Multi-rotor loading unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to a multi-rotor loading unmanned aerial vehicle which comprises a rack, a cabin and a foot stool. The engine room and the foot stool are fixedly connected with the rack, an upper-layer engine arm and a lower-layer engine arm are arranged in the rack, the upper-layer engine arm and the lower-layer engine arm are fixedly connected through a first support rod and a second support rod, meanwhile, the upper-layer engine arm and the lower-layer engine arm are both arranged in a two-section foldable mode, and a connecting assembly is arranged at the folding position. The upper-layer vehicle arm and the lower-layer vehicle arm can be unfolded and folded in the horizontal direction through the connecting assemblies and are locked after being unfolded. According to the unmanned aerial vehicle, by arranging the two layers of vehicle arms, the load capacity of the unmanned aerial vehicle is greatly improved, the effective load of the unmanned aerial vehicle can reach 100 kg through connection and fixation of the support rods and arrangement of the propellers, the blank of the large-load field of an existing unmanned aerial vehicle is filled up, in addition, the upper-layer vehicle arms and the lower-layer vehicle arms are arranged in a foldable mode, and the unmanned aerial vehicle is convenient to use. The occupied area can be effectively saved when the unmanned aerial vehicle is parked, and convenience is brought to use.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a multi-rotor load-carrying unmanned aerial vehicle. Background Art

[0002] A multi-rotor drone is a special unmanned helicopter with three or more rotor axes. Multi-rotor drones perform well in terms of controllability and stability, but due to their low energy efficiency, the load capacity of multi-rotor drones is generally low.

[0003] Multi-rotor drones require multiple rotors to provide lift, which makes them less efficient in consuming energy than single-rotor drones (such as fixed-wing drones) or rotorless drones (such as fixed-wing aircraft); low energy efficiency means that drones can carry less payload at the same volume or weight; in addition, multi-rotor drones are generally inferior to fixed-wing drones in terms of endurance and hovering time, which limits their application in situations where long-term missions are required (such as search and rescue and firefighting).

[0004] Therefore, although multi-rotor UAVs perform better in terms of controllability and stability, they are often not as good as fixed-wing UAVs in tasks requiring high payload and long endurance. Therefore, the present invention proposes a multi-rotor load-bearing UAV, which greatly improves the effective payload of the multi-rotor UAV, fills the gap in the field of large payload of multi-rotor UAVs, and lays a solid foundation for the multi-field application of multi-rotor UAVs. Summary of the invention

[0005] The purpose of the present invention is to provide a multi-rotor load-bearing UAV to solve the problem that the load-bearing capacity of existing multi-rotor UAVs is generally low, thereby limiting their application in more fields.

[0006] To achieve the above object, the present invention adopts the following technical solution: a multi-rotor load-carrying UAV, comprising a frame, a cabin and a tripod, wherein a battery is installed in the cabin, and the cabin and the tripod are respectively fixedly connected to the frame;

[0007] The frame includes a first connecting member and a second connecting member arranged up and down, the first connecting member and the second connecting member are fixedly connected, an upper machine arm is fixedly connected via the first connecting member, and a lower machine arm is fixedly connected via the second connecting member;

[0008] The upper machine arm is connected to the lower machine arm through a first support rod, and the two ends of the first support rod are respectively fixedly connected to the upper machine arm and the lower machine arm; the lower machine arm is connected to the first connecting member through a second support rod, and the two ends of the second support rod are respectively hinged to the lower machine arm and the first connecting member;

[0009] The wing arms of the upper machine arm and the lower machine arm are both provided with two sections, namely the first wing arm and the second wing arm, and the first wing arm and the second wing arm of the upper and lower layers are both connected by a connecting assembly in a foldable manner without being disassembled;

[0010] The upper second wing arm is connected to the upper propeller, the lower second wing arm is connected to the lower propeller, the upper propeller is set downward, and the lower propeller is set upward.

[0011] Furthermore, the number of the upper machine arms and the number of the lower machine arms are both three, and in the horizontal plane orthographic projection, the upper machine arms and the lower machine arms are evenly arranged with an interval of 60° between each other.

[0012] Furthermore, each of the upper machine arms is connected to the two lower machine arms via two first bracket rods, and each of the lower machine arms is connected to the first connecting member via a second bracket rod.

[0013] Furthermore, the tripod is fixedly connected to the bottom of the connecting assembly on each lower machine arm at the same time.

[0014] Furthermore, the connecting component includes a first component, a second component and a locking piece; one end of the first component is fixedly connected to one end of the first wing arm, and one end of the second component is fixedly connected to the second wing arm; the other end of the first component is hinged to the other end of the second component in the horizontal direction, and the locking piece is respectively connected to the first component and the second component.

[0015] Furthermore, the locking member includes an armrest end, a hinged end and a connecting rod, the hinged end is hinged to the first component, and both ends of the connecting rod are respectively hinged to the second component and the armrest end.

[0016] Furthermore, both ends of the first support rod are respectively fixedly connected to the first components in the upper and lower layer connection components, and the second support rod is hinged to the lower layer arm at the first component in the lower layer connection component.

[0017] Furthermore, the cabin is fixedly installed in a space area enclosed by the first support rod and the second support rod.

[0018] Furthermore, the lower part of the second connecting member is fixedly connected to the quick-release connector.

[0019] Furthermore, the load capacity of the UAV can reach 100kg.

[0020] Beneficial effects of the present invention:

[0021] 1. The UAV of the present invention adopts a double-layer arm structure design, and supports between the upper and lower arms, which can effectively ensure the stability of the arms. At the same time, the propellers of the upper and lower arms are relatively arranged, which improves the force of the aircraft and correspondingly improves the efficiency. The effective load of the UAV of the present invention can reach 100kg, filling the gap in the field of large load-bearing multi-rotor UAVs;

[0022] 2. The arms of the drone of the present invention are foldable, so that the arms of the drone of the present invention can be folded and retracted when docked, which reduces the space occupied during docking and brings convenience to use. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the overall structure of the present invention (machine arm unfolded state);

[0024] Figure 2 It is a schematic diagram of the overall structure of the frame of the present invention;

[0025] Figure 3 is a schematic diagram of the installation structure of the first bracket rod of the present invention;

[0026] Figure 4 The present invention Figure 3 A partial enlarged schematic diagram of part A;

[0027] Figure 5 is a schematic diagram of the second bracket rod installation structure of the present invention;

[0028] Figure 6 The present invention Figure 5 A partial enlarged schematic diagram of part B;

[0029] Figure 7 It is a schematic diagram of the tripod installation structure of the present invention;

[0030] Figure 8 Schematic diagram of the connection assembly structure of the present invention (locked state);

[0031] Fig. 9 is a schematic diagram of the use of the locking member of the present invention;

[0032] Fig.10 It is a schematic diagram of the overall structure of the present invention (machine arm folded state);

[0033] Fig.11 It is a schematic diagram of the structure of the connection assembly of the present invention (open state).

[0034] The names corresponding to the marks in the figure are:

[0035] 1. Frame; 11. First connecting piece; 12. Second connecting piece; 121. Quick-release connector; 13. Connecting rod; 14. Upper arm; 141. Upper first wing arm; 142. Upper second wing arm; 143. Upper propeller; 15. Lower arm; 151. Lower first wing arm; 152. Lower second wing arm; 153. Lower propeller; 16. First bracket rod; 17. Second bracket rod; 2. Cabin; 3. Tripod; 4. Connecting assembly; 41. First assembly; 42. Second assembly; 43. Locking piece; 431. Handrail end; 432. Articulated end; 433. Connecting rod. DETAILED DESCRIPTION

[0036] The technical solution of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention.

[0037] like Figure 1 As shown in FIG7 , the load-carrying UAV of the present invention includes a frame, a cabin is fixedly installed through the frame, a battery is installed in the cabin, the battery is used to power the propeller of the UAV, a tripod is fixedly installed below the frame, the tripod is used to support the UAV, and a quick-release connector is also fixedly installed below the frame, the quick-release connector is used to carry the UAV load.

[0038] like Figure 2-3 As shown in 5 and 7, the frame of the present invention includes an upper and lower layer, and a first connecting member and a second connecting member are arranged in the frame. The first connecting member and the second connecting member are arranged up and down in space, and the first connecting member and the second connecting member are fixedly connected by a connecting rod; an upper machine arm is fixedly installed by the first connecting member, and a lower machine arm is fixedly installed by the second connecting member; the upper machine arm is connected to the lower machine arm by a first support rod, and each upper machine arm is connected to two lower machine arms at the same time, and the first support rod is fixedly connected to the upper machine arm and the lower machine arm at the same time; the first connecting member is connected to the lower machine arm through the second support rod, and the second support rod is hinged to the first connecting member and the second support rod at the same time; the tripod is fixedly connected to all the lower machine arms at the same time.

[0039] like Figure 3-6As shown in 8-9, the upper arm and the lower arm are both connected in sections, wherein the upper arm includes an upper first wing arm and an upper second wing arm, and the upper first wing arm and the upper second wing arm are connected by a connecting assembly; the lower arm includes a lower first wing arm and a lower second wing arm, and the lower first wing arm and the lower second wing arm are also connected by a connecting assembly; the connecting assembly includes a first assembly, a second assembly and a locking piece. Taking the upper arm as an example, one end of the first assembly is fixedly connected to the upper first wing arm, one end of the second assembly is fixedly connected to the upper second wing arm, the other end of the first assembly is hinged to the other end of the second assembly, and a locking piece is arranged between the first assembly and the second assembly, the locking piece includes an armrest end, a hinged end and a connecting rod, the hinged end is hinged to the first assembly, one end of the connecting rod is hinged to the second assembly, and the other end of the connecting rod is hinged to the armrest end.

[0040] The first component on the upper arm is fixedly connected to the first component on the lower arm through the first bracket rod, thereby realizing the connection between the upper arm and the lower arm; the first component on the lower arm is connected to the first connecting piece through the second bracket rod, thereby realizing the articulation of the second bracket rod with the lower arm and the first connecting piece respectively.

[0041] An upper propeller is fixedly installed through an upper second wing arm in the upper arm, and a lower propeller is fixedly installed through a lower second wing arm on the lower arm. The upper propeller is installed downward and the lower propeller is installed upward.

[0042] like Figure 1 9-11, when the drone needs to be folded from the extended state to the folded state, hold the armrest and Fig. 9 Rotate the upper second wing arm and the lower second wing arm in the clockwise direction to turn the drone into the folded state. The opening and closing operation is opposite to the above and will not be described in detail.

[0043] The principle of the present invention is:

[0044] The UAV of the present invention adopts an upper and lower arm design, which improves the load-bearing capacity of the UAV, and in terms of structural design, the propeller on the upper arm 14 is set downward, and the propeller on the lower arm 15 is set upward, which makes the thrust surfaces of the upper and lower arms basically in the same plane, which helps to improve the stability of the aircraft while effectively improving the load-bearing capacity of the aircraft. In addition, the downward setting of the propeller of the upper arm 14 also makes the propeller less interfered by the wing arm, so that the efficiency of the upper propeller 143 is higher, which also helps to improve the load-bearing capacity of the aircraft. In addition, it should be noted that for the lower propeller 153, the downward installation method cannot be adopted. On the one hand, the downward installation makes the thrust surface height of the aircraft differ greatly, which affects the flight stability and also affects the load-bearing capacity. In addition, the downward installation is too close to the ground. If the aircraft tilts, there is a greater safety hazard.

[0045] In addition, the structural design of the frame 1 of the present invention also makes the structure of the drone of the present invention more stable, and at the same time improves the stress condition of the frame, which plays a positive role in improving the load-bearing capacity of the drone; in the present invention, the two ends of the first bracket rod 16 are fixedly connected to improve the stability of the frame 1, and at the same time, the two ends of the second bracket rod 17 are hinged to effectively eliminate radial forces, so that the force is transmitted along the axial direction of the second bracket rod 17, thereby improving the stress condition of the frame 1, making the frame more stable, and providing a strong guarantee for improving the load-bearing capacity.

[0046] Example 1

[0047] The drone of this embodiment is made of carbon fiber + aviation aluminum alloy as a whole. For example, the tripod and the support rod are made of aviation aluminum alloy, and the propeller and the wing arm are made of carbon fiber, so that the drone of the present invention has a lighter weight and higher structural strength.

[0048] The drone of this embodiment is a 6-rotor drone, with three rotors on the upper and lower arms. In the horizontal plane projection, the upper arms and the lower arms are evenly arranged with an interval of 60° between each other. The unfolded size of the drone of this embodiment is 3480×2010×1200 (mm), the folded size is 1600×1500×1200 (mm), and the wheelbase is 3350mm (the wheelbase is the distance between two symmetrical propeller motors).

[0049] The drone propeller of this embodiment uses a 63-inch carbon fiber folding propeller; adopts a high-efficiency FOC power system, and uses 6 18S 36000mAh power batteries, and is equipped with an intelligent super-fast charger; adopts a GPS+RTK positioning system, and the remote control uses a 7-inch industrial touch screen + eye-viewing screen, with a remote control distance of 5-20km; the protection level is IP45.

[0050] The overall weight of the drone of this embodiment is only 43kg (excluding the weight of the power battery). According to actual measurements, the maximum load of the drone of this embodiment is 100kg, the maximum take-off weight is 210kg, the maximum flight speed is 15m / s, the maximum ascent speed is 5m / s, the maximum descent speed is 4m / s, the maximum take-off altitude is 4000m, the safe wind speed is ≤ level 7, and the operating temperature is -20 to 50°C.

[0051] The UAV of this embodiment has a flight time of 78 minutes when it is unloaded; 26 minutes when it is fully loaded; and 41 minutes when it is loaded with 50 kg.

[0052] The drone of the present invention is proposed for the first time, filling the gap in the field of multi-rotor drones with large load capacity; the drone of the present invention adopts the design concept and process of a woven frame, and the double-layer overlapping six-rotor structure optimizes the force conduction direction of the wing arm, and perfectly utilizes the characteristics of various materials to complement each other, so that a lighter and stronger body can be built with less material; the structural design of the drone of the present invention uses only 3kg of material to withstand an impact force of more than 500kg, which is an excellent load-bearing structural design. Its upper and lower staggered body and horizontal folding structure can achieve a smaller storage size; the core structure of the drone of the present invention uses aviation-grade aluminum alloy material; the appearance is EPP foam-filled and the fuselage is lightweight. The foam is both an outer shell and a structural support. The whole machine weighs only 43kg. The excellent weight performance of the whole machine creates a huge advantage of long endurance. The drone of the present invention is a flying platform with both load-bearing and endurance advantages, and can be used in various scenarios such as emergency rescue and transportation and supply, fire fighting, etc.

[0053] The present invention is not limited to the above-mentioned optimal implementation mode. Anyone can derive other various forms of products under the inspiration of the present invention. However, no matter what changes are made in the shape or structure, all technical solutions that are the same or similar to those of the present application fall within the protection scope of the present invention.

Claims

1. A multi-rotor load-carrying UAV, comprising a frame (1), a cabin (2) and a tripod (3), wherein a battery is installed in the cabin (2), and characterized in that: The cabin (2) and the tripod (3) are respectively fixedly connected to the frame (1); The frame (1) comprises a first connecting member (11) and a second connecting member (12) arranged in an upper and lower manner, the first connecting member (11) and the second connecting member (12) are fixedly connected, an upper machine arm (14) is fixedly connected via the first connecting member (11), and a lower machine arm (15) is fixedly connected via the second connecting member (12); The upper machine arm (14) is connected to the lower machine arm (15) via a first support rod (16), and the two ends of the first support rod (16) are respectively fixedly connected to the upper machine arm (14) and the lower machine arm (15); the lower machine arm (15) is connected to the first connecting member (11) via a second support rod (17), and the two ends of the second support rod (17) are respectively hinged to the lower machine arm (15) and the first connecting member (11); The wing arms of the upper machine arm (14) and the lower machine arm (15) are both provided with two sections, namely the first wing arm and the second wing arm, and the first wing arm and the second wing arm of the upper and lower layers are both connected by a connecting assembly (4) so ​​as to be foldable and non-detachable; The upper second wing arm (142) is connected to the upper propeller (143), the lower second wing arm (152) is connected to the lower propeller (153), the upper propeller (143) is set downward, and the lower propeller (153) is set upward.

2. A multi-rotor load-carrying UAV according to claim 1, characterized in that: The number of the upper machine arms (14) and the number of the lower machine arms (15) are both three. In the horizontal plane orthographic projection, the upper machine arms (14) and the lower machine arms (15) are evenly arranged at an interval of 60 degrees from each other.

3. A multi-rotor load-carrying UAV according to claim 2, characterized in that: Each of the upper machine arms (14) is connected to two lower machine arms (15) via two first support rods (16), and each of the lower machine arms (15) is connected to a first connecting member (11) via a second support rod (17).

4. The multi-rotor load-carrying UAV according to claim 2, characterized in that: The tripod (3) is simultaneously fixedly connected to the bottom of the connecting assembly (4) on each lower machine arm (15).

5. A multi-rotor load-carrying UAV according to claim 4, characterized in that: The connecting component (4) comprises a first component (41), a second component (42) and a locking member (43); one end of the first component (41) is fixedly connected to one end of the first wing arm, and one end of the second component (42) is fixedly connected to the second wing arm; the other end of the first component (41) and the other end of the second component (42) are hinged in the horizontal direction, and the locking member (43) is respectively connected to the first component (41) and the second component (42).

6. A multi-rotor load-carrying UAV according to claim 5, characterized in that: The locking member (43) comprises an armrest end (431), a hinged end (432) and a connecting rod (433), wherein the hinged end (432) is hinged to the first component (41), and the two ends of the connecting rod (433) are respectively hinged to the second component (42) and the armrest end (431).

7. The multi-rotor load-carrying UAV according to claim 5, characterized in that: The two ends of the first support rod (16) are respectively fixedly connected to the first component (41) in the upper and lower layer connection components (4), and the second support rod (17) is hinged to the lower layer machine arm (15) at the first component (41) in the lower layer connection component (4).

8. The multi-rotor load-carrying UAV according to claim 7, characterized in that: The cabin (2) is fixedly installed in a space area surrounded by a first support rod (16) and a second support rod (17).

9. The multi-rotor load-carrying UAV according to claim 1, characterized in that: The lower part of the second connecting member (12) is fixedly connected to the quick-release connector (121).

10. A multi-rotor load-carrying UAV according to any one of claims 1 to 9, characterized in that: The payload of the UAV can reach 100kg.

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