CN113911374A - Oil moves duct engine mounting structure - Google Patents
Oil moves duct engine mounting structure Download PDFInfo
- Publication number
- CN113911374A CN113911374A CN202111340799.5A CN202111340799A CN113911374A CN 113911374 A CN113911374 A CN 113911374A CN 202111340799 A CN202111340799 A CN 202111340799A CN 113911374 A CN113911374 A CN 113911374A
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- frame
- support frame
- engine
- double
- shock
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- 230000035939 shock Effects 0.000 claims abstract description 26
- 238000010521 absorption reaction Methods 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000007858 starting material Substances 0.000 description 2
- 239000002828 fuel tank Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/04—Aircraft characterised by the type or position of power plants of piston type
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
-
- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses an oil-driven ducted engine mounting structure which comprises a power frame and an engine, wherein the power frame comprises a first double-section supporting frame and a second double-section supporting frame which are fixed on a main bearing ring of a duct, an annular frame and an extension part which are connected between the first double-section supporting frame and the second double-section supporting frame, and a cross rod which is connected between the first double-section supporting frame and the second double-section supporting frame. The upper portion of engine passes through first cover, second cover, third cover and the fourth cover of moving away to avoid possible earthquakes links to each other with the extension, and the lower part is moved away to avoid possible earthquakes and is overlapped and link to each other with the horizontal pole through fifth cover and sixth cover of moving away to avoid possible earthquakes. The vibration influence of the engine is transmitted to the main bearing ring through the shock absorption of the power frame, the main bearing ring bears most of the force and the disturbance of the aircraft, the rigidity of the main bearing ring is enhanced, the rigidity of the ducted aircraft can be effectively increased, the weight of the aircraft can be reduced, and the flight capability of the aircraft is effectively improved.
Description
Technical Field
The invention relates to the field of ducted aircrafts, in particular to an oil-driven ducted engine mounting structure.
Background
In the case of ducted aircraft using piston engines, the resistance of the compressed gas in the cylinder and the frictional resistance of the relative movement in the engine itself and in the accessories must be overcome at the start of the engine. Overcoming the starting drag torque and generating sufficient starting rotation speed are the necessary conditions for smooth starting of the engine. The starting mode of the piston engine can be divided into three types of hand starting, compressed air starting and electric starting according to the external energy source for starting. The hand-cranking starting scheme not only has higher requirements on professional knowledge and use experience of operators, but also has certain dangers. The compressed air starting device has a complex structure and heavier weight, and is generally only used for large engines such as marine main engines. Because the starting of the electric starter has the advantages of simple structure, convenient operation, quick starting, low cost and good reliability, the aviation piston type engine mostly adopts the mode at present.
Some piston engines are produced with electric starters and often with transmission components, which not only increase the weight of the aircraft, but also make the overall arrangement more cumbersome to design and use because of the bulk problems. The engine without the starting mechanism needs to be additionally installed when in use, and besides the problems, the starting mechanism of each set of system needs to be designed respectively, which is not beneficial to the model selection and the updating of the engine.
In addition, during the starting process of the ducted aircraft, the ducted engine runs to provide power, and the engine needs to be fixed and needs to be damped, so that the disturbance of the aircraft during the operation process is reduced, and the aircraft can fly safely and stably.
Therefore, the mounting structure of the oil-driven ducted engine needs to be designed, so that the vibration of the oil-driven ducted engine during operation can be buffered, the side pulling force generated to the engine by belt transmission during rotation of the propeller can be controlled, and the stable flight of the ducted aircraft is ensured.
Disclosure of Invention
The invention aims to solve the technical problem of the prior art and provides a six-point shock absorption type oil-driven ducted engine mounting structure with outstanding shock absorption effect and stable structure.
In order to solve the technical problems, the invention adopts the following technical scheme:
the invention relates to an oil-driven ducted engine mounting structure, which comprises a power frame and an engine, wherein the power frame comprises
The first double-section supporting frame and the second double-section supporting frame are fixed on a main bearing ring of the culvert; the first double-section supporting frame and the second double-section supporting frame are respectively positioned on two sides of the main bearing ring;
an annular frame and an extension connected between the first and second double section support frames; the number of the extending parts is two, the extending parts are respectively positioned on two sides of the annular frame and are integrally formed with the annular frame; one of the extension parts is provided with a first shock-absorbing sleeve, a second shock-absorbing sleeve, a third shock-absorbing sleeve and a fourth shock-absorbing sleeve;
the supporting frame is connected to the annular frame;
and a cross bar connected between the first double-section support frame and the second double-section support frame; the cross rod is positioned below the annular frame and the extension part, and a fifth shock-absorbing sleeve and a sixth shock-absorbing sleeve are arranged on the cross rod;
the upper portion of engine passes through first cover, second cover, third cover and the fourth cover of moving away to avoid possible earthquakes links to each other with the extension, and the lower part is moved away to avoid possible earthquakes and is overlapped and link to each other with the horizontal pole through fifth cover and sixth cover of moving away to avoid possible earthquakes.
Furthermore, the number of the support frames is four, the support frames are respectively a first support frame, a second support frame, a third support frame and a fourth support frame, and the ends of the first support frame, the second support frame, the third support frame and the fourth support frame are all connected to the main bearing ring.
Still further, the end heads of the two extending parts are respectively hinged with the first double-section support frame and the second double-section support frame.
Still further, the cross rod is fixed on the first double-section supporting frame and the second double-section supporting frame through two threaded connections.
Still further, still include the oil tank, the oil tank erects in the annular frame, and communicate with the engine through oil pipe.
Still further, the engine includes the engine organism and sets up first mount, the second mount of engine organism downside, first mount and second mount respectively with fifth cover and sixth cover link to each other of moving away to avoid possible earthquakes.
Still further, the engine still includes power take off gear, power take off gear provides power for the oar through the belt.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention provides a six-point shock-absorbing type oil-driven ducted engine mounting structure, which has a simple mounting structure form and an obvious shock-absorbing effect, ensures the stable flight of an aircraft, facilitates the overall arrangement of the ducted aircraft, has a simple structure and facilitates the model selection and the disassembly of an engine; the engine is installed on the power frame, and the power frame is fixed on main bearing ring, therefore the shock of engine influences the shock attenuation through the power frame and transmits to main bearing ring on, main bearing ring bears most power and the disturbance of aircraft, strengthens the rigidity of main bearing ring and can effectual increase ducted aircraft's rigidity, can alleviate the weight of aircraft, the flight ability of effectual improvement aircraft.
Drawings
The invention is further illustrated in the following description with reference to the drawings.
FIG. 1 is a schematic view of an oil-driven ducted engine mounting structure of the present invention;
FIG. 2 is a top view of the combination of the fuel tank and the engine with the power frame of the present invention;
FIG. 3 is a schematic view of the power frame of the present invention;
FIG. 4 is a front view of the engine to belt connection of the present invention;
description of reference numerals: 1. an oil tank;
2. a power frame; 201. a first shock-absorbing sleeve; 202. a second shock-absorbing sleeve; 203. a third shock-absorbing sleeve; 204. a fourth shock-absorbing sleeve; 205. a fifth shock-absorbing sleeve; 206. a sixth shock-absorbing sleeve; 207. an annular frame; 208. a first support frame; 209. a second support frame; 210. a third support frame; 211. a fourth support frame; 212. a first double-section support frame; 213. a second two-section support frame; 214. a cross bar; 215. an extension portion;
3. an engine; 301, 302-fixed frame, 303-power output gear, 304-engine body;
4. a belt;
5. a main bearing ring.
Detailed Description
The invention is further described with reference to the following figures and detailed description.
As shown in fig. 1 to 4, the present invention provides one specific embodiment of an oil-driven ducted engine mounting structure, which comprises an oil tank 1, a power frame 2, a ducted engine 3, a belt 4 and a main bearing ring 5, specifically, the power frame 2 comprises a first two-section support frame 212 and a second two-section support frame 213 fixed on the main bearing ring 5 of the ducted engine, an annular frame 207 and an extension part 215 connected between the first two-section support frame 212 and the second two-section support frame 213, and a cross bar 214 threaded between the first two-section support frame 212 and the second two-section support frame 213. The first double-section supporting frame 212 and the second double-section supporting frame 213 are respectively arranged at two sides of the main bearing ring 5. The number of the extension parts 215 is two, the extension parts are respectively located on two sides of the annular frame 207 and are integrally formed with the annular frame 207, and the ends of the two extension parts 215 are respectively hinged with the first double-section support frame 212 and the second double-section support frame 213, so that the structure is stable. A first shock absorbing sleeve 201, a second shock absorbing sleeve 202, a third shock absorbing sleeve 203 and a fourth shock absorbing sleeve 204 are mounted on one of the extending portions 215, the cross rod 214 is located below the annular frame 207 and the extending portions 215, a fifth shock absorbing sleeve 205 and a sixth shock absorbing sleeve 206 are mounted on the cross rod 214, the first shock absorbing sleeve 201, the second shock absorbing sleeve 202, the third shock absorbing sleeve 203 and the fourth shock absorbing sleeve 204 correspond to the fifth shock absorbing sleeve 205 and the sixth shock absorbing sleeve 206 in the up-down position, and the upper portion of the engine 3 is connected with the extending portions 215 through the first shock absorbing sleeve 201, the second shock absorbing sleeve 202, the third shock absorbing sleeve 203 and the fourth shock absorbing sleeve 204 to buffer shocks in all directions; the lower part is connected to the cross bar 214 through the fifth shock-absorbing sleeve 205 and the sixth shock-absorbing sleeve 206 for further shock-absorbing treatment.
In order to enhance the supporting strength of the annular frame, a supporting frame is mounted on the annular frame 207. The number of the support frames is four, the support frames are respectively a first support frame 208, a second support frame 209, a third support frame 210 and a fourth support frame 211, one end of the first support frame 208, one end of the second support frame 209, one end of the third support frame 210 and one end of the fourth support frame 211 are arranged on the annular frame, and the other end of the first support frame 208, one end of the second support frame 209, one end of the third support frame 210 and the other end of the fourth support frame 211 are arranged on the main bearing ring 5.
An oil tank 1 is erected in the annular frame 207, the upper portion of the oil tank is cylindrical, the lower portion of the oil tank is conical, and the oil tank is communicated with the engine 3 through an oil pipe.
The engine 3 includes an engine body 304, a power output gear 303, and a first mount 301 and a second mount 302 mounted on the lower side of the engine body 304. The power take off gear 303 provides power to the paddles through the belt 4. The first fixing frame 301 and the second fixing frame 302 are respectively connected with the fifth shock absorbing sleeve 205 and the sixth shock absorbing sleeve 206.
The main bearing ring 5 is wrapped on the periphery of the culvert body to control the roundness and the stability of the aircraft.
The above-described embodiments are merely illustrative of the preferred embodiments of the present invention, and do not limit the scope of the present invention, and various modifications and improvements of the technical solutions of the present invention can be made by those skilled in the art without departing from the spirit of the present invention, and the technical solutions of the present invention are within the scope of the present invention defined by the claims.
Claims (7)
1. The utility model provides an oil moves duct engine mounting structure, includes power frame (2) and engine (3), its characterized in that: the power frame (2) comprises
A first double-section support frame (212) and a second double-section support frame (213) which are fixed on a main bearing ring (5) of the duct; the first double-section supporting frame (212) and the second double-section supporting frame (213) are respectively positioned at two sides of the main bearing ring (5);
an annular frame (207) and an extension (215) connected between the first two-section support frame (212) and the second two-section support frame (213); the number of the extending parts (215) is two, and the extending parts are respectively positioned at two sides of the annular frame (207) and are integrally formed with the annular frame (207); one of the extension parts (215) is provided with a first shock-absorbing sleeve (201), a second shock-absorbing sleeve (202), a third shock-absorbing sleeve (203) and a fourth shock-absorbing sleeve (204);
the supporting frame is connected to the annular frame (207);
and a cross bar (214) connected between the first two-section support frame (212) and the second two-section support frame (213); the cross bar (214) is positioned below the annular frame (207) and the extension part (215), and a fifth shock-absorbing sleeve (205) and a sixth shock-absorbing sleeve (206) are arranged on the cross bar (214);
the upper portion of engine (3) is passed through first cover (201), second cover (202), third cover (203) and the fourth cover (204) of moving away to avoid possible earthquakes links to each other with extension (215) move away to avoid possible earthquakes, and the lower part is moved away to avoid possible earthquakes cover (205) and sixth cover (206) and is linked to each other with horizontal pole (214) through the fifth.
2. The oil driven ducted engine mounting structure according to claim 1, characterized in that: the number of the support frames is four, the support frames are respectively a first support frame (208), a second support frame (209), a third support frame (210) and a fourth support frame (211), and the ends of the first support frame (208), the second support frame (209), the third support frame (210) and the fourth support frame (211) are all connected to the main bearing ring (5).
3. The oil driven ducted engine mounting structure according to claim 1, characterized in that: the ends of the two extending parts (215) are respectively hinged with the first double-section support frame (212) and the second double-section support frame (213).
4. The oil driven ducted engine mounting structure according to claim 1, characterized in that: the cross rod (214) is fixed on the first double-section support frame (212) and the second double-section support frame (213) through two threaded connections.
5. The oil driven ducted engine mounting structure according to claim 1, characterized in that: the oil tank (1) is erected in the annular frame (207) and is communicated with the engine (3) through an oil pipe.
6. The oil driven ducted engine mounting structure according to claim 1, characterized in that: the engine (3) comprises an engine body (304) and a first fixing frame (301) and a second fixing frame (302) which are arranged on the lower side of the engine body (304), wherein the first fixing frame (301) and the second fixing frame (302) are respectively connected with a fifth shock absorbing sleeve (205) and a sixth shock absorbing sleeve (206).
7. The oil driven ducted engine mounting structure according to claim 6, characterized in that: the engine (3) further comprises a power output gear (303), and the power output gear (303) provides power for the paddle through a belt (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111340799.5A CN113911374B (en) | 2021-11-12 | 2021-11-12 | Oil moves duct engine mounting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111340799.5A CN113911374B (en) | 2021-11-12 | 2021-11-12 | Oil moves duct engine mounting structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113911374A true CN113911374A (en) | 2022-01-11 |
| CN113911374B CN113911374B (en) | 2023-06-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111340799.5A Active CN113911374B (en) | 2021-11-12 | 2021-11-12 | Oil moves duct engine mounting structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113911374B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104773290A (en) * | 2015-03-19 | 2015-07-15 | 南京航空航天大学 | Twin-duct coaxial multi-rotor flying motor |
| CN105711837A (en) * | 2016-01-28 | 2016-06-29 | 襄阳宏伟航空器有限责任公司 | Double-duct unmanned aerial vehicle |
| CN106927023A (en) * | 2017-03-27 | 2017-07-07 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of agricultural plant protection controls culvert type unmanned plane with rudder face |
| CN108528736A (en) * | 2018-05-25 | 2018-09-14 | 张博 | Light passenger's flight slide plate |
| CN109703748A (en) * | 2017-10-26 | 2019-05-03 | 深圳光启合众科技有限公司 | Rotor craft |
| CN210971511U (en) * | 2019-12-13 | 2020-07-10 | 河北福莱卡航空科技有限公司 | Four-wheel aircraft rear wheel cage type double shock-absorbing device |
| CN111942580A (en) * | 2020-09-24 | 2020-11-17 | 河南鲲之腾教育科技有限公司 | Pass through quick-witted frame and pass through machine |
| CN112849393A (en) * | 2021-01-24 | 2021-05-28 | 西北工业大学 | Miniaturized duct aircraft |
| CN113022845A (en) * | 2021-05-27 | 2021-06-25 | 北京航空航天大学 | Coaxial tilt rotor aircraft and thin-film aircraft combined with same |
-
2021
- 2021-11-12 CN CN202111340799.5A patent/CN113911374B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104773290A (en) * | 2015-03-19 | 2015-07-15 | 南京航空航天大学 | Twin-duct coaxial multi-rotor flying motor |
| CN105711837A (en) * | 2016-01-28 | 2016-06-29 | 襄阳宏伟航空器有限责任公司 | Double-duct unmanned aerial vehicle |
| CN106927023A (en) * | 2017-03-27 | 2017-07-07 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of agricultural plant protection controls culvert type unmanned plane with rudder face |
| CN109703748A (en) * | 2017-10-26 | 2019-05-03 | 深圳光启合众科技有限公司 | Rotor craft |
| CN108528736A (en) * | 2018-05-25 | 2018-09-14 | 张博 | Light passenger's flight slide plate |
| CN210971511U (en) * | 2019-12-13 | 2020-07-10 | 河北福莱卡航空科技有限公司 | Four-wheel aircraft rear wheel cage type double shock-absorbing device |
| CN111942580A (en) * | 2020-09-24 | 2020-11-17 | 河南鲲之腾教育科技有限公司 | Pass through quick-witted frame and pass through machine |
| CN112849393A (en) * | 2021-01-24 | 2021-05-28 | 西北工业大学 | Miniaturized duct aircraft |
| CN113022845A (en) * | 2021-05-27 | 2021-06-25 | 北京航空航天大学 | Coaxial tilt rotor aircraft and thin-film aircraft combined with same |
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| Publication number | Publication date |
|---|---|
| CN113911374B (en) | 2023-06-20 |
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