CA2893338A1 - Fuselage structure of an unmanned helicopter - Google Patents
Fuselage structure of an unmanned helicopter Download PDFInfo
- Publication number
- CA2893338A1 CA2893338A1 CA2893338A CA2893338A CA2893338A1 CA 2893338 A1 CA2893338 A1 CA 2893338A1 CA 2893338 A CA2893338 A CA 2893338A CA 2893338 A CA2893338 A CA 2893338A CA 2893338 A1 CA2893338 A1 CA 2893338A1
- Authority
- CA
- Canada
- Prior art keywords
- beams
- unmanned helicopter
- fuselage structure
- side frames
- cross beams
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 229910000831 Steel Inorganic materials 0.000 abstract description 4
- 239000010959 steel Substances 0.000 abstract description 4
- 238000012423 maintenance Methods 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 238000005452 bending Methods 0.000 abstract description 2
- 238000009434 installation Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/17—Helicopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
- Working Measures On Existing Buildindgs (AREA)
- Automatic Assembly (AREA)
Abstract
An I-beam fuselage structure of an unmanned helicopter includes two side frames and a rotor wing frame mounted between the two side frames, and the side frames are I-beams. The fuselage structure takes I-beams as a main body structure, the inside of which is shaped like a trapezoid structure and is strengthened by a stiffening beam, characterized by high strength, simple structure and few components, disassembled quickly for maintenance. H-section steel is used for manufacturing beam structures, which further increases the lateral rigidity and resistance to bending of the fuselage structure. In addition, both the size and the weight of the fuselage structure are reduced, thus reducing the weight of the unmanned helicopter and improving the loiter time and running efficiency of the unmanned helicopter. Parts of the unmanned helicopter may be mounted on an extension beam arranged in parallel when the I-beams and the cross beams are not long enough, thus improving the flexibility in assembly of the fuselage structure.
In addition, the extension beam may further improve the strength of the I-beams and the cross beams. Hollowed-out grooves on the stiffening beam may not only facilitate installation of the frame plate but also further reduce the weight of the fuselage structure.
In addition, the extension beam may further improve the strength of the I-beams and the cross beams. Hollowed-out grooves on the stiffening beam may not only facilitate installation of the frame plate but also further reduce the weight of the fuselage structure.
Description
SPECIFICATION
I-BEAM FUSELAGE STRUCTURE OF AN UNMANNED
HELICOPTER
TECHNICAL FIELD
The utility model relates to the field of unmanned helicopter, and more particularly, to an I-beam fuselage structure of an unmanned helicopter.
BACKGROUND OF THE INVENTION
In the prior art, the fuselage structure of an unmanned helicopter mainly is obtained by improving the fuselage structure of a model airplane, following the method for designing a side plate under stress. This fuselage structure is narrow in space and low in strength, unable to provide good protection for a carrying device.
A different fuselage structure is provided in a prior patent the Bridge-type Structure of a Turboshaft Unmanned Helicopter (Application Number: 201110434831.6), which has many defects although solving the above-mentioned problems. This fuselage structure is complex in design, multiple in parts, difficult for manufacturing, high in cost, cumbersome in assembly and insufficient in strength. When it is necessary to repair internal parts of the unmanned helicopter, this structure design causes great difficulty in disassembly and assembly and thus being inconvenient for repairing the unmanned helicopter.
SUMMARY OF THE INVENTION
In allusion to problems in the fuselage structure of the existing unmanned helicopter such as complex design, multiple parts, high cost, insufficient strength, cumbersome assembly, inconvenient maintenance and so on, the utility model designs an I-beam fuselage structure of an unmanned helicopter.
The I-beam fuselage structure of an unmanned helicopter provided in the utility model includes two side frames and a rotor wing frame mounted between the two side frames, and the side frames are 1-beams.
