CN117550071A - Aircraft and cross-domain method thereof - Google Patents

Abstract

The application discloses an aircraft and a cross-domain method thereof. The aircraft includes an aircraft body, a first lift system, and a second lift system. The vehicle body has a first shell and a second shell, the first shell comprising a first section and a second section arranged along a first direction, the first direction being parallel to an axial direction of the vehicle body; the second shell is arranged on one side of the first section in a second direction, and the second direction is parallel to the radial direction of the aircraft body. The first mattress-lifting system has a first deployment mechanism and a first flexible bladder, the first deployment mechanism configured to drive the first flexible bladder to collapse and/or to expand snugly along the second casing away from the outer bottom wall of the first casing. The second lifting system is arranged on the second shell and is provided with a second unfolding mechanism and at least two second flexible bags which are arranged at intervals along the first direction, and the second unfolding mechanism is configured to drive the at least two second flexible bags to shrink and/or respectively unfold towards two ends of the outside of the second shell along the first direction.

Description

Aircraft and cross-domain method thereof

Technical Field

The application belongs to the field of aircrafts, and particularly relates to an aircrafts and a cross-domain method thereof.

Background

The air-water interface crossing aircraft is an aircraft which can adapt to an air-water amphibious working environment and has stronger survivability. In general, to achieve rapid take-off of an aircraft across a water-air interface and on the water surface, it is necessary to greatly increase the lift of the aircraft in a short time or reduce the resistance to movement. However, most of the existing cross-domain aircrafts capable of realizing the functions do not have the capability of resisting waves, are only suitable for finishing the take-off and landing process on calm water surfaces, and cannot adapt to complex sea conditions.

Disclosure of Invention

The embodiment of the application provides an aircraft and a cross-domain method thereof, which are used for improving the wave resistance performance of the aircraft and reducing the movement resistance, so that the aircraft is suitable for realizing rapid cross-domain under various water conditions.

According to a first aspect of the present application, embodiments of the present application provide an aircraft comprising: an aircraft body having a first shell and a second shell, the first shell comprising a first section and a second section arranged along a first direction, the first direction being parallel to an axial direction of the aircraft body; the second shell is arranged on one side of the first section in a second direction, and the second direction is parallel to the radial direction of the aircraft body; a first mattress lifting system having a first deployment mechanism and a first flexible bladder, the first deployment mechanism configured to drive the first flexible bladder to collapse and/or to expand snugly along the second housing away from the outer bottom wall of the first housing; and a second lifting system arranged on the second shell and provided with a second folding and unfolding mechanism and at least two second flexible bags which are arranged at intervals along the first direction, wherein the second folding and unfolding mechanism is configured to drive the at least two second flexible bags to shrink and/or respectively unfold towards two ends of the outside of the second shell along the first direction.

Optionally, in the deployed state of the first flexible bladder and the at least two second flexible bladders, the at least two second flexible bladders are respectively located at two opposite ends of the first flexible bladder along the first direction.

Optionally, the first flexible bladder and each second flexible bladder are each contracted within the interior of the second housing in the contracted state.

Optionally, the second housing is provided with a first opening opened and/or covered by the first opening and closing mechanism, and at least two second openings opened and/or covered by at least two second opening and closing mechanisms; the first flexible bags are contracted in the second shell or expanded out of the second shell through the first openings, and each second flexible bag is contracted in the second shell or expanded out of the second shell through a corresponding second opening.

Optionally, the first opening and closing mechanism is configured to open the first opening and drive the first flexible bladder to move to the outside of the second housing through the first opening, and is configured to drive the first flexible bladder to move to the inside of the second housing through the first opening and cover the first opening.

Optionally, the first opening and closing mechanism is arranged in the second shell and comprises a first driving piece, a connecting rod mechanism and a first cover plate; the connecting rod mechanism is connected with the first driving piece, the first cover plate and the first flexible bag, and drives the first cover plate to move along the first direction under the driving action of the first driving piece so as to open and/or cover the first opening, and drives the first flexible bag to move along the second direction so as to enter and exit the second shell through the first opening.

Optionally, the number of the first cover plates is two, the two first cover plates are symmetrically arranged along the first direction and about the first opening, and the link mechanism is hinged with one of the first cover plates; the first opening and closing mechanism further comprises two gear connecting rods symmetrically arranged along the first direction and about the first opening, and two rotating shaft connecting rods symmetrically arranged along the first direction and about the first opening, wherein each gear connecting rod and each rotating shaft connecting rod are configured to rotate around a rotating shaft fixed on the second shell and parallel to the second direction, one ends of the two gear connecting rods are respectively hinged with the two first cover plates in a sliding mode, teeth used for being meshed with each other are respectively arranged at the other ends of the two gear connecting rods, and the two rotating shaft connecting rods are respectively hinged with the two first cover plates.

Optionally, the second opening and closing mechanism is configured to open the second opening and drive the second flexible bladder to move to the outside of the second housing through the second opening, and is configured to drive the second flexible bladder to move to the inside of the second housing through the second opening and cover the second opening.

Optionally, the second opening and closing mechanism includes a second driving member, a rotation support shaft, a first connecting member, a second connecting member, and a second cover plate; the rotary supporting shaft is arranged in the second shell, extends parallel to the bottom wall of the second shell, deviating from the first shell, and is connected with a rotary output shaft of the second driving piece; the first connecting piece and the second connecting piece are fixedly sleeved on the supporting shaft so as to rotate around the rotating supporting shaft under the driving of the second driving piece, the other end of the first connecting piece is connected with the second flexible bag, and the other end of the second connecting piece is connected with the second cover plate.

Optionally, the first folding mechanism includes: the air duct is communicated with the outside of the aircraft body and the first flexible bag; and the air flow driving device is arranged in the air duct and is used for driving external air to enter the first flexible bag through the air duct so as to enable the first flexible bag to be unfolded and/or driving air in the first flexible bag to be discharged through the air duct so as to enable the first flexible bag to be contracted.

Optionally, the second folding mechanism includes: the gas storage device is used for storing gas and is communicated with the air duct; and at least two flexible connecting pipes, each flexible connecting pipe being connected between the gas storage device and a corresponding one of the second flexible bags.

Optionally, the width of the first flexible bag in the third direction in the unfolded state is consistent with the width of the outer bottom wall in the third direction, the third direction is parallel to the radial direction of the aircraft body, and the first direction, the second direction and the third direction are perpendicular to each other; and/or the length of the first flexible bladder in the first direction in the expanded state corresponds to the length of the outer bottom wall in the first direction.

According to a second aspect of the present application, there is also provided a cross-domain method according to any of the above aircraft, the cross-domain method comprising: receiving a cross-domain instruction for indicating a change in aircraft domain; and controlling the first folding and unfolding mechanism to adjust the folding and unfolding state of the first flexible bag and/or controlling the second folding and unfolding mechanism to adjust the folding and unfolding state of at least two second flexible bags according to the cross-domain instruction.

The aircraft provided by the embodiment of the application comprises an aircraft body, a first lifting system and a second lifting system. The vehicle body comprises a first shell and a second shell, the first shell comprises a first section and a second section which are arranged along a first direction, and the second shell is arranged on one side of the first section in a second direction, wherein the first direction is parallel to the axial direction of the vehicle body, and the second direction is parallel to the radial direction of the vehicle body. Therefore, a structure with a broken-order shape can be formed between the second section of the first shell and the second shell, when the aircraft floats on the water surface, the second section of the first shell can be suspended above the water surface, the contact area between the aircraft main body and the water is reduced, the viscous resistance of the aircraft is reduced, and the aircraft can take off quickly to the mid-air cross-domain. The first flexible bag of the first lifting system and the second flexible bag of the second lifting system can provide larger buoyancy when being unfolded, so that the problem of small buoyancy caused by small contact area between the aircraft main body and water is solved. And the first flexible bag is attached and unfolded along the outer bottom wall of the second shell, so that stable buoyancy support can be provided for the aircraft main body; the second flexible bag is expanded to the outside both ends along the first direction of second casing, can play the wave breaking effect in a plurality of directions, and the appearance design of aircraft main part, first flexible bag and the combination of second flexible bag can make the aircraft not only be suitable for at calm water surface quick cross-domain, but also be suitable for at the quick cross-domain of complicated waters condition.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments of the present application will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

Fig. 1 is a schematic structural view of an aircraft according to one embodiment of the present application.

Fig. 2 is a schematic cross-sectional view of fig. 1 along A-A.

Fig. 3 is a schematic structural view of a portion of the components of the aircraft shown in fig. 1.

Fig. 4 is a schematic exploded view of some of the elements of the aircraft of fig. 1.

Fig. 5 is a schematic view of the structure of a second opening and closing mechanism and a second flexible bladder of the aircraft of fig. 1.

Fig. 6 is a schematic view of another part of the components of the aircraft of fig. 1.

Fig. 7 is a flow diagram of a cross-domain method of an aircraft according to one embodiment of the present application.

Detailed Description

Features and exemplary embodiments of various aspects of the present application are described in detail below to make the objects, technical solutions and advantages of the present application more apparent, and to further describe the present application in conjunction with the accompanying drawings and the detailed embodiments. It should be understood that the specific embodiments described herein are merely configured to explain the present application and are not configured to limit the present application. It will be apparent to one skilled in the art that the present application may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present application by showing examples of the present application.

It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising … …" does not exclude the presence of other like elements in a process, method, article or apparatus that comprises the element.

It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The embodiments will be described in detail below with reference to the accompanying drawings.

Fig. 1 is a schematic structural view of an aircraft according to an embodiment of the present application, and fig. 2 is a schematic sectional structural view of fig. 1 in A-A direction. Referring to fig. 1 and 2, an aircraft 1 provided in an embodiment of the present application includes an aircraft body 10, a first lift system, and a second lift system.

The aircraft body 10 has a first shell 11 and a second shell 12, the first shell 11 comprising a first section 111 and a second section 112 arranged along a first direction X, the first direction X being parallel to the axial direction of the aircraft body 10. The second shell 12 is provided on one side of the first section 111 in a second direction Y, which is parallel to the radial direction of the aircraft body 10. The first mattress lifting system has a first deployment mechanism 21 and a first flexible bladder 22, the first deployment mechanism 21 being configured to drive the first flexible bladder 22 to collapse and/or to expand snugly along the second housing 12 away from the outer bottom wall 121 of the first housing 11. The second cushion-up system is provided on the second housing 12, and has a second deployment mechanism 31 and at least two second flexible bags 32 arranged at intervals along the first direction X, and the second deployment mechanism 31 is configured to drive the at least two second flexible bags 32 to contract and/or to respectively expand toward both ends of the outside of the second housing 12 along the first direction X.

The first housing 11 and the second housing 12 may be integrally formed, or may be fixedly connected together by welding, riveting, or the like. The inner space of the first housing 11 may be partitioned from the inner space of the second housing 12 by a partition plate so as to arrange related components in the first housing 11 and the second housing 12, respectively.

The first section 111 may be adjacent to a fore portion of the aircraft body 10 in the first direction X and the second section 112 may be adjacent to a aft portion of the aircraft body 10 in the first direction X. A second shell 12 provided on one side of the first section 111 in the second direction Y is also adjacent to the bow of the aircraft body 10.

The axial direction of the vehicle body 10 may be a length direction of the vehicle body 10, and the second direction Y may be a radial direction parallel to a width direction of the vehicle body 10.

The first flexible bladder 22 and the second flexible bladder 32 may be air bags, air cushions, air bags, or the like, which may be inflated or deflated to change the configuration. The volume of the first flexible bladder 22 in the deployed state is greater than the volume of the second flexible bladder 32 in the deployed state.

In the embodiment shown in fig. 1, the first flexible bladder 22 and each second flexible bladder 32 of the vehicle 1 are both in an expanded state, and in the embodiment shown in fig. 2, the first flexible bladder 22 and each second flexible bladder 32 of the vehicle 1 are both in a contracted state.

The aircraft 1 provided in the embodiment of the present application includes an aircraft body 10, a first ascent system, and a second ascent system. The aircraft body 10 comprises a first hull 11 and a second hull 12, the first hull 11 comprising a first section 111 and a second section 112 arranged in a first direction X, the second hull 12 being provided on one side of the first section 111 in a second direction Y. Wherein the first direction X is parallel to the axial direction of the aircraft body 10 and the second direction Y is parallel to the radial direction of the aircraft body 10. Thereby, a broken-order morphology can be formed between the second section 112 of the first housing 11 and the second housing 12. When the aircraft 1 floats on the water surface, the second section 112 of the first shell 11 can be suspended above the water surface, so that the contact area between the aircraft body 10 and the water is reduced, the viscous resistance of the aircraft 1 is reduced, and the aircraft 1 can take off quickly to cross-domain in space. The first flexible bladder 22 of the first lift system and the second flexible bladder 32 of the second lift system can provide greater buoyancy when deployed, which overcomes the problem of low buoyancy caused by the small contact area of the aircraft body 10 with water due to the broken-order morphological structural design. Also, the first flexible bladder 22 is snugly deployed along the outer bottom wall 121 of the second casing 12, which may provide stable buoyant support for the aircraft body 10. The second flexible bag 32 is unfolded towards the two ends of the second shell 12 along the first direction X, so that the wave breaking effect can be achieved in multiple directions, and the appearance design of the aircraft body 10, the combination of the first flexible bag 22 and the second flexible bag 32 can enable the aircraft 1 to be suitable for not only rapidly crossing the domain on calm water, but also rapidly crossing the domain in complex water conditions.

In some embodiments, in the expanded state of both the first flexible bladder 22 and the at least two second flexible bladders 32, the at least two second flexible bladders 32 are positioned at opposite ends of the first flexible bladder 22 in the first direction X, respectively.

In the deployed state of both the first flexible bladder 22 and the at least two second flexible bladders 32, the at least two second flexible bladders 32 may be symmetrically distributed at opposite ends of the first flexible bladder 22 in the first direction X.

The number of second flexible bags 32 may be an even number, and the number of second flexible bags 32 at both ends of the first flexible bag 22 in the first direction X thereof is the same. Illustratively, the number of second flexible bladders 32 may be two, with two second flexible bladders 32 being symmetrically disposed at opposite ends of first flexible bladder 22 in first direction X.

According to the embodiment of the application, at least two second flexible bags 32 are unfolded at two opposite ends of the first flexible bag 22 along the first direction X, and the wave breaking effect can be achieved along any direction of the first direction X, so that the wave resistance of the aircraft 1 is improved.

In some embodiments, first flexible bladder 22 and each second flexible bladder 32 are both contracted inside second housing 12 in the contracted state.

The first flexible bladder 22 and the second flexible bladder 32 are each deployed outside the second housing 12 in a deployed state to effectively lift the buoyancy of the vehicle 1 in or on the water. The first flexible bag 22 and the second flexible bag 32 are contracted in the second shell 12 in the contracted state, and when the aircraft 1 spans an airspace, the first flexible bag 22 and the second flexible bag 32 do not increase the aerodynamic resistance of the aircraft 1, so that the aircraft 1 can take off quickly.

In some embodiments, the second housing 12 is provided with a first opening 122 that is opened and/or covered by the first opening and closing mechanism 40, and at least two second openings 123 that are opened and/or covered by the at least two second opening and closing mechanisms 50. The first flexible bags 22 are contracted inside the second housing 12 or expanded outside the second housing 12 through the first openings 122, and each of the second flexible bags 32 is contracted inside the second housing 12 or expanded outside the second housing 12 through a corresponding one of the second openings 123.

The first opening and the second opening may both be provided in a bottom wall of the second housing 12 facing away from the first housing 11. The first openings 122 may be located at a middle portion of the bottom wall of the second housing 12 in the first direction X, and each of the second openings 123 may be located at two opposite end portions of the bottom wall of the second housing 12 in the first direction X.

By providing the first opening and the second opening on the second housing 12, the first flexible bag 22 and the second flexible bag 32 can be allowed to enter and exit the second housing 12 through the first opening and the second opening respectively, so that the switching of the folded and unfolded states is realized. The first opening is opened and/or covered by the first opening and closing mechanism 40, and the second opening is opened and/or covered by the second opening and closing mechanism 50, so that water or air can be effectively prevented from being poured into the second housing 12 through the first opening and the second opening.

In some embodiments, the first opening and closing mechanism 40 is configured to open the first opening and move the first flexible bladder 22 through the first opening to the exterior of the second housing 12, and is configured to move the first flexible bladder 22 through the first opening to the interior of the second housing 12 and cover the first opening.

When the first flexible bag 22 needs to be deployed, the first opening and closing mechanism 40 may drive the first flexible bag 22 to move toward the first opening while opening the first opening, and when the first opening is safely opened, the first flexible bag 22 moves to the outside of the second housing 12. When the first flexible bag 22 needs to be contracted, the first contraction and expansion mechanism 21 firstly contracts the first flexible bag 22 to reduce the volume thereof. Then, the first opening and closing mechanism 40 drives the contracted first flexible bag 22 to move into the second housing 12 through the first opening and gradually cover the first opening. After the first flexible bladder 22 is moved into the second housing 12, the first opening is completely covered.

According to the embodiment of the application, the first opening is opened and closed through the first opening and closing mechanism 40, and the first flexible bag 22 is driven to enter and exit the second shell 12, so that the structure integration level is high, the structure is simple, and the state switching efficiency of the first flexible bag 22 is improved.

Fig. 3 is a schematic structural view of a part of the components of the aircraft shown in fig. 1, and fig. 4 is an exploded schematic structural view of a part of the components of the aircraft shown in fig. 1. Referring to fig. 2, 3 and 4, in some embodiments, a first opening and closing mechanism 40 is provided within the second housing 12 and includes a first driver 41, a linkage 42 and a first cover plate 43. The linkage 42 is connected to the first driving member 41, the first cover plate 43 and the first flexible bag 22, and the linkage 42 drives the first cover plate 43 to move along the first direction X to open and/or cover the first opening under the driving action of the first driving member 41, and drives the first flexible bag 22 to move along the second direction Y to pass in and out the second housing 12 through the first opening.

The link mechanism 42 may include a first link assembly 421 and a second link assembly 422 hinged to each other, and one end 4211 of the first link assembly 421 is connected to the first driving member 41 for movement in the first direction X under the driving of the first driving member 41. One end 4211 of the first link assembly 421 is further hinged to the first cover plate 43 to drive the first cover plate 43 to move synchronously along the first direction X when moving along the first direction X, and to pivot relative to the first cover plate 43. The first cover plate 43 may be moved in the first direction X by the first link assembly 421 to open and/or cover the first opening. The second link assembly 422 includes a first link 4221 and a second link 4222 hinged to each other, and the first link assembly 421 is hinged to a hinge shaft of the first link 4221 and the second link 4222. One end of the first link 4221 is hinged to a support frame 60 in the second housing 12, and the second link 4222 is connected to the first flexible bladder 22. When one end 4211 of the first link assembly 421 moves along the first direction X, the first link 4221 and the second link 4222 are driven to pivot, so as to adjust the position of the first flexible bladder 22 in the second direction Y. By the articulation of the first linkage assembly 421 and the second linkage assembly 422, the first flexible bladder 22 is moved in the second direction Y to move in and out of the second housing 12 through the first opening.

The first driving member 41 is coupled to the first end of the linkage mechanism 42 in a manner including, but not limited to, a fixed connection, a mating connection, etc. The first driving member 41 may include a motor capable of rotating in forward and reverse directions.

The first cover 43 may be disposed on an inner bottom wall of the second housing 12 and move along the first direction X to improve a sealing effect between the first cover 43 and the second housing 12.

It will be appreciated that in the deployed state of the first flexible bladder 22, a partial region of the first flexible bladder 22 may occlude the first opening, thereby avoiding the ingress of water or air into the second housing 12 through the first opening.

In some embodiments, the number of first cover plates 43 is two, and two first cover plates 43 are symmetrically disposed about the first opening along the first direction X, and the link mechanism 42 is hinged to one of the first cover plates 43. The first opening and closing mechanism 40 further includes two gear links 44 disposed symmetrically about the first opening in the first direction X, and two rotating shaft links 45 disposed symmetrically about the first opening in the first direction X, each of the gear links 44 and each of the rotating shaft links 45 being configured to rotate about a rotating shaft fixed to the second housing 12 and parallel to the second direction Y, one ends of the two gear links 44 being slidably hinged with the two first cover plates 43, respectively, the other ends of the two gear links 44 being provided with serrations 444 for meshing with each other, respectively, and the two rotating shaft links 45 being hinged with the two first cover plates 43, respectively.

The rotational axes of the gear links 44 and the rotational axis links 45 are different from each other.

The gear link 44 and the spindle link 45 each rotate in a plane parallel to the bottom wall of the second housing 12. Each gear link 44 is generally L-shaped and includes a first rod segment 441 and a second rod segment 442. The first rod section 441 is provided with a sliding groove 443 extending along the length direction thereof, the first cover plate 43 is provided with a sliding block 431 in a protruding manner, and the sliding block 431 is slidably inserted into the sliding groove 443. The toothing 444 of the gear link 44 is formed at the end of the second rod section 442. The toothed ends of the two gear links 44 mesh. During the process that the link mechanism 42 drives one of the first cover plates 43 to move, one of the gear links 44 connected with the first cover plate 43 rotates, and under the meshing action, the one of the gear links 44 drives the other gear link 44 to rotate, so that the other first cover plate 43 is driven to move along the first direction X.

According to the embodiment of the application, the first openings are opened and closed through the two first cover plates 43, so that the moving displacement of the single first cover plate 43 is reduced, the moving stroke of the link mechanism 42 is shortened, the space occupied by the first opening and closing mechanism 40 is reduced, and the structure is more compact. According to the embodiment of the application, by arranging the symmetrical two gear connecting rods 44, the two first cover plates 43 can be driven to synchronously move through one connecting rod mechanism 42, so that the number of the connecting rod mechanisms 42 is reduced, the structure is further simplified, and the control precision is improved. Furthermore, the arrangement of the two rotating shaft connecting rods 45 can exert guiding and limiting effects on the movement of the two first cover plates 43, so that the possibility of position deviation of the two first cover plates 43 is reduced.

In some embodiments, the second opening and closing mechanism 50 is configured to open the second opening and move the second flexible bladder 32 through the second opening to the exterior of the second housing 12, and is configured to move the second flexible bladder 32 through the second opening to the interior of the second housing 12 and cover the second opening.

When the second flexible bag 32 needs to be deployed, the second opening and closing mechanism 50 can drive the second flexible bag 32 to move towards the second opening while opening the second opening, and when the second opening is safely opened, the second flexible bag 32 moves to the outside of the second housing 12. When the second flexible bag 32 needs to be contracted, the second contraction and expansion mechanism 31 firstly contracts the second flexible bag 32 to reduce the volume thereof. Then, the second opening and closing mechanism 50 drives the contracted second opening of the second flexible bag 32 to move into the second housing 12, and gradually covers the second opening. After the second flexible bladder 32 is moved into the second housing 12, the second opening is completely covered.

According to the embodiment of the application, the second opening is opened and closed through the second opening and closing mechanism 50, and the second flexible bag 32 is driven to enter and exit the second shell 12, so that the structure integration level is high, the structure is simple, and the state switching efficiency of the second flexible bag 32 is improved.

Fig. 5 is a schematic view of the structure of a second opening and closing mechanism and a second flexible bladder of the aircraft of fig. 1. In some embodiments, the second opening and closing mechanism 50 includes a second driving member 51, a rotation support shaft 52, a first connecting member 53, a second connecting member 54, and a second cover plate 55. The rotation support shaft 52 is provided in the second housing 12 and extends parallel to the bottom wall of the second housing 12 facing away from the first housing 11, and the rotation support shaft 52 is connected to the rotation output shaft of the second driving member 51. The first connecting piece 53 and the second connecting piece 54 are fixedly sleeved on the supporting shaft 52 so as to rotate along with the rotating supporting shaft 52 under the driving of the second driving piece 51, the other end of the first connecting piece 53 is connected to the second flexible bag 32, and the other end of the second connecting piece 54 is connected to the second cover plate 55.

The first and second connection members 53 and 54 are disposed along the axial direction of the rotation support shaft 52 and fixedly connected to the second flexible bladder 32 and the second cover plate 55, respectively. When the first connecting piece 53 rotates along with the rotation supporting shaft 52, the second flexible bag 32 can be driven to rotate, so that the second flexible bag 32 generates a partial displacement along the second direction Y, and the movement of the second flexible bag 32 in the second direction Y is realized. When the second link 54 rotates with the rotation support shaft 52, the second cover plate 55 is rotated, thereby switching between a position covering the second opening and a position opening the second opening.

In the expanded state of the second flexible bladder 32, the second cover plate 55 may be positioned inside the second flexible bladder 32 toward the first flexible bladder 22 to reduce the fluid resistance created by the second cover plate 55. In the deployed state of both the second flexible bladder 32 and the first flexible bladder 22, the second cover plate 55 may be positioned between the second flexible bladder 32 and the first flexible bladder 22.

The first and second connection members 53 and 54 may each be a connection plate to improve connection stability.

It will be appreciated that in the deployed state of the second flexible bladder 32, a partial region of the second flexible bladder 32 may occlude the second opening, thereby avoiding the ingress of water or air into the second housing 12 through the second opening.

In some embodiments, the first retracting mechanism 21 includes an air duct 211 and an airflow driving device 212. The air duct 211 communicates with the exterior of the aircraft body 10 and the first flexible bladder 22. An air flow driving device 212 is disposed in the air duct 211 for driving external air into the first flexible bag 22 through the air duct 211 to cause the first flexible bag 22 to expand and/or driving air in the first flexible bag 22 to be discharged through the air duct 211 to cause the first flexible bag 22 to contract.

The air flow outlet of the air flow drive device 212 may be in indirect communication with the first flexible bladder 22 via the air delivery conduit 90.

The air duct 211 may extend through the first and second housings 11 and 12 in the second direction Y, and one end of the air duct 211 may communicate with the outside through an air vent 113 opened on a top wall of the first housing 11 facing away from the second housing 12. The vent 113 is provided with a breathable waterproof membrane that allows only gas to pass therethrough.

The airflow driving device 212 may be a fan, the fan type including but not limited to axial flow, centrifugal or through-flow, etc. The airflow driving device 212 may be mounted on the support frame 60.

An on-off valve may be provided in the air pipe 90, and when the on-off valve is opened, the air channel 211 is communicated with the first flexible bag 22, and when the on-off valve is closed, the communication between the air channel 211 and the first flexible bag 22 is blocked.

Fig. 6 is a schematic view of another part of the components of the aircraft of fig. 1. In some embodiments, the second deployment mechanism 31 includes a gas storage device 311 and at least two flexible connecting tubes 312. The gas storage device 311 is used for storing gas and is communicated with the air duct 211. Each flexible connection pipe 312 is connected between the gas storage device 311 and a corresponding one of the second flexible bags 32.

The air storage device 311 and the air duct 211 may be communicated through a connection pipe 313, and a control valve may be provided in the connection pipe 313. When the control valve is opened, the air flow driving device 212 can convey air into the air storage device 311 through the air duct 211, and when the control valve is closed, communication between the air storage device 311 and the air duct 211 is blocked.

The air storage device 311 can be further provided with a pressure sensor 314 to detect the air pressure in the air storage device 311 in real time, so as to ensure the stability of the air charging process.

The flexible connection pipe 312 may deform to some extent with the movement of the second flexible bladder 32 and maintain the communication relationship between the air storage device 311 and the second flexible bladder 32.

The gas storage device 311 may be a high pressure gas storage tank. The number of air storage devices 311 is the same as the number of second flexible bags 32 to configure one air storage device 311 for each second flexible bag 32, respectively.

By arranging the gas storage device 311, certain gas is stored for the second flexible bag 32, so that the second flexible bag 32 can be unfolded in time under special conditions.

In some embodiments, the width of the first flexible bladder 22 in the third direction Z in the deployed state corresponds to the width of the outer bottom wall 121 in the third direction Z, the third direction Z being parallel to the radial direction of the aircraft body 10, the first direction X, the second direction Y, and the third direction Z being perpendicular. Thereby, the first flexible bladder 22 can stably support the second housing 12 in the third direction Z.

In some embodiments, the length of first flexible bladder 22 in the first direction X in the expanded state corresponds to the length of outer bottom wall 121 in first direction X. Thereby, the first flexible bladder 22 can stably support the second housing 12 in the first direction X.

The width of the first flexible bladder 22 in the third direction Z and the length of the first flexible bladder in the first direction X are the same as the width and length of the outer bottom wall 121, respectively, which corresponds to the projection of the first flexible bladder 22 in the plane of the outer bottom wall 121 and the projection of the outer bottom wall 121 in the plane overlap each other after the first flexible bladder is deployed, so that a uniform and stable floating effect can be achieved on the entire aircraft body 10.

In some embodiments, the end of the second section 112 facing away from the first section 111 in the first direction X is provided with a propulsion device 70, the propulsion device 70 being configured to rotate about an axis of rotation parallel to the first direction X. The side of the first hull 11 facing away from the second hull 12 in the second direction Y is provided with wings 80, the wings 80 being controllably deployed to extend in the radial direction of the aircraft body 10 or to be folded in parallel with the axial direction of the aircraft body 10.

The propulsion device 70 serves as a power unit of the aircraft 1 for driving the aircraft 1 for sailing. Since the propulsion device 70 is disposed at the end of the second section 112 facing away from the first section 111 along the first direction X, when the vehicle 1 is on the water surface, the propulsion device 70 is suspended above the water surface as the second section 112, no matter whether the vehicle 1 is in the water area or the airspace medium, the rotation of the propulsion device 70 is not affected, and the propulsion device 70 can provide greater power for the vehicle 1, so that the maneuvering performance of the vehicle 1 is improved.

In some embodiments, the aircraft 1 may further comprise a communication unit, a heading adjustment unit, a counterweight unit, a wing steering engine, a control unit, etc. The communication unit and the course adjustment unit may be disposed outside the first housing 11, and the counterweight unit, the wing steering engine, the control unit, and the like may be disposed inside the first housing 11.

According to a second aspect of the present application, embodiments of the present application further provide a method for cross-domain of an aircraft, which is applied to the aircraft 1 according to any of the foregoing embodiments. Fig. 7 is a schematic flow chart of a cross-domain method of an aircraft according to an embodiment of the present application, referring to fig. 7, the cross-domain method of an aircraft provided in the embodiment of the present application includes:

step S10, receiving a cross-domain instruction for indicating to change the navigation domain of the aircraft 1; and

step S20, controlling the first deployment mechanism 21 to adjust the deployment state of the first flexible bladder 22 and/or controlling the second deployment mechanism 31 to adjust the deployment state of the at least two second flexible bladders 32 according to the cross-domain instruction.

The first flexible bladder 22 is snugly deployed along the outer bottom wall 121 of the second shell 12 to provide stable buoyant support for the aircraft body 10. The second flexible bag 32 is unfolded towards the two ends of the second shell 12 along the first direction X, so that the wave breaking effect can be achieved in multiple directions, and the appearance design of the aircraft body 10, the combination of the first flexible bag 22 and the second flexible bag 32 can enable the aircraft 1 to be suitable for not only rapidly crossing the domain on calm water, but also rapidly crossing the domain in complex water conditions.

In some embodiments, when the cross-domain instruction is used to instruct the aircraft 1 to change from underwater navigation to water navigation, step S20 may specifically include: controlling the second deploying and retracting mechanism 31 to deploy at least two second flexible bags 32 to the front and rear ends outside the second housing 12 respectively; after the aircraft 1 floats to the water surface, the first unfolding mechanism 21 is controlled to unfold the first flexible bag 22 along the outer bottom wall of the second shell 12; after the first flexible bladder 22 is deployed, the second deployment mechanism 31 may be selectively controlled to collapse at least two second flexible bladders 32. When the water surface is calm, the second retracting mechanism 31 can be controlled to retract at least two second flexible bags 32; at least two second flexible bladders 32 may be maintained in an expanded condition when the surface waves are large.

In some embodiments, when the cross-domain instruction is used to instruct the aircraft 1 to change from the water voyage to the air voyage, step S20 may specifically include: after the aircraft 1 is separated from the water surface, the first deployment mechanism 21 is controlled to retract the first flexible bladder 22. Further, the second retracting mechanism 31 may also be controlled to retract at least two second flexible bladders 32.

In some embodiments, when the cross-domain instruction is used to instruct the aircraft 1 to change from an air voyage to a water voyage, step S20 may specifically include: when the vertical distance between the vehicle 1 and the water surface reaches the preset distance, the second deployment mechanism 31 is controlled to deploy at least two second flexible bags 32 to the front and rear ends of the outside of the second casing 12, respectively, and the first deployment mechanism 21 is controlled to deploy the first flexible bag 22 along the outer bottom wall 121 of the second casing 12 in a fitting manner, and the deployment sequence of the first flexible bag 22 and the second flexible bag 32 is not particularly limited; after the aircraft 1 contacts the water surface, the at least two second flexible bags 32 are selectively contracted by the second retracting mechanism 31 according to the water surface condition, and the details are not repeated here.

In some embodiments, when the cross-domain instruction is used to instruct the aircraft 1 to change from a water voyage to an underwater voyage, step S20 may specifically include: the first deployment mechanism 21 is controlled to deflate the first flexible bladder 22. Further, the second retracting mechanism 31 may also be controlled to retract at least two second flexible bladders 32.

In some embodiments, when the cross-domain instruction is used to instruct the aircraft 1 to change from an air voyage to an underwater voyage, step S20 may specifically include: when the vertical distance between the aircraft 1 and the water surface reaches the preset distance, the second unfolding mechanism 31 is controlled to unfold at least two second flexible bags 32 to the front and rear ends outside the second shell 12 respectively, and the first unfolding mechanism 21 is controlled to unfold the first flexible bags 22 along the outer bottom wall 121 of the second shell 12 in a fitting manner; after the aircraft 1 is in contact with the water surface, the second deployment mechanism 31 is controlled to collapse at least two second flexible bags 32 and the first flexible bag 22 is contracted by the first deployment mechanism 21.

In some embodiments, when the cross-domain instruction is used to instruct the aircraft 1 to change from underwater navigation to airborne navigation, step S20 may specifically include: controlling the second deploying and retracting mechanism 31 to deploy at least two second flexible bags 32 to the front and rear ends outside the second housing 12 respectively; after the aircraft 1 leaves the water surface, the second deployment mechanism 31 is controlled to collapse at least two second flexible bags 32.

In the description of the embodiments of the present application, the term "and/or" is merely an association relationship describing an association object, and indicates that three relationships may exist, for example, m and/or n may indicate: m alone, m and n simultaneously, and n alone. In addition, the character "/" herein generally indicates that the front and rear associated objects are an "or" relationship.

In the description of the embodiments of the present application, the orientation or positional relationship indicated by the technical terms "vertical", "horizontal", "top", "bottom", "inside", "outside", "circumferential", etc. are based on the orientation or positional relationship shown in the drawings, merely for convenience of describing the embodiments of the present application and simplifying the description, and are not indicative or implying that the apparatus or element in question must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the embodiments of the present application.

In the description of the embodiments of the present application, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured" and the like are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally formed; or may be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the embodiments of the present application will be understood by those of ordinary skill in the art according to the specific circumstances.

In the examples of the present application, "parallel" includes not only the case of absolute parallelism but also the case of substantially parallelism as is conventionally recognized in engineering; meanwhile, "vertical" includes not only the case of absolute vertical but also the case of substantially vertical as conventionally recognized in engineering. Illustratively, the angle between the two directions is 85 ° -90 °, which can be considered to be perpendicular; the included angle between the two directions is 0-5 degrees, and the two directions can be considered to be parallel.

While the invention has been described with reference to certain preferred embodiments, it will be understood by those skilled in the art that various changes and substitutions of equivalents may be made and equivalents will be apparent to those skilled in the art without departing from the scope of the invention. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (13)

1. An aircraft, comprising:

an aircraft body having a first shell and a second shell, the first shell comprising a first section and a second section arranged along a first direction, the first direction being parallel to an axial direction of the aircraft body; the second shell is arranged on one side of the first section in a second direction, and the second direction is parallel to the radial direction of the aircraft body;

a first lift system having a first deployment mechanism and a first flexible bladder, the first deployment mechanism configured to drive the first flexible bladder to collapse and/or to expand snugly along the second housing away from the outer bottom wall of the first housing; and

the second lifting system is arranged on the second shell, and is provided with a second folding and unfolding mechanism and at least two second flexible bags which are arranged at intervals along the first direction, and the second folding and unfolding mechanism is configured to drive the at least two second flexible bags to shrink and/or respectively unfold towards the two ends of the outer part of the second shell along the first direction.

2. The vehicle of claim 1, wherein the vehicle is configured to,

and in the state that the first flexible bag and the at least two second flexible bags are both unfolded, the at least two second flexible bags are respectively positioned at two opposite ends of the first flexible bag along the first direction.

3. The vehicle of claim 1, wherein the vehicle is configured to,

the first flexible bladder and each of the second flexible bladders are contracted inside the second housing in a contracted state.

4. The vehicle of claim 3, wherein the vehicle is configured to,

the second housing is provided with a first opening which is opened and/or covered by a first opening and closing mechanism, and at least two second openings which are opened and/or covered by at least two second opening and closing mechanisms;

the first flexible bags are contracted in the second shell or expanded out of the second shell through the first openings, and each second flexible bag is contracted in the second shell or expanded out of the second shell through a corresponding second opening.

5. The vehicle of claim 4, wherein the vehicle is configured to,

the first opening and closing mechanism is configured to open the first opening and drive the first flexible bladder to move to the outside of the second housing through the first opening, and is configured to drive the first flexible bladder to move to the inside of the second housing through the first opening and cover the first opening.

6. The vehicle of claim 5, wherein the first opening and closing mechanism is disposed within the second housing and comprises a first driver, a linkage, and a first cover plate;

the connecting rod mechanism is connected with the first driving piece, the first cover plate and the first flexible bag, and drives the first cover plate to move along the first direction under the driving action of the first driving piece so as to open and/or cover the first opening, and drives the first flexible bag to move along the second direction so as to pass through the first opening to enter and exit the second shell.

7. The vehicle of claim 6, wherein the vehicle is configured to,

the number of the first cover plates is two, the two first cover plates are symmetrically arranged along the first direction and are related to the first opening, and the connecting rod mechanism is hinged with one of the first cover plates;

the first opening and closing mechanism further comprises two gear connecting rods symmetrically arranged along the first direction and relative to the first opening, two rotating shaft connecting rods symmetrically arranged along the first direction and relative to the first opening, each gear connecting rod and each rotating shaft connecting rod are configured to rotate around a rotating shaft fixed on the second shell and parallel to the second direction, one end of each gear connecting rod is respectively hinged with the two first cover plates in a sliding mode, the other ends of the two gear connecting rods are respectively provided with toothed patterns used for being meshed with each other, and the two rotating shaft connecting rods are respectively hinged with the two first cover plates.

8. The vehicle of claim 4, wherein the vehicle is configured to,

the second opening and closing mechanism is configured to open the second opening and drive the second flexible bladder to move to the outside of the second housing through the second opening, and is configured to drive the second flexible bladder to move to the inside of the second housing through the second opening and cover the second opening.

9. The vehicle of claim 8, wherein the vehicle is configured to,

the second opening and closing mechanism comprises a second driving piece, a rotary supporting shaft, a first connecting piece, a second connecting piece and a second cover plate; wherein the method comprises the steps of

The rotary supporting shaft is arranged in the second shell, extends parallel to the bottom wall of the second shell, which is away from the first shell, and is connected with the rotary output shaft of the second driving piece; the first connecting piece and the second connecting piece are fixedly sleeved on the supporting shaft, so that the first connecting piece and the second connecting piece rotate around the rotating supporting shaft under the driving of the second driving piece, the other end of the first connecting piece is connected with the second flexible bag, and the other end of the second connecting piece is connected with the second cover plate.

10. The vehicle of claim 1, wherein the first deployment mechanism comprises:

the air duct is communicated with the outside of the aircraft main body and the first flexible bag; and

the air flow driving device is arranged in the air duct and used for driving external air to enter the first flexible bag through the air duct so as to enable the first flexible bag to be unfolded and/or driving air in the first flexible bag to be discharged through the air duct so as to enable the first flexible bag to be contracted.

11. The vehicle of claim 10, wherein the second deployment mechanism comprises:

the gas storage device is used for storing gas and is communicated with the air duct; and

and at least two flexible connecting pipes, wherein each flexible connecting pipe is connected between the gas storage device and a corresponding second flexible bag.

12. The vehicle of claim 1, wherein the vehicle is configured to,

the width of the first flexible bag in the third direction in the unfolded state is consistent with the width of the outer bottom wall in the third direction, the third direction is parallel to the radial direction of the aircraft main body, and the first direction, the second direction and the third direction are perpendicular to each other; and/or

The length of the first flexible bladder in the first direction in the deployed state corresponds to the length of the outer bottom wall in the first direction.

13. A method of cross-domain aircraft according to any one of claims 1 to 12, comprising:

receiving a cross-domain instruction for instructing a change in the aircraft's domain; and

and controlling the first folding and unfolding mechanism to adjust the folding and unfolding state of the first flexible bags and/or controlling the second folding and unfolding mechanism to adjust the folding and unfolding state of the at least two second flexible bags according to the cross-domain instruction.