Distributed propulsion device

Abstract

The present invention discloses a distributed propulsion device, which includes a flight assembly composed of multiple aircrafts. At least two adjacent aircrafts are flexibly connected to enable the projection of the distributed propulsion device to change. During the flight of the distributed propulsion device, according to the actual environmental needs, the relatively positions of the flexibly connected aircrafts can be changed, thereby changing the structure of the distributed propulsion device. In the distributed propulsion device provided in this application, since at least two adjacent aircrafts are flexibly connected to enable the projection of the distributed propulsion device to change, that is, the distributed propulsion device can change its shape according to the environment, and thus adapt to various positions that need to be flown through. Therefore, the versatility of the distributed propulsion device is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and particularly to a distributed propulsion device. Background Art

[0002] An aircraft is a flying object that can leave the ground, fly in space and be controlled by humans. With the development of science, various aircraft have gradually emerged. For example, a ducted rotor manned flying vehicle that appears to relieve road traffic pressure can not only achieve vertical takeoff and landing and hover flight like a helicopter, but also drive on ordinary roads. It is a convenient and widely used three-dimensional transportation vehicle.

[0003] The power part of a traditional aircraft consists of multiple fixedly connected aircraft, where adjacent aircraft are fixedly connected to provide power during flight.

[0004] However, due to the fixed shape and size of the aircraft, when flying in complex low-altitude or narrow tunnels, it is easy to interfere and collide with the surrounding environment, resulting in low versatility of the propulsion device.

[0005] Therefore, how to improve the versatility of the distributed propulsion device is a technical problem that needs to be solved urgently by those skilled in the art. Summary of the Invention

[0006] The object of the present invention is to provide a distributed propulsion device with improved versatility.

[0007] To achieve the above object, the present invention provides a distributed propulsion device, including a flight assembly composed of multiple aircraft, and at least two adjacent aircraft are flexibly connected so that the projection of the distributed propulsion device changes.

[0008] Preferably, the aircraft of the flight assembly are arranged in an array, and at least two adjacent aircraft are flexibly connected through a first rotating device.

[0009] Preferably, the aircraft are arranged in a matrix, and at least two longitudinally adjacent rows of the aircraft are flexibly connected, and the two flexibly connected rows of aircraft are rotatably connected one-to-one through a first rotating device.

[0010] Preferably, two adjacent aircraft in each transverse column are fixedly connected.

[0011] Preferably, at least two adjacent transverse columns of the aircraft are rotatably connected through a second rotating device.

[0012] Preferably, a plurality of the aircraft are arranged in a circular array, and adjacent two circles of the aircraft are connected. Among adjacent two circles of the aircraft, at least the outer circle of the aircraft is rotatably connected to the adjacent inner circle of the aircraft through a first rotating device, and the rotatable aircraft in the same circle are rotatably connected through the second rotating device.

[0013] Preferably, the first rotating device and / or the second rotating device is a connecting rod driving device. The connecting rod driving device includes a connecting rod assembly hinged to each other and a connecting rod control device for driving the connecting rod assembly to rotate. Opposite ends of the connecting rod assembly are fixedly connected to adjacent two of the aircraft.

[0014] Preferably, the connecting rod control device includes a telescopic rod and a control device for controlling the telescopic movement of the telescopic rod; the connecting rod assembly includes a hinged rod and a hinge seat hinged to one end of the hinged rod. The hinge seat and the other end of the hinged rod are respectively fixedly connected to adjacent two of the aircraft. One end of the telescopic rod is hinged to the rod body of the hinged rod, and the other end is hinged to the aircraft where the hinge seat is installed.

[0015] Preferably, the connecting rod assembly includes a first connecting rod and a second connecting rod hinged to the first connecting rod. The first connecting rod and the second connecting rod are respectively fixedly connected to adjacent two of the aircraft; the connecting rod control device includes a cable and a cable winding and unwinding device for controlling the winding and unwinding of the cable. When the cable is wound and unwound, the first connecting rod and the second connecting rod rotate around the hinge point.

[0016] Preferably, the aircraft at the edge share one connecting rod control device, and the aircraft at the edge is flexibly connected to the adjacent inner circle of the aircraft.

[0017] Preferably, the connecting rod assembly includes a first connecting portion and a second connecting portion respectively fixedly connected to adjacent two of the aircraft. A rotating shaft is provided on the first connecting portion, and a sleeve sleeved on the rotating shaft and capable of rotating relative to the rotating shaft is provided on the second connecting portion. A locking block is provided on the first connecting portion, and engaging teeth capable of engaging with each other are provided on both the locking block and the end of the sleeve;

[0018] The connecting rod control device includes an elastic reset member, a cable and a cable winding and unwinding device for controlling the winding and unwinding of the cable. The free end of the cable is connected to the sleeve. One end of the elastic reset member is fixedly connected to the sleeve, and the other end is connected to the rotating shaft. The cable winding and unwinding device is installed on the second connecting portion. When the cable is tightened, the sleeve overcomes the resistance of the elastic reset member and disengages from the engaging teeth of the locking block. When the cable is released, the sleeve is under the elastic force of the elastic reset member, and the engaging teeth of the rotating shaft are engaged with the engaging teeth of the locking block.

[0019] Preferably, there are two sleeves, and the two sleeves are symmetrically arranged on opposite sides of the locking block. The elastic resetting members correspond to the sleeves one by one;

[0020] The cable includes sub-cables and a main cable connected to one end of the sub-cables. The other ends of the sub-cables are connected to the second connecting portion away from the teeth. All the sub-cables are connected to the main cable.

[0021] Preferably, the elastic resetting member is sleeved on the rotating shaft.

[0022] Preferably, the first rotating device and / or the second rotating device is a folding rod driving device. The folding rod driving device includes a folding rod assembly and a servo driving the folding rod assembly to rotate;

[0023] The folding rod assembly includes a first connecting rod and a first rotating rod. The first connecting rod and the first rotating rod are connected to two adjacent aircrafts. The first connecting rod is hinged to the first rotating rod. The folding rod driving device drives the first rotating rod to rotate relative to the first connecting rod to change the angle between the first connecting rod and the first rotating rod;

[0024] The servo is installed on the aircraft at the position where the first rotating rod is installed.

[0025] Preferably, the first rotating device and / or the second rotating device is a folding rod driving device. The folding rod driving device includes a folding rod assembly and a driving device driving the folding rod assembly to rotate;

[0026] The folding rod assembly includes a first connecting rod, a first rotating rod, a second connecting rod and a second rotating rod. The first connecting rod and the second connecting rod are connected to two adjacent aircrafts. The first connecting rod is hinged to the first rotating rod. The folding rod driving device drives the first rotating rod to rotate relative to the first connecting rod to change the angle between the first connecting rod and the first rotating rod. The first connecting rod and the second connecting rod are fixed on the same aircraft. The first rotating rod and the second rotating rod are installed on the other aircraft. A strip hole for the end of the second rotating rod to slide reciprocally is provided on the second connecting rod. A slider installed in the strip hole is provided on the second rotating rod. The folding rod driving device drives the first rotating rod and the second rotating rod to rotate.

[0027] Preferably, the aircrafts at the edge are sequentially connected through a telescopic device.

[0028] Preferably, the aircraft includes a ducted body, a fan arranged in the ducted body, and an energy supply device driving the fan to work;

[0029] The power supply device is located on the duct body;

[0030] Or the power supply device is located on the ground and is electrically connected to the fan.

[0031] Preferably, the outer diameter of the duct body is 10 mm - 190 mm.

[0032] In the above technical solution, the distributed propulsion device provided by the present invention includes a flight assembly composed of multiple aircraft, and at least two adjacent aircraft are flexibly connected so that the projection of the distributed propulsion device changes. During flight, according to actual environmental needs, the flexibly connected aircraft can change their relative positions, thereby changing the structure of the distributed propulsion device.

[0033] As can be seen from the above description, in the distributed propulsion device provided in this application, since at least two adjacent aircraft are flexibly connected so that the projection of the distributed propulsion device changes, that is, the distributed propulsion device can change its shape according to the environment, thereby adapting to various positions that need to be flown through. Therefore, the versatility of the distributed propulsion device is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only the embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained according to the provided drawings.

[0035] Figure 1 It is a schematic structural diagram of the distributed propulsion device provided by the embodiment of the present invention;

[0036] Figure 2 It is a schematic structural diagram of the first shape of the distributed propulsion device provided by the embodiment of the present invention rotating through the first link drive device;

[0037] Figure 3 It is a schematic structural diagram of the second shape of the distributed propulsion device provided by the embodiment of the present invention rotating through the first link drive device;

[0038] Figure 4 It is a schematic structural diagram of the third shape of the distributed propulsion device provided by the embodiment of the present invention rotating through the first link drive device;

[0039] Figure 5 It is an installation position diagram of the first link drive device and the aircraft provided by the embodiment of the present invention;

[0040] Figure 6 is Figure 5 the enlarged view of the first link drive device shown;

[0041] Figure 7 is the schematic structural diagram of the distributed propulsion device provided by the embodiment of the present invention rotating through the second link drive device;

[0042] Figure 8 is Figure 7 the enlarged view of the second link drive device shown;

[0043] Figure 9 is the schematic structural diagram of the distributed propulsion device provided by the embodiment of the present invention rotating through the third link drive device;

[0044] Figure 10 is the schematic structural diagram of the distributed propulsion device provided by the embodiment of the present invention rotating through the folding rod drive device;

[0045] Figure 11 is the installation position diagram of the folding rod drive device rotating provided by the embodiment of the present invention;

[0046] Figure 12 is the overall layout diagram of the distributed propulsion device provided by the embodiment of the present invention rotating through the folding rod drive device;

[0047] Figure 13 is the schematic structural diagram of the distributed propulsion device provided by the embodiment of the present invention rotating through the fourth link drive device;

[0048] Figure 14 is Figure 13 the enlarged installation position diagram of the fourth link drive device shown.

[0049] Wherein Figures 1 to 14 in:

[0050] 1 - aircraft, 2 - first rotating device, 3 - second rotating device;

[0051] 4 - link drive device, 41 - articulated rod, 42 - telescopic rod, 43 - articulated seat;

[0052] 5 - folding rod assembly, 51 - first rotating rod, 52 - first connecting rod, 53 - second rotating rod, 54 - slider, 55 - second connecting rod, 56 - strip hole, 57 - first mounting seat, 58 - second mounting seat;

[0053] 6 - folding rod drive device, 61 - servo, 62 - first connecting rod, 63 - first rotating rod;

[0054] 7-link drive device, 71-main cable, 72-sub cable, 73-first connection part, 74-locking block, 75-second connection part, 76-elastic reset part, 77-rotating shaft. Detailed implementation

[0055] The core of the present invention is to provide a distributed propulsion device with improved versatility.

[0056] In order to enable those skilled in the art to better understand the technical solutions of the present invention, the present invention will be further described in detail below with reference to the drawings and embodiments.

[0057] Please refer to Figures 1 to 14 .

[0058] In a specific implementation, the distributed propulsion device provided by the specific embodiment of the present invention includes a flight component composed of multiple aircraft 1. At least two adjacent aircraft 1 are flexibly connected so that the projection of the distributed propulsion device changes. The projection can be based on a certain reference point, and the relative position of any position point in the structure can change (including spatial angle, distance). The specific projection can be the projection of the distributed propulsion device on a specific plane, specifically the projection on a horizontal plane, a vertical plane or other planes. During the flight of the distributed propulsion device, according to the actual environmental needs, the flexibly connected aircraft 1 can change their relative positions, thereby changing the projection structure of the distributed propulsion device. As Figure 1 is the external view of the distributed propulsion device, Figure 2 is the external view of the distributed propulsion device when it is bent to one side. Figure 3 is the external view of the distributed propulsion device in a wavy state. Figure 4 is the external view of the distributed propulsion device in another wavy state. Figure 12 is the external view of the distributed propulsion device in a flat state.

[0059] Specifically, the aircraft 1 includes a duct body, a fan arranged in the duct body, and an energy supply device for driving the fan to work; when a bladeless aircraft 1 is used, the fan does not need to be arranged. Since the diameter of the duct body is small, the overall structure of the distributed propulsion device has large flexibility and can achieve a large degree of deformation.

[0060] The energy supply device is used to drive the fan to rotate to provide lift. The energy supply device is a battery arranged on the duct body and flies with the aircraft 1. Batteries can be arranged on each duct body respectively, or only on some duct bodies. Or the driving mechanism is arranged on the ground, and electric energy is transmitted to the fan through a tether cable to drive the fan to work.

[0061] Specifically, the outer diameter of the duct body is 10 mm - 190 mm. The outer diameter of the duct body can be about 95 mm - 105 mm. In this application, the diameter of the duct body is designed to be relatively small, so that the power sources of the entire distributed propulsion device are discretized.

[0062] From the above description, it can be seen that in the distributed propulsion device provided in the specific embodiment of this application, since at least two adjacent aircraft 1 are flexibly connected to change the projection of the distributed propulsion device, that is, the distributed propulsion device can change its shape according to the environment, and thus can adapt to a variety of positions that need to be flown through. Therefore, the versatility of the distributed propulsion device is improved.

[0063] Specifically, the aircraft 1 of the flight assembly are arranged in an array, and at least two adjacent aircraft 1 are flexibly connected by a first rotating device 2. The diameter of the duct body is relatively small, so that the lift sources are discretely distributed on the entire distributed propulsion device, and the matrix arrangement makes the lift sources evenly distributed on the entire device. The distributed propulsion device includes aircraft 1 arranged in a rectangular array or a circular array, and the overall outline is circular or rectangular, forming a large plane, and the aircraft 1 located at the edge can approach each other.

[0064] In a specific embodiment, the aircraft 1 are arranged in a matrix, and at least two longitudinally adjacent rows of aircraft 1 are flexibly connected. The two flexibly connected rows of aircraft 1 are rotatably connected to each other one by one through a first rotating device 2. The distributed propulsion device includes multiple rows of aircraft 1 arranged side by side to form a matrix, and each row of aircraft 1 curls, folds or approaches each other in the same direction.

[0065] Specifically, two adjacent aircraft 1 in each horizontal column are fixedly connected. The distributed propulsion device includes multiple rows of aircraft 1, forming a large plane. The adjacent rows of aircraft 1 can be fixedly connected, and a first rotating device 2 is provided on at least one row of aircraft 1.

[0066] In order to realize the angle transformation of the distributed propulsion device, preferably, at least two horizontally adjacent columns of aircraft 1 are rotatably connected by a second rotating device 3.

[0067] In another specific embodiment, multiple aircraft 1 can be arranged in a circular array, and adjacent two circles of aircraft 1 are connected. Among the adjacent two circles of aircraft 1, at least the outer circle of aircraft 1 and the adjacent inner circle of aircraft 1 are rotatably connected by a first rotating device 2, and the rotatable aircraft 1 in the same circle are rotatably connected by a second rotating device 3. Preferably, the aircraft 1 are arranged in multiple concentric circles, and at least the outermost aircraft 1 can curl, fold or approach each other in the same direction.

[0068] Of course, the aircraft 1 in the distributed propulsion device can also be in a strip shape or a ring shape. Specifically, it includes aircraft 1 arranged in a row or a circle, and each aircraft 1 can be concentrated by curling, folding or shrinking, resulting in a smaller volume.

[0069] Specifically, the first rotating device 2 and / or the second rotating device 3 is a connecting rod driving device 4. The connecting rod driving device 4 includes a connecting rod assembly 5 and a connecting rod control device for driving the connecting rod assembly 5 to rotate. The opposite ends of the connecting rod assembly 5 are fixedly connected to two adjacent aircraft 1.

[0070] As Figure 5 and Figure 6 shown, the connecting rod control device includes a telescopic rod 42 and a control device for controlling the telescopic movement of the telescopic rod 42. The connecting rod assembly includes a hinge rod 41 and a hinge seat 43 hinged to one end of the hinge rod 41. The hinge seat 43 and the other end of the hinge rod 41 are respectively fixedly connected to two adjacent aircraft 1. One end of the telescopic rod 42 is hinged to the rod body of the hinge rod 41, and the other end is hinged to the aircraft 1 on which the hinge seat 43 is installed. The telescopic rod 42 can be a traditional electric push rod.

[0071] Specifically, the two ends of the hinge rod 41 are respectively a fixed end and a hinged end. The fixed end of the hinge rod 41 is fixed on the outer wall of any aircraft 1, and the hinged end is rotatably connected to the hinge seat 43. The hinge seat 43 is fixedly connected to the outer wall of the adjacent aircraft 1. One end of the telescopic rod 42 is rotatably connected to the middle of the hinge rod 41, and the other end is rotatably connected to the outer wall of the aircraft 1 on which the hinge seat 43 is installed.

[0072] As Figure 5 shown, the left telescopic rod 42 is in a compressed state, and the left aircraft 1 rotates downward relative to the middle aircraft 1. The right telescopic rod 42 is in an extended state, and the middle aircraft 1 rotates upward relative to the right aircraft 1. Different deformations of the distributed propulsion device are achieved through different actions of the telescopic rods 42 at different positions.

[0073] In another deformed state, as Figure 2 shown, each telescopic rod 42 extends, and the entire distributed propulsion device bends upward and finally rolls into a cylindrical shape. As Figure 3 and Figure 4 shown, counting from left to right, two telescopic rods 42 are compressed, then two telescopic rods 42 extend, and then two telescopic rods 42 are compressed again (only one is shown in the figure), and this pattern cycles in turn, and the entire distributed propulsion device deforms into a wavy shape. In Figure 5 the adjacent telescopic rods 42 are respectively compressed and extended, presenting a wavy shape as a whole. Figure 3 Compared with Figure 5In contrast, two adjacent telescopic rods 42 are in the same state, and two adjacent telescopic rods 42 in sequence are in another state, with a wider spacing between the waves.

[0074] Figures 1 to 5 Shown is the movement of the telescopic rods 42 between the aircraft 1 arranged horizontally in a row, which causes the distributed propulsion device to curl in a certain direction. At this time, the movements of the longitudinally connected telescopic rods 42 in each column are exactly the same, and the longitudinally connected telescopic rods 42 in each column do not move. That is to say, the upper surfaces of the aircraft 1 arranged vertically in columns are on the same plane and do not deform.

[0075] It is also possible to make the longitudinally arranged telescopic rods 42 start to move after the horizontally arranged telescopic rods 42 complete their movements, and the shape of the entire distributed propulsion device can be further deformed. At this time, both the first rotating device 2 and the second rotating device 3 are link drive devices 4. When the longitudinally arranged telescopic rods 42 move, the horizontally arranged telescopic rods 42 may make some adaptive fine-tuning.

[0076] As another implementable way, the aircraft 1 located at the edge are directly connected by a telescopic device. The specific telescopic device can be a telescopic rod or a telescopic cylinder. The shortening of the telescopic device makes the aircraft 1 located at the edge approach each other, causing the outer edge of the large plane to contract and deform into a circle or rectangle with a smaller outline, which is convenient for passing through narrow lanes.

[0077] In a specific embodiment, the link assembly includes a first link and a second link hinged to the first link. The first link and the second link are respectively fixedly connected to two adjacent aircraft 1; the link control device includes a cable and a cable retracting and releasing device for controlling the retracting and releasing of the cable. When the cable is retracted and released, the first link and the second link rotate around the hinge point. The first connecting portion and the second connecting portion are both arranged on the outer wall of each duct body. Only the first connecting portion or the second connecting portion is arranged at the propulsion modules at both ends, and the first connecting portion and the second connecting portion are arranged on both sides of the propulsion modules in the middle. The first connecting portion of each aircraft 1 can be rotatably connected to the second connecting portion of the adjacent aircraft 1 on one side, and the second connecting portion of each aircraft 1 can be rotatably connected to the first connecting portion of the adjacent aircraft 1 on the other side.

[0078] The distributed propulsion device further includes a cable that sequentially connects each aircraft 1 in series. The cable is arranged on the upper side and / or the lower side of the aircraft 1. By driving the cable on one side to move, each aircraft 1 rotates, so that the propulsion module curls in the same direction and deforms into a long strip shape, which is convenient for passing through narrow lanes.

[0079] In a specific embodiment, the aircraft 1 located at the edge is softly connected to the aircraft 1 located in the middle through a flexible rope, fabric or hinge, and no power is transmitted between the aircraft 1 in the outer circle and the aircraft 1 in the inner circle. Of course, the aircraft 1 located at the edge and the aircraft 1 located in the middle can also be telescopically connected through a hydraulic tappet.

[0080] The distributed propulsion device further includes a cable that connects the aircraft 1s located at the edge in series. The cable is arranged on the upper side and / or the lower side of the large plane of the aircraft 1. By driving the cable on one side to act, each aircraft 1 rotates, so that the large plane of the distributed propulsion device curls in the same direction (curls upward or downward) and deforms into a long strip shape, which is convenient for passing through a narrow roadway.

[0081] Specifically, each aircraft 1 located at the edge can be softly connected through a flexible rope, fabric or hinge. Cables are respectively arranged on the upper side and the lower side of the large plane. The cables on both sides are pulled simultaneously, so that the aircraft 1s located at the edge approach each other, the entire distributed propulsion device is tightened, and the large plane is squeezed inward and even becomes spherical.

[0082] Preferably, the aircraft 1s in the same row or the same column share a connecting rod control device.

[0083] Specifically, the aircraft 1s at the edge share a connecting rod control device, and the aircraft 1s located at the edge are softly connected to the adjacent aircraft 1s in the inner circle.

[0084] As Figure 13 and Figure 14 shown, the connecting rod assembly includes a first connecting portion 73 and a second connecting portion 75 that are respectively fixedly connected to two adjacent aircraft 1s. A rotating shaft 77 is provided on the first connecting portion 73, and a sleeve that is sleeved on the rotating shaft 77 and can rotate relative to the rotating shaft 77 is provided on the second connecting portion 75. A locking block 74 is provided on the first connecting portion 73, and engaging teeth that can be engaged with each other are provided on both the locking block 74 and the end of the sleeve.

[0085] The connecting rod control device includes an elastic reset member 76, a cable and a cable retracting and releasing device for controlling the retracting and releasing of the cable. The free end of the cable is connected to the sleeve. One end of the elastic reset member 76 is fixedly connected to the sleeve, and the other end is connected to the rotating shaft 77. The cable retracting and releasing device is installed on the second connecting portion 75. When the cable is tightened, the sleeve overcomes the resistance of the elastic reset member 76 and disengages from the engaging teeth of the locking block 74. When the cable is released, the sleeve is under the elastic force of the elastic reset member 76, and the engaging teeth of the rotating shaft 77 are engaged with the engaging teeth of the locking block 74. The rotating shaft 77 is perpendicularly arranged relative to the central axis of the duct body. When the cable pulls each aircraft 1 to curl and deform, each aircraft 1 realizes relative rotation through the cooperation of the rotating shaft 77 and the sleeve. When deformation is not required, the cooperating rotating shaft and sleeve are clamped tightly to prevent relative movement.

[0086] In a specific embodiment, there are two sleeves, which are symmetrically arranged on opposite sides of the locking block 74, and the elastic resetting members 76 correspond to the sleeves one by one.

[0087] The cable includes a sub-cable 72 and a main cable 71 connected to one end of the sub-cable 72. The other end of the sub-cable 72 is connected to the second connecting portion 75 away from the engaging teeth, and all the sub-cables 72 are connected to the main cable 71.

[0088] In order to guide the movement of the elastic resetting member 76, preferably, the elastic resetting member 76 is sleeved on the rotating shaft 77. Specifically, the elastic resetting member 76 is preferably a spring.

[0089] As Figure 10 and Figure 11 shown, in a specific embodiment, the first rotating device 2 and / or the second rotating device 3 is a folding rod driving device 56, and the folding rod driving device 6 includes a folding rod assembly and a servo 61 for driving the folding rod assembly to rotate.

[0090] As Figure 3 shown, the folding rod assembly includes a first connecting rod 61 and a first rotating rod 63. The first connecting rod 61 and the first rotating rod 63 are connected to two adjacent aircrafts 1. The first connecting rod 61 is hinged to the first rotating rod 63, and the folding rod driving device 56 drives the first rotating rod 63 to rotate relative to the first connecting rod 61 to change the angle between the first connecting rod 61 and the first rotating rod 63.

[0091] The servo 61 is installed on the aircraft 1 where the first rotating rod 63 is installed. Specifically, the two folding rod assemblies are at the same height relative to the aircraft 1. The servo 61 is arranged in the aircraft 1 where the first rotating rod 63 is located in the aircraft 1, and the servo 61 drives the first rotating rod 63 to rotate relative to the first connecting rod 61.

[0092] In a specific embodiment, the first rotating device 2 and / or the second rotating device 3 is a folding rod driving device, and the folding rod driving device includes a folding rod assembly 5 and a driving device for driving the folding rod assembly 5 to rotate.

[0093] As Figure 7 and Figure 8, the folding rod assembly 5 includes a first connecting rod 52, a first rotating rod 51, a second connecting rod 55 and a second rotating rod 53. The first connecting rod 52 and the second connecting rod 55 are connected to two adjacent aircraft 1. The first connecting rod 52 is hinged to the first rotating rod 51, and they rotate in the same plane. The folding rod driving device drives the first rotating rod 51 to rotate relative to the first connecting rod 52 to change the angle between the first connecting rod 52 and the first rotating rod 51. The first connecting rod 52 and the second connecting rod 55 are fixed on the same aircraft 1, and the first rotating rod 51 and the second rotating rod 53 are installed on another aircraft 1. A strip-shaped hole 56 for the end of the second rotating rod 53 to slide reciprocally is provided on the second connecting rod 55, and a slider 54 installed in the strip-shaped hole 56 is provided on the second rotating rod 53. The folding rod driving device drives the first rotating rod 51 and the second rotating rod 53 to rotate. Specifically, the strip-shaped hole 56 can be a rectangular hole or an oval hole, etc.

[0094] When Figure 9 the aircraft 1 on the right side in the figure rotates downward relative to the middle aircraft 1, the second rotating rod 53 between them slides to the left in the strip-shaped hole 56; when the aircraft 1 on the left side rotates upward relative to the middle aircraft 1, the second rotating rod 53 between them slides to the right in the strip-shaped hole 56.

[0095] Preferably, as Figure 7 shown, there are two first connecting rods 52, two first rotating rods 51, two second connecting rods 55 and two second rotating rods 53. The two first connecting rods 52 and the two second connecting rods 55 are at the same height relative to the aircraft 1, and the second connecting rods 55 and the second rotating rods 53 are vertically corresponding to the first connecting rods 52 and the first rotating rods 51 respectively below.

[0096] Furthermore, the adjacent aircraft 1 arranged longitudinally in a column and the aircraft 1 arranged horizontally in a row are all connected by folding rod assemblies 5 with the same structure.

[0097] As another implementable way, the adjacent aircraft 1 arranged longitudinally in a column can be fixedly connected, and the folding rod driving device is connected to each aircraft 1 in one or two rows at the outermost side. As another implementable way, the adjacent aircraft 1 arranged longitudinally in a column can also be flexibly connected, and each row of aircraft 1 corresponds to its own folding rod group respectively.

[0098] To improve the stability of the aircraft 1 during flight, preferably, there are at least two folding rod groups. When the axis of the aircraft 1 is perpendicular to the horizontal plane, the two folding rod groups are arranged side by side in the horizontal direction.

[0099] When the aircraft 1 is distributed in a circular array, preferably, the aircraft 1 in the same circle share a connecting rod control device.

[0100] Specifically, for the aircraft 1 distributed in a circular array, the outermost aircraft 1 share a connecting rod control device, and the aircraft 1 at the edge are softly connected to the adjacent inner ring aircraft 1.

[0101] In the present application, the overall distributed propulsion device is deformed by means of curling, folding or approaching each other, etc., changing its shape and size, and improving its flexibility and passability. When flying and operating in complex field environments or tunnels, it can not only maintain sufficient lift through a large number of fans, but also achieve its deformation through the relative movement between the duct bodies.

[0102] In the present application, the diameter of the duct body is designed to be small, so that the lift sources of the entire distributed propulsion device are discretized and evenly distributed, maintaining the stability during flight, and also improving the flexibility of the overall structure during curling or folding, enabling it to be curled or folded into a smaller size, which is convenient for wide promotion and use.

[0103] In this specification, the various embodiments are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. For the same or similar parts among the various embodiments, reference may be made to each other.

[0104] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be obvious to those skilled in the art. The general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to these embodiments shown herein, but will be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A distributed propulsion device, characterized in that, It includes a flight assembly composed of multiple aircraft (1), and at least two adjacent aircraft (1) are flexibly connected to change the projection of the distributed propulsion device; The aircraft (1) of the flight assembly are arranged in an array, and at least two adjacent aircraft (1) are flexibly connected by a first rotating device (2); The aircraft (1) are arranged in a matrix, and at least two longitudinally adjacent rows of the aircraft (1) are flexibly connected. The two rows of flexibly connected aircraft (1) are rotatably connected one-to-one by a first rotating device (2); at least two laterally adjacent columns of the aircraft (1) are rotatably connected by a second rotating device (3); The first rotating device (2) and / or the second rotating device (3) is a connecting rod driving device (4). The connecting rod driving device (4) includes a connecting rod assembly and a connecting rod control device for driving the connecting rod assembly to rotate. The opposite ends of the connecting rod assembly are fixedly connected to two adjacent aircraft (1); The connecting rod control device includes a telescopic rod (42) and a control device for controlling the telescopic movement of the telescopic rod (42); the connecting rod assembly includes a hinged rod (41) and a hinge seat (43) hinged to one end of the hinged rod (41). The hinge seat (43) and the other end of the hinged rod (41) are respectively fixedly connected to two adjacent aircraft (1). One end of the telescopic rod (42) is hinged to the rod body of the hinged rod (41), and the other end is hinged to the aircraft (1) where the hinge seat (43) is installed. Different deformations of the distributed propulsion device are realized through different actions of the telescopic rods (42) at different positions. The different deformations include planar, wavy or cylindrical.

2. The distributed propulsion device according to claim 1, characterized in that, The telescopic rod (42) is an electric push rod.

3. The distributed propulsion device according to claim 1, characterized in that, One end of the telescopic rod (42) is rotatably connected to the middle of the hinged rod (41), and the other end of the telescopic rod (42) is rotatably connected to the outer wall of the aircraft (1) where the hinge seat (43) is installed.

4. The distributed propulsion device according to claim 1, characterized in that, The aircraft (1) includes a duct body, a fan arranged in the duct body, and an energy supply device for driving the fan to work; The energy supply device is located on the duct body; Or the energy supply device is located on the ground and is electrically connected to the fan.

5. The distributed propulsion device according to claim 4, characterized in that, The outer diameter of the duct body is 10 mm - 190 mm.

6. A distributed propulsion device, characterized in that, It includes a flight assembly composed of multiple aircraft (1), and at least two adjacent aircraft (1) are flexibly connected to change the projection of the distributed propulsion device; The aircraft (1) of the flight assembly are arranged in an array, and at least two adjacent aircraft (1) are flexibly connected by a first rotating device (2); A plurality of the aircraft (1) are arranged in a circular array, and adjacent two circles of the aircraft (1) are connected. Among the adjacent two circles of the aircraft (1), at least the outer circle of the aircraft (1) is rotatably connected to the adjacent inner circle of the aircraft (1) by a first rotating device (2), and the rotatable aircraft (1) in the same circle are rotatably connected by a second rotating device (3); The first rotating device (2) and / or the second rotating device (3) is a connecting rod driving device (4). The connecting rod driving device (4) includes a connecting rod assembly and a connecting rod control device for driving the connecting rod assembly to rotate. Opposite ends of the connecting rod assembly are fixedly connected to two adjacent aircraft (1). The connecting rod control device includes a telescopic rod (42) and a control device for controlling the telescopic movement of the telescopic rod (42). The connecting rod assembly includes a hinged rod (41) and a hinge seat (43) hinged to one end of the hinged rod (41). The hinge seat (43) and the other end of the hinged rod (41) are respectively fixedly connected to two adjacent aircraft (1). One end of the telescopic rod (42) is hinged to the rod body of the hinged rod (41), and the other end is hinged to the aircraft (1) on which the hinge seat (43) is installed. The aircraft (1) is arranged in multiple concentric circles, and different deformations of the distributed propulsion device are realized through different actions of the telescopic rods (42) at different positions.

7. The distributed propulsion device according to claim 6, characterized in that, The telescopic rod (42) is an electric push rod.

8. The distributed propulsion device according to claim 6, wherein, One end of the telescopic rod (42) is rotatably connected to the middle of the hinged rod (41), and the other end of the telescopic rod (42) is rotatably connected to the outer wall of the aircraft (1) on which the hinge seat (43) is installed.

9. The distributed propulsion device according to claim 6, characterized in that, The aircraft (1) includes a duct body, a fan arranged in the duct body, and an energy supply device for driving the fan to work. The energy supply device is located on the duct body. Or the energy supply device is located on the ground and is electrically connected to the fan.

10. The distributed propulsion device according to claim 9, characterized in that, The outer diameter of the duct body is 10 mm - 190 mm.

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