Frame structure and multi-rotor aircraft

Abstract

The present application provides a frame structure and a multi-rotor aircraft, wherein the frame structure is composed of multiple carbon tubes forming multiple triangular structures and has high overall stability; the motor and the propeller are installed on the third connecting member, and the third connecting member is supported by the third rod and the fourth rod. The single rod in the traditional structure that bears the tension can be changed to multiple rods that disperse the force. Under the condition of large tension output, the deformation caused by the single arm of the multi-rotor aircraft can be better suppressed, thereby ensuring the flight safety of the multi-rotor aircraft; the proportion of the frame structure in the maximum take-off weight of the multi-rotor aircraft is small, which means that the proportion of the load is large. Compared with the traditional structure, it can carry a larger weight or more cargo.

Description

Technical Field

[0001] The present application relates to the field of aircraft frames, and in particular to a frame structure and a multi-rotor aircraft. Background Art

[0002] Multirotor aircraft are used in logistics, transportation, mapping, and emergency communications. To cope with harsh flight conditions and payload requirements, they need to improve load capacity while maintaining chassis strength. The upper limit of a multirotor's payload capacity is determined by the maximum propulsion efficiency of its single arm, while the lower limit is determined by the strength of its chassis. The strength of a multirotor's chassis is positively correlated with its size and wall thickness.

[0003] For a given multirotor's single-arm maximum propulsion efficiency, the larger the size and wall thickness of its frame, the greater its load-bearing capacity. However, this also increases the weight of the frame as a percentage of the multirotor's overall maximum takeoff weight. Assuming a 2-fold increase in a multirotor's load-bearing capacity, the overall maximum takeoff weight would increase by 2.5-3 times. This means the load the multirotor can carry is smaller than the increase in its overall weight, and its overall efficiency decreases. Furthermore, larger dimensions negatively impact the multirotor's maneuverability, flight control rate, and stability. Summary of the Invention

[0004] The present application provides a frame structure and a multi-rotor aircraft, which solves the problem of a large proportion of frame weight in the prior art.

[0005] On the one hand, the present application provides a frame structure, comprising a main support frame with a conical structure and a plurality of rotor support frames with conical structures, wherein the rotor support frames are distributed around the main support frame and connected to the main support frame, and the tips of the main support frames face away from the main support frame;

[0006] The main support frame includes a plurality of first rods, a plurality of second rods, a plurality of first connecting members and a second connecting member, wherein the first rods are connected end to end through the first connecting members, the first connecting members are respectively connected to one end of the second rods, and the other ends of the second rods converge at the second connecting member and are connected to the second connecting member;

[0007] The rotor support frame corresponds to the first rod one by one, the rotor support frame is connected to the first connecting member and the second connecting member, and the tip of the rotor support frame is flush with the second connecting member.

[0008] In a possible implementation, the rotor support frame includes a third rod, two fourth rods and a third connecting member;

[0009] One end of the third rod is connected to the second connecting member;

[0010] One end of the fourth rod is connected to two adjacent first connecting members;

[0011] The other ends of the third rod and the fourth rod converge at the third connecting member and are connected to the third connecting member.

[0012] In a possible implementation, the first connecting member, the second connecting member, and the third connecting member each have a plurality of accommodating cavities, and the ends of the first rod, the second rod, the third rod, and the fourth rod are respectively inserted into and fixed in the corresponding accommodating cavities.

[0013] In a possible implementation, each of the first connecting members includes a first part and a second part, each of the first part and the second part having a plurality of accommodating cavities; the second connecting member includes a plurality of third parts, the plurality of third parts being distributed along a circumference and having a plurality of accommodating cavities;

[0014] Each of the second rods comprises a rod body A and a rod body B, one end of the rod body A is respectively inserted into the corresponding accommodation cavity of the first part, one end of the rod body B is respectively inserted into the corresponding accommodation cavity of the second part, and the other ends of the rod body A and the rod body B are respectively inserted into the accommodation cavities of two adjacent third parts;

[0015] The two ends of the first rod are respectively inserted into the receiving cavities of the adjacent first part and the second part;

[0016] The first part is detachably connected to the adjacent second part;

[0017] Two adjacent third parts are detachably connected.

[0018] In one possible implementation, the first part is provided with a first contact plane and a first connecting ear; the second part is provided with a second contact plane and a second connecting ear; the first contact plane is in contact with the second contact plane, and the first connecting ear and the second connecting ear are staggered and detachably connected;

[0019] The third part is provided with a third contact surface, a fourth contact surface, a third connecting ear and a fourth connecting ear. The third contact surface is in contact with the fourth contact surface of another adjacent third part. The third connecting ear and the fourth connecting ear of another adjacent third part are staggered and detachably connected.

[0020] In a possible implementation, through holes are provided on the first connecting ear, the second connecting ear, the third connecting ear and the fourth connecting ear; the through hole of the first connecting ear and the through hole of the second connecting ear are coaxial and connected by bolts; the through hole of the third connecting ear and the through hole of the fourth connecting ear are coaxial and connected by bolts.

[0021] In a possible implementation, the frame structure further includes a first ring, and the third parts are all rotatably mounted on the first ring.

[0022] In a possible implementation, the frame structure further includes a second ring, and the second ring includes a plurality of straight segments corresponding one-to-one to the first rods, and the first part and the second part corresponding to each first rod are rotatably mounted on the same straight segment.

[0023] On the other hand, the present application provides a multi-rotor aircraft, which includes the frame structure described above, and also includes multiple propellers, multiple motors and a power supply; the power supply is fixed in the space formed by the first rod and the second rod; a motor is installed at the tip of each rotor support frame, the propeller is installed on the motor, and the motor is electrically connected to the power supply.

[0024] The embodiments of the present application provide a frame structure and a multi-rotor aircraft, wherein the frame structure is composed of multiple first rods, second rods, etc. to form multiple triangular structures, and has high overall stability; the motor and the propeller are arranged at the tip of the rotor support frame, and the tip of the rotor support frame is multi-point aggregated, which can change the single rod in the traditional structure to bear tension to multiple points of dispersed force. Under the condition of large tension output, the deformation caused by the single arm of the multi-rotor aircraft can be better suppressed, thereby ensuring the flight safety of the multi-rotor aircraft; the proportion of the frame structure in the maximum take-off weight of the multi-rotor aircraft is small, which means that the proportion of the load is large. Compared with the traditional structure, it can carry a larger weight or more cargo. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solution of the present application, the following is a brief introduction to the drawings required for use in the embodiments. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0026] Figure 1 This is a structural diagram of a frame structure provided in the first embodiment of the present application;

[0027] Figure 2 This is a schematic top view of a frame structure provided in the first embodiment of the present application;

[0028] Figure 3This is a structural diagram of a frame structure provided in the second embodiment of the present application;

[0029] Figure 4 This is a schematic structural diagram of a unit frame provided in the second embodiment of the present application;

[0030] Figure 5 This is a schematic diagram of the connection between the first component and the second component provided in the second embodiment of the present application;

[0031] Figure 6 This is a schematic structural diagram of the third component provided in the second embodiment of the present application;

[0032] Figure 7 This is a schematic diagram of the connection between the first ring member and the second connecting member provided in the third embodiment of the present application;

[0033] Figure 8 This is a schematic diagram of the connection between the second ring member and the first connecting member provided in the fourth embodiment of the present application;

[0034] Figure 9 This is a schematic structural diagram of a folded form provided by the fifth embodiment of the present application;

[0035] Figure 10 This is a schematic diagram of the folded form provided by the fifth embodiment of the present application;

[0036] Figure 11 It is a schematic diagram of the traditional frame structure of a quadrotor aircraft;

[0037] Illustration:

[0038] Among them, 11, first rod; 12, second rod; 121, rod body A; 122, rod body B; 13, third rod; 14, fourth rod; 21, first connecting member; 211, first part; 212, second part; 213, first contact plane; 214, first connecting ear; 215, second contact plane; 216, second connecting ear; 22, second connecting member; 221, third part; 222, third contact surface; 223, fourth contact surface; 224, third connecting ear; 225, fourth connecting ear; 23, third connecting member; 3, first ring; 4, second ring; 5, sleeve; 6, base. DETAILED DESCRIPTION

[0039] The following embodiments are described in detail, with examples illustrated in the accompanying drawings. When the following description refers to the drawings, identical numbers in different figures represent identical or similar elements unless otherwise indicated. The embodiments described in the following embodiments are not intended to represent all possible implementations consistent with the present application. They are merely examples of systems and methods consistent with certain aspects of the present application, as detailed in the claims.

[0040] See also Figure 1 , which is a structural diagram of a frame structure provided in the first embodiment of the present application; see Figure 2 , a schematic diagram of a top view of a frame structure provided by the first embodiment of the present application. The embodiment of the present application provides a frame structure, comprising a main support frame of a conical structure and several rotor support frames of a conical structure, the rotor support frames corresponding one-to-one with the rotors of the multi-rotor aircraft, the rotor support frames being distributed around the main support frame and connected to the main support frame, the tip of the main support frame facing away from the main support frame; the main support frame comprises several first rods 11, several second rods 12, several first connecting members 21 and one second connecting member 22, the first rods 11 being connected end to end through the first connecting member 21, the first connecting member 21 being connected to one end of each second rod 12, the other end of the second rod 12 converging at the second connecting member 22 and connected to the second connecting member 22; the rotor support frames corresponding one-to-one with the first rods 11, the rotor support frames being connected to the first connecting member 21 and the second connecting member 22, the tip of the rotor support frames being flush with the second connecting member 22.

[0041] Specifically, when used for a quadrotor aircraft, the frame structure includes four horizontal first rods 11, four second rods 12, four third rods 13, four pairs of fourth rods 14, four first connecting members 21, one second connecting member 22 and four third connecting members 23; the rotor support frame is composed of one third rod 13, one pair of fourth rods 14 and one third connecting member 23, the first rod 11, the second rod 12, the third rod 13 and the fourth rod 14 are all made of carbon tubes; the first connecting member 21, the second connecting member 22 and the third connecting member 23 are all provided with a plurality of accommodating cavities for accommodating the ends of the carbon tubes, and the accommodating cavities are cylindrical; the four first rods 11 are connected by the first connecting member 21 The first rods 11 are connected end to end, with the ends of the first connecting member 21 respectively inserted into the accommodating cavities of the first connecting member 21 to form a regular quadrilateral; each first connecting member 21 includes 5 accommodating cavities, corresponding to 2 first rods 11, 1 second rod 12 and 2 fourth rods 14, and one end of the second rod 12 and the fourth rod 14 are both inserted into the accommodating cavities of the first connecting member 21; the second connecting member 22 includes 8 accommodating cavities, and the other end of the second rod 12 and one end of the third rod 13 are both inserted into the accommodating cavities of the second connecting member 22; each third connecting member 23 includes 3 accommodating cavities, and the other ends of the third rod 13 and a pair of fourth rods 14 are both inserted into the accommodating cavities of the third connecting member 23.

[0042] The carbon tube and the accommodating cavity are bonded with resin, or by interference fit, threaded connection, etc.; in addition, a radially penetrating screw hole is opened at the accommodating cavity, and a radially penetrating screw hole is opened at the end of the carbon tube. After the carbon tube is inserted into the accommodating cavity, the central axes of the two screw holes coincide and are further fixed by screws, thereby further ensuring the stability of the connection, and preventing the loosening of the frame structure connection caused by vibration or bad weather.

[0043] The frame structure in the above content is an integrated structure, and its structural strength and weight reach the optimal ratio.

[0044] See also Figure 3 , which is a structural diagram of a frame structure provided in the second embodiment of the present application; see Figure 4 , which is a schematic diagram of the structure of a unit frame provided in the second embodiment of the present application. This embodiment of the present application provides another frame structure for a quadrotor aircraft. While ensuring structural strength, the frame structure is split into four unit frames. Each unit frame includes a rotor support frame and 1 / 4 of the main support frame for easy transportation.

[0045] See also Figure 5 , which is a schematic diagram of the connection between the first part and the second part provided in the second embodiment of the present application. On the basis of the aforementioned embodiment, the first connecting member 21 further includes a first part 211 and a second part 212, each of which is provided with three accommodating cavities, the first part 211 is provided with a first contact plane 213 and a plurality of first connecting ears 214 with through holes, the second part 212 is provided with a second contact plane 215 and a plurality of second connecting ears 216 with through holes; the first contact plane 213 is fitted with the second contact plane 215, the through hole center axis of the first connecting ear 214 coincides with the through hole center axis of the second connecting ear 216, the first connecting ear 214 and the second connecting ear 216 are staggered, and the coaxial through holes are connected by bolts;

[0046] The two fourth rods 14 corresponding to each unit frame are respectively inserted into the accommodating cavities of the first part 211 and the second part 212 at both ends of the corresponding first rod 11;

[0047] The bolts are half-thread bolts, which can more conveniently connect and separate the first part 211 and the second part 212;

[0048] See also Figure 6, which is a structural diagram of the third part provided in the second embodiment of the present application. The second connecting member 22 includes four third parts 221 distributed along a circumference, and each third part 221 is provided with three accommodating cavities; the third part 221 is provided with two third contact surfaces 222, two fourth contact surfaces 223, a plurality of third connecting ears 224 with through holes, and a plurality of fourth connecting ears 225 with through holes. When the third contact surface 222 of the third part 221 is in contact with the fourth contact surface 223 of the adjacent third part 221, the through hole of the third connecting ear 224 of the third part 221 coincides with the central axis of the through hole of the fourth connecting ear 225 of the adjacent third part 221. The third connecting ear 224 and the fourth connecting ear 225 are staggered, and the coaxial through holes are connected by half-thread bolts.

[0049] See also Figure 3 Each second rod 12 includes a rod body A121 and a rod body B122; one end of the rod body A121 is inserted into the first part 211, one end of the rod body B122 is inserted into the second part 212, and the other ends of the rod body A121 and the rod body B122 are respectively inserted into two adjacent third parts 221;

[0050] In the embodiment of the present application, the frame structure can be divided into 4 unit frames, such as Figure 4 As shown, each unit frame includes a first rod 11, a rod body A121, a rod body B122, a third rod 13, two fourth rods 14, a first part 211, a second part 212, a third part 221 and a third connecting member 23; one end of the first rod 11, one end of the rod body A121 and one end of one fourth rod 14 are all inserted into the accommodating cavity of the first part 211; the other end of the first rod 11, one end of the rod body B122 and one end of another fourth rod 14 are all inserted into the accommodating cavity of the second part 212; the other end of the rod body A121, the other end of the rod body B122 and one end of the third rod 13 are all inserted into the accommodating cavity of the third part 221; the other end of the third rod 13 and the other ends of the two fourth rods 14 are all inserted into the accommodating cavity of the third connecting member 23;

[0051] The four unit frames forming the frame structure are evenly spaced, and the frame structure includes a plurality of triangular structures connected by the carbon tubes, and has high structural stability. The unit frames can be connected or combined using a few bolts, which is easy to operate, simple in structure, and low in cost. Storage or transportation in the form of unit frames takes up less space.

[0052] The outer diameter of the carbon tube is 36 mm, and the wall thickness is 1 mm; the length of the third rod 13 is 1550 mm.

[0053] The embodiment of the present application further provides a quadrotor aircraft comprising the above-mentioned frame structure, wherein the weight of the structural parts of the quadrotor aircraft is 6.2 kg, the weight of the carbon tubes is 2.6 kg, and the total weight is 8.8 kg;

[0054] The quadrotor aircraft also includes 4 propellers, 4 motors and a power supply; the propellers are rotors, and the power supply is fixed in the space formed by the first rod 11 and the second rod 12; a motor is installed on each third connecting member 23, and a propeller is installed on each motor, and the motor is electrically connected to the power supply; the maximum take-off weight of the quadrotor aircraft is 100 kilograms.

[0055] The maximum take-off weight of the quadrotor aircraft including the integrated frame structure of the aforementioned embodiment can also reach 100 kilograms, but the integrated frame structure is lighter than the split frame structure.

[0056] See also Figure 7 , which is a schematic diagram of the connection between the first ring member and the second connecting member provided in the third embodiment of the present application. This embodiment of the present application provides another frame structure for a quadrotor aircraft. Based on the previous embodiment, the second connecting member 22 is designed as a folding structure, thereby enabling the folding of the frame structure for easy storage and transportation. Folding and storage are achieved by disassembling bolts, which is also very convenient to operate.

[0057] The frame structure also includes a first ring member 3 made of a hollow tube, which is formed by four straight rods connected end to end. The straight rods are made of hollow tubes, and the angle between two adjacent straight rods is 90°; each third part 221 is provided with a penetrating connecting hole, and the first ring member 3 passes through the connecting hole, and each straight rod passes through one connecting hole, so that the third part 221 can rotate relative to the first ring member 3; since each third part 221 corresponds to a unit frame, the bolts connecting the two adjacent unit frames are removed, and the unit frame can rotate upward around the first ring member 3.

[0058] See also Figure 8 , which is a schematic diagram of the connection between the second ring member and the first connecting member provided in the fourth embodiment of the present application. This embodiment of the present application provides another foldable frame structure, which also includes a second ring member 4 made of a hollow tube. The second ring member 4 is also made of four straight rods connected end to end, and the angle between two adjacent rods is 90°. The second ring member 4 is arranged on the inner side of the first rod 11. The first part 211 and the second part 212 are both fixed with a sleeve 5, and the sleeve 5 is sleeved on the second ring member 4. After removing the corresponding bolts, the unit frame can be rotated downward around the second ring member 4.

[0059] The above two folding forms can gather the unfolded unit frames into one place. The gathered frame structure is approximately strip-shaped. From the perspective of spatial form, it is easier to transport. Moreover, after gathering, especially the upward rotating gathering method, the propeller can be protected by the unit frame, reducing the chance of damage during transportation.

[0060] See also Figure 9 , is a schematic diagram of the structure of the folded form provided by the fifth embodiment of the present application, and specifically, is a schematic diagram of the unfolded folded form. This embodiment of the present application provides another foldable frame structure, which also includes a base 6. Taking a quadrotor aircraft as an example, the base 6 is located between four unit frames. The connection or disassembly method between the unit frames is the same as that of the above embodiment. Four hinge seats are provided on the surface of the base 6 facing the unit frames. The third part 221 on each unit frame corresponds to one hinge seat and is rotatably connected thereto. Specifically, the connection can be achieved through a pin shaft, and the unit frame can rotate upward around the pin shaft or the hinge seat.

[0061] See also Figure 10 , is a schematic diagram of the folding form provided by the fifth embodiment of the present application. This embodiment of the present application can also gather the unfolded unit frames together, reducing their occupied space and reducing the difficulty of transportation; through the above multiple implementation methods, the folding can meet the different usage needs of different users.

[0062] See also Figure 11 , a schematic diagram of a conventional quadrotor frame structure. A conventional quadrotor is constructed using the same power supply, motor, and rotor dimensions as the aforementioned embodiment, meeting a maximum takeoff weight of 100 kg. To ensure the aircraft's overall flight stability and ability to withstand extreme conditions, the overall power system is designed with a thrust-to-weight ratio of 2:1; the maximum tensile force a single arm can withstand should be no less than 50 kg. To ensure the conventional quadrotor can withstand this tensile force without excessive deformation while also ensuring the conventional frame structure does not contribute significantly to the overall weight of the aircraft, the conventional frame structure is constructed using carbon tubes with an outer diameter of 60 mm and a wall thickness of 3 mm.

[0063] The carbon tubes in the traditional frame structure are connected by a center disk. The center disk is machined from a whole piece of 7075 aluminum alloy to retain the maximum strength of the material. The overall strength of the center disk is improved by combining it with reinforcing ribs. The center disk weighs 12.68 kg, the four motor fixings weigh a total of 6.18 kg, and the four carbon tubes made of carbon fiber weigh 5.4 kg, for a total weight of 24.26 kg.

[0064] Compared with traditional quadrotor aircraft, the quadrotor aircraft including the frame structure in the second embodiment uses the same specifications of power supply, motor and rotor of the same size, and achieves the same structural strength and maximum take-off weight of 100 kg. The weight of the frame structure in the second embodiment is only 38% of the traditional structure. Correspondingly, it is obvious that under the same conditions, the weight of the frame structure of the present application accounts for a much smaller proportion of the maximum take-off weight of the multi-rotor aircraft made with it than the weight of the traditional frame accounts for a much smaller proportion of the maximum take-off weight of the multi-rotor aircraft made with it.

[0065] In the third embodiment, a first ring 3 for folding is added, and in the fourth embodiment, a second ring 4 and a sleeve 5 are added. The weight of the first ring 3 is less than that of the second ring 4 and the sleeve 5. In the fourth embodiment, the weight of the frame structure is 44% of the weight of the traditional frame. It can be seen that the technical solutions of the third and fourth embodiments are superior to the traditional frame structure.

[0066] Compared with the split frame structure in the second embodiment, the first connecting member 21 and the second connecting member 22 in the integrated frame structure in the first embodiment are both integrated structures, and the number of second rods 12 connected to the first connecting member 21 is one, and the demand for bolted connecting members is less. Therefore, the first embodiment is lighter than the second embodiment.

[0067] A frame structure and a multi-rotor aircraft are provided in the embodiments of the present application. The frame structure is composed of multiple carbon tubes to form multiple triangular structures, and has high overall stability; the motor and the propeller are installed on the third connecting member, and the third connecting member is supported by a third rod and a fourth rod. The single rod in the traditional structure that bears tension can be changed to a multi-rod distributed force. Under the condition of large tension output, the deformation caused by the single arm of the multi-rotor aircraft can be better suppressed, thereby ensuring the flight safety of the multi-rotor aircraft; the proportion of the frame structure in the maximum take-off weight of the multi-rotor aircraft is small, which means that the proportion of the load is large. Compared with the traditional structure, it can carry a larger weight or more cargo.

[0068] In other embodiments of the present application, the rotor support frame corresponds one-to-one to the number of rotors of the multi-rotor aircraft. When the number of rotors of the multi-rotor aircraft is different from the aforementioned embodiments, a rotor support frame corresponding to the number of rotors is selected to ensure that when the rotor support frame is connected to the main support frame, the resultant force of the rotor support frame falls on the center of the main support frame.

[0069] Similar parts between the embodiments provided in this application can be referenced to each other. The specific implementation methods provided above are only a few examples under the overall concept of this application and do not constitute a limitation on the scope of protection of this application. For those skilled in the art, any other implementation methods expanded based on the scheme of this application without expending creative work shall fall within the scope of protection of this application.

Claims

1. A frame structure, characterized in that: For a multi-rotor aircraft, comprising: a main support frame of a conical structure and a plurality of rotor support frames of a conical structure, wherein the rotor support frames are distributed around the main support frame and connected to the main support frame, and the tips of the rotor support frames are away from the main support frame; The main support frame comprises a plurality of first rods (11), a plurality of second rods (12), a plurality of first connecting members (21) and a second connecting member (22), wherein the first rods (11) are connected end to end via the first connecting members (21), the first connecting members (21) are respectively connected to one end of the second rod (12), and the other ends of the second rods (12) converge at the second connecting member (22) and are connected to the second connecting member (22); The rotor support frame corresponds to the first rod (11) one by one, the rotor support frame is connected to the first connecting member (21) and the second connecting member (22), and the tip of the rotor support frame is flush with the second connecting member (22); Each of the first connecting members (21) comprises a first part (211) and a second part (212), each of the first part (211) and the second part (212) having a plurality of accommodating cavities; the second connecting member (22) comprises a plurality of third parts (221), the plurality of third parts (221) being distributed along a circumference and having a plurality of accommodating cavities; Each of the second rods (12) comprises a rod body A (121) and a rod body B (122), one end of the rod body A (121) is respectively inserted into the corresponding accommodation cavity of the first part (211), one end of the rod body B (122) is respectively inserted into the corresponding accommodation cavity of the second part (212), and the other ends of the rod body A (121) and the rod body B (122) are respectively inserted into the accommodation cavities of two adjacent third parts (221); The two ends of the first rod (11) are respectively inserted into the accommodating cavities of the adjacent first part (211) and second part (212); The first part (211) is detachably connected to the adjacent second part (212); Two adjacent third parts (221) are detachably connected; The first part (211) is provided with a first contact plane (213) and a first connecting ear (214); the second part (212) is provided with a second contact plane (215) and a second connecting ear (216); the first contact plane (213) is fitted with the second contact plane (215), and the first connecting ear (214) and the second connecting ear (216) are staggered and detachably connected; The third part (221) is provided with a third contact surface (222), a fourth contact surface (223), a third connecting ear (224) and a fourth connecting ear (225); the third contact surface (222) is in contact with the fourth contact surface (223) of another adjacent third part (221); the third connecting ear (224) and the fourth connecting ear (225) of another adjacent third part (221) are staggered and detachably connected; The frame structure further comprises a first ring member (3), and the third parts (221) are all rotatably mounted on the first ring member (3).

2. The frame structure according to claim 1, characterized in that: The rotor support frame comprises a third rod (13), two fourth rods (14) and a third connecting member (23); One end of the third rod (13) is connected to the second connecting member (22); One end of the fourth rod (14) is connected to two adjacent first connecting members (21); The other ends of the third rod (13) and the fourth rod (14) converge at the third connecting member (23) and are connected to the third connecting member (23).

3. The frame structure according to claim 2, characterized in that: The first connecting member (21), the second connecting member (22) and the third connecting member (23) each have a plurality of accommodating cavities, and the ends of the first rod (11), the second rod (12), the third rod (13) and the fourth rod (14) are respectively inserted into and fixed in the corresponding accommodating cavities.

4. The frame structure according to any one of claims 1 to 3, characterized in that: Through holes are provided on the first connecting ear (214), the second connecting ear (216), the third connecting ear (224) and the fourth connecting ear (225); the through hole of the first connecting ear (214) and the through hole of the second connecting ear (216) are coaxial and connected by bolts; the through hole of the third connecting ear (224) and the through hole of the fourth connecting ear (225) are coaxial and connected by bolts.

5. A frame structure, characterized in that: For a multi-rotor aircraft, comprising: a main support frame of a conical structure and a plurality of rotor support frames of a conical structure, wherein the rotor support frames are distributed around the main support frame and connected to the main support frame, and the tips of the rotor support frames are away from the main support frame; The main support frame comprises a plurality of first rods (11), a plurality of second rods (12), a plurality of first connecting members (21) and a second connecting member (22), wherein the first rods (11) are connected end to end via the first connecting members (21), the first connecting members (21) are respectively connected to one end of the second rod (12), and the other ends of the second rods (12) converge at the second connecting member (22) and are connected to the second connecting member (22); The rotor support frame corresponds to the first rod (11) one by one, the rotor support frame is connected to the first connecting member (21) and the second connecting member (22), and the tip of the rotor support frame is flush with the second connecting member (22); Each of the first connecting members (21) comprises a first part (211) and a second part (212), each of the first part (211) and the second part (212) having a plurality of accommodating cavities; the second connecting member (22) comprises a plurality of third parts (221), the plurality of third parts (221) being distributed along a circumference and having a plurality of accommodating cavities; Each of the second rods (12) comprises a rod body A (121) and a rod body B (122), one end of the rod body A (121) is respectively inserted into the corresponding accommodation cavity of the first part (211), one end of the rod body B (122) is respectively inserted into the corresponding accommodation cavity of the second part (212), and the other ends of the rod body A (121) and the rod body B (122) are respectively inserted into the accommodation cavities of two adjacent third parts (221); The two ends of the first rod (11) are respectively inserted into the accommodating cavities of the adjacent first part (211) and second part (212); The first part (211) is detachably connected to the adjacent second part (212); Two adjacent third parts (221) are detachably connected; The first part (211) is provided with a first contact plane (213) and a first connecting ear (214); the second part (212) is provided with a second contact plane (215) and a second connecting ear (216); the first contact plane (213) is fitted with the second contact plane (215), and the first connecting ear (214) and the second connecting ear (216) are staggered and detachably connected; The third part (221) is provided with a third contact surface (222), a fourth contact surface (223), a third connecting ear (224) and a fourth connecting ear (225); the third contact surface (222) is in contact with the fourth contact surface (223) of another adjacent third part (221); the third connecting ear (224) and the fourth connecting ear (225) of another adjacent third part (221) are staggered and detachably connected; The frame structure further comprises a second ring member (4), and the second ring member (4) comprises a plurality of straight segments corresponding one to one with the first rods (11), and the first part (211) and the second part (212) corresponding to each first rod (11) are both rotatably mounted on the same straight segment.

6. A multi-rotor aircraft comprising the frame structure according to any one of claims 1 to 5, characterized in that: It also includes: multiple propellers, multiple motors and a power supply; the power supply is fixed in the space formed by the first rod (11) and the second rod (12); a motor is installed at the tip of each rotor support frame, the propeller is installed on the motor, and the motor is electrically connected to the power supply.

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