh leading edge motor rotor 1172 is located in the seventh leading edge motor stator 1171 , and a sixth leading edge motor is provided at the second end of the fourth leading edge connecting rod 104 The leading edge connecting piece 119 , the fourth leading edge connecting piece 104 is connected to the seventh leading edge motor stator 1171 through the sixth leading edge connecting piece 119 , and a seventh leading edge connecting piece is provided at the first end of the fifth leading edge connecting piece 105 120, the seventh leading edge motor rotor 1172 is connected to the fifth leading edge link 105 through the seventh leading edge connecting piece 120, for example, the seventh leading edge connecting piece 120 is a U-shaped connecting piece, and the seventh leading edge motor rotor 1172 It is rotatably connected with the two sides of the seventh leading edge connecting piece 120, the bottom edge of the seventh leading edge connecting piece 120 is connected with the first end of the fifth leading edge link 105, and the fifth leading edge link 105 The second end is connected to the leading edge end flap 8 .

FIG. 13 shows the middle multi-link structure located in the middle of the flank, which includes a first middle link 201 , a second middle link 202 and a third middle link 203 connected in sequence, wherein the first middle link 201 is connected to the The support link 10 is connected, and the third middle edge link 203 is connected with the middle end fin 9 .

In order to enable the middle multi-link structure in the middle of the side wings to swing with multiple degrees of freedom, the middle link and the support link and the adjacent middle links are connected by a motor. Specifically, the first middle link 101 The connection with the support link 10 is through the first middle motor 211 and the second middle motor 212 , the first middle link 201 and the second middle link 202 are connected through the third middle motor 213 , and the second middle link 202 It is connected with the third middle link 203 through the fourth middle motor 214 . The first middle motor 211 is an outer rotor motor, and the second middle motor 212 , the third middle motor 213 and the fourth middle motor 214 are inner rotor motors.

It should be noted that, in the embodiment of the present disclosure, the number of the connecting rods and the arrangement of the motors between the connecting rods can be adjusted and set according to the actual situation, and are not limited to the arrangement in the embodiment.

Further, as described above, the first middle link 201 and the support link 10 are connected by the first middle motor 211 and the second middle motor 212, and the first middle motor 211 and the second middle motor 212 cooperate with each other to make the side wings The structure achieves the ability to swing vertically along the plane where the main body of the aircraft is located, and at the same time, it can also enable the side wing structure to achieve the ability to swing longitudinally along the main body of the aircraft. Specifically, as shown in Figures 14 and 15, the first middle motor 211 includes A middle motor rotor 2111 and a first middle motor stator 2112, the second middle motor 212 includes a second middle motor stator 2121 and a second middle motor rotor 2122, wherein the first middle motor stator 2112 is located in the first middle motor rotor 2111, The second middle motor rotor 2122 is located in the second middle motor stator 2121, and the first middle motor stator 2112 is connected to the support link 10, so that the first middle motor stator 2112 and the support link 10 are coaxially arranged, and the first middle motor rotor 2111 The first middle connecting member 204 is connected to the second middle motor stator 2121 so that the directions of the first middle motor stator 2112 and the second middle motor rotor 2122 are perpendicular to each other. The middle connecting piece 205, the second middle motor stator 2121 is connected with the first middle connecting rod 101 through the second middle connecting piece 205, for example, the first middle connecting piece 204 and the second middle connecting piece 205 are U-shaped connecting pieces, the first The middle motor rotor 2111 is fixedly arranged between the two sides of the first middle connecting piece 204, the bottom edge of the first middle connecting piece 204 is connected with the side surface of the second middle motor stator 2121, and the second middle motor rotor 2122 is connected with the second middle motor stator 2121. The two sides of the middle connecting piece 205 are rotatably connected, and the bottom edge of the second middle connecting piece 205 is connected with the first end of the first middle connecting rod 201 .

As described above, the first middle link 201 and the second middle link 202 are connected by the third middle motor 213 . Specifically, as shown in FIGS. 16 and 17 , the third middle motor 213 includes a third middle motor stator 2131 and the third middle motor rotor 2132, wherein the third middle motor rotor 2132 is located in the third middle motor stator 2131, and a third middle connecting piece 206 is provided at the second end of the first middle link 201, and the first middle link 201 is connected with the third middle motor stator 2131 through the third middle connecting piece 206 , a fourth middle connecting piece 207 is provided at the first end of the second middle connecting rod 202 , and the third middle motor rotor 2132 passes through the fourth middle connecting piece 207 Connected with the second middle link 202, for example, the fourth middle link 207 is a U-shaped link, the third middle motor rotor 2132 is rotatably connected with both sides of the fourth middle link 207, and the fourth middle link The bottom edge of 207 is connected with the first end of the second middle link 202 .

As described above, the second middle link 202 and the third middle link 203 are connected by the fourth middle motor 214 , specifically, as shown in FIGS. 18 and 19 , the fourth middle motor 214 includes a fourth middle motor stator 2141 and the fourth middle motor rotor 2142, wherein the fourth middle motor rotor 2142 is located in the fourth middle motor stator 2141, and a fifth middle connecting piece 208 is provided at the second end of the second middle connecting rod 202, and the second middle connecting The rod 202 is connected with the fourth middle motor stator 2141 through the fifth middle connecting piece 208 , the sixth middle connecting piece 209 is provided at the first end of the third middle connecting rod 203 , and the fourth middle motor rotor 2142 passes through the sixth middle connecting piece 209 is connected with the third middle link 203, for example, the sixth middle connecting piece 209 is a U-shaped connecting piece, the fourth middle motor rotor 2142 is rotatably connected with the two sides of the sixth middle connecting piece 209, and the sixth middle connecting piece is connected The bottom edge of the piece 209 is connected with the first end of the third middle link 203 , and the second end of the third middle link 203 is connected with the middle end tab 9 .

FIG. 20 shows a trailing edge multi-link structure located at the trailing edge of the flank, which includes a first trailing edge link 301 and a second trailing edge link 302 connected in sequence, wherein the first trailing edge link 301 is connected with the support Rod 10 is connected.

In order to enable the trailing edge multi-link structure of the trailing edge of the flank to swing with multiple degrees of freedom, the trailing edge link and the support link and the adjacent trailing edge links are connected by a motor. Specifically, the first The trailing edge link 301 and the support link 10 are connected by the first trailing edge motor 311 and the second trailing edge motor 312, and the first trailing edge link 301 and the second trailing edge link 302 are connected by the third trailing edge Motor 313 is connected. The first trailing edge motor 311 is an outer rotor motor, and the second trailing edge motor 312 and the third trailing edge motor 313 are inner rotor motors.

It should be noted that, in the embodiment of the present disclosure, the number of the connecting rods and the arrangement of the motors between the connecting rods can be adjusted and set according to the actual situation, and are not limited to the arrangement in the embodiment.

Further, as described above, the first trailing edge link 301 and the support link 10 are connected through the first trailing edge motor 311 and the second trailing edge motor 312 , and the first trailing edge motor 311 and the second trailing edge motor 312 The mutual cooperation can enable the flank structure to achieve the vertical swing capability along the plane where the aircraft body is located, and at the same time, it can also enable the flank structure to achieve the longitudinal swing capability of the aircraft main body. Specifically, as shown in Figures 21 and 22, the first The trailing edge motor 311 includes a first trailing edge motor rotor 3111 and a first trailing edge motor stator 3112, and the second trailing edge motor 312 includes a second trailing edge motor stator 3121 and a second trailing edge motor rotor 3122, wherein the first trailing edge motor 3121 The motor stator 3112 is located in the first trailing edge motor rotor 3111, the second trailing edge motor rotor 3122 is located in the second trailing edge motor stator 3121, and the first trailing edge motor stator 3112 is connected to the support link 10, so that the first trailing edge motor The stator 3112 and the support link 10 are coaxially arranged, and the first trailing edge motor rotor 3111 is connected to the second trailing edge motor stator 3121 through the first trailing edge connecting piece 303 , so that the first trailing edge motor stator 3112 and the second trailing edge motor are connected The directions of the rotors 3122 are perpendicular to each other, a second trailing edge connecting member 304 is provided at the first end of the first trailing edge connecting rod 301 , and the second trailing edge motor stator 3121 is connected to the first trailing edge through the second trailing edge connecting member 304 The rod 301 is connected, for example, the first trailing edge connecting piece 303 and the second trailing edge connecting piece 304 are U-shaped connecting pieces, and the first trailing edge motor rotor 3111 is fixedly arranged between the two sides of the first trailing edge connecting piece 303 During the time, the bottom edge of the first trailing edge connecting piece 303 is connected with the side surface of the second trailing edge motor stator 3121, the second trailing edge motor rotor 3122 is rotatably connected with the two sides of the second trailing edge connecting piece 304, the second trailing edge connecting piece 304 The bottom edge of the trailing edge connecting member 304 is connected with the first end of the first trailing edge link 301 .

As described above, the first trailing edge link 301 and the second trailing edge link 302 are connected through the third trailing edge motor 313. Specifically, as shown in FIG. 23 and FIG. 24, the third trailing edge motor 313 includes a third trailing edge motor 313. Three trailing edge motor stators 3131 and third trailing edge motor rotors 3132 , wherein the third trailing edge motor rotor 3132 is located in the third trailing edge motor stator 3131 , and a third trailing edge connecting rod 301 is provided at the second end of the first trailing edge connecting rod 301 . The trailing edge connecting piece 305 , the first trailing edge link 301 is connected to the third trailing edge motor stator 3131 through the third trailing edge connecting piece 305 , and a fourth trailing edge connection is provided at the first end of the second trailing edge link 302 member 306, the third trailing edge motor rotor 3132 is connected to the second trailing edge link 302 through a fourth trailing edge connecting member 306, for example, the fourth trailing edge connecting member 306 is a U-shaped connecting member, and the third trailing edge motor rotor 3132 It is rotatably connected with the two sides of the fourth trailing edge connecting piece 306 , and the bottom edge of the fourth trailing edge connecting piece 306 is connected with the first end of the second trailing edge link 302 .

As shown in FIG. 1 , multiple groups of fins 4 are set between the leading edge multi-link structure 1 , the middle multi-link structure 2 and the trailing edge multi-link structure 3 , as shown in FIG. 25 , each group of fins includes At least one fin unit 5, adjacent fin units 5 are connected by a ball hinge, for example, can be connected by a ball hinge, so that the adjacent fin units 5 can rotate relative to each other; The blade unit 5 is sleeved on the corresponding link mechanism, and the number of the blade unit 5 is adjusted according to the wing width. The multi-link structure 2 and the rear-edge multi-link structure 3 are both sleeved with a fin unit 5, and at the position located in the middle of the side wing structure, the front-edge multi-link structure 1 and the middle multi-link structure 2 can be sleeved with fins As for the unit 5, the wing unit 5 can be set only on the leading edge multi-link structure 1 at the position close to the wing tip. Further, the front end and the rear end of the fin unit 5 sleeved on the same multi-link structure are connected by a fixing part, and the fixing part here can be elastic fiber wire or metal wire, so as to ensure that the fin unit 5 sleeved on the same multi-link structure is connected by a fixed part. The vane unit 5 on the multi-link structure can swing synchronously based on the corresponding multi-link structure, so as to realize the pitching motion of the side wing structure.

In order to facilitate the swinging of different link mechanisms, in one embodiment, a conical hole 6 is provided on the fin unit 5 sleeved with the leading edge multi-link structure 1 , therefore, it is sleeved with the leading edge multi-link structure 1 . The fin unit 5, as a passive fin, can swing up and down, left and right, and such a fin unit 5 can swing freely with the swing of the link mechanism; A chute 7 is set on the fin unit 5 of the link structure 3, so that the distance between the multi-link structures can be adjusted to a certain extent, so that, for example, the leading edge multi-link structure 1 and the middle multi-link structure can be adjusted. Asynchronous swing is realized between the structures 2, so as to realize the function of controlling the variable pitch angle of the flank structure; of course, in another embodiment, it is different from the vane unit 5 set in the leading edge multi-link structure 1. structure, the fin unit 5 can be set on the motor on the link mechanism as an active drive type fin, so as to be driven based on the movement of the motor. For example, as shown in Figure 26, the active drive type fin can generally be set on the side wing The position of the structure close to the wing tip; the wing unit 5 can be sleeved on the outer side of the sixth leading edge motor rotor 1161 of the sixth leading edge motor 116, and two protrusions are provided on the surface of the sixth leading edge motor rotor 1161 In order to play a limiting role, the fin unit 5 can be sleeved between the two protruding parts and restricted to move between the two protruding parts, so that the position of the fin unit 5 is relatively fixed on the sixth leading edge motor. The outer side of the rotor 1161 does not slide in the direction of the frame of the aircraft body or in the direction of the wing tip. It should be noted that the sizes of the fin units 5 sleeved on different link structures are adjusted according to the airfoil shape.

Further, considering that the first leading edge link 101 and the support link 10 are connected by the first leading edge motor 111 and the second leading edge motor 112, the first middle link 101 and the support link 10 are connected by the first leading edge motor 111 and the second leading edge motor 112. A middle motor 211 is connected to the second middle motor 212, and the first trailing edge link 301 and the support link 10 are connected through the first trailing edge motor 311 and the second trailing edge motor 312, as shown in Figures 27-30, The support link 10 includes a first segment 11 , a second segment 12 , a third segment 13 and a fourth segment 14 , wherein the two ends of the first leading edge motor stator 1112 of the first leading edge motor 111 are respectively connected to the first segment 11 . is coaxially connected to the second segment 12 , the two ends of the first middle motor stator 2112 of the first middle motor 211 are coaxially connected to the second segment 12 and the third segment 13 respectively, and the first trailing edge of the first trailing edge motor 311 Both ends of the motor stator 3112 are coaxially connected to the third segment 13 and the fourth segment 14 respectively.

With the flank structure of this embodiment, when the first leading edge motor 111 , the third leading edge motor 113 , the fifth leading edge motor 115 and the seventh leading edge motor 117 are rotated, the corresponding central motors rotate in the same direction, so that the corresponding The connecting rod swings up and down, thereby realizing the up and down swing of the flank structure; when the second leading edge motor 112, the second middle motor 212 and the second trailing edge motor 312 are used to swing synchronously, the front and rear swing of the flank structure is realized; The leading edge motor 114 rotates to effect the twisting of the end portion of the flank structure.

Embodiments of the present disclosure provide flank structures that feature a widely variable airfoil in both chordwise and spanwise directions, the flank structure having variable airfoil shape, the ability to vary widely in pitch angle, along the wingspan at the distal end portion The ability to twist in the direction, the ability to swing vertically in a large range along the plane where the main body of the vehicle is located, and the ability to swing longitudinally in a large range along the main body of the vehicle, can be adjusted for complex flow fields or environments, and the movement speed can be greatly improved and exercise efficiency, and can achieve high maneuverability.

In the following second embodiment, the implementation of the flank structure through two multi-link structures is described in detail.

Figure 31, Figure 32 and Figure 33 respectively show the structural schematic diagram of the flank structure with two multi-link structures. In this flank structure, the leading edge and the middle part of the flank respectively extend from the aircraft main body to the wing tip direction. Two multi-link structures are arranged, namely, the leading edge multi-link structure 1 and the middle multi-link structure 2, which are arranged in sequence from the head to the tail of the main body of the aircraft, and the total length decreases in turn. The first end of the link structure is connected to the support link 10 located on the main body of the aircraft, and the direction of the support link 10 is consistent with the depth direction of the main body of the aircraft. The two multi-link structures are independent according to the control instructions. to better simulate the movement of the creature; a fin is set between the above-mentioned multi-link mechanisms, and the fin is composed of a fin unit, wherein the fin unit can usually be made of rigid materials. The fin unit near the tail of the aircraft can be made entirely of flexible material, or made of half rigid and half flexible material, so that the fin unit located near the tail of the aircraft has the ability to passively deform flexibly. The flank structure in the embodiment of the present disclosure has the characteristics of a widely variable airfoil in both the chordwise and spanwise directions, and has the capability of variable airfoil shape and wide range of pitch angle, and the far end of the flank structure away from the main body of the aircraft. Parts have the ability to twist in the spanwise direction, the ability to swing in a large vertical range along the plane of the aircraft body, and the ability to swing widely in the longitudinal direction of the aircraft body.

Fig. 34 shows the leading edge multi-link structure located at the leading edge of the flank, which includes a first leading edge link 101, a second leading edge link 102, a third leading edge link 103, and a fourth leading edge connected in sequence The connecting rod 104 and the fifth leading edge link 105 , wherein the first leading edge link 101 is connected with the support link 10 , and the fifth leading edge link 105 is connected with the leading edge end flap 8 .

In order to enable the leading edge multi-link structure of the leading edge of the flank to swing with multiple degrees of freedom, the leading edge link and the support link and the adjacent leading edge links are connected by a motor. Specifically, the first The leading edge link 101 and the support link 10 are connected by the first leading edge motor 111 and the second leading edge motor 112, and the first leading edge link 101 and the second leading edge link 102 are connected by the third leading edge The motor 113 is connected, the second leading edge link 102 and the third leading edge link 103 are connected through the fourth leading edge motor 114 and the fifth leading edge motor 115, and the third leading edge link 103 is connected with the fourth leading edge. The rods 104 are connected through a sixth leading edge motor 116 , and the fourth leading edge link 104 and the fifth leading edge link 105 are connected through a seventh leading edge motor 117 . The first leading edge motor 111 and the sixth leading edge motor 116 are outer rotor motors, the second leading edge motor 112 , the third leading edge motor 113 , the fourth leading edge motor 114 , the fifth leading edge motor 115 and the seventh leading edge motor 112 The leading edge motor 117 is an inner rotor motor.

It should be noted that, in the embodiment of the present disclosure, the number of the connecting rods and the arrangement of the motors between the connecting rods can be adjusted and set according to the actual situation, and are not limited to the arrangement in the embodiment.

Further, as described above, the first leading edge link 101 and the support link 10 are connected through the first leading edge motor 111 and the second leading edge motor 112 , and the first leading edge motor 111 and the second leading edge motor 112 The mutual cooperation can enable the flank structure to achieve the vertical swing ability along the plane where the aircraft body is located, and at the same time, it can also enable the flank structure to achieve the longitudinal swing ability of the aircraft main body. Specifically, as shown in Figures 35 and 36, the first The leading edge motor 111 includes a first leading edge motor rotor 1111 and a first leading edge motor stator 1112, and the second leading edge motor 112 includes a second leading edge motor stator 1121 and a second leading edge motor rotor 1122, wherein the first leading edge motor The motor stator 1112 is located in the first leading edge motor rotor 1111, the second leading edge motor rotor 1122 is located in the second leading edge motor stator 1121, and the first leading edge motor stator 1112 is connected with the support link 10, so that the first leading edge motor The stator 1112 and the support link 10 are coaxially arranged, and the first leading edge motor rotor 1111 is connected to the second leading edge motor stator 1121 through the first leading edge connecting piece 106 , so that the first leading edge motor stator 1112 and the second leading edge motor are connected The directions of the rotors 1122 are perpendicular to each other, a second leading edge connecting member 107 is provided at the first end of the first leading edge link 101 , and the second leading edge motor stator 1121 is connected to the first leading edge link through the second leading edge connecting member 107 101 connection, for example, the first leading edge connecting piece 106 and the second leading edge connecting piece 107 may be U-shaped connecting pieces, and the first leading edge motor rotor 1111 is fixedly arranged between the two sides of the first leading edge connecting piece 106. During the time, the bottom edge of the first front edge connector 106 is connected with the side surface of the second front edge motor stator 1121, the second front edge motor rotor 1122 is rotatably connected with the two sides of the second front edge connector 107, and the second front edge motor rotor 1122 The bottom edge of the leading edge connecting piece 107 is connected with the first end of the first leading edge link 101 .

As described above, the first leading edge link 101 and the second leading edge link 102 are connected through the third leading edge motor 113 . Specifically, as shown in FIGS. 37 and 38 , the third leading edge motor 113 includes the first leading edge motor 113 Three leading edge motor stators 1131 and third leading edge motor rotors 1132 , wherein the third leading edge motor rotor 1132 is located in the third leading edge motor stator 1131 , and a third leading edge motor rotor 1132 is provided at the second end of the first leading edge connecting rod 101 . Leading edge connecting piece 108 , the first leading edge connecting piece 101 is connected with the third leading edge motor stator 1131 through the third leading edge connecting piece 108 , and a fourth leading edge connecting piece is provided at the first end of the second leading edge connecting piece 102 109, the third leading edge motor rotor 1132 is connected to the second leading edge link 102 through the fourth leading edge connecting piece 109, for example, the fourth leading edge connecting piece 109 is a U-shaped connecting piece, and the third leading edge motor rotor 1132 It is rotatably connected with the two sides of the fourth leading edge connecting piece 109 , and the bottom edge of the fourth leading edge connecting piece 109 is connected with the first end of the second leading edge connecting piece 102 .

As described above, the second leading edge link 102 and the third leading edge link 103 are connected through the fourth leading edge motor 114 and the fifth leading edge motor 115 , wherein the fourth leading edge motor 114 and the fifth leading edge motor The motors 115 cooperate with each other so that the distal part of the wing structure away from the aircraft body can achieve the ability to swing vertically along the plane of the wing body near the trunk end of the wing, and can also make the distal part of the wing structure away from the aircraft body to have a twist in the spanwise direction ability to swing. Specifically, as shown in FIGS. 39 and 40 , the fourth leading edge motor 114 includes a fourth leading edge motor stator 1141 and a fourth leading edge motor rotor 1142 , and the fifth leading edge motor 115 includes a fifth leading edge motor stator 1151 and a fourth leading edge motor rotor 1142 . The fifth leading edge motor rotor 1152, wherein the fourth leading edge motor rotor 1142 is located in the fourth leading edge motor stator 1141, the fifth leading edge motor rotor 1152 is located in the fifth leading edge motor stator 1151, and the second leading edge connecting rod 102 is coaxially connected to the fourth leading edge motor rotor 1142 , the fourth leading edge motor stator 1141 and the fifth leading edge motor stator 1151 are vertically connected to each other, and a fifth leading edge is provided at the first end of the third leading edge connecting rod 103 The connecting piece 118 and the fifth leading edge motor rotor 1152 are connected with the third leading edge connecting rod 103 through the fifth leading edge connecting piece 118 , so that the fifth leading edge motor 115 can make the wing structure realize the torsion action in the spanwise direction For example, the fifth leading edge connecting piece 118 is a U-shaped connecting piece, the fifth leading edge motor rotor 1152 and the two sides of the fifth leading edge connecting piece 118 are rotatably connected, and the bottom edge of the fifth leading edge connecting piece 110 Connected with the first end of the third leading edge link 103 .

As mentioned above, the third leading edge link 103 and the fourth leading edge link 104 are connected by the sixth leading edge motor 116, wherein the sixth leading edge motor 116 can make the distal part of the flank structure have a pitching motion. Specifically, as shown in FIG. 41 , the sixth leading edge motor 116 includes a sixth leading edge motor rotor 1161 and a sixth leading edge motor stator 1162 , wherein the sixth leading edge motor stator 1162 is located on the sixth leading edge motor rotor In 1161, the third leading edge link 103 is coaxially connected to the first end of the sixth leading edge motor stator 1162, and the second end of the sixth leading edge motor stator 1162 is coaxially connected to the fourth leading edge link 104 .

As described above, the fourth leading edge link 104 and the fifth leading edge link 105 are connected through the seventh leading edge motor 117 . Specifically, as shown in FIGS. 42 and 43 , the seventh leading edge motor 117 includes a Seven leading edge motor stators 1171 and seventh leading edge motor rotors 1172 , wherein the seventh leading edge motor rotor 1172 is located in the seventh leading edge motor stator 1171 , and a sixth leading edge motor is provided at the second end of the fourth leading edge connecting rod 104 The leading edge connecting piece 119 , the fourth leading edge connecting piece 104 is connected to the seventh leading edge motor stator 1171 through the sixth leading edge connecting piece 119 , and a seventh leading edge connecting piece is provided at the first end of the fifth leading edge connecting piece 105 120, the seventh leading edge motor rotor 1172 is connected to the fifth leading edge link 105 through the seventh leading edge connecting piece 120, for example, the seventh leading edge connecting piece 120 is a U-shaped connecting piece, and the seventh leading edge motor rotor 1172 It is rotatably connected with the two sides of the seventh leading edge connecting piece 120, the bottom edge of the seventh leading edge connecting piece 120 is connected with the first end of the fifth leading edge link 105, and the fifth leading edge link 105 The second end is connected to the leading edge end flap 8 .

Fig. 44 shows the middle multi-link structure located in the middle of the flank, which includes a first middle link 201, a second middle link 202 and a third middle link 203 connected in sequence, wherein the first middle link 201 is connected to the The support link 10 is connected, and the third middle edge link 203 is connected with the middle end fin 9 .

In order to enable the middle multi-link structure in the middle of the side wings to swing with multiple degrees of freedom, the middle link and the support link and the adjacent middle links are connected by a motor. Specifically, the first middle link 101 The connection with the support link 10 is through the first middle motor 211 and the second middle motor 212 , the first middle link 201 and the second middle link 202 are connected through the third middle motor 213 , and the second middle link 202 It is connected with the third middle link 203 through the fourth middle motor 214 . The first middle motor 211 is an outer rotor motor, and the second middle motor 212 , the third middle motor 213 and the fourth middle motor 214 are inner rotor motors.

It should be noted that, in the embodiment of the present disclosure, the number of the connecting rods and the arrangement of the motors between the connecting rods can be adjusted and set according to the actual situation, and are not limited to the arrangement in the embodiment.

Further, as described above, the first middle link 201 and the support link 10 are connected by the first middle motor 211 and the second middle motor 212, and the first middle motor 211 and the second middle motor 212 cooperate with each other to make the side wings The structure realizes the ability to swing vertically along the plane where the main body of the aircraft is located, and at the same time, it can also make the wing structure realize the ability to swing longitudinally along the main body of the aircraft. Specifically, as shown in FIG. 45 and FIG. A middle motor rotor 2111 and a first middle motor stator 2112, the second middle motor 212 includes a second middle motor stator 2121 and a second middle motor rotor 2122, wherein the first middle motor stator 2112 is located in the first middle motor rotor 2111, The second middle motor rotor 2122 is located in the second middle motor stator 2121, and the first middle motor stator 2112 is connected to the support link 10, so that the first middle motor stator 2112 and the support link 10 are coaxially arranged, and the first middle motor rotor 2111 The first middle connecting member 204 is connected to the second middle motor stator 2121 so that the directions of the first middle motor stator 2112 and the second middle motor rotor 2122 are perpendicular to each other. The middle connecting piece 205, the second middle motor stator 2121 is connected with the first middle connecting rod 101 through the second middle connecting piece 205, for example, the first middle connecting piece 204 and the second middle connecting piece 205 are U-shaped connecting pieces, the first The middle motor rotor 2111 is fixedly arranged between the two sides of the first middle connecting piece 204, the bottom edge of the first middle connecting piece 204 is connected with the side surface of the second middle motor stator 2121, and the second middle motor rotor 2122 is connected with the second middle motor stator 2121. The two sides of the middle connecting piece 205 are rotatably connected, and the bottom edge of the second middle connecting piece 205 is connected with the first end of the first middle connecting rod 201 .

As described above, the first middle link 201 and the second middle link 202 are connected by the third middle motor 213 . Specifically, as shown in FIGS. 47 and 48 , the third middle motor 213 includes a third middle motor stator 2131 and the third middle motor rotor 2132, wherein the third middle motor rotor 2132 is located in the third middle motor stator 2131, and a third middle connecting piece 206 is provided at the second end of the first middle link 201, and the first middle link 201 is connected with the third middle motor stator 2131 through the third middle connecting piece 206 , a fourth middle connecting piece 207 is provided at the first end of the second middle connecting rod 202 , and the third middle motor rotor 2132 passes through the fourth middle connecting piece 207 Connected with the second middle link 202, for example, the fourth middle link 207 is a U-shaped link, the third middle motor rotor 2132 is rotatably connected with both sides of the fourth middle link 207, and the fourth middle link The bottom edge of 207 is connected with the first end of the second middle link 202 .

As described above, the second middle link 202 and the third middle link 203 are connected through the fourth middle motor 214. Specifically, as shown in FIGS. 49 and 50 , the fourth middle motor 214 includes a fourth middle motor stator 2141 and the fourth middle motor rotor 2142, wherein the fourth middle motor rotor 2142 is located in the fourth middle motor stator 2141, and a fifth middle connecting piece 208 is provided at the second end of the second middle connecting rod 202, and the second middle connecting The rod 202 is connected with the fourth middle motor stator 2141 through the fifth middle connecting piece 208 , the sixth middle connecting piece 209 is provided at the first end of the third middle connecting rod 203 , and the fourth middle motor rotor 2142 passes through the sixth middle connecting piece 209 is connected with the third middle link 203, for example, the sixth middle connecting piece 209 is a U-shaped connecting piece, the fourth middle motor rotor 2142 is rotatably connected with the two sides of the sixth middle connecting piece 209, and the sixth middle connecting piece is connected The bottom edge of the piece 209 is connected with the first end of the third middle link 203 , and the second end of the third middle link 203 is connected with the middle end tab 9 .

31-33, multiple sets of fins 4 are sleeved between the leading edge multi-link structure 1 and the middle multi-link structure 2, as shown in Figure 51, each set of fins includes at least one fin unit 5 , the adjacent fin units 5 are connected by a ball hinge, for example, they can be connected by a ball hinge, so that the adjacent fin units 5 can rotate relative to each other; each fin unit 5 is sleeved on the On the corresponding link mechanism, the number of wing units 5 is adjusted according to the wing width. For example, at the position close to the support link 10 of the main body of the aircraft and at the position in the middle of the flank structure, the multi-link structure 1 on the leading edge can be used. The fin unit 5 is sleeved on the multi-link structure 2 and the middle part, and the fin unit 5 can be sleeved only on the leading edge multi-link structure 1 at the position close to the wing tip. Further, the front end and the rear end of the fin unit 5 sleeved on the same multi-link structure are connected by a fixing part, and the fixing part here can be elastic fiber wire or metal wire, so as to ensure that the fin unit 5 sleeved on the same multi-link structure is connected by a fixed part. The vane unit 5 on the multi-link structure can swing synchronously based on the corresponding multi-link structure, so as to realize the pitching motion of the side wing structure.

In order to facilitate the swinging of different link mechanisms, in one embodiment, a conical hole 6 is provided on the fin unit 5 sleeved with the leading edge multi-link structure 1 , therefore, it is sleeved with the leading edge multi-link structure 1 . The fin unit 5 can swing up, down, left and right as a passive fin, and such a fin unit 5 can swing freely with the swing of the link mechanism; A chute 7 is provided on the 5, so that the distance between the multi-link structures can be adjusted to a certain extent, so that for example, the front edge multi-link structure 1 and the middle multi-link structure 2 can achieve asynchronous swing, In order to realize the function of controlling the variable pitch angle of the flank structure; of course, in another embodiment, the fin unit 5 set with the leading edge multi-link structure 1 has a different structure, and the fin unit 5 is an active drive type. The fins can be sleeved on the motor on the link mechanism so as to be driven based on the motion of the motor. For example, as shown in Figure 52, the actively driven fins can generally be set at a position close to the wing tip of the flank structure; The unit 5 can be sleeved on the outer side of the sixth leading edge motor rotor 1161 of the sixth leading edge motor 116, and two protrusions are provided on the surface of the sixth leading edge motor rotor 1161 to play a limiting role, and the fin unit 5 can be sleeved between the two protruding parts and limited to move between the two protruding parts, so that the position of the vane unit 5 is relatively fixed on the outside of the sixth leading edge motor rotor 1161 and will not move toward the aircraft. The main body's skeletal direction or sliding towards the wingtips. It should be noted that the sizes of the fin units 5 sleeved on different link structures are adjusted according to the airfoil shape.

Further, considering that the first leading edge link 101 and the support link 10 are connected by the first leading edge motor 111 and the second leading edge motor 112, the first middle link 101 and the support link 10 are connected by the first leading edge motor 111 and the second leading edge motor 112. A middle motor 211 and a second middle motor 212 are connected. As shown in FIGS. 53-55 , the support link 10 includes a first section 11 , a second section 12 and a third section 13 , wherein the first leading edge motor 111 has a first section 11 , a second section 12 and a third section 13 Both ends of a leading edge motor stator 1112 are coaxially connected to the first segment 11 and the second segment 12 respectively, and both ends of the first middle motor stator 2112 of the first middle motor 211 are respectively connected to the second segment 12 and the third segment 13 Coaxial connection.

With the flank structure of this embodiment, when the first leading edge motor 111 , the third leading edge motor 113 , the fifth leading edge motor 115 and the seventh leading edge motor 117 are rotated, the corresponding central motors rotate in the same direction, so that the corresponding The connecting rod swings up and down, thereby realizing the up and down swing of the side wing structure; when the second leading edge motor 112 and the second middle motor 212 are used to synchronously swing, the back and forth swing of the side wing structure is realized; when the fourth leading edge motor 114 is used to rotate, the The end portions of the flanking structures are twisted.

Embodiments of the present disclosure provide flank structures that feature a widely variable airfoil in both chordwise and spanwise directions, the flank structure having variable airfoil shape, the ability to vary widely in pitch angle, along the wingspan at the distal end portion The ability to twist in the direction, the ability to swing vertically in a large range along the plane where the main body of the vehicle is located, and the ability to swing longitudinally in a large range along the main body of the vehicle, can be adjusted for complex flow fields or environments, and the movement speed can be greatly improved and exercise efficiency, and can achieve high maneuverability.

In the following third embodiment, the implementation of the flank structure through a multi-link structure is described in detail.

Fig. 56, Fig. 57 and Fig. 58 respectively show the schematic structural diagrams of the flank structure with a multi-link structure. In this flank structure, a multi-link is arranged on the leading edge of the flank extending from the aircraft body to the wing tip direction. The structure is the leading edge multi-link structure 1. The first end of this multi-link structure is connected to the support link 10 located on the main body of the aircraft, and the direction of the support link 10 is consistent with the depth direction of the main body of the aircraft. . The above-mentioned multi-link structure performs independent movement according to the control command, so as to better simulate the movement of the living beings. The above-mentioned multi-link structure is sleeved with fins, and the fins are composed of fin units, wherein the fin units can usually be selected. It is made of rigid material. Preferably, the wing unit near the tail of the aircraft can be made of flexible material completely, or made of half rigid and half flexible material, so that the wing unit near the tail of the aircraft has the ability of passive flexible deformation . The flank structure in the embodiment of the present disclosure has the characteristics of a widely variable airfoil in both the chordwise and spanwise directions, and has the capability of variable airfoil shape and wide range of pitch angle, and the far end of the flank structure away from the main body of the aircraft. Parts have the ability to twist in the spanwise direction, the ability to swing in a large vertical range along the plane of the aircraft body, and the ability to swing widely in the longitudinal direction of the aircraft body.

Fig. 59 shows the leading edge multi-link structure located at the leading edge of the flank, which includes a first leading edge link 101, a second leading edge link 102, a third leading edge link 103, and a fourth leading edge connected in sequence The connecting rod 104 and the fifth leading edge link 105 , wherein the first leading edge link 101 is connected with the support link 10 , and the fifth leading edge link 105 is connected with the leading edge end flap 8 .

In order to enable the leading edge multi-link structure of the leading edge of the flank to swing with multiple degrees of freedom, the leading edge link and the support link and the adjacent leading edge links are connected by a motor. Specifically, the first The leading edge link 101 and the support link 10 are connected by the first leading edge motor 111 and the second leading edge motor 112, and the first leading edge link 101 and the second leading edge link 102 are connected by the third leading edge The motor 113 is connected, the second leading edge link 102 and the third leading edge link 103 are connected through the fourth leading edge motor 114 and the fifth leading edge motor 115, and the third leading edge link 103 is connected with the fourth leading edge. The rods 104 are connected through a sixth leading edge motor 116 , and the fourth leading edge link 104 and the fifth leading edge link 105 are connected through a seventh leading edge motor 117 . The first leading edge motor 111 and the sixth leading edge motor 116 are outer rotor motors, the second leading edge motor 112 , the third leading edge motor 113 , the fourth leading edge motor 114 , the fifth leading edge motor 115 and the seventh leading edge motor 112 The leading edge motor 117 is an inner rotor motor.

It should be noted that, in the embodiment of the present disclosure, the number of the connecting rods and the arrangement of the motors between the connecting rods can be adjusted and set according to the actual situation, and are not limited to the arrangement in the embodiment.

Further, as described above, the first leading edge link 101 and the support link 10 are connected through the first leading edge motor 111 and the second leading edge motor 112 , and the first leading edge motor 111 and the second leading edge motor 112 The mutual cooperation can enable the side wing structure to achieve the vertical swing capability along the plane where the aircraft body is located, and at the same time, it can also enable the side wing structure to realize the longitudinal swing capability of the aircraft body. Specifically, as shown in Figures 60 and 61, the first The leading edge motor 111 includes a first leading edge motor rotor 1111 and a first leading edge motor stator 1112, and the second leading edge motor 112 includes a second leading edge motor stator 1121 and a second leading edge motor rotor 1122, wherein the first leading edge motor The motor stator 1112 is located in the first leading edge motor rotor 1111, the second leading edge motor rotor 1122 is located in the second leading edge motor stator 1121, and the first leading edge motor stator 1112 is connected with the support link 10, so that the first leading edge motor The stator 1112 and the support link 10 are coaxially arranged, and the first leading edge motor rotor 1111 is connected to the second leading edge motor stator 1121 through the first leading edge connecting piece 106 , so that the first leading edge motor stator 1112 and the second leading edge motor are connected The directions of the rotors 1122 are perpendicular to each other, a second leading edge connecting member 107 is provided at the first end of the first leading edge link 101 , and the second leading edge motor stator 1121 is connected to the first leading edge link through the second leading edge connecting member 107 101 connection, for example, the first leading edge connecting piece 106 and the second leading edge connecting piece 107 may be U-shaped connecting pieces, and the first leading edge motor rotor 1111 is fixedly arranged between the two sides of the first leading edge connecting piece 106. During the time, the bottom edge of the first front edge connector 106 is connected with the side surface of the second front edge motor stator 1121, the second front edge motor rotor 1122 is rotatably connected with the two sides of the second front edge connector 107, and the second front edge motor rotor 1122 The bottom edge of the leading edge connecting piece 107 is connected with the first end of the first leading edge link 101 .

As described above, the first leading edge link 101 and the second leading edge link 102 are connected through the third leading edge motor 113. Specifically, as shown in FIG. 62 and FIG. 63, the third leading edge motor 113 includes the first leading edge motor 113. Three leading edge motor stators 1131 and third leading edge motor rotors 1132 , wherein the third leading edge motor rotor 1132 is located in the third leading edge motor stator 1131 , and a third leading edge motor rotor 1132 is provided at the second end of the first leading edge connecting rod 101 . Leading edge connecting piece 108 , the first leading edge connecting piece 101 is connected with the third leading edge motor stator 1131 through the third leading edge connecting piece 108 , and a fourth leading edge connecting piece is provided at the first end of the second leading edge connecting piece 102 109, the third leading edge motor rotor 1132 is connected to the second leading edge link 102 through the fourth leading edge connecting piece 109, for example, the fourth leading edge connecting piece 109 is a U-shaped connecting piece, and the third leading edge motor rotor 1132 It is rotatably connected with the two sides of the fourth leading edge connecting piece 109 , and the bottom edge of the fourth leading edge connecting piece 109 is connected with the first end of the second leading edge connecting piece 102 .

As described above, the second leading edge link 102 and the third leading edge link 103 are connected through the fourth leading edge motor 114 and the fifth leading edge motor 115 , wherein the fourth leading edge motor 114 and the fifth leading edge motor The motors 115 cooperate with each other so that the distal part of the wing structure away from the aircraft body can achieve the ability to swing vertically along the plane of the wing body near the trunk end of the wing, and can also make the distal part of the wing structure away from the aircraft body to have a twist in the spanwise direction ability to swing. Specifically, as shown in FIGS. 64 and 65 , the fourth leading edge motor 114 includes a fourth leading edge motor stator 1141 and a fourth leading edge motor rotor 1142 , and the fifth leading edge motor 115 includes a fifth leading edge motor stator 1151 and a fourth leading edge motor rotor 1142 . The fifth leading edge motor rotor 1152, wherein the fourth leading edge motor rotor 1142 is located in the fourth leading edge motor stator 1141, the fifth leading edge motor rotor 1152 is located in the fifth leading edge motor stator 1151, and the second leading edge connecting rod 102 is coaxially connected to the fourth leading edge motor rotor 1142 , the fourth leading edge motor stator 1141 and the fifth leading edge motor stator 1151 are vertically connected to each other, and a fifth leading edge is provided at the first end of the third leading edge connecting rod 103 The connecting piece 118 and the fifth leading edge motor rotor 1152 are connected with the third leading edge connecting rod 103 through the fifth leading edge connecting piece 118 , so that the fifth leading edge motor 115 can make the wing structure realize the torsion action in the spanwise direction For example, the fifth leading edge connecting piece 118 is a U-shaped connecting piece, the fifth leading edge motor rotor 1152 and the two sides of the fifth leading edge connecting piece 118 are rotatably connected, and the bottom edge of the fifth leading edge connecting piece 110 Connected with the first end of the third leading edge link 103 .

As mentioned above, the third leading edge link 103 and the fourth leading edge link 104 are connected by the sixth leading edge motor 116, wherein the sixth leading edge motor 116 can make the distal part of the flank structure have a pitching motion. Specifically, as shown in FIG. 66, the sixth leading edge motor 116 includes a sixth leading edge motor rotor 1161 and a sixth leading edge motor stator 1162, wherein the sixth leading edge motor stator 1162 is located on the sixth leading edge motor rotor In 1161, the third leading edge link 103 is coaxially connected to the first end of the sixth leading edge motor stator 1162, and the second end of the sixth leading edge motor stator 1162 is coaxially connected to the fourth leading edge link 104 .

As described above, the fourth leading edge link 104 and the fifth leading edge link 105 are connected through the seventh leading edge motor 117. Specifically, as shown in FIG. 67 and FIG. 68 , the seventh leading edge motor 117 includes the seventh leading edge motor 117. Seven leading edge motor stators 1171 and seventh leading edge motor rotors 1172 , wherein the seventh leading edge motor rotor 1172 is located in the seventh leading edge motor stator 1171 , and a sixth leading edge motor is provided at the second end of the fourth leading edge connecting rod 104 The leading edge connecting piece 119 , the fourth leading edge connecting piece 104 is connected to the seventh leading edge motor stator 1171 through the sixth leading edge connecting piece 119 , and a seventh leading edge connecting piece is provided at the first end of the fifth leading edge connecting piece 105 120, the seventh leading edge motor rotor 1172 is connected to the fifth leading edge link 105 through the seventh leading edge connecting piece 120, for example, the seventh leading edge connecting piece 120 is a U-shaped connecting piece, and the seventh leading edge motor rotor 1172 It is rotatably connected with the two sides of the seventh leading edge connecting piece 120, the bottom edge of the seventh leading edge connecting piece 120 is connected with the first end of the fifth leading edge link 105, and the fifth leading edge link 105 The second end is connected to the leading edge end flap 8 .

56-58, multiple sets of fins 4 are sleeved on the leading edge multi-link structure 1. As shown in Figure 57, each set of fins 4 includes a fin unit 5, and the number of fin units 5 is based on The wing width is adjusted; further, the front end and the rear end of the fin unit 5 sleeved on the leading edge multi-link structure 1 are connected by a fixed part, and the fixed part here can be an elastic fiber wire or a metal wire to It is ensured that the wing unit 5 sleeved on the same multi-link structure can swing synchronously based on the corresponding multi-link structure, so as to realize the pitching motion of the side wing structure.

In order to facilitate the swinging of different link mechanisms, in one embodiment, as shown in FIG. 69 , a conical hole 6 is set on the fin unit 5 sleeved with the leading edge multi-link structure 1. The fin unit 5 sleeved by the link structure 1 can swing up, down, left and right as a passive fin, and such a fin unit 5 can swing freely with the swing of the link mechanism; of course, in another embodiment, with the The fin unit 5 set in the leading edge multi-link structure 1 has different structures. The fin unit 5 can be set on the motor on the link mechanism as an active driving type fin, so as to realize the driving based on the movement of the motor, For example, as shown in FIG. 70 , the active driving type fins can generally be arranged at the wing tips of the flank structure; Two protrusions are provided on the surface of the rotor 1161 of the six leading edge motor to play a limiting role, and the fin unit 5 can be sleeved between the two protrusions and limited to move between the two protrusions, so that The position of the vane unit 5 is relatively fixed on the outer side of the sixth leading edge motor rotor 1161 without sliding in the direction of the frame of the aircraft body or the direction of the wing tip. It should be noted that the sizes of the fin units 5 sleeved on different link structures are adjusted according to the airfoil shape.

Further, considering that the first leading edge link 101 and the support link 10 are connected by the first leading edge motor 111 and the second leading edge motor 112, as shown in FIGS. 71 and 72, the support link 10 includes a first leading edge motor 111 and a second leading edge motor 112. Section 11 and second section 12, wherein both ends of the first leading edge motor stator 1112 of the first leading edge motor 111 are coaxially connected to the first section 11 and the second section 12, respectively.

With the flank structure of this embodiment, when the first leading edge motor 111 , the third leading edge motor 113 , the fifth leading edge motor 115 and the seventh leading edge motor 117 are rotated, the corresponding connecting rods swing up and down, thereby realizing The side wing structure swings up and down; when the fourth leading edge motor 114 and the sixth leading edge motor 116 are used to synchronously swing, the pitch motion of the side wing structure is realized; when the fourth leading edge motor 114 is used to rotate, the end part of the side wing structure is twisted.

Embodiments of the present disclosure provide flank structures that feature a widely variable airfoil in both chordwise and spanwise directions, the flank structure having variable airfoil shape, the ability to vary widely in pitch angle, along the wingspan at the distal end portion The ability to twist in the direction, the ability to swing vertically in a large range along the plane where the main body of the vehicle is located, and the ability to swing longitudinally in a large range along the main body of the vehicle, can be adjusted for complex flow fields or environments, and the movement speed can be greatly improved and exercise efficiency, and can achieve high maneuverability.

The above embodiments are only exemplary embodiments of the present disclosure, and are not intended to limit the present disclosure, and the protection scope of the present disclosure is defined by the claims. Those skilled in the art can make various modifications or equivalent replacements to the present disclosure within the spirit and protection scope of the present disclosure, and such modifications or equivalent replacements should also be regarded as falling within the protection scope of the present disclosure.

Claims (10)

1. A flank structure for an aircraft, characterized by comprising a plurality of multi-link structures, each of the multi-link structures extending from the main body of the aircraft to the wingtip direction, and a plurality of the multi-link structures. The structures are arranged in sequence from the head to the tail of the main body of the aircraft and the total length decreases in sequence, The first end of the first link of the multi-link structure and the support link on the main body of the aircraft are connected by a first motor and a second motor, and the stator of the first motor is connected to the support The connecting rods are coaxially connected, and the rotor of the first motor is connected to the stator of the second motor through a first connecting piece, so that the directions of the stator of the first motor and the rotor of the second motor are perpendicular to each other, and the stator of the second motor is The second connecting piece is connected with the first connecting rod, so that the side wing structure can swing vertically along the plane where the aircraft body is located, and the side wing structure can swing in the longitudinal direction of the aircraft body; A plurality of the multi-link structures are configured to perform independent movements respectively according to control instructions, so that asynchronous swings can be performed among the plurality of the multi-link structures, so that the pitch angles of the side wing structures are variable; Each of the multi-link structures includes a plurality of links connected in sequence from the main body of the aircraft to the wingtip direction, and the adjacent links are connected by a motor; The interconnection between the connecting rod and the motor can also realize the following changes or movements of the flank structure: The airfoil is variable and the distal portion is spanwise twistable. 2 . The flank structure according to claim 1 , wherein the support link is consistent with the length direction of the aircraft main body. 3 . 3 . The side wing structure according to claim 1 , wherein the second end of the multi-link structure is connected to the end wing. 4 . 4 . The side wing structure according to claim 1 , wherein a plurality of groups of fins are sleeved on the multi-link structure, and each group of the fins includes at least one fin unit. 5 . 5 . The side wing structure according to claim 4 , wherein the number of the fin units in each group of the fins is less than or equal to the number of the multi-link structure. 6 . 6 . The side wing structure according to claim 4 , wherein in the same group of the fins, the adjacent fin units are connected by means of spherical hinges. 7 . 7 . The side wing structure according to claim 4 , wherein the front ends or the rear ends of all the wing units sleeved on the same multi-link structure are connected by a fixed part. 8 . 8 . The side wing structure according to claim 7 , wherein the fixing portion is an elastic fiber wire or a metal wire. 9 . 9 . The side wing structure according to claim 4 , wherein a conical hole or a chute is arranged on the wing unit. 10 . 10. An aircraft employing the flank structure of any one of claims 1-9.

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