CN218537119U - Aircraft power component - Google Patents
Aircraft power component Download PDFInfo
- Publication number
- CN218537119U CN218537119U CN202223072141.3U CN202223072141U CN218537119U CN 218537119 U CN218537119 U CN 218537119U CN 202223072141 U CN202223072141 U CN 202223072141U CN 218537119 U CN218537119 U CN 218537119U
- Authority
- CN
- China
- Prior art keywords
- fixed mounting
- mounting
- aerial vehicle
- unmanned aerial
- aircraft power
- 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.)
- Active
Links
Images
Abstract
The utility model relates to an aircraft power component technical field just discloses an aircraft power component, including main part mechanism, monitoring mechanism and power unit, monitoring mechanism is located main part mechanism's upper end, power unit is located main part mechanism's upper end, main part mechanism includes unmanned aerial vehicle body, wing, switch and shutdown key, wing fixed mounting is at the front end of unmanned aerial vehicle body, switch fixed mounting is in the upper end of unmanned aerial vehicle body, shutdown key fixed mounting is in the upper end of unmanned aerial vehicle body, monitoring mechanism is including installation base, installation screw, installation base fixed mounting is in the upper end of unmanned aerial vehicle body. This aircraft power component through installation and improvement to power unit for this aircraft power component's installation dismantlement ability promotes to some extent, and in the in-service use process, can be as required portable change screw, sparingly dismantle installation time, has improved this aircraft power component's convenience.
Description
Technical Field
The utility model relates to an aircraft power component technical field specifically is an aircraft power component.
Background
Along with the continuous development of society, scientific and technical field is also constantly promoting, and unmanned aerial vehicle technique is also constantly promoting, and unmanned aerial vehicle is also small aircraft, and the indispensable spare part of aircraft is power component.
However, due to poor installation capability of the aircraft power assembly in the prior art, the propeller on the power assembly cannot be quickly disassembled and replaced in the actual use process of the aircraft power assembly, and the propeller needs to be disassembled and installed for a long time when needing to be replaced, so that the use efficiency is affected.
And because the monitoring ability of aircraft power component among the prior art is not good, lead to aircraft power component in the in-service use in-process, portable multi-angle monitoring can't, influence the work efficiency of aircraft.
SUMMERY OF THE UTILITY MODEL
Technical problem to be solved
An object of the utility model is to provide an aircraft power component to the installation ability who proposes among the prior art aircraft power component is not good in solving above-mentioned background art, leads to aircraft power component in the in-service use, can't carry out quick dismantlement change to power component upper screw, need consume the problem of dismantling the installation for a long time when needing to change.
(II) technical scheme
In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides an aircraft power component, includes main part mechanism, monitoring mechanism and power unit, monitoring mechanism is located the upper end of main part mechanism, power unit is located the upper end of main part mechanism, main part mechanism includes unmanned aerial vehicle body, wing, switch and shutdown key, wing fixed mounting is at the front end of unmanned aerial vehicle body, switch fixed mounting is in the upper end of unmanned aerial vehicle body, shutdown key fixed mounting is in the upper end of unmanned aerial vehicle body, monitoring mechanism is including installation base, installation screw, support frame, swivelling joint axle one, spliced pole, control casing and camera lens, installation base fixed mounting is in the upper end of unmanned aerial vehicle body.
Preferably, installation screw fixed mounting is in the upper end of installation base, support frame fixed mounting is in the upper end of installation screw, a rotatory connecting axle fixed mounting has realized the effect of the control of being convenient for in the upper end of support frame through the installation to installation screw and rotatory connecting axle one, and in the in-service use process, can the portable multi-foot pad monitor, improved this aircraft power component's availability factor.
Preferably, spliced pole fixed mounting is in the upper end of rotatory connecting axle one, control casing fixed mounting is in the upper end of spliced pole, camera lens fixed mounting has realized the effect of the control of being convenient for through the installation to spliced pole and camera lens in the inside of control casing, and in the in-service use process, the multiple foot pad that can be handy is monitored, has improved this aircraft power component's availability factor.