The I-beams include two cross beams in parallel, two connecting beams are fixedly connected nn n between the two cross beams, the two connecting beams are arranged slantwise so that a trapezoid structure is formed between both, a stiffening beam is fixedly connected between the two connecting beams, and both the cross beams and the connecting beams are made from H-section aviation aluminum or steel.
A plurality of engine fixed mounts is arranged between the two side frames.
Preferably, an extension beam is arranged in parallel on the cross beams, and the engine fixed mounts are fixed to the extension beam.
Preferably, the stiffening beam is in parallel with the cross beams and is provided with a plurality of hollowed-out grooves.
Preferably, a frame plate is mounted between the stiffening beams of the two side frames, plugs arranged at both sides of the frame plate are plugged into corresponding hollowed-out grooves.
The beneficial effects of the utility model are as below: the fuselage structure takes I-beams as a main body structure, the inside of which is shaped like a trapezoid structure and is strengthened by a stiffening beam, characterized by high strength, simple structure and few components, disassembled quickly for maintenance. H-section steel is used for manufacturing beam structures, which further increases the lateral rigidity and resistance to bending of the fuselage structure. In addition, both the size and the weight of the fuselage structure are reduced, thus reducing the weight of the unmanned helicopter and improving the loiter time and running efficiency of the unmanned helicopter. Parts of the unmanned helicopter may be mounted on an extension beam arranged in parallel when the cross beams of the I-beams are not long enough, thus improving the flexibility in assembly of the fuselage structure. In addition, the extension beam may further improve the strength of the cross beams of the I-beams. Hollowed-out grooves on the stiffening beam may not only facilitate installation of the frame plate but also further reduce the weight of the fuselage structure.
According to one aspect of the present invention, there is provided an I-beam fuselage structure of an unmanned helicopter, comprising two side frames and a rotor wing frame mounted between the two side frames, the side frames are I-beams; the I-beams
I-BEAM FUSELAGE STRUCTURE OF AN UNMANNED
HELICOPTER
TECHNICAL FIELD
The utility model relates to the field of unmanned helicopter, and more particularly, to an I-beam fuselage structure of an unmanned helicopter.
BACKGROUND OF THE INVENTION
In the prior art, the fuselage structure of an unmanned helicopter mainly is obtained by improving the fuselage structure of a model airplane, following the method for designing a side plate under stress. This fuselage structure is narrow in space and low in strength, unable to provide good protection for a carrying device.
A different fuselage structure is provided in a prior patent the Bridge-type Structure of a Turboshaft Unmanned Helicopter (Application Number: 201110434831.6), which has many defects although solving the above-mentioned problems. This fuselage structure is complex in design, multiple in parts, difficult for manufacturing, high in cost, cumbersome in assembly and insufficient in strength. When it is necessary to repair internal parts of the unmanned helicopter, this structure design causes great difficulty in disassembly and assembly and thus being inconvenient for repairing the unmanned helicopter.
SUMMARY OF THE INVENTION
In allusion to problems in the fuselage structure of the existing unmanned helicopter such as complex design, multiple parts, high cost, insufficient strength, cumbersome assembly, inconvenient maintenance and so on, the utility model designs an I-beam fuselage structure of an unmanned helicopter.
The I-beam fuselage structure of an unmanned helicopter provided in the utility model includes two side frames and a rotor wing frame mounted between the two side frames, and the side frames are 1-beams.
The I-beams include two cross beams in parallel, two connecting beams are fixedly connected nn n between the two cross beams, the two connecting beams are arranged slantwise so that a trapezoid structure is formed between both, a stiffening beam is fixedly connected between the two connecting beams, and both the cross beams and the connecting beams are made from H-section aviation aluminum or steel.
A plurality of engine fixed mounts is arranged between the two side frames.
Preferably, an extension beam is arranged in parallel on the cross beams, and the engine fixed mounts are fixed to the extension beam.
Preferably, the stiffening beam is in parallel with the cross beams and is provided with a plurality of hollowed-out grooves.
Preferably, a frame plate is mounted between the stiffening beams of the two side frames, plugs arranged at both sides of the frame plate are plugged into corresponding hollowed-out grooves.
The beneficial effects of the utility model are as below: the fuselage structure takes I-beams as a main body structure, the inside of which is shaped like a trapezoid structure and is strengthened by a stiffening beam, characterized by high strength, simple structure and few components, disassembled quickly for maintenance. H-section steel is used for manufacturing beam structures, which further increases the lateral rigidity and resistance to bending of the fuselage structure. In addition, both the size and the weight of the fuselage structure are reduced, thus reducing the weight of the unmanned helicopter and improving the loiter time and running efficiency of the unmanned helicopter. Parts of the unmanned helicopter may be mounted on an extension beam arranged in parallel when the cross beams of the I-beams are not long enough, thus improving the flexibility in assembly of the fuselage structure. In addition, the extension beam may further improve the strength of the cross beams of the I-beams. Hollowed-out grooves on the stiffening beam may not only facilitate installation of the frame plate but also further reduce the weight of the fuselage structure.
According to one aspect of the present invention, there is provided an I-beam fuselage structure of an unmanned helicopter, comprising two side frames and a rotor wing frame mounted between the two side frames, the side frames are I-beams; the I-beams
2 =
comprise two cross beams in parallel, two connecting beams are fixedly connected between the two cross beams, the two connecting beams are arranged slantwise so that a trapezoid structure is formed between both, a stiffening beam is fixedly connected between the two connecting beams, and both the cross beams and the connecting beams have H-type cross sections; wherein the stiffening beam is in parallel with the cross beams, and the stiffening beam is provided with a plurality of hollowed-out grooves and a plurality of engine fixed mounts are arranged between the two side frames.
BRIEF DESCRIPTION OF THE DRAWINGS
Fig. 1 is a structure diagram of the I-beam fuselage structure.
1 0 Fig. 2 is a structure diagram of I-beams.
DESCRIPTION OF THE EMBODIMENTS
2a SPECIFICATION
As shown in Fig. 1, the I-beam fuselage structure of an unmanned helicopter provided in the utility model includes two side frames 1 and a rotor wing frame 2 mounted between the two side frames 1, the rotor wing of the unmanned helicopter is mounted on the rotor wing frame, and the side frames 1 are I-beams.
As shown in Fig. 2, the I-beams include two cross beams 3 in parallel, two connecting beams 4 are fixedly connected between the two cross beams 3, the two connecting beams 4 are arranged slantwise so that a structure the inside of which is shaped like a trapezoid comprises the two connecting beams 4 and the two cross beams 3, besides, a stiffening beam 5 is fixedly connected between the two connecting beams 4.
Both the cross beams 3 and the connecting beams 4 are made from H-section steel, a plurality of engine fixed mounts 6 are mounted between the two side frames 1, and the engine of the unmanned helicopter is mounted on the engine fixed mounts 6.
According to the needs of the structure, an extension beam 7 may be arranged in parallel on the I-beams 3 so that the engine fixed mounts 6 or other devices in the unmanned helicopter may be fixed to the extension beam 7. The extension beam 7 may be mounted on either one of the cross beams 3 of each I-beam, or both cross beams 3 are respectively provided with an extension beam 7.
The stiffening beam 5 is in parallel with the cross beams 3 so that two trapezoid structures are formed between the two connecting beams, which further improves the strength of the I-beams and the fuselage structure.
A plurality of hollowed-out grooves 8 are arranged on the stiffening beam 5, a frame plate 9 is mounted between the two side frames 1 and the stiffening beam 5, and plugs arranged at both sides of the frame plate 9 are plugged into corresponding hollowed-out grooves 8.
The frame plate 9 may be configured to support a master gear mounted on the principal axis of the rotor wing, and also configured to mount other parts in the unmanned helicopter.
In order to assemble the unmanned helicopter with this fuselage structure, only a plurality of brackets needs mounting between the two side frames 1 and other parts in the unmanned helicopter are arranged on these brackets.
k 9(110
comprise two cross beams in parallel, two connecting beams are fixedly connected between the two cross beams, the two connecting beams are arranged slantwise so that a trapezoid structure is formed between both, a stiffening beam is fixedly connected between the two connecting beams, and both the cross beams and the connecting beams have H-type cross sections; wherein the stiffening beam is in parallel with the cross beams, and the stiffening beam is provided with a plurality of hollowed-out grooves and a plurality of engine fixed mounts are arranged between the two side frames.
BRIEF DESCRIPTION OF THE DRAWINGS
Fig. 1 is a structure diagram of the I-beam fuselage structure.
1 0 Fig. 2 is a structure diagram of I-beams.
DESCRIPTION OF THE EMBODIMENTS
2a SPECIFICATION
As shown in Fig. 1, the I-beam fuselage structure of an unmanned helicopter provided in the utility model includes two side frames 1 and a rotor wing frame 2 mounted between the two side frames 1, the rotor wing of the unmanned helicopter is mounted on the rotor wing frame, and the side frames 1 are I-beams.
As shown in Fig. 2, the I-beams include two cross beams 3 in parallel, two connecting beams 4 are fixedly connected between the two cross beams 3, the two connecting beams 4 are arranged slantwise so that a structure the inside of which is shaped like a trapezoid comprises the two connecting beams 4 and the two cross beams 3, besides, a stiffening beam 5 is fixedly connected between the two connecting beams 4.
Both the cross beams 3 and the connecting beams 4 are made from H-section steel, a plurality of engine fixed mounts 6 are mounted between the two side frames 1, and the engine of the unmanned helicopter is mounted on the engine fixed mounts 6.
According to the needs of the structure, an extension beam 7 may be arranged in parallel on the I-beams 3 so that the engine fixed mounts 6 or other devices in the unmanned helicopter may be fixed to the extension beam 7. The extension beam 7 may be mounted on either one of the cross beams 3 of each I-beam, or both cross beams 3 are respectively provided with an extension beam 7.
The stiffening beam 5 is in parallel with the cross beams 3 so that two trapezoid structures are formed between the two connecting beams, which further improves the strength of the I-beams and the fuselage structure.
A plurality of hollowed-out grooves 8 are arranged on the stiffening beam 5, a frame plate 9 is mounted between the two side frames 1 and the stiffening beam 5, and plugs arranged at both sides of the frame plate 9 are plugged into corresponding hollowed-out grooves 8.
The frame plate 9 may be configured to support a master gear mounted on the principal axis of the rotor wing, and also configured to mount other parts in the unmanned helicopter.
In order to assemble the unmanned helicopter with this fuselage structure, only a plurality of brackets needs mounting between the two side frames 1 and other parts in the unmanned helicopter are arranged on these brackets.
k 9(110
Claims (3)
1. An I-beam fuselage structure of an unmanned helicopter, comprising two side frames and a rotor wing frame mounted between the two side frames, the side frames are I-beams;
the I-beams comprise two cross beams in parallel, two connecting beams are fixedly connected between the two cross beams, the two connecting beams are arranged slantwise so that a trapezoid structure is formed between both, a stiffening beam is fixedly connected between the two connecting beams, and both the cross beams and the connecting beams have H-type cross sections; wherein the stiffening beam is in parallel with the cross beams, and the stiffening beam is provided with a plurality of hollowed-out grooves and a plurality of engine fixed mounts are arranged between the two side frames.
the I-beams comprise two cross beams in parallel, two connecting beams are fixedly connected between the two cross beams, the two connecting beams are arranged slantwise so that a trapezoid structure is formed between both, a stiffening beam is fixedly connected between the two connecting beams, and both the cross beams and the connecting beams have H-type cross sections; wherein the stiffening beam is in parallel with the cross beams, and the stiffening beam is provided with a plurality of hollowed-out grooves and a plurality of engine fixed mounts are arranged between the two side frames.
