CN114435602A - Unmanned aerial vehicle engine mounting bracket - Google Patents
Unmanned aerial vehicle engine mounting bracket Download PDFInfo
- Publication number
- CN114435602A CN114435602A CN202210273914.XA CN202210273914A CN114435602A CN 114435602 A CN114435602 A CN 114435602A CN 202210273914 A CN202210273914 A CN 202210273914A CN 114435602 A CN114435602 A CN 114435602A
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- China
- Prior art keywords
- engine
- back plate
- mounting hole
- aerial vehicle
- unmanned aerial
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- 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.)
- Pending
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- 230000035939 shock Effects 0.000 claims description 7
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 238000010521 absorption reaction Methods 0.000 claims 2
- 238000009434 installation Methods 0.000 abstract description 11
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000000034 method Methods 0.000 abstract description 2
- 238000005452 bending Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
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Classifications
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- B64D27/40—
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- 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
Abstract
The invention provides an engine mounting frame for an aircraft engine with unconventional mounting hole sites. The engine mounting frame is only composed of two supports and a back plate, and is simple in structure and convenient to process. The appearance of engine mounting bracket is designed to engine hole site characteristics to convert unconventional installation hole site into conventional installation hole site, be convenient for install on unmanned aerial vehicle. The engine mounting frame structure is simplified by combining the engine structure, and the lightening holes are formed, so that the weight of the engine mounting frame is reduced while the strength and the rigidity of the whole structure are ensured. The engine mounting rack disclosed by the invention is light in weight, convenient to use, safe, reliable and simple in structure, and is beneficial to improving the flight performance of the unmanned aerial vehicle.
Description
Technical Field
The invention relates to an innovative design of an unmanned aerial vehicle engine mounting frame, meets the lightweight requirement of aviation parts, and belongs to the field of aviation design.
Background
The engine of general unmanned aerial vehicle is installed on the unmanned aerial vehicle fuselage through four points that are four angular points of rectangle, and conventional unmanned aerial vehicle engine also designs the mounting hole according to this conventionality, and its installation is comparatively convenient. However, for some unconventional drone engines, there are special hole site designs that require special engine mounts to be designed for mounting to the drone. The invention designs an engine mounting frame aiming at an aircraft engine with unconventional mounting hole sites, and has the characteristics of safety, reliability, simple structure, light weight and convenience in use.
Disclosure of Invention
For the unmanned aerial vehicle engine with unconventional installation hole sites, the structural form of an engine installation frame needs to be reasonably planned, and the engine installation frame is converted into the installation hole sites commonly used by the unmanned aerial vehicle, so that the installation is convenient. The engine is the power source of unmanned aerial vehicle, also is the part of load concentration effect, and its engine mounting bracket need fully consider the load state, makes it safe and reliable in engine operation in-process. As a part for the unmanned aerial vehicle, the structure needs to be reasonably optimized, and the self weight is reduced as much as possible so as to improve the flight performance of the unmanned aerial vehicle.
Drawings
FIG. 1 is a schematic top elevational view of an engine mount according to one embodiment of the invention.
FIG. 2 is a schematic view of the back of the engine mount of the embodiment shown in FIG. 1.
FIG. 3 is a schematic front bottom view of the engine mount of the embodiment shown in FIG. 1.
FIG. 4 is a schematic illustration of an engine mounting hole site according to one embodiment of the present invention.
FIG. 5 is a schematic front view of an engine mounted to the engine mount of the embodiment shown in FIG. 1.
FIG. 6 is a rear schematic view of an engine mounted to the engine mount of the embodiment shown in FIG. 1.
Fig. 7 is a schematic view of the mounting of the engine to the fuselage of the drone according to one embodiment of the present invention.
FIG. 8 is a schematic view of the loads and vibrations received and transmitted by the engine mount of the embodiment shown in FIG. 1.
Detailed Description
1) Engine mounting frame structure
The overall structure of the engine mount (6) according to one embodiment of the present invention is shown in fig. 1, 2 and 3, and includes a back plate (4) and two brackets (10). Two horizontal engine mounting holes (1) are arranged on the back plate (4), and two bosses (3) are arranged, so that structural interference between the back plate (4) and an engine (15) (shown in figures 4, 5 and 6) can be avoided. The back plate (4) extends to the left and the right sides to form four lugs (8) on the basis of the supporting bracket (10), and four mounting holes (9) are formed in the lugs. The bracket (10) is a triangular structure, and one upper side of the bracket comprises a flange (14) and a support plate (13) to form a T-shaped cross section. Two engine vertical mounting holes (12) are arranged at the foremost end of the bracket (10), and reinforcing columns (11) are correspondingly arranged so as to improve the rigidity near the engine vertical mounting holes (12). As shown in figure 3, the joint of the bracket (10) and the back plate (4) is provided with a large-radius fillet (5) to avoid stress concentration. In order to reduce the weight, a first lightening hole (2) is formed in the center of the back plate (4), and a second lightening hole (7) is formed in the center of the supporting plate (13).
2) Form of installation and load bearing analysis
The mounting hole site of the engine (15) is shown in fig. 4. The bottom of the front surface of the utility model is provided with two vertical threaded holes (17), and the bottom of the back surface is provided with two horizontal threaded holes (16). The engine mount (6) is mounted to the engine (15) schematically as shown in fig. 5 and 6, and the engine (15) is fixed to the engine mount (6) by two vertical screws (19) and two horizontal screws (18). As shown in fig. 7, the engine mounting bracket (6) is connected with the shock absorbing column (22) through the nut (21), and then is integrally mounted on the unmanned aerial vehicle body (20).
As shown in fig. 8, the load applied to the engine (15) is mainly thrust and self-gravity, and the operation of the engine (15) also causes longitudinal vibration. These loads are transmitted to the engine mount (6) by means of the vertical screws (19) and the horizontal screws (18). The bracket (10) here acts as a cantilever beam, with a high bending stiffness to withstand and transfer vertical loads, and a large radius fillet (5) to avoid fatigue problems under vibration. Propeller thrust is transmitted back through flanges (14) on the brackets (10), and finally the back plate (4) transmits load and vibration through the lugs (8) to the unmanned aerial vehicle fuselage (20) via the shock-absorbing columns (22).
In the actual installation operation, fix engine (15) on engine mounting bracket (6) through two vertical screw (19) and two horizontal screw (18), then install shock column (22) on engine mounting bracket (6) with nut (21), install corresponding structure on unmanned aerial vehicle fuselage (20) with shock column (22) again, can use.
The advantages and beneficial effects of the invention include:
1) under the prerequisite that satisfies the requirement of installation engine, bearing and transmission load, simple structure only comprises two supports and a backplate, and sets up lightening hole, and light in weight is favorable to unmanned aerial vehicle flight.
2) The unconventional hole site characteristics that combine two vertical screw holes of engine and two horizontal screw holes set up the engine mounting hole that corresponds on the engine mounting bracket for the engine can conveniently be fixed on the engine mounting bracket, and set up four mounting holes that are rectangle four-angle-point distribution on the engine mounting bracket, trun into the unconventional mounting hole site of engine into conventional mounting hole site, facilitated installing on unmanned aerial vehicle.
3) The rigidity of the transverse side of the support is poor, but after the engine mounting frame is installed on an engine, the engine and the engine mounting frame form an integral structure, so that the rigidity of the transverse side of the engine mounting frame is improved, and the stability is good. Therefore, the engine mount does not need to have a specially designed structure in the corresponding direction, and thus is lighter in weight while transmitting the same load.
Claims (6)
1. An unmanned aerial vehicle engine mounting bracket, its characterized in that includes:
a back plate (4), two engine horizontal mounting holes (1) are arranged on the back plate (4),
two bosses (3) arranged on the back plate (4),
four lugs (8) extending from the back plate (4) along the lateral direction, each lug (8) is provided with a shock-absorbing column mounting hole (9), the shock-absorbing column mounting holes (9) on the four lugs (8) are distributed in a rectangular four-corner-point manner,
two brackets (10), each of which is a triangular structure extending outward from the back plate (4), one upper side of the triangular structure comprises a flange (14) and a support plate (13) forming a T-shaped cross-sectional shape,
an engine vertical mounting hole (12) arranged at the foremost end of the bracket (10),
a reinforcing column (11) arranged around the vertical mounting hole (12) of the engine,
wherein:
the engine vertical mounting hole (12) is used for enabling a vertical screw (19) to pass through and is connected with a vertical threaded hole (17) at the bottom of the front surface of the engine (15),
the horizontal mounting hole (1) of the engine is used for enabling a horizontal screw (18) to pass through and is connected with a horizontal threaded hole (16) at the bottom of the back surface of the engine (15),
the shock absorption column (22) passes through the shock absorption column mounting hole (9) and is mounted on the lug plate (8) through a nut (21),
the shock absorbing posts (22) are mounted to corresponding structures on the drone fuselage (20).
2. The unmanned aerial vehicle engine mount of claim 1, characterized in that:
the joint of the bracket (10) and the back plate (4) is provided with a large-radius fillet (5) for avoiding stress concentration.
3. The unmanned aerial vehicle engine mount of claim 1 or 2, wherein:
a first lightening hole (2) is arranged in the center of the back plate (4),
the center of the supporting plate (13) is provided with a second lightening hole (7).
4. An unmanned aerial vehicle, its characterized in that includes:
a shock absorbing post (22) mounted to the drone fuselage (20),
unmanned aerial vehicle engine mounting bracket, it includes:
a back plate (4), two engine horizontal mounting holes (1) are arranged on the back plate (4),
two bosses (3) arranged on the back plate (4),
four lugs (8) extending from the back plate (4) to the left and right sides, each lug (8) is provided with a shock-absorbing column mounting hole (9), the shock-absorbing column mounting holes (9) on the four lugs (8) are distributed in a rectangular four-corner-point manner,
two brackets (10), each of which is a triangular structure extending outwardly from the back plate (4), one upper side of the triangular structure including a flange (14) and a support plate (13) forming a T-shaped cross-sectional shape,
an engine vertical mounting hole (12) arranged at the foremost end of the bracket (10),
a reinforcing column (11) arranged around the vertical mounting hole (12) of the engine,
the engine is provided with a vertical threaded hole (17) at the bottom of the front surface and a horizontal threaded hole (16) at the bottom of the back surface,
wherein:
the engine vertical mounting hole (12) is used for enabling a vertical screw (19) to pass through and is connected with a vertical threaded hole (17) at the bottom of the front surface of the engine (15),
the horizontal mounting hole (1) of the engine is used for enabling a horizontal screw (18) to pass through and is connected with a horizontal threaded hole (16) at the bottom of the back surface of the engine (15),
the shock-absorbing column (22) passes through the shock-absorbing column mounting hole (9) and is mounted on the lug plate (8) through a nut (21).
5. A drone according to claim 4, characterized in that:
the joint of the bracket (10) and the back plate (4) is provided with a large-radius fillet (5) for avoiding stress concentration.
6. A drone according to claim 4 or 5, characterised in that:
the center of the back plate (4) is provided with a first lightening hole (2),
the center of the supporting plate (13) is provided with a second lightening hole (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210273914.XA CN114435602A (en) | 2022-03-19 | 2022-03-19 | Unmanned aerial vehicle engine mounting bracket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210273914.XA CN114435602A (en) | 2022-03-19 | 2022-03-19 | Unmanned aerial vehicle engine mounting bracket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114435602A true CN114435602A (en) | 2022-05-06 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210273914.XA Pending CN114435602A (en) | 2022-03-19 | 2022-03-19 | Unmanned aerial vehicle engine mounting bracket |
Country Status (1)
| Country | Link |
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| CN (1) | CN114435602A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4108401A (en) * | 1976-12-07 | 1978-08-22 | Sullivan Products, Inc. | Motor mount for use in model airplane |
| CN106697304A (en) * | 2017-02-28 | 2017-05-24 | 天峋（常州）智能科技有限公司 | High-reliability aircraft engine mounting mechanism |
| US20190202549A1 (en) * | 2016-09-09 | 2019-07-04 | SZ DJI Technology Co., Ltd. | Load assembly and unmanned aerial vehicle |
| CN110836175A (en) * | 2018-08-16 | 2020-02-25 | 上海科泰运输制冷设备有限公司 | Rail transit air conditioner vertical compressor fixing device and fixing method |
| US20200339270A1 (en) * | 2019-04-24 | 2020-10-29 | Hfe International | Motor mounting system |
| CN112706948A (en) * | 2021-03-26 | 2021-04-27 | 北京中科宇航技术有限公司 | Inertial measurement unit support and inertial measurement unit assembly |
| CN214251564U (en) * | 2021-03-10 | 2021-09-21 | 十堰东森汽车密封件有限公司 | Two-way dynamic and static rigidity testing device for commercial vehicle power assembly suspension |
| CN113562183A (en) * | 2021-09-07 | 2021-10-29 | 北京航空航天大学 | Heat dissipation and vibration reduction system of engine direct-drive hybrid power device for unmanned aerial vehicle |
| CN113581476A (en) * | 2021-08-11 | 2021-11-02 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Engine back support structure and airplane |
-
2022
- 2022-03-19 CN CN202210273914.XA patent/CN114435602A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4108401A (en) * | 1976-12-07 | 1978-08-22 | Sullivan Products, Inc. | Motor mount for use in model airplane |
| US20190202549A1 (en) * | 2016-09-09 | 2019-07-04 | SZ DJI Technology Co., Ltd. | Load assembly and unmanned aerial vehicle |
| CN106697304A (en) * | 2017-02-28 | 2017-05-24 | 天峋（常州）智能科技有限公司 | High-reliability aircraft engine mounting mechanism |
| CN110836175A (en) * | 2018-08-16 | 2020-02-25 | 上海科泰运输制冷设备有限公司 | Rail transit air conditioner vertical compressor fixing device and fixing method |
| US20200339270A1 (en) * | 2019-04-24 | 2020-10-29 | Hfe International | Motor mounting system |
| CN214251564U (en) * | 2021-03-10 | 2021-09-21 | 十堰东森汽车密封件有限公司 | Two-way dynamic and static rigidity testing device for commercial vehicle power assembly suspension |
| CN112706948A (en) * | 2021-03-26 | 2021-04-27 | 北京中科宇航技术有限公司 | Inertial measurement unit support and inertial measurement unit assembly |
| CN113581476A (en) * | 2021-08-11 | 2021-11-02 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Engine back support structure and airplane |
| CN113562183A (en) * | 2021-09-07 | 2021-10-29 | 北京航空航天大学 | Heat dissipation and vibration reduction system of engine direct-drive hybrid power device for unmanned aerial vehicle |
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