Preferably, the power mechanism comprises a motor, a rotating connecting shaft II, a transmission shaft, a mounting support, a first fixing hole, a mounting hole, a first fixing screw, a first gasket, a connecting end, a propeller, a second gasket, a fixing mounting sheet, a second fixing hole and a second fixing screw, the motor is fixedly mounted at the upper end of the wing, and the rotating connecting shaft II is fixedly mounted at the upper end of the motor and is mounted on the motor and the rotating connecting shaft II.
Preferably, transmission shaft fixed mounting extends to the upper end of swivelling joint axle two in the upper end of motor, installing support movable mounting is in the upper end of swivelling joint axle two, both ends around the installing support are fixed mounting to a fixed orifices fixed mounting, both ends about the installing support are through the installation to transmission shaft and installing support for this aircraft power component's installation dismantlement ability promotes to some extent, and in the in-service use process, can be as required portable change screw, sparingly dismantle installation time, improved this aircraft power component's convenience.
Preferably, a fixed screw movable mounting is at the upper end of a fixed hole I, a gasket movable mounting is at the upper end of the mounting hole, a connecting end is movably mounted at the upper end of the gasket I, the screw is fixedly mounted at the outer end of the connecting end, and the screw and the gasket I are mounted, so that the mounting and dismounting capacity of the aircraft power assembly is improved to some extent, the screw can be changed portably as required in the actual use process, the mounting time is saved, and the convenience of the aircraft power assembly is improved.
Preferably, two movable mounting of gasket are in the upper end of link, fixed mounting piece movable mounting is in the upper end of gasket two, two fixed mounting of fixed orifices are in the inside of fixed mounting piece, two movable mounting of fixed screw are in two upper ends of fixed orifices, through the installation to fixed orifices two and fixed screw two for this aircraft power pack's installation dismantlement ability promotes to some extent, and in the in-service use process, can be as required handy change screw, sparingly dismantle installation time, improved this aircraft power pack's convenience.
Compared with the prior art, the beneficial effects of the utility model are that:
1. the power mechanism is installed and improved, so that the installation and disassembly capacity of the power assembly of the aircraft is improved, the propeller can be conveniently replaced as required in the actual use process, the disassembly and assembly time is saved, and the convenience of the power assembly of the aircraft is improved;
2. the power assembly of the aircraft realizes the function of convenient operation and control by installing and improving the main body mechanism, is simple to operate and more stable to fly in the actual use process, and improves the practicability of the power assembly of the aircraft;
3. this aircraft power component through installation and improvement to monitoring mechanism, has realized the effect of the control of being convenient for, and in the in-service use process, the multi-foot pad that can be portable monitors, has improved this aircraft power component's availability factor.
Drawings
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a schematic sectional view of the present invention;
FIG. 3 is a schematic view of the xxx structure of the present invention;
fig. 4 is a schematic structural diagram of xxx of the present invention.
In the figure: 1. a main body mechanism; 101. an unmanned aerial vehicle body; 102. an airfoil; 103. a power switch; 104. a shutdown key; 2. a monitoring mechanism; 201. installing a base; 202. mounting screws; 203. a support frame; 204. rotating the first connecting shaft; 205. connecting columns; 206. monitoring the housing; 207. a lens; 3. a power mechanism; 301. a motor; 302. rotating the connecting shaft II; 303. a drive shaft; 304. mounting a bracket; 305. a first fixing hole; 306. mounting holes; 307. a first fixing screw; 308. a first gasket; 309. a connecting end; 310. a propeller; 311. a second gasket; 312. fixing the mounting plate; 313. a second fixing hole; 314. and a second fixing screw.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts all belong to the protection scope of the present invention.
Referring to fig. 1-4, the present invention provides a technical solution: the utility model provides an aircraft power component, including main part mechanism 1, monitoring mechanism 2 and power unit 3, monitoring mechanism 2 is located main part mechanism 1's upper end, power unit 3 is located main part mechanism 1's upper end, main part mechanism 1 includes unmanned aerial vehicle body 101, wing 102, switch 103 and shutdown key 104, wing 102 fixed mounting is at the front end of unmanned aerial vehicle body 101, switch 103 fixed mounting is in the upper end of unmanned aerial vehicle body 101, shutdown key 104 fixed mounting is in the upper end of unmanned aerial vehicle body 101, monitoring mechanism 2 is including installation base 201, installation screw 202, support frame 203, swivelling joint axle 204, spliced pole 205, control casing 206 and camera lens 207, installation base 201 fixed mounting is in the upper end of unmanned aerial vehicle body 101.
