CN112478178A - Mounting structure is placed to single rotor no aileron unmanned aerial vehicle engine - Google Patents
Mounting structure is placed to single rotor no aileron unmanned aerial vehicle engine Download PDFInfo
- Publication number
- CN112478178A CN112478178A CN202011559565.5A CN202011559565A CN112478178A CN 112478178 A CN112478178 A CN 112478178A CN 202011559565 A CN202011559565 A CN 202011559565A CN 112478178 A CN112478178 A CN 112478178A
- Authority
- CN
- China
- Prior art keywords
- engine
- clutch
- mounting
- aileron
- rotor
- 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.)
- Pending
Links
- 238000009434 installation Methods 0.000 claims abstract description 18
- 230000035939 shock Effects 0.000 claims abstract description 16
- 239000000463 material Substances 0.000 claims description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 4
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- 230000002787 reinforcement Effects 0.000 claims description 2
- 230000002349 favourable effect Effects 0.000 abstract description 3
- 238000005461 lubrication Methods 0.000 abstract 1
- 238000010521 absorption reaction Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 239000010687 lubricating oil Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 240000004282 Grewia occidentalis Species 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/06—Helicopters with single rotor
-
- B64D27/40—
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Abstract
The invention discloses a single-rotor wing non-aileron unmanned aerial vehicle engine placing and mounting structure which comprises an engine main body and a clutch, wherein a shock pad is mounted at the lower end of the engine main body, the right upper end of the engine main body is supported by an engine rear mounting seat, a clutch bearing is additionally arranged on the end surface of the clutch, an engine mounting plate is connected with the clutch bearing, the engine mounting plate comprises an engine mounting left plate and an engine mounting right plate, the engine mounting left plate and the engine mounting right plate are fixedly connected with an engine front mounting plate and an engine hanging bracket to form a whole, and an engine front mounting seat is arranged at the upper end of the engine hanging bracket. This mounting structure is placed to single rotor does not have aileron unmanned aerial vehicle engine, and the engine level is placed, is favorable to the bearing lubrication at output shaft position, and its structure is convenient in installing and removing, uses and maintains the convenience, reduces use cost, and the installation accuracy is not high, and the assembly degree of difficulty is little.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a single-rotor non-aileron unmanned aerial vehicle engine placing and mounting structure.
Background
Unmanned aerial vehicle of small-size low load is mostly the motor, and it is less with the small-size unmanned aerial vehicle of engine as power, but to the unmanned aerial vehicle about 200 kilograms at the weight of taking off, the first key element of unmanned aerial vehicle design is chooseed for use and rationally used to engine performance parameter. The good operation of the engine plays a decisive role in the stable flight of the airplane;
the engine power part of the helicopter is the core part of the unmanned helicopter, whether the function of the engine power part can stably and continuously operate to directly determine the life of the helicopter, most of the existing engine installation modes are four-corner double-angle hoisting type assembly, the engine is vertically placed, the output shaft is upward, and the tail ends of four angles are fixed with the helicopter body through shock absorbing pads. This way of mounting the engine is undoubtedly the best way from a purely force analysis point of view. However, the structure has the following defects in comprehensive consideration:
1. the double-angle part is difficult to process, and meanwhile, the requirements on four fixed angle positions of the double angle fixed on the engine are too high, so that the installation is difficult.
2. The vertical placement of the engine may result in the bearings that secure the engine output shaft not being adequately lubricated by the lubricating oil, where the longer the engine operating time, the greater the risk of bearing damage.
Therefore, the installation structure for placing the engine of the single-rotor aileron-free unmanned aerial vehicle is provided.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a single-rotor non-aileron unmanned aerial vehicle engine placing and mounting structure, which solves the problems that the double-angle part of the single-rotor non-aileron unmanned aerial vehicle engine in the prior art is difficult to process, and the position of four fixed angles of the double angles fixed on the engine is too high, so that the mounting is difficult; the vertical placement of the engine can result in the problem that the bearings that secure the engine output shaft are not adequately lubricated by the lubricating oil, where the risk of bearing damage increases the longer the engine runs.
The utility model provides a mounting structure is placed to single rotor no aileron unmanned aerial vehicle engine, this mounting structure includes engine main part and clutch, the shock pad is installed to the lower extreme of engine main part, and the upper right end of engine main part is supported by the mount pad behind the engine, the terminal surface of clutch increases a clutch bearing, is connected engine mounting panel and clutch bearing, and this engine mounting panel includes engine installation left board and engine installation right board, with engine installation left board, engine installation right board and engine before mounting panel and the engine gallows be connected fixedly and be a whole, the upper end of this engine gallows is provided with mount pad before the engine, below is with the engine fixed plate with above-mentioned whole reinforcement.
Preferably, an engine support bearing is mounted inside the engine main body.
Preferably, the clutch is also provided with a clutch connecting shaft connected with a taper hole of an output shaft of the engine.
Preferably, the materials of the shock pad, the engine mounting plate, the engine rear mounting seat, the engine hanger, the engine front mounting seat, the engine front mounting plate, the engine support bearing, the clutch bearing and the clutch connecting shaft are all 7075 aviation aluminum materials.
Preferably, the shock pad is assembled on the fixed seat.
Preferably, the engine hanger is fixed to a root plane of an output shaft of the engine.
Compared with the prior art, the invention has the following beneficial effects: this mounting structure is placed to single rotor no aileron unmanned aerial vehicle engine, this mounting structure can be used to let the reasonable installation of engine place, simultaneously can be with the better integration of organism, guarantee a mechanical structure of aircraft flight safety, and this structure has stronger stability, characteristics such as simple manufacture and installation are convenient, the engine level is placed, it is lubricated to be favorable to the bearing at output shaft position, its structure is convenient in installing and removing, the use is maintained conveniently, use cost is reduced, the installation accuracy is not high, the assembly degree of difficulty is little.
Drawings
FIG. 1 is a front view of an engine mount mounting structure of the present invention;
FIG. 2 is a top view of the engine mount mounting structure of the present invention;
FIG. 3 is a schematic view of the internal output shaft bearing structure of the engine of the present invention;
FIG. 4 is a schematic view of the overall structure of the clutch;
in the figure: 1. an engine main body; 2. a shock pad; 3. an engine mounting plate; 4. an engine rear mounting base; 5. an engine pylon; 6. an engine front mounting base; 7. an engine front mounting plate; 8. an engine support bearing; 9. a clutch; 10. a clutch bearing; 11. the clutch is connected with the shaft.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-4, a mounting structure for placing an engine of a single-rotor non-aileron unmanned aerial vehicle comprises an engine main body 1 and a clutch 9, wherein a shock pad 2 is mounted at the lower end of the engine main body 1, the upper right end of the engine main body 1 is supported by a rear engine mounting seat 4, a clutch bearing 10 is additionally arranged on the end surface of the clutch 9, an engine mounting plate 3 is connected with the clutch bearing 10, the engine mounting plate 3 comprises an engine mounting left plate and an engine mounting right plate, the engine mounting left plate, the engine mounting right plate, a front engine mounting plate 7 and an engine hanger 5 are fixedly connected into a whole, a front engine mounting seat 6 is arranged at the upper end of the engine hanger 5, and the whole is reinforced by an engine fixing plate below.
An engine support bearing 8 is mounted inside the engine body 1.
The clutch 9 is also provided with a clutch connecting shaft 11 connected with a taper hole of an output shaft of the engine.
The materials of the shock pad 2, the engine mounting plate 3, the engine rear mounting seat 4, the engine hanger 5, the engine front mounting seat 6, the engine front mounting plate 7, the engine support bearing 8, the clutch bearing 10 and the clutch connecting shaft 11 are all 7075 aviation aluminum materials.
The shock pad 2 is assembled on the fixed seat.
The engine hanger 5 is fixed with the root plane of the output shaft of the engine.
It should be noted that the mounting structure is roughly composed of an engine main body 1, a clutch 9, an engine rear fixing support, an engine front fixing seat, a shock pad 2 and other components, wherein the engine rear fixing support is connected with a mounting hole of the engine main body 1, mounting hole sites of the shock pad 2 are arranged at two ends of the fixing support, an engine hanger 5 is fixed with the root plane of an output shaft of the engine main body 1, then the clutch 9 is fixed on the output shaft of the engine, a bearing is added on the end face of the clutch 9 to connect the mounting plate of the engine main body 1 with the engine rear fixing support, finally, the engine mounting left and right plates, the engine front mounting plate and the engine hanger are connected and fixed to form a whole, and the whole is reinforced by an engine fixing plate below. The engine front fixing seats are fixed on the left and right mounting plates of the engine respectively, the shock absorption pads are assembled on the fixing seats, and then the engine front fixing seats and the engine rear fixing supports form a four-point shock absorption structure to be fixed on the engine body, and the engine is horizontally placed. All parts are made of 7075 aviation aluminum materials, and the parts are tightly connected and fixed together by the structure, so that the integrity is strong, and the conditions required by the work of an engine are met;
this mounting structure can be used to let the reasonable installation of engine place, can be simultaneously with the organism better combine together, guarantee aircraft flight safety's a mechanical structure, and this structure has stronger stability, characteristics such as simple manufacture and installation are convenient, the engine level is placed, is favorable to the bearing at output shaft position to be lubricated, its structure is convenient in installing and removing, use maintenance is convenient, reduces use cost, the installation accuracy is not high, the assembly degree of difficulty is little.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. The utility model provides a mounting structure is placed to single rotor no aileron unmanned aerial vehicle engine, this mounting structure includes engine main part (1) and clutch (9), its characterized in that: shock pad (2) are installed to the lower extreme of engine main part (1), and the upper right end of engine main part (1) is supported by mount pad (4) behind the engine, clutch bearing (10) are increased to the terminal surface of clutch (9), are connected engine mounting panel (3) and clutch bearing (10), and this engine mounting panel (3) are including engine installation left board and engine installation right board, are connected engine installation left board, engine installation right board and engine before mounting panel (7) and engine gallows (5) and are fixed and be a whole, and mount pad (6) before this engine gallows (5) upper end is provided with an engine, and the below is with the engine fixed plate with above-mentioned whole reinforcement.
2. The single-rotor aileron-less drone engine mount structure of claim 1 wherein: an engine supporting bearing (8) is installed inside the engine main body (1).
3. The single-rotor aileron-less drone engine mount structure of claim 1 wherein: and the clutch (9) is also provided with a clutch connecting shaft (11) connected with a taper hole of an output shaft of the engine.
4. The single-rotor aileron-less drone engine mount structure of claim 1 wherein: the material of shock pad (2), engine mounting panel (3), mount pad (4) behind the engine, engine gallows (5), mount pad (6) before the engine, mount pad (7) before the engine, engine support bearing (8), clutch bearing (10) and clutch connecting axle (11) is 7075 aviation aluminum product.
5. The single-rotor aileron-less drone engine mount structure of claim 1 wherein: the shock pad (2) is assembled on the fixed seat.
6. The single-rotor aileron-less drone engine mount structure of claim 1 wherein: the engine hanger (5) is fixed with the root plane of the output shaft of the engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011559565.5A CN112478178A (en) | 2020-12-25 | 2020-12-25 | Mounting structure is placed to single rotor no aileron unmanned aerial vehicle engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011559565.5A CN112478178A (en) | 2020-12-25 | 2020-12-25 | Mounting structure is placed to single rotor no aileron unmanned aerial vehicle engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112478178A true CN112478178A (en) | 2021-03-12 |
Family
ID=74915494
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011559565.5A Pending CN112478178A (en) | 2020-12-25 | 2020-12-25 | Mounting structure is placed to single rotor no aileron unmanned aerial vehicle engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112478178A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115716536A (en) * | 2022-10-25 | 2023-02-28 | 中国航发沈阳发动机研究所 | Thin-wall high-strength oblique support plate bearing frame structure |
-
2020
- 2020-12-25 CN CN202011559565.5A patent/CN112478178A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115716536A (en) * | 2022-10-25 | 2023-02-28 | 中国航发沈阳发动机研究所 | Thin-wall high-strength oblique support plate bearing frame structure |
| CN115716536B (en) * | 2022-10-25 | 2023-07-21 | 中国航发沈阳发动机研究所 | Thin-wall high-strength inclined support plate bearing frame structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4531694A (en) | Turbine engine drive and mounting assembly for fixed wing aircraft | |
| CN109178301A (en) | A kind of fixed-wing rotor mixing unmanned plane | |
| CN105775120A (en) | Multi-rotor unmanned aerial vehicle | |
| CN110481767B (en) | Foldable variable-pitch four-rotor aircraft based on oil-electricity hybrid power and using method | |
| CN205524969U (en) | Unmanned aerial vehicle with multiple rotor wings | |
| CN112478178A (en) | Mounting structure is placed to single rotor no aileron unmanned aerial vehicle engine | |
| CN110803280A (en) | Pure electric manned vehicle | |
| CN214397262U (en) | Mounting structure is placed to single rotor no aileron unmanned aerial vehicle engine | |
| CN210027900U (en) | Battery compartment of multi-rotor manned aircraft and manned aircraft comprising battery compartment | |
| CN106005401A (en) | Unmanned aerial vehicle tail tilting pair power mechanism | |
| CN206704550U (en) | To the depopulated helicopter fuselage interior structure of arrangement after a kind of turboaxle motor | |
| CN113148188A (en) | Dual-power vertical take-off and landing fixed-wing unmanned aerial vehicle | |
| CN213008695U (en) | Unmanned coaxial helicopter frame structure of heavy load and helicopter | |
| CN110155312B (en) | Battery compartment of multi-rotor manned aircraft and manned aircraft comprising battery compartment | |
| CN208102333U (en) | The double-deck rotor wings frame in a kind of unmanned plane | |
| CN220701360U (en) | Multi-rotor unmanned aerial vehicle with oil-electricity mixing function | |
| CN219884096U (en) | Tilting rotor unmanned aerial vehicle | |
| CN212401536U (en) | Aircraft with a flight control device | |
| CN212501011U (en) | Large-load unmanned coaxial helicopter | |
| CN216185991U (en) | Multi-rotor unmanned aerial vehicle | |
| CN220786158U (en) | Unmanned helicopter body framework and unmanned helicopter body structure | |
| CN218368317U (en) | Power battery mounting structure and aircraft that has it | |
| CN210310856U (en) | High-load all-terrain fixed-wing unmanned aerial vehicle device | |
| CN208993916U (en) | A kind of multi-rotor unmanned aerial vehicle | |
| CN220114817U (en) | Fuselage structure force transmission assembly of double-rotor unmanned helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |