Aircraft and flight system

Abstract

The invention relates to the field of aircrafts, aims to solve the problem that a foot stool in the prior art cannot be folded or is inconvenient to fold, and provides an aircraft and a flight system. The aircraft comprises an aircraft body, aircraft arms, foot stools and a linkage structure. The vehicle arms are rotatably connected to the vehicle body and can be folded or unfolded relative to the vehicle body. The foot stool is rotatably connected to the vehicle arm and can be folded or unfolded relative to the vehicle arm. The linkage structure is in linkage fit with the machine arms and the foot stool and used for transmitting rotation of the machine arms relative to the machine body to the foot stool so as to drive the foot stool to rotate relative to the machine arms, and the foot stool can be folded or unfolded. The folding aircraft has the beneficial effects that the folding operation of the aircraft is convenient, and the folded aircraft has a relatively small size.

Description

Technical Field

[0001] The present application relates to the field of aircraft, and more particularly, to aircraft and flight systems. Background Art

[0002] An aircraft includes a body, an arm rotatably connected to the body, and a tripod rigidly connected to the arm. In some aircraft (such as drones), the tripod is fixedly connected to the arm, which has problems such as being easily damaged and taking up a large space. Summary of the Invention

[0003] The present application provides an aircraft and a flight system to solve the problem in the prior art that the aircraft's tripod occupies a large space and is easily damaged.

[0004] In a first aspect, embodiments of the present application provide an aircraft comprising a fuselage, an arm, a tripod, and a linkage structure. The arm is rotatably connected to the fuselage and can be folded or unfolded relative to the fuselage. The tripod is rotatably connected to the arm and can be folded or unfolded relative to the arm. The linkage structure cooperates with the arm and the tripod, respectively, to transmit the rotation of the arm relative to the fuselage to the tripod, thereby driving the tripod to rotate relative to the arm, thereby folding or unfolding the tripod.

[0005] In the embodiments of this application, a linkage structure can link the rotation of the aircraft arms and the rotation of the tripod. This allows the tripod to fold or unfold as the arms fold or unfold, making operation easy. The folded aircraft has a smaller size, making it easier to pack and transport. The folding tripod also reduces the risk of damage. Furthermore, this structure can optimize space layout and improve design convenience.

[0006] In one possible embodiment, the linkage structure includes a linkage rope, the linkage rope including a first fixed end and a second fixed end, the first fixed end being fixed to the fuselage, and the second fixed end being fixed to the tripod. When the aircraft arm is folded relative to the aircraft body, the aircraft arm and the linkage rope abut against each other and push the linkage rope to slide relative to the aircraft arm, so that the linkage rope pulls the tripod to fold relative to the aircraft arm. Alternatively, when the aircraft arm is unfolded relative to the aircraft body, the aircraft arm and the linkage rope abut against each other and push the linkage rope to slide relative to the aircraft arm, so that the linkage rope pulls the tripod to unfold relative to the aircraft arm.

[0007] In one possible embodiment, the linkage structure further includes an elastic member, elastically supported between the aircraft arm and the tripod. When the linkage rope is used to pull the tripod to fold relative to the aircraft arm, the elastic member is used to provide a restoring force for the tripod to unfold relative to the aircraft arm. When the linkage rope is used to pull the tripod to unfold relative to the aircraft arm, the elastic member is used to provide a restoring force for the tripod to fold relative to the aircraft arm.

[0008] In a possible embodiment, the aircraft arm is provided with a cam portion. When the aircraft arm is folded relative to the fuselage, the cam portion abuts against the linkage rope and pushes the linkage rope to slide relative to the aircraft arm, so that the linkage rope pulls the tripod to fold relative to the aircraft arm.

[0009] In one possible embodiment, the arm has a first end and a second end, with the cam portion disposed at the first end. A hole is disposed in the arm, extending from the first end to the second end. Two ends of a linkage rope extend through the hole to connect the fuselage and the tripod, respectively.

[0010] In one possible embodiment, the cam portion has an outer cam surface on its outer periphery, and the channel has an opening extending through the outer cam surface. The linkage rope includes an exposed rope segment located between the first fixed end and the opening. The distance from the opening to the rotational center of the cam portion is less than the distance from the first fixed end to the rotational center of the cam portion.

[0011] In a possible implementation, the distance from the outer cam surface to the rotation center of the cam portion gradually increases from the side of the outer cam surface close to the opening to the side close to the first fixed end.

[0012] In one possible embodiment, the fuselage is provided with a through hole that passes through the interior space and the exterior space of the fuselage. The exposed rope segment passes through the through hole and extends into the interior space of the fuselage, with the first fixed end fixed to a side of the fuselage close to the interior space.

[0013] In a possible embodiment, the machine arm further comprises a mounting seat, which is arranged at one end of the machine arm away from the machine body. The mounting seat is provided with a guide block, and the guide block is provided with a guide hole for the linkage rope to pass through.

[0014] In a second aspect, an embodiment of the present application provides a flight system, comprising a remote controller and the aforementioned aircraft. The remote controller is capable of communicating with the aircraft and is used to control the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying any creative work.

[0016] Figure 1 This is a schematic structural diagram of an aircraft according to an embodiment of the present application.

[0017] Figure 2 for Figure 1 A three-dimensional view of part of the structure of the aircraft in the unfolded state.

[0018] Figure 3 for Figure 1A three-dimensional diagram of part of the structure of the aircraft in a folded state.

[0019] Figure 4 for Figure 2 Exploded diagram.

[0020] Figure 5 This is an exploded view of part of the aircraft structure.

[0021] Figure 6 This is a cross-sectional view of a portion of the aircraft structure in an unfolded state.

[0022] Figure 7 for Figure 6 Schematic diagram of part of the aircraft structure after the arms are folded.

[0023] Figure 8 This is a schematic structural diagram of the flight system according to an embodiment of the present application.

[0024] Key component symbols: 100 - aircraft; 120 - propeller assembly; 121 - drive member; 122 - propeller; 110 - frame assembly; 10 - fuselage; 11 - side panel; 12 - mounting plate; 13 - first shaft; 14 - screw column; 15 - screw; 20 - arm; 20a - first end; 20b - second end; 21 - cam portion; 22 - mounting seat; 23 - guide block; 24 - second shaft; 30 - tripod; 31 - connection point; 40 - linkage structure; 41- linkage rope; 41a- first fixed end; 41b- second fixed end; 411- exposed rope segment; 42- elastic member; P1- external cam surface; K1- channel; K2- inner hole; K3- through hole; K4- opening; K5- guide hole; K6- through hole; K7- rotational matching hole; X- length direction; Y- width direction; Z- height direction; Q1- internal space; Q2- external space; 1000- flight system; 200- remote control. DETAILED DESCRIPTION

[0025] The technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments.

[0026] It should be noted that when an element is referred to as being "fixed to" another element, it may be directly on the other element or there may also be an element centered therein. When an element is considered to be "connected to" another element, it may be directly connected to the other element or there may also be an element centered therein. When an element is considered to be "set on" another element, it may be directly set on the other element or there may also be an element centered therein. The terms "vertical", "horizontal", "left", "right" and similar expressions used herein are for illustrative purposes only.

[0027] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art to which this application belongs. The terms used herein in the specification of this application are only for the purpose of describing specific embodiments and are not intended to limit this application. The term "and / or" as used herein includes any and all combinations of one or more of the relevant listed items.

[0028] Some embodiments of the present application are described in detail. In the absence of conflict, the following embodiments and features of the embodiments can be combined with each other.

[0029] Example See also Figure 1 This embodiment provides an aircraft 100. The aircraft 100 may be a drone (such as a multi-rotor drone) or other flying equipment.

[0030] The aircraft 100 includes a frame assembly 110 and a propeller assembly 120. The propeller assembly 120 is mounted on the frame assembly 110 and can provide lift for the aircraft 100.

[0031] There can be one or more propeller assemblies 120, and the distribution of the propeller assemblies 120 can be set as needed. Figure 1 In the embodiment, there are four propeller assemblies 120 in total, and the four propeller assemblies 120 are distributed in two rows and two columns along the length direction X (or front-to-back direction) and the width direction Y of the aircraft 100 .

[0032] In this embodiment, the propeller assembly 120 includes a driving member 121 and a propeller 122 . The propeller 122 is connected to the driving member 121 and is configured to rotate under the drive of the driving member 121 .

[0033] The driving member 121 can be a rotating motor, the fixed part of the motor (such as the motor casing) is fixedly mounted on the frame assembly 110, and the output shaft of the motor is connected to the propeller 122 to drive the propeller 122 to rotate, thereby providing lift or controlling the running direction, attitude, etc. of the aircraft 100.

[0034] Figure 2 In the embodiment, the machine arm 20 and the tripod 30 are in the unfolded state. Figure 3 In the embodiment, the machine arm 20 and the tripod 30 are in a folded state.

[0035] See also Figure 2 and Figure 3 The frame assembly 110 includes a body 10 , an arm 20 and a tripod 30 .

[0036] The fuselage 10 may include an outer shell of the aircraft 100 and serve as a mounting base for other structural members (such as the arms 20 , etc.) or electronic components (such as batteries and main control boards) of the aircraft 100 .

[0037] The arms 20 are rotatably connected to the fuselage 10 and can be folded or unfolded relative to the fuselage 10. The number of the arms 20 can be the same as the number of the propeller assemblies 120, for example Figure 1 In the embodiment, there are four arms 20, which are connected to different positions of the fuselage 10, and four propeller assemblies 120 are respectively installed on the four arms 20. In this way, the power (such as lift) provided by the four propeller assemblies 120 can act on the arms 20, and drive the fuselage 10 to move through the arms 20.

[0038] The tripod 30 is rotatably connected to the arm 20 and can be folded or unfolded relative to the arm 20. When the aircraft 100 is parked on the ground or a platform, the tripod 30 can be supported on the ground or platform. The number of tripods 30 can be the same as the number of arms 20. For example, there can be four tripods 30. When supported on the ground or platform, the four tripods 30 can stably support the aircraft 100. During landing, the tripod 30 can also cushion the impact of the aircraft 100 landing.

[0039] In this embodiment, the aircraft 100 is in flight, and the arms 20 and the legs 30 are both in the unfolded state (eg, Figure 2 When not in use, the arms 20 and the legs 30 can be folded to reduce the volume occupied, making it easier to pack, transport, and carry the aircraft 100.

[0040] See also Figure 4-Figure 6 The frame assembly 110 of this embodiment further includes a linkage structure 40. The linkage structure 40 cooperates with the arm 20 and the tripod 30 to transmit the rotation of the arm 20 relative to the body 10 to the tripod 30, thereby driving the rotation of the tripod 30 relative to the arm 20. In other words, the linkage structure 40 can link the rotation of the arm 20 and the tripod 30, allowing the tripod 30 to automatically fold when the arm 20 is folded, or automatically unfold when the arm 20 is unfolded, providing convenient use. The implementation of the linkage structure 40 will be described in detail below.

[0041] Continue to see Figure 4-Figure 6 The arm 20 is generally in the shape of a long strip, and has a first end 20a and a second end 20b. The first end 20a is rotatably connected to the body 10, and the tripod 30 is rotatably connected to the second end 20b.

[0042] In this embodiment, the tripod 30 is attached to the side of the arm 20 facing away from the aircraft 100 in the height direction Z (i.e., the lower side of the aircraft 100 during normal use). Optionally, the drive member 121 of the propeller assembly 120 is fixed to the side of the arm 20 facing away from the tripod 30 (i.e., the upper side during normal use). This ensures that the tripod 30 does not interfere with the drive member 121 when folded.

[0043] The linkage structure 40 includes a linkage rope 41. The linkage rope 41 can be a steel wire rope or other flexible rope capable of transmitting tension but not thrust. In other embodiments, the linkage structure 40 can also utilize structures other than the linkage rope 41, such as a connecting rod mechanism or gear transmission mechanism connecting the arm 20 and the tripod 30, without limitation herein.

[0044] The linkage rope 41 includes a first fixed end 41a and a second fixed end 41b. The first fixed end 41a is fixed to the fuselage 10, and the second fixed end 41b is fixed to the tripod 30. In this embodiment, when the arm 20 is folded relative to the fuselage 10, the arm 20 abuts against the linkage rope 41, pushing the linkage rope 41 to slide relative to the arm 20, causing the linkage rope 41 to pull the tripod 30 to fold relative to the arm 20. In this case, the linkage rope 41 serves to coordinate the folding of the arm 20 and the tripod 30.

[0045] In this embodiment, the arm 20 optionally includes a cam portion 21, which can be located at the first end 20a of the arm 20. The cam portion 21 is supported between the ends of a linkage rope 41. When the arm 20 is folded relative to the fuselage 10, the cam portion 21 abuts against the linkage rope 41 and pushes the linkage rope 41 to slide relative to the arm 20, causing the linkage rope 41 to pull the tripod 30 to fold relative to the arm 20. In this manner, the linkage rope 41 cooperates with the cam portion 21 located at the first end 20a of the arm 20 to achieve transmission, reliably achieving the folding of the tripod 30. Furthermore, the cam portion 21 only involves modifying the outer shape of one end of the arm 20. Furthermore, the linkage rope 41 can be made of a material with a very small diameter (e.g., less than 1 mm), taking up little space and being lightweight, making it particularly suitable for weight-sensitive aircraft 100 (particularly small aircraft such as drones).

[0046] In this embodiment, a hole K1 is optionally provided within the arm 20, extending from the first end 20a to the second end 20b. The ends of the linkage rope 41 extend through the hole K1, respectively connecting the fuselage 10 and the tripod 30. Of course, to enable the linkage rope 41 to rotate the tripod 30, the connection point 31 between the linkage rope 41 and the tripod 30 is located outside the rotation axis of the tripod 30 relative to the arm 20. For example, it is located on the side of the tripod 30 closest to the fuselage 10, away from the rotation axis of the tripod 30.

[0047] In this embodiment, optionally, see Figure 6 The arm 20 can be configured as a shell-like structure, with the inner hole K2 hollowed out in the middle of its longitudinal direction to reduce its weight. The cam portion 21 can be a solid structure with a high fill ratio to ensure its high structural strength. A through-hole K3 is formed in the cam portion 21, which connects to the inner hole K2, thereby forming a channel K1 for the linkage rope 41 to pass through. The inner hole K2 also serves as a portion of the channel K1, reducing the required depth of the channel K1 and lowering the processing requirements.

[0048] In this embodiment, the outer peripheral side of the cam portion 21 has an outer cam surface P1, and the through hole K3 of the channel K1 has an opening K4 that passes through the outer cam surface P1. The linkage rope 41 includes an exposed rope segment 411 located between the first fixed end 41a and the opening K4. The distance L1 from the opening K4 to the rotation center of the cam portion 21 is smaller than the distance L2 from the first fixed end 41a to the rotation center of the cam portion 21. In addition, the distance from the outer cam surface P1 to the rotation center of the cam portion 21 gradually increases from the side of the outer cam surface P1 close to the opening K4 to the side close to the first fixed end 41a. In this way, when the arm 20 is folded relative to the fuselage 10, the exposed rope segment 411 is pushed outward by the outer cam surface P1. Specifically, in combination with Figure 7 Based on the shape design of the outer cam surface P1, during the folding process, the linkage rope 41 is pulled out from the opening K4 more under the drive of the outer cam surface P1. Figure 7 As shown in the figure, the length of the exposed rope section 411 of the linkage rope 41 becomes longer. Accordingly, the end of the linkage rope 41 connected to the tripod 30 moves toward the side close to the fuselage 10, so that the linkage rope 41 pulls the tripod 30 toward the side close to the fuselage 10, so that the tripod 30 is synchronously folded relative to the frame. The force transmission structure is simple and effective, and has little effect on the weight and appearance of the aircraft 100.

[0049] Main references Figure 4 In this embodiment, the fuselage 10 has side panels 11 on either side of the width direction Y. The side panels 11 serve as the outer shell of the fuselage 10 along the width direction Y. The side panels 11 are provided with through-holes K6 that extend through the interior space Q1 and the exterior space Q2 of the fuselage 10. The interior space Q1 can be used to install electrical components such as batteries and main control boards of the aircraft 100. The exterior space Q2 refers to the space outside the fuselage 10, i.e., the space external to the fuselage 10.

[0050] Two mounting plates 12 are connected to the side panel 11. These two mounting plates 12 are spaced apart and opposite each other along the height direction Z (or vertical direction) of the aircraft 100. A through hole K6 is located between the two side panels 11. The cam portion 21 is rotatably connected between the two mounting plates 12 via a first shaft 13. Specifically, the axial ends of the first shaft 13 are fixed to the two mounting plates 12. The cam portion 21 is provided with rotationally engaged holes K7, which rotatably fit over the first shaft 13. The exposed rope segment 411 passes through the through hole K6 and extends into the interior space Q1 of the fuselage 10, with its first fixed end 41a fixed to the side of the fuselage 10 closest to the interior space Q1. This allows the external cam surface P1 of the cam portion 21 and the exposed rope segment 411 of the linkage rope 41 to be contained within the interior space Q1 of the fuselage 10, minimizing the adverse effects of the external cam surface P1 and the linkage rope 41 on the aerodynamic shape of the fuselage 10. At the same time, the exposed rope section 411 of the linkage rope 41 is located inside the fuselage 10 and can be protected by the fuselage 10 and not easily affected by the environment, and is not easily damaged by accidental hooking or other reasons, ensuring the use, installation and service life of the aircraft 100.

[0051] Optionally, the body 10 is further provided with a screw post 14, which is used to compress the first fixed end 41a of the linkage cord 41 together with a screw 15. The screw post 14 is located on the side of the side panel 11 near the interior space Q1. After the first fixed end 41a of the linkage cord 41 extends through the through hole K6 into the interior space Q1, it is locked and fixed to the screw post 14 by the screw 15. The first fixed end 41a can be rolled into a circular shape to increase its contact area with the screw post 14 and the screw 15, ensuring a secure fixation of the first fixed end 41a.

[0052] In this embodiment, the arm 20 optionally further includes a mounting base 22, located at the second end 20b of the arm 20. The mounting base 22 includes a guide block 23, which has a guide hole K5 through which the linkage rope 41 passes. The guide block 23 and the guide hole K5 facilitate the movement of the linkage rope 41 and facilitate connection of the linkage rope 41 to the tripod 30 at a suitable angle.

[0053] Main references Figure 5 In this embodiment, the linkage structure 40 further includes an elastic member 42. The elastic member 42 is elastically supported between the arm 20 and the tripod 30, providing a restoring force to allow the tripod 30 to unfold relative to the arm 20. When the arm 20 is unfolded relative to the body 10, the outer cam surface P1 releases the linkage rope 41, and the elastic member 42 automatically deploys the tripod 30, providing convenient operation. Specifically, in the folded state, a certain amount of elastic potential energy is stored between the tripod 30 and the arm 20, enabling the tripod 30 to automatically deploy when the arm 20 is deployed.

[0054] Optionally, the tripod 30 is rotatably connected to the arm 20 via the second shaft 24. The elastic member 42 is a torsion spring, which is disposed outside the second shaft 24 and elastically abuts between the arm 20 and the tripod 30. In other embodiments, the elastic member 42 may also be other structures, such as a tension spring, etc., which is not limited here.

[0055] In the aforementioned embodiment, the linkage rope 41 is used to link the folding of the machine arm 20 and the folding of the tripod 30 , and the elastic member 42 is used to provide a restoring force for the tripod 30 to unfold relative to the machine arm 20 .

[0056] In other embodiments, the reverse arrangement can be employed, whereby the linkage rope 41 is used to link the deployment of the arm 20 and the tripod 30. In this case, when the arm 20 is deployed relative to the fuselage 10, the arm 20 (e.g., the cam portion 21 of the arm 20) abuts against the linkage rope 41, pushing the linkage rope 41 to slide relative to the arm 20, causing the linkage rope 41 to pull the tripod 30 to deploy relative to the arm 20. An elastic member 42 is elastically supported between the arm 20 and the tripod 30, providing a restoring force to fold the tripod 30 relative to the arm 20.

[0057] See also Figure 8 This embodiment further provides a flight system 1000. The flight system 1000 includes an aircraft 100 and a remote controller 200. The remote controller 200 is communicably connected to the aircraft 100 and is used to control the aircraft 100.

[0058] The above embodiments are only used to illustrate the technical solutions of the present application and are not intended to limit the present application. Although the present application has been described in detail with reference to the above preferred embodiments, those skilled in the art should understand that modifications or equivalent replacements of the technical solutions of the present application should not depart from the spirit and scope of the technical solutions of the present application.

Claims

1. An aircraft, characterized in that: The aircraft comprises: body; an arm rotatably connected to the fuselage and capable of being folded or unfolded relative to the fuselage; a tripod rotatably connected to the arm and capable of being folded or unfolded relative to the arm; and The linkage structure is respectively coordinated with the machine arm and the tripod, and is used to transmit the rotation of the machine arm relative to the machine body to the tripod, so as to drive the tripod to rotate relative to the machine arm, so that the tripod is folded or unfolded.

2. The aircraft according to claim 1, characterized in that: The linkage structure includes a linkage rope, and the linkage rope includes a first fixed end and a second fixed end, the first fixed end is fixed to the fuselage, and the second fixed end is fixed to the tripod; When the aircraft arm is folded relative to the fuselage, the aircraft arm and the linkage rope are pressed against each other and push the linkage rope to slide relative to the aircraft arm, so that the linkage rope pulls the tripod to fold relative to the aircraft arm, or, When the machine arm is unfolded relative to the fuselage, the machine arm and the linkage rope are pressed against each other and push the linkage rope to slide relative to the machine arm, so that the linkage rope pulls the tripod to unfold relative to the machine arm.

3. The aircraft according to claim 2, characterized in that: The linkage structure further includes an elastic member, wherein the elastic member is elastically supported between the machine arm and the tripod; When the linkage rope is used to pull the tripod to fold relative to the machine arm, the elastic member is used to provide a restoring force for the tripod to unfold relative to the machine arm; When the linkage rope is used to pull the tripod to unfold relative to the machine arm, the elastic member is used to provide a restoring force for folding the tripod relative to the machine arm.

4. The aircraft according to claim 2, characterized in that: The machine arm is provided with a cam portion. When the machine arm is folded relative to the machine body, the cam portion is pressed against the linkage rope and pushes the linkage rope to slide relative to the machine arm, so that the linkage rope pulls the tripod to fold relative to the machine arm.

5. The aircraft according to claim 4, characterized in that: The machine arm has a first end and a second end, and the cam portion is provided at the first end; The arm is provided with a hole, and the hole runs from the first end to the second end; The two ends of the linkage rope pass through the holes respectively to connect the fuselage and the tripod respectively.

6. The aircraft according to claim 5, characterized in that: The outer peripheral side of the cam portion has an outer cam surface, and the channel has an opening passing through the outer cam surface; The linkage rope includes an exposed rope section located between the first fixed end and the opening; A distance from the opening to a rotation center of the cam portion is smaller than a distance from the first fixed end to a rotation center of the cam portion.

7. The aircraft according to claim 6, characterized in that: A distance from the outer cam surface to the rotation center of the cam portion gradually increases from a side of the outer cam surface close to the opening to a side close to the first fixed end.

8. The aircraft according to claim 6, characterized in that: The fuselage is provided with a through hole, and the through hole passes through the internal space and the external space of the fuselage; The exposed rope section passes through the through hole and extends into the internal space of the fuselage, and the first fixing end is fixed to a side of the fuselage close to the internal space.

9. The aircraft according to claim 2, characterized in that: The arm further comprises a mounting base, which is provided at an end of the arm away from the fuselage; The mounting seat is provided with a guide block, and the guide block is provided with a guide hole for the linkage rope to pass through.

10. A flight system, characterized in that: include: The aircraft according to any one of claims 1 to 9; as well as, A remote controller is capable of communicating with the aircraft and is used to control the aircraft.

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