The power mechanism 3 comprises a motor 301, a second rotary connecting shaft 302, a transmission shaft 303, a mounting bracket 304, a first fixing hole 305, a mounting hole 306, a first fixing screw 307, a first gasket 308, a connecting end 309, a propeller 310, a second gasket 311, a first fixing mounting sheet 312, a second fixing hole 313 and a second fixing screw 314, wherein the motor 301 is fixedly mounted at the upper end of the wing 102, the second rotary connecting shaft 302 is fixedly mounted at the upper end of the motor 301, the transmission shaft 303 is fixedly mounted at the upper end of the motor 301 and extends to the upper end of the second rotary connecting shaft 302, the mounting bracket 304 is movably mounted at the upper end of the second rotary connecting shaft 302, the first fixing hole 305 is fixedly mounted at the front end and the rear end of the mounting bracket 304, the mounting hole 306 is fixedly mounted at the left end and the right end of the mounting bracket 304, a first fixing screw 307 is movably arranged at the upper end of the first fixing hole 305, a first gasket 308 is movably arranged at the upper end of the mounting hole 306, a connecting end 309 is movably arranged at the upper end of the first gasket 308, a propeller 310 is fixedly arranged at the outer end of the connecting end 309, a second gasket 311 is movably arranged at the upper end of the connecting end 309, a fixed mounting piece 312 is movably arranged at the upper end of the second gasket 311, a second fixing hole 313 is fixedly arranged inside the fixed mounting piece 312, a second fixing screw 314 is movably arranged at the upper end of the second fixing hole 313, a motor 301 drives a transmission shaft 303 to rotate a second rotating connecting shaft 302, meanwhile, the propeller 310 is rotated, the second fixing screw 314 is screwed out to take down the fixed mounting piece 312, and then the propeller 310 is replaced.
The working principle is as follows: when using, firstly press down switch 103 starter motor 301 and drive transmission shaft 303 and rotate two 302 of rotatory connecting axle, make screw 310 rotate simultaneously, make unmanned aerial vehicle fly up, when needing to change screw 310, unscrew out two 314 of fixed screw and take off fixed mounting piece 312, then change screw 310, can be with installing support 304 steady mounting on two 302 of rotatory connecting axle through a fixed screw 307, can fix control casing 206 on unmanned aerial vehicle body 101 through installation base 201 and installation screw 202, can make control casing 206 and camera lens 207 multi-angle control through a rotatory connecting axle 204, high durability and convenient use, press shut down key 104 when not using and shut down.
It should be finally noted that the above contents are only used to illustrate the technical solutions of the present invention, but not to limit the protection scope of the present invention, and the simple modification or equivalent replacement performed by the technical solutions of the present invention by those skilled in the art does not depart from the spirit and scope of the technical solutions of the present invention.
Claims (7)
1. The utility model provides an aircraft power component, includes main part mechanism (1), monitoring mechanism (2) and power unit (3), its characterized in that: monitoring mechanism (2) are located the upper end of main part mechanism (1), power unit (3) are located the upper end of main part mechanism (1), main part mechanism (1) includes unmanned aerial vehicle body (101), wing (102), switch (103) and shutdown key (104), wing (102) fixed mounting is at the front end of unmanned aerial vehicle body (101), switch (103) fixed mounting is in the upper end of unmanned aerial vehicle body (101), shutdown key (104) fixed mounting is in the upper end of unmanned aerial vehicle body (101), monitoring mechanism (2) are including installation base (201), installation screw (202), support frame (203), rotatory connecting axle (204), spliced pole (205), control casing (206) and camera lens (207), installation base (201) fixed mounting is in the upper end of unmanned aerial vehicle body (101).
2. An aircraft power pack according to claim 1, wherein: the mounting screw (202) is fixedly mounted at the upper end of the mounting base (201), the supporting frame (203) is fixedly mounted at the upper end of the mounting screw (202), and the rotating connecting shaft I (204) is fixedly mounted at the upper end of the supporting frame (203).
