A non-load-bearing fuselage structure for an unmanned helicopter

Abstract

The present invention specifically discloses a non-load-bearing fuselage structure of an unmanned helicopter, including: an upper main beam, including a first upper main beam and a second upper main beam arranged at intervals, and an upper bulkhead fixedly connected to the first upper main beam and the second upper main beam; a lower main beam, including a first lower main beam and a second lower main beam arranged at intervals, and a lower bulkhead fixedly connected to the first lower main beam and the second lower main beam; a connecting beam, including a first connecting beam fixedly connected to the first upper main beam and the first lower main beam, and a second connecting beam fixedly connected to the second upper main beam and the second lower main beam; an engine fixing frame, which is fixedly connected to the first lower main beam and the second lower main beam respectively. The overall strength of the upper main beam and the lower main beam can be significantly enhanced by arranging the upper bulkhead and the lower bulkhead, and the upper main beam and the lower main beam are integrated by the connecting beam to form a non-load-bearing fuselage structure, and the engine is fixed to the lower main beam by the engine fixing frame, which simplifies the design and assembly process of the fuselage structure and facilitates disassembly, assembly and maintenance.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned helicopters, and in particular to a non-load-bearing fuselage structure of an unmanned helicopter. Background Art

[0002] The fuselage structure of traditional unmanned helicopters is mainly based on a load-bearing fuselage structure, which follows the design method of the side panel of the casing. There is no separate frame structure that bears external forces. The structural components that bear external forces are integrated with the side panel of the casing, and the engine, transmission system and other mechanical structures can be directly installed on this part. This fuselage structure has narrow space, is difficult to disassemble and assemble, has low strength, limited load-bearing capacity, is not resistant to falling, and cannot provide good protection for airborne equipment, especially when equipped with a high-power engine, the vibration is large, and it is not suitable for flight work.

[0003] The fuselage structure of the unmanned helicopter in the prior art, such as the prior patent with application number 201710264448.8, discloses a hollow arched truss fuselage structure of an unmanned helicopter. Although it solves the problem that the fuselage structure of the traditional unmanned helicopter does not have a separate frame structure to withstand external forces to a certain extent, it still has many shortcomings. The fuselage structure of the unmanned helicopter is complex in design, the spatial layout is not reasonable, and the strength is still relatively insufficient. Especially when the interior of the unmanned helicopter needs to be repaired, this structural design also makes disassembly and assembly extremely difficult, which is not conducive to the maintenance of the unmanned helicopter.

[0004] Therefore, there is an urgent need for a non-load-bearing fuselage structure of an unmanned helicopter to solve the above problems. Summary of the invention

[0005] The purpose of the present invention is to provide a non-load-bearing fuselage structure for an unmanned helicopter, so as to solve the problems in the prior art that the non-load-bearing fuselage structure for an unmanned helicopter is complex in structural design and has an unreasonable spatial layout, and that the fuselage structure is difficult to disassemble and assemble, which is not conducive to the maintenance of the unmanned helicopter, especially when the interior of the unmanned helicopter needs maintenance.

[0006] The present invention provides a non-load-bearing fuselage structure of an unmanned helicopter, and the non-load-bearing fuselage structure of an unmanned helicopter comprises:

[0007] An upper main beam, comprising a first upper main beam and a second upper main beam which are arranged at intervals and both extend along a first direction, and an upper bulkhead having two ends respectively fixed to the first upper main beam and the second upper main beam, wherein a plurality of the upper bulkheads are arranged at intervals along the first direction;

[0008] A lower main beam, comprising a first lower main beam and a second lower main beam which are arranged at intervals and both extend along the first direction, and a lower bulkhead having two ends respectively fixed to the first lower main beam and the second lower main beam, wherein a plurality of the lower bulkheads are arranged at intervals along the first direction;

[0009] A connecting beam, comprising a plurality of first connecting beams and a plurality of second connecting beams, wherein both ends of the plurality of first connecting beams are respectively fixedly connected to the first upper main beam and the first lower main beam, and both ends of the plurality of second connecting beams are respectively fixedly connected to the second upper main beam and the second lower main beam;

[0010] The engine fixing frame has two sides respectively fixedly connected to the first lower main beam and the second lower main beam.

[0011] Preferably, the non-load-bearing fuselage structure of the unmanned helicopter also includes two reduction gearbox support frames for installing a reducer, the two reduction gearbox support frames are spaced apart along the extension direction of the first lower main beam, the two reduction gearbox support frames are respectively fixedly connected to the first upper main beam and the second upper main beam, and the two ends of the reducer are respectively installed on the two reduction gearbox support frames.

[0012] Preferably, the non-load-bearing fuselage structure of the unmanned helicopter further comprises a first frame plate, the two ends of the first frame plate are respectively fixedly connected to the two reduction box support frames, the reduction box is transmission-connected to one end of the bottom of the main shaft of the unmanned helicopter and is used to drive the main shaft to rotate, the main shaft passes through the first frame plate, a rotor head is installed at one end of the top of the main shaft, the rotor head is used to fix the rotor, and a parachute bag is installed on the rotor head;

[0013] A pressure bearing and a stop member are sleeved on the main shaft, the stop member is fixedly connected to the main shaft, the pressure bearing comprises an upper plate, a lower plate and a plurality of balls located between the upper plate and the lower plate, the upper plate is fixedly connected to the stop member, and the lower plate is fixedly connected to the first frame plate.

[0014] Preferably, the non-load-bearing fuselage structure of the unmanned helicopter further includes a tail tube support frame, the tail tube support frame is fixedly connected to the first upper main beam and the second upper main beam at the same time, and a first through hole is provided on the tail tube support frame.

[0015] Preferably, the two reduction gearbox support frames are spaced apart along the first direction, and the reduction gearbox support frame is provided with a fixing hole for being sleeved on the reduction gearbox, and the fixing hole and the first through hole are coaxially arranged.

[0016] Preferably, the non-load-bearing fuselage structure of the unmanned helicopter also includes end plates, which are respectively fixed to the first upper main beam, the second upper main beam, the first lower main beam and the second lower main beam, the end plates and the connecting beam are respectively located on both sides of the engine fixing frame, and the end plates and the reduction gearbox support frame are respectively located on both sides of the tail pipe support frame.

[0017] Preferably, a second through hole is provided on the end plate, and the second through hole is coaxially arranged with the first through hole.

[0018] Preferably, the non-load-bearing fuselage structure of the unmanned helicopter also includes a first end beam and a second end beam, wherein the two ends of the first end beam are respectively fixedly connected to the first upper main beam and the first lower main beam, and the second end beam is respectively fixedly connected to the second upper main beam and the second lower main beam.

[0019] Preferably, the first end beam and the end plate are respectively fixedly connected to two ends of the first lower main beam, and the second end beam and the end plate are respectively fixedly connected to two ends of the second lower main beam.

[0020] Preferably, the engine mounting bracket is provided with a groove for fixing the engine, and the number of the groove is one or two.

[0021] Preferably, the non-load-bearing fuselage structure of the unmanned helicopter also includes two reinforcing beams, the number of the first connecting beam and the number of the second connecting beams are both two, the two first connecting beams are respectively fixedly connected to the two ends of one of the reinforcing beams, and the two second connecting beams are respectively fixedly connected to the two ends of the other reinforcing beam.

[0022] The beneficial effects of the present invention are:

[0023] By providing multiple upper bulkheads and multiple lower bulkheads, the overall strength of the upper main beam and the lower main beam can be significantly enhanced; the upper main beam and the lower main beam are integrated into one by connecting the beam to form a non-load-bearing fuselage structure, and by fixing an engine fixing bracket for fixing the engine on the lower main beam, the design and assembly process of the fuselage structure are simplified. Especially when the interior of the unmanned helicopter needs to be repaired, this structural design greatly simplifies the difficulty of disassembly and assembly, which is conducive to the maintenance of the unmanned helicopter. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 The structure of the non-load-bearing fuselage structure of the unmanned helicopter in the embodiment of the present invention is schematically shown. Figure 1 ;

[0025] Figure 2 The structure of the non-load-bearing fuselage structure of the unmanned helicopter in the embodiment of the present invention is schematically shown. Figure 2 .

[0026] In the figure:

[0027] 1. Upper main beam; 11. First upper main beam; 12. Second upper main beam; 13. Upper partition frame;

[0028] 2. Lower main beam; 21. First lower main beam; 22. Second lower main beam; 23. Lower bulkhead;

[0029] 3. Connecting beam; 31. First connecting beam; 32. Second connecting beam;

[0030] 4. Engine mounting bracket; 41. Groove;

[0031] 5. Reducer box support frame; 51. Fixing hole;

[0032] 6. Tail pipe support frame; 61. First through hole;

[0033] 7. end plate; 71. second through hole

[0034] 81. first end beam; 82. second end beam;

[0035] 91. Strengthening beam; 92. Second frame plate;

[0036] 101. Reducer; 102. First frame plate; 103. Main shaft; 104. Stop member; 105. Pressure bearing; 106. Rotor head; 107. Parachute bag. DETAILED DESCRIPTION

[0037] The technical solution of the present invention is further described below with reference to the accompanying drawings and through specific implementation methods.

[0038] like Figure 1 and Figure 2As shown, this embodiment provides a non-load-bearing fuselage structure of an unmanned helicopter, which includes an upper main beam 1, a lower main beam 2, a connecting beam 3 and an engine mounting bracket 4. The upper main beam 1 includes a first upper main beam 11, a second upper main beam 12 and a plurality of upper bulkheads 13. The first upper main beam 11 and the second upper main beam 12 are spaced apart and arranged in parallel, and the first upper main beam 11 and the second upper main beam 12 both extend along a first direction. The plurality of upper bulkheads 13 are fixedly connected to the first upper main beam 11 at one end and to the second upper main beam 12 at the other end, and the plurality of upper bulkheads 13 are spaced apart along the first direction. The lower main beam 2 includes a first lower main beam 21, a second lower main beam 22 and a plurality of lower bulkheads 23. The first lower main beam 21 and the second lower main beam 22 are arranged in parallel and spaced apart from each other, and both extend along a first direction. The plurality of lower bulkheads 23 are fixedly connected to the first lower main beam 21 at one end and to the second lower main beam 22 at the other end, and the plurality of lower bulkheads 23 are spaced apart from each other along the first direction. In this embodiment, the lower main beam 2 is located directly below the upper main beam 1, and the first lower main beam 21 and the second lower main beam 22 are respectively located at the four vertices of a rectangle with the first lower main beam 21 and the second lower main beam 22. The connecting beam 3 includes a first connecting beam 31 and a second connecting beam 32. Both ends of the first connecting beams 31 are respectively fixedly connected to the first upper main beam 11 and the first lower main beam 21, and both ends of the second connecting beams 32 are respectively fixedly connected to the second upper main beam 12 and the second lower main beam 22. The first connecting beams 31 and the second connecting beams 32 are arranged at intervals along the first direction. In this embodiment, the number of the first connecting beams 31 and the second connecting beams 32 is two, and the two first connecting beams 31 are arranged oppositely and tilted, and the two second connecting beams 32 are arranged oppositely and tilted, that is, the two first connecting beams 31 and the first upper main beam 11 and the first lower main beam 21 form a trapezoidal structure, and the two second connecting beams 32 and the second upper main beam 12 and the second lower main beam 22 form a trapezoidal structure. The engine mounting bracket 4 is used to fix the engine and the engine mounting bracket 4 is respectively fixedly connected to the first lower main beam 21 and the second lower main beam 22. The engine is connected to the reducer 101 in a transmission manner. Specifically, the engine mounting bracket 4 is provided with grooves 41 for fixing the engine, and each groove 41 can be used to fix one engine. In this embodiment, the number of grooves 41 is two, so that two engines can be fixed. In other embodiments, the number of grooves 41 can also be one. In this embodiment, the overall strength of the upper main beam 1 and the lower main beam 2 can be significantly enhanced by providing a plurality of upper bulkheads 13 and a plurality of lower bulkheads 23; the upper main beam 1 and the lower main beam 2 are integrated into one by the connecting beam 3 to form a non-load-bearing fuselage structure, and the engine mounting bracket 4 for fixing the engine is fixed on the lower main beam 2, which simplifies the design and assembly process of the fuselage structure. In particular, when the interior of the unmanned helicopter needs to be repaired, this structural design greatly simplifies the difficulty of disassembly and assembly, which is conducive to the maintenance of the unmanned helicopter.

[0039] The unmanned helicopter non-load-bearing fuselage structure also includes a reduction box support frame 5 and a tail pipe support frame 6. The reduction box support frame 5 is respectively fixed to the first upper main beam 11 and the second upper main beam 12. In this embodiment, two reduction box support frames 5 are provided. The two reduction box support frames 5 are spaced apart along the first direction. The reduction box support frame 5 is provided with fixing holes 51 for being sleeved on the reduction box. The two fixing holes 51 can be sleeved on both ends of the reduction box and the reduction box can be fixed. The engine and the reduction box 101 are connected in transmission. The tail pipe support frame 6 is respectively fixed to the first upper main beam 11 and the second upper main beam 12. The tail pipe support frame 6 is provided with a first through hole 61. The first through hole 61 is used to fix the tail pipe structure. The transmission mechanism of the helicopter tail rotor can be wrapped and fixed by the tail pipe structure. Preferably, the fixing hole 51 and the first through hole 61 are coaxially arranged.

[0040] The unmanned helicopter non-load-bearing fuselage structure also includes a first frame plate 102, the two ends of the first frame plate 102 are respectively fixed to the two reduction box support frames 5, the reducer 101 is connected to one end of the bottom of the main shaft 103 of the unmanned helicopter and is used to drive the main shaft 103 to rotate, the main shaft 103 passes through the first frame plate 102, and a rotor head 106 is installed at one end of the top of the main shaft 103, the rotor head 106 is used to fix the rotor, and a parachute bag 107 is installed on the rotor head 106. The main shaft 103 is sleeved with a pressure bearing 105 and a stopper 104, the stopper 104 is fixed to the main shaft 103, the pressure bearing 105 includes an upper piece, a lower piece and a plurality of balls located between the upper piece and the lower piece, the plurality of balls are installed on a retainer, and the retainer is located between the upper piece and the lower piece, wherein the upper piece is fixed to the stopper 104, and the lower piece is fixed to the first frame plate 102. When the main shaft 103 rotates, the main shaft 103 drives the stopper 104 and the upper plate to rotate synchronously, while the lower plate and the first frame plate 102 remain stationary. By adopting the pressure bearing 105, the axial force on the main shaft 103 can be better borne.

[0041] When the drone opens the parachute, the rotor head is subjected to a huge downward impact force, which is transmitted to the main shaft 103 and transmitted downward along the axis of the main shaft 103. The stopper 104 and the main shaft 103 are always locked. The stopper 104 connects the main shaft 103 and the pressure bearing 105 as a whole. The axial force generated by the opening of the parachute is further transmitted to the first frame 102 through the stopper 104 and the pressure bearing 105, and then transmitted to the first upper main beam 11 and the second upper main beam 12 through the reduction box support frame 5. Therefore, through this series of force transmission, the impact force when the drone opens the parachute ultimately acts on the main beam of the fuselage, which is the strongest main load-bearing beam. In this way, other relatively "thin" components do not bear or bear very little impact force when the parachute is opened, ensuring that various structures inside the fuselage of the drone are not damaged at the moment of opening the parachute.

[0042] The unmanned helicopter non-load-bearing fuselage structure also includes an end plate 7, a first end beam 81 and a second end beam 82. The end plate 7 is respectively fixed to the first upper main beam 11, the second upper main beam 12, the first lower main beam 21 and the second lower main beam 22. The end plate 7 and the connecting beam 3 are respectively located on both sides of the engine fixing frame 4, and the end plate 7 and the reduction box support frame 5 are respectively located on both sides of the tail pipe support frame 6. The end plate 7 is provided with a second through hole 71, which is coaxially arranged with the first through hole 61, and the second through hole 71 is also used to fix the tail pipe structure. The two ends of the first end beam 81 are respectively fixed to the first upper main beam 11 and the first lower main beam 21, and the second end beam 82 is respectively fixed to the second upper main beam 12 and the second lower main beam 22. Specifically, the first end beam 81 and the second end beam 82 are both arc-shaped, and one end of the first end beam 81 is tangent to the first upper main beam 11, and the other end is perpendicular to the first lower main beam 21, and one end of the second end beam 82 is tangent to the second upper main beam 12, and the other end is perpendicular to the second lower main beam 22. In this embodiment, the first end beam 81 and the end plate 7 are respectively fixed to the two ends of the first lower main beam 21, and the second end beam 82 and the end plate 7 are respectively fixed to the two ends of the second lower main beam 22. Preferably, weight-reducing holes for reducing weight are provided on the end plate 7, the first end beam 81, and the second end beam 82.

[0043] The unmanned helicopter non-load-bearing fuselage structure further includes two reinforcing beams 91, the number of the first connecting beam 31 and the number of the second connecting beam 32 are both two, the two first connecting beams 31 are respectively fixedly connected to the two ends of one of the reinforcing beams 91, and the two second connecting beams 32 are respectively fixedly connected to the two ends of the other reinforcing beam 91. Preferably, the reinforcing beam 91 is provided with a weight-reducing hole for reducing weight, and a second frame plate 92 is fixedly connected between the two reinforcing beams 91, and the second frame plate 92 is used to support the main gear installed on the main shaft of the rotor mechanism, and can also be used to install other components of the unmanned helicopter.

[0044] In this embodiment, the two first connecting beams 31, the reinforcing beam 91, the first upper main beam 11, the first lower main beam 21 and the first end beam 81 are integrated as a whole, and together constitute the first main support structure. They can be milled from a whole plate and have strong strength. Similarly, the two second connecting beams 32, the reinforcing beam 91, the first lower main beam 21, the second lower main beam 22 and the second end beam 81 are integrated as a whole, and together constitute the second main support structure.

[0045] The unmanned helicopter non-load-bearing fuselage structure in this embodiment has a fuselage assembly process as follows:

[0046] 1) Connect the first main support structure and the second main support structure together through multiple bulkheads. Specifically, the two ends of the upper bulkhead 13 are respectively connected to the first upper main beam 11 and the second upper main beam 12 by bolts, and the two ends of the lower bulkhead 23 are respectively connected to the first lower main beam 21 and the second lower main beam 22 by bolts.

[0047] 2) Both ends of the second frame plate 92 are connected to the two reinforcing beams 91 by bolts.

[0048] 3) Both ends of the engine mounting bracket 4 are connected to the first lower main beam 21 and the second lower main beam 22 by bolts respectively.

[0049] 4) Two reduction gearbox support frames 5 and two tail pipe support frames 6 are sequentially installed between the first upper main beam 11 and the second upper main beam 12. Specifically, the two ends of the reduction gearbox support frame 5 are respectively connected to the first upper main beam 11 and the second upper main beam 12 by bolts; the two ends of the tail pipe support frame 6 are respectively connected to the first upper main beam 11 and the second upper main beam 12 by bolts.

[0050] 5) An end plate 7 is installed at the ends of the first upper main beam 11, the second upper main beam 12, the first lower main beam 21 and the second lower main beam 22, and the four corners of the end plate 7 are connected to the ends of the first upper main beam 11, the second upper main beam 12, the first lower main beam 21 and the second lower main beam 22 by bolts respectively.

[0051] The non-load-bearing fuselage structure of the unmanned helicopter directly supports a series of major components such as the engine, reduction gearbox, and tail pipe structure. It can withstand the internal and external forces generated when the aircraft is flying, and can also withstand the huge impact force at the moment of parachute opening. It has high strength, good space, and strong carrying capacity, and can provide good protection for airborne equipment. The components are connected by bolts for easy disassembly and assembly. It can also carry high-power engines or dual engines, which is suitable for unmanned helicopters to fly in harsh environments.

[0052] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the embodiments here. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. A non-load-bearing fuselage structure of an unmanned helicopter, characterized in that: include: An upper main beam (1) comprising a first upper main beam (11) and a second upper main beam (12) which are arranged at intervals and extend along a first direction, and an upper bulkhead (13) whose two ends are respectively connected to the first upper main beam (11) and the second upper main beam (12) by bolts, wherein a plurality of the upper bulkheads (13) are arranged at intervals along the first direction; A lower main beam (2) comprising a first lower main beam (21) and a second lower main beam (22) which are arranged at intervals and both extend along the first direction, and a lower bulkhead (23) whose two ends are respectively connected to the first lower main beam (21) and the second lower main beam (22) by bolts, wherein a plurality of the lower bulkheads (23) are arranged at intervals along the first direction; A connecting beam (3), comprising a plurality of first connecting beams (31) and a plurality of second connecting beams (32), wherein both ends of the plurality of first connecting beams (31) are respectively fixedly connected to the first upper main beam (11) and the first lower main beam (21), and both ends of the plurality of second connecting beams (32) are respectively fixedly connected to the second upper main beam (12) and the second lower main beam (22); An engine fixing frame (4), two ends of which are respectively connected to the first lower main beam (21) and the second lower main beam (22) by bolts; There are two reduction gearbox support frames (5), the two reduction gearbox support frames (5) are arranged at intervals along the extension direction of the first lower main beam (21), the two reduction gearbox support frames (5) are respectively connected to the first upper main beam (11) and the second upper main beam (12) by bolts, and the two ends of the reducer (101) are respectively mounted on the two reduction gearbox support frames (5); a first frame plate (102), wherein both ends of the first frame plate (102) are respectively fixedly connected to the two reduction box support frames (5); the reduction box (101) is drivingly connected to one end of the bottom of the main shaft (103) of the unmanned helicopter and is used to drive the main shaft (103) to rotate; the main shaft (103) passes through the first frame plate (102); a rotor head (106) is installed at one end of the top of the main shaft (103); the rotor head (106) is used to fix the rotor; and a parachute bag (107) is installed on the rotor head (106); a pressure bearing (105) and a stopper (104) are sleeved on the main shaft (103); the stopper (104) and the main shaft (103) are fixedly connected; the pressure bearing (105) comprises an upper plate, a lower plate and a plurality of balls located between the upper plate and the lower plate; the upper plate and the stopper (104) are fixedly connected; and the lower plate and the first frame plate (102) are fixedly connected; a tail pipe support frame (6), the tail pipe support frame (6) being fixedly connected to the first upper main beam (11) and the second upper main beam (12), and the tail pipe support frame (6) being provided with a first through hole (61); an end plate (7) connected to the first upper main beam (11), the second upper main beam (12), the first lower main beam (21), and the second lower main beam (22) respectively by bolts; the end plate (7) and the connecting beam (3) are respectively located on both sides of the engine fixing frame (4); and the end plate (7) and the reduction box support frame (5) are respectively located on both sides of the tail pipe support frame (6); A first end beam (81) and a second end beam (82), wherein two ends of the first end beam (81) are respectively fixedly connected to the first upper main beam (11) and the first lower main beam (21), and the second end beam (82) is respectively fixedly connected to the second upper main beam (12) and the second lower main beam (22), the first end beam (81) and the end plate (7) are respectively fixedly connected to two ends of the first lower main beam (21), and the second end beam (82) and the end plate (7) are respectively fixedly connected to two ends of the second lower main beam (22).

2. The unmanned helicopter non-load bearing fuselage structure according to claim 1 is characterized in that: The two reduction box support frames (5) are spaced apart along the first direction, and the reduction box support frame (5) is provided with a fixing hole (51) for being sleeved on the reduction box, and the fixing hole (51) and the first through hole (61) are coaxially arranged.

3. The unmanned helicopter non-load bearing fuselage structure according to claim 2 is characterized in that: The end plate (7) is provided with a second through hole (71), and the second through hole (71) is coaxially arranged with the first through hole (61).

4. The unmanned helicopter non-load bearing fuselage structure according to claim 1, characterized in that: The engine fixing frame (4) is provided with a groove (41) for fixing the engine, and the number of the groove (41) is one or two.

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