CN205801533U - A kind of multi-rotor aerocraft - Google Patents
A kind of multi-rotor aerocraft Download PDFInfo
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- CN205801533U CN205801533U CN201620727504.8U CN201620727504U CN205801533U CN 205801533 U CN205801533 U CN 205801533U CN 201620727504 U CN201620727504 U CN 201620727504U CN 205801533 U CN205801533 U CN 205801533U
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- rotor aerocraft
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- propeller
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Abstract
This utility model relates to a kind of unmanned vehicle, particularly relate to a kind of multi-rotor aerocraft, it solves the technical problem that the multi-rotor aerocraft being to provide a kind of drop resistant ability by force and to people's safety, and it includes the body being made up of flight controller, wireless remote controlled receiver and power transfer module；The rotor assemblies that the propeller by motor, being connected with machine shaft and the electron speed regulator being connected with motor form；The frame being connected with described body and rotor assemblies；Described frame is constituted groined type by two longitudinal horns and two horizontal horns intersections；The mounting seat of described rotor assemblies is located at described longitudinal horn and the infall of horizontal horn；The periphery of described groined type frame is provided with the guard circle preventing described rotor assemblies from being clashed into surrounded by hollow cylinder PE Foam.Described horn is made up of carbon fiber board or hollow carbon fiber pipe.This utility model can be used for indoor flight training and uses.
Description
Technical field
This utility model relates to a kind of unmanned vehicle, particularly relates to a kind of multi-rotor aerocraft, it include body,
Frame, propeller and motor.
Background technology
In unmanned plane industry, multi-rotor aerocraft refers to the rotor quantity aircraft more than or equal to three, and this is a kind of knot
The aircraft that structure is simple, manipulation is flexible, flight attitude is stable.Sensor and micro-process is included in the body of multi-rotor aerocraft
Device；It passes through various kinds of sensors perception state of flight, and sends rotary speed instruction by microprocessor to each rotor motor and adjust
The different flight attitudes of aircraft.Having benefited from the most micro electronmechanical, the development of sensor technology, multi-rotor aerocraft extensively should
For fields such as model plane, aerial photographing platforms.
The multi-rotor aerocraft being suitable for indoor training flight is important application, at present, and this kind of multi-rotor aerocraft
Being small volume, the class that wheelbase is less, its frame is made up of the horn of cross intersection, and propeller and motor are arranged at horn
Free end；When indoor flight, once aircraft hits wall, propeller and motor general unbearably shock and damages；Further, high-speed rotary
The propeller turned constitutes a threat to also for the safety of neighbouring manipulation people.
This is the weak point of existing multi-rotor aerocraft.
Summary of the invention
For shortcoming or the deficiency of above-mentioned prior art, the technical problem to be solved in the present invention is to provide a kind of drop resistant ability
Multi-rotor aerocraft by force and to people's safety.
For solving above-mentioned technical problem, the present invention has a following composition: the multi-rotor aerocraft of the present invention, including by flying
Controller, wireless remote controlled receiver and the body of power transfer module composition；The propeller that by motor, is connected with machine shaft and
The rotor assemblies of the electron speed regulator composition being connected with motor；The frame being connected with described body and rotor assemblies；It is characterized in that:
Described frame is constituted groined type by two longitudinal horns and two horizontal horns intersections；The mounting seat of described rotor assemblies is located at institute
State longitudinal horn and the infall of horizontal horn；The periphery of described groined type frame is provided with by preventing that hollow cylinder PE Foam surrounds
The guard circle that only described rotor assemblies is clashed into.
Described horn is made up of carbon fiber board or hollow carbon fiber pipe.
Described propeller is positioned at below described motor.
Described propeller is SANYE oar.
Compared with prior art, it is an advantage of the current invention that: 1 when aircraft is collided by indoor barrier, hollow
The guard circle that cylinder PE Foam surrounds can absorb part Impact energy, the machine that carbon fiber board or hollow carbon fiber pipe are constituted simultaneously
Arm and groined type frame the most relatively impact resistance, thus can effectively protect body, motor and propeller, make they unlikely damages, when
When people met by aircraft, propeller also will not get to people, so this design also makes aircraft become the safest.
2 install downwards due to motor, and use SANYE oar, when propeller revolves, and when producing downward air-flow, horn is not located
In the downwash flow of propeller, making flying power system effectiveness improve, the flight time increases.
3 this utility model simple in construction, with low cost, produce and easy to maintenance.
Accompanying drawing explanation
Fig. 1 is the front view of the multi-rotor aerocraft of utility model.
Fig. 2 is the left view of Fig. 1.
Fig. 3 is the axonometric chart of multi-rotor aerocraft of the present utility model.
Fig. 4 is the structural representation of body of the present utility model.
Detailed description of the invention
Below with reference to accompanying drawing, the technique effect of design, concrete structure and the generation of the present invention is described further, with
It is fully understood from the purpose of the present invention, feature and effect.
Referring to Fig. 1 ~ Fig. 3, the multi-rotor aerocraft of the present invention is mainly by body 1, rotor assemblies and described body and rotor
Frame and the guard circle 4 being located at frame peripheral that assembly is connected form.Body 1 is a rectangular box body, and it is by upper and lower two
Block carbon plate and aluminium alloy cylinder and screw are spliced.Rotor assemblies is made up of motor 21, propeller 22 and electron speed regulator 23.
Frame is made up of 31,32, two longitudinal horns 33,34 of two horizontal horns, and it connects and composes a groined type.Machine
Arm is mainly made up of carbon fiber board, or the effective screw of square hollow carbon fiber is formed by connecting, and the intensity of this material makes it
Body compares impact resistance.At the infall of four horns constituting groined type, it is provided with the mounting seat for installing described rotor assemblies
20, motor 21 is fixed in mounting seat 20 and installs downwards, and propeller 22 is arranged in motor 21 rotating shaft, and it is just at motor
Lower section, the rotating shaft of motor 21 can drive propeller 22 to rotate.When propeller rotates, when producing downward air-flow, horn is not
It is in the downwash flow of propeller, thus propeller efficiency can effectively improve.
Described mounting seat 20 has four, and they form a tetragon, during normal vehicle operation, are positioned at diagonal angle
The direction of rotation of the motor in mounting seat is consistent, and the direction of rotation of the motor being positioned in adjacent mounting seat is contrary, in FIG,
If be numbered four motors, the upper right corner is No. 1 motor, and the upper left corner is No. 2 motors, and the lower left corner is No. 3 motor, bottom right
Angle is No. 4 motor, and No. 1 motor and No. 3 motors use the propeller in the direction that turns clockwise, No. 2 and No. 4 motors employing inverse times
The propeller that pin direction rotates.Whether which motor or propeller, they are all the easily worn parts in aircraft.
Guard circle 4 is surrounded by a ultralight hollow cylinder PE Foam, and it encloses right around airframe one, is rendered as
The square of one band round edge.In the outermost of the well word machine frame being made up of horn, namely on the free end of each horn,
All it is connected to one and is wrapped in this hollow cylinder Margarita with the thin slice circle aluminum component 41 of aluminium alloy forging forming, eight circular aluminum components
Cotton outer wall, thus guard circle and frame connect into an entirety.Referring to Fig. 2, the diameter of ultralight hollow cylinder PE Foam is wanted
More than motor and the height of propeller, thus the easily worn part of aircraft is enclosed in guard circle, and this peripheral circle is ultralight
Hollow cylinder PE Foam can absorb the aircraft collision from indoor barrier, effectively protects body, motor and propeller,
Making they unlikely damages, when people met by aircraft, propeller also will not get to people, so this design also makes aircraft become
The safest.
Referring to Fig. 4, the outer wall of the dead ahead of box body is provided with power transfer module 11, and it is provided as whole electronic devices and components
Supplying cell electricity is also detected by the stabilized power source that works with other expanded circuit, so installs primarily to convenient electricity
Source modular converter heat radiation；The outer wall in the dead astern of box body is provided with LED light 12, so installs primarily to conveniently watch
The battery electric quantity of LED instruction and the state of flight of aircraft.The main control letter placed for receiving wireless remote control in box body
Number wireless remote control connect device 13 and for controlling the flight controller of state of flight；Flight controller includes forming inertia measurement list
Unit 14(IMU) 3-axis acceleration flowmeter sensor and three-axis gyroscope sensor, its be used for measure multi-rotor aerocraft flight
The attitude of period；Flight controller also includes three axle geomagnetic sensors 15, and it is for measuring the earth's magnetic field of multi-rotor aerocraft；Fly
Line control unit also include form pico computer 16 for processing the single-chip microcomputer of flying quality and for performing the list of control command
Sheet machine.
The electron speed regulator being connected with motor is used for regulating the rotating speed of machine shaft, and its installation site is against the installation of motor
Seat, in propeller downwash flow, such installation can be effectively improved the radiating efficiency of electron speed regulator, also makes its work imitate
Rate increases.Flight controller according to the state of flight of Inertial Measurement Unit perception aircraft, and can pass through electron speed regulator
Change the rotating speed of propeller, thus obtain the active force changing attitude, control the flight of aircraft with this.
According to the teaching of the present embodiment, those skilled in the art can realize in other scope completely
Technical scheme.
Claims (8)
1. a multi-rotor aerocraft, including the machine being made up of flight controller, wireless remote controlled receiver and power transfer module
Body；The rotor assemblies that the propeller by motor, being installed on machine shaft and the electron speed regulator being connected with motor form；With described
The frame that body and rotor assemblies connect；It is characterized in that: described frame is by two longitudinal horns and two horizontal horns intersection structures
Become groined type；The mounting seat of described motor is located at described longitudinal horn and the infall of horizontal horn；Described groined type frame
Periphery is provided with the guard circle that the protection easily worn part surrounded by hollow cylinder PE Foam is clashed into.
2. multi-rotor aerocraft as claimed in claim 1, is characterized in that: described horn is by carbon fiber board or hollow carbon fiber pipe
Constitute.
3. multi-rotor aerocraft as claimed in claim 1, is characterized in that: described propeller is positioned at below described motor.
4. multi-rotor aerocraft as claimed in claim 1, is characterized in that: described propeller is SANYE oar.
5. multi-rotor aerocraft as claimed in claim 1, is characterized in that: described electron speed regulator is arranged on horn neighbouring electricity
At the mounting seat of machine.
6. multi-rotor aerocraft as claimed in claim 1, is characterized in that: flight controller includes three axles for attitude measurement
Acceierometer sensor and three-axis gyroscope sensor, for processing the single-chip microcomputer of flying quality and for performing control command
Single-chip microcomputer and three axle geomagnetic sensors.
7. multi-rotor aerocraft as claimed in claim 1, is characterized in that: described body be shaped as rectangle box body；Described
On the outer wall of the dead ahead that power transfer module is located at this box body.
8. multi-rotor aerocraft as claimed in claim 7, is characterized in that: described body also includes being located at the dead astern of box body
LED light on outer wall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620727504.8U CN205801533U (en) | 2016-07-12 | 2016-07-12 | A kind of multi-rotor aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620727504.8U CN205801533U (en) | 2016-07-12 | 2016-07-12 | A kind of multi-rotor aerocraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205801533U true CN205801533U (en) | 2016-12-14 |
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ID=57510716
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620727504.8U Active CN205801533U (en) | 2016-07-12 | 2016-07-12 | A kind of multi-rotor aerocraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205801533U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109110139A (en) * | 2018-09-07 | 2019-01-01 | 佛山皖和新能源科技有限公司 | A kind of novel unmanned plane auxiliary lifting device |
-
2016
- 2016-07-12 CN CN201620727504.8U patent/CN205801533U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109110139A (en) * | 2018-09-07 | 2019-01-01 | 佛山皖和新能源科技有限公司 | A kind of novel unmanned plane auxiliary lifting device |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |