Aircraft and flight system

Abstract

The utility model 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

Aircraft and flight systems Technical Field

[0001] This application relates to the field of aircraft, and more specifically, to aircraft and flight systems. Background Technology

[0002] An aircraft consists of a fuselage, rotatable arms connected to the fuselage, and landing gear rigidly connected to the arms. In some aircraft (such as drones), the landing gear is fixedly connected to the arms. However, the landing gear is prone to damage and occupies a large amount of space. Summary of the Invention

[0003] This application provides an aircraft and a flight system to solve the problems of large space occupation and easy damage of the landing gear of aircraft in the known art.

[0004] In a first aspect, embodiments of this application provide an aircraft, including a fuselage, an arm, landing gear, and a linkage structure. The arm is rotatably connected to the fuselage and can be folded or unfolded relative to the fuselage. The landing gear is rotatably connected to the arm and can be folded or unfolded relative to the arm. The linkage structure is respectively linked and cooperates with the arm and the landing gear to transmit the rotation of the arm relative to the fuselage to the landing gear, thereby causing the landing gear to rotate relative to the arm, causing the landing gear to fold or unfold.

[0005] In the embodiments of this application, the linkage structure can coordinate the rotation of the boom and the landing gear, so that when the boom is folded or unfolded, the landing gear can be folded or unfolded accordingly. This is convenient to operate, and the folded aircraft has a smaller volume, which facilitates packaging and transportation. Folding the landing gear can also reduce the possibility of landing gear damage. In addition, this structure can optimize the spatial layout and improve design convenience.

[0006] In one possible implementation, the linkage structure includes a linkage rope, which has 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 boom is folded relative to the fuselage, the boom abuts against the linkage rope, pushing the linkage rope to slide relative to the boom, thereby causing the linkage rope to pull the tripod to fold relative to the boom. Alternatively, when the boom is unfolded relative to the fuselage, the boom abuts against the linkage rope, pushing the linkage rope to slide relative to the boom, thereby causing the linkage rope to pull the tripod to unfold relative to the boom.

[0007] In one possible implementation, the linkage structure further includes an elastic element that is elastically supported between the boom and the tripod. When the linkage cable is used to pull the tripod folding relative to the boom, the elastic element provides a restoring force for the tripod's unfolding relative to the boom. Conversely, when the linkage cable is used to pull the tripod unfolding relative to the boom, the elastic element provides a restoring force for the tripod's folding relative to the boom.

[0008] In one possible implementation, the boom is provided with a cam portion. When the boom folds relative to the body, the cam portion abuts against the linkage rope and pushes the linkage rope to slide relative to the boom, so that the linkage rope pulls the tripod to fold relative to the boom.

[0009] In one possible implementation, the arm has a first end and a second end, with a cam portion located at the first end. The arm has a channel extending from the first end to the second end. The two ends of a linkage rope pass through the channel to connect to the machine body and the tripod, respectively.

[0010] In one possible implementation, the outer peripheral side of the cam portion has an outer cam surface, and the channel has an opening penetrating 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 rotation center of the cam portion is less than the distance from the first fixed end to the rotation center of the cam portion.

[0011] In one 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 near the opening to the side near the first fixed end.

[0012] In one possible implementation, the fuselage has a through-hole that connects the internal and external spaces of the fuselage. An exposed rope segment passes through the through-hole and extends into the internal space of the fuselage, with the first fixed end secured to the side of the fuselage closest to the internal space.

[0013] In one possible implementation, the arm further includes a mounting base located at the end of the arm away from the machine body. The mounting base has a guide block with guide holes for the linkage rope to pass through.

[0014] Secondly, embodiments of this application provide a flight system including a remote controller and the aforementioned aircraft. The remote controller is communicatively connected to the aircraft and is used to control the aircraft. Attached Figure Description

[0015] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings in the embodiments will be briefly described below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 is a schematic diagram of the structure of the aircraft according to an embodiment of this application.

[0017] Figure 2 is a three-dimensional view of part of the structure of the aircraft in Figure 1 in the deployed state.

[0018] Figure 3 is a perspective view of part of the structure of the aircraft in Figure 1 in a folded state.

[0019] Figure 4 is an exploded view of Figure 2.

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

[0021] Figure 6 is a cross-sectional view of part of the aircraft's structure in the deployed state.

[0022] Figure 7 is a schematic diagram of part of the structure of the aircraft in Figure 6 after the arms are folded.

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

[0024] Key component symbols: 100-Aircraft; 120-Propeller assembly; 121-Drive component; 122-Propeller; 110-Frame assembly; 10-Fuselage; 11-Side plate; 12-Mounting plate; 13-First shaft; 14-Screw post; 15-Screw; 20-Arm; 20a-First end; 20b-Second end; 21-Cam; 22-Mounting base; 23-Guide block; 24-Second shaft; 30-Legs; 31-Connection point; 40 - Linkage structure; 41- Linkage rope; 41a- First fixed end; 41b- Second fixed end; 411- Exposed rope segment; 42- Elastic element; P1- Outer cam surface; K1- Channel; K2- Inner hole; K3- Through hole; K4- Opening; K5- Guide hole; K6- Through hole; K7- Rotation mating hole; X- Length direction; Y- Width direction; Z- Height direction; Q1- Internal space; Q2- External space; 1000- Flight system; 200- Remote controller. Detailed Implementation

[0025] The technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments.

[0026] It should be noted that when a component is said to be "fixed to" another component, it can be directly on the other component or there may be an intervening component. When a component is said to be "connected to" another component, it can be directly connected to the other component or there may be an intervening component. When a component is said to be "set on" another component, it can be directly set on the other component or there may be an intervening component. The terms "vertical," "horizontal," "left," "right," and similar expressions used in this document are for illustrative purposes only.

[0027] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0028] Some embodiments of this application are described in detail. Unless otherwise specified, the following embodiments and features can be combined with each other.

[0029] Example

[0030] Referring to 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.

[0031] 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 to the aircraft 100.

[0032] There may be one or more propeller assemblies 120, and the distribution of the propeller assemblies 120 can be set as needed. For example, in Figure 1, 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 width direction Y of the aircraft 100.

[0033] In this embodiment, the propeller assembly 120 includes a drive member 121 and a propeller 122. The propeller 122 is connected to the drive member 121 and is used to rotate under the drive of the drive member 121.

[0034] The drive unit 121 can be a rotary motor. The fixed part of the motor (such as the motor housing) is fixedly mounted on the frame assembly 110. 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.

[0035] In Figure 2, the boom 20 and the landing gear 30 are in the extended state. In Figure 3, the boom 20 and the landing gear 30 are in the folded state.

[0036] Referring to Figures 2 and 3, the frame assembly 110 includes a fuselage 10, an arm 20, and a tripod 30.

[0037] The fuselage 10 may include the outer shell of the aircraft 100 and serve as a mounting base for other structural components (such as the arms 20) or electronic components (such as batteries and main control boards) of the aircraft 100.

[0038] The arms 20 are rotatably connected to the fuselage 10 and can be folded or unfolded relative to the fuselage 10. The number of arms 20 can be the same as the number of propeller assemblies 120. For example, in Figure 1, there are four arms 20, which are connected to different positions on the fuselage 10, and four propeller assemblies 120 are respectively mounted 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.

[0039] The landing gear 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 platform, the landing gear 30 can support it. The number of landing gear 30 can be the same as the number of arms 20; for example, there can be four landing gear 30s. When all four landing gear 30s are supported on the ground or platform, they can stably support the aircraft 100. During the landing of the aircraft 100, the landing gear 30 can also cushion the impact of the landing.

[0040] In this embodiment, when the aircraft 100 is in flight, both the arms 20 and the landing gear 30 are in an extended state (as shown in Figure 2). When not in use, the arms 20 and the landing gear 30 can be folded to reduce the volume occupied and facilitate the packaging, transportation, and carrying of the aircraft 100.

[0041] Referring to Figures 4-6, the frame assembly 110 in this embodiment also includes a linkage structure 40. The linkage structure 40 works in conjunction with the arm 20 and the legs 30 to transmit the rotation of the arm 20 relative to the body 10 to the legs 30, thereby causing the legs 30 to rotate relative to the arm 20. In other words, the linkage structure 40 can link the rotation of the arm 20 and the rotation of the legs 30, so that the legs 30 automatically folds when the arm 20 is folded, or automatically unfolds when the arm 20 is unfolded, making it convenient to use. The implementation of the linkage structure 40 will be described in detail below.

[0042] Referring again to Figures 4-6, the arm 20 is roughly elongated, with two ends, namely the first end 20a and the second end 20b. The first end 20a is rotatably connected to the fuselage 10, and the landing gear 30 is rotatably connected to the second end 20b.

[0043] In this embodiment, the landing gear 30 is connected to the side of the arm 20 away from the aircraft 100 in the height direction Z (i.e., below the aircraft 100 in its normal operating state). Optionally, the drive unit 121 of the propeller assembly 120 is fixed to the side of the arm 20 away from the landing gear 30 (i.e., above it in its normal operating state). In this way, when the landing gear 30 is folded, it will not interfere with the drive unit 121.

[0044] The linkage structure 40 includes a linkage rope 41. The linkage rope 41 can be a steel wire rope or other flexible rope that can transmit tension but not thrust. In other embodiments, the linkage structure 40 can also use a structure other than the linkage rope 41, such as a linkage mechanism or gear transmission mechanism connected between the arm 20 and the leg 30, which is not limited here.

[0045] 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 machine body 10, and the second fixed end 41b is fixed to the tripod 30. In this embodiment, when the machine arm 20 folds relative to the machine body 10, the machine arm 20 abuts against the linkage rope 41, pushing the linkage rope 41 to slide relative to the machine arm 20, so that the linkage rope 41 pulls the tripod 30 to fold relative to the machine arm 20. At this time, the linkage rope 41 is used to link the folding of the machine arm 20 and the folding of the tripod 30.

[0046] In this embodiment, optionally, the arm 20 is provided with 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 two ends of the linkage rope 41, and 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, so that the linkage rope 41 pulls the landing gear 30 to fold relative to the arm 20. In this way, the transmission is achieved by the cooperation of the linkage rope 41 and the cam portion 21 located at the first end 20a of the arm 20, which can reliably realize the folding of the landing gear 30. Moreover, the cam portion 21 only involves the modification of the shape of one end of the arm 20, and the linkage rope 41 can be made of a material with a very small diameter (e.g., less than 1 mm), which occupies little space and is lightweight, making it very suitable for use in weight-sensitive aircraft 100 (especially small aircraft such as drones).

[0047] In this embodiment, optionally, the arm 20 is provided with a channel K1, which extends from the first end 20a to the second end 20b. The two ends of the linkage rope 41 pass through the channel K1 to connect the body 10 and the tripod 30, respectively. Of course, to enable the linkage rope 41 to pull the tripod 30 to rotate, 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 surface of the tripod 30 near the body 10, away from the rotation axis of the tripod 30.

[0048] In this embodiment, optionally, referring mainly to Figure 6, the arm 20 can be configured as a shell structure, with an inner hole K2 formed by hollowing out the middle part along its length, so that the arm 20 has a lower weight. The cam part 21 can have a solid structure with a large filling rate to ensure that the cam part 21 has high structural strength. A through hole K3 is provided on the cam part 21, which connects to the inner hole K2, thus forming a channel K1 for the linkage rope 41 to pass through. The inner hole K2 also serves as part of the channel K1, reducing the required drilling depth of the channel K1 and reducing processing requirements.

[0049] In this embodiment, the outer periphery 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 less than the distance L2 from the first fixed end 41a to the rotation center of the cam portion 21. Furthermore, from the side of the outer cam surface P1 near the opening K4 to the side near the first fixed end 41a, the distance from the outer cam surface P1 to the rotation center of the cam portion 21 gradually increases. Thus, when the arm 20 folds relative to the body 10, the exposed rope segment 411 is pushed outward by the outer cam surface P1. Specifically, referring to FIG7, based on the above-mentioned shape design of the outer cam surface P1, during the folding process, the linkage rope 41 is pulled out more from the opening K4 under the drive of the outer cam surface P1. As shown in Figure 7, the length of the exposed section 411 of the linkage rope 41 increases. Correspondingly, one end of the linkage rope 41 connected to the landing gear 30 moves closer to the fuselage 10, thereby causing the linkage rope 41 to pull the landing gear 30 closer to the fuselage 10, so that the landing gear 30 folds relative to the frame synchronously. The force transmission structure is simple and effective, and has a slight impact on the weight and shape of the aircraft 100.

[0050] Referring primarily to Figure 4, in this embodiment, the fuselage 10 has side plates 11 on both sides of its width direction Y. The side plates 11 are outer shell plates of the fuselage 10 along both sides of its width direction Y, and each side plate 11 has a through hole K6 that connects the internal space Q1 and the external space Q2 of the fuselage 10. The internal space Q1 can be used to install electrical components such as the aircraft 100's battery and main control board. The external space Q2 refers to the space outside the fuselage 10, i.e., the space of the external environment of the fuselage 10.

[0051] Two mounting plates 12 are connected to the side plate 11. The two mounting plates 12 are connected to the side plate 11 at intervals along the height direction Z (or vertical direction) of the aircraft 100. A through hole K6 is located between the two side plates 11. A cam part 21 is rotatably connected between the two mounting plates 12 via a first shaft 13. Specifically, the two ends of the first shaft 13 are fixed to the two mounting plates 12 respectively. The cam part 21 is provided with a rotating fitting hole K7, which is rotatably fitted onto the first shaft 13. The exposed rope section 411 passes through the through hole K6 and extends into the internal space Q1 of the fuselage 10, and the first fixed end 41a is fixed to the side of the fuselage 10 near the internal space Q1. In this way, the outer cam surface P1 of the cam part 21 and the exposed rope section 411 of the linkage rope 41 are both accommodated in the internal space Q1 of the fuselage 10, reducing the adverse effects of the outer cam surface P1 and the linkage rope 41 on the aerodynamic shape of the fuselage 10. Meanwhile, the exposed rope segment 411 of the linkage rope 41 is located inside the fuselage 10, which can be protected by the fuselage 10 and is not easily affected by the environment, and is not easily damaged by accidental snagging or other reasons, thus ensuring the use, installation and service life of the aircraft 100.

[0052] Optionally, the body 10 is further provided with a screw post 14, which, together with a screw 15, clamps the first fixed end 41a of the linkage rope 41. The screw post 14 is located on the side plate 11 near the internal space Q1. After the first fixed end 41a of the linkage rope 41 extends into the internal space Q1 through the through hole K6, it is locked and fixed to the screw post 14 by the screw 15. The first fixed end 41a can be coiled into a circle to increase its contact area with the screw post 14 and the screw 15, ensuring reliable fixation of the first fixed end 41a.

[0053] Optionally, in this embodiment, the arm 20 further includes a mounting base 22, which is located at the second end 20b of the arm 20. The mounting base 22 is provided with a guide block 23, which has a guide hole K5 for the linkage rope 41 to pass through. The guide block 23 and the guide hole K5 facilitate the guidance of the movement of the linkage rope 41 and make it convenient for the linkage rope 41 to be connected to the foot 30 at a suitable angle.

[0054] Referring primarily to Figure 5, in this embodiment, the linkage structure 40 also includes an elastic element 42. The elastic element 42 is elastically supported between the arm 20 and the legs 30, providing a restoring force for the legs 30 to unfold relative to the arm 20. When the arm 20 unfolds relative to the body 10, the outer cam surface P1 releases the linkage rope 41, and the elastic element 42 can automatically unfold the legs 30, making it convenient to use. That is, in the folded state, a certain amount of elastic potential energy is stored between the legs 30 and the arm 20, which allows the legs 30 to automatically unfold when the arm 20 unfolds.

[0055] Optionally, the tripod 30 is rotatably connected to the arm 20 via the second shaft 24. The elastic element 42 is a torsion spring, which is sleeved outside the second shaft 24 and elastically abuts against the arm 20 and the tripod 30. In other embodiments, the elastic element 42 may also be other structures, such as a tension spring, etc., which are not limited here.

[0056] In the aforementioned embodiments, the linkage rope 41 is used to link the folding of the linkage arm 20 and the folding of the tripod 30, and the elastic element 42 is used to provide the restoring force for the tripod 30 to unfold relative to the linkage arm 20.

[0057] In other embodiments, the configuration can be reversed, where the linkage rope 41 is used to coordinate the deployment of the boom 20 and the tripod 30. In this case, when the boom 20 is deployed relative to the body 10, the boom 20 (e.g., the cam portion 21 of the boom 20) abuts against the linkage rope 41 and pushes the linkage rope 41 to slide relative to the boom 20, causing the linkage rope 41 to pull the tripod 30 to deploy relative to the boom 20. An elastic element 42 is elastically supported between the boom 20 and the tripod 30, providing a restoring force for the tripod 30 when folded relative to the boom 20.

[0058] Referring to Figure 8, this embodiment also provides a flight system 1000. The flight system 1000 includes an aircraft 100 and a remote controller 200. The remote controller 200 is communicatively connected to the aircraft 100 and is used to control the aircraft 100.

[0059] The above embodiments are only used to illustrate the technical solutions of this application and are not intended to limit it. Although this application has been described in detail with reference to the above preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions to the technical solutions of this application should not depart from the spirit and scope of the technical solutions of this application.

Claims

1. An aircraft, characterized in that, The aircraft includes: a fuselage; an arm rotatably connected to the fuselage and capable of folding or unfolding relative to the fuselage; a landing gear rotatably connected to the arm and capable of folding or unfolding relative to the arm; and a linkage structure that is linked and cooperates with the arm and the landing gear respectively, for transmitting the rotation of the arm relative to the fuselage to the landing gear, thereby causing the landing gear to rotate relative to the arm, so as to fold or unfold the landing gear.

2. The aircraft according to claim 1, characterized in that: The linkage structure includes a linkage rope, which has a first fixed end and a second fixed end. The first fixed end is fixed to the machine body, and the second fixed end is fixed to the tripod. When the machine arm is folded relative to the machine body, the machine arm abuts 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. Alternatively, when the machine arm is unfolded relative to the machine body, the machine arm abuts 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 unfold relative to the machine arm.

3. The aircraft according to claim 2, characterized in that: The linkage structure also includes an elastic element that is elastically supported between the arm and the tripod; when the linkage rope is used to pull the tripod to fold relative to the arm, the elastic element is used to provide a restoring force for the tripod to unfold relative to the arm. When the linkage rope is used to pull the tripod out relative to the boom, the elastic element is used to provide the restoring force for the tripod to fold relative to the boom.

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

5. The aircraft according to claim 4, characterized in that: The arm has a first end and a second end, and the cam is located at the first end; the arm has a channel that extends from the first end to the second end; the two ends of the linkage rope pass through the channel to connect the body and the legs respectively.

6. The aircraft according to claim 5, characterized in that: The outer periphery of the cam portion has an outer cam surface, and the channel has an opening that passes 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 rotation center of the cam portion is less than the distance from the first fixed end to the rotation center of the cam portion.

7. The aircraft according to claim 6, characterized in that: 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 near the opening to the side near the first fixed end.

8. The aircraft according to claim 6, characterized in that: The body has a through hole that connects the internal space and the external space of the body; the exposed rope segment passes through the through hole and extends into the internal space of the body, and the first fixed end is fixed to the side of the body closer to the internal space.

9. The aircraft according to claim 2, characterized in that: The arm also includes a mounting base located at one end of the arm away from the body; the mounting base 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 1-9; And a remote controller, which is capable of communicating with the aircraft and is used to control the aircraft.

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