3. An aircraft power pack according to claim 2, wherein: the connecting column (205) is fixedly mounted at the upper end of the first rotating connecting shaft (204), the monitoring shell (206) is fixedly mounted at the upper end of the connecting column (205), and the lens (207) is fixedly mounted inside the monitoring shell (206).
4. An aircraft power pack according to claim 3, wherein: the power mechanism (3) comprises a motor (301), a second rotating connecting shaft (302), a transmission shaft (303), a mounting bracket (304), a first fixing hole (305), a mounting hole (306), a first fixing screw (307), a first gasket (308), a connecting end (309), a propeller (310), a second gasket (311), a fixing mounting sheet (312), a second fixing hole (313) and a second fixing screw (314), wherein the motor (301) is fixedly mounted at the upper end of the wing (102), and the second rotating connecting shaft (302) is fixedly mounted at the upper end of the motor (301).
5. An aircraft power pack according to claim 4, wherein: transmission shaft (303) fixed mounting extends to the upper end of rotatory connecting axle two (302) in the upper end of motor (301), installing support (304) movable mounting is in the upper end of rotatory connecting axle two (302), both ends around fixed orifices one (305) fixed mounting installing support (304), both ends about installing support (304) fixed mounting is in installing support (306).
6. An aircraft power pack according to claim 5, wherein: the first fixing screw (307) is movably arranged at the upper end of the first fixing hole (305), the first gasket (308) is movably arranged at the upper end of the mounting hole (306), the connecting end (309) is movably arranged at the upper end of the first gasket (308), and the propeller (310) is fixedly arranged at the outer end of the connecting end (309).
7. An aircraft power pack according to claim 6, wherein: the second gasket (311) is movably mounted at the upper end of the connecting end (309), the fixed mounting piece (312) is movably mounted at the upper end of the second gasket (311), the second fixing hole (313) is fixedly mounted in the fixed mounting piece (312), and the second fixing screw (314) is movably mounted at the upper end of the second fixing hole (313).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223072141.3U CN218537119U (en) | 2022-11-18 | 2022-11-18 | Aircraft power component |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223072141.3U CN218537119U (en) | 2022-11-18 | 2022-11-18 | Aircraft power component |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218537119U true CN218537119U (en) | 2023-02-28 |
Family
ID=85262672
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223072141.3U Active CN218537119U (en) | 2022-11-18 | 2022-11-18 | Aircraft power component |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218537119U (en) |
-
2022
- 2022-11-18 CN CN202223072141.3U patent/CN218537119U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN218537119U (en) | Aircraft power component | |
| CN210799126U (en) | Engine radiator | |
| CN112009229A (en) | Battery arrangement device for new energy automobile | |
| CN111942135B (en) | New energy battery mounting rack and mounting method thereof | |
| CN219421240U (en) | Electricity-saving controller for communication engineering | |
| CN112238129A (en) | New energy battery recovery unit | |
| CN214155226U (en) | Power-saving control device for positioning equipment | |
| CN212623013U (en) | Conduction testing instrument for producing wire harness | |
| CN211593224U (en) | New forms of energy battery sticker machine | |
| CN218110159U (en) | Cutting cooling mechanism | |
| CN220527399U (en) | Efficient and energy-saving device of electric power system convenient to install and detach | |
| CN220509054U (en) | Handheld electric energy quality analyzer | |
| CN214177038U (en) | Motor with dustproof heat radiation structure | |
| CN216351133U (en) | Wireless internal resistance monitoring device applied to UPS storage battery pack | |
| CN210006401U (en) | detachable driving board card convenient to overhaul | |
| CN213547268U (en) | Step motor for stage lighting equipment | |
| CN218950763U (en) | Traction machine structure convenient for maintenance and repair for elevator | |
| CN219228122U (en) | Power conversion device for air monitoring system | |
| CN220368887U (en) | Diesel engine controller box | |
| CN215030687U (en) | Rotating device for dispenser | |
| CN211720859U (en) | Generator set controller convenient for dismounting touch frame structure | |
| CN220068053U (en) | Wall-mounted monitoring display | |
| CN220749937U (en) | Press type bracket lamp end cover | |
| CN213092496U (en) | Distribution room anti-overflow water early warning device | |
| CN211681956U (en) | Detachable and quickly-installed maintenance platform |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |