CN209739314U - Unmanned helicopter non-bearing type fuselage structure - Google Patents
Unmanned helicopter non-bearing type fuselage structure Download PDFInfo
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- CN209739314U CN209739314U CN201920444493.6U CN201920444493U CN209739314U CN 209739314 U CN209739314 U CN 209739314U CN 201920444493 U CN201920444493 U CN 201920444493U CN 209739314 U CN209739314 U CN 209739314U
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Abstract
The utility model particularly discloses an unmanned helicopter non-bears formula fuselage structure, include: the upper main beam comprises a first upper main beam and a second upper main beam which are arranged at intervals, and an upper partition frame fixedly connected with the first upper main beam and the second upper main beam; the lower main beam comprises a first lower main beam and a second lower main beam which are arranged at intervals, and a lower bulkhead fixedly connected with the first lower main beam and the second lower main beam; the connecting beam comprises a first connecting beam fixedly connected with a first upper main beam and a first lower main beam, and a second connecting beam fixedly connected with a second upper main beam and a second lower main beam; and the engine fixing frame is fixedly connected with the first lower main beam and the second lower main beam respectively. The upper separation frame and the lower separation frame are arranged to obviously enhance the overall strength of the upper main beam and the lower main beam, the upper main beam and the lower main beam are integrated through the connecting beam to form a non-bearing type machine body structure, the engine is fixed on the lower main beam through the engine fixing frame, the design and the assembly process of the machine body structure are simplified, and the disassembly, assembly and maintenance are convenient.
Description
Technical Field
the utility model relates to an unmanned helicopter technical field especially relates to an unmanned helicopter non-bears formula fuselage structure.
Background
The traditional unmanned helicopter mainly uses a bearing type helicopter body structure as a main part, follows the design method of the stress of a side plate of a shell, does not have an independent frame structure bearing external force, and a structural part bearing the external force and the side plate part of the shell are integrated into a whole and can be directly provided with mechanical structures such as an engine, a transmission system and the like. The aircraft body has narrow structural space, troublesome disassembly and assembly, low strength, limited bearing capacity, no falling resistance, no good protection for airborne equipment, large vibration especially when carrying a high-power engine and no suitability for flying work.
Unmanned helicopter cavity arch truss fuselage structure among the prior art, disclosed an unmanned helicopter in the prior patent of application number 201710264448.8, though solved the problem that traditional unmanned helicopter's fuselage structure does not have the solitary rack construction who bears external force to a certain extent, but still there is more not enough, this unmanned helicopter's fuselage structural design is complicated, spatial layout is reasonable inadequately, and intensity is still comparatively less than the scheduling problem, especially when the inside of unmanned helicopter needs the maintenance, this kind of structural design has also led to the fact very big degree of difficulty for the dismouting, be unfavorable for the maintenance of unmanned helicopter.
therefore, there is a need for a non-load-bearing fuselage structure of an unmanned helicopter to solve the above problems.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a: the utility model provides a non-formula fuselage structure that bears of unmanned helicopter to solve among the prior art that the structural design of non-formula fuselage structure that bears of unmanned helicopter is complicated, spatial layout is not reasonable enough, especially when the inside of unmanned helicopter need be maintained, fuselage structure dismouting difficulty is unfavorable for the problem of unmanned helicopter maintenance.
The utility model provides an unmanned helicopter non-bears formula fuselage structure, this unmanned helicopter non-bears formula fuselage structure includes:
The upper main beam comprises a first upper main beam and a second upper main beam which are arranged at intervals and extend along a first direction, and upper partition frames of which two ends are fixedly connected with the first upper main beam and the second upper main beam respectively, wherein the upper partition frames are arranged at intervals along the first direction;
The lower main beam comprises a first lower main beam and a second lower main beam which are arranged at intervals and extend along the first direction, and lower partition frames of which two ends are fixedly connected with the first lower main beam and the second lower main beam respectively, wherein the lower partition frames are arranged at intervals along the first direction;
the connecting beams comprise a plurality of first connecting beams and a plurality of second connecting beams, two ends of the first connecting beams are fixedly connected with the first upper main beam and the first lower main beam respectively, and two ends of the second connecting beams are fixedly connected with the second upper main beam and the second lower main beam respectively;
And two sides of the engine fixing frame are fixedly connected with the first lower main beam and the second lower main beam respectively.
Preferably, the unmanned helicopter non-bearing fuselage structure further comprises two reduction gearbox support frames for mounting a speed reducer, the two reduction gearbox support frames are arranged at intervals along the extending direction of the first lower main beam, the two reduction gearbox support frames are fixedly connected with the first upper main beam and the second upper main beam respectively, and two ends of the speed reducer are mounted on the two reduction gearbox support frames respectively.
Preferably, the unmanned helicopter non-bearing fuselage structure further comprises a first frame plate, two ends of the first frame plate are fixedly connected with the two reduction gearbox supporting frames respectively, the speed reducer is in transmission connection with one end of the bottom of a main shaft of the unmanned helicopter and is used for driving the main shaft to rotate, the main shaft penetrates through the first frame plate, a rotor head is mounted at one end of the top of the main shaft and is used for fixing a rotor wing, and an umbrella bag is mounted on the rotor head;
The utility model discloses a bearing, including main shaft, pressure bearing, end position piece, pressure bearing, lower piece, first frame plate rigid coupling, the cover is equipped with pressure bearing and ends the position piece on the main shaft, end the position piece with the main shaft rigid coupling, pressure bearing includes the piece, down the piece and is located the piece with a plurality of balls between the piece down, the piece with end position piece rigid coupling, down the piece with first frame plate rigid coupling.
Preferably, the unmanned helicopter non-bearing fuselage structure further comprises a tail pipe support frame, the tail pipe support frame is fixedly connected with the first upper main beam and the second upper main beam at the same time, and the tail pipe support frame is provided with a first through hole.
Preferably, the two gearbox supporting frames are arranged at intervals along the first direction, fixing holes for being sleeved on the gearbox are formed in the gearbox supporting frames, and the fixing holes and the first through holes are arranged coaxially.
Preferably, the unmanned helicopter non-bearing fuselage structure further comprises end plates, the end plates are fixedly connected with the first upper main beam, the second upper main beam, the first lower main beam and the second lower main beam respectively, the end plates and the connecting beams are located on two sides of the engine fixing frame respectively, and the end plates and the reduction gearbox supporting frames are located on two sides of the tail pipe supporting frame respectively.
preferably, a second through hole is formed in the end plate, and the second through hole and the first through hole are coaxially arranged.
Preferably, the unmanned helicopter non-bearing fuselage structure further comprises a first end beam and a second end beam, wherein two ends of the first end beam are fixedly connected with the first upper main beam and the first lower main beam respectively, and the second end beam is fixedly connected with the second upper main beam and the second lower main beam respectively.
Preferably, the first end beam and the end plate are respectively and fixedly connected to two ends of the first lower main beam, and the second end beam and the end plate are respectively and fixedly connected to two ends of the second lower main beam.
preferably, the engine fixing frame is provided with one or two grooves for fixing the engine.
Preferably, the unmanned helicopter non-load-bearing fuselage structure further comprises two reinforcing beams, the number of the first connecting beams and the number of the second connecting beams are two, the two first connecting beams are fixedly connected with two ends of one of the reinforcing beams respectively, and the two second connecting beams are fixedly connected with two ends of the other reinforcing beam respectively.
The utility model has the advantages that:
The integral strength of the upper main beam and the lower main beam can be obviously enhanced by arranging the plurality of upper partition frames and the plurality of lower partition frames; the upper main beam and the lower main beam form a whole through the connecting beam to form a non-bearing type fuselage structure, and the engine fixing frame used for fixing the engine is fixed on the lower main beam, so that the design and the assembly process of the fuselage structure are simplified, and particularly when the interior of the unmanned helicopter needs to be maintained, the structural design greatly simplifies the disassembly and assembly difficulty and is beneficial to the maintenance of the unmanned helicopter.
Drawings
fig. 1 is a first schematic structural diagram of a non-load-bearing fuselage structure of an unmanned helicopter according to an embodiment of the present invention;
Fig. 2 is a schematic structural diagram ii of the non-load-bearing fuselage structure of the unmanned helicopter in the embodiment of the present invention.
In the figure:
1. an upper main beam; 11. a first upper main beam; 12. a second upper main beam; 13. an upper spacer frame;
2. A lower main beam; 21. a first lower main beam; 22. a second lower main beam; 23. a lower bulkhead;
3. A connecting beam; 31. a first connecting beam; 32. a second connecting beam;
4. An engine mount; 41. a groove;
5. A reduction gearbox support frame; 51. a fixing hole;
6. A tail pipe support frame; 61. a first through hole;
7. An end plate; 71. second through hole
81. A first end beam; 82. a second end beam;
91. A reinforcing beam; 92. a second frame plate;
101. A speed reducer; 102. a first frame plate; 103. a main shaft; 104. a stop member; 105. a pressure bearing; 106. a rotor head; 107. an umbrella bag.
Detailed Description
the technical solution of the present invention is further explained by the following embodiments with reference to the accompanying drawings.
as shown in fig. 1 and fig. 2, the present embodiment provides a non-self-supporting fuselage structure of an unmanned helicopter, the non-self-supporting fuselage structure of an unmanned helicopter includes an upper main beam 1, a lower main beam 2, a connecting beam 3 and an engine fixing frame 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 arranged in parallel at intervals, and the first upper main beam 11 and the second upper main beam 12 both extend along a first direction, one end of each of the plurality of upper bulkheads 13 is fixedly connected to the first upper main beam 11, the other end of each of the plurality of upper bulkheads 13 is fixedly connected to the second upper main beam 12, and the plurality of upper bulkheads 13 are arranged at intervals along. The lower main beam 2 comprises a first lower main beam 21, a second lower main beam 22 and a plurality of lower separation frames 23, the first lower main beam 21 and the second lower main beam 22 are arranged in a spaced mode and in parallel, the first lower main beam 21 and the second lower main beam 22 extend along a first direction, one end of each of the plurality of lower separation frames 23 is fixedly connected with the first lower main beam 21, the other end of each of the plurality of lower separation frames 23 is fixedly connected with the second lower main beam 22, and the plurality of lower separation frames 23 are arranged along the first direction at intervals. In this embodiment, the lower main beams 2 are located right below the upper main beam 1, and the first and second lower main beams 21 and 22 are located at four vertices of a rectangle, respectively. The connecting beams 3 comprise first connecting beams 31 and second connecting beams 32, two ends of the first connecting beams 31 are fixedly connected with the first upper main beam 11 and the first lower main beam 21 respectively, and two ends of the second connecting beams 32 are fixedly connected with the second upper main beam 12 and the second lower main beam 22 respectively; the plurality of first connecting beams 31 and the plurality of 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 number of the second connecting beams 32 are two, the two first connecting beams 31 are arranged oppositely and obliquely, and the two second connecting beams 32 are arranged oppositely and obliquely, that is, the two first connecting beams 31, the first upper main beam 11 and the first lower main beam 21 form a trapezoidal structure, and the two second connecting beams 32, the second upper main beam 12 and the second lower main beam 22 form a trapezoidal structure. The engine fixing frame 4 is used for fixing the engine, and the engine fixing frame 4 is fixedly connected with the first lower main beam 21 and the second lower main beam 22 respectively. The engine is in transmission connection with the speed reducer 101. Specifically, the engine fixing frame 4 is provided with grooves 41 for fixing the engine, each groove 41 can be used for fixing one engine, and the number of the grooves 41 is two in the embodiment, so that the double engines can be fixed. In other embodiments, the number of grooves 41 may 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 the plurality of upper bulkheads 13 and the plurality of lower bulkheads 23; the upper main beam 1 and the lower main beam 2 form a whole through the connecting beam 3 to form a non-bearing type fuselage structure, and the engine fixing frame 4 for fixing an engine is fixed on the lower main beam 2, so that the design and the assembly process of the fuselage structure are simplified, and particularly when the interior of the unmanned helicopter needs to be maintained, the structural design greatly simplifies the disassembly and assembly difficulty and is beneficial to the maintenance of the unmanned helicopter.
the non-bearing fuselage structure of the unmanned helicopter further comprises a reduction gearbox supporting frame 5 and a tail pipe supporting frame 6. The reduction gearbox supporting frame 5 is fixedly connected with the first upper main beam 11 and the second upper main beam 12 respectively, two reduction gearbox supporting frames 5 are arranged in the embodiment, the two reduction gearbox supporting frames 5 are arranged at intervals along the first direction, fixing holes 51 used for being sleeved on the reduction gearbox are formed in the reduction gearbox supporting frames 5, the two ends of the reduction gearbox are sleeved with the two fixing holes 51 through the fixing holes, the reduction gearbox is fixed, and the engine is in transmission connection with the reduction gearbox 101. The tail pipe support frame 6 is fixedly connected with the first upper main beam 11 and the second upper main beam 12 respectively, a first through hole 61 is formed in the tail pipe support frame 6, the first through hole 61 is used for fixing a tail pipe structure, and a transmission mechanism of a tail rotor of the helicopter can be wrapped and fixed through the tail pipe structure. Preferably, the fixing hole 51 and the first through hole 61 are coaxially disposed.
The unmanned helicopter non-bearing fuselage structure further comprises a first frame plate 102, two ends of the first frame plate 102 are fixedly connected with the two reduction gearbox supporting frames 5 respectively, the speed reducer 101 is in transmission connection with one end of the bottom of a main shaft 103 of the unmanned helicopter and is used for driving the main shaft 103 to rotate, the main shaft 103 penetrates 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 for fixing a rotor, and an umbrella bag 107 is installed on the rotor head 106. The main shaft 103 is sleeved with a pressure bearing 105 and a stop part 104, the stop part 104 is fixedly connected with the main shaft 103, the pressure bearing 105 comprises an upper plate, a lower plate and a plurality of balls positioned between the upper plate and the lower plate, the plurality of balls are arranged on a retainer, the retainer is positioned between the upper plate and the lower plate, the upper plate is fixedly connected with the stop part 104, and the lower plate is fixedly connected with the first frame plate 102. When the main shaft 103 rotates, the main shaft 103 drives the stop member 104 and the upper plate to rotate synchronously, while the lower plate and the first frame plate 102 remain stationary. By using the pressure bearing 105, the axial force to which the main shaft 103 is subjected can be better received.
when the unmanned aerial vehicle is opened, the downward great impact force borne by the rotor head is transmitted to the main shaft 103 and transmitted downwards along the axial direction of the main shaft 103, the stop piece 104 and the main shaft 103 are always in a locking state, the main shaft 103 and the pressure bearing 105 are connected into a whole by the stop piece 104, the axial force generated by opening the unmanned aerial vehicle is further transmitted to the first frame plate 102 through the stop piece 104 and the pressure bearing 105, and then is transmitted to the first upper main beam 11 and the second upper main beam 12 through the reduction gearbox supporting frame 5. Therefore, through the transmission of the series of forces, the impact force when the unmanned aerial vehicle opens the umbrella is finally applied to the main beam with the firmest main bearing force of the body. Like this other spare part that comparatively "list is thin" does not bear or bear little impact force when the parachute-opening, guarantees that unmanned aerial vehicle is not destroyed at the inside various structures of fuselage in the moment of parachute-opening.
The non-bearing fuselage structure of the unmanned helicopter further comprises an end plate 7, a first end beam 81 and a second end beam 82, wherein the end plate 7 is fixedly connected with 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, the end plate 7 and the connecting beam 3 are located on two sides of the engine fixing frame 4 respectively, and the end plate 7 and the reduction gearbox supporting frame 5 are located on two sides of the tail pipe supporting frame 6 respectively. The end plate 7 is provided with a second through hole 71, the second through hole 71 is coaxially arranged with the first through hole 61, and the second through hole 71 is also used for fixing a tail pipe structure. The two ends of the first end beam 81 are fixedly connected with the first upper main beam 11 and the first lower main beam 21 respectively, the second end beam 82 is fixedly connected with the second upper main beam 12 and the second lower main beam 22 respectively, specifically, the first end beam 81 and the second end beam 82 are both arc-shaped, one end of the first end beam 81 is tangent to the first upper main beam 11, the other end of the first end beam 81 is perpendicular to the first lower main beam 21, one end of the second end beam 82 is tangent to the second upper main beam 12, and the other end of the second end beam is perpendicular to the second lower main beam 22. In this embodiment, the first end beam 81 and the end plate 7 are respectively and 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 and fixedly connected to two ends of the second lower main beam 22. Preferably, the end plate 7, the first end beam 81 and the second end beam 82 are provided with lightening holes for reducing weight.
the unmanned helicopter non-bearing fuselage structure further comprises two reinforcing beams 91, the number of the first connecting beams 31 and the number of the second connecting beams 32 are two, the two first connecting beams 31 are fixedly connected with two ends of one reinforcing beam 91 respectively, and the two second connecting beams 32 are fixedly connected with two ends of the other reinforcing beam 91 respectively. Preferably, the stiffening beams 91 are provided with lightening holes for reducing weight, a second frame plate 92 is fixedly connected between the two stiffening beams 91, and the second frame plate 92 is used for supporting a main gear installed on a main shaft of the rotor mechanism and can also be used for installing other parts of the unmanned helicopter.
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 to form a first main supporting structure. The whole plate can be milled to form the high-strength steel plate, and the high-strength steel plate has high 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 to form a second main supporting structure.
in the non-load-bearing fuselage structure of the unmanned helicopter in the embodiment, the assembly process of the fuselage part is as follows:
1) And connecting the first main supporting structure and the second main supporting structure together through a plurality of partition frames. Specifically, two ends of the upper bulkhead 13 are respectively connected with the first upper main beam 11 and the second upper main beam 12 through bolts, and two ends of the lower bulkhead 23 are respectively connected with the first lower main beam 21 and the second lower main beam 22 through bolts.
2) and the two ends of the second frame plate 92 are respectively connected with the two reinforcing beams 91 through bolts.
3) And two ends of the engine fixing frame 4 are respectively connected with the first lower main beam 21 and the second lower main beam 22 through bolts.
4) two reduction box support frames 5 and two tail pipe support frames 6 are sequentially arranged between the first upper main beam 11 and the second upper main beam 12. Specifically, two ends of the reduction gearbox supporting frame 5 are respectively connected with a first upper main beam 11 and a second upper main beam 12 through bolts; two ends of the tail pipe support frame 6 are respectively connected with the first upper main beam 11 and the second upper main beam 12 through bolts.
5) And end plates 7 are arranged 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 four corners of each end plate 7 are respectively connected with 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 through bolts.
The non-bearing type fuselage structure of the unmanned helicopter directly supports a series of main components such as an engine, a reduction gearbox, a tail pipe structure and the like, can bear internal force and external force generated when the airplane flies, can also bear huge impact force at the moment of parachute opening, has higher strength, good space and strong bearing capacity, and can provide good protection for airborne equipment; the parts are connected through bolts, so that the assembly and disassembly are convenient; the helicopter can also be provided with a high-power engine or a double engine, and is suitable for the unmanned helicopter to fly and work in severe environment.
it is obvious that the above embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.
Claims (10)
1. A non-bearing fuselage structure of an unmanned helicopter, comprising:
The upper main beam (1) comprises 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 upper partition frames (13) of which two ends are fixedly connected with the first upper main beam (11) and the second upper main beam (12) respectively, wherein the upper partition frames (13) are arranged at intervals along the first direction;
the lower main beam (2) comprises a first lower main beam (21) and a second lower main beam (22) which are arranged at intervals and extend along the first direction, and lower partition frames (23) of which two ends are fixedly connected with the first lower main beam (21) and the second lower main beam (22) respectively, wherein the lower partition frames (23) are arranged at intervals along the first direction;
The connecting beam (3) comprises a plurality of first connecting beams (31) and a plurality of second connecting beams (32), two ends of the first connecting beams (31) are fixedly connected with the first upper main beam (11) and the first lower main beam (21) respectively, and two ends of the second connecting beams (32) are fixedly connected with the second upper main beam (12) and the second lower main beam (22) respectively;
And two sides of the engine fixing frame (4) are fixedly connected with the first lower main beam (21) and the second lower main beam (22) respectively.
2. the unmanned helicopter non-bearing fuselage structure of claim 1, characterized in that, the unmanned helicopter non-bearing fuselage structure further comprises two reduction gearbox support frames (5) for installing a speed reducer, the two reduction gearbox support frames (5) are arranged at intervals along the extending direction of the first lower main beam (21), the two reduction gearbox support frames (5) are respectively fixedly connected with the first upper main beam (11) and the second upper main beam (12), and two ends of the speed reducer (101) are respectively installed on the two reduction gearbox support frames (5).
3. the unmanned helicopter non-carrying fuselage structure of claim 2, characterized in that the unmanned helicopter non-carrying fuselage structure further comprises a first frame plate (102), both ends of the first frame plate (102) are fixedly connected with the two reduction gearbox support frames (5), respectively, the speed reducer (101) is in transmission connection with one end of the bottom of a main shaft (103) of the unmanned helicopter and is used for driving the main shaft (103) to rotate, the main shaft (103) penetrates through the first frame plate (102), one end of the top of the main shaft (103) is provided with a rotor head (106), the rotor head (106) is used for fixing a rotor, and an umbrella bag (107) is arranged on the rotor head (106);
The utility model discloses a bearing, including main shaft (103), pressure bearing (105) and end position spare (104), end position spare (104) with main shaft (103) rigid coupling, pressure bearing (105) include last piece, lower piece and be located go up the piece with a plurality of balls between the lower piece, go up the piece with end position spare (104) rigid coupling, lower piece with first frame plate (102) rigid coupling.
4. The unmanned helicopter non-carrying fuselage structure of claim 2, characterized in that it further comprises a tail pipe support frame (6), wherein the tail pipe support frame (6) is fixedly connected to the first upper main beam (11) and the second upper main beam (12) at the same time, and the tail pipe support frame (6) is provided with a first through hole (61).
5. the unmanned helicopter non-bearing fuselage structure of claim 4 characterized in that two reduction gearbox support frames (5) are arranged along the first direction at intervals, the reduction gearbox support frames (5) are provided with fixing holes (51) for sleeving the reduction gearbox, and the fixing holes (51) and the first through holes (61) are arranged coaxially.
6. the unmanned helicopter non-carrying fuselage structure of claim 4 characterized in that it further comprises an end plate (7), said end plate (7) is fixedly connected with said first upper main beam (11), said second upper main beam (12), said first lower main beam (21) and said second lower main beam (22) respectively, said end plate (7) and said connecting beam (3) are located on both sides of said engine mount (4) respectively, and said end plate (7) and said reduction gearbox support frame (5) are located on both sides of said tail pipe support frame (6) respectively.
7. The unmanned helicopter non-carrying fuselage structure of claim 6 characterized in that a second through hole (71) is provided on the end plate (7), said second through hole (71) being arranged coaxially with the first through hole (61).
8. The unmanned helicopter non-self-carrying fuselage structure of claim 6 further comprising a first end beam (81) and a second end beam (82), wherein the first end beam (81) has two ends fixedly connected to the first upper main beam (11) and the first lower main beam (21), respectively, and the second end beam (82) has two ends fixedly connected to the second upper main beam (12) and the second lower main beam (22), respectively.
9. The unmanned helicopter non-carrying fuselage structure of claim 8 characterized in that the first end beam (81) and the end plate (7) are respectively secured to both ends of the first lower main beam (21), and the second end beam (82) and the end plate (7) are respectively secured to both ends of the second lower main beam (22).
10. The unmanned helicopter non-carrying fuselage structure of claim 1 characterized in that the engine mount (4) is provided with grooves (41) for fixing the engine, the number of the grooves (41) being one or two.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201920444493.6U CN209739314U (en) | 2019-04-03 | 2019-04-03 | Unmanned helicopter non-bearing type fuselage structure |
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| CN201920444493.6U CN209739314U (en) | 2019-04-03 | 2019-04-03 | Unmanned helicopter non-bearing type fuselage structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109850118A (en) * | 2019-04-03 | 2019-06-07 | 天津宏泽天成科技有限公司 | A kind of unmanned helicopter Non-carrying type airframe structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109850118A (en) * | 2019-04-03 | 2019-06-07 | 天津宏泽天成科技有限公司 | A kind of unmanned helicopter Non-carrying type airframe structure |
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Effective date of registration: 20200811 Address after: 300000 Tianjin city Dongli District Junliangcheng Tengfei Road No. 3 floor of building B Patentee after: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. Address before: 300000 Tianjin Science and Technology Museum, No. 94 Longchang Road, Hexi District Patentee before: TIANJIN HONGZE TIANCHENG TECHNOLOGY Co.,Ltd. |
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Effective date of registration: 20221010 Address after: Room 105, Building 9, Area B3 (formerly Area 2 of Ronghui Business Park), Enterprise Headquarters Base, Binhai-Zhongguancun Science and Technology Park, Economic and Technological Development Zone, Binhai New Area, Tianjin 300457 Patentee after: Tianjin Phoenix Intelligent Technology Co.,Ltd. Address before: Floor 1, block B, No.3, Tengfei Road, Junliang City, Dongli District, Tianjin Patentee before: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. |