2. The I-beam fuselage structure of an unmanned helicopter according to claim 1, wherein an extension beam is arranged in parallel on the cross beams, and the engine fixed mounts are fixed to the extension beam.
3. The I-beam fuselage structure of an unmanned helicopter according to claim 1, wherein a frame plate is mounted between the two side frames and the stiffening beam, plugs arranged at both sides of the frame plate are plugged into corresponding hollowed-out grooves.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420366873.XU CN203958601U (en) | 2014-07-03 | 2014-07-03 | The I-shaped beam type airframe structure of depopulated helicopter |
| CN201420366873X | 2014-07-03 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2893338A1 true CA2893338A1 (en) | 2015-12-03 |
| CA2893338C CA2893338C (en) | 2016-07-19 |
Family
ID=51919221
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2893338A Expired - Fee Related CA2893338C (en) | 2014-07-03 | 2015-06-02 | Fuselage structure of an unmanned helicopter |
Country Status (3)
| Country | Link |
|---|---|
| CN (1) | CN203958601U (en) |
| CA (1) | CA2893338C (en) |
| WO (1) | WO2016000485A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109677584A (en) * | 2018-12-29 | 2019-04-26 | 一飞智控(天津)科技有限公司 | DCB Specimen unmanned aerial vehicle body |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104590583B (en) * | 2014-12-19 | 2016-06-29 | 四川精石航空科技开发有限公司 | A kind of frock for microlight-type helicopter main frame |
| CN105156873B (en) * | 2015-09-09 | 2019-04-09 | 申科谱自动化科技（珠海）有限公司 | A kind of profile |
| CN105752326B (en) * | 2016-04-07 | 2018-06-22 | 珠海紫燕无人飞行器有限公司 | Rack and unmanned helicopter |
| CN106477019A (en) * | 2016-11-08 | 2017-03-08 | 芜湖万户航空航天科技有限公司 | Helicopter fuselage upper plate |
| CN106672194A (en) * | 2017-02-24 | 2017-05-17 | 沈阳卓翼航空科技有限公司 | Skeleton structure of agricultural unmanned aerial vehicle |
| CN109808876B (en) * | 2019-03-26 | 2023-09-19 | 河南谷翼自动化科技有限公司 | Coaxial double-wing aircraft |
| 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 |
| CN111928092A (en) * | 2020-07-17 | 2020-11-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Mounting bracket and have its mounting structure |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7198224B2 (en) * | 2005-02-24 | 2007-04-03 | Sikorsky Aircraft Corporation | Energy absorbing airframe for a vertical lift vehicle |
| US8920594B2 (en) * | 2005-08-03 | 2014-12-30 | Sikorsky Aircraft Corporation | Composite thermoplastic matrix airframe structure and method of manufacture therefore |
| FR2896770B1 (en) * | 2006-01-27 | 2008-04-11 | Eurocopter France | SIDE-HOLDING ANTI-CRASH COMPOSITE STRUCTURE FOR AIRCRAFT. |
| JP5260778B1 (en) * | 2012-10-08 | 2013-08-14 | ヒロボー株式会社 | Unmanned helicopter |
| CN103523199A (en) * | 2013-09-29 | 2014-01-22 | 郭献民 | Novel tubular-structure electric unmanned helicopter |
-
2014
- 2014-07-03 CN CN201420366873.XU patent/CN203958601U/en not_active Expired - Fee Related
-
2015
- 2015-04-30 WO PCT/CN2015/077906 patent/WO2016000485A1/en active Application Filing
- 2015-06-02 CA CA2893338A patent/CA2893338C/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109677584A (en) * | 2018-12-29 | 2019-04-26 | 一飞智控(天津)科技有限公司 | DCB Specimen unmanned aerial vehicle body |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2016000485A1 (en) | 2016-01-07 |
| CN203958601U (en) | 2014-11-26 |
| CA2893338C (en) | 2016-07-19 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKLA | Lapsed |
Effective date: 20190603 |