CN218641060U - Combined aircraft wingtip connecting and separating mechanism and combined aircraft - Google Patents

Abstract

The utility model provides a modular aircraft wingtip connection and separation mechanism and modular aircraft, first wingtip hinge mount pad has first guide way, first and second locking recess, first spring assembly and first spring bolt group are connected, first connecting rod and the cooperation of first locking recess alternative, second connecting rod and the cooperation of second locking recess alternative, first lockpin has first lockpin bank, second wingtip hinge mount pad has the second guide way, third locking recess and fourth locking recess, second spring assembly and second spring bolt group are connected, third connecting rod and the cooperation of third locking recess alternative, fourth connecting rod and the cooperation of fourth locking recess alternative, the second lockpin has second lockpin bank of cells, second lockpin bank of cells and the cooperation of first spring bolt group alternative, first lockpin bank of cells and the cooperation of second spring bolt group alternative. Use the technical scheme of the utility model to solve aeroelasticity technical problem such as nonlinear deformation that big aspect ratio aircraft brought.

Description

Combined aircraft wingtip connecting and separating mechanism and combined aircraft

Technical Field

The utility model relates to a combination formula aircraft technical field especially relates to a modular aircraft wingtip connection and separation mechanism and combination formula aircraft.

Background

The high-altitude long-endurance aircraft can perform reconnaissance and monitoring, search and tracking, disaster exploration, meteorological research and other tasks, and is widely applied to the military and civil fields. Endurance performance is the core requirement of flight performance of the high-altitude long-endurance aircraft, and directly determines indexes such as voyage and endurance. The wing structure generally adopts the layout of high aspect ratio when designing, and in order to reduce energy consumption and lighten the structural weight, the wing material adopts light composite material in a large number. However, the aircraft has large aspect ratio, so that the structure has high flexibility, the structure deforms greatly in the flight process, the problem of geometric nonlinear aeroelasticity occurs, and the flight safety is influenced.

In addition to high aspect ratio wings, combination aircraft, that is, aircraft combining a plurality of individual aircraft into a high aspect ratio wing, may also be used. On one hand, the endurance performance is improved, and the fuel consumption rate is improved; on the other hand, the system can also be used as a cluster formation to fly, after the system reaches a task destination, each single aircraft is separated, and the task is executed independently, so that the application potential is huge. However, the combined aircraft can take off at the same time and is limited by airports due to the large spread length. In addition, if a single-body takeoff aerial combination mode is adopted, various problems of insufficient flight mechanical stability, high control difficulty and the like can be faced.

SUMMERY OF THE UTILITY MODEL

The utility model provides a modular separating mechanism and combination formula aircraft are connected to aircraft wingtip can solve among the prior art aeroelasticity technical problem such as nonlinear deformation that big aspect ratio aircraft brought.

According to the utility model discloses an aspect provides a modular separating mechanism is connected to aircraft wingtip, and modular separating mechanism is connected to aircraft wingtip includes: the first wingtip rib is fixedly arranged at the end part of a wing of a first aircraft, the first motor and the second motor are arranged on the first wingtip rib, the first motor is in driving connection with the first connecting rod, the second motor is in driving connection with the second connecting rod, the first motor is used for driving the first connecting rod to move, the second motor is used for driving the second connecting rod to move, and the moving directions of the first connecting rod and the second connecting rod are opposite; the first wing tip hinge mounting seat is provided with a first guide groove, a first locking groove and a second locking groove, the first spring group is connected with the first spring group, the first spring group is perpendicular to the first guide groove, the first hinge assembly is fixedly arranged on the first wing tip hinge mounting seat, the first connecting rod is selectively matched with the first locking groove, the second connecting rod is selectively matched with the second locking groove, and the first locking pin is provided with a first locking pin groove group; the second wingtip rib is fixedly arranged at the end part of the wing of the second aircraft, the third motor and the fourth motor are arranged on the second wingtip rib, the third motor is in driving connection with the third connecting rod, the fourth motor is in driving connection with the fourth connecting rod, the third motor is used for driving the third connecting rod to move, the fourth motor is used for driving the fourth connecting rod to move, and the moving directions of the third connecting rod and the fourth connecting rod are opposite; the second wingtip hinge mounting base is provided with a second guide groove, a third locking groove and a fourth locking groove, the second spring group is connected with the second spring group, the second spring group is perpendicular to the second guide groove, the second hinge assembly is fixedly arranged on the second wingtip hinge mounting base, the second guide groove is used for guiding the first lock pin, the first guide groove is used for guiding the second lock pin, the third connecting rod is selectively matched with the third locking groove, the fourth connecting rod is selectively matched with the fourth locking groove, the second lock pin is provided with a second lock pin groove group, the second lock pin groove group is selectively matched with the first lock pin group, and the first lock pin groove group is selectively matched with the second lock pin group; the hinge assembly comprises a rotating element and a split pin, wherein the rotating element respectively penetrates through a first hinge assembly and a second hinge assembly so as to realize the rotatable connection of a first wing tip hinge mounting seat and a second wing tip hinge mounting seat, and the split pin is arranged at the end part of the rotating element; when the wing of the first aircraft and the wing of the second aircraft are in a folding connection state, the first guide groove is separated from the second lock pin, the second guide groove is separated from the first lock pin, the first connecting rod is matched with the first locking groove, the second connecting rod is matched with the second locking groove, the third connecting rod is matched with the third locking groove, and the fourth connecting rod is matched with the fourth locking groove; when the wings of the first aircraft and the wings of the second aircraft are in an unfolded state, the first guide groove is matched with the second lock pin, the second guide groove is matched with the first lock pin, the second lock pin slot group is matched with the first lock tongue group, and the first lock pin slot group is matched with the second lock tongue group; when the wing of the first aircraft is separated from the wing of the second aircraft, the first connecting rod is separated from the first locking groove, the second connecting rod is separated from the second locking groove, the third connecting rod is separated from the third locking groove, and the fourth connecting rod is separated from the fourth locking groove.

Further, any connecting rod comprises a first connecting section, a first connecting rod protrusion and a second connecting rod protrusion, the first connecting rod protrusion is connected with one end of the first connecting section, the second connecting rod protrusion is connected with the other end of the first connecting section, any locking groove comprises a first locking hole and a second locking hole, the first connecting rod protrusion is selectively matched with the first locking hole, and the second connecting rod protrusion is selectively matched with the second locking hole.

Furthermore, the first lock tongue group comprises a first lock tongue and a second lock tongue, the first spring group comprises a first spring and a second spring, the first spring is connected with the first lock tongue, the second spring is connected with the second lock tongue, the second lock tongue group comprises a third lock tongue and a fourth lock tongue, the second spring group comprises a third spring and a fourth spring, the third spring is connected with the third lock tongue, the fourth spring is connected with the fourth lock tongue, the first lock tongue groove group comprises a first lock tongue groove and a second lock tongue groove which are oppositely arranged, the second lock tongue groove group comprises a third lock tongue groove and a fourth lock tongue groove which are oppositely arranged, the first lock tongue can be selectively matched with the third lock tongue groove, the second lock tongue can be selectively matched with the fourth lock tongue groove, the third lock tongue can be selectively matched with the first lock tongue groove, and the fourth lock tongue can be selectively matched with the second lock tongue groove.

Furthermore, the wing tip connection and separation mechanism of the combined aircraft further comprises a first lock tongue mounting box, a second lock tongue mounting box, a third lock tongue mounting box and a fourth lock tongue mounting box, the first lock tongue mounting box and the second lock tongue mounting box are arranged on the first wing tip hinge mounting seat, the third lock tongue mounting box and the fourth lock tongue mounting box are arranged on the second wing tip hinge mounting seat, the first lock tongue and the first spring are arranged in the first lock tongue mounting box, the second lock tongue and the second spring are arranged in the second lock tongue mounting box, the third lock tongue and the third spring are arranged in the third lock tongue mounting box, and the fourth lock tongue and the fourth spring are arranged in the fourth lock tongue mounting box.

Furthermore, the first lock pin comprises a first lock pin cylindrical section and a first lock pin conical section which are connected, the first lock pin groove and the second lock pin groove are oppositely arranged on the first lock pin conical section, the second lock pin comprises a second lock pin cylindrical section and a second lock pin conical section which are connected, and the third lock pin groove and the fourth lock pin groove are oppositely arranged on the second lock pin conical section.

Further, the first hinge assembly comprises a first hinge unit, a second hinge unit and a third hinge unit which are sequentially arranged at intervals, the second hinge assembly comprises a fourth hinge unit and a fifth hinge unit which are sequentially arranged at intervals, when the wing of the first aircraft is connected with the wing of the second aircraft, the fourth hinge unit is arranged between the first hinge unit and the second hinge unit, and the fifth hinge unit is arranged between the second hinge unit and the third hinge unit.

Furthermore, any motor comprises a motor body and a motor telescopic rod, the motor telescopic rod is connected with the motor body, and the motor telescopic rod is connected with the corresponding connecting rod.

Furthermore, the combined aircraft wing tip connecting and separating mechanism further comprises a first anti-collision block group and a second anti-collision block group, the first anti-collision block group is arranged on the first wing tip hinge mounting seat, the second anti-collision block group is arranged on the second wing tip hinge mounting seat, and the first anti-collision block group and the second anti-collision block group are used for buffering anti-collision impact.

Furthermore, the first anti-collision block group comprises a first anti-collision block and a second anti-collision block, the first anti-collision block is arranged on one side of the first wingtip hinge mounting seat, and the second anti-collision block is arranged on the other side of the first wingtip hinge mounting seat; the second anti-collision block group comprises a third anti-collision block and a fourth anti-collision block, the third anti-collision block is arranged on one side of the second wingtip hinge mounting seat, and the fourth anti-collision block is arranged on the other side of the second wingtip hinge mounting seat.

According to another aspect of the present invention, there is provided a combined aircraft, the combined aircraft comprises a first aircraft, a second aircraft and a combined aircraft wing tip connection and separation mechanism, the combined aircraft wing tip connection and separation mechanism is the combined aircraft wing tip connection and separation mechanism described above, the first aircraft is connected with the second aircraft through the combined aircraft wing tip connection and separation mechanism.

Use the technical scheme of the utility model, a modular separating mechanism is connected to aircraft wingtip is provided, and this modular separating mechanism is connected to aircraft wingtip can realize that each monomer aircraft wing is collapsible, can not receive the airport restriction because of the exhibition is too big, has reduced the requirement to the environment of taking off and landing. The combined type aircraft is launched by the booster, wings of the aircraft are unfolded and locked with each other after the combined type aircraft is launched, and after the combined type aircraft reaches the required time and range of flight, wing tip mechanism separation is completed under a separation instruction, and the combined type aircraft and the wing tip mechanism are respectively used for executing tasks by single aircraft. Compared with the prior art, the utility model provides a modular aircraft wingtip connection and separation mechanism is simple, nimble, reliable, easy dismounting, is convenient for maintain to have low-cost advantage concurrently, can solve aeroelastic problems such as nonlinear deformation that the high aspect ratio wing brought.

Drawings

The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.

Fig. 1 shows a schematic structural view of a wingtip rib and a wingtip hinge mount of a first aircraft according to an embodiment of the present invention;

fig. 2 shows a schematic structural diagram of a wingtip rib and a wingtip hinge mount of a second aircraft according to an embodiment of the present invention;

fig. 3 is a schematic view illustrating an assembly of a first wing tip rib and a first wing tip hinge mount provided according to an embodiment of the present invention;

fig. 4 is a schematic view illustrating an assembly structure of a second wingtip rib, a motor and a connecting rod according to an embodiment of the present invention;

fig. 5 shows a schematic structural view of a second locking pin lock provided according to an embodiment of the present invention;

fig. 6 shows a schematic structural view of a first lock pin lock provided according to an embodiment of the present invention;

fig. 7 shows a schematic structural diagram of the installation of the first motor and the second motor according to the embodiment of the present invention;

fig. 8 shows a schematic structural view of a first wingtip rib provided according to an embodiment of the present invention;

fig. 9 shows a schematic view of the internal structure of a first wingtip hinge mount provided according to an embodiment of the present invention;

fig. 10 is a schematic diagram illustrating an internal structure of a second wingtip hinge mount according to an embodiment of the present invention;

FIG. 11 illustrates a schematic structural view of a composite aircraft wing deployed in place and locked in accordance with a specific embodiment of the present invention;

fig. 12 is a schematic structural view illustrating the deployment of a composite aircraft wing according to an embodiment of the present invention;

fig. 13 illustrates a composite aircraft wing fold provided in accordance with a particular embodiment of the present invention;

fig. 14 is a schematic diagram illustrating an internal structure of a first tongue locking mounting box according to an embodiment of the present invention.

Wherein the figures include the following reference numerals:

10. a first wingtip rib; 20. a first motor; 21. a motor body; 22. a motor telescopic rod; 30. a second motor; 40. a first link; 41. a first connection section; 42. a first link projection; 43. a second link projection; 50. a second link; 60. a first wingtip hinge mount; 60a, a first guide groove; 60b, a first locking groove; 61b, a first locking hole; 62b, a second locking hole; 60c, a second locking groove; 70. a first hinge assembly; 71. a first hinge unit; 72. a second hinge unit; 73. a third hinge unit; 80. a first latch set; 81. a first bolt; 82. a second bolt; 90. a first spring set; 91. a first spring; 92. a second spring; 100. a first lock pin; 100a, a first lock keyway group; 101a, a first latch slot; 102a, a second latch slot; 101. a first cylindrical lockpin section; 102. a first latch tapered section; 110. a second wingtip rib; 120. a third motor; 130. a fourth motor; 140. a third link; 150. a fourth link; 160. a second wingtip hinge mount; 160a, a second guide groove; 160b, a third locking groove; 160c, a fourth locking groove; 170. a second hinge assembly; 171. a fourth hinge unit; 172. a fifth hinge unit; 180. a second bolt set; 181. a third bolt; 182. a fourth bolt; 190. a second spring set; 191. a third spring; 192. a fourth spring; 200. a second lock pin; 200a, a second lock pin groove group; 201a, a third latch slot; 202a, a fourth latch slot; 201. a second locking pin cylindrical section; 202. a second locking pin tapered section; 210. a rotating element; 220. a cotter pin; 240. a first lock tongue mounting box; 250. a second bolt mounting box; 260. a third bolt mounting box; 270. a fourth bolt mounting box; 280. a first anti-collision block group; 281. a first crash block; 282. a second anti-collision block; 290. a second anti-collision block group; 291. a third collision prevention block; 292. a fourth anti-collision block; 1000. the wing tip of the combined aircraft is connected with the separation mechanism; 2000. a wing of a first aircraft; 3000. a wing of a second aircraft.

Detailed Description

It should be noted that, in the present application, the embodiments and features of the embodiments may be combined with each other without conflict. The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.

It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.

Unless specifically stated otherwise, the relative arrangement of the components and steps, the numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present invention. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as exemplary only and not as limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.

As shown in fig. 1 to 14, according to an embodiment of the present invention, there is provided a combined aircraft wing tip connection and disconnection mechanism, which includes a first wing tip rib 10, a first motor 20, a second motor 30, a first connecting rod 40, a second connecting rod 50, a first wing tip hinge mount 60, a first hinge assembly 70, a first latch set 80, a first spring set 90, a first latch 100, a second wing tip rib 110, a third motor 120, a fourth motor 130, a third connecting rod 140, a fourth connecting rod 150, a second wing tip hinge mount 160, a second hinge assembly 170, a second latch set 180, a second spring set 190, a second latch 200, a rotating element 210 and a split pin 220, wherein the first wing tip rib 10 is fixedly disposed at a wing end of a first aircraft, the first motor 20 and the second motor 30 are disposed on the first wing tip rib 10, the first motor 20 is drivingly connected to the first connecting rod 40, the second motor 30 is drivingly connected to the second connecting rod 50, the first connecting rod 20 is used for driving the second connecting rod 40 to move, and the second connecting rod 50 is used for moving the second connecting rod 50 in the opposite direction; the first wing tip hinge mounting base 60 has a first guide groove 60a, a first locking groove 60b and a second locking groove 60c, a first spring set is connected with the first bolt set 80, the first bolt set 80 is arranged perpendicular to the first guide groove 60a, the first hinge assembly 70 is fixedly arranged on the first wing tip hinge mounting base 60, the first connecting rod 40 is selectively matched with the first locking groove 60b, the second connecting rod 50 is selectively matched with the second locking groove 60c, the first locking pin 100 has a first locking pin groove set 100a, the second wing tip rib 110 is fixedly arranged at the end of the second aircraft wing, the third motor 120 and the fourth motor 130 are arranged on the second wing tip rib 110, the third motor 120 is in driving connection with the third connecting rod 140, the fourth motor 130 is in driving connection with the fourth connecting rod 150, the third motor 120 is used for driving the third connecting rod 140 to move, the fourth motor 130 is used for driving the fourth connecting rod 150 to move, and the moving directions of the third connecting rod 140 and the fourth connecting rod 150 are opposite, the second wing hinge mount 160 has a second guide slot 160a, a third locking slot 160b and a fourth locking slot 160c, the second spring assembly 190 is connected with the second bolt assembly 180, the second bolt assembly 180 is vertically disposed with the second guide slot 160a, the second hinge assembly 170 is fixedly disposed on the second wing hinge mount 160, the second guide slot 160a is used for guiding the first lock pin 100, the first guide slot 60a is used for guiding the second lock pin 200, the third link 140 is selectively cooperated with the third locking slot 160b, the fourth link 150 is selectively cooperated with the fourth locking slot 160c, the second lock pin 200 has a second lock pin slot set 200a, the second lock pin slot set 200a is selectively cooperated with the first bolt set 80, the first lock pin slot set 100a is selectively cooperated with the second bolt set 180, the rotary element 210 respectively passes through the first hinge assembly 70 and the second hinge assembly 170 to realize that the first wing hinge mount 60 is selectively cooperated with the first wing hinge assembly 60 and the first bolt set 80 A rotatable connection of the wingtip hinge mount 160, a cotter pin 220 provided at the end of the rotating element 210; when the wing of the first aircraft and the wing of the second aircraft are in a folding connection state, the first guide groove 60a is separated from the second lock pin 200, the second guide groove 160a is separated from the first lock pin 100, the first link 40 is matched with the first locking groove 60b, the second link 50 is matched with the second locking groove 60c, the third link 140 is matched with the third locking groove 160b, and the fourth link 150 is matched with the fourth locking groove 160 c; when the wings of the first aircraft and the wings of the second aircraft are in the unfolded state, the first guide groove 60a is matched with the second lock pin 200, the second guide groove 160a is matched with the first lock pin 100, the second lock pin groove group 200a is matched with the first lock tongue group 80, and the first lock pin groove group 100a is matched with the second lock tongue group 180; when the wing of the first aircraft is separated from the wing of the second aircraft, the first link 40 is separated from the first locking groove 60b, the second link 50 is separated from the second locking groove 60c, the third link 140 is separated from the third locking groove 160b, and the fourth link 150 is separated from the fourth locking groove 160 c.

By applying the configuration mode, a combined aircraft wing tip connecting and separating mechanism is provided, in the process of connecting two aircraft wing tips, firstly, a first wing tip hinge mounting seat of a first aircraft is sleeved with a first wing tip rib, then a first motor pushes a first connecting rod to move upwards, a second motor pushes a second connecting rod to move downwards, a first connecting rod 40 is matched with a first locking groove 60b on the first wing tip hinge mounting seat, a second connecting rod 50 is matched with a second locking groove 60c on the first wing tip hinge mounting seat, and the first motor and the second motor complete locking after the two aircraft wing tips are in place; the second wingtip hinge mount of the second aircraft is sleeved with the second wingtip rib, then the third motor pushes the third connecting rod to move upwards, the fourth motor pushes the fourth connecting rod to move downwards, the third connecting rod 140 is matched with the third locking groove 160b, the fourth connecting rod 150 is matched with the fourth locking groove 160c, and the third motor and the fourth motor complete locking after the second wingtip hinge mount is in place. After the wingtip hinge installation seats are fixed on the two aircrafts respectively, the rotating elements respectively penetrate through the first hinge assembly 70 and the second hinge assembly 170 of the two aircrafts and are fixed by the cotter pins 220, then the wings of the two aircrafts are restored to be folded, and the two aircrafts are changed into a combined body from a single aircraft.

Wing flattening process: after the combined aircraft is launched by the booster, the wing of the first aircraft rotates around the first hinge assembly 70, the wing of the second aircraft rotates around the second hinge assembly 80, in the rotating process, the first lock pin 100 extends into a second guide groove on a hinge mounting seat of a second wing tip, the first lock pin 100 touches the second lock tongue group 180, the second lock tongue group 180 applies pressure to the second spring group 190, the second spring group 190 is compressed under the force, when the first lock pin 100 reaches the bottom of the second guide groove, the second lock tongue group is released from constraint, and the second lock tongue group extends into the first lock pin groove group 100a under the action of the second spring group 190 to be locked; the second lock pin 200 extends into a first guide groove on the first wing tip hinge mounting seat, the second lock pin 200 touches the first lock tongue group 80, the first lock tongue group 80 applies pressure to the first spring group 90, the first spring group 90 is compressed under the stress, when the second lock pin 200 reaches the bottom of the first guide groove, the first lock tongue group is released from restraint, the first lock tongue group extends into the second lock tongue groove group under the action of the first spring group 90 to be locked, and the wing of the combined aircraft is flattened and locked. And then performing the time-of-flight voyage mission flight according to the overall requirements.

Wing tip separation process: after receiving a separation instruction, the first motor pushes the first connecting rod to move downwards, and the second motor pushes the second connecting rod to move upwards until the first connecting rod and the second connecting rod do not protrude out of the surface of the first wingtip rib, so that the first wingtip hinge mounting seat is unlocked; the third motor promotes the third connecting rod and moves down, and the fourth motor promotes the fourth connecting rod and moves up, until third connecting rod and fourth connecting rod do not stick out the surface of second winged tip rib, accomplish the unblock to second winged tip hinge mount pad, under the disturbance of first aircraft and second aircraft to the not equidirectional motion, first winged tip hinge mount pad breaks away from first winged tip rib, second winged tip hinge mount pad breaks away from second winged tip rib to throw down under the action of gravity certainly, each aircraft is with monomer executive task.

According to the above, the utility model provides a modular aircraft wingtip connection separating mechanism can realize that each monomer aircraft wing is collapsible, can not receive the airport restriction because of the exhibition is too big, has reduced the requirement to the environment of taking off and land. The combined type aircraft is launched by the booster, wings of the aircraft are unfolded and locked with each other after the combined type aircraft is launched, and after the combined type aircraft reaches the required time and flight, the wing tip mechanism is separated under a separation instruction, and the combined type aircraft and the wing tip mechanism are respectively used for executing tasks by single aircraft. Compared with the prior art, the utility model provides a modular aircraft wingtip connection and separation mechanism is simple, nimble, reliable, easy dismounting, is convenient for maintain to have low-cost advantage concurrently, can solve aeroelastic problems such as nonlinear deformation that the high aspect ratio wing brought.

Further, in the utility model discloses in, as shown in fig. 9 and 10, in order to realize the reliable connection and the smooth separation of wing tip hinge mount pad and wing tip rib, arbitrary connecting rod all includes first linkage segment 41, first connecting rod arch 42 and second connecting rod arch 43, first connecting rod arch 42 is connected with the one end of first linkage segment 41, second connecting rod arch 43 is connected with the other end of first linkage segment 41, arbitrary locking recess all includes first locking hole 61b and second locking hole 62b, first connecting rod arch 42 and first locking hole 61b alternative cooperation, second connecting rod arch 43 and second locking hole 62b alternative cooperation.

Under this configuration, for the first aircraft, when the reliable connection of the first wingtip hinge mount and the first wingtip rib needs to be completed, the first link moves upward in the linear direction under the driving of the first motor until the first link protrusion 42 of the first link is engaged with the first locking hole 61b of the first locking groove, and the second link protrusion 43 of the first link is engaged with the second locking hole 62b of the first locking groove; and under the driving of the second motor, the second connecting rod moves downwards along the linear direction until the first connecting rod protrusion 42 of the second connecting rod is matched with the first locking hole 61b of the second locking groove, and the second connecting rod protrusion 43 of the second connecting rod is matched with the second locking hole 62b of the second locking groove, so that the reliable connection of the first wingtip hinge mounting seat and the first wingtip rib is completed. When the first wingtip hinge mounting seat and the first wingtip rib need to be reliably separated, the first connecting rod moves downwards along the linear direction under the driving of the first motor until the first connecting rod protrusion 42 of the first connecting rod is separated from the first locking hole 61b of the first locking groove, and the second connecting rod protrusion 43 of the first connecting rod is separated from the second locking hole 62b of the first locking groove; under the driving of the second motor, the second link moves upward in a linear direction until the first link projection 42 of the second link is separated from the first locking hole 61b of the second locking recess and the second link projection 43 of the second link is separated from the second locking hole 62b of the second locking recess, at which time the reliable separation of the first wingtip hinge mount and the first wingtip rib is completed. The process of reliable connection and smooth separation of the wingtip hinge mount of the second aircraft and the wingtip rib is the same as that of the first aircraft, and the details are not repeated here.

Further, in the present invention, in order to improve the reliability of locking after the wing tip hinge mount and the wing tip rib are flattened, the first latch set 80 may be configured to include a first latch tongue 81 and a second latch tongue 82, the first spring set 90 includes a first spring 91 and a second spring 92, the first spring 91 is connected to the first latch tongue 81, the second spring 92 is connected to the second latch tongue 82, the second latch tongue set 180 includes a third latch tongue 181 and a fourth latch tongue 182, the second spring set 190 includes a third spring 191 and a fourth spring 192, the third spring 191 is connected to the third latch tongue 181, the fourth spring 192 is connected to the fourth latch tongue 182, the first latch groove set 100a includes a first latch groove 101a and a second latch groove 102a which are oppositely disposed, the second latch groove set 200a includes a third latch groove 201a and a fourth latch groove 202a which are oppositely disposed, the first latch tongue 81 is selectively engageable with the third latch groove 201a, the second latch groove 82 is selectively engageable with the fourth latch groove 182 a, the third latch groove 201a is selectively engageable with the fourth latch groove 102 a.

Under the configuration, after the combined aircraft is launched by the booster, the wing of the first aircraft rotates around the first hinge assembly 70, the wing of the second aircraft rotates around the second hinge assembly 80, during the rotation, the first lock pin 100 extends into the second guide groove on the hinge mounting seat of the second wing tip, the first lock pin 100 touches the third lock tongue 181 and the fourth lock tongue 182, the third lock tongue 181 applies pressure to the third spring 191, the fourth lock tongue 182 applies pressure to the fourth spring 192, the third spring 191 and the fourth spring 192 are compressed under the force, when the first lock pin 100 reaches the bottom of the second guide groove, the third lock tongue 181 and the fourth lock tongue 182 are released from constraint, the third lock tongue 181 extends into the first lock pin groove 101a under the action of the third spring 191 to be locked, and the fourth lock tongue 182 extends into the second lock pin groove 102a under the action of the fourth spring 192 to be locked; the second lock pin 200 extends into the first guide groove on the first wing tip hinge mounting seat, the second lock pin 200 touches the first lock tongue 81 and the second lock tongue 82, the first lock tongue 81 applies pressure to the first spring 91, the second lock tongue 82 applies pressure to the second spring 92, the first spring 91 and the second spring 92 are stressed and compressed, when the second lock pin 200 reaches the bottom of the first guide groove, the first lock tongue 81 and the second lock tongue 82 are released from constraint, the first lock tongue 81 extends into the third lock pin groove 201a under the action of the first spring to be locked, the second lock tongue 82 extends into the fourth lock pin groove 202a under the action of the second spring to be locked, and the wing of the combined aircraft is flattened and locked. And then the time-of-flight voyage mission is carried out according to the overall requirements.

Further, the utility model discloses in, for the convenience installation of spring bolt and spring, combined type aircraft wing tip connection separating mechanism still includes first spring bolt mounting box 240, second spring bolt mounting box 250, third spring bolt mounting box 260 and fourth spring bolt mounting box 270, first spring bolt mounting box 240 and second spring bolt mounting box 250 set up on first wing tip hinge mount pad 60, third spring bolt mounting box 260 and fourth spring bolt mounting box 270 set up on second wing tip hinge mount pad 160, first spring bolt 81 and first spring 91 set up in first spring bolt mounting box 240, second spring bolt 82 and second spring 92 set up in second spring bolt mounting box 250, third spring bolt 181 and third spring 191 set up in third spring bolt mounting box 260, fourth spring bolt 182 and fourth spring 192 set up in fourth spring bolt mounting box 270.

Furthermore, in the present invention, in order to enable the lock pin to enter the guide groove more smoothly, and then to complete the reliable connection between the wing tip hinge mount and the wing tip rib, the first lock pin 100 may be configured to include a first lock pin cylindrical section 101 and a first lock pin tapered section 102 which are connected, the first lock pin groove 101a and the second lock pin groove 102a are relatively disposed on the first lock pin tapered section 102, the second lock pin 200 includes a second lock pin cylindrical section 201 and a second lock pin tapered section 202 which are connected, and the third lock pin groove 201a and the fourth lock pin groove 202a are relatively disposed on the second lock pin tapered section 202. The relative arrangement of the utility model refers to the centrosymmetric arrangement of two lockpin grooves relative lockpin conical sections.

Further, in the present invention, in order to improve the reliability of the connection of the wing tip hinge mount, the first hinge assembly 70 may be configured to include a first hinge unit 71, a second hinge unit 72, and a third hinge unit 73 which are sequentially spaced apart, the second hinge assembly 170 includes a fourth hinge unit 171 and a fifth hinge unit 172 which are sequentially spaced apart, when the wing of the first aircraft is connected to the wing of the second aircraft, the fourth hinge unit 171 is disposed between the first hinge unit 71 and the second hinge unit 72, and the fifth hinge unit 172 is disposed between the second hinge unit 72 and the third hinge unit 73. As other embodiments of the present invention, the number of hinge units of the first hinge assembly and the second hinge assembly is not limited, as long as it can be ensured that the two wing tip hinge mounts can smoothly rotate.

Furthermore, the utility model discloses in, for the motion of drive connecting rod along linear direction smoothly, arbitrary motor all includes motor body 21 and motor telescopic link 22, and motor telescopic link 22 is connected with motor body 21, and motor telescopic link 22 is connected with corresponding connecting rod.

Further, the utility model discloses in, in order to absorb the collision energy of two planes wing spreading in-process, play the cushioning effect, prevent simultaneously that two planes wing from upwards rotating after flat, play limiting displacement, can connect separating mechanism configuration with combination formula aircraft wing tip and still include first bump block group 280 and second bump block group 290, first bump block group 280 sets up on first wing tip hinge mount pad 60, second bump block group 290 sets up on second wing tip hinge mount pad 160, first bump block group 280 and second bump block group 290 are used for the buffering anticollision to strike.

As a specific embodiment of the present invention, in order to further improve the energy absorption effect, the first anti-collision block set 280 includes a first anti-collision block 281 and a second anti-collision block 282, the first anti-collision block 281 is disposed on one side of the first wing tip hinge mounting seat 60, and the second anti-collision block 282 is disposed on the other side of the first wing tip hinge mounting seat 60; the second anti-collision block set 290 includes a third anti-collision block 291 and a fourth anti-collision block 292, the third anti-collision block 291 is disposed on one side of the second wingtip hinge mount 160, and the fourth anti-collision block 292 is disposed on the other side of the second wingtip hinge mount 160.

According to a specific embodiment of the utility model, a modular aircraft, this modular aircraft include first aircraft, second aircraft and modular aircraft wingtip connection and separation mechanism, modular aircraft wingtip connection and separation mechanism be as above modular aircraft wingtip connection and separation mechanism, first aircraft passes through modular aircraft wingtip connection and separation mechanism and is connected with the second aircraft.

Use this kind of configuration, provide a modular aircraft, this modular aircraft include as above modular aircraft wingtip connection separating mechanism, because the utility model provides a modular aircraft wingtip connection separating mechanism can realize that each monomer aircraft wing is collapsible, can not receive the airport restriction because of the exhibition is too big, has reduced the requirement to the environment of taking off and land. The combined type aircraft is launched by the booster, wings of the aircraft are unfolded and locked with each other after the combined type aircraft is launched, and after the combined type aircraft reaches the required time and flight, the wing tip mechanism is separated under a separation instruction, and the combined type aircraft and the wing tip mechanism are respectively used for executing tasks by single aircraft. Therefore, the wing tip connecting and separating mechanism of the combined aircraft is used in the combined aircraft, so that the combined aircraft can meet the performance of high altitude long endurance, has cluster distributed task execution capacity, and can solve the aeroelastic problems such as nonlinear deformation and the like caused by wings with large aspect ratio.

In order to further understand the present invention, the following description will be made with reference to fig. 1 to 14 for the connection and separation mechanism of the combined type aircraft wing tip.

As shown in fig. 1 to 14, according to an embodiment of the present invention, there is provided a combined aircraft wing tip connection and disconnection mechanism, which includes a first wing tip rib 10, a first motor 20, a second motor 30, a first connecting rod 40, a second connecting rod 50, a first wing tip hinge mount 60, a first hinge assembly 70, a first latch bolt assembly 80, a first spring assembly 90, a first latch bolt 100, a second wing tip rib 110, a third motor 120, a fourth motor 130, a third connecting rod 140, a fourth connecting rod 150, a second wing tip hinge mount 160, a second hinge assembly 170, a second latch bolt assembly 180, a second spring assembly 190, a second latch bolt 200, a rotating element 210, a split pin 220, a first latch bolt mount 240, a second latch bolt mount 250, a third latch bolt mount 260, a fourth latch bolt mount 270, a first bump protection mount 280, and a second bump protection mount 290, wherein the first wing tip rib 10 is fixedly disposed at a wing end of a first aircraft, the first wing tip rib 20 and the second latch bolt mount 250 are disposed on the first connecting rod 40, the second connecting rod 30 is connected to the first connecting rod 20, the second connecting rod 30 is connected to the second connecting rod 50, the second motor 30 is movable in a direction, and the second connecting rod drive motor 30, and the second connecting rod drive motor 30 is used for moving the second connecting rod drive motor 50; the first wing tip hinge mounting base 60 has a first guide groove 60a, a first locking groove 60b and a second locking groove 60c, a first spring set is connected with the first locking tongue set 80, the first locking tongue set 80 is vertically arranged with the first guide groove 60a, the first hinge assembly 70 is fixedly arranged on the first wing tip hinge mounting base 60, the first connecting rod 40 can be selectively matched with the first locking groove 60b, the second connecting rod 50 can be selectively matched with the second locking groove 60c, and the first locking pin 100 has a first locking pin groove set 100a. A first crash block 281 is provided on one side of the first wingtip hinge mount 60 and a second crash block 282 is provided on the other side of the first wingtip hinge mount 60; the third bump prevention block 291 is provided at one side of the second wing tip hinge mount 160, and the fourth bump prevention block 292 is provided at the other side of the second wing tip hinge mount 160.

The second wingtip rib 110 is fixedly arranged at the end of the wing of the second aircraft, the third motor 120 and the fourth motor 130 are arranged on the second wingtip rib 110, the third motor 120 is drivingly connected with the third link 140, the fourth motor 130 is drivingly connected with the fourth link 150, the third motor 120 is used for driving the third link 140 to move, the fourth motor 130 is used for driving the fourth link 150 to move, the moving directions of the third link 140 and the fourth link 150 are opposite, the second wingtip hinge mount 160 is provided with a second guide slot 160a, a third locking groove 160b and a fourth locking groove 160c, the second spring set 190 is connected with the second bolt set 180, the second bolt set 180 is vertically arranged with the second guide slot 160a, the second hinge assembly 170 is fixedly arranged on the second wingtip hinge mount 160, the second guide slot 160a is used for guiding the first hinge pin 100, the first guide groove 60a is used for guiding the second lock pin 200, the third link 140 is selectively matched with the third locking groove 160b, the fourth link 150 is selectively matched with the fourth locking groove 160c, the second lock pin 200 has a second lock pin groove group 200a, the second lock pin groove group 200a is selectively matched with the first lock tongue group 80, the first lock pin groove group 100a is selectively matched with the second lock tongue group 180, the rotating element 210 respectively passes through the first hinge assembly 70 and the second hinge assembly 170 to realize the rotatable connection of the first wing tip hinge mounting seat 60 and the second wing tip hinge mounting seat 160, the rotating element 210 comprises a cylindrical stop head and a rotating shaft, the diameter of the cylindrical stop head is larger than that of the rotating shaft, the cylindrical stop head is arranged at one end of the rotating element 210, the split pin 220 is arranged at the other end of the rotating element 210, the first hinge assembly and the second hinge assembly are prevented from being removed from the rotating member by the cylindrical stopper and the cotter pin.

Any one of the connecting rods comprises a first connecting section 41, a first connecting rod protrusion 42 and a second connecting rod protrusion 43, the first connecting rod protrusion 42 is connected with one end of the first connecting section 41, the second connecting rod protrusion 43 is connected with the other end of the first connecting section 41, any one of the locking grooves comprises a first locking hole 61b and a second locking hole 62b, the first connecting rod protrusion 42 can be selectively matched with the first locking hole 61b, and the second connecting rod protrusion 43 can be selectively matched with the second locking hole 62 b.

The first locking tongue set 80 is configured to include a first locking tongue 81 and a second locking tongue 82, the first spring set 90 includes a first spring 91 and a second spring 92, the first spring 91 is connected with the first locking tongue 81, the second spring 92 is connected with the second locking tongue 82, the second locking tongue set 180 includes a third locking tongue 181 and a fourth locking tongue 182, the second spring set 190 includes a third spring 191 and a fourth spring 192, the third spring 191 is connected with the third locking tongue 181, the fourth spring 192 is connected with the fourth locking tongue 182, the first locking tongue groove set 100a includes a first locking tongue groove 101a and a second locking tongue groove 102a which are oppositely arranged, the second locking tongue groove set 200a includes a third locking tongue groove 201a and a fourth locking tongue groove 202a which are oppositely arranged, the first locking tongue 81 is selectively engageable with the third locking tongue 201a, the second locking tongue 82 is selectively engageable with the fourth locking tongue 202a, the third locking tongue 181 is selectively engageable with the first locking tongue groove 101a, and the fourth locking tongue 182 is selectively engageable with the second locking tongue 102 a.

The wingtips of the two aircrafts are connected: firstly, a first wing tip hinge mounting seat of a first aircraft is sleeved with a first wing tip rib, then a first motor pushes a first connecting rod to move upwards, a second motor pushes a second connecting rod to move downwards, the first connecting rod 40 is matched with a first locking groove 60b on the first wing tip hinge mounting seat, the second connecting rod 50 is matched with a second locking groove 60c on the first wing tip hinge mounting seat, and the first motor and the second motor complete locking after the first connecting rod and the second connecting rod are in place; the second wingtip hinge mount of the second aircraft is sleeved with the second wingtip rib, then the third motor pushes the third connecting rod to move upwards, the fourth motor pushes the fourth connecting rod to move downwards, the first connecting rod 40 is matched with the first locking groove 60b on the first wingtip hinge mount, the third connecting rod 140 is matched with the third locking groove 160b, the fourth connecting rod 150 is matched with the fourth locking groove 160c, and the locking is completed by the third motor and the fourth motor after the positioning. After the wingtip hinge installation seats are fixed on the two aircrafts respectively, the rotating elements respectively penetrate through the first hinge assembly 70 and the second hinge assembly 170 of the two aircrafts and are fixed by the cotter pins 220, then the wings of the two aircrafts are restored to be folded, and the two aircrafts are changed into a combined body from a single aircraft.

Wing flattening process: after the combined aircraft is launched by the booster, the wing of the first aircraft rotates around the first hinge assembly 70, the wing of the second aircraft rotates around the second hinge assembly 80, in the rotating process, the first lock pin 100 extends into a second guide groove on a hinge mounting seat of the second wing tip, the first lock pin 100 touches the third lock tongue 181 and the fourth lock tongue 182, the third lock tongue 181 exerts pressure on the third spring 191, the fourth lock tongue 182 exerts pressure on the fourth spring 192, the third spring 191 and the fourth spring 192 are compressed under the force, after the first lock pin 100 reaches the bottom of the second guide groove, the third lock tongue 181 and the fourth lock tongue 182 are released from constraint, the third lock tongue 181 extends into the first lock pin groove 101a under the action of the third spring 191 to be locked, and the fourth lock tongue 182 extends into the second lock pin groove 102a under the action of the fourth spring 192 to be locked; the second lock pin 200 extends into the first guide groove on the first wing tip hinge mounting seat, the second lock pin 200 touches the first lock tongue 81 and the second lock tongue 82, the first lock tongue 81 applies pressure to the first spring 91, the second lock tongue 82 applies pressure to the second spring 92, the first spring 91 and the second spring 92 are stressed and compressed, when the second lock pin 200 reaches the bottom of the first guide groove, the first lock tongue 81 and the second lock tongue 82 are released from constraint, the first lock tongue 81 extends into the third lock pin groove 201a under the action of the first spring to be locked, the second lock tongue 82 extends into the fourth lock pin groove 202a under the action of the second spring to be locked, and the wing of the combined aircraft is flattened and locked. And then the time-of-flight voyage mission is carried out according to the overall requirements.

Wingtip separation process: when the separation instruction is received, the first connecting rod moves downwards along the linear direction under the driving of the first motor until the first connecting rod protrusion 42 of the first connecting rod is separated from the first locking hole 61b of the first locking groove, and the second connecting rod protrusion 43 of the first connecting rod is separated from the second locking hole 62b of the first locking groove; under the drive of the second motor, the second connecting rod moves upwards along the linear direction until the first connecting rod protrusion 42 of the second connecting rod is separated from the first locking hole 61b of the second locking groove, and the second connecting rod protrusion 43 of the second connecting rod is separated from the second locking hole 62b of the second locking groove, until the first connecting rod and the second connecting rod do not protrude out of the surface of the first wing tip rib, and the first wing tip hinge mounting seat is unlocked; the third motor promotes the third connecting rod and moves down, and the fourth motor promotes the fourth connecting rod and moves up, until third connecting rod and fourth connecting rod do not stick out the surface of second winged tip rib, accomplish the unblock to second winged tip hinge mount pad, under the disturbance of first aircraft and second aircraft to the not equidirectional motion, first winged tip hinge mount pad breaks away from first winged tip rib, second winged tip hinge mount pad breaks away from second winged tip rib to throw down under the action of gravity certainly, each aircraft is with monomer executive task.

To sum up, the utility model provides a modular separating mechanism is connected to aircraft wingtip, this modular separating mechanism is connected to aircraft wingtip can realize that each monomer aircraft wing is collapsible, can not receive the airport restriction because of the exhibition is too big, has reduced the requirement to the environment of taking off and landing. The combined type aircraft is launched by the booster, wings of the aircraft are unfolded and locked with each other after the combined type aircraft is launched, and after the combined type aircraft reaches the required time and flight, the wing tip mechanism is separated under a separation instruction, and the combined type aircraft and the wing tip mechanism are respectively used for executing tasks by single aircraft. Compared with the prior art, the utility model provides a modular aircraft wingtip connection and separation mechanism is simple, nimble, reliable, easy dismounting, is convenient for maintain to have low-cost advantage concurrently, can solve aeroelastic problems such as nonlinear deformation that the high aspect ratio wing brought.

For ease of description, spatially relative terms such as "over 8230 \ 8230;,"' over 8230;, \8230; upper surface "," above ", etc. may be used herein to describe the spatial relationship of one device or feature to another device or feature as shown in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary terms "at 8230; \8230; 'above" may include both orientations "at 8230; \8230;' above 8230; 'at 8230;' below 8230;" above ". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and if not stated otherwise, the terms have no special meaning, and therefore, the scope of the present invention should not be construed as being limited.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (10)

1. The utility model provides a modular aircraft wingtip connection and disconnection mechanism which characterized in that, modular aircraft wingtip connection and disconnection mechanism includes:

the wing tip structure comprises a first wing tip rib (10), a first motor (20), a second motor (30), a first connecting rod (40) and a second connecting rod (50), wherein the first wing tip rib (10) is fixedly arranged at the end part of a wing of a first aircraft, the first motor (20) and the second motor (30) are arranged on the first wing tip rib (10), the first motor (20) is in driving connection with the first connecting rod (40), the second motor (30) is in driving connection with the second connecting rod (50), the first motor (20) is used for driving the first connecting rod (40) to move, the second motor (30) is used for driving the second connecting rod (50) to move, and the moving directions of the first connecting rod (40) and the second connecting rod (50) are opposite;

a first wing tip hinge mounting seat (60), a first hinge assembly (70), a first latch tongue set (80), a first spring set (90) and a first latch pin (100), wherein the first wing tip hinge mounting seat (60) is provided with a first guide groove (60 a), a first locking groove (60 b) and a second locking groove (60 c), the first spring set (90) is connected with the first latch tongue set (80), the first latch tongue set (80) is vertically arranged with the first guide groove (60 a), the first hinge assembly (70) is fixedly arranged on the first wing tip hinge mounting seat (60), the first connecting rod (40) is selectively matched with the first locking groove (60 b), the second connecting rod (50) is selectively matched with the second locking groove (60 c), and the first latch pin (100) is provided with a first latch groove set (100 a);

the second wingtip rib (110), the third motor (120), the fourth motor (130), the third connecting rod (140) and the fourth connecting rod (150), the second wingtip rib (110) is fixedly arranged at the end of a wing of a second aircraft, the third motor (120) and the fourth motor (130) are arranged on the second wingtip rib (110), the third motor (120) is in driving connection with the third connecting rod (140), the fourth motor (130) is in driving connection with the fourth connecting rod (150), the third motor (120) is used for driving the third connecting rod (140) to move, the fourth motor (130) is used for driving the fourth connecting rod (150) to move, and the moving directions of the third connecting rod (140) and the fourth connecting rod (150) are opposite;

a second wing hinge mount (160), a second hinge assembly (170), a second latch bolt set (180), a second spring set (190), and a second lock pin (200), wherein the second wing hinge mount (160) has a second guide slot (160 a), a third lock slot (160 b), and a fourth lock slot (160 c), the second spring set (190) and the second latch bolt set (180) are connected, the second latch bolt set (180) is disposed perpendicular to the second guide slot (160 a), the second hinge assembly (170) is fixedly disposed on the second wing hinge mount (160), the second guide slot (160 a) is used for guiding the first lock pin (100), the first guide slot (60 a) is used for guiding the second lock pin (200), the third link (140) is selectively engageable with the third lock slot (160 b), the fourth link (150) is selectively engageable with the fourth lock slot (160 c), the second latch bolt set (200 a) is selectively engageable with the second latch bolt set (100 a), and the second latch bolt set (200 a) is selectively engageable with the second latch bolt set (80 a);

a rotating element (210) and a cotter pin (220), the rotating element (210) passing through the first hinge assembly (70) and the second hinge assembly (170) respectively to enable rotatable connection of the first wingtip hinge mount (60) and the second wingtip hinge mount (160), the cotter pin (220) being disposed at an end of the rotating element (210);

wherein, when the wing of the first aircraft is in the folded connection state with the wing of the second aircraft, the first guide groove (60 a) is separated from the second lock pin (200), the second guide groove (160 a) is separated from the first lock pin (100), the first link (40) is engaged with the first locking groove (60 b), the second link (50) is engaged with the second locking groove (60 c), the third link (140) is engaged with the third locking groove (160 b), and the fourth link (150) is engaged with the fourth locking groove (160 c); when the wing of the first aircraft and the wing of the second aircraft are in a unfolding state, the first guide groove (60 a) is matched with the second lock pin (200), the second guide groove (160 a) is matched with the first lock pin (100), the second lock pin groove group (200 a) is matched with the first lock tongue group (80), and the first lock pin groove group (100 a) is matched with the second lock tongue group (180); when the wing of the first aircraft is separated from the wing of the second aircraft, the first link (40) is separated from the first locking groove (60 b), the second link (50) is separated from the second locking groove (60 c), the third link (140) is separated from the third locking groove (160 b), and the fourth link (150) is separated from the fourth locking groove (160 c).

2. The wing tip connection and separation mechanism of a combined type aircraft according to claim 1, wherein any one of the link rods includes a first link section (41), a first link protrusion (42), and a second link protrusion (43), the first link protrusion (42) is connected to one end of the first link section (41), the second link protrusion (43) is connected to the other end of the first link section (41), and any one of the locking recesses includes a first locking hole (61 b) and a second locking hole (62 b), the first link protrusion (42) is selectively engageable with the first locking hole (61 b), and the second link protrusion (43) is selectively engageable with the second locking hole (62 b).

3. The modular aircraft wing tip connection release mechanism of claim 2, wherein the first latch set (80) comprises a first latch tongue (81) and a second latch tongue (82), the first spring set (90) comprises a first spring (91) and a second spring (92), the first spring (91) is connected to the first latch tongue (81), the second spring (92) is connected to the second latch tongue (82), the second latch tongue set (180) comprises a third latch tongue (181) and a fourth latch tongue (182), the second spring set (190) comprises a third spring (191) and a fourth spring (192), the third spring (191) is connected to the third latch tongue (181), the fourth spring (192) is connected to the fourth latch tongue (182), the first latch groove set (100 a) comprises a first latch groove (101 a) and a second latch groove (102 a) which are oppositely disposed, the second latch groove (200 a) comprises a third latch groove (101 a) and a second latch groove (202 a) which are selectively engageable with the third latch tongue (81 a), the second latch groove (201 a) and the fourth latch groove (202 a) are selectively engageable with the latch groove (201 a), the fourth locking tongue (182) is selectively engageable with the second locking pin groove (102 a).

4. The wing tip attachment and detachment mechanism of a modular aircraft according to claim 3, further comprising a first tongue mounting box (240), a second tongue mounting box (250), a third tongue mounting box (260), and a fourth tongue mounting box (270), wherein the first tongue mounting box (240) and the second tongue mounting box (250) are disposed on the first wing tip hinge mount (60), the third tongue mounting box (260) and the fourth tongue mounting box (270) are disposed on the second wing tip hinge mount (160), the first tongue (81) and the first spring (91) are disposed in the first tongue mounting box (240), the second tongue (82) and the second spring (92) are disposed in the second tongue mounting box (250), the third tongue (181) and the third spring (191) are disposed in the third tongue mounting box (260), and the fourth tongue mounting box (182) and the fourth tongue mounting box (270) are disposed in the fourth tongue mounting box (192).

5. The wing tip connection and disconnection mechanism of a modular aircraft according to claim 4, wherein the first lock pin (100) comprises a first lock pin cylindrical section (101) and a first lock pin tapered section (102) which are connected, the first lock pin groove (101 a) and the second lock pin groove (102 a) are oppositely disposed on the first lock pin tapered section (102), the second lock pin (200) comprises a second lock pin cylindrical section (201) and a second lock pin tapered section (202) which are connected, and the third lock pin groove (201 a) and the fourth lock pin groove (202 a) are oppositely disposed on the second lock pin tapered section (202).

6. The combined aircraft wing tip connection and disconnection mechanism of any one of claims 1 to 5, wherein the first hinge assembly (70) comprises a first hinge unit (71), a second hinge unit (72) and a third hinge unit (73) which are sequentially arranged at intervals, the second hinge assembly (170) comprises a fourth hinge unit (171) and a fifth hinge unit (172) which are sequentially arranged at intervals, when the wing of the first aircraft is connected with the wing of the second aircraft, the fourth hinge unit (171) is arranged between the first hinge unit (71) and the second hinge unit (72), and the fifth hinge unit (172) is arranged between the second hinge unit (72) and the third hinge unit (73).

7. The wing tip connecting and disconnecting mechanism of the combined type aircraft as claimed in claim 6, wherein any one of the motors comprises a motor body (21) and a motor telescopic rod (22), the motor telescopic rod (22) is connected with the motor body (21), and the motor telescopic rod (22) is connected with a corresponding connecting rod.

8. The combined aircraft wing tip connection and disconnection mechanism of claim 7, further comprising a first bump block set (280) and a second bump block set (290), wherein the first bump block set (280) is disposed on the first wing tip hinge mount (60), the second bump block set (290) is disposed on the second wing tip hinge mount (160), and the first bump block set (280) and the second bump block set (290) are used for buffering bump impact.

9. The modular aircraft wing tip connection-disconnection mechanism of claim 8, wherein the first bump block set (280) comprises a first bump block (281) and a second bump block (282), the first bump block (281) being disposed on one side of the first wing tip hinge mount (60) and the second bump block (282) being disposed on the other side of the first wing tip hinge mount (60); the second anti-collision block set (290) comprises a third anti-collision block (291) and a fourth anti-collision block (292), the third anti-collision block (291) is arranged on one side of the second wingtip hinge mounting seat (160), and the fourth anti-collision block (292) is arranged on the other side of the second wingtip hinge mounting seat (160).

10. A modular aircraft comprising a first aircraft, a second aircraft and a modular aircraft wing tip attachment and detachment mechanism according to any of claims 1 to 9, the first aircraft being connected to the second aircraft via the modular aircraft wing tip attachment and detachment mechanism.

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