CN104691737A - Support arm assembly for multi-rotor aircrafts, rack and aircraft - Google Patents
Support arm assembly for multi-rotor aircrafts, rack and aircraft Download PDFInfo
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- CN104691737A CN104691737A CN201510097404.1A CN201510097404A CN104691737A CN 104691737 A CN104691737 A CN 104691737A CN 201510097404 A CN201510097404 A CN 201510097404A CN 104691737 A CN104691737 A CN 104691737A
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- connecting element
- down arm
- hold
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- aircraft
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Abstract
The invention discloses a support arm assembly for multi-rotor aircrafts, a rack and an aircraft. The support arm assembly comprises a body connector, a support arm and a motor soleplate, wherein one end of the support arm is connected with a body through the body connector, the motor soleplate is fixedly arranged at the other end of the support arm, the two ends of the support arm are of a square section beam structure, the middle section of the support arm is of an airfoil-profile section beam structure, and the body connector comprises a body fixed part, a support arm fixed part and a clamp hook. The body fixed part is fixedly connected with the body, the body fixed part is provided with a hinge pin which is use for being in interference fit with the clamp hook, and the support arm fixed part is fixedly connected with the support arm, hinged with the body fixed part, and provided with a limiting piece. The support arm can effectively reduce the lift force loss caused by rotor downwash in the flight process of a multi-rotor aircraft, and improve the endurance, voyage and load capacity of the aircraft; and due to the body connector, a support arm for a multi-rotor aircraft can be simply and quickly folded, thereby effectively reducing the volume of the multi-rotor aircraft, and improving the portability of the multi-rotor aircraft.
Description
Technical field
the present invention relates to aircraft field, particularly a kind of multi-rotor aerocraft supporting arm assembly, frame and aircraft.
Background technology
Multi-rotor aerocraft compared to fixed wing aircraft or helicopter flight more steadily, can hovering, side fly and after to fly etc. to switch rapidly between state of flight, takeoff and landing performance and maneuvering performance good, be suitable for very much performing the tasks such as fixed point is scouted, taken photo by plane, aerial mapping, there is military affairs and civil use widely.
The flight support arm of existing multi-rotor aerocraft adopts pipe or mouth word to cut section bar structure usually, awing the downwash flow of rotor is through flight support arm, downward application force can be had to hold-down arm, this force direction is contrary with lift direction, larger loss is brought to the lift of whole aircraft, thus when shortening the boat of aircraft and voyage, reduce the load-carrying capacity of aircraft.
The flight support arm of existing multi-rotor aerocraft is fixedly mounted in frame usually, makes the volume of whole aircraft very large like this, brings very large inconvenience to carry and storage etc.Also there are some improvement projects in prior art, such as, adopt detachable or folding hold-down arm scheme etc.Multi-rotor aerocraft fuselage and hold-down arm when carrying and store of detachable hold-down arm scheme are separately deposited, and seem comparatively scattered, not too convenient.Folding type supporting arm scheme is an entirety all the time when carrying and store, the setup time advantageously before shortening multi-rotor aerocraft and using.More common folding type supporting arm scheme is bolted the hold-down arm of rotor wing unmanned aerial vehicle and fuselage, when needing to launch hold-down arm, and loose bolts, promoting hold-down arm is that axle center horizontally rotates to the position vertical with fuselage surface with bolt; Then binding bolt completes hold-down arm expansion.But this method needs to carry out rotation process to bolt, the rapid deployment that cannot realize hold-down arm is with folding, and unmanned plane integral structure under hold-down arm folded state is compact not.
Summary of the invention
The object of the invention is to overcome the problems referred to above, a kind of multi-rotor aerocraft supporting arm assembly, frame and aircraft are provided.
For achieving the above object, the method that the present invention adopts is: a kind of multi-rotor aerocraft supporting arm assembly, comprise fuselage attaching parts, hold-down arm, motor mount, described hold-down arm one end is connected with fuselage by described fuselage attaching parts, the other end is installed with described motor mount, described hold-down arm integral structure is hollow girder structure, two ends are that mouth word cuts section bar structure, stage casing is aerofoil section girder construction, smooth transition between the described two-port word section of cutting section bar and described stage casing aerofoil section beam section.
Cross-sectional plane as preferably described hold-down arm stage casing aerofoil section beam of the present invention is one or more hollow air foil shapes arranged side by side, length is equal to or greater than 50% rotor radius length, position is arranged at 30%-80% rotor radius corresponding on described hold-down arm and maybe this fragment position is included, and it is parallel that the aerofoil profile string of a musical instrument of aerofoil section is set to carry out flow path direction with rotor downwash.
As preferably of the present invention, described fuselage attaching parts comprises fuselage connecting element, hold-down arm connecting element and grab, described fuselage connecting element and fuselage are connected, which is provided with for the bearing pin with described grab interference fit, described hold-down arm connecting element and described hold-down arm are connected, hinged with described fuselage connecting element, which is provided with banking stop, described grab one end and described hold-down arm connecting element hinged, bearing pin interference fit on the hook portion of the other end and described fuselage connecting element, described hold-down arm upon deployment, banking stop on described hold-down arm connecting element contacts with the bearing pin on described fuselage connecting element, described grab is fixedly connected with the bearing pin on described fuselage connecting element, described hold-down arm is when packing up, bearing pin on described grab and described fuselage connecting element disengages, bearing pin on banking stop on described hold-down arm connecting element and described fuselage connecting element disengages.
The invention also discloses a kind of aircraft frame, described frame is configured with above-mentioned multi-rotor aerocraft supporting arm assembly.
The invention also discloses a kind of aircraft, described aircraft configuration has above-mentioned frame.
Disclosed aircraft of the present invention, is preferably multi-rotor aerocraft.
Beneficial effect:
Technical solution of the present invention compares traditional rotor craft hold-down arm can effectively reduce the loss of lift that in multi-rotor aerocraft flight course, rotor down-wash flow brings, when improving the boat of aircraft and voyage and load-carrying capacity.Fuselage attaching parts in technical solution of the present invention makes multi-rotor aerocraft hold-down arm simply promptly to fold, and effectively reduces the volume of multi-rotor aerocraft, improves the portability of multi-rotor aerocraft.
Accompanying drawing explanation
Fig. 1 is many flight support arm component schematic diagram;
Fig. 2 is the A-A cross-sectional view of flight support arm in Fig. 1;
Fig. 3 is the structural representation of flight support arm, motor and rotor;
Fig. 4 is the mounting structure schematic diagram of fuselage attaching parts;
Fig. 5 is multi-rotor aerocraft frame schematic diagram;
Fig. 6 is the structural representation before and after multi-rotor aerocraft folds;
Fig. 7 is the structural representation after multi-rotor aerocraft folds;
In figure: 1, supporting arm assembly, 2, frame, 3, aircraft, 4, fuselage attaching parts, 5, hold-down arm, 51, mouth word cuts section bar structure, 52, aerofoil section girder construction, 6, motor mount, 7, fuselage, 8, fuselage connecting element, 9, hold-down arm connecting element, 10, banking stop, 11, grab, 12, bearing pin, 13, rotor.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, illustrate the present invention further, the present embodiment is implemented under premised on technical solution of the present invention, should understand these embodiments and only be not used in for illustration of the present invention and limit the scope of the invention.
Embodiment 1:
A kind of multi-rotor aerocraft supporting arm assembly 1 as shown in accompanying drawing 1 to Fig. 3, comprises fuselage attaching parts 4, hold-down arm 5, motor mount 6.Hold-down arm 5 one end is connected with fuselage 7 by fuselage attaching parts 4, and the other end is installed with motor mount 6.
Hold-down arm 5 integral structure is hollow girder structure, and two ends are that mouth word cuts section bar structure 51, and stage casing is aerofoil section girder construction 52.Smooth transition between the two-port word section of cutting section bar and stage casing aerofoil section beam section.The cross-sectional plane of hold-down arm 5 stage casing aerofoil section beam is one or more hollow air foil shapes arranged side by side, length is equal to or greater than 50% rotor 13 radius length, position is arranged at 30%-80% rotor 13 radius corresponding on hold-down arm 5 and maybe this fragment position is included, and it is parallel that the aerofoil profile string of a musical instrument of aerofoil section is set to wash flow path direction 13 times with rotor.
As shown in Figure 4, be fuselage attaching parts 4 schematic diagram disclosed by the invention, fuselage attaching parts 4 comprises fuselage connecting element 8, hold-down arm connecting element 9 and grab 11.Fuselage connecting element 8 is fixing repeatedly with fuselage 7, which is provided with for the bearing pin 12 with grab 11 interference fit.Hold-down arm connecting element 9 is fixedly connected with hold-down arm 5, and fuselage connecting element 8 is hinged, which is provided with banking stop 10.Grab 11 one end and hold-down arm connecting element 9 hinged, bearing pin 12 interference fit on the hook portion of the other end and fuselage connecting element 8.Hold-down arm 5 upon deployment, banking stop 10 on hold-down arm connecting element 9 contacts with the bearing pin 12 on fuselage connecting element 8, grab 11 is fixedly connected with the bearing pin 12 on fuselage connecting element 8, upwards rotate relative to fuselage 7 for limiting hold-down arm 5 at flying time limit bit slice 10, simultaneously transmit to fuselage 7 lift that rotor 13 provides, when not flying grab 11 can limit hold-down arm 5 relatively fuselage 7 rotate.Hold-down arm 5 is when packing up, and grab 11 disengages with the bearing pin 11 on fuselage connecting element 8, and the banking stop 10 on hold-down arm connecting element 9 and the bearing pin 12 on fuselage connecting element 8 disengage.
As shown in Figure 5, be frame 2 schematic diagram of aircraft disclosed by the invention, this frame 2 is configured with multi-rotor aerocraft supporting arm assembly 1 as previously described.After being configured with multi-rotor aerocraft supporting arm assembly 1, aircraft frame 2 can carry out rapid deployment with folding.In the present embodiment, the flight support arm 5 of aircraft frame 2 can be folded to below fuselage 7 from fuselage 7 side along the root of hold-down arm 5, and its folding angles, more than 90 °, substantially reduces the volume of whole aircraft.
As shown in Figure 6, be aircraft 3 schematic diagram disclosed by the invention, aircraft comprises frame 2, and described frame 2 is configured with multi-rotor aerocraft supporting arm assembly 1 as previously described.Aircraft of the present invention is multi-rotor aerocraft.
Technical solution of the present invention compares traditional rotor craft hold-down arm can effectively reduce the loss of lift that in multi-rotor aerocraft flight course, rotor down-wash flow brings, when improving the boat of aircraft and voyage and load-carrying capacity.Fuselage attaching parts in technical solution of the present invention makes multi-rotor aerocraft hold-down arm simply promptly to fold, and effectively reduces the volume of multi-rotor aerocraft, improves the portability of multi-rotor aerocraft.
Technological means disclosed in the present invention program is not limited only to the technological means disclosed in above-mentioned technological means, also comprises the technical scheme be made up of above technical characteristic combination in any.The above is the specific embodiment of the present invention; it should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention; can also make some improvements and modifications, these improvements and modifications are also considered as protection scope of the present invention.
Claims (6)
1. a multi-rotor aerocraft supporting arm assembly, it is characterized in that: comprise fuselage attaching parts, hold-down arm, motor mount, described hold-down arm one end is connected with fuselage by described fuselage attaching parts, the other end is installed with described motor mount, described hold-down arm integral structure is hollow girder structure, two ends are that mouth word cuts section bar structure, and stage casing is aerofoil section girder construction, smooth transition between the described two-port word section of cutting section bar and described stage casing aerofoil section beam section.
2. a kind of multi-rotor aerocraft supporting arm assembly according to claim 1, it is characterized in that: the cross-sectional plane of described hold-down arm stage casing aerofoil section beam is one or more hollow air foil shapes arranged side by side, length is equal to or greater than 50% rotor radius length, position is arranged at 30%-80% rotor radius corresponding on described hold-down arm and maybe this fragment position is included, and it is parallel that the aerofoil profile string of a musical instrument of aerofoil section is set to carry out flow path direction with rotor downwash.
3. a kind of multi-rotor aerocraft supporting arm assembly according to claim 1 and 2, it is characterized in that: described fuselage attaching parts comprises fuselage connecting element, hold-down arm connecting element and grab, described fuselage connecting element and fuselage are connected, which is provided with for the bearing pin with described grab interference fit, described hold-down arm connecting element and described hold-down arm are connected, hinged with described fuselage connecting element, which is provided with banking stop, described grab one end and described hold-down arm connecting element hinged, bearing pin interference fit on the hook portion of the other end and described fuselage connecting element, described hold-down arm upon deployment, banking stop on described hold-down arm connecting element contacts with the bearing pin on described fuselage connecting element, described grab is fixedly connected with the bearing pin on described fuselage connecting element, described hold-down arm is when packing up, bearing pin on described grab and described fuselage connecting element disengages, bearing pin on banking stop on described hold-down arm connecting element and described fuselage connecting element disengages.
4. an aircraft frame, is characterized in that: described frame is configured with the multi-rotor aerocraft supporting arm assembly according to any one of claim 1-3.
5. an aircraft, is characterized in that: described aircraft configuration has frame as claimed in claim 4.
6. aircraft according to claim 5, is characterized in that: described aircraft is multi-rotor aerocraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510097404.1A CN104691737B (en) | 2015-03-05 | 2015-03-05 | A kind of multi-rotor aerocraft supporting arm assembly, frame and aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510097404.1A CN104691737B (en) | 2015-03-05 | 2015-03-05 | A kind of multi-rotor aerocraft supporting arm assembly, frame and aircraft |
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| CN104691737A true CN104691737A (en) | 2015-06-10 |
| CN104691737B CN104691737B (en) | 2016-06-01 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105000163A (en) * | 2015-08-23 | 2015-10-28 | 张子林 | Downwards foldable-type multi-rotor wing unmanned aerial vehicle |
| CN105109679A (en) * | 2015-08-23 | 2015-12-02 | 张子林 | Locking component and multi-rotor unmanned aerial vehicle |
| WO2017121038A1 (en) * | 2016-01-14 | 2017-07-20 | 骅星科技发展有限公司 | Novel folding unmanned aerial vehicle |
| WO2017132794A1 (en) * | 2016-02-01 | 2017-08-10 | 张琬彬 | Rectangular unmanned aerial vehicle arm |
| WO2017143644A1 (en) * | 2016-02-22 | 2017-08-31 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle and frame thereof, kit, assembly method, and operation method |
| CN107792352A (en) * | 2016-08-29 | 2018-03-13 | 天津中翔腾航科技股份有限公司 | A kind of six rotor wing unmanned aerial vehicles |
| WO2022226933A1 (en) * | 2021-04-29 | 2022-11-03 | 深圳市大疆创新科技有限公司 | Vertical takeoff and landing fixed-wing unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105000163A (en) * | 2015-08-23 | 2015-10-28 | 张子林 | Downwards foldable-type multi-rotor wing unmanned aerial vehicle |
| CN105109679A (en) * | 2015-08-23 | 2015-12-02 | 张子林 | Locking component and multi-rotor unmanned aerial vehicle |
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| WO2017121038A1 (en) * | 2016-01-14 | 2017-07-20 | 骅星科技发展有限公司 | Novel folding unmanned aerial vehicle |
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| EP3419894A4 (en) * | 2016-02-22 | 2019-02-06 | SZ DJI Technology Co., Ltd. | Foldable multi-rotor aerial vehicle |
| WO2017143644A1 (en) * | 2016-02-22 | 2017-08-31 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle and frame thereof, kit, assembly method, and operation method |
| CN108698685B (en) * | 2016-02-22 | 2021-11-02 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle, frame, kit, assembly method and operation method thereof |
| EP3971084A1 (en) * | 2016-02-22 | 2022-03-23 | SZ DJI Technology Co., Ltd. | Aéronef multi-rotor pliable |
| US11427319B2 (en) | 2016-02-22 | 2022-08-30 | SZ DJI Technology Co., Ltd. | Foldable multi-rotor aerial vehicle |
| CN107792352A (en) * | 2016-08-29 | 2018-03-13 | 天津中翔腾航科技股份有限公司 | A kind of six rotor wing unmanned aerial vehicles |
| WO2022226933A1 (en) * | 2021-04-29 | 2022-11-03 | 深圳市大疆创新科技有限公司 | Vertical takeoff and landing fixed-wing unmanned aerial vehicle |
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| CN104691737B (en) | 2016-06-01 |
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Effective date of registration: 20180222 Address after: Nanjing Baixia High-tech Industrial Park in Jiangsu province 210000 Building No. 4 Room 305 Patentee after: Nanjing Tao - Aviation Technology Co. Ltd. Address before: Nanjing Baixia High-tech Industrial Park in Jiangsu province 210000 Building No. 4 Room 305 Patentee before: Ge